Nuclear Weapons: The Reliable Replacement Warhead Program

DTIC Science & Technology

2006-03-09

time to age. The United States introduced generation after generation of new nuclear “delivery vehicles ” — bombers, missile submarines, and land-based...missile’s carrying capacity divided among fewer warheads, each CRS-13 29 Ballistic missiles carry warheads inside reentry vehicles (RVs). An RV is a...streamlined shell that protects its warhead from the intense heat and other stresses of reentering the atmosphere at high speed. RVs are designed to carry a

Automatic rapid attachable warhead section

DOEpatents

Trennel, A.J.

1994-05-10

Disclosed are a method and apparatus for automatically selecting warheads or reentry vehicles from a storage area containing a plurality of types of warheads or reentry vehicles, automatically selecting weapon carriers from a storage area containing at least one type of weapon carrier, manipulating and aligning the selected warheads or reentry vehicles and weapon carriers, and automatically coupling the warheads or reentry vehicles with the weapon carriers such that coupling of improperly selected warheads or reentry vehicles with weapon carriers is inhibited. Such inhibition enhances safety of operations and is achieved by a number of means including computer control of the process of selection and coupling and use of connectorless interfaces capable of assuring that improperly selected items will be rejected or rendered inoperable prior to coupling. Also disclosed are a method and apparatus wherein the stated principles pertaining to selection, coupling and inhibition are extended to apply to any item-to-be-carried and any carrying assembly. 10 figures.

Automatic rapid attachable warhead section

DOEpatents

Trennel, Anthony J.

1994-05-10

Disclosed are a method and apparatus for (1) automatically selecting warheads or reentry vehicles from a storage area containing a plurality of types of warheads or reentry vehicles, (2) automatically selecting weapon carriers from a storage area containing at least one type of weapon carrier, (3) manipulating and aligning the selected warheads or reentry vehicles and weapon carriers, and (4) automatically coupling the warheads or reentry vehicles with the weapon carriers such that coupling of improperly selected warheads or reentry vehicles with weapon carriers is inhibited. Such inhibition enhances safety of operations and is achieved by a number of means including computer control of the process of selection and coupling and use of connectorless interfaces capable of assuring that improperly selected items will be rejected or rendered inoperable prior to coupling. Also disclosed are a method and apparatus wherein the stated principles pertaining to selection, coupling and inhibition are extended to apply to any item-to-be-carried and any carrying assembly.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Norris, R.S.; Arkin, W.M.

The US. nuclear stockpile is at its lowest level since late 1958 or early 1959. In the past year, many weapons were returned to central military storage depots in the United States and funneled to the Energy Department's Pantex facility for final disassembly and disposal. This article presents a table showing the author's current estimate of the composition of the current operational stockpile, which contains some 10,500 warheads. Also categorized are warheads in [open quotes]inactive reserve[close quotes] and warheads awaiting eventual disassembly. The warheads are generally grouped as bombs, submarine-launched ballistic missiles, intercontinental ballistic missiles, air-launched cruise missiles, and sea-launchedmore » cruise missiles. Initial production dates and yield are listed for the warheads.« less

Experimental demonstration of an isotope-sensitive warhead verification technique using nuclear resonance fluorescence.

PubMed

Vavrek, Jayson R; Henderson, Brian S; Danagoulian, Areg

2018-04-24

Future nuclear arms reduction efforts will require technologies to verify that warheads slated for dismantlement are authentic without revealing any sensitive weapons design information to international inspectors. Despite several decades of research, no technology has met these requirements simultaneously. Recent work by Kemp et al. [Kemp RS, Danagoulian A, Macdonald RR, Vavrek JR (2016) Proc Natl Acad Sci USA 113:8618-8623] has produced a novel physical cryptographic verification protocol that approaches this treaty verification problem by exploiting the isotope-specific nature of nuclear resonance fluorescence (NRF) measurements to verify the authenticity of a warhead. To protect sensitive information, the NRF signal from the warhead is convolved with that of an encryption foil that contains key warhead isotopes in amounts unknown to the inspector. The convolved spectrum from a candidate warhead is statistically compared against that from an authenticated template warhead to determine whether the candidate itself is authentic. Here we report on recent proof-of-concept warhead verification experiments conducted at the Massachusetts Institute of Technology. Using high-purity germanium (HPGe) detectors, we measured NRF spectra from the interrogation of proxy "genuine" and "hoax" objects by a 2.52 MeV endpoint bremsstrahlung beam. The observed differences in NRF intensities near 2.2 MeV indicate that the physical cryptographic protocol can distinguish between proxy genuine and hoax objects with high confidence in realistic measurement times.

Behavior Characteristics of Type I (75/25) Octol during Melt Pouring HE Warhead M250 (Chaparral)

DTIC Science & Technology

1979-09-01

COVERED BEHAVIOR CHARACTERISTICS OF TYPE 1 (75/25) "OCTOL DURING MELT POURING HE WARHEAD I M250 (CHAPARRAL) 6. PERFORMING ORG. APrPORT NUMBER 7. AUTHOR...Military Specification, HMX, MIL-H-45444B, Amendment 2, dated 12 July 1977. 4 6. Military Specification, Warhead, Guided Missile, HE, M250 , Loading...CHARACTERISTICS OF TYPE i (75/25) OCTOL DURING MELT POURING HE WARHEAD M250 (CHAPARRAL) HERMAN J. FRIGAND SEPTEMBER 1979 US ARMY ARMAMENT RESEARCH AND

50th Annual Fuze Conference Session 5

DTIC Science & Technology

2006-05-11

level •Underwater Shock NDIA Fuze Conf 2006 5 Warhead Lethality MOFN has two potential warheads EX 183 HE-MOFN •MK 64 PROJECTILE BODY • PBXN - 106 ...EXPLOSIVE FILL EX 184 HE-MOFN •HIFRAG PROJECTILE BODY • PBXN - 106 EXPLOSIVE FILL Warhead lethality effect is fragmentation NDIA Fuze Conf 2006 6 Warhead...NDIA Fuze Conf 2006 19 Min Engagement Hazard • Worst Case Operational Configuration: – Projectile = EX 184 HE-MOFN • MK 64 Projectile w PBXN - 106 fill

Survivability of the Hardened Mobile Launcher When Attacked by a Hypothetical Rapidly Retargetable ICBM System.

DTIC Science & Technology

1986-03-01

Aimpoints 22 Overviev 22 Random Movement of the RML 23 Computing Burst Locations and the HMIL’s Final Location 23 Selecting the HIMLs Speed. 29...described threat. The actual model used in this study is an MEASIC computer program . written and run on an Apple Macintosh computer . It is described in...mechanics of the computer program that models the warheads’ flight time sequence, it will be helpful to explain some of the elements of the sequence

Experimental demonstration of an isotope-sensitive warhead verification technique using nuclear resonance fluorescence

DOE Office of Scientific and Technical Information (OSTI.GOV)

Vavrek, Jayson R.; Henderson, Brian S.; Danagoulian, Areg

Future nuclear arms reduction efforts will require technologies to verify that warheads slated for dismantlement are authentic without revealing any sensitive weapons design information to international inspectors. Despite several decades of research, no technology has met these requirements simultaneously. Recent work by Kemp et al. [Kemp RS, Danagoulian A, Macdonald RR, Vavrek JR (2016) Proc Natl Acad Sci USA 113:8618–8623] has produced a novel physical cryptographic verification protocol that approaches this treaty verification problem by exploiting the isotope-specific nature of nuclear resonance fluorescence (NRF) measurements to verify the authenticity of a warhead. To protect sensitive information, the NRF signal frommore » the warhead is convolved with that of an encryption foil that contains key warhead isotopes in amounts unknown to the inspector. The convolved spectrum from a candidate warhead is statistically compared against that from an authenticated template warhead to determine whether the candidate itself is authentic. Here in this paper we report on recent proof-of-concept warhead verification experiments conducted at the Massachusetts Institute of Technology. Using high-purity germanium (HPGe) detectors, we measured NRF spectra from the interrogation of proxy “genuine” and “hoax” objects by a 2.52 MeV endpoint bremsstrahlung beam. The observed differences in NRF intensities near 2.2 MeV indicate that the physical cryptographic protocol can distinguish between proxy genuine and hoax objects with high confidence in realistic measurement times.« less

Experimental demonstration of an isotope-sensitive warhead verification technique using nuclear resonance fluorescence

DOE PAGES

Vavrek, Jayson R.; Henderson, Brian S.; Danagoulian, Areg

2018-04-10

Future nuclear arms reduction efforts will require technologies to verify that warheads slated for dismantlement are authentic without revealing any sensitive weapons design information to international inspectors. Despite several decades of research, no technology has met these requirements simultaneously. Recent work by Kemp et al. [Kemp RS, Danagoulian A, Macdonald RR, Vavrek JR (2016) Proc Natl Acad Sci USA 113:8618–8623] has produced a novel physical cryptographic verification protocol that approaches this treaty verification problem by exploiting the isotope-specific nature of nuclear resonance fluorescence (NRF) measurements to verify the authenticity of a warhead. To protect sensitive information, the NRF signal frommore » the warhead is convolved with that of an encryption foil that contains key warhead isotopes in amounts unknown to the inspector. The convolved spectrum from a candidate warhead is statistically compared against that from an authenticated template warhead to determine whether the candidate itself is authentic. Here in this paper we report on recent proof-of-concept warhead verification experiments conducted at the Massachusetts Institute of Technology. Using high-purity germanium (HPGe) detectors, we measured NRF spectra from the interrogation of proxy “genuine” and “hoax” objects by a 2.52 MeV endpoint bremsstrahlung beam. The observed differences in NRF intensities near 2.2 MeV indicate that the physical cryptographic protocol can distinguish between proxy genuine and hoax objects with high confidence in realistic measurement times.« less

MILITARY RESEARCH: Researchers Target Flaws in Ballistic Missile Defense Plan.

PubMed

Malakoff, D; Cho, A

2000-06-16

More than three dozen scientists journeyed to Washington, D.C., this week to warn lawmakers that a proposed $60 billion U.S. missile defense system, designed to knock incoming warheads out of the sky, is technically flawed because it can't pick out real warheads from decoys. Pentagon officials heatedly deny a new report by one scientist that contractors have rigged trials to hide the problem, although they admit that some tests were simplified to save time. In the wake of these events, a leading Democrat is urging President Bill Clinton to delay a pending decision on building the system.

The Future of the U.S. Nuclear Weapons Program

NASA Astrophysics Data System (ADS)

Brooks, Linton F.

2007-03-01

This paper will examine our plans for the future of the U.S. nuclear weapons program including efforts to ``transform'' the stockpile and supporting infrastructure. We proceed from the premise that the United States will need a safe, secure, and reliable nuclear deterrent for the foreseeable future. Moreover, the Stockpile Stewardship Program is working. Today's stockpile---comprised of legacy warheads left over from the Cold War---is safe and reliable. That said, we see increased risk, absent nuclear testing, in assuring the long-term safety and reliability of our current stockpile. Nor is today's nuclear weapons complex sufficiently ``responsive'' to fixing technical problems in the stockpile, or to potential adverse geopolitical change. Our task is to work to ensure that the U.S. nuclear weapons enterprise, including the stockpile and supporting infrastructure, meets long-term national security needs. Our approach is to develop and field replacement warheads for the legacy stockpile---so-called Reliable Replacement Warheads (RRW)---as a means to transform both the nuclear stockpile and supporting infrastructure.

Warhead Confirmation: A Follow-on to New START

DOE Office of Scientific and Technical Information (OSTI.GOV)

MacArthur, Duncan W.

This presentation's slides are comprised of the following: Warhead Confirmation: A Follow-on to New START; What May Change?; Generic Arms Reduction Treaty; Challenges; Dismantlement and Warhead Confirmation; Confirmation Approaches; Certification; Information Barriers (IBs); The Fissile Material Transparency Technology Demonstration (FMTTD); More Recent Implementations; The Monitor’s View; Authentication; Authentication Options; Authentication in Phases; and Future Treaties.

Shock sensing dual mode warhead

DOE Office of Scientific and Technical Information (OSTI.GOV)

Shamblen, M.; Walchak, M.T.; Richmond, L.

1980-12-31

A shock sensing dual mode warhead is provided for use against both soft and hard targets and is capable of sensing which type of target has been struck. The warhead comprises a casing made of a ductile material containing an explosive charge and a fuze assembly. The ductile warhead casing will mushroom upon striking a hard target while still confining the explosive. Proper ductility and confinement are necessary for fuze shock sensing. The fuze assembly contains a pair of parallel firing trains, one initiated only by dynamic pressure caused high impact deceleration and one initiated by low impact deceleration. Themore » firing train actuated by high impact deceleration senses dynamic pressure transmitted, during deformation of the warhead, through the explosive filler which is employed as a fuzing signature. The firing train actuated by low impact deceleration contains a pyrotechnic delay to allow penetration of soft targets.« less

View from southwest to northeast of warhead handling building. Note ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

View from southwest to northeast of warhead handling building. Note earth embankment. The personnel entrance (left) and equipment entrance can clearly be seen in center of photograph. To the right is the emergency exit tunnel constructed of corrugated metal pipe. This building was salvaged and sealed after site inactivation - Stanley R. Mickelsen Safeguard Complex, Warhead Handling Building, Within Exclusion Area, Nekoma, Cavalier County, ND

Fiscal Year 2012 United States Air Force Agency Financial Report

DTIC Science & Technology

2012-01-01

Air Force Research Laboratory (AFRL) and Lawrence Livermore National Laboratory (LLNL) aggressively designed and tested an advanced warhead to...Reaper procurement & RPA capabilities, Light Attack Armed Reconnaissance buys, Joint Strike Fighter, satellites). Research , Development, Test and...Military Personnel Operations, Readiness & Support Procurement Research , Development, Test & Evaluation

Plant Equipment Packages: Are they a Credible Deterrent to War

DTIC Science & Technology

1990-12-01

PEP# TYPE CONTRACTOR/FACILITY NAME LOCATION 0112 WARHEAD CHAPARRAL M250 0112 WARHEAD HELFIRE MISSILE SYSTEM 0112 WARHEAD HE M225 LAP (DRAGON) 0112...0149 GRENADE SMK SCRN RP UKL8A3 F/ M250 LAUNCHER 0149 ROCKET 66MM INCEND TPA 4RD CLIP M74 0149 WARHEAD RKT 2.75IN SMK WP M156 W/FZ PD M427 0149 ROCKET...M25A2 (COMPLETE) 0149 GRENADE HAND/RIFLE SMK WP M34 W/F M206A2. 0149 GRENADE HAND RIOT CS ABC-M7A3 W/FZ M201AI 0149 GRENADE SMK SCRN RP UKL8A3 F/ M250

A zero-knowledge protocol for nuclear warhead verification

NASA Astrophysics Data System (ADS)

Glaser, Alexander; Barak, Boaz; Goldston, Robert J.

2014-06-01

The verification of nuclear warheads for arms control involves a paradox: international inspectors will have to gain high confidence in the authenticity of submitted items while learning nothing about them. Proposed inspection systems featuring `information barriers', designed to hide measurements stored in electronic systems, are at risk of tampering and snooping. Here we show the viability of a fundamentally new approach to nuclear warhead verification that incorporates a zero-knowledge protocol, which is designed in such a way that sensitive information is never measured and so does not need to be hidden. We interrogate submitted items with energetic neutrons, making, in effect, differential measurements of both neutron transmission and emission. Calculations for scenarios in which material is diverted from a test object show that a high degree of discrimination can be achieved while revealing zero information. Our ideas for a physical zero-knowledge system could have applications beyond the context of nuclear disarmament. The proposed technique suggests a way to perform comparisons or computations on personal or confidential data without measuring the data in the first place.

Nuclear Weapons: The Reliable Replacement Warhead Program

DTIC Science & Technology

2005-07-20

time to age. The United States introduced generation after generation of new nuclear “delivery vehicles ” — bombers, missile submarines, and land...less constrained in weight because bombers carry heavier loads than missiles. 26 Ballistic missiles carry warheads inside reentry vehicles (RVs). An...RV is a streamlined shell that protects its warhead from the intense heat and other stresses of reentering the atmosphere at high speed. RVs are

Unmaking the bomb: Verifying limits on the stockpiles of nuclear weapons

NASA Astrophysics Data System (ADS)

Glaser, Alexander

2017-11-01

Verifying limits on the stockpiles of nuclear weapons may require the ability for international in-spectors to account for individual warheads, even when non-deployed, and to confirm the authenticity of nuclear warheads prior to dismantlement. These are fundamentally new challenges for nuclear verification, and they have been known for some time; unfortunately, due to a lack of sense of urgency, research in this area has not made substantial progress over the past 20 years. This chapter explores the central outstanding issues and offers a number of possible paths forward. In the case of confirming numerical limits, these in-clude innovative tagging techniques and approaches solely based on declarations using modern crypto-graphic escrow schemes; with regard to warhead confirmation, there has recently been increasing interest in developing fundamentally new measurement approaches where, in one form or another, sensitive infor-mation is not acquired in the first place. Overall, new international R&D efforts could more usefully focus on non-intrusive technologies and approaches, which may show more promise for early demonstration and adoption. In the meantime, while warhead dismantlements remain unverified, nuclear weapon states ought to begin to document warhead assembly, refurbishment, and dismantlement activities and movements of warheads and warhead components through the weapons complex in ways that international inspectors will find credible at a later time. Again, such a process could be enabled by modern cryptographic techniques such as blockchaining. Finally, and perhaps most importantly, it is important to recognize that the main reason for the complexity of technologies and approaches needed for nuclear disarmament verification is the requirement to protect information that nuclear weapon states consider sensitive. Ultimately, if information security concerns cannot be resolved to the satisfaction of all stakeholders, an alternative would be to "reveal the secret" and to make available select warhead design information.

Secure Image Hash Comparison for Warhead Verification

DOE Office of Scientific and Technical Information (OSTI.GOV)

Bruillard, Paul J.; Jarman, Kenneth D.; Robinson, Sean M.

2014-06-06

The effort to inspect and verify warheads in the context of possible future arms control treaties is rife with security and implementation issues. In this paper we review prior work on perceptual image hashing for template-based warhead verification. Furthermore, we formalize the notion of perceptual hashes and demonstrate that large classes of such functions are likely not cryptographically secure. We close with a brief discussion of fully homomorphic encryption as an alternative technique.

Precession feature extraction of ballistic missile warhead with high velocity

NASA Astrophysics Data System (ADS)

Sun, Huixia

2018-04-01

This paper establishes the precession model of ballistic missile warhead, and derives the formulas of micro-Doppler frequency induced by the target with precession. In order to obtain micro-Doppler feature of ballistic missile warhead with precession, micro-Doppler bandwidth estimation algorithm, which avoids velocity compensation, is presented based on high-resolution time-frequency transform. The results of computer simulations confirm the effectiveness of the proposed method even with low signal-to-noise ratio.

Scope Complexity Options Risks Excursions (SCORE) Version 3.0 Mathematical Description.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Gearhart, Jared Lee; Samberson, Jonell Nicole; Shettigar, Subhasini

The purpose of the Scope, Complexity, Options, Risks, Excursions (SCORE) model is to estimate the relative complexity of design variants of future warhead options. The results of this model allow those considering these options to understand the complexity tradeoffs between proposed warhead options. The core idea of SCORE is to divide a warhead option into a well- defined set of scope elements and then estimate the complexity of each scope element against a well understood reference system. The uncertainty associated with estimates can also be captured. A weighted summation of the relative complexity of each scope element is used tomore » determine the total complexity of the proposed warhead option or portions of the warhead option (i.e., a National Work Breakdown Structure code). The SCORE analysis process is a growing multi-organizational Nuclear Security Enterprise (NSE) effort, under the management of the NA- 12 led Enterprise Modeling and Analysis Consortium (EMAC), that has provided the data elicitation, integration and computation needed to support the out-year Life Extension Program (LEP) cost estimates included in the Stockpile Stewardship Management Plan (SSMP).« less

Physics and technology of the arms race

NASA Astrophysics Data System (ADS)

Garwin, R. L.

1983-10-01

Traditional military concepts of superiority and effectiveness (as embodied in Lanchester's law) have little relevance to thermonuclear weapons, with their enormous effectiveness in destruction of society. Few are needed to saturate their deterrent effect, but their military effectiveness is limited. The evolution and future of strategic nuclear forces is discussed, and their declining marginal utility emphasized. Some calculatons relevant to the nuclear confrontation are presented (Lanchester's Law; skin effect of VLF and ELF signals to submarines; the rocket equation; simple radar-range equation) and recommendations presented for future strategic forces and arms control initiatives. Recommended programs include a silo-based 12-ton single-warhead missile (SICM), the development of buried-bomb defense of individual Minuteman silos, the completion of the deployment of air-launched cruise missiles on the B-52 fleet, and the development of small (1000-ton) submarines for basing ICBM-range missiles. Limiting the threat by arms control should include ratification of SALT II, followed by negotiation of a protrocool to allow a SICM and dedicated silo to be deployed for each two, SALT-II-allowed warheads given up; a ban on weapons in space and anti-satellite tests; and an eventual reduction to 1000 nuclear warheads in U.S. and Soviet inventories.

Test Area C-64 Range Environmental Assessment, Revision 1

DTIC Science & Technology

2010-10-01

DOI U.S. Department of the Interior DNL Day–Night Average Sound Level DU Depleted Uranium EBD Environmental Baseline Document EIAP Environmental...vulnerability, burning sensitivity, drop tests, bullet impact tests, sympathetic detonation tests, advanced warhead design tests, and depleted uranium (DU...land back to range use. Source: U.S. Air Force, 2009 DU = depleted uranium ; ERP = Environmental Restoration Program; LUC = land use control; RW

High-Velocity Impact Fragmentation of Projectiles Experimental Results

DTIC Science & Technology

2016-10-01

Program (JIMTP) Tube -Launched, Optically Tracked, Wire-Guided (TOW) 2B Insensitive Munitions (IM) Warhead effort. The referenced experiments were...conducted to determine the velocity reduction and fragmentation profile of barrier materials subjected to impact by the IM Fragment Impact (FI) test...9 LIST OF TABLES Table Title Page 1. Single Material Test Matrix

Department of Defense In-House RDT and E Activities

DTIC Science & Technology

1976-10-30

BALLISTIC TESTS.FAC AVAL FCR TESIS OF SP ELELTRONIC’ FIl’ CON EQUIP 4 RELATED SYSTEMS E COMPONFNTZ, 35 INSTALLATION: MEDICAL BIOENGINEERINC- R&D LABORATORY...ANALYSIS OF CHEMICAL AND METALLOGRAPHIC EFFECTS, MICROBIOLOGICAL EFFECTS, CLIMATIC ENVIRONMENTAL EFFECTS. TEST AND EVALUATE WARHEADS AND SPECIAL...CCMMUNICATI’N SYST:M INSTRUMENTED DROP ZONES ENGINEERING TEST FACILITY INSTRUMENTATION CALIBRATICN FACILITY SCIENTIFIC COMPUTER CENTER ENVIRONMENTAL TESY

Simulation Study on Jet Formability and Damage Characteristics of a Low-Density Material Liner

PubMed Central

Tang, Wenhui; Ran, Xianwen

2018-01-01

The shaped charge tandem warhead is an effective weapon against the ERA (explosive reactive armor). Whether the pre-warhead can reliably initiate the ERA directly determines the entire performance of the tandem warhead. The existing shaped charge pre-warhead mostly adopts a metal shaped jet, which effectively initiates the ERA, but interferes the main shaped jet. This article, on the other hand, explores the possibility of producing a pre-warhead using a low-density material as the liner. The nonlinear dynamic analysis software Autodyn-2D is used to simulate and compare three kinds of low-density shaped jets, including floatglass, Lucite, and Plexiglas, to the copper shaped jet in the effectiveness of impacting ERA. Based on the integrative criteria (including u-d initiation criterion, explosive reactive degree, explosive pressure, and particle velocity of the panels), it can be determined whether the low-density shaped jet can reliably initiate the sandwich charge. The results show that the three kinds of low-density shaped jets can not only initiate the reaction armor, but are also superior to the existing copper shaped jet in ductility, jet tip velocity, jet tip diameter, and the mass; namely, it is feasible to use the low-density material shaped jet to destroy the ERA. PMID:29300351

Mechanical Analysis of W78/88-1 Life Extension Program Warhead Design Options

DOE Office of Scientific and Technical Information (OSTI.GOV)

Spencer, Nathan

2014-09-01

Life Extension Program (LEP) is a program to repair/replace components of nuclear weapons to ensure the ability to meet military requirements. The W78/88-1 LEP encompasses the modernization of two major nuclear weapon reentry systems into an interoperable warhead. Several design concepts exist to provide different options for robust safety and security themes, maximum non-nuclear commonality, and cost. Simulation is one capability used to evaluate the mechanical performance of the designs in various operational environments, plan for system and component qualification efforts, and provide insight into the survivability of the warhead in environments that are not currently testable. The simulation effortsmore » use several Sandia-developed tools through the Advanced Simulation and Computing program, including Cubit for mesh generation, the DART Model Manager, SIERRA codes running on the HPC TLCC2 platforms, DAKOTA, and ParaView. Several programmatic objectives were met using the simulation capability including: (1) providing early environmental specification estimates that may be used by component designers to understand the severity of the loads their components will need to survive, (2) providing guidance for load levels and configurations for subassembly tests intended to represent operational environments, and (3) recommending design options including modified geometry and material properties. These objectives were accomplished through regular interactions with component, system, and test engineers while using the laboratory's computational infrastructure to effectively perform ensembles of simulations. Because NNSA has decided to defer the LEP program, simulation results are being documented and models are being archived for future reference. However, some advanced and exploratory efforts will continue to mature key technologies, using the results from these and ongoing simulations for design insights, test planning, and model validation.« less

Strategic Studies Quarterly- Spring 2016

DTIC Science & Technology

2016-01-01

under one treaty or another. Advocates promoted the 1963 Partial Test Ban Treaty as a stabilizing agreement that would restrict nuclear tests to the...revealed missile and warhead performance in testing -even questioning whether the Soviets were providing false information on open transmission...liferator might use one or more weapons coercively, irresponsibly, or accidentally. It could hand a nuclear weapon off to a terrorist group , or it could

DOE Office of Scientific and Technical Information (OSTI.GOV)

Reynolds, Adam F.; Steinfeldt, Bradley Alexander; Lafleur, Jarret Marshall

The U.S. nuclear stockpile hedge is an inventory of non-deployed nuclear warheads and a force structure capable of deploying those warheads. Current guidance is to retain this hedge to mitigate the risk associated with the technical failure of any single warhead type or adverse geopolitical developments that could require augmentation of the force. The necessary size of the hedge depends on the composition of the nuclear stockpile and assumed constraints. Knowing the theoretical minimum hedge given certain constraints is useful when considering future weapons policy. HedgeHOGS, an Excel-based tool, was developed to enable rapid calculation of the minimum hedge sizemore » associated with varying active stockpile composition and hedging strategies.« less

Dual mode warhead

DOE Office of Scientific and Technical Information (OSTI.GOV)

Obrsky, J.; Alexander, A.A.; Griffen, O.H.

1980-12-31

A dual mode warhead is provided for use against both soft and hard targets and capable of sensing which type of target has been struck comprising a casing made of a ductile material containing an explosive charge and a fuze assembly. The ductile warhead casing will mushroom and later split upon striking a hard target while still confining the explosive. Proper ductility and confinement are necessary for fuze sensing. The fuze assembly contains a pair of parallel firing trains, one initiated only by high and one by low impact deceleration. The firing train actuated by low impact deceleration contains amore » pyrotechnic delay to allow penetration of soft targets.« less

Signature analysis of ballistic missile warhead with micro-nutation in terahertz band

NASA Astrophysics Data System (ADS)

Li, Ming; Jiang, Yue-song

2013-08-01

In recent years, the micro-Doppler effect has been proposed as a new technique for signature analysis and extraction of radar targets. The ballistic missile is known as a typical radar target and has been paid many attentions for the complexities of its motions in current researches. The trajectory of a ballistic missile can be generally divided into three stages: boost phase, midcourse phase and terminal phase. The midcourse phase is the most important phase for radar target recognition and interception. In this stage, the warhead forms a typical micro-motion called micro-nutation which consists of three basic micro-motions: spinning, coning and wiggle. This paper addresses the issue of signature analysis of ballistic missile warhead in terahertz band via discussing the micro-Doppler effect. We establish a simplified model (cone-shaped) for the missile warhead followed by the micro-motion models including of spinning, coning and wiggle. Based on the basic formulas of these typical micro-motions, we first derive the theoretical formula of micro-nutation which is the main micro-motion of the missile warhead. Then, we calculate the micro-Doppler frequency in both X band and terahertz band via these micro-Doppler formulas. The simulations are given to show the superiority of our proposed method for the recognition and detection of radar micro targets in terahertz band.

Verification Challenges at Low Numbers

DOE Office of Scientific and Technical Information (OSTI.GOV)

Benz, Jacob M.; Booker, Paul M.; McDonald, Benjamin S.

2013-06-01

Many papers have dealt with the political difficulties and ramifications of deep nuclear arms reductions, and the issues of “Going to Zero”. Political issues include extended deterrence, conventional weapons, ballistic missile defense, and regional and geo-political security issues. At each step on the road to low numbers, the verification required to ensure compliance of all parties will increase significantly. Looking post New START, the next step will likely include warhead limits in the neighborhood of 1000 . Further reductions will include stepping stones at1000 warheads, 100’s of warheads, and then 10’s of warheads before final elimination could be considered ofmore » the last few remaining warheads and weapons. This paper will focus on these three threshold reduction levels, 1000, 100’s, 10’s. For each, the issues and challenges will be discussed, potential solutions will be identified, and the verification technologies and chain of custody measures that address these solutions will be surveyed. It is important to note that many of the issues that need to be addressed have no current solution. In these cases, the paper will explore new or novel technologies that could be applied. These technologies will draw from the research and development that is ongoing throughout the national laboratory complex, and will look at technologies utilized in other areas of industry for their application to arms control verification.« less

Comprehensive Nuclear-Test-Ban Treaty: Background and Current Developments

DTIC Science & Technology

2009-11-23

there are no plans to do so.’”5 Critics expressed concern about the implications of these policies for testing and new weapons. A statement by...opportunity to design and build new nuclear weapons, and abandon a ten-year-old moratorium on nuclear weapons testing.”6 Another critic felt that increased...cannot diagnose or remedy a problem in a warhead critical the U.S. nuclear deterrent without conducting a nuclear test.10 Similarly, a Statement of

Comprehensive Nuclear-Test-Ban Treaty: Background and Current Developments

DTIC Science & Technology

2010-01-06

the future, but there are no plans to do so.’”5 Critics expressed concern about the implications of these policies for testing and new weapons. A...seek the opportunity to design and build new nuclear weapons, and abandon a ten-year-old moratorium on nuclear weapons testing.”6 Another critic felt...warhead critical the U.S. nuclear deterrent without conducting a nuclear test.10 Similarly, a Statement of Administration Policy on S. 1547, FY2008

A Study on: Exploring U.S. Missile Defense Requirements in 2010: What Are the Policy and Technology Challenges?

DTIC Science & Technology

1997-04-01

technology matures. Mid-course phase Warhead & Booster ■’-=>- penaid deployment burnout v y...phase Warhead & Booster _^, penaid deployment burnout v y^ complete...and penaids fit so equippec I) are deployed immediately following boost phase burnout . • Large deceleration occurs from atmospheric drag upon re

Central Asia in Context: Local Rules of the Great Game

DTIC Science & Technology

2013-05-23

warheads to Russia by 1995, and dismantled the testing facility at Semipalatinsk by 2000. Likewise, they participated with the United States in PROJECT...to take small steps to test the reaction of the new international system, in order to develop more coherent long-term strategies. As Lena Jonson...between the variables.31 If certain variables are missing, or other extraneous variables are present, the researcher can conduct other tests to consider

Comprehensive Nuclear-Test-Ban Treaty: Background and Current Developments

DTIC Science & Technology

2009-01-28

safe. So he has not ruled out testing in the future, but there are no plans to do so.’”5 Critics expressed concern about the implications of these...nuclear weapons testing.”6 Another critic felt that increased funding for test readiness would in effect give prior approval for testing. In July 2002 a...moratorium. We may find at some future time that we cannot diagnose or remedy a problem in a warhead critical the U.S. nuclear deterrent without

DIVWAG Model Documentation. Volume II. Programmer/Analyst Manual. Part 6.

DTIC Science & Technology

1976-07-01

Routine IALFA BARUPE BARU REDCLK none MOVEDT MVDT NFIRE NFRE MINGET none MVPATH MVPT NCUNIT NCUN XXIT none OVER13 none BAMUNT BAMU RANDU none SUPRES SUPS... NFIRE : 802 THE REQUESTED WEAPON OR WARHEAD IS NOT AVAILABLE The unit that was ordered to fire the nuclear round does not have the weapon or warhead in

A new method of passive counting of nuclear missile warheads -a white paper for the Defense Threat Reduction Agency

DOE Office of Scientific and Technical Information (OSTI.GOV)

Morris, Christopher; Durham, J. Matthew; Guardincerri, Elena

Cosmic ray muon imaging has been studied for the past several years as a possible technique for nuclear warhead inspection and verification as part of the New Strategic Arms Reduction Treaty between the United States and the Russian Federation. The Los Alamos team has studied two different muon imaging methods for this application, using detectors on two sides and one side of the object of interest. In this report we present results obtained on single sided imaging of configurations aimed at demonstrating the potential of this technique for counting nuclear warheads in place with detectors above the closed hatch ofmore » a ballistic missile submarine.« less

A fast recognition method of warhead target in boost phase using kinematic features

NASA Astrophysics Data System (ADS)

Chen, Jian; Xu, Shiyou; Tian, Biao; Wu, Jianhua; Chen, Zengping

2015-12-01

The radar targets number increases from one to more when the ballistic missile is in the process of separating the lower stage rocket or casting covers or other components. It is vital to identify the warhead target quickly among these multiple targets for radar tracking. A fast recognition method of the warhead target is proposed to solve this problem by using kinematic features, utilizing fuzzy comprehensive method and information fusion method. In order to weaken the influence of radar measurement noise, an extended Kalman filter with constant jerk model (CJEKF) is applied to obtain more accurate target's motion information. The simulation shows the validity of the algorithm and the effects of the radar measurement precision upon the algorithm's performance.

Verification Challenges at Low Numbers

DOE Office of Scientific and Technical Information (OSTI.GOV)

Benz, Jacob M.; Booker, Paul M.; McDonald, Benjamin S.

2013-07-16

This paper will explore the difficulties of deep reductions by examining the technical verification challenges. At each step on the road to low numbers, the verification required to ensure compliance of all parties will increase significantly. Looking post New START, the next step will likely include warhead limits in the neighborhood of 1000 (Pifer 2010). Further reductions will include stepping stones at 100’s of warheads, and then 10’s of warheads before final elimination could be considered of the last few remaining warheads and weapons. This paper will focus on these three threshold reduction levels, 1000, 100’s, 10’s. For each, themore » issues and challenges will be discussed, potential solutions will be identified, and the verification technologies and chain of custody measures that address these solutions will be surveyed. It is important to note that many of the issues that need to be addressed have no current solution. In these cases, the paper will explore new or novel technologies that could be applied. These technologies will draw from the research and development that is ongoing throughout the national lab complex, and will look at technologies utilized in other areas of industry for their application to arms control verification.« less

Millimeter wave radars raise weapon IQ

NASA Astrophysics Data System (ADS)

Lerner, E. J.

1985-02-01

The problems encountered by laser and IR homing devices for guided munitions may be tractable with warhead-mounted mm-wave radars. Operating at about 100 GHz and having several kilometers range, mm-wave radars see through darkness, fog, rain and smoke. The radar must be coupled with an analyzer that discerns moving and stationary targets and higher priority targets. The target lock-on can include shut-off of the transmitter and reception of naturally-generated mm-waves bouncing off the target when in the terminal phase of the flight. Monopulse transmitters have simplified the radar design, although mass production of finline small radar units has yet to be accomplished, particularly in combining GaAs, ferrites and other materials on one monolithic chip.

Comprehensive Nuclear-Test-Ban Treaty: Background and Current Developments

DTIC Science & Technology

2010-12-07

there are no plans to do so.’”4 Critics expressed concern about the implications of these policies for testing and new weapons. Physicians for...design and build new nuclear weapons, and abandon a ten-year-old moratorium on nuclear weapons testing.”5 Another critic felt that increased funding for...guarantees regarding the voluntary moratorium. We may find at some future time that we cannot diagnose or remedy a problem in a warhead critical the U.S

HIBAL Program. Preliminary Warhead-Design. Volume II. Appendices.

DTIC Science & Technology

1980-09-15

Mild Steel (iAi i018). ............. 11-2 B. SAE 4130 .. .. .. .... ...... ....... 11-3 C. SAE 4140 ......... .... .... ......... 11-3 D, SAE 4340...11-7 - Test Data for SAE 4140 Steel Frag- ments ...... ................ 11-14 Figure II-7A - 4142 ... .............. 11-15 Figure 11-8 - Test Data...included the following types of steel: SAE 1018, 4130, 4140 and 4340; 5-317 and 5-876 Carpenter tool steel; Anico HY-80 and SSS-100 steel; AISI-S7

1. View top of warhead handling building (northwest to southeast) ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

1. View top of warhead handling building (northwest to southeast) of missile launch area. Sprint silos are seen on the left; Spartan silos on the right; and the missile site control building in the distant background and to the right. Launch area antennae and launch chamber covers can be seen - Stanley R. Mickelsen Safeguard Complex, Missile Launch Area, Within Exclusion Area, Nekoma, Cavalier County, ND

A study of the reactivity of S(VI)-F containing warheads with nucleophilic amino-acid side chains under physiological conditions.

PubMed

Mukherjee, H; Debreczeni, J; Breed, J; Tentarelli, S; Aquila, B; Dowling, J E; Whitty, A; Grimster, N P

2017-11-22

Sulfonyl fluorides (SFs) have recently emerged as a promising warhead for the targeted covalent modification of proteins. Despite numerous examples of the successful deployment of SFs as covalent probe compounds, a detailed exploration of the factors influencing the stability and reactivity of SFs has not yet appeared. In this work we present an extensive study on the influence of steric and electronic factors on the reactivity and stability of the SF and related S VI -F groups. While SFs react rapidly with N-acetylcysteine, the resulting adducts were found to be unstable, rendering SFs inappropriate for the durable covalent inhibition of cysteine residues. In contrast, SFs afforded stable adducts with both N-acetyltyrosine and N-acetyllysine; furthermore, we show that the reactivity of arylsulfonyl fluorides towards these nucleophilic amino acids can be predictably modulated by adjusting the electronic properties of the warhead. These trends were largely conserved when the covalent reaction occurred within a protein binding pocket. We have also obtained a crystal structure depicting covalent modification of the catalytic lysine of a tyrosine kinase (FGFR1) by the ATP analog 5'-O-3-((fluorosulfonyl)benzoyl)adenosine (m-FSBA). Highly reactive warheads were demonstrated to be unstable with respect to hydrolysis in buffered aqueous solutions, indicating that warhead reactivity must be carefully tuned to provide optimal rates of protein modification. Our results demonstrate that the reactivity of SFs complements that of more commonly studied acrylamides, and we hope that this work spurs the rational design of novel SF-containing covalent probe compounds and inhibitors, particularly in cases where a suitably positioned cysteine residue is not present.

Physical cryptographic verification of nuclear warheads

PubMed Central

Kemp, R. Scott; Danagoulian, Areg; Macdonald, Ruaridh R.; Vavrek, Jayson R.

2016-01-01

How does one prove a claim about a highly sensitive object such as a nuclear weapon without revealing information about the object? This paradox has challenged nuclear arms control for more than five decades. We present a mechanism in the form of an interactive proof system that can validate the structure and composition of an object, such as a nuclear warhead, to arbitrary precision without revealing either its structure or composition. We introduce a tomographic method that simultaneously resolves both the geometric and isotopic makeup of an object. We also introduce a method of protecting information using a provably secure cryptographic hash that does not rely on electronics or software. These techniques, when combined with a suitable protocol, constitute an interactive proof system that could reject hoax items and clear authentic warheads with excellent sensitivity in reasonably short measurement times. PMID:27432959

Physical cryptographic verification of nuclear warheads

NASA Astrophysics Data System (ADS)

Kemp, R. Scott; Danagoulian, Areg; Macdonald, Ruaridh R.; Vavrek, Jayson R.

2016-08-01

How does one prove a claim about a highly sensitive object such as a nuclear weapon without revealing information about the object? This paradox has challenged nuclear arms control for more than five decades. We present a mechanism in the form of an interactive proof system that can validate the structure and composition of an object, such as a nuclear warhead, to arbitrary precision without revealing either its structure or composition. We introduce a tomographic method that simultaneously resolves both the geometric and isotopic makeup of an object. We also introduce a method of protecting information using a provably secure cryptographic hash that does not rely on electronics or software. These techniques, when combined with a suitable protocol, constitute an interactive proof system that could reject hoax items and clear authentic warheads with excellent sensitivity in reasonably short measurement times.

Physical cryptographic verification of nuclear warheads.

PubMed

Kemp, R Scott; Danagoulian, Areg; Macdonald, Ruaridh R; Vavrek, Jayson R

2016-08-02

How does one prove a claim about a highly sensitive object such as a nuclear weapon without revealing information about the object? This paradox has challenged nuclear arms control for more than five decades. We present a mechanism in the form of an interactive proof system that can validate the structure and composition of an object, such as a nuclear warhead, to arbitrary precision without revealing either its structure or composition. We introduce a tomographic method that simultaneously resolves both the geometric and isotopic makeup of an object. We also introduce a method of protecting information using a provably secure cryptographic hash that does not rely on electronics or software. These techniques, when combined with a suitable protocol, constitute an interactive proof system that could reject hoax items and clear authentic warheads with excellent sensitivity in reasonably short measurement times.

Nuclear pursuits

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1993-05-01

This table lists quantities of warheads (in stockpile, peak number per year, total number built, number of known test explosions), weapon development milestones (developers of the atomic bomb and hydrogen bomb, date of first operational ICBM, first nuclear-powered naval SSN in service, first MIRVed missile deployed), and testing milestones (first fission test, type of boosted fission weapon, multistage thermonuclear test, number of months from fission bomb to multistage thermonuclear bomb, etc.), and nuclear infrastructure (assembly plants, plutonium production reactors, uranium enrichment plants, etc.). Countries included in the tally are the United States, Soviet Union, Britain, France, and China.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Marleau, Peter; Brubaker, Erik; Deland, Sharon M.

This report summarizes the discussion and conclusions reached during a table top exercise held at Sandia National Laboratories, Albuquerque on September 3, 2014 regarding a recently described approach for nuclear warhead verification based on the cryptographic concept of a zero-knowledge protocol (ZKP) presented in a recent paper authored by Glaser, Barak, and Goldston. A panel of Sandia National Laboratories researchers, whose expertise includes radiation instrumentation design and development, cryptography, and arms control verification implementation, jointly reviewed the paper and identified specific challenges to implementing the approach as well as some opportunities. It was noted that ZKP as used in cryptographymore » is a useful model for the arms control verification problem, but the direct analogy to arms control breaks down quickly. The ZKP methodology for warhead verification fits within the general class of template-based verification techniques, where a reference measurement is used to confirm that a given object is like another object that has already been accepted as a warhead by some other means. This can be a powerful verification approach, but requires independent means to trust the authenticity of the reference warhead - a standard that may be difficult to achieve, which the ZKP authors do not directly address. Despite some technical challenges, the concept of last-minute selection of the pre-loads and equipment could be a valuable component of a verification regime.« less

Roadmap to MaRIE January 2015

DOE Office of Scientific and Technical Information (OSTI.GOV)

Barnes, Cris William

After the decision to end nuclear testing and the inception of the Stockpile Stewardship program, the condition of the stockpile was the primary mission driver. During the first two decades of stewardship, the primary program goal could be described as underwriting the Stockpile-to-Target Sequence (STS), the military requirements on the conditions the nuclear warheads needed to survive and still operate.

Reactivity and Fragmentation of Aluminum-based Structural Energetic Materials under Explosive Loading

NASA Astrophysics Data System (ADS)

Glumac, Nick; Clemenson, Michael; Guadarrama, Jose; Krier, Herman

2015-06-01

Aluminum-cased warheads have been observed to generate enhanced blast and target damage due to reactivity of the aluminum fragments with ambient air. This effect can more than double the output of a conventional warhead. The mechanism by which the aluminum reacts under these conditions remains poorly understood. We undertake a highly controlled experimental study to investigate the phenomenon of aluminum reaction under explosive loading. Experiments are conducted with Al 6061 casings and PBX-N9 explosive with a fixed charge to case mass ratio of 1:2. Results are compared to inert casings (steel), as well as to tests performed in nitrogen environments to isolate aerobic and anaerobic effects. Padded walls are used in some tests to isolate the effects of impact-induced reactions, which are found to be non-negligible. Finally, blast wave measurements and quasi-static pressure measurements are used to isolate the fraction of case reaction that is fast enough to drive the primary blast wave from the later time reaction that generates temperature and overpressure only in the late-time fireball. Fragment size distributions, including those in the micron-scale range, are collected and quantified.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Perkins, Casey J.; Brigantic, Robert T.; Keating, Douglas H.

There is a need to develop and demonstrate technical approaches for verifying potential future agreements to limit and reduce total warhead stockpiles. To facilitate this aim, warhead monitoring systems employ both concepts of operations (CONOPS) and technologies. A systems evaluation approach can be used to assess the relative performance of CONOPS and technologies in their ability to achieve monitoring system objectives which include: 1) confidence that a treaty accountable item (TAI) initialized by the monitoring system is as declared; 2) confidence that there is no undetected diversion from the monitoring system; and 3) confidence that a TAI is dismantled asmore » declared. Although there are many quantitative methods that can be used to assess system performance for the above objectives, this paper focuses on a simulation perspective primarily for the ability to support analysis of the probabilities that are used to define operating characteristics of CONOPS and technologies. This paper describes a discrete event simulation (DES) model, comprised of three major sub-models: including TAI lifecycle flow, monitoring activities, and declaration behavior. The DES model seeks to capture all processes and decision points associated with the progressions of virtual TAIs, with notional characteristics, through the monitoring system from initialization through dismantlement. The simulation updates TAI progression (i.e., whether the generated test objects are accepted and rejected at the appropriate points) all the way through dismantlement. Evaluation of TAI lifecycles primarily serves to assess how the order, frequency, and combination of functions in the CONOPS affect system performance as a whole. It is important, however, to note that discrete event simulation is also capable (at a basic level) of addressing vulnerabilities in the CONOPS and interdependencies between individual functions as well. This approach is beneficial because it does not rely on complex mathematical models, but instead attempts to recreate the real world system as a decision and event driven simulation. Finally, because the simulation addresses warhead confirmation, chain of custody, and warhead dismantlement in a modular fashion, a discrete-event model could be easily adapted to multiple CONOPS for the exploration of a large number of “what if” scenarios.« less

U.S. Strategic Nuclear Forces: Background, Developments, and Issues

DTIC Science & Technology

2016-03-10

Strategic Offensive Reduction Treaty (known as the Moscow Treaty) between the United States and Russia, this number was to decline to no more than 2,200...the 2002 Moscow Treaty. According to the Bush Administration, operationally deployed warheads were those deployed on missiles and stored near bombers...given time. The warheads that could be carried on those submarines would not count against the Moscow Treaty limits because they would not be

Future Enablers: Air Force Smart Weapons in the 2040s

DTIC Science & Technology

2013-04-01

it is designed to have the same explosive effect as a 2,000 pound warhead. 136 The penetration ability of warheads has improved as well. The GBU - 39 ...Accountability Office, Defense Acquisitions : Assessment of Selected Weapons Programs, 12. 26 US Government Accountability Office, Joint Strike... Acquisitions : Assessment of Selected Weapons Programs, 65. 29 Ibid. 30 Kathleen Miller, Tony Capaccio, and Danielle Ivory, “F-35 Fighter Too Big to Kill as

Nuclear Weapons: The Reliable Replacement Warhead Program

DTIC Science & Technology

2005-06-03

inside reentry vehicles (RVs). An RV is a streamlined shell that protects its warhead from the intense heat and other stresses of reentering the...generation after generation of new nuclear “delivery vehicles ” — bombers, missile submarines, and land-based missiles — each of which would typically...reentry vehicle and the missile’s guidance. The ability to conduct small strikes depends on command and control. There may be various ways to reduce

The Development of a Dual-Warhead Impact System for Dynamic Linearity Measurement of a High-g Micro-Electro-Mechanical-Systems (MEMS) Accelerometer

PubMed Central

Shi, Yunbo; Yang, Zhicai; Ma, Zongmin; Cao, Huiliang; Kou, Zhiwei; Zhi, Dan; Chen, Yanxiang; Feng, Hengzhen; Liu, Jun

2016-01-01

Despite its extreme significance, dynamic linearity measurement for high-g accelerometers has not been discussed experimentally in previous research. In this study, we developed a novel method using a dual-warhead Hopkinson bar to measure the dynamic linearity of a high-g acceleration sensor with a laser interference impact experiment. First, we theoretically determined that dynamic linearity is a performance indicator that can be used to assess the quality merits of high-g accelerometers and is the basis of the frequency response. We also found that the dynamic linearity of the dual-warhead Hopkinson bar without an accelerometer is 2.5% experimentally. Further, we verify that dynamic linearity of the accelerometer is 3.88% after calibrating the Hopkinson bar with the accelerometer. The results confirm the reliability and feasibility of measuring dynamic linearity for high-g accelerometers using this method. PMID:27338383

The colibactin warhead crosslinks DNA

NASA Astrophysics Data System (ADS)

Vizcaino, Maria I.; Crawford, Jason M.

2015-05-01

Members of the human microbiota are increasingly being correlated to human health and disease states, but the majority of the underlying microbial metabolites that regulate host-microbe interactions remain largely unexplored. Select strains of Escherichia coli present in the human colon have been linked to the initiation of inflammation-induced colorectal cancer through an unknown small-molecule-mediated process. The responsible non-ribosomal peptide-polyketide hybrid pathway encodes ‘colibactin’, which belongs to a largely uncharacterized family of small molecules. Genotoxic small molecules from this pathway that are capable of initiating cancer formation have remained elusive due to their high instability. Guided by metabolomic analyses, here we employ a combination of NMR spectroscopy and bioinformatics-guided isotopic labelling studies to characterize the colibactin warhead, an unprecedented substituted spirobicyclic structure. The warhead crosslinks duplex DNA in vitro, providing direct experimental evidence for colibactin's DNA-damaging activity. The data support unexpected models for both colibactin biosynthesis and its mode of action.

Vertical nuclear proliferation.

PubMed

Sidel, Victor W

2007-01-01

All the nuclear-weapon states are working to develop new nuclear-weapon systems and upgrade their existing ones. Although the US Congress has recently blocked further development of small nuclear weapons and earth-penetrating nuclear weapons, the United States is planning a range of new warheads under the Reliable Replacement Warhead programme, and renewing its nuclear weapons infrastructure. The United Kingdom is spending 1 billion pounds sterling on updating the Atomic Weapons Establishment at Aldermaston, and about 20 billion pounds sterling on replacing its Vanguard submarines and maintaining its Trident warhead stockpile. The US has withdrawn from the Anti-Ballistic Missile Treaty and plans to install missile defence systems in Poland and the Czech Republic; Russia threatens to upgrade its nuclear countermeasures. The nuclear-weapon states should comply with their obligations under Article VI of the Non-Proliferation Treaty, as summarised in the 13-point plan agreed at the 2000 NPT Review Conference, and they should negotiate a Nuclear Weapons Convention.

Physical cryptographic verification of nuclear warheads

DOE PAGES

Kemp, R. Scott; Danagoulian, Areg; Macdonald, Ruaridh R.; ...

2016-07-18

How does one prove a claim about a highly sensitive object such as a nuclear weapon without revealing information about the object? This paradox has challenged nuclear arms control for more than five decades. We present a mechanism in the form of an interactive proof system that can validate the structure and composition of an object, such as a nuclear warhead, to arbitrary precision without revealing either its structure or composition. We introduce a tomographic method that simultaneously resolves both the geometric and isotopic makeup of an object. We also introduce a method of protecting information using a provably securemore » cryptographic hash that does not rely on electronics or software. Finally, these techniques, when combined with a suitable protocol, constitute an interactive proof system that could reject hoax items and clear authentic warheads with excellent sensitivity in reasonably short measurement times.« less

Nonstrategic Nuclear Weapons at an Inflection Point

DTIC Science & Technology

2017-07-01

11 figure 5. the B61 Mod 12 Nuclear Bomb and the f...B61 Mod 12 Nuclear Bomb , US Department of Energy, “NNSA Reaches B61-12 Life Extension Program Milestone: First Full-System Mechanical Environment Test... bomb ).22 20 Some warheads were to be to be eliminated; others were to be maintained in central storage. See Susan J. Koch, The Presidential Nuclear

Nuclear Warheads: The Reliable Replacement Warhead program and the Life Extension Program

DTIC Science & Technology

2007-12-03

eliminate the need for ESD controls.”67 CRS-22 68 The Defense Nuclear Facilities Safety Board was created by Congress 1988 “as an independent oversight...public health and safety’ at DOE’s defense nuclear facilities .” U.S. Defense Nuclear Facilities Safety Board. “Who We Are,” at [http://www.dnfsb.gov...about/index.html]. 69 Personal communication, Kent Fortenberry, Technical Director, Defense Nuclear Facilities Safety Board, September 14, 2006. 70

Nuclear Warheads: The Reliable Replacement Warhead Program and the Life Extension Program

DTIC Science & Technology

2006-12-13

Defense Nuclear Facilities Safety Board was created by Congress 1988 "as an independent oversight organization within the Executive Branch charged... nuclear facilities ." U.S. Defense Nuclear Facilities Safety Board. “Who We Are,” at [http://www.dnfsb.gov/about/index.html]. involving CHE and plutonium...approach, if successful, would “reduce or eliminate the need for ESD controls.”42 Kent Fortenberry, Technical Director of the Defense Nuclear Facilities

Nuclear Warheads: The Reliable Replacement Warhead Program and the Life Extension Program

DTIC Science & Technology

2007-04-04

Information provided by Pantex Plant, Sept. 19, 2006. 50 The Defense Nuclear Facilities Safety Board was created by Congress 1988 “as an independent...protection of public health and safety’ at DOE’s defense nuclear facilities .” U.S. Defense Nuclear Facilities Safety Board. “Who We Are,” at [http...www.dnfsb.gov/about/index.html]. 51 Personal communication, Kent Fortenberry, Technical Director, Defense Nuclear Facilities Safety Board, Sept. 14, 2006

Nuclear Warheads: The Reliable Replacement Warhead Program and the Life Extension Program

DTIC Science & Technology

2007-07-16

The Defense Nuclear Facilities Safety Board was created by Congress 1988 “as an independent oversight organization within the Executive Branch charged... nuclear facilities .” U.S. Defense Nuclear Facilities Safety Board. “Who We Are,” at [http://www.dnfsb.gov/about/index.html]. beginning, addressed safety...approach, if successful, would “reduce or eliminate the need for ESD controls.”55 Kent Fortenberry, Technical Director of the Defense Nuclear Facilities Safety

The Future Nuclear Arms Control Agenda and Its Potential Implications for the Air Force

DTIC Science & Technology

2015-08-01

triad of delivery systems will need to be replaced. Nuclear warhead life-cycle extension also will need to continue, assuming it remains too difficult...U.S. and Russian strategic nuclear forces. Thus, formal U.S.-Russian arms control negotiations for strategic nuclear systems will almost certainly...reductions in numbers of deployed systems to a more far-reaching agreement that would begin a process of verified elimination of nuclear warheads. The

Peptide nucleic acid probe for protein affinity purification based on biotin-streptavidin interaction and peptide nucleic acid strand hybridization.

PubMed

Tse, Jenny; Wang, Yuanyuan; Zengeya, Thomas; Rozners, Eriks; Tan-Wilson, Anna

2015-02-01

We describe a new method for protein affinity purification that capitalizes on the high affinity of streptavidin for biotin but does not require dissociation of the biotin-streptavidin complex for protein retrieval. Conventional reagents place both the selectively reacting group (the "warhead") and the biotin on the same molecule. We place the warhead and the biotin on separate molecules, each linked to a short strand of peptide nucleic acid (PNA), synthetic polymers that use the same bases as DNA but attached to a backbone that is resistant to attack by proteases and nucleases. As in DNA, PNA strands with complementary base sequences hybridize. In conditions that favor PNA duplex formation, the warhead strand (carrying the tagged protein) and the biotin strand form a complex that is held onto immobilized streptavidin. As in DNA, the PNA duplex dissociates at moderately elevated temperature; therefore, retrieval of the tagged protein is accomplished by a brief exposure to heat. Using iodoacetate as the warhead, 8-base PNA strands, biotin, and streptavidin-coated magnetic beads, we demonstrate retrieval of the cysteine protease papain. We were also able to use our iodoacetyl-PNA:PNA-biotin probe for retrieval and identification of a thiol reductase and a glutathione transferase from soybean seedling cotyledons. Copyright © 2014 Elsevier Inc. All rights reserved.

Selectable fragmentation warhead

DOEpatents

Bryan, Courtney S.; Paisley, Dennis L.; Montoya, Nelson I.; Stahl, David B.

1993-01-01

A selectable fragmentation warhead capable of producing a predetermined number of fragments from a metal plate, and accelerating the fragments toward a target. A first explosive located adjacent to the plate is detonated at selected number of points by laser-driven slapper detonators. In one embodiment, a smoother-disk and a second explosive, located adjacent to the first explosive, serve to increase acceleration of the fragments toward a target. The ability to produce a selected number of fragments allows for effective destruction of a chosen target.

Aircraft Survivability. Spring 2011

DTIC Science & Technology

2011-01-01

test Figure 4 Mixed Lagrangian and SPH Simulation of the Bullet Impacting the Floor Section Figure 5 Predictions of Damage to Penetrator, CMC Layer...aircraft and regulating the flow of liquid to simulate both the intrinsic change in plume intensity and the apparent change in intensity of a simulated ...the development of a digital simulation to conduct end game studies of the Eagle missile warhead- fuze combination. This was one of the first

U.S. Strategic Nuclear Forces: Background, Developments, and Issues

DTIC Science & Technology

2014-05-15

5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7...cover targets in and around Asia. It also has undertaken efforts to extend the life of the missiles and warheads so that they and the submarines can...that the Air Force had to “keep a robust test program all the way through the life of the program.”29 With the test assets available before this

The LRCM: (the Long-Range Strategic Cruise Missile) Asymmetries, Deterrence and SAL (Strategic Arms Limitation)

DTIC Science & Technology

1976-03-01

about the same pro- portion of the useful payload. The J-85-4A non- afterburning turbojet engines installed in the F5 aircraft occupy about 25% of the...about one kiloton TNT equivalent yield per 1 5 Pretty and Archer, op. cit. 32 pound of warhead weight. Thus, a 200 KT warhead will weigh about 200...explosion is equivalent to a conventional unit of energy release equal to one thousand short tons of TNT , or about 10 calories, 1.15 x 10 kilowatt

Structural Vulnerability of the Boeing B-29 Aircraft Wing to Damage by Warhead Fragments

NASA Technical Reports Server (NTRS)

Kordes, Eldon E.; OSullivan, William J., Jr.

1952-01-01

An elementary type of analysis has been used to determine the amount of wing tip that must be severed to produce irrevocable loss of control of a B-29 airplane. The remaining inboard structure of the Boeing B-29 wing has then been analyzed and curves are presented for the estimated reduction in structural strength due to four general types of damage produced by rod-type warhead fragments. The curves indicate the extent of structural damage required to produce a kill of the aircraft within 10 seconds.

Countermeasures to the US National Missile Defense

NASA Astrophysics Data System (ADS)

Gronlund, Lisbeth

2001-04-01

One of the key technical questions about national missile defenses is whether they can be expected to work under real-world conditions if the attacker takes steps to defeat the defense. This talk will discuss steps that an emerging missile state could take to confuse, overwhelm, or otherwise defeat the planned US NMD system developed by the Clinton administration. It will consider three such ``countermeasures" that would be within the technical capability of a state that could develop and deploy a long-range missile capable of reaching the United States, which is the threat the NMD system is intended to defend against. The talk will be based on the April 2000 report ``Countermeasures: A Technical Evaluation of the Operational Effectiveness of the Planned US National Missile Defense System," which was co-authored by the speaker and 10 other physicists and engineers. Although the talk will refer to the ground-based NMD system under development, the conclusions are applicable to any mid-course NMD system using hit-to-kill infrared-homing interceptors, regardless of their basing mode. The three countermeasures considered are: (1) biological weapons deployed on 100 or more small bomblets, or submunitions, that would be released shortly after the boost phase; (2) nuclear warheads with anti-simulation balloon decoys, in which the attacker disguises the warhead by enclosing it in an aluminum-coated mylar balloon and releasing it along with a large number of otherwise similar but empty balloons; and (3) nuclear warheads with cooled shrouds, in which the attacker foils the kill vehicle's homing process by covering each nuclear warhead with a double-walled cone containing liquid nitrogen.

NEW DEVELOPMENTS AND APPLICATIONS OF SUPERHEATED EMULSIONS: WARHEAD VERIFICATION AND SPECIAL NUCLEAR MATERIAL INTERDICTION.

PubMed

d'Errico, F; Chierici, A; Gattas-Sethi, M; Philippe, S; Goldston, R; Glaser, A

2018-04-25

In recent years, neutron detection with superheated emulsions has received renewed attention thanks to improved detector manufacturing and read-out techniques, and thanks to successful applications in warhead verification and special nuclear material (SNM) interdiction. Detectors are currently manufactured with methods allowing high uniformity of the drop sizes, which in turn allows the use of optical read-out techniques based on dynamic light scattering. Small detector cartridges arranged in 2D matrices are developed for the verification of a declared warhead without revealing its design. For this application, the enabling features of the emulsions are that bubbles formed at different times cannot be distinguished from each other, while the passive nature of the detectors avoids the susceptibility to electronic snooping and tampering. Large modules of emulsions are developed to detect the presence of shielded special nuclear materials hidden in cargo containers 'interrogated' with high energy X-rays. In this case, the enabling features of the emulsions are photon discrimination, a neutron detection threshold close to 3 MeV and a rate-insensitive read-out.

Precession missile feature extraction using sparse component analysis of radar measurements

NASA Astrophysics Data System (ADS)

Liu, Lihua; Du, Xiaoyong; Ghogho, Mounir; Hu, Weidong; McLernon, Des

2012-12-01

According to the working mode of the ballistic missile warning radar (BMWR), the radar return from the BMWR is usually sparse. To recognize and identify the warhead, it is necessary to extract the precession frequency and the locations of the scattering centers of the missile. This article first analyzes the radar signal model of the precessing conical missile during flight and develops the sparse dictionary which is parameterized by the unknown precession frequency. Based on the sparse dictionary, the sparse signal model is then established. A nonlinear least square estimation is first applied to roughly extract the precession frequency in the sparse dictionary. Based on the time segmented radar signal, a sparse component analysis method using the orthogonal matching pursuit algorithm is then proposed to jointly estimate the precession frequency and the scattering centers of the missile. Simulation results illustrate the validity of the proposed method.

North Korea’s Nuclear Weapons Development and Diplomacy

DTIC Science & Technology

2007-01-03

December 23, 2006. P. A12. Many of Kim Jong-il’s luxury goods purchases have been in Europe. They include Mercedes Benz and BMW automobiles, expensive...small scale atomic bomb. Most believed that North Korea had not reached the technology level to test the prototype of a small nuclear warhead.1 The...and possibly other weapons technology to Iran. There are known divisions within the Chinese government and Communist Party over the issue of support

Report of the Secretary of Defense Task Force on DoD Nuclear Weapons Management. Phase 1. The Air Force’s Nuclear Mission

DTIC Science & Technology

2008-09-01

under- resourced. • Missile transfer vans /warhead transfer vans require upgrades. • ICBM weapon system test sets under-funded; the coding system...Air Force’s Nuclear Mission D-1 Appendix D. Current B-52 Basing Status Barksdale AFB, LA 64 B-52Hs Minot AFB, ND 27 B-52Hs Edwards AFB, CA 3...Barksdale – 64 B-52s 2 BW (ACC) 15 TF; 24 CC; 7 BAI 53 WG (ACC) 2 Test Coded 917 WG (AFRC) 8 CC; 1 BAI 7 Unfunded AR Edwards - 3 B-52s 412 TW 2 Test

Yield and Blast Analyses with a Unified Theory of Explosions

DTIC Science & Technology

1982-08-01

and afterburning of PBXN 103. The ambient conditions are for the test site at Socorro, NM, altitude -- 5200 feet. The input mass was 1038 pounds...essentially the warhead, most of which is PBXN -103. This was the very first test of the code. The relative yield is plFj.ed as T (time). The TOA yield, .90...YO =YO*1.0 ’Relative yields from earlier runs or fits 52 ’ 1 G = 106 cal = 4pi/3*le6 kg m^2/m^3/sec^2 53 AB=.00 ’Afterburning fraction 56 YO = Y0*(I

REDUCTIONS WITHOUT REGRET: DEFINING THE NEEDED CAPABILITIES

DOE Office of Scientific and Technical Information (OSTI.GOV)

Swegle, J.; Tincher, D.

This is the second of three papers (in addition to an introductory summary) aimed at providing a framework for evaluating future reductions or modifications of the U.S. nuclear force, first by considering previous instances in which nuclear-force capabilities were eliminated; second by looking forward into at least the foreseeable future at the features of global and regional deterrence (recognizing that new weapon systems currently projected will have expected lifetimes stretching beyond our ability to predict the future); and third by providing examples of past or possible undesirable outcomes in the shaping of the future nuclear force, as well as somemore » closing thoughts for the future. This paper begins with a discussion of the current nuclear force and the plans and procurement programs for the modernization of that force. Current weapon systems and warheads were conceived and built decades ago, and procurement programs have begun for the modernization or replacement of major elements of the nuclear force: the heavy bomber, the air-launched cruise missile, the ICBMs, and the ballistic-missile submarines. In addition, the Nuclear Weapons Council has approved a new framework for nuclear-warhead life extension not fully fleshed out yet that aims to reduce the current number of nuclear explosives from seven to five, the so-called 3+2 vision. This vision includes three interoperable warheads for both ICBMs and SLBMs (thus eliminating one backup weapon) and two warheads for aircraft delivery (one gravity bomb and one cruise-missile, eliminating a second backup gravity bomb). This paper also includes a discussion of the current and near-term nuclear-deterrence mission, both global and regional, and offers some observations on future of the strategic deterrence mission and the challenges of regional and extended nuclear deterrence.« less

Aircraft Survivability: Space Survivability - Time to Get Serious, Summer 2008

DTIC Science & Technology

2008-01-01

modified to allow a capabil- ity to launch MANPADS with live warheads. Thus, METS was born. METS is a single - stage cold gas gun that uses compressed...30 feet from the target (see Figure 3). API projectiles or frag- ments fired from the gun passed through a sabot catcher (a thick metal plate with a...Body (T=2040K) Fit Water (T=2010K) Detectors Sabot catcher Shot line Gun Test Fixture Target Panel Figure 2 An Instantaneous Temperature Measurement in

Proceedings of the Army Symposium on Solid Mechanics, 1982 - Critical Mechanics Problems in Systems Design, 21-23 September 1982, Bass River, Cape Cod, Massachusetts

DTIC Science & Technology

1982-09-01

INTRODUCTION In the design of lightly armored vehicles it is of critical importance to be able to predict the vulnerability of these systems to...to similar geometry steel projectiles tested previously. INTRODUCTION The use of magnesium in proposed warhead designs has prompted renewed...to examine these excursions. INTRODUCTION The survival of a deeply buried missile capsule in a sand shaft was being evaluated during the

The Effects of Warhead-Induced Damage on the Aeroelastic Characteristics of Lifting Surfaces. Volume 2. Aerodynamic Effects

DTIC Science & Technology

1980-07-01

port Scannivalves, each with a DRUCK PDCR22, I psid pressure transducer. MODEL The models used in all the aerodynamic tests were left-half, T-38...14 - 2. . -0. 3 c3 -G.076 -- . 7 -0. -1.047 -0.031 .01A .G,2 15 -0.0.2 -0. Wl -0.0F2 -0.’q.1 -1 .c; 0. ... I ncilence: -7. -ei. fl’ 3D ’:i~t’): 0.010 e

History of the Shaped Charge Effect: The First 100 Years

DTIC Science & Technology

1990-03-22

patent, wave shapers, follow-through, U.S. 1949 39 6.5-in. ATAR HEAT rocket, U.S. NOTS, 1950 (schematic) 40 Test of 15-in. long standoff shaped charge...Swiss chemist Frederick Schoenbein in 1845, and nitroglycerin, derived by Ascanio Sobrero, professor of Chemistry at the University of Turin, Italy, in...totally new warhead and fuze system and delivery of the first 1000 rounds to Korea in less than 20 days! The 6.5-Inch ATAR (Code Name "RAM") The 6.5

Ballistic missile precession frequency extraction based on the Viterbi & Kalman algorithm

NASA Astrophysics Data System (ADS)

Wu, Longlong; Xie, Yongjie; Xu, Daping; Ren, Li

2015-12-01

Radar Micro-Doppler signatures are of great potential for target detection, classification and recognition. In the mid-course phase, warheads flying outside the atmosphere are usually accompanied by precession. Precession may induce additional frequency modulations on the returned radar signal, which can be regarded as a unique signature and provide additional information that is complementary to existing target recognition methods. The main purpose of this paper is to establish a more actual precession model of conical ballistic missile warhead and extract the precession parameters by utilizing Viterbi & Kalman algorithm, which improving the precession frequency estimation accuracy evidently , especially in low SNR.

DOE Office of Scientific and Technical Information (OSTI.GOV)

EDENBURN,MICHAEL W.; TROST,LAWRENCE C.

This paper compares the cost and effectiveness of several potential options that may be used to monitor silo-based ballistic missiles. Silo door monitoring can be used to verify that warheads removed to deactivate or download silo-based ballistic missiles have not been replaced. A precedent for monitoring warhead replacement using reentry vehicle on site inspections (RV-OSIs) and using satellites has been established by START-I and START-II. However, other monitoring options have the potential to be less expensive and more effective. Three options are the most promising if high verification confidence is desired: random monitoring using door sensors; random monitoring using mannedmore » or unmanned aircraft; and continuous remote monitoring using unattended door sensors.« less

Carbamates as Potential Prodrugs and a New Warhead for HDAC Inhibition.

PubMed

King, Kristina; Hauser, Alexander-Thomas; Melesina, Jelena; Sippl, Wolfgang; Jung, Manfred

2018-02-02

We designed and synthesized carbamates of the clinically-approved HDAC (histone deacetylase) inhibitor vorinostat (suberoylanilide hydroxamic acid, SAHA) in order to validate our previously-proposed hypothesis that these carbamates might serve as prodrugs for hydroxamic acid containing HDAC inhibitors. Biochemical assays proved our new compounds to be potent inhibitors of histone deacetylases in vitro, and they also showed antiproliferative effects in leukemic cells. These results, as well as stability analysis led to the suggestion that the intact carbamates are inhibitors of histone deacetylases themselves, representing a new zinc-binding warhead in HDAC inhibitor design. This suggestion was further supported by the synthesis and evaluation of a carbamate derivative of the HDAC6-selective inhibitor bufexamac.

Inhibition of DD-Peptidases by a Specific Trifluoroketone: Crystal Structure of a Complex with the Actinomadura R39 DD-Peptidase†

PubMed Central

Dzhekieva, Liudmila; Adediran, S. A.; Herman, Raphael; Kerff, Frédéric; Duez, Colette; Charlier, Paulette; Sauvage, Eric; Pratt, R.F.

2013-01-01

Inhibitors of bacterial DD-peptidases represent potential antibiotics. In the search for alternatives to β-lactams, we have investigated a series of compounds designed to generate transition state analogue structures on reaction with DD-peptidases. The compounds contain a combination of a peptidoglycan-mimetic specificity handle and a warhead capable of delivering a tetrahedral anion to the enzyme active site. The latter include a boronic acid, two alcohols, an aldehyde and a trifluoroketone. The compounds were tested against two low molecular mass class C DD-peptidases. As expected from previous observations, the boronic acid was a potent inhibitor, but, rather unexpectedly from precedent, the trifluoroketone [D-α-aminopimelyl-(1,1,1-trifluoro-3-amino)butan-2-one] was also very effective. Taking into account competing hydration, the trifluoroketone was the strongest inhibitor of the Actinomadura R39 DD-peptidase, with a subnanomolar (free ketone) inhibition constant. A crystal structure of the complex between the trifluoroketone and the R39 enzyme showed that a tetrahedral adduct had indeed formed with the active site serine nucleophile. The trifluoroketone moiety, therefore, should be considered along with boronic acids and phosphonates, as a warhead that can be incorporated into new and effective DD-peptidase inhibitors and therefore, perhaps, antibiotics. PMID:23484909

Inhibition of DD-peptidases by a specific trifluoroketone: crystal structure of a complex with the Actinomadura R39 DD-peptidase.

PubMed

Dzhekieva, Liudmila; Adediran, S A; Herman, Raphael; Kerff, Frédéric; Duez, Colette; Charlier, Paulette; Sauvage, Eric; Pratt, R F

2013-03-26

Inhibitors of bacterial DD-peptidases represent potential antibiotics. In the search for alternatives to β-lactams, we have investigated a series of compounds designed to generate transition state analogue structures upon reaction with DD-peptidases. The compounds contain a combination of a peptidoglycan-mimetic specificity handle and a warhead capable of delivering a tetrahedral anion to the enzyme active site. The latter includes a boronic acid, two alcohols, an aldehyde, and a trifluoroketone. The compounds were tested against two low-molecular mass class C DD-peptidases. As expected from previous observations, the boronic acid was a potent inhibitor, but rather unexpectedly from precedent, the trifluoroketone [D-α-aminopimelyl(1,1,1-trifluoro-3-amino)butan-2-one] was also very effective. Taking into account competing hydration, we found the trifluoroketone was the strongest inhibitor of the Actinomadura R39 DD-peptidase, with a subnanomolar (free ketone) inhibition constant. A crystal structure of the complex between the trifluoroketone and the R39 enzyme showed that a tetrahedral adduct had indeed formed with the active site serine nucleophile. The trifluoroketone moiety, therefore, should be considered along with boronic acids and phosphonates as a warhead that can be incorporated into new and effective DD-peptidase inhibitors and therefore, perhaps, antibiotics.

Wavelet feature extraction for reliable discrimination between high explosive and chemical/biological artillery

NASA Astrophysics Data System (ADS)

Hohil, Myron E.; Desai, Sachi V.; Bass, Henry E.; Chambers, Jim

2005-03-01

Feature extraction methods based on the discrete wavelet transform and multiresolution analysis are used to develop a robust classification algorithm that reliably discriminates between conventional and simulated chemical/biological artillery rounds via acoustic signals produced during detonation. Distinct characteristics arise within the different airburst signatures because high explosive warheads emphasize concussive and shrapnel effects, while chemical/biological warheads are designed to disperse their contents over large areas, therefore employing a slower burning, less intense explosive to mix and spread their contents. The ensuing blast waves are readily characterized by variations in the corresponding peak pressure and rise time of the blast, differences in the ratio of positive pressure amplitude to the negative amplitude, and variations in the overall duration of the resulting waveform. Unique attributes can also be identified that depend upon the properties of the gun tube, projectile speed at the muzzle, and the explosive burn rates of the warhead. In this work, the discrete wavelet transform is used to extract the predominant components of these characteristics from air burst signatures at ranges exceeding 2km. Highly reliable discrimination is achieved with a feedforward neural network classifier trained on a feature space derived from the distribution of wavelet coefficients and higher frequency details found within different levels of the multiresolution decomposition.

Guided Multiple Launch Rocket System/Guided Multiple Launch Rocket System Alternative Warhead (GMLRS/GMLRS AW)

DTIC Science & Technology

2015-12-01

Physical Configuration Audit for the GMLRS AW was completed at the system level in March 2015. ​Director of Operational Test and Evaluation Assessment...Confidence Level Confidence Level of cost estimate for current APB: 50% The confidence level used in establishing the cost estimate for GMLRS/GMLRS AW...PAUC Development Estimate Changes PAUC Production Estimate Econ Qty Sch Eng Est Oth Spt Total 0.039 -0.003 0.001 0.001 0.009 0.037 0.000 0.000 0.045

Hi-G electronic gated camera for precision trajectory analysis

NASA Astrophysics Data System (ADS)

Snyder, Donald R.; Payne, Scott; Keller, Ed; Longo, Salvatore; Caudle, Dennis E.; Walker, Dennis C.; Sartor, Mark A.; Keeler, Joe E.; Kerr, David A.; Fail, R. Wallace; Gannon, Jim; Carrol, Ernie; Jamison, Todd A.

1997-12-01

It is extremely difficult and expensive to determine the flight attitude and aimpoint of small maneuvering miniature air vehicles from ground based fixed or tracking photography. Telemetry alone cannot provide sufficient information bandwidth on 'what' the ground tracking is seeing and consequently 'why' it did or did not function properly. Additionally, it is anticipated that 'smart' and 'brilliant' guided vehicles now in development will require a high resolution imaging support system to determine which target and which part of a ground feature is being used for navigation or targeting. Other requirements include support of sub-component separation from developmental supersonic vehicles, where the clean separation from the container is not determinable from ground based film systems and film cameras do not survive vehicle breakup and impact. Hence, the requirement is to develop and demonstrate an imaging support system for development/testing that can provide the flight vehicle developer/analyst with imagery (combined with miniature telemetry sources) sufficient to recreate the trajectory, terminal navigation, and flight termination events. This project is a development and demonstration of a real-time, launch-rated, shuttered, electronic imager, transmitter, and analysis system. This effort demonstrated boresighted imagery from inside small flight vehicles for post flight analysis of trajectory, and capture of ground imagery during random triggered vehicle functions. The initial studies for this capability have been accomplished by the Experimental Dynamics Section of the Air Force Wright Laboratory, Armament Directorate, Eglin AFB, Florida, and the Telemetry Support Branch of the Army Material Research and Development Center at Picatinny Arsenal, New Jersey. It has been determined that at 1/10,000 of a second exposure time, new ultra-miniature CCD sensors have sufficient sensitivity to image key ground target features without blur, thereby providing data for trajectory, timing, and advanced sensor development. This system will be used for ground tracking data reduction in support of small air vehicle and munition testing. It will provide a means of integrating the imagery and telemetry data from the item with ground based photographic support. The technique we have designed will exploit off-the-shelf software and analysis components. A differential GPS survey instrument will establish a photogrammetric calibration grid throughout the range and reference targets along the flight path. Images from the on-board sensor will be used to calibrate the ortho- rectification model in the analysis software. The projectile images will be transmitted and recorded on several tape recorders to insure complete capture of each video field. The images will be combined with a non-linear video editor into a time-correlated record. Each correlated video field will be written to video disk. The files will be converted to DMA compatible format and then analyzed for determination of the projectile altitude, attitude and position in space. The resulting data file will be used to create a photomosaic of the ground the projectile flew over and the targets it saw. The data will be then transformed to a trajectory file and used to generate a graphic overlay that will merge digital photo data of the range with actual images captured. The plan is to superimpose the flight path of the projectile, the path of the weapons aimpoint, and annotation of each internal sequence event. With tools used to produce state-of-the-art computer graphics, we now think it will be possible to reconstruct the test event from the viewpoint of the warhead, the target, and a 'God's-Eye' view looking over the shoulder of the projectile.

Scenarios for exercising technical approaches to verified nuclear reductions

DOE Office of Scientific and Technical Information (OSTI.GOV)

Doyle, James

2010-01-01

Presidents Obama and Medvedev in April 2009 committed to a continuing process of step-by-step nuclear arms reductions beyond the new START treaty that was signed April 8, 2010 and to the eventual goal of a world free of nuclear weapons. In addition, the US Nuclear Posture review released April 6, 2010 commits the US to initiate a comprehensive national research and development program to support continued progress toward a world free of nuclear weapons, including expanded work on verification technologies and the development of transparency measures. It is impossible to predict the specific directions that US-RU nuclear arms reductions willmore » take over the 5-10 years. Additional bilateral treaties could be reached requiring effective verification as indicated by statements made by the Obama administration. There could also be transparency agreements or other initiatives (unilateral, bilateral or multilateral) that require monitoring with a standard of verification lower than formal arms control, but still needing to establish confidence to domestic, bilateral and multilateral audiences that declared actions are implemented. The US Nuclear Posture Review and other statements give some indication of the kinds of actions and declarations that may need to be confirmed in a bilateral or multilateral setting. Several new elements of the nuclear arsenals could be directly limited. For example, it is likely that both strategic and nonstrategic nuclear warheads (deployed and in storage), warhead components, and aggregate stocks of such items could be accountable under a future treaty or transparency agreement. In addition, new initiatives or agreements may require the verified dismantlement of a certain number of nuclear warheads over a specified time period. Eventually procedures for confirming the elimination of nuclear warheads, components and fissile materials from military stocks will need to be established. This paper is intended to provide useful background information for establishing a conceptual approach to a five-year technical program plan for research and development of nuclear arms reductions verification and transparency technologies and procedures.« less

CALCM: The untold story of the weapon used to start the Gulf war

NASA Astrophysics Data System (ADS)

Nielson, John T.

1994-07-01

The Conventional Air Launched Cruise Missile (CALCM) was developed from the strategic ALCM, AGM-86, by integrating GPS navigation into the missile in place of terrain correlation (TERCOM). In addition, the nuclear warhead was replaced by conventional explosives. The CALCM was developed, tested, and fielded in a single year (mid-1986 - mid-1987) by the Boeing Company where the author was then employed. Although the GPS technology used, a Rockwell single channel aided receiver, has been eclipsed by newer receivers with additional capabilities and newer technology, many innovative things were done in completing the CALCM integration: the external loading of almanac data along with other mission data, three satellite navigation capability, and the use of a single channel receiver in a dynamic flight environment. This effort demonstrated that GPS outputs can be integrated quickly into an existing weapon system using the traditional loosely coupled 'cascaded filter' approach. Although this approach is not as ideal as a tightly coupled integration using raw GPS data, the use of cascaded filters resulted in a weapon that was able to be rapidly fielded. The Air Force had sufficient confidence in the missile, that after four years of operational testing, 35 of these missiles were targeted at key sites at the start of the Gulf War in 1991. This effort, which was declassified in 1992, resulted in the first weapon in the DoD inventory to be operational using GPS navigation. The effort deserves consideration as a model as to how GPS integration can be performed.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Zimmerman, P.D.

Intercontinental ballistic missiles based in silos have become relatively vulnerable, at least in theory, to counter-force attacks. This theoretical vulnerability may not, in fact, be a serious practical concern; it is nonetheless troubling both to policy-makers and to the public. Furthermore, the present generation of ICBMs is aging (the Minuteman II single warhead missile will exceed its operational life-span early in the next decade) and significant restructuring of the ballistic missile force may well be necessary if a Strategic Arms Reduction Treaty (START) is signed. This paper compares several proposed schemes for modernizing the ICBM force. Because the rail-garrison MIRVdmore » mobile system is the least costly alternative to secure a large number of strategic warheads, it receives a comparatively large amount of attention.« less

Engineering Development of the XM261 Multipurpose Submunition Warhead and the XM267 Submunition Training Warhead

DTIC Science & Technology

1985-01-01

C 41 i • 1 *- ( X: — a» «-» ** »o ** -- *o h X» O i a» —• o *J 3 O 41 • o • •-» E flj ...34 *- * • -’--’’’ -"- • - - i’ i • i’ i * i i - iin td mä • i • • • na >Mi*i^BiB*a***ftfc *. *. • ii ^^•^^^^Vf^^V •«’•»•* •"• ^•W^ WT.i« ii, i...c C 3 TD O <Ü (O c* C C*_l oooooooooooooooooo i-H O HOOH i-HOt—«OI-HOOOOOOO CO en oo en en oooocncocncocncncncncncncn OcnH

Nuclear disarmament verification via resonant phenomena.

PubMed

Hecla, Jake J; Danagoulian, Areg

2018-03-28

Nuclear disarmament treaties are not sufficient in and of themselves to neutralize the existential threat of the nuclear weapons. Technologies are necessary for verifying the authenticity of the nuclear warheads undergoing dismantlement before counting them toward a treaty partner's obligation. Here we present a concept that leverages isotope-specific nuclear resonance phenomena to authenticate a warhead's fissile components by comparing them to a previously authenticated template. All information is encrypted in the physical domain in a manner that amounts to a physical zero-knowledge proof system. Using Monte Carlo simulations, the system is shown to reveal no isotopic or geometric information about the weapon, while readily detecting hoaxing attempts. This nuclear technique can dramatically increase the reach and trustworthiness of future nuclear disarmament treaties.

A Covert Disruptive Technology: Test and Development of the Corona Satellite

NASA Technical Reports Server (NTRS)

Peebles, Curtis

2008-01-01

The launching by the Soviet Union of the Sputnik satellite in 19457 was an impetuous to the United States. The Intercontinental ballistic Missile (ICBM) that launched the Earth's first satellite, could have been armed with a nuclear warhead, that could destroy an American city. The primary intelligence requirement that the US had was to determine the actual size of the Soviet missile program. To this end, a covert, high-risk photoreconnaissance satellite was developed. The code name of this program was "Corona." This article describes the trials and eventual successes of the Corona program.

From weapons to white dwarfs

NASA Astrophysics Data System (ADS)

Cartlidge, Edwin

2016-10-01

Military research centres that use giant lasers to study conditions inside nuclear warheads are increasingly opening their doors to university students. Edwin Cartlidge asks what the labs and the researchers have to gain from the arrangement

A comparative study of warheads for design of cysteine protease inhibitors.

PubMed

Silva, Daniel G; Ribeiro, Jean F R; De Vita, Daniela; Cianni, Lorenzo; Franco, Caio Haddad; Freitas-Junior, Lucio H; Moraes, Carolina Borsoi; Rocha, Josmar R; Burtoloso, Antonio C B; Kenny, Peter W; Leitão, Andrei; Montanari, Carlos A

2017-11-15

The effects on potency of cruzain inhibition of replacing a nitrile group with alternative warheads were explored. The oxime was almost an order of magnitude more potent than the corresponding nitrile and has the potential to provide access to the prime side of the catalytic site. Dipeptide aldehydes and azadipeptide nitriles were found to be two orders of magnitude more potent cruzain inhibitors than the corresponding dipeptide nitriles although potency differences were modulated by substitution at P1 and P3. Replacement of the α methylene of a dipeptide aldehyde with cyclopropane led to a loss of potency of almost three orders of magnitude. The vinyl esters and amides that were characterized as reversible inhibitors were less potent than the corresponding nitrile by between one and two orders of magnitude. Copyright © 2017 Elsevier Ltd. All rights reserved.

77 FR 15394 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-National Warheads...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-03-15

...; Gomez Research Associates, Inc., Huntsville, AL; Custom Analytical Engineering Systems, Inc., Flintstone... the Act on November 25, 2011 (76 FR 72724). Patricia A. Brink, Director of Civil Enforcement...

Smart dual-functional warhead for folate receptor-specific activatable imaging and photodynamic therapy.

PubMed

Kim, Jisu; Tung, Ching-Hsuan; Choi, Yongdoo

2014-09-21

A smart dual-targeted theranostic agent becomes highly fluorescent and phototoxic only when its linker is cleaved by tumor-associated lysosomal enzyme cathepsin B after internalization into folate receptor-positive cancer cells.

2. View from missile site control building (south to north) ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

2. View from missile site control building (south to north) of missile launch area, showing warhead handling building in background - Stanley R. Mickelsen Safeguard Complex, Missile Launch Area, Within Exclusion Area, Nekoma, Cavalier County, ND

DOCKTITE-a highly versatile step-by-step workflow for covalent docking and virtual screening in the molecular operating environment.

PubMed

Scholz, Christoph; Knorr, Sabine; Hamacher, Kay; Schmidt, Boris

2015-02-23

The formation of a covalent bond with the target is essential for a number of successful drugs, yet tools for covalent docking without significant restrictions regarding warhead or receptor classes are rare and limited in use. In this work we present DOCKTITE, a highly versatile workflow for covalent docking in the Molecular Operating Environment (MOE) combining automated warhead screening, nucleophilic side chain attachment, pharmacophore-based docking, and a novel consensus scoring approach. The comprehensive validation study includes pose predictions of 35 protein/ligand complexes which resulted in a mean RMSD of 1.74 Å and a prediction rate of 71.4% with an RMSD below 2 Å, a virtual screening with an area under the curve (AUC) for the receiver operating characteristics (ROC) of 0.81, and a significant correlation between predicted and experimental binding affinities (ρ = 0.806, R(2) = 0.649, p < 0.005).

Feature extraction of micro-motion frequency and the maximum wobble angle in a small range of missile warhead based on micro-Doppler effect

NASA Astrophysics Data System (ADS)

Li, M.; Jiang, Y. S.

2014-11-01

Micro-Doppler effect is induced by the micro-motion dynamics of the radar target itself or any structure on the target. In this paper, a simplified cone-shaped model for ballistic missile warhead with micro-nutation is established, followed by the theoretical formula of micro-nutation is derived. It is confirmed that the theoretical results are identical to simulation results by using short-time Fourier transform. Then we propose a new method for nutation period extraction via signature maximum energy fitting based on empirical mode decomposition and short-time Fourier transform. The maximum wobble angle is also extracted by distance approximate approach in a small range of wobble angle, which is combined with the maximum likelihood estimation. By the simulation studies, it is shown that these two feature extraction methods are both valid even with low signal-to-noise ratio.

6. Photocopy of photograph, U.S. Army, ca. 1955 (original print ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

6. Photocopy of photograph, U.S. Army, ca. 1955 (original print located at Rocky Mountain Arsenal, Commerce City, Colorado). AERIAL VIEW OF BUILDING 1611. VIEW TO NORTHEAST. 'THIS IS THE HONEST JOHN WARHEAD DEMILITARIZATION PLANT. THE DEMILITARIZATION PROCESS CONSISTS OF STRIPPING AND OPENING THE WARHEAD MANUALLY AND DOWNLOADING THE M139 BOMBLETS ONTO A CONVEYOR WHICH CARRIES THEM THROUGH A PUNCH, DRAIN AND RINSE MACHINE INTO A ROTARY RETORT DEACTIVATION FURNACE WHERE THE BURSTER IS BURNED. THE BOMBLET SHELLS, WHICH ARE ALUMINUM, ARE THEN CONVEYED TO A DECONTAMINATION FURNACE WHERE THEY ARE MELTED AND CAST INTO INGOTS. THE GB, WHICH IS COLLECTED IN THE PUNCH, DRAIN AND RINSE MACHINE, IS CONDUCTED TO A STORAGE TANK AND, ULTIMATELY, IS NEUTRALIZED ... - Rocky Mountain Arsenal, Ammunition Demolition Building-Tail Fin Storage & Assembly, 2750 feet South of Ninth Avenue; 3480 feet East of D Street, Commerce City, Adams County, CO

78 FR 52787 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-National Warheads...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-26

...; Serco, Inc., Reston, VA; Simulations, LLC, Simsbury, CT; SURVICE Engineering Company, LLC, Belcamp, MD... 54611). Patricia A. Brink, Director of Civil Enforcement, Antitrust Division. [FR Doc. 2013-20687 Filed...

Strategic Deterrence for the Future

DTIC Science & Technology

2015-08-01

progress in the strategic field has been considerable. Washington should carefully examine going below New START levels of warheads and launchers ...chief of staff of plans, policies, and requirements, US Pacific Fleet; congressional appropriations liaison officer for the Office of the Secretary

Discovery of highly potent, selective, covalent inhibitors of JAK3

DOE Office of Scientific and Technical Information (OSTI.GOV)

Kempson, James; Ovalle, Damaso; Guo, Junqing

A useful and novel set of tool molecules have been identified which bind irreversibly to the JAK3 active site cysteine residue. The design was based on crystal structure information and a comparative study of several electrophilic warheads.

75 FR 80536 - Notice Pursuant to the National Cooperative Research and Production Act of 1993 National Warheads...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-22

.... Specifically, Franklin Engineering Group, Inc., Franklin, TN; RDM Engineering, LLC, East Brunswick, NJ; Rocky..., Director of Civil Enforcement, Antitrust Division. [FR Doc. 2010-32052 Filed 12-21-10; 8:45 am] BILLING...

Part III: A Modest Proposal: How to Prevent the Extinctions.

ERIC Educational Resources Information Center

Discover, 1984

1984-01-01

Estimates between 750 and 1,000 potentially dangerous asteroids in orbits crossing that of the earth. Discusses how space probes armed with warheads can be used to rendezvous with these asteroids (or comets) to divert them from the earth. (BC)

3. View from missile site control building (southeast to northwest) ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

3. View from missile site control building (southeast to northwest) of missile launch area showing universal missile building on left and warhead handling building in background. - Stanley R. Mickelsen Safeguard Complex, Missile Launch Area, Within Exclusion Area, Nekoma, Cavalier County, ND

A deimmunised form of the ribotoxin, α-sarcin, lacking CD4+ T cell epitopes and its use as an immunotoxin warhead

PubMed Central

Jones, Tim D.; Hearn, Arron R.; Holgate, Robert G.E.; Kozub, Dorota; Fogg, Mark H.; Carr, Francis J.; Baker, Matthew P.; Lacadena, Javier; Gehlsen, Kurt R.

2016-01-01

Fungal ribotoxins that block protein synthesis can be useful warheads in the context of a targeted immunotoxin. α-Sarcin is a small (17 kDa) fungal ribonuclease produced by Aspergillus giganteus that functions by catalytically cleaving a single phosphodiester bond in the sarcin–ricin loop of the large ribosomal subunit, thus making the ribosome unrecognisable to elongation factors and leading to inhibition of protein synthesis. Peptide mapping using an ex vivo human T cell assay determined that α-sarcin contained two T cell epitopes; one in the N-terminal 20 amino acids and the other in the C-terminal 20 amino acids. Various mutations were tested individually within each epitope and then in combination to isolate deimmunised α-sarcin variants that had the desired properties of silencing T cell epitopes and retention of the ability to inhibit protein synthesis (equivalent to wild-type, WT α-sarcin). A deimmunised variant (D9T/Q142T) demonstrated a complete lack of T cell activation in in vitro whole protein human T cell assays using peripheral blood mononuclear cells from donors with diverse HLA allotypes. Generation of an immunotoxin by fusion of the D9T/Q142T variant to a single-chain Fv targeting Her2 demonstrated potent cell killing equivalent to a fusion protein comprising the WT α-sarcin. These results represent the first fungal ribotoxin to be deimmunised with the potential to construct a new generation of deimmunised immunotoxin therapeutics. PMID:27578884

Towards Tuneable Retaining Glycosidase-Inhibiting Peptides by Mimicry of a Plant Flavonol Warhead.

PubMed

Yoshisada, Ryoji; van Gijzel, Lieke; Jongkees, Seino A K

2017-12-05

Retaining glycosidases are an important class of enzymes involved in glycan degradation. To study better the role of specific enzymes in deglycosylation processes, and thereby the importance of particular glycosylation patterns, a set of potent inhibitors, each specific to a particular glycosidase, would be an invaluable toolkit. Towards this goal, we detail here a more in-depth study of a prototypical macrocyclic peptide inhibitor of the model retaining glycosidase human pancreatic α-amylase (HPA). Notably, incorporation of l-DOPA into this peptide affords an inhibitor of HPA with potency that is tenfold higher (K i =480 pm) than that of the previously found consensus sequence. This represents a first successful step in converting a recently discovered natural-product-derived motif, already specific for the catalytic side-chain arrangement conserved in the active sites of retaining glycosidases, into a tuneable retaining glycosidase inhibition warhead. © 2017 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim.

Scope of Work for the Joint Mk 38 Warhead/Atlas F Missile Firing Program

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1964-11-16

List of principles & responsibilities of this Sandia/AEC & Air Force joint program for verifying the functionability of the W28/AGM-28A/B-52 weapon system under actual routine handling, assembling, and firing during a stockpile-to-target sequence.

Busting Myths about Nuclear Deterrence

DTIC Science & Technology

2015-01-01

clearly showed Kim Jung Un’s in- tent to develop ballistic missiles capable of delivering a nuclear warhead against an Asian ally and possibly US...consequences of such aggression against the United States. Carl von Clausewitz ob- served in his classic work, On War, that when the potential exists for

48 CFR 252.223-7002 - Safety precautions for ammunition and explosives.

Code of Federal Regulations, 2013 CFR

2013-10-01

... ammunition and explosives. 252.223-7002 Section 252.223-7002 Federal Acquisition Regulations System DEFENSE ACQUISITION REGULATIONS SYSTEM, DEPARTMENT OF DEFENSE CLAUSES AND FORMS SOLICITATION PROVISIONS AND CONTRACT...) Ammunition; (iii) Rockets; (iv) Missiles; (v) Warheads; (vi) Devices; and (vii) Components of (i) through (vi...

48 CFR 252.223-7002 - Safety precautions for ammunition and explosives.

Code of Federal Regulations, 2012 CFR

2012-10-01

... ammunition and explosives. 252.223-7002 Section 252.223-7002 Federal Acquisition Regulations System DEFENSE ACQUISITION REGULATIONS SYSTEM, DEPARTMENT OF DEFENSE CLAUSES AND FORMS SOLICITATION PROVISIONS AND CONTRACT...) Ammunition; (iii) Rockets; (iv) Missiles; (v) Warheads; (vi) Devices; and (vii) Components of (i) through (vi...

48 CFR 252.223-7002 - Safety precautions for ammunition and explosives.

Code of Federal Regulations, 2014 CFR

2014-10-01

... ammunition and explosives. 252.223-7002 Section 252.223-7002 Federal Acquisition Regulations System DEFENSE ACQUISITION REGULATIONS SYSTEM, DEPARTMENT OF DEFENSE CLAUSES AND FORMS SOLICITATION PROVISIONS AND CONTRACT...) Ammunition; (iii) Rockets; (iv) Missiles; (v) Warheads; (vi) Devices; and (vii) Components of (i) through (vi...

U.S. Strategic Nuclear Forces: Background, Developments, and Issues

DTIC Science & Technology

2017-02-10

This program area is specifically seeking to support the solid rocket motor research and development industrial base , so that it will have the...... Research Service Summary Even though the United States is in the process of reducing the number of warheads deployed on its long-range missiles and

Aluminum Micro-Balloons as Improved Fuel for Warhead Explosives

DTIC Science & Technology

2018-01-29

12-1-0006 Dr. Jerry W. Forbes Prepared by: Energetics Technology Center 10400 O Donnell Place Suite 202 St. Charles, MD 20603...the goal of enhancing blast waves. This 6.2 grant work provides the baseline technology to understand shock wave experiments done and to be done

Yields of Soviet underground nuclear explosions at Novaya Zemlya, 1964-1976, from seismic body and surface waves

PubMed Central

Sykes, Lynn R.; Wiggins, Graham C.

1986-01-01

Surface and body wave magnitudes are determined for 15 U.S.S.R. underground nuclear weapons tests conducted at Novaya Zemlya between 1964 and 1976 and are used to estimate yields. These events include the largest underground explosions detonated by the Soviet Union. A histogram of body wave magnitude (mb) values indicates a clustering of explosions at a few specific yields. The most pronounced cluster consists of six explosions of yield near 500 kilotons. Several of these seem to be tests of warheads for major strategic systems that became operational in the late 1970s. The largest Soviet underground explosion is estimated to have a yield of 3500 ± 600 kilotons, somewhat smaller than the yield of the largest U.S. underground test. A preliminary estimation of the significance of tectonic release is made by measuring the amplitude of Love waves. The bias in mb for Novaya Zemlya relative to the Nevada test site is about 0.35, nearly identical to that of the eastern Kazakhstan test site relative to Nevada. PMID:16593645

Low-resolution gamma-ray spectrometry for an information barrier based on a multi-criteria template-matching approach

NASA Astrophysics Data System (ADS)

Göttsche, Malte; Schirm, Janet; Glaser, Alexander

2016-12-01

Gamma-ray spectrometry has been successfully employed to identify unique items containing special nuclear materials. Template information barriers have been developed in the past to confirm items as warheads by comparing their gamma signature to the signature of true warheads. Their development has, however, not been fully transparent, and they may not be sensitive to some relevant evasion scenarios. We develop a fully open template information barrier concept, based on low-resolution measurements, which, by design, reduces the extent of revealed sensitive information. The concept is based on three signatures of an item to be compared to a recorded template. The similarity of the spectrum is assessed by a modification of the Kolmogorov-Smirnov test to confirm the isotopic composition. The total gamma count rate must agree with the template as a measure of the projected surface of the object. In order to detect the diversion of fissile material from the interior of an item, a polyethylene mask is placed in front of the detector. Neutrons from spontaneous and induced fission events in the item produce 2.223 MeV gamma rays from neutron capture by hydrogen-1 in the mask. This peak is detected and its intensity scales with the item's fissile mass. The analysis based on MCNP Monte Carlo simulations of various plutonium configurations suggests that this concept can distinguish a valid item from a variety of invalid ones. The concept intentionally avoids any assumptions about specific spectral features, such as looking for specific gamma peaks of specific isotopes, thereby facilitating a fully unclassified discussion. By making all aspects public and allowing interested participants to contribute to the development and benchmarking, we enable a more open and inclusive discourse on this matter.

75 FR 33268 - Technology Innovation Program (TIP) Notice of Availability of Funds; Amendment

Federal Register 2010, 2011, 2012, 2013, 2014

2010-06-11

... military/ weaponry applications (e.g. warhead manufacture, chemical/biological warfare materials production.... production of biofuels or small molecule drugs); Projects that primarily focus on drug discovery or design of... design that are not a part of the manufacturing of engineered tissues; and Projects that do not have a...

77 FR 34067 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-National Warheads...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-08

..., 21 CT, Inc., Austin, TX; Cerebrus Corporation, Morris Plains, NJ; Conax Florida Corporation, St... DEPARTMENT OF JUSTICE Antitrust Division Notice Pursuant to the National Cooperative Research and..., 2012, pursuant to Section 6(a) of the National Cooperative Research and Production Act of 1993, 15 U.S...

76 FR 59161 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-National Warheads...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-23

...., Albuquerque, NM; Tetra Tech, Inc., Honolulu, HI; Trident Research, LLC, Austin, TX; Unified Design Corporation, Rockaway, NJ; and University of Texas at Austin, Austin, TX, have withdrawn as parties to this venture. No... DEPARTMENT OF JUSTICE Antitrust Division Notice Pursuant to the National Cooperative Research and...

76 FR 72724 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-National Warheads...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-25

.... Specifically, Accurate Munition Systems, Inc., Austin, TX; Excelitas Technologies Sensors, Inc., Miamisburg, OH... DEPARTMENT OF JUSTICE Antitrust Division Notice Pursuant to the National Cooperative Research and... 04, 2011, pursuant to Section 6(a) of the National Cooperative Research and Production Act of 1993...

78 FR 16868 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-National Warheads...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-03-19

..., PA; Systems and Materials Research Corporation, Austin, TX; and Targeted GeoSystems, LLC, Madison, AL... DEPARTMENT OF JUSTICE Antitrust Division Notice Pursuant to the National Cooperative Research and... 19, 2013, pursuant to Section 6(a) of the National Cooperative Research and Production Act of 1993...

76 FR 16820 - Notice Pursuant to the National Cooperative Research and Production Act of 1993-National Warheads...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-25

... DEPARTMENT OF JUSTICE Antitrust Division Notice Pursuant to the National Cooperative Research and... 25, 2011, pursuant to Section 6(a) of the National Cooperative Research and Production Act of 1993.... Specifically, Directed Energy Technologies, Inc., Sumerduck, VA; MaxPower, Inc., Harleysville, PA; Omnitek...

Rain Premature Susceptibility Study on the Proposed Piezoelectric Contact Fuze System for Triggering the MC-132 in the TX-5X1 Weapon

DOE Office of Scientific and Technical Information (OSTI.GOV)

Wehrle, R.D.

1953-06-18

The probability of the occurrence of rain during the "armed" portion of the fall of a bomb is approximately 1/25. Therefore, rain is considered a problem in premature detonation of the warhead through activation of the contact fuze system.

Using Elementary Mechanics to Estimate the Maximum Range of ICBMs

ERIC Educational Resources Information Center

Amato, Joseph

2018-01-01

North Korea's development of nuclear weapons and, more recently, intercontinental ballistic missiles (ICBMs) has added a grave threat to world order. The threat presented by these weapons depends critically on missile range, i.e., the ability to reach North America or Europe while carrying a nuclear warhead. Using the limited information available…

Scope Complexity Options Risks Excursions (SCORE) Factor Mathematical Description.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Gearhart, Jared Lee; Samberson, Jonell Nicole; Shettigar, Subhasini

The purpose of the Scope, Complexity, Options, Risks, Excursions (SCORE) model is to estimate the relative complexity of design variants of future warhead options, resulting in scores. SCORE factors extend this capability by providing estimates of complexity relative to a base system (i.e., all design options are normalized to one weapon system). First, a clearly defined set of scope elements for a warhead option is established. The complexity of each scope element is estimated by Subject Matter Experts (SMEs), including a level of uncertainty, relative to a specific reference system. When determining factors, complexity estimates for a scope element canmore » be directly tied to the base system or chained together via comparable scope elements in a string of reference systems that ends with the base system. The SCORE analysis process is a growing multi-organizational Nuclear Security Enterprise (NSE) effort, under the management of the NA-12 led Enterprise Modeling and Analysis Consortium (EMAC). Historically, it has provided the data elicitation, integration, and computation needed to support the out-year Life Extension Program (LEP) cost estimates included in the Stockpile Stewardship Management Plan (SSMP).« less

Proteasome inhibition by new dual warhead containing peptido vinyl sulfonyl fluorides.

PubMed

Brouwer, Arwin J; Herrero Álvarez, Natalia; Ciaffoni, Adriano; van de Langemheen, Helmus; Liskamp, Rob M J

2016-08-15

The success of inhibition of the proteasome by formation of covalent bonds is a major victory over the long held-view that this would lead to binding the wrong targets and undoubtedly lead to toxicity. Great challenges are now found in uncovering ensembles of new moieties capable of forming long lasting ties. We have introduced peptido sulfonyl fluorides for this purpose. Tuning the reactivity of this electrophilic trap may be crucial for modulating the biological action. Here we describe incorporation of a vinyl moiety into a peptido sulfonyl fluoride backbone, which should lead to a combined attack of the proteasome active site threonine on the double bond and the sulfonyl fluoride. Although this led to strong proteasome inhibitors, in vitro studies did not unambiguously demonstrate the formation of the proposed seven-membered ring structure. Possibly, formation of a seven-membered covalent adduct with the proteosomal active site threonine can only be achieved within the context of the enzyme. Nevertheless, this dual warhead concept may provide exclusive possibilities for duration and selectivity of proteasome inhibition. Copyright © 2016 Elsevier Ltd. All rights reserved.

Nuclear almanac: confronting the atom in war and peace

DOE Office of Scientific and Technical Information (OSTI.GOV)

Dennis, J.

1984-01-01

The MIT Faculty Coalition for Disarmament prepared this almanac for those who wish to find in a single volume of factual account of the discovery, development, and use of nuclear energy - as well as a critical evaluation of policy issues raised by nuclear armaments and nuclear power. It is their hope that, with this knowledge readily accessible, public opinion will be better informed and public policy more responsible and wise. In an introductory essay, Henry S. Commager, distinguished historian at Amherst College challenges us to put the interests of all peoples ahead of national loyalties. Another introductory essay bymore » Nan Randall, consultant to the Office of Technology Assessment, in Charlottesville: a fictional account, pictures the effects on an old and beautiful city fortunate enough to escape the warheads in a large-scale nuclear war. Twenty-six separate chapters are then included under 9 separate Parts: the Story of Nuclear Weapons; Nuclear Weapons Effects; Nuclear War; Nuclear Warheads; Consequences; International Issues; Nuclear Energy; Action; and Background. A separate abstract was prepared for each of the 26 chapters.« less

The polar warhead of a TRIM24 bromodomain inhibitor rearranges a water-mediated interaction network.

PubMed

Liu, Jiuyang; Li, Fudong; Bao, Hongyu; Jiang, Yiyang; Zhang, Shuya; Ma, Rongsheng; Gao, Jia; Wu, Jihui; Ruan, Ke

2017-04-01

Tripartite motif-containing protein 24 (TRIM24) is closely correlated with multiple cancers, and a recent study demonstrated that the bromodomain of TRIM24 is essential for the proliferation of lethal castration-resistant prostate cancer. Here, we identify three new inhibitors of the TRIM24 bromodomain using NMR fragment-based screening. The crystal structures of two new inhibitors in complex with the TRIM24 bromodomain reveal that the water-bridged interaction network is conserved in the same fashion as those for known benzoimidazolone inhibitors. Interestingly, the polar substitution on the warhead of one new inhibitor pulls the whole ligand approximately 2 Å into the inner side pocket of the TRIM24 bromodomain, and thus exhibits a binding mode significantly different from other known bromodomain ligands. This mode provides a useful handle for further hit-to-lead evolution toward novel inhibitors of the TRIM24 bromodomain. Structural data are available in the PDB under the accession numbers 5H1T, 5H1U, and 5H1V. © 2017 Federation of European Biochemical Societies.

Commissioning the GTA accelerator

DOE Office of Scientific and Technical Information (OSTI.GOV)

Sander, O.R.; Atkins, W.H.; Bolme, G.O.

1992-09-01

The Ground Test Accelerator (GTA) is supported by the Strategic Defense command as part of their Neutral Particle Beam (NPB) program. Neutral particles have the advantage that in space they are unaffected by the earth`s magnetic field and travel in straight lines unless they enter the earth`s atmosphere and become charged by stripping. Heavy particles are difficult to stop and can probe the interior of space vehicles; hence, NPB can function as a discriminator between warheads and decoys. We are using GTA to resolve the physics and engineering issues related to accelerating, focusing, and steering a high-brightness, high-current H{sup -}more » beam and then neutralizing it. Our immediate goal is to produce a 24-MeV, 50mA device with a 2% duty factor.« less

Commissioning the GTA accelerator

DOE Office of Scientific and Technical Information (OSTI.GOV)

Sander, O.R.; Atkins, W.H.; Bolme, G.O.

1992-01-01

The Ground Test Accelerator (GTA) is supported by the Strategic Defense command as part of their Neutral Particle Beam (NPB) program. Neutral particles have the advantage that in space they are unaffected by the earth's magnetic field and travel in straight lines unless they enter the earth's atmosphere and become charged by stripping. Heavy particles are difficult to stop and can probe the interior of space vehicles; hence, NPB can function as a discriminator between warheads and decoys. We are using GTA to resolve the physics and engineering issues related to accelerating, focusing, and steering a high-brightness, high-current H{sup -}more » beam and then neutralizing it. Our immediate goal is to produce a 24-MeV, 50mA device with a 2% duty factor.« less

Development of Optimum Theoretical Warhead Design Criteria

DTIC Science & Technology

1976-12-01

d11 iipl 7(I d Ld TheeC ~ desity veocityl metail Lqa tin rqiStec. ~~i~i~ f’Iqain5t tl-G IHC e( j Ut io ti T cnhe relorittenquateioin now tbevoimbes: a...cvelopment arid Education Conmmand, Quantico Mobility Support Division, Major Thorp (1) Waj (aiecs Division, Mai ine Coips Landing Forc 1)cvelopment

Applied Computational Fluid Dynamics in Support of Aircraft/Store Compatibility and Weapons Integration -2007 Edition

DTIC Science & Technology

2007-06-01

CFD in the AFSEO The SBD, designated GBU - 39 /B, contains a 250 production environment include the requirement for rapid pound warhead, measures 6 feet...Take Off (RATO) Separation." ITEA Conference, Apr 2006. Figure 3. B-52/MOP Figure 1. GBU - 39 /B small diameter bomb computational model Figure 4. MOP

2009 Joint CBRN Conference

DTIC Science & Technology

2009-06-25

Operational Science & Technology Conference & Exhibition August 3 - 6, 2009 Honolulu, HI "Synchronizing Operators and Technologists " Warheads & Ballistics...1027 Microbial-Vac Systems Inc. 627 Military Medical Technology 1115 Modec, Inc...AT&L) TRADOC VCSAFORSCOM INSCOM Medical Dept BD RDE COMMAND AMC RDECs ARL SLAD ATEC AEC DTC OTC HELSTF USAKA/RTS ASA(ALT) PEO STRI PM ITTS IMO TMO

Le Monde’s Perception of the U.S.-Soviet Strategic Balance: An Update for 1979-1981.

DTIC Science & Technology

1983-12-01

ICBMs in silos comprised 56 percent of their launchers [ lanceurs ], 75 percent of their warheads [ogives], and 70 percent of their throw-weight. For the... structures , in-place protection of one part of the population (about 20 million inhabitants) is anticipated, and the movement of the rest to less

[A Method to Measure the Velocity of Fragments of Large Equivalence Explosion Field Based on Explosion Flame Spectral Analysis].

PubMed

Liu, Ji; Yu, Li-xia; Zhang, Bin; Zhao Dong-e; Liij, Xiao-yan; Wang, Heng-fei

2016-03-01

The deflagration fire lasting for a long time and covering a large area in the process of large equivalent explosion makes it difficult to obtain velocity parameters of fragments in the near-field. In order to solve the problem, it is proposed in this paper a photoelectric transceiver integrated method which utilize laser screen as the sensing area. The analysis of three different types of warhead explosion flame spectral distribution of radiation shows that 0.3 to 1.0 μm within the band is at relatively low intensity. On the basis of this, the optical system applies the principle of determining the fixed distance by measuring the time and the reflector technology, which consists of single longitudinal mode laser, cylindrical Fresnel lens, narrow-band filters and high-speed optical sensors, etc. The system has its advantage, such as transceiver, compact structure and combination of narrowband filter and single longitudinal mode laser, which can stop the spectrum of fire from suppressing the interference of background light effectively. Large amounts of experiments in different models and equivalent have been conducted to measure the velocity of difference kinds of warheads, obtaining higher signal-to-noise ratio of the waveform signal after a series of signal de-noising and recognition through NI company data acquisition and recording system. The experimental results show that this method can complete the accurately test velocity of fragments around center of the explosion. Specifically, the minimum size of fragments can be measured is 4 mm while the speed can be obtained is up to 1 200 m x s(-1) and the capture rate is better than 95% comparing with test results of target plate. At the same time, the system adopts Fresnel lenses-transparent to form a rectangular screen, which makes the distribution of rectangular light uniform in vertical direction, and the light intensity uniformity in horizontal direction is more than 80%. Consequently, the system can distinguish preliminarily the correspondence between the velocity and the sizes of prefabricated fragments.

Abort Flight Test Project Overview

NASA Technical Reports Server (NTRS)

Sitz, Joel

2007-01-01

A general overview of the Orion abort flight test is presented. The contents include: 1) Abort Flight Test Project Overview; 2) DFRC Exploration Mission Directorate; 3) Abort Flight Test; 4) Flight Test Configurations; 5) Flight Test Vehicle Engineering Office; 6) DFRC FTA Scope; 7) Flight Test Operations; 8) DFRC Ops Support; 9) Launch Facilities; and 10) Scope of Launch Abort Flight Test

Two-Black Box Concept for Warhead Verification

DOE Office of Scientific and Technical Information (OSTI.GOV)

Bates, Cameron Russell; Frame, Katherine Chiyoko; Mckigney, Edward Allen

2017-03-06

We have created a possible solution to meeting the requirements of certification/authentication while still employing complicated criteria. Technical solutions to protecting information from the host in an inspection environment needs to be assessed by those with specific expertise but, LANL can still study the verification problem. The two-black box framework developed provides another potential solution to the confidence vs. certification paradox.

Between Scylla and Charybdis: Theater Nuclear Forces in Europe.

DTIC Science & Technology

1985-03-01

Soviets lost what credibility they may have had in the wake of the KAL tragedy . The Soviets were also less than optimistic about their chances of...at Seneca Army Depot, NY. 30 The W82 ERW has a yield of < 2 KT and was intended to replace the W48. Costs have climbed to $3 mill. per warhead, but

Argumentation in the Canadian House of Commons on the Issue of Nuclear Weapons for Canada.

ERIC Educational Resources Information Center

Jones, John Alfred

The Cuban missile crisis of October 1962 forced the Canadian House of Commons to consider whether Canadian forces in NORAD and NATO were effective without nuclear warheads on special weapons systems. This paper provides an overview of the debates and their milieu, identifies the issues involved, and analyzes the effects of the argumentation. The…

Army Tactical Missile System and Fixed-Wing Aircraft Capabilities in the Joint Time-Sensitive Targeting Process

DTIC Science & Technology

2006-01-01

Air Force recently introduced the guided bomb unit ( GBU )- 39 small diameter bomb (SDB). This 250-pound class bomb is accurate and minimizes CD compared...munitions dispenser. The Navy has procured the AGM-154C, which carries a 500-pound unitary warhead. The Air Force expects to field the GBU - 39 SDB in

Sensor Technology Assessment for Ordnance and Explosive Waste Detection and Location. Revision B.

DTIC Science & Technology

1995-03-01

5 Figure 1.5 Examples Of Anti-Tank Mines .................... .................... 5 Figure 1.6. Sample Drawing of a Bomb...6 Figure 1.7. Examples of Scatterable Anti-Personnel Mines (top) and Scatterable Anti-Tank Mines (bottom...individuals, and therefore the OEW items must be detected and located. OEW examples are bombs, warheads, guided missiles, mortars, small arms, mines

U.S. Strategic Nuclear Forces: Background, Developments, and Issues

DTIC Science & Technology

2013-10-22

32 Safety, Security, and Management ...by Amy F. Woolf. 2 Natural Resources Defense Council. Table of U.S. Strategic Offensive Force Loadings. Archive of Nuclear Data. http://www.nrdc.org...12000 14000 16000 60 62 64 66 68 70 72 74 76 78 80 82 84 86 88 90 Year N um be r Launchers Warheads Source: Natural Resources Defense Council

An NMR-Guided Screening Method for Selective Fragment Docking and Synthesis of a Warhead Inhibitor.

PubMed

Khattri, Ram B; Morris, Daniel L; Davis, Caroline M; Bilinovich, Stephanie M; Caras, Andrew J; Panzner, Matthew J; Debord, Michael A; Leeper, Thomas C

2016-07-16

Selective hits for the glutaredoxin ortholog of Brucella melitensis are determined using STD NMR and verified by trNOE and (15)N-HSQC titration. The most promising hit, RK207, was docked into the target molecule using a scoring function to compare simulated poses to experimental data. After elucidating possible poses, the hit was further optimized into the lead compound by extension with an electrophilic acrylamide warhead. We believe that focusing on selectivity in this early stage of drug discovery will limit cross-reactivity that might occur with the human ortholog as the lead compound is optimized. Kinetics studies revealed that lead compound 5 modified with an ester group results in higher reactivity than an acrylamide control; however, after modification this compound shows little selectivity for bacterial protein versus the human ortholog. In contrast, hydrolysis of compound 5 to the acid form results in a decrease in the activity of the compound. Together these results suggest that more optimization is warranted for this simple chemical scaffold, and opens the door for discovery of drugs targeted against glutaredoxin proteins-a heretofore untapped reservoir for antibiotic agents.

A Trojan-Horse Peptide-Carboxymethyl-Cytidine Antibiotic from Bacillus amyloliquefaciens.

PubMed

Serebryakova, Marina; Tsibulskaya, Darya; Mokina, Olga; Kulikovsky, Alexey; Nautiyal, Manesh; Van Aerschot, Arthur; Severinov, Konstantin; Dubiley, Svetlana

2016-12-07

Microcin C and related antibiotics are Trojan-horse peptide-adenylates. The peptide part is responsible for facilitated transport inside the sensitive cell, where it gets processed to release a toxic warhead-a nonhydrolyzable aspartyl-adenylate, which inhibits aspartyl-tRNA synthetase. Adenylation of peptide precursors is carried out by MccB THIF-type NAD/FAD adenylyltransferases. Here, we describe a novel microcin C-like compound from Bacillus amyloliquefaciens. The B. amyloliquefaciens MccB demonstrates an unprecedented ability to attach a terminal cytidine monophosphate to cognate precursor peptide in cellular and cell free systems. The cytosine moiety undergoes an additional modification-carboxymethylation-that is carried out by the C-terminal domain of MccB and the MccS enzyme that produces carboxy-SAM, which serves as a donor of the carboxymethyl group. We show that microcin C-like compounds carrying terminal cytosines are biologically active and target aspartyl-tRNA synthetase, and that the carboxymethyl group prevents resistance that can occur due to modification of the warhead. The results expand the repertoire of known enzymatic modifications of peptides that can be used to obtain new biological activities while avoiding or limiting bacterial resistance.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Bacha,U.; Barilla, J.; Gabelli, S.

Coronaviruses comprise a large group of RNA viruses with diverse host specificity. The emergence of highly pathogenic strains like the SARS coronavirus (SARS-CoV), and the discovery of two new coronaviruses, NL-63 and HKU1, corroborates the high rate of mutation and recombination that have enabled them to cross species barriers and infect novel hosts. For that reason, the development of broad-spectrum antivirals that are effective against several members of this family is highly desirable. This goal can be accomplished by designing inhibitors against a target, such as the main protease 3CLpro (Mpro), which is highly conserved among all coronaviruses. Here 3CLpromore » derived from the SARS-CoV was used as the primary target to identify a new class of inhibitors containing a halomethyl ketone warhead. The compounds are highly potent against SARS 3CLpro with Ki's as low as 300 nm. The crystal structure of the complex of one of the compounds with 3CLpro indicates that this inhibitor forms a thioether linkage between the halomethyl carbon of the warhead and the catalytic Cys 145. Furthermore, Structure Activity Relationship (SAR) studies of these compounds have led to the identification of a pharmacophore that accurately defines the essential molecular features required for the high affinity.« less

Marine-Sourced Anti-Cancer and Cancer Pain Control Agents in Clinical and Late Preclinical Development †

PubMed Central

Newman, David J.; Cragg, Gordon M.

2014-01-01

The marine habitat has produced a significant number of very potent marine-derived agents that have the potential to inhibit the growth of human tumor cells in vitro and, in a number of cases, in both in vivo murine models and in humans. Although many agents have entered clinical trials in cancer, to date, only Cytarabine, Yondelis® (ET743), Eribulin (a synthetic derivative based on the structure of halichondrin B), and the dolastatin 10 derivative, monomethylauristatin E (MMAE or vedotin) as a warhead, have been approved for use in humans (Adcetris®). In this review, we show the compounds derived from marine sources that are currently in clinical trials against cancer. We have included brief discussions of the approved agents, where they are in trials to extend their initial approved activity (a common practice once an agent is approved), and have also included an extensive discussion of the use of auristatin derivatives as warheads, plus an area that has rarely been covered, the use of marine-derived agents to ameliorate the pain from cancers in humans, and to act as an adjuvant in immunological therapies. PMID:24424355

National Center for Nuclear Security - NCNS

ScienceCinema

None

2018-01-16

As the United States embarks on a new era of nuclear arms control, the tools for treaty verification must be accurate and reliable, and must work at stand-off distances. The National Center for Nuclear Security, or NCNS, at the Nevada National Security Site, is poised to become the proving ground for these technologies. The center is a unique test bed for non-proliferation and arms control treaty verification technologies. The NNSS is an ideal location for these kinds of activities because of its multiple environments; its cadre of experienced nuclear personnel, and the artifacts of atmospheric and underground nuclear weapons explosions. The NCNS will provide future treaty negotiators with solid data on verification and inspection regimes and a realistic environment in which future treaty verification specialists can be trained. Work on warhead monitoring at the NCNS will also support future arms reduction treaties.

Society of Flight Test Engineers, Annual Symposium, 21st, Garden Grove, CA, Aug. 6-10, 1990, Proceedings

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1990-01-01

The present conference on flight testing encompasses avionics, flight-testing programs, technologies for flight-test predictions and measurements, testing tools, analysis methods, targeting techniques, and flightline testing. Specific issues addressed include flight testing of a digital terrain-following system, a digital Doppler rate-of-descent indicator, a high-technology testbed, a low-altitude air-refueling flight-test program, techniques for in-flight frequency-response testing for helicopters, limit-cycle oscillation and flight-flutter testing, and the research flight test of a scaled unmanned air vehicle. Also addressed are AV-8B V/STOL performance analysis, incorporating pilot-response time in failure-case testing, the development of pitot static flightline testing, targeting techniques for ground-based hover testing, a low-profilemore » microsensor for aerodynamic pressure measurement, and the use of a variable-capacitance accelerometer for flight-test measurements.« less

Analysis of the Use of Defense Technical Information Center Resources By Research and Development Centers and Laboratories in the U.S. Army

DTIC Science & Technology

1985-11-08

and ." faster printers, they could significantly reduce problems exper- Sienced with slow turnaround for delivery of documents from DTIC. 5.35. Table...forgotten re- ports on rifle war games that proved very useful to our studies." (BRL) Saved 2 weeks and $3,000: "A new warhead development program

Apogee, Perigee, and Recovery: Chronology of Army Exploitation of Space

DTIC Science & Technology

1989-01-01

46 17. A BMD Advanced Technology Center infrared optical sensor is shown prior to mounting into a specially designed payload...wave infrared sensors to detect and track enemy ballistic missile warheads ..................... 50 21. In June 1984, the U.S. Army launched the...LWIR Long Wavelength Infrared MAAG Military Assistance Advisory Group MET SAT Meteorology Satellite MHV Miniature Homing Device MICOM Missile Command

Mark XIV Torpedo Case Study

DTIC Science & Technology

2011-02-26

Bureau of Ordnance in the meantime had corresponded with Albert Einstein at Princeton University on a variety of issues including torpedo detonation... Einstein was paid $25/day as a consultant and quickly understood the problem. The contact exploder’s firing pin located in the very front warhead...were finally identified and corrected. In all seriousness, God only knows how many submariners died as a result of those defective torpedoes, which

Trials Against Conqueror Tanks with Additional Ballistic Protection. Part 2: The Use of Large Hollow-Charge Warheads

DTIC Science & Technology

1957-05-01

4 Ears. Ism could not be examined on account of bilateral chronic suppurative otitis media (C. SO.M.). (The middle ear full of thick pus and drum, if...examined on account of chronic suppurative otitis media (C. S.0. K.). (Middle ear full of thick ps.) Would have survived. Driver’s Seat Upper Rabbit

The New START Treaty: Central Limits and Key Provisions

DTIC Science & Technology

2014-04-08

the parties maintained during the life of the treaty. The parties then multiplied...change during the life of the treaty. The parties will not, however, visit each missile to count and calculate the total number of warheads in the force...Unlike the Moscow Treaty, however, the parties will provide and update these numbers every six months during the life of the treaty, rather than

The New START Treaty: Central Limits and Key Provisions

DTIC Science & Technology

2014-08-27

the parties maintained during the life of the treaty. The parties then multiplied...change during the life of the treaty. The parties will not, however, visit each missile to count and calculate the total number of warheads in the ...Unlike the Moscow Treaty, however, the parties will provide and update these numbers every six months during the life of the treaty, rather than

Assessment of the Emerging Biocruise Threat

DTIC Science & Technology

2000-08-01

navigation and guidance system is located in the front; and the fuel and warhead are typically located in the midbody .66 (See Figure 1.) Guidance of a...unitary or submunitions Undetermined Undetermined MUPSOW South Africa Air & ground Conventional/ unitary or submunitions 200+ 2002 Storm Shadow ...replicating agents, bacteria or viruses, or nonreplicating materials, toxins or physiologically active proteins or peptides, that can be produced by living

Strategic Studies Quarterly. Winter 2015

DTIC Science & Technology

2016-09-19

and policy that nurtured it and Amer- ica to greatness. While 600 million people watched Apollo 11 landing on the moon, only 11,000 watched...Business,” Washington Post, 11 February 2013. 64. James R. Clapper, Worldwide Threat Assessment of the US Intelligence Community , state- ment for the...aerospace community united for the “first offset strategy” of integrating nuclear warheads on bombs and missiles, which enabled Pres. Dwight

Microstructure and Dynamic Failure Properties of Freeze-Cast Materials for Thermobaric Warhead Cases

DTIC Science & Technology

2012-12-01

Function LLNL Lawrence Livermore National Laboratory PDF Probability Density Function PMMA Poly(Methyl Methacrylate) RM Reactive Materials SEM...FREEZE CAST MATERIALS Freeze casting technology combines compounds such as aluminum oxide and poly(methyl methacrylate) ( PMMA ) to develop a...Subsequently, the porous structure can be infiltrated with a variety of materials, such as a standard polymer like PMMA . This hybrid material is believed

Combating Terrorism in a Globalized World

DTIC Science & Technology

2002-05-01

warhead is detonated in London or a smallpox outbreak in Tokyo or a nerve agent is introduced into the Washington, DC, subway system. An initiative...and convey a more positive image of the Western world. Furthermore, the civilized world should work together to provide disen- franchised youth...59 Economic growth in developing countries leads to reduced poverty, increased food security, and higher standards of living, including better health

2005 Precision Strike Annual Programs Review

DTIC Science & Technology

2005-04-20

Control Canards (4) Polyurethane Foam Support DPICM (404 M101 Grenades) Warhead Fuze: Electronic Safe & Arm Device (ESAD) UNCLASSIFIED UNCLASSIFIED PF...SYSTEMS: • JASSM: Colonel James Geurts, USAF JASSM PM • ATACMS : Colonel Earnest Harris, USA PM, Precision Fires Rockets & Missiles, PEO Space and...UNCLASSIFIED UNCLASSIFIED Viper Strike Lineage ATACMS Delivered Base BATs Viper Strike SAL Seeker Proof of Principle Demos I & II Hunter-Viper Strike

Reliable classification of high explosive and chemical/biological artillery using acoustic sensors

NASA Astrophysics Data System (ADS)

Desai, Sachi V.; Hohil, Myron E.; Bass, Henry E.; Chambers, Jim

2005-05-01

Feature extraction methods based on the discrete wavelet transform and multiresolution analysis are used to develop a robust classification algorithm that reliably discriminates between conventional and simulated chemical/biological artillery rounds via acoustic signals produced during detonation utilizing a generic acoustic sensor. Based on the transient properties of the signature blast distinct characteristics arise within the different acoustic signatures because high explosive warheads emphasize concussive and shrapnel effects, while chemical/biological warheads are designed to disperse their contents over large areas, therefore employing a slower burning, less intense explosive to mix and spread their contents. The ensuing blast waves are readily characterized by variations in the corresponding peak pressure and rise time of the blast, differences in the ratio of positive pressure amplitude to the negative amplitude, and variations in the overall duration of the resulting waveform. Unique attributes can also be identified that depend upon the properties of the gun tube, projectile speed at the muzzle, and the explosive burn rates of the warhead. The algorithm enables robust classification of various airburst signatures using acoustics. It is capable of being integrated within an existing chemical/biological sensor, a stand-alone generic sensor, or a part of a disparate sensor suite. When emplaced in high-threat areas, this added capability would further provide field personal with advanced battlefield knowledge without the aide of so-called "sniffer" sensors that rely upon air particle information based on direct contact with possible contaminated air. In this work, the discrete wavelet transform is used to extract the predominant components of these characteristics from air burst signatures at ranges exceeding 2km while maintaining temporal sequence of the data to keep relevance to the transient differences of the airburst signatures. Highly reliable discrimination is achieved with a feedforward neural network classifier trained on a feature space derived from the distribution of wavelet coefficients and higher frequency details found within different levels of the multiresolution decomposition the neural network then is capable of classifying new airburst signatures as Chemical/Biological or High Explosive.

Delayed Gamma-ray Spectroscopy for Safeguards Applications

DOE Office of Scientific and Technical Information (OSTI.GOV)

Mozin, Vladimir

The delayed gamma-ray assay technique utilizes an external neutron source (D-D, D-T, or electron accelerator-driven), and high-resolution gamma-ray spectrometers to perform characterization of SNM materials behind shielding and in complex configurations such as a nuclear fuel assembly. High-energy delayed gamma-rays (2.5 MeV and above) observed following the active interrogation, provide a signature for identification of specific fissionable isotopes in a mixed sample, and determine their relative content. Potential safeguards applications of this method are: 1) characterization of fresh and spent nuclear fuel assemblies in wet or dry storage; 2) analysis of uranium enrichment in shielded or non-characterized containers or inmore » the presence of a strong radioactive background and plutonium contamination; 3) characterization of bulk and waste and product streams at SNM processing plants. Extended applications can include warhead confirmation and warhead dismantlement confirmation in the arms control area, as well as SNM diagnostics for the emergency response needs. In FY16 and prior years, the project has demonstrated the delayed gamma-ray measurement technique as a robust SNM assay concept. A series of empirical and modeling studies were conducted to characterize its response sensitivity, develop analysis methodologies, and analyze applications. Extensive experimental tests involving weapons-grade Pu, HEU and depleted uranium samples were completed at the Idaho Accelerator Center and LLNL Dome facilities for various interrogation time regimes and effects of the neutron source parameters. A dedicated delayed gamma-ray response modeling technique was developed and its elements were benchmarked in representative experimental studies, including highresolution gamma-ray measurements of spent fuel at the CLAB facility in Sweden. The objective of the R&D effort in FY17 is to experimentally demonstrate the feasibility of the delayed gamma-ray interrogation of shielded SNM samples with portable neutron sources suitable for field applications.« less

77 FR 9628 - Taking and Importing Marine Mammals: Taking Marine Mammals Incidental to Navy's Mission...

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-17

..., and post-test monitoring for both sonar events. No stranded or injured marine mammals or sea turtles.... The monitoring included two re-test flights; two flights during the test; and one post-test flight... two pre-test flights; one flight during the test; and one post-test flight. Focal follow behavioral...

Overview of Experimental Capabilities - Supersonics

NASA Technical Reports Server (NTRS)

Banks, Daniel W.

2007-01-01

This viewgraph presentation gives an overview of experimental capabilities applicable to the area of supersonic research. The contents include: 1) EC Objectives; 2) SUP.11: Elements; 3) NRA; 4) Advanced Flight Simulator Flexible Aircraft Simulation Studies; 5) Advanced Flight Simulator Flying Qualities Guideline Development for Flexible Supersonic Transport Aircraft; 6) Advanced Flight Simulator Rigid/Flex Flight Control; 7) Advanced Flight Simulator Rapid Sim Model Exchange; 8) Flight Test Capabilities Advanced In-Flight Infrared (IR) Thermography; 9) Flight Test Capabilities In-Flight Schlieren; 10) Flight Test Capabilities CLIP Flow Calibration; 11) Flight Test Capabilities PFTF Flowfield Survey; 12) Ground Test Capabilities Laser-Induced Thermal Acoustics (LITA); 13) Ground Test Capabilities Doppler Global Velocimetry (DGV); 14) Ground Test Capabilities Doppler Global Velocimetry (DGV); and 15) Ground Test Capabilities EDL Optical Measurement Capability (PIV) for Rigid/Flexible Decelerator Models.

The Comparison Of In-Flight Pitot Static Calibration Method By Using Radio Altimeter As Reference with GPS and Tower Fly By Methods On CN235-100 MPA

NASA Astrophysics Data System (ADS)

Derajat; Hariowibowo, Hindawan

2018-04-01

The new proposed In-Flight Pitot Static Calibration Method has been carried out during Development and Qualification of CN235-100 MPA (Military Patrol Aircraft). This method is expected to reduce flight hours, less human resources required, no additional special equipment, simple analysis calculation and finally by using this method it is expected to automatically minimized operational cost. At The Indonesian Aerospace (IAe) Flight Test Center Division, the development and updating of new flight test technique and data analysis method as specially for flight physics test subject are still continued to be developed as long as it safety for flight and give additional value for the industrial side. More than 30 years, Flight Test Data Engineers at The Flight Test center Division work together with the Air Crew (Test Pilots, Co-Pilots, and Flight Test Engineers) to execute the flight test activity with standard procedure for both the existance or development test techniques and test data analysis. In this paper the approximation of mathematical model, data reduction and flight test technique of The In-Flight Pitot Static Calibration by using Radio Altimeter as reference will be described and the test results had been compared with another methods ie. By using Global Position System (GPS) and the traditional method (Tower Fly By Method) which were used previously during this Flight Test Program (Ref. [10]). The flight test data case are using CN235-100 MPA flight test data during development and Qualification Flight Test Program at Cazaux Airport, France, in June-November 2009 (Ref. [2]).

B-52B-008/DTV (Drop Test Vehicle) configuration 1 (with and without fins) flight test results - captive flight and drop test missions

NASA Technical Reports Server (NTRS)

Quade, D. A.

1978-01-01

The B-52B-008 drop test consisted of one takeoff roll to 60 KCAS, two captive flights to accomplish limited safety of flight flutter and structural demonstration testing, and seven drop test flights. Of the seven drop test missions, one flight was aborted due to the failure of the hook mechanism to release the drop test vehicle (DTV); but the other six flights successfully dropped the DTV.

Flight assessment of a large supersonic drone aircraft for research use

NASA Technical Reports Server (NTRS)

Eckstrom, C. V.; Peele, E. L.

1974-01-01

An assessment is made of the capabilities of the BQM-34E supersonic drone aircraft as a test bed research vehicle. This assessment is made based on a flight conducted for the purpose of obtaining flight test measurements of wing loads at various maneuver flight conditions. Flight plan preparation, flight simulation, and conduct of the flight test are discussed along with a presentation of the test data obtained and an evaluation of how closely the flight test followed the test plan.

Orion Launch Abort System Jettison Motor Performance During Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

McCauley, Rachel J.; Davidson, John B.; Winski, Richard G.

2015-01-01

This paper presents an overview of the flight test objectives and performance of the Orion Launch Abort System during Exploration Flight Test-1. Exploration Flight Test-1, the first flight test of the Orion spacecraft, was managed and led by the Orion prime contractor, Lockheed Martin, and launched atop a United Launch Alliance Delta IV Heavy rocket. This flight test was a two-orbit, high-apogee, high-energy entry, low-inclination test mission used to validate and test systems critical to crew safety. This test included the first flight test of the Launch Abort System performing Orion nominal flight mission critical objectives. Although the Orion Program has tested a number of the critical systems of the Orion spacecraft on the ground, the launch environment cannot be replicated completely on Earth. Data from this flight will be used to verify the function of the jettison motor to separate the Launch Abort System from the crew module so it can continue on with the mission. Selected Launch Abort System flight test data is presented and discussed in the paper. Through flight test data, Launch Abort System performance trends have been derived that will prove valuable to future flights as well as the manned space program.

Free Flight Ground Testing of ADEPT in Advance of the Sounding Rocket One Flight Experiment

NASA Technical Reports Server (NTRS)

Smith, B. P.; Dutta, S.

2017-01-01

The Adaptable Deployable Entry and Placement Technology (ADEPT) project will be conducting the first flight test of ADEPT, titled Sounding Rocket One (SR-1), in just two months. The need for this flight test stems from the fact that ADEPT's supersonic dynamic stability has not yet been characterized. The SR-1 flight test will provide critical data describing the flight mechanics of ADEPT in ballistic flight. These data will feed decision making on future ADEPT mission designs. This presentation will describe the SR-1 scientific data products, possible flight test outcomes, and the implications of those outcomes on future ADEPT development. In addition, this presentation will describe free-flight ground testing performed in advance of the flight test. A subsonic flight dynamics test conducted at the Vertical Spin Tunnel located at NASA Langley Research Center provided subsonic flight dynamics data at high and low altitudes for multiple center of mass (CoM) locations. A ballistic range test at the Hypervelocity Free Flight Aerodynamics Facility (HFFAF) located at NASA Ames Research Center provided supersonic flight dynamics data at low supersonic Mach numbers. Execution and outcomes of these tests will be discussed. Finally, a hypothesized trajectory estimate for the SR-1 flight will be presented.

Flight Test Engineering

NASA Technical Reports Server (NTRS)

Pavlock, Kate Maureen

2013-01-01

Although the scope of flight test engineering efforts may vary among organizations, all point to a common theme: flight test engineering is an interdisciplinary effort to test an asset in its operational flight environment. Upfront planning where design, implementation, and test efforts are clearly aligned with the flight test objective are keys to success. This chapter provides a top level perspective of flight test engineering for the non-expert. Additional research and reading on the topic is encouraged to develop a deeper understanding of specific considerations involved in each phase of flight test engineering.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Frye, A.

After decades of diplomatic wrangling, breakthroughs have come on many fronts, both bilateral and multilateral. Not only have Soviets and now Russians joined Americans in agreements to make massive reductions in strategic arms, but the overwhelming majority of nations have signed on to indefinite extension of the Nuclear Nonproliferation Treaty (NPT). Leaders in Ukraine, Kazakstan, and Belarus have greatly contributed to the nonproliferation regime by returning thousands of Soviet nuclear weapons to Russia for safekeeping and elimination, a process to be completed this fall with the departure of the last few warheads from Belarus. The Conventional Forces in Europe Treatymore » has ratified and reinforced the transformation of the military balance on the continent, although the altered political landscape after the collapse of the Soviet empire will require nettlesome changes in its provisions. The long-sought Chemical Weapons Convention should enter into force shortly, and, despite India`s recalcitrance, a comprehensive nuclear test ban enjoys nearly universal support.« less

Rocky Flats Plant: Test bed for transitioning from weapons production mission to environmental restoration, waste management, and economic development missions

DOE Office of Scientific and Technical Information (OSTI.GOV)

Benjamin, A.; Murthy, K.S.; Krenzer, R.W.

1993-01-07

Redirection of Rocky Flats Plant's (RF) mission is an inevitable result of changes in the worldwide social, political, and environmental factors. These changes were exemplified in the cancellation of the W-88 Warhead in January 1992, by the President of the United States. These unprecedented changes have altered the RF's traditional nuclear weapons production mission to the transition mission, i.e., cleanup, preparation for deactivation and decontamination, decommissioning, dismantlement and demolition, and when appropriate, economic development, of the facilities. The purpose of this paper is to describe the essentials of the technical approach and management actions advanced by EG G Rocky Flats,more » Inc., to organize, staff, direct, and control the activities necessary to transition the RF from its historical weapons production mission to the transition mission.« less

Rocky Flats Plant: Test bed for transitioning from weapons production mission to environmental restoration, waste management, and economic development missions

DOE Office of Scientific and Technical Information (OSTI.GOV)

Benjamin, A.; Murthy, K.S.; Krenzer, R.W.

1993-01-07

Redirection of Rocky Flats Plant`s (RF) mission is an inevitable result of changes in the worldwide social, political, and environmental factors. These changes were exemplified in the cancellation of the W-88 Warhead in January 1992, by the President of the United States. These unprecedented changes have altered the RF`s traditional nuclear weapons production mission to the transition mission, i.e., cleanup, preparation for deactivation and decontamination, decommissioning, dismantlement and demolition, and when appropriate, economic development, of the facilities. The purpose of this paper is to describe the essentials of the technical approach and management actions advanced by EG&G Rocky Flats, Inc.,more » to organize, staff, direct, and control the activities necessary to transition the RF from its historical weapons production mission to the transition mission.« less

Dynamic Fracture Behavior of Plastic-Bonded Explosives

NASA Astrophysics Data System (ADS)

Fu, Hua; Li, Jun-Ling; Tan, Duo-Wang; Ifp, Caep Team

2011-06-01

Plastic-Bonded Explosives (PBX) are used as important energetic materials in nuclear or conventional weapons. Arms Warhead in the service process and the ballistic phase, may experience complex process such as long pulse and higher loading, compresson, tension and reciprocating compression - tension, friction with the projectile shell, which would lead to explosive deformation and fracture.And the dynamic deformation and fracture behavior of PBX subsequently affect reaction characteristics and initiation mechanism in explosives, then having influence on explosives safety. The dynamic fracure behavior of PBX are generally complex and not well studied or understood. In this paper, the dynamic fracture of explosives are conducted using a Kolsky bar. The Brazilian test, also known as a indirect tensile test or splitting test, is chosen as the test method. Tensile strength under different strain rates are obtained using quartz crystal embedded in rod end. The dynamic deformation and fracture process are captured in real-time by high-speed digital camera, and the displacement and strain fields distribution before specimen fracture are obtained by digital correlation method. Considering the non-uniform microstructure of explosives,the dynamic fracture behavior of explosive are simulated by discrete element method, the simulation results can reproduce the deformation and fracture process in Brazilian test using a maximum tensile strain criterion.

JPRS Report, Near East & South Asia

DTIC Science & Technology

1988-02-17

Tunisia [THE EGYPTIAN GAZETTE, 4 Jan 88] 2 PALESTINIAN AFFAIRS PLO Affirms CW Intentions [JORDAN TIMES, 13 Jan 88] 2 Economic Effects of Bank...warheads but would only use them as a last resort. /9274 Economic Effects of Bank Reform Appraised 45190011 Algiers EL MOUDHAJID (SUPPLEMENT...resources that they will have to utilize and to optimize in order to successfully shoul- der the effects of economic reform. JPRS-NEA-88-008 17

Weapons Systems, United States Army 1997.

DTIC Science & Technology

1997-01-01

fewer grenades, a new warhead section fuze and a modified center core burster. The XM85 grenade is equipped with a new self -destruct fuze designed to...Liquid Propellant Gun and an automated loading system. Crusader also requires 3 fewer crewmen than previous self -propelled artillery systems. The new ...market, creating new market opportunities for commercial rotocraft and ensuring the continued supremacy of this technol- ogy that is so critical to

Transforming The Munitions And Missile Maintenance Officer Career Field

DTIC Science & Technology

2016-04-01

is a United States Air Force Officer currently attending Air and Space Command College at Maxwell Air Force Base , AL. Maj Edington was previously...INTRODUCTION Since the unauthorized transportation of nuclear warheads from Minot Air Force Base (MAFB) to Barksdale Air Force Base (BAFB) and the mistaken... base .66 These factors coupled with risk-aversion for anything but perfect results during inspections (i.e. zero defects), and the well-established

The United Kingdom: Issues for the United States

DTIC Science & Technology

2007-07-16

of its EU partners than to the United States. For example, like other EU member states, Britain places great emphasis on multilateral... the prospects for the future of the U.S.-UK partnership, especially in the unfolding Brown era. It also describes UK views on political, security...delivery systems for its nuclear warheads since 1963. During the Cold War, the UK served as a vital base for U.S.

77 FR 77043 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2012-12-31

... MK-84 2000 lb General Purpose Bombs; 1,725 MK-82 500 lb General Purpose Bombs; 1,725 BLU-109 Bombs; 3,450 GBU-39 Small Diameter Bombs; 11,500 FMU-139 Fuses; 11,500 FMU-143 Fuses; and 11,500 FMU-152 Fuses... and 1,725 KMU-572 (GBU-38) for MK-82 warheads); 3,450 MK-84 2000 lb General Purpose Bombs; 1,725 MK-82...

Veiled Normalization: The Implications of Japanese Missile Defense

DTIC Science & Technology

2008-09-01

phasizing defensive principles . Si milarly, a s tate that is intent on reg ional hegemony or aggressive expansion will shap e its forces and...1 Mindy Kotler and Daisuke Okuyama. “Japan’s Global Ambivalence.” Foreign Policy, no. 130, (2002): 96-97. 19...the use of nuclear warheads on defensive weapons would be constitutional.23 It bears mention that Japan’s three Non-Nuclear Principles , stating that

Ultra-Fine Highly Energetic Core-Shell Nanoparticles with Triggerable Protective Coatings

DTIC Science & Technology

2013-02-01

volume ratios and strong electronic coupling, which offers higher stored energy densities and decreased warhead size. Current technologies produce nano...aluminum (Al) – the most attractive high-energetic candidate for the use in explosives because of its density and high relative heat of oxide...major breakthrough in the area of explosive materials. II. Project Objectives The overall objective of this research program was to develop a new

Computer Aided Self-Forging Fragment Design,

DTIC Science & Technology

1978-06-01

This value is reached so quickly that HEMP solutions using work hardening and those using only elastic—perfectly plastic formulations are quite...Elastic— Plastic Flow, UCRL—7322 , Lawrence Radiation Laboratory , Livermore , California (1969) . 4. Giroux , E. D . , HEMP Users Manual, UCRL—5l079...Laboratory, the HEMP computer code has been developed to serve as an effective design tool to simplify this task considerably. Using this code, warheads 78 06

Diversified Submarine Weapon Suite: A Systems Engineering Approach

DTIC Science & Technology

2008-12-01

safe distance from the launch platform. The warhead itself is a PBXN -3 explosive-loaded, end-initiated, annular blast/fragment unit, with 194...59 C 18.295 10 3 84 22 0 7 0 79 C 23.165 10 3 84 19 0 0 11 83 D 23.295 10 3 70 24 0 5 5 102 B 28.46 10 3 70 21 0 0 12 106 D 28.37

Warhead Performance Calculations for Threat Hazard Assessment

DTIC Science & Technology

1996-08-01

0.59 PBXN -107 1.41 1.45 0.925 0.924 PBXN -109 1.34 1.44 1.19 0.6 AFX-931 1.16 1.43 1.08 0.23 data AH comb,x mdet,x) mcomb,TNT* &omb,TNT a *AHmmb,m...k] (45) EW = E/(4.610 x 106 ) , explosive yield in TNT equivalents, kg; with E in joules. where E = energy of explosion in consistent units V

Joint Armaments Conference, Exhibition and Firing Demonstration

DTIC Science & Technology

2010-05-20

10195 - Effects of Barrel Length on Sound Measurement, Bore Pressure, and Bullet Velocity, Dr. Philip Dater, Gemtech · 10186 - MEMS S&A...Systems · 10033 - Selectable Effects Warhead Technology Demonstration, Mr. Eric Volkmann, ATK Untitled Document 2010armament.html[3/29/2016 2:19:07...Propellant for Use in 120mm Tank Training Rounds, Mr. Jim Wedwick, ATK · 10001 - Ageing Effects on Performance of Small and Medium Calibre Ammunition

Unmanned Systems in Perspective

DTIC Science & Technology

2014-05-22

sized warhead designed for precision engagement of small targets.56 Medea Benjamin of Code Pink calls it a “robotic suicide bomber . . . an unmanned...Other writers decry a coming age of “ suicide drones,” evidently unaware of the irony of the phrase.125 Admiral Dennis Blair, former US Director of... temptation to meddle, but instant responsiveness, in most cases, is an illusion. The exception to the myth of the “instant kill” further strengthens

Laser agile illumination for object tracking and classification - Feasibility study

NASA Technical Reports Server (NTRS)

Scholl, Marija S.; Vanzyl, Jakob J.; Meinel, Aden B.; Meinel, Marjorie P.; Scholl, James W.

1988-01-01

The 'agile illumination' concept for discrimination between ICBM warheads and decoys involves a two-aperture illumination with coherent light, diffraction of light by propagation, and a resulting interference pattern on the object surface. A scanning two-beam interference pattern illuminates one object at a time; depending on the shape, momentum, spinning, and tumbling characteristics of the interrogated object, different temporal signals will be obtained for different classes of objects.

Irreversible 4-Aminopiperidine Transglutaminase 2 Inhibitors for Huntington's Disease.

PubMed

Prime, Michael E; Brookfield, Frederick A; Courtney, Stephen M; Gaines, Simon; Marston, Richard W; Ichihara, Osamu; Li, Marie; Vaidya, Darshan; Williams, Helen; Pedret-Dunn, Anna; Reed, Laura; Schaertl, Sabine; Toledo-Sherman, Leticia; Beconi, Maria; Macdonald, Douglas; Muñoz-Sanjuan, Ignacio; Dominguez, Celia; Wityak, John

2012-09-13

A new series of potent TG2 inhibitors are reported that employ a 4-aminopiperidine core bearing an acrylamide warhead. We establish the structure-activity relationship of this new series and report on the transglutaminase selectivity and in vitro ADME properties of selected compounds. We demonstrate that the compounds do not conjugate glutathione in an in vitro setting and have superior plasma stability over our previous series.

14 CFR 91.305 - Flight test areas.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Flight test areas. 91.305 Section 91.305... AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Special Flight Operations § 91.305 Flight test areas. No person may flight test an aircraft except over open water, or sparsely populated...

14 CFR 91.305 - Flight test areas.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Flight test areas. 91.305 Section 91.305... AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Special Flight Operations § 91.305 Flight test areas. No person may flight test an aircraft except over open water, or sparsely populated...

14 CFR 91.305 - Flight test areas.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight test areas. 91.305 Section 91.305... AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Special Flight Operations § 91.305 Flight test areas. No person may flight test an aircraft except over open water, or sparsely populated...

Flight Test of GL-1 Glider Half Scale Prototype

NASA Astrophysics Data System (ADS)

Fikri Zulkarnain, Muhammad; Fazlur Rahman, Muhammad; Luthfi Imam Nurhakim, Muhammad; Arifianto, Ony; Mulyanto, Taufiq

2018-04-01

GL-1 is a single-seat mid-performance glider, designed to be Indonesian National Glider. The Glider have been developing since 2014. The development produced a half scale prototype called BL-1, which had accomplished static test in 2016, then followed by first flight test at April 20th 2017, and second flight test at May 21st 2017. The purpose of the flight test was to obtain familiarization of the aircraft, aerodynamics characteristics and flow visualization, with data from flight recorded in FDR. The flight test resulted in two flights with total length of 21 minutes. The data from FDR and flight test documents extracted to analyze the characteristics and behavior of the aircraft during flight test. The aerodynamics characteristic was close to analytical results. The control was good; however, the effectiveness of control surface may need to be further analyzed. The result of the flight test will be used as a reference for further improvements and may need further testing.

From an automated flight-test management system to a flight-test engineer's workstation

NASA Technical Reports Server (NTRS)

Duke, E. L.; Brumbaugh, R. W.; Hewett, M. D.; Tartt, D. M.

1992-01-01

Described here are the capabilities and evolution of a flight-test engineer's workstation (called TEST PLAN) from an automated flight-test management system. The concept and capabilities of the automated flight-test management system are explored and discussed to illustrate the value of advanced system prototyping and evolutionary software development.

Flight Test Series 3: Flight Test Report

NASA Technical Reports Server (NTRS)

Marston, Mike; Sternberg, Daniel; Valkov, Steffi

2015-01-01

This document is a flight test report from the Operational perspective for Flight Test Series 3, a subpart of the Unmanned Aircraft System (UAS) Integration in the National Airspace System (NAS) project. Flight Test Series 3 testing began on June 15, 2015, and concluded on August 12, 2015. Participants included NASA Ames Research Center, NASA Armstrong Flight Research Center, NASA Glenn Research Center, NASA Langley Research center, General Atomics Aeronautical Systems, Inc., and Honeywell. Key stakeholders analyzed their System Under Test (SUT) in two distinct configurations. Configuration 1, known as Pairwise Encounters, was subdivided into two parts: 1a, involving a low-speed UAS ownship and intruder(s), and 1b, involving a high-speed surrogate ownship and intruder. Configuration 2, known as Full Mission, involved a surrogate ownship, live intruder(s), and integrated virtual traffic. Table 1 is a summary of flights for each configuration, with data collection flights highlighted in green. Section 2 and 3 of this report give an in-depth description of the flight test period, aircraft involved, flight crew, and mission team. Overall, Flight Test 3 gathered excellent data for each SUT. We attribute this successful outcome in large part from the experience that was acquired from the ACAS Xu SS flight test flown in December 2014. Configuration 1 was a tremendous success, thanks to the training, member participation, integration/testing, and in-depth analysis of the flight points. Although Configuration 2 flights were cancelled after 3 data collection flights due to various problems, the lessons learned from this will help the UAS in the NAS project move forward successfully in future flight phases.

14 CFR 437.25 - Flight test plan.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Flight test plan. 437.25 Section 437.25... TRANSPORTATION LICENSING EXPERIMENTAL PERMITS Requirements to Obtain an Experimental Permit Flight Test Plan § 437.25 Flight test plan. An applicant must— (a) Describe any flight test program, including estimated...

14 CFR 437.25 - Flight test plan.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Flight test plan. 437.25 Section 437.25... TRANSPORTATION LICENSING EXPERIMENTAL PERMITS Requirements to Obtain an Experimental Permit Flight Test Plan § 437.25 Flight test plan. An applicant must— (a) Describe any flight test program, including estimated...

14 CFR 437.25 - Flight test plan.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Flight test plan. 437.25 Section 437.25... TRANSPORTATION LICENSING EXPERIMENTAL PERMITS Requirements to Obtain an Experimental Permit Flight Test Plan § 437.25 Flight test plan. An applicant must— (a) Describe any flight test program, including estimated...

From an automated flight-test management system to a flight-test engineer's workstation

NASA Technical Reports Server (NTRS)

Duke, E. L.; Brumbaugh, Randal W.; Hewett, M. D.; Tartt, D. M.

1991-01-01

The capabilities and evolution is described of a flight engineer's workstation (called TEST-PLAN) from an automated flight test management system. The concept and capabilities of the automated flight test management systems are explored and discussed to illustrate the value of advanced system prototyping and evolutionary software development.

Fatigue-test acceleration with flight-by-flight loading and heating to simulate supersonic-transport operation

NASA Technical Reports Server (NTRS)

Imig, L. A.; Garrett, L. E.

1973-01-01

Possibilities for reducing fatigue-test time for supersonic-transport materials and structures were studied in tests with simulated flight-by-flight loading. In order to determine whether short-time tests were feasible, the results of accelerated tests (2 sec per flight) were compared with the results of real-time tests (96 min per flight). The effects of design mean stress, the stress range for ground-air-ground cycles, simulated thermal stress, the number of stress cycles in each flight, and salt corrosion were studied. The flight-by-flight stress sequences were applied to notched sheet specimens of Ti-8Al-1Mo-1V and Ti-6Al-4V titanium alloys. A linear cumulative-damage analysis accounted for large changes in stress range of the simulated flights but did not account for the differences between real-time and accelerated tests. The fatigue lives from accelerated tests were generally within a factor of two of the lives from real-time tests; thus, within the scope of the investigation, accelerated testing seems feasible.

Genotoxicity assessment of an energetic propellant compound, 3-nitro-1,2,4-triazol-5-one (NTO).

PubMed

Reddy, Gunda; Song, Jian; Kirby, Paul; Lent, Emily M; Crouse, Lee C B; Johnson, Mark S

2011-02-03

3-Nitro-1,2,4-triazol-5-one (NTO) is an energetic explosive proposed for use in weapon systems, to reduce the sensitivity of warheads. In order to develop toxicity data for safety assessment, we investigated the genotoxicity of NTO, using a battery of genotoxicity tests, which included the Ames test, Chinese Hamster Ovary (CHO) cell chromosome aberration test, L5178Y TK(+/-) mouse lymphoma mutagenesis test and rat micronucleus test. NTO was not mutagenic in the Ames test or in Escherichia coli (WP2uvrA). NTO did not induce chromosomal aberrations in CHO cells, with or without metabolic activation. In the L5178Y TK(+/-) mouse lymphoma mutagenesis test, all of the NTO-treated cultures had mutant frequencies that were similar to the average frequencies of solvent control-treated cultures, indicating a negative result. Confirmatory tests for the three in vitro tests also produced negative results. The potential in vivo clastogenicity and aneugenicity of NTO was evaluated using the rat peripheral blood micronucleus test. NTO was administered by oral gavage to male and female Sprague-Dawley rats for 14 days at doses up to 2g/kg/day. Flow cytometric analysis of peripheral blood demonstrated no significant induction of micronucleated reticulocytes relative to the vehicle control (PEG-200). These studies reveal that NTO was not genotoxic in either in vitro or in vivo tests and suggest a low risk of genetic hazards associated with exposure. Copyright © 2010 Elsevier B.V. All rights reserved.

Space Shuttle Orbiter Approach and Landing Test Evaluation Report. Captive-Active Flight Test Summary

NASA Technical Reports Server (NTRS)

1977-01-01

Captive-active tests consisted of three mated carrier aircraft/Orbiter flights with an active manned Orbiter. The objectives of this series of flights were to (1) verify the separation profile, (2) verify the integrated structure, aerodynamics, and flight control system, (3) verify Orbiter integrated system operations, and (4) refine and finalize carrier aircraft, Orbiter crew, and ground procedures in preparation for free flight tests. A summary description of the flights is presented with assessments of flight test requirements, and of the performance operations, and of significant flight anomalies is included.

The Presidential Nuclear Initiatives of 1991-1992

DTIC Science & Technology

2012-09-01

and/or warhead downloading ), and use START Treaty procedures to implement it. This was the first serious public proposal to emerge from a longstanding...discussion to relevant technolo- gies , rather than to venture into more sensitive areas of nuclear weapons practice and procedures.56 Gorbachev did not...States. The same basic points were made by 11 republic heads in the Alma- Ata Declaration on December 21.58 On December 25, Gorbachev submitted his

Tracking Next-Generation Automatic Identification Technology (AIT) into 2035

DTIC Science & Technology

2010-04-01

Non-proliferation and Treaty inspections  Shielding / EMI issues  Security/Integrity/Encryption  Taiwan Shipment Fact Sheet http...followed the technical data, but had no idea that they had a live nuclear warhead. While the nuclear ALCM was loaded on the munitions trailer , the...three-man team continued to assemble the other seven ALCMs. As the end of shift neared, all eight ALCMs were loaded on the munitions trailers and the

A Shotline Method for Modeling Projectile Geometry

DTIC Science & Technology

1986-06-01

by block number) GIFT Target Description Vulnerability Analysis COMGEOM Shotlining Warhead Lethality MISFIR 20. ABSTRACT fConfteue an r»r»r«» eUm It rt...target interaction is centered upon the program MISFIR, written in CDC Fortran 5. MISFIR is built on the formalisms of the GIFT (Geometric...a ray-tracing subroutine added to GIFT (viz. SHOTCYL); MISFIR itself, together with its subprograms; and an application program, called FUZES, which

Design Manual for Impact Damage Tolerant Aircraft Structure

DTIC Science & Technology

1981-10-01

controlled AAA guns having a very high rate of fire, is a significant threat. The final type of non -exploding military projectile-missile warhead fragments...8217~ AGARD-AG-238 NORTH 4TLANTIC TR!EATY ORGANIZATION ADVISORY GROUP FOR AERGSPACE RESEARCH AND DEVELOPMENT (ORGANISATION DU TRAITE DE L’ATLANTIQUE NORD...within the Working Group on Impact Damage Tolerance of Structures and also at the Specialists’ Meeting held in Ankara in September 1975 (see AGARD

JPRS Report, China

DTIC Science & Technology

1987-12-31

inconsistent with Japan’s declared policy of opening up her markets. JPRS-CAR-87-061 31 December 1987 28 ECONOMIC 2. The "three lows "— low oil prices, the...intermediate- range warheads in Soviet Asia and the United States, respectively. But the United States and some Western European nations soon demanded...Union insisted on keeping 100 intermediate- range guided missiles in Asia while balking at the U.S. demand that it be allowed to deploy an equal

A CD276 Antibody Guided Missile with One Warhead and Two Targets: The Tumor and Its Vasculature.

PubMed

Khan, Kabir A; Kerbel, Robert S

2017-04-10

In this issue of Cancer Cell, Seaman et al. demonstrate that antibody drug conjugates (ADCs) against CD276 expressed by tumor cells and tumor vasculature have promising anti-tumor activity while showing little toxicity. Importantly, these agents have the potential to target both angiogenic vessels and non-angiogenic vessels co-opted by tumor cells. Copyright © 2017 Elsevier Inc. All rights reserved.

Regional Power Ballistic Missiles. An Emerging Threat to Deployed US forces?

DTIC Science & Technology

1990-05-01

packaging and dispensing submunitions are straightforward: the MLRS submunitions are simply nestled in polyurethane foam ; and cluster munitions such as the...several U.S. mobile ballistic missile systems, both ground-launched and air-launched. The Army Tactical Missile System ( ATACMS ), a mobile TBM...weight class have also been presented. (99:185-187) Warheads with "light" submunitions are used on the US LANCE and Army Tactical Missile System ( ATACMS

Air-to-air radar flight testing

NASA Astrophysics Data System (ADS)

Scott, Randall E.

1988-06-01

This volume in the AGARD Flight Test Techniques Series describes flight test techniques, flight test instrumentation, ground simulation, data reduction and analysis methods used to determine the performance characteristics of a modern air-to-air (a/a) radar system. Following a general coverage of specification requirements, test plans, support requirements, development and operational testing, and management information systems, the report goes into more detailed flight test techniques covering a/a radar capabilities of: detection, manual acquisition, automatic acquisition, tracking a single target, and detection and tracking of multiple targets. There follows a section on additional flight test considerations such as electromagnetic compatibility, electronic countermeasures, displays and controls, degraded and backup modes, radome effects, environmental considerations, and use of testbeds. Other sections cover ground simulation, flight test instrumentation, and data reduction and analysis. The final sections deal with reporting and a discussion of considerations for the future and how they may affect radar flight testing.

Flight Test of the F/A-18 Active Aeroelastic Wing Airplane

NASA Technical Reports Server (NTRS)

Clarke, Robert; Allen, Michael J.; Dibley, Ryan P.; Gera, Joseph; Hodgkinson, John

2005-01-01

Successful flight-testing of the Active Aeroelastic Wing airplane was completed in March 2005. This program, which started in 1996, was a joint activity sponsored by NASA, Air Force Research Laboratory, and industry contractors. The test program contained two flight test phases conducted in early 2003 and early 2005. During the first phase of flight test, aerodynamic models and load models of the wing control surfaces and wing structure were developed. Design teams built new research control laws for the Active Aeroelastic Wing airplane using these flight-validated models; and throughout the final phase of flight test, these new control laws were demonstrated. The control laws were designed to optimize strategies for moving the wing control surfaces to maximize roll rates in the transonic and supersonic flight regimes. Control surface hinge moments and wing loads were constrained to remain within hydraulic and load limits. This paper describes briefly the flight control system architecture as well as the design approach used by Active Aeroelastic Wing project engineers to develop flight control system gains. Additionally, this paper presents flight test techniques and comparison between flight test results and predictions.

Conduct and Results of YF-16 RPRV Stall/Spin Drop Model Tests

DTIC Science & Technology

1977-04-01

Bomb Recovery System Tests Iron Bird Recovery System Tests Captive Flights Typical Flight Operations Flight Planning and Pilot Training...helicopter tow qualification test, one model tow qualification test, three Iron Bird parachute recovery system verification tests, three captive tests...Corresponding Full-Scale YF-16 Altitude -Reference 1: Woodcock , Robert J., Some Notes on Free-Flight Model Seal- ing, AFFDL-TM-73-123-FCC, Air Force Flight

Automated flight test management system

NASA Technical Reports Server (NTRS)

Hewett, M. D.; Tartt, D. M.; Agarwal, A.

1991-01-01

The Phase 1 development of an automated flight test management system (ATMS) as a component of a rapid prototyping flight research facility for artificial intelligence (AI) based flight concepts is discussed. The ATMS provides a flight engineer with a set of tools that assist in flight test planning, monitoring, and simulation. The system is also capable of controlling an aircraft during flight test by performing closed loop guidance functions, range management, and maneuver-quality monitoring. The ATMS is being used as a prototypical system to develop a flight research facility for AI based flight systems concepts at NASA Ames Dryden.

Digital Fly-By-Wire Flight Control Validation Experience

NASA Technical Reports Server (NTRS)

Szalai, K. J.; Jarvis, C. R.; Krier, G. E.; Megna, V. A.; Brock, L. D.; Odonnell, R. N.

1978-01-01

The experience gained in digital fly-by-wire technology through a flight test program being conducted by the NASA Dryden Flight Research Center in an F-8C aircraft is described. The system requirements are outlined, along with the requirements for flight qualification. The system is described, including the hardware components, the aircraft installation, and the system operation. The flight qualification experience is emphasized. The qualification process included the theoretical validation of the basic design, laboratory testing of the hardware and software elements, systems level testing, and flight testing. The most productive testing was performed on an iron bird aircraft, which used the actual electronic and hydraulic hardware and a simulation of the F-8 characteristics to provide the flight environment. The iron bird was used for sensor and system redundancy management testing, failure modes and effects testing, and stress testing in many cases with the pilot in the loop. The flight test program confirmed the quality of the validation process by achieving 50 flights without a known undetected failure and with no false alarms.

Initial Flight Test of the Production Support Flight Control Computers at NASA Dryden Flight Research Center

NASA Technical Reports Server (NTRS)

Carter, John; Stephenson, Mark

1999-01-01

The NASA Dryden Flight Research Center has completed the initial flight test of a modified set of F/A-18 flight control computers that gives the aircraft a research control law capability. The production support flight control computers (PSFCC) provide an increased capability for flight research in the control law, handling qualities, and flight systems areas. The PSFCC feature a research flight control processor that is "piggybacked" onto the baseline F/A-18 flight control system. This research processor allows for pilot selection of research control law operation in flight. To validate flight operation, a replication of a standard F/A-18 control law was programmed into the research processor and flight-tested over a limited envelope. This paper provides a brief description of the system, summarizes the initial flight test of the PSFCC, and describes future experiments for the PSFCC.

Ion beam plume and efflux characterization flight experiment study. [space shuttle payload

NASA Technical Reports Server (NTRS)

Sellen, J. M., Jr.; Zafran, S.; Cole, A.; Rosiak, G.; Komatsu, G. K.

1977-01-01

A flight experiment and flight experiment package for a shuttle-borne flight test of an 8-cm mercury ion thruster was designed to obtain charged particle and neutral particle material transport data that cannot be obtained in conventional ground based laboratory testing facilities. By the use of both ground and space testing of ion thrusters, the flight worthiness of these ion thrusters, for other spacecraft applications, may be demonstrated. The flight experiment definition for the ion thruster initially defined a broadly ranging series of flight experiments and flight test sensors. From this larger test series and sensor list, an initial flight test configuration was selected with measurements in charged particle material transport, condensible neutral material transport, thruster internal erosion, ion beam neutralization, and ion thrust beam/space plasma electrical equilibration. These measurement areas may all be examined for a seven day shuttle sortie mission and for available test time in the 50 - 100 hour period.

ACAS-Xu Initial Self-Separation Flight Tests

NASA Technical Reports Server (NTRS)

Marston, Mike; Baca, Gabe

2015-01-01

The purpose of this flight test report is to document and report the details of the ACAS Xu (Airborne Collision Avoidance System For Unmanned Aircraft) / Self-Separation flight test series performed at Edwards AFB from November to December of 2014. Included in this document are details about participating aircraft, aircrew, mission crew, system configurations, flight data, flight execution, flight summary, test results, and lessons learned.

14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Flight instruction; Simulated instrument flight and certain flight tests. 91.109 Section 91.109 Aeronautics and Space FEDERAL AVIATION... OPERATING AND FLIGHT RULES Flight Rules General § 91.109 Flight instruction; Simulated instrument flight and...

14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Flight instruction; Simulated instrument flight and certain flight tests. 91.109 Section 91.109 Aeronautics and Space FEDERAL AVIATION... OPERATING AND FLIGHT RULES Flight Rules General § 91.109 Flight instruction; Simulated instrument flight and...

14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Flight instruction; Simulated instrument flight and certain flight tests. 91.109 Section 91.109 Aeronautics and Space FEDERAL AVIATION... OPERATING AND FLIGHT RULES Flight Rules General § 91.109 Flight instruction; Simulated instrument flight and...

14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Flight instruction; Simulated instrument flight and certain flight tests. 91.109 Section 91.109 Aeronautics and Space FEDERAL AVIATION... OPERATING AND FLIGHT RULES Flight Rules General § 91.109 Flight instruction; Simulated instrument flight and...

14 CFR 91.109 - Flight instruction; Simulated instrument flight and certain flight tests.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Flight instruction; Simulated instrument flight and certain flight tests. 91.109 Section 91.109 Aeronautics and Space FEDERAL AVIATION... OPERATING AND FLIGHT RULES Flight Rules General § 91.109 Flight instruction; Simulated instrument flight and...

Dynamic stability and handling qualities tests on a highly augmented, statically unstable airplane

NASA Technical Reports Server (NTRS)

Gera, Joseph; Bosworth, John T.

1987-01-01

Initial envelope clearance and subsequent flight testing of a new, fully augmented airplane with an extremely high degree of static instability can place unusual demands on the flight test approach. Previous flight test experience with these kinds of airplanes is very limited or nonexistent. The safe and efficient flight testing may be further complicated by a multiplicity of control effectors that may be present on this class of airplanes. This paper describes some novel flight test and analysis techniques in the flight dynamics and handling qualities area. These techniques were utilized during the initial flight envelope clearance of the X-29A aircraft and were largely responsible for the completion of the flight controls clearance program without any incidents or significant delays.

Space shuttle orbiter test flight series

NASA Technical Reports Server (NTRS)

Garrett, D.; Gordon, R.; Jackson, R. B.

1977-01-01

The proposed studies on the space shuttle orbiter test taxi runs and captive flight tests were set forth. The orbiter test flights, the approach and landing tests (ALT), and the ground vibration tests were cited. Free flight plans, the space shuttle ALT crews, and 747 carrier aircraft crew were considered.

Crew Exploration Vehicle Launch Abort System Flight Test Overview

NASA Technical Reports Server (NTRS)

Williams-Hayes, Peggy S.

2007-01-01

The Constellation program is an organization within NASA whose mission is to create the new generation of spacecraft that will replace the Space Shuttle after its planned retirement in 2010. In the event of a catastrophic failure on the launch pad or launch vehicle during ascent, the successful use of the launch abort system will allow crew members to escape harm. The Flight Test Office is the organization within the Constellation project that will flight-test the launch abort system on the Orion crew exploration vehicle. The Flight Test Office has proposed six tests that will demonstrate the use of the launch abort system. These flight tests will be performed at the White Sands Missile Range in New Mexico and are similar in nature to the Apollo Little Joe II tests performed in the 1960s. An overview of the launch abort system flight tests for the Orion crew exploration vehicle is given. Details on the configuration of the first pad abort flight test are discussed. Sample flight trajectories for two of the six flight tests are shown.

Determination of UAV pre-flight Checklist for flight test purpose using qualitative failure analysis

NASA Astrophysics Data System (ADS)

Hendarko; Indriyanto, T.; Syardianto; Maulana, F. A.

2018-05-01

Safety aspects are of paramount importance in flight, especially in flight test phase. Before performing any flight tests of either manned or unmanned aircraft, one should include pre-flight checklists as a required safety document in the flight test plan. This paper reports on the development of a new approach for determination of pre-flight checklists for UAV flight test based on aircraft’s failure analysis. The Lapan’s LSA (Light Surveillance Aircraft) is used as a study case, assuming this aircraft has been transformed into the unmanned version. Failure analysis is performed on LSA using fault tree analysis (FTA) method. Analysis is focused on propulsion system and flight control system, which fail of these systems will lead to catastrophic events. Pre-flight checklist of the UAV is then constructed based on the basic causes obtained from failure analysis.

Navigation and flight director guidance for the NASA/FAA helicopter MLS curved approach flight test program

NASA Technical Reports Server (NTRS)

Phatak, A. V.; Lee, M. G.

1985-01-01

The navigation and flight director guidance systems implemented in the NASA/FAA helicopter microwave landing system (MLS) curved approach flight test program is described. Flight test were conducted at the U.S. Navy's Crows Landing facility, using the NASA Ames UH-lH helicopter equipped with the V/STOLAND avionics system. The purpose of these tests was to investigate the feasibility of flying complex, curved and descending approaches to a landing using MLS flight director guidance. A description of the navigation aids used, the avionics system, cockpit instrumentation and on-board navigation equipment used for the flight test is provided. Three generic reference flight paths were developed and flown during the test. They were as follows: U-Turn, S-turn and Straight-In flight profiles. These profiles and their geometries are described in detail. A 3-cue flight director was implemented on the helicopter. A description of the formulation and implementation of the flight director laws is also presented. Performance data and analysis is presented for one pilot conducting the flight director approaches.

Pegasus air-launched space booster flight test program

NASA Astrophysics Data System (ADS)

Elias, Antonio L.; Knutson, Martin A.

1995-03-01

Pegasus is a satellite-launching space rocket dropped from a B52 carrier aircraft instead of launching vertically from a ground pad. Its three-year, privately-funded accelerated development was carried out under a demanding design-to-nonrecurring cost methodology, which imposed unique requirements on its flight test program, such as the decision not to drop an inert model from the carrier aircraft; the number and type of captive and free-flight tests; the extent of envelope exploration; and the decision to combine test and operational orbital flights. The authors believe that Pegasus may be the first vehicle where constraints in the number and type of flight tests to be carried out actually influenced the design of the vehicle. During the period November 1989 to February of 1990 a total of three captive flight tests were conducted, starting with a flutter clearing flight and culminating in a complete drop rehearsal. Starting on April 5, 1990, two combination test/operational flights were conducted. A unique aspect of the program was the degree of involvement of flight test personnel in the early design of the vehicle and, conversely, of the design team in flight testing and early flight operations. Various lessons learned as a result of this process are discussed throughout this paper.

HIFIRE Flight 2 Overview and Status Update 2011

NASA Technical Reports Server (NTRS)

Jackson, Kevin R.; Gruber, Mark R.; Buccellato, Salvatore

2011-01-01

A collaborative international effort, the Hypersonic International Flight Research Experimentation (HIFiRE) Program aims to study basic hypersonic phenomena through flight experimentation. HIFiRE Flight 2 teams the United States Air Force Research Lab (AFRL), NASA, and the Australian Defence Science and Technology Organisation (DSTO). Flight 2 will develop an alternative test technique for acquiring high enthalpy scramjet flight test data, allowing exploration of accelerating hydrocarbon-fueled scramjet performance and dual-to-scram mode transition up to and beyond Mach 8 flight. The generic scramjet flowpath is research quality and the test fuel is a simple surrogate for an endothermically cracked liquid hydrocarbon fuel. HIFiRE Flight 2 will be a first of its kind in contribution to scramjets. The HIFiRE program builds upon the HyShot and HYCAUSE programs and aims to leverage the low-cost flight test technique developed in those programs. It will explore suppressed trajectories of a sounding rocket propelled test article and their utility in studying ramjet-scramjet mode transition and flame extinction limits research. This paper describes the overall scramjet flight test experiment mission goals and objectives, flight test approach and strategy, ground test and analysis summary, development status and project schedule. A successful launch and operation will present to the scramjet community valuable flight test data in addition to a new tool, and vehicle, with which to explore high enthalpy scramjet technologies.

The NASA super pressure balloon - A path to flight

NASA Astrophysics Data System (ADS)

Cathey, H. M.

2009-07-01

The National Aeronautics and Space Administration's Balloon Program Office has invested significant time and effort in extensive ground testing of model super pressure balloons. The testing path has been developed as an outgrowth of the results of the super pressure balloon test flight in 2006. Summary results of the June 2006 super pressure test flight from Kiruna, Sweden are presented including the balloon performance and "lessons learned". This balloons flight performance exceeded expectations, but did not fully deploy. The flight was safely terminated by command. The results of this test flight refocused the project's efforts toward additional ground testing and analysis; a path to flight. A series of small 4 m diameter models were made and tested to further explore the deployment and structural capabilities of the balloons and materials. A series of ˜27 m model balloons were successfully tested indoors. These balloons successfully replicated the cleft seen in the Sweden flight, explored the deployment trade space to help characterize better design approaches, and demonstrated an acceptable fix to the deployment issue. Photogrammetry was employed during these ˜27 m model tests to help characterize both the balloon and gore shape evolution under pressurization. A ˜8.5 m ground model was used to explore the design and materials performance. Results of these tests will be presented. A general overview of some of the other project advancements made related to demonstrating the strain arresting nature of the proposed design, materials and analysis work will also be presented. All of this work has prepared a clear path toward a renewed round of test flights. This paper will give an overview of the development approach pursued for this super pressure balloon development. A description of the balloon design, including the modifications made as a result of the lessons learned, is presented. A short deployment test flight of the National Aeronautics and Space Administration's super pressure balloon took place in June 2008. This flight was from Ft. Sumner, New Mexico. Preliminary results of this flight are presented. Future plans for both ground testing and additional test flights are also presented. Goals of the future test flights, which are staged in increments of increasing suspended load and altitude, are presented. This includes the projected balloon volumes, payload capabilities, test flight locations, and proposed flight schedule.

Aeroelastic Deformation: Adaptation of Wind Tunnel Measurement Concepts to Full-Scale Vehicle Flight Testing

NASA Technical Reports Server (NTRS)

Burner, Alpheus W.; Lokos, William A.; Barrows, Danny A.

2005-01-01

The adaptation of a proven wind tunnel test technique, known as Videogrammetry, to flight testing of full-scale vehicles is presented. A description is presented of the technique used at NASA's Dryden Flight Research Center for the measurement of the change in wing twist and deflection of an F/A-18 research aircraft as a function of both time and aerodynamic load. Requirements for in-flight measurements are compared and contrasted with those for wind tunnel testing. The methodology for the flight-testing technique and differences compared to wind tunnel testing are given. Measurement and operational comparisons to an older in-flight system known as the Flight Deflection Measurement System (FDMS) are presented.

The chocolate-colored expanse of Rogers Dry Lake frames the sleek lines of the Boeing / NASA X-48B subscale demonstrator during a test flight at Edwards AFB

NASA Image and Video Library

2007-08-14

Boeing Phantom Works' subscale Blended Wing Body technology demonstration aircraft began its initial flight tests from NASA's Dryden Flight Research Center at Edwards Air Force Base, Calif. in the summer of 2007. The 8.5 percent dynamically scaled unmanned aircraft, designated the X-48B by the Air Force, is designed to mimic the aerodynamic characteristics of a full-scale large cargo transport aircraft with the same blended wing body shape. The initial flight tests focused on evaluation of the X-48B's low-speed flight characteristics and handling qualities. About 25 flights were planned to gather data in these low-speed flight regimes. Based on the results of the initial flight test series, a second set of flight tests was planned to test the aircraft's low-noise and handling characteristics at transonic speeds.

Synthesis of Bis(1-Methyl-3-Propyl-4-Nitro)imidazolium Dodecahydrododecaborate and Bis(1-Methyl-3-Propyl-5-Nitro)imidazolium Dodecahydrododecaborate Salts: A New Class of Energetic Fuels

DTIC Science & Technology

2013-02-01

AND ENGINEERING CENTER Munitions Engineering Technology Center Picatinny Arsenal, New Jersey The views, opinions, and/or...ORGANIZATION NAME(S) AND ADDRESS(ES) U.S. Army ARDEC, METC Energetics, Warheads & Manufacturing Technology Directorate (RDAR-MEE-W) Picatinny Arsenal, NJ...crystal x-ray diffraction, Fourier transform infrared ( FTIR ), melting points, and densities - are provided along with thermal gravimetric analysis of

Soviet-West European Relations: Recent Trends and Near-Term Prospects.

DTIC Science & Technology

1986-03-01

chilly reception from the Soviet leadership. Indeed, his Soviet hosts reminded him that the volcanic destruction of Pompeii paled in comparison with a...single nuclear warhead, and are reported to have threatened that "we will turn Italy into a Pompeii " if Italy contin- ued with INF deployments on...threatens to turn Italy "into a Pompeii " May 7, 1984 Soviet Union announces decision to boycott Olympics May 14, 1984 Soviet Union announces movement of

Investigation of a Passive, Temporal, Neutron Monitoring System that Functions within the Confines of Start I

DTIC Science & Technology

2003-03-01

was appreciated and their expertise was invaluable. I would also like to thank laboratory technician, Mr. Eric Taylor, whose assistance, skill...Sagdeev, “Detecting Nuclear Warheads,” in Reversing the Arms Race: How to Achieve and Verify Deep Reductions in the Nuclear Arsenals. Ed. F. von ... Hippel and R.Z. Sagdeev. New York: Gordon and Breach Science Publishers, 1990 7) Brigman, Charles J. Introduction To The Physics of Nuclear Weapon

Techniques for SMM/THz Chemical Analysis: Investigations and Exploitation of the Large Molecule Limit

DTIC Science & Technology

2014-03-03

Society of America, (12 2012): 2643. doi: Christopher F. Neese, Ivan R. Medvedev, Grant M. Plummer, Aaron J. Frank, Christopher D. Ball, Frank C. De...NCNCS in view of quantum monodromy, Physical Chem Chem Physics, (02 2010): . doi: Ivan R. Medvedev, Christopher F. Neese, Grant M. Plummer, Frank C...Christopher F. Neese, Frank C. De Lucia, Ivan R. Medvedev, Bob D. Guenther . Terahertz Signature Modeling for Kill Assessment and Warhead Materials

The Forgotten Service: Determining the US Army’s Role in Shaping American Strategy in the Asia-Pacific Region

DTIC Science & Technology

2014-06-01

The Limits of Air Power: The American Bombing of North Vietnam (Lincoln: University of Nebraska Press, 2006, 43. 93 Russell F. Weigley, The...Korea’s bombardment of Yeonpyong, its construction of new uranium enrichment facilities, and development of nuclear warheads and missiles.23 The...89. Weigley, Russell F. The American Way of War: A History of United States Military Strategy and Policy. Bloomington: Indiana University Press

DOE Office of Scientific and Technical Information (OSTI.GOV)

Bunch, Kyle J.; Williams, Laura S.; Jones, Anthony M.

The 2010 ratification of the New START Treaty has been widely regarded as a noteworthy national security achievement for both the Obama administration and the Medvedev-Putin regime, but deeper cuts are envisioned under future arms control regimes. Future verification needs will include monitoring the storage of warhead components and fissile materials and verifying dismantlement of warheads, pits, secondaries, and other materials. From both the diplomatic and technical perspectives, verification under future arms control regimes will pose new challenges. Since acceptable verification technology must protect sensitive design information and attributes, non-nuclear non-sensitive signatures may provide a significant verification tool without themore » use of additional information barriers. The use of electromagnetic signatures to monitor nuclear material storage containers is a promising technology with the potential to fulfill these challenging requirements. Research performed at Pacific Northwest National Laboratory (PNNL) has demonstrated that low frequency electromagnetic signatures of sealed metallic containers can be used to confirm the presence of specific components on a “yes/no” basis without revealing classified information. Arms control inspectors might use this technique to verify the presence or absence of monitored items, including both nuclear and non-nuclear materials. Although additional research is needed to study signature aspects such as uniqueness and investigate container-specific scenarios, the technique potentially offers a rapid and cost-effective tool to verify reduction and dismantlement of U.S. and Russian nuclear weapons.« less

Orion Pad Abort 1 Flight Test: Simulation Predictions Versus Flight Data

NASA Technical Reports Server (NTRS)

Stillwater, Ryan Allanque; Merritt, Deborah S.

2011-01-01

The presentation covers the pre-flight simulation predictions of the Orion Pad Abort 1. The pre-flight simulation predictions are compared to the Orion Pad Abort 1 flight test data. Finally the flight test data is compared to the updated simulation predictions, which show a ove rall improvement in the accuracy of the simulation predictions.

Flight and Integrated Vehicle Testing: Laying the Groundwork for the Next Generation of Space Exploration Launch Vehicles

NASA Technical Reports Server (NTRS)

Taylor, J. L.; Cockrell, C. E.

2009-01-01

Integrated vehicle testing will be critical to ensuring proper vehicle integration of the Ares I crew launch vehicle and Ares V cargo launch vehicle. The Ares Projects, based at Marshall Space Flight Center in Alabama, created the Flight and Integrated Test Office (FITO) as a separate team to ensure that testing is an integral part of the vehicle development process. As its name indicates, FITO is responsible for managing flight testing for the Ares vehicles. FITO personnel are well on the way toward assembling and flying the first flight test vehicle of Ares I, the Ares I-X. This suborbital development flight will evaluate the performance of Ares I from liftoff to first stage separation, testing flight control algorithms, vehicle roll control, separation and recovery systems, and ground operations. Ares I-X is now scheduled to fly in summer 2009. The follow-on flight, Ares I-Y, will test a full five-segment first stage booster and will include cryogenic propellants in the upper stage, an upper stage engine simulator, and an active launch abort system. The following flight, Orion 1, will be the first flight of an active upper stage and upper stage engine, as well as the first uncrewed flight of an Orion spacecraft into orbit. The Ares Projects are using an incremental buildup of flight capabilities prior to the first operational crewed flight of Ares I and the Orion crew exploration vehicle in 2015. In addition to flight testing, the FITO team will be responsible for conducting hardware, software, and ground vibration tests of the integrated launch vehicle. These efforts will include verifying hardware, software, and ground handling interfaces. Through flight and integrated testing, the Ares Projects will identify and mitigate risks early as the United States prepares to take its next giant leaps to the Moon and beyond.

Development and Evaluation of a Performance Modeling Flight Test Approach Based on Quasi Steady-State Maneuvers

NASA Technical Reports Server (NTRS)

Yechout, T. R.; Braman, K. B.

1984-01-01

The development, implementation and flight test evaluation of a performance modeling technique which required a limited amount of quasisteady state flight test data to predict the overall one g performance characteristics of an aircraft. The concept definition phase of the program include development of: (1) the relationship for defining aerodynamic characteristics from quasi steady state maneuvers; (2) a simplified in flight thrust and airflow prediction technique; (3) a flight test maneuvering sequence which efficiently provided definition of baseline aerodynamic and engine characteristics including power effects on lift and drag; and (4) the algorithms necessary for cruise and flight trajectory predictions. Implementation of the concept include design of the overall flight test data flow, definition of instrumentation system and ground test requirements, development and verification of all applicable software and consolidation of the overall requirements in a flight test plan.

Development and flight test of an experimental maneuver autopilot for a highly maneuverable aircraft

NASA Technical Reports Server (NTRS)

Duke, Eugene L.; Jones, Frank P.; Roncoli, Ralph B.

1986-01-01

This report presents the development of an experimental flight test maneuver autopilot (FTMAP) for a highly maneuverable aircraft. The essence of this technique is the application of an autopilot to provide precise control during required flight test maneuvers. This newly developed flight test technique is being applied at the Dryden Flight Research Facility of NASA Ames Research Center. The FTMAP is designed to increase the quantity and quality of data obtained in test flight. The technique was developed and demonstrated on the highly maneuverable aircraft technology (HiMAT) vehicle. This report describes the HiMAT vehicle systems, maneuver requirements, FTMAP development process, and flight results.

Development of load spectra for Airbus A330/A340 full scale fatigue tests

NASA Technical Reports Server (NTRS)

Schmidt, H.-J.; Nielsen, Thomas

1994-01-01

For substantiation of the recently certified medium range Airbus A330 and long range A340 the full scale fatigue tests are in progress. The airframe structures of both aircraft types are tested by one set of A340 specimens. The development of the fatigue test spectra for the two major test specimens which are the center fuselage and wing test and the rear fuselage test is described. The applied test load spectra allow a realistic simulation of flight, ground and pressurization loads and the finalization of the tests within the pre-defined test period. The paper contains details about the 1 g and incremental flight and ground loads and the establishment of the flight-by-flight test program, i.e., the definition of flight types, distribution of loads within the flights and randomization of flight types in repeated blocks. Special attention is given to procedures applied for acceleration of the tests, e.g. omission of lower spectrum loads and a general increase of all loads by ten percent.

The development of a Flight Test Engineer's Workstation for the Automated Flight Test Management System

NASA Technical Reports Server (NTRS)

Tartt, David M.; Hewett, Marle D.; Duke, Eugene L.; Cooper, James A.; Brumbaugh, Randal W.

1989-01-01

The Automated Flight Test Management System (ATMS) is being developed as part of the NASA Aircraft Automation Program. This program focuses on the application of interdisciplinary state-of-the-art technology in artificial intelligence, control theory, and systems methodology to problems of operating and flight testing high-performance aircraft. The development of a Flight Test Engineer's Workstation (FTEWS) is presented, with a detailed description of the system, technical details, and future planned developments. The goal of the FTEWS is to provide flight test engineers and project officers with an automated computer environment for planning, scheduling, and performing flight test programs. The FTEWS system is an outgrowth of the development of ATMS and is an implementation of a component of ATMS on SUN workstations.

The use of an automated flight test management system in the development of a rapid-prototyping flight research facility

NASA Technical Reports Server (NTRS)

Duke, Eugene L.; Hewett, Marle D.; Brumbaugh, Randal W.; Tartt, David M.; Antoniewicz, Robert F.; Agarwal, Arvind K.

1988-01-01

An automated flight test management system (ATMS) and its use to develop a rapid-prototyping flight research facility for artificial intelligence (AI) based flight systems concepts are described. The ATMS provides a flight test engineer with a set of tools that assist in flight planning and simulation. This system will be capable of controlling an aircraft during the flight test by performing closed-loop guidance functions, range management, and maneuver-quality monitoring. The rapid-prototyping flight research facility is being developed at the Dryden Flight Research Facility of the NASA Ames Research Center (Ames-Dryden) to provide early flight assessment of emerging AI technology. The facility is being developed as one element of the aircraft automation program which focuses on the qualification and validation of embedded real-time AI-based systems.

Orion Launch Abort System Performance on Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

McCauley, R.; Davidson, J.; Gonzalez, Guillermo

2015-01-01

This paper will present an overview of the flight test objectives and performance of the Orion Launch Abort System during Exploration Flight Test-1. Exploration Flight Test-1, the first flight test of the Orion spacecraft, was managed and led by the Orion prime contractor, Lockheed Martin, and launched atop a United Launch Alliance Delta IV Heavy rocket. This flight test was a two-orbit, high-apogee, high-energy entry, low-inclination test mission used to validate and test systems critical to crew safety. This test included the first flight test of the Launch Abort System preforming Orion nominal flight mission critical objectives. NASA is currently designing and testing the Orion Multi-Purpose Crew Vehicle (MPCV). Orion will serve as NASA's new exploration vehicle to carry astronauts to deep space destinations and safely return them to earth. The Orion spacecraft is composed of four main elements: the Launch Abort System, the Crew Module, the Service Module, and the Spacecraft Adapter (Fig. 1). The Launch Abort System (LAS) provides two functions; during nominal launches, the LAS provides protection for the Crew Module from atmospheric loads and heating during first stage flight and during emergencies provides a reliable abort capability for aborts that occur within the atmosphere. The Orion Launch Abort System (LAS) consists of an Abort Motor to provide the abort separation from the Launch Vehicle, an Attitude Control Motor to provide attitude and rate control, and a Jettison Motor for crew module to LAS separation (Fig. 2). The jettison motor is used during a nominal launch to separate the LAS from the Launch Vehicle (LV) early in the flight of the second stage when it is no longer needed for aborts and at the end of an LAS abort sequence to enable deployment of the crew module's Landing Recovery System. The LAS also provides a Boost Protective Cover fairing that shields the crew module from debris and the aero-thermal environment during ascent. Although the Orion Program has tested a number of the critical systems of the Orion spacecraft on the ground, the launch environment cannot be replicated completely on Earth. A number of flight tests have been conducted and are planned to demonstrate the performance and enable certification of the Orion Spacecraft. Exploration Flight Test 1, the first flight test of the Orion spacecraft, was successfully flown on December 5, 2014 from Cape Canaveral Air Force Station's Space Launch Complex 37. Orion's first flight was a two-orbit, high-apogee, high-energy entry, low-inclination test mission used to validate and test systems critical to crew safety, such as heat shield performance, separation events, avionics and software performance, attitude control and guidance, parachute deployment and recovery operations. One of the key separation events tested during this flight was the nominal jettison of the LAS. Data from this flight will be used to verify the function of the jettison motor to separate the Launch Abort System from the crew module so it can continue on with the mission. The LAS nominal jettison event on Exploration Flight Test 1 occurred at six minutes and twenty seconds after liftoff (See Fig. 3). The abort motor and attitude control motors were inert for Exploration Flight Test 1, since the mission did not require abort capabilities. A suite of developmental flight instrumentation was included on the flight test to provide data on spacecraft subsystems and separation events. This paper will focus on the flight test objectives and performance of the LAS during ascent and nominal jettison. Selected LAS subsystem flight test data will be presented and discussed in the paper. Exploration Flight Test -1 will provide critical data that will enable engineering to improve Orion's design and reduce risk for the astronauts it will protect as NASA continues to move forward on its human journey to Mars. The lessons learned from Exploration Flight Test 1 and the other Flight Test Vehicles will certainly contribute to the vehicle architecture of a human-rated space launch vehicle.

Ares I-X Separation and Reentry Trajectory Analyses

NASA Technical Reports Server (NTRS)

Tartabini, Paul V.; Starr, Brett R.

2011-01-01

The Ares I-X Flight Test Vehicle was launched on October 28, 2009 and was the first and only test flight of NASA s two-stage Ares I launch vehicle design. The launch was successful and the flight test met all of its primary and secondary objectives. This paper discusses the stage separation and reentry trajectory analysis that was performed in support of the Ares I-X test flight. Pre-flight analyses were conducted to assess the risk of stage recontact during separation, to evaluate the first stage flight dynamics during reentry, and to define the range safety impact ellipses of both stages. The results of these pre-flight analyses were compared with available flight data. On-board video taken during flight showed that the flight test vehicle successfully separated without any recontact. Reconstructed trajectory data also showed that first stage flight dynamics were well characterized by pre-flight Monte Carlo results. In addition, comparisons with flight data indicated that the complex interference aerodynamic models employed in the reentry simulation were effective in capturing the flight dynamics during separation. Finally, the splash-down locations of both stages were well within predicted impact ellipses.

A flight test facility design for examining digital information transfer

NASA Technical Reports Server (NTRS)

Knox, Charles E.

1990-01-01

Information is given in viewgraph form on a flight test facility design for examining digital information transfer. Information is given on aircraft/ground exchange, data link research activities, data link display format, a data link flight test, and the flight test setup.

Flight testing the fixed-wing configuration of the Rotor Systems Research Aircraft (RSRA)

NASA Technical Reports Server (NTRS)

Hall, G. W.; Morris, P. M.

1985-01-01

The Rotor Systems Research Aircraft (RSRA) is a unique research aircraft designed to flight test advanced helicopter rotor system. Its principal flight test configuration is as a compound helicopter. The fixed wing configuration of the RSRA was primarily considered an energy fly-home mode in the event it became necessary to sever an unstable rotor system in flight. While it had always been planned to flight test the fixed wing configuration, the selection of the RSRA as the flight test bed for the X-wing rotor accelerated this schedule. This paper discusses the build-up to, and the test of, the RSRA fixed wing configuration. It is written primarily from the test pilot's perspective.

Flight Test Results from the Rake Airflow Gage Experiment on the F-15B Airplane

NASA Technical Reports Server (NTRS)

Frederick, Michael A.; Ratnayake, Nalin A.

2010-01-01

The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center using the Dryden F-15B research test bed airplane. The objective of this flight test was to ascertain the flow-field angularity, local Mach number profile, total pressure distortion, and dynamic pressure at the aerodynamic interface plane of the Channeled Centerbody Inlet Experiment. This new mixed-compression, supersonic inlet is planned for flight test in the near term. Knowledge of the flow-field characteristics at this location underneath the airplane is essential to flight test planning and computational modeling of the new inlet, and it is also applicable for future propulsion systems research that may use the Propulsion Flight Test Fixture. This report describes the flight test preparation and execution, and the local flowfield properties calculated from pressure measurements of the rake. Data from the two Rake Airflow Gage Experiment research flights demonstrate that the F-15B airplane, flying at a free-stream Mach number of 1.65 and a pressure altitude of 40,000 ft, would achieve the desired local Mach number for the future inlet flight test. Interface plane distortion levels of 2 percent and a local angle of attack of 2 were observed at this condition. Alternative flight conditions for future testing and an exploration of certain anomalous data also are provided.

Flight Test Results from the Rake Airflow Gage Experiment on the F-15B Airplane

NASA Technical Reports Server (NTRS)

Frederick, Michael A.; Ratnayake, Nalin A.

2011-01-01

The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center using the Dryden F-15B research test bed airplane. The objective of this flight test was to ascertain the flow-field angularity, local Mach number profile, total pressure distortion, and dynamic pressure at the aerodynamic interface plane of the Channeled Centerbody Inlet Experiment. This new mixed-compression, supersonic inlet is planned for flight test in the near term. Knowledge of the flow-field characteristics at this location underneath the airplane is essential to flight test planning and computational modeling of the new inlet, an< it is also applicable for future propulsion systems research that may use the Propulsion Flight Test Fixture. This report describes the flight test preparation and execution, and the local flow-field properties calculated from pressure measurements of the rake. Data from the two Rake Airflow Gage Experiment research flights demonstrate that the F-15B airplane, flying at a free-stream Mach number of 1.65 and a pressure altitude of 40,000 ft, would achieve the desired local Mach number for the future inlet flight test. Interface plane distortion levels of 2 percent and a local angle of attack of -2 deg were observed at this condition. Alternative flight conditions for future testing and an exploration of certain anomalous data also are provided.

Development of a simple, self-contained flight test data acquisition system

NASA Technical Reports Server (NTRS)

Clarke, R.; Shane, D.; Roskam, J.; Rummer, D. I.

1982-01-01

The flight test system described combines state-of-the-art microprocessor technology and high accuracy instrumentation with parameter identification technology which minimize data and flight time requirements. The system was designed to avoid permanent modifications of the test airplane and allow quick installation. It is capable of longitudinal and lateral-directional stability and control derivative estimation. Details of this system, calibration and flight test procedures, and the results of the Cessna 172 flight test program are presented. The system proved easy to install, simple to operate, and capable of accurate estimation of stability and control parameters in the Cessna 172 flight tests.

Remotely Piloted Vehicles for Experimental Flight Control Testing

NASA Technical Reports Server (NTRS)

Motter, Mark A.; High, James W.

2009-01-01

A successful flight test and training campaign of the NASA Flying Controls Testbed was conducted at Naval Outlying Field, Webster Field, MD during 2008. Both the prop and jet-powered versions of the subscale, remotely piloted testbeds were used to test representative experimental flight controllers. These testbeds were developed by the Subsonic Fixed Wing Project s emphasis on new flight test techniques. The Subsonic Fixed Wing Project is under the Fundamental Aeronautics Program of NASA's Aeronautics Research Mission Directorate (ARMD). The purpose of these testbeds is to quickly and inexpensively evaluate advanced concepts and experimental flight controls, with applications to adaptive control, system identification, novel control effectors, correlation of subscale flight tests with wind tunnel results, and autonomous operations. Flight tests and operator training were conducted during four separate series of tests during April, May, June and August 2008. Experimental controllers were engaged and disengaged during fully autonomous flight in the designated test area. Flaps and landing gear were deployed by commands from the ground control station as unanticipated disturbances. The flight tests were performed NASA personnel with support from the Maritime Unmanned Development and Operations (MUDO) team of the Naval Air Warfare Center, Aircraft Division

Design and Testing of Flight Control Laws on the RASCAL Research Helicopter

NASA Technical Reports Server (NTRS)

Frost, Chad R.; Hindson, William S.; Moralez. Ernesto, III; Tucker, George E.; Dryfoos, James B.

2001-01-01

Two unique sets of flight control laws were designed, tested and flown on the Army/NASA Rotorcraft Aircrew Systems Concepts Airborne Laboratory (RASCAL) JUH-60A Black Hawk helicopter. The first set of control laws used a simple rate feedback scheme, intended to facilitate the first flight and subsequent flight qualification of the RASCAL research flight control system. The second set of control laws comprised a more sophisticated model-following architecture. Both sets of flight control laws were developed and tested extensively using desktop-to-flight modeling, analysis, and simulation tools. Flight test data matched the model predicted responses well, providing both evidence and confidence that future flight control development for RASCAL will be efficient and accurate.

Hyper-X Engine Design and Ground Test Program

NASA Technical Reports Server (NTRS)

Voland, R. T.; Rock, K. E.; Huebner, L. D.; Witte, D. W.; Fischer, K. E.; McClinton, C. R.

1998-01-01

The Hyper-X Program, NASA's focused hypersonic technology program jointly run by NASA Langley and Dryden, is designed to move hypersonic, air-breathing vehicle technology from the laboratory environment to the flight environment, the last stage preceding prototype development. The Hyper-X research vehicle will provide the first ever opportunity to obtain data on an airframe integrated supersonic combustion ramjet propulsion system in flight, providing the first flight validation of wind tunnel, numerical and analytical methods used for design of these vehicles. A substantial portion of the integrated vehicle/engine flowpath development, engine systems verification and validation and flight test risk reduction efforts are experimentally based, including vehicle aeropropulsive force and moment database generation for flight control law development, and integrated vehicle/engine performance validation. The Mach 7 engine flowpath development tests have been completed, and effort is now shifting to engine controls, systems and performance verification and validation tests, as well as, additional flight test risk reduction tests. The engine wind tunnel tests required for these efforts range from tests of partial width engines in both small and large scramjet test facilities, to tests of the full flight engine on a vehicle simulator and tests of a complete flight vehicle in the Langley 8-Ft. High Temperature Tunnel. These tests will begin in the summer of 1998 and continue through 1999. The first flight test is planned for early 2000.

Post-Flight Assessment of Low Density Supersonic Decelerator Flight Dynamics Test 2 Simulation

NASA Technical Reports Server (NTRS)

Dutta, Soumyo; Bowes, Angela L.; White, Joseph P.; Striepe, Scott A.; Queen, Eric M.; O'Farrel, Clara; Ivanov, Mark C.

2016-01-01

NASA's Low Density Supersonic Decelerator (LDSD) project conducted its second Supersonic Flight Dynamics Test (SFDT-2) on June 8, 2015. The Program to Optimize Simulated Trajectories II (POST2) was one of the flight dynamics tools used to simulate and predict the flight performance and was a major tool used in the post-flight assessment of the flight trajectory. This paper compares the simulation predictions with the reconstructed trajectory. Additionally, off-nominal conditions seen during flight are modeled in the simulation to reconcile the predictions with flight data. These analyses are beneficial to characterize the results of the flight test and to improve the simulation and targeting of the subsequent LDSD flights.

Armstrong Flight Research Center Flight Test Capabilities and Opportunities for the Applications of Wireless Data Acquisition Systems

NASA Technical Reports Server (NTRS)

Hang, Richard

2015-01-01

The presentation will overview NASA Armstrong Flight Research Centers flight test capabilities, which can provide various means for flight testing of passive and active wireless sensor systems, also, it will address the needs of the wireless data acquisition solutions for the centers flight instrumentation issues such as additional weight caused by added instrumentation wire bundles, connectors, wire cables routing, moving components, etc., that the Passive Wireless Sensor Technology Workshop may help. The presentation shows the constraints and requirements that the wireless sensor systems will face in the flight test applications.

The DAST-1 remotely piloted research vehicle development and initial flight testing

NASA Technical Reports Server (NTRS)

Kotsabasis, A.

1981-01-01

The development and initial flight testing of the DAST (drones for aerodynamic and structural testing) remotely piloted research vehicle, fitted with the first aeroelastic research wing ARW-I are presented. The ARW-I is a swept supercritical wing, designed to exhibit flutter within the vehicle's flight envelope. An active flutter suppression system (FSS) designed to increase the ARW-I flutter boundary speed by 20 percent is described. The development of the FSS was based on prediction techniques of structural and unsteady aerodynamic characteristics. A description of the supporting ground facilities and aircraft systems involved in the remotely piloted research vehicle (RPRV) flight test technique is given. The design, specification, and testing of the remotely augmented vehicle system are presented. A summary of the preflight and flight test procedures associated with the RPRV operation is given. An evaluation of the blue streak test flight and the first and second ARW-I test flights is presented.

Flight control system design factors for applying automated testing techniques

NASA Technical Reports Server (NTRS)

Sitz, Joel R.; Vernon, Todd H.

1990-01-01

Automated validation of flight-critical embedded systems is being done at ARC Dryden Flight Research Facility. The automated testing techniques are being used to perform closed-loop validation of man-rated flight control systems. The principal design features and operational experiences of the X-29 forward-swept-wing aircraft and F-18 High Alpha Research Vehicle (HARV) automated test systems are discussed. Operationally applying automated testing techniques has accentuated flight control system features that either help or hinder the application of these techniques. The paper also discusses flight control system features which foster the use of automated testing techniques.

Executable assertions and flight software

NASA Technical Reports Server (NTRS)

Mahmood, A.; Andrews, D. M.; Mccluskey, E. J.

1984-01-01

Executable assertions are used to test flight control software. The techniques used for testing flight software; however, are different from the techniques used to test other kinds of software. This is because of the redundant nature of flight software. An experimental setup for testing flight software using executable assertions is described. Techniques for writing and using executable assertions to test flight software are presented. The error detection capability of assertions is studied and many examples of assertions are given. The issues of placement and complexity of assertions and the language features to support efficient use of assertions are discussed.

Flight Research Using F100 Engine P680063 in the NASA F-15 Airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Conners, Timothy R.; Maxwell, Michael D.

1994-01-01

The value of flight research in developing and evaluating gas turbine engines is high. NASA Dryden Flight Research Center has been conducting flight research on propulsion systems for many years. The F100 engine has been tested in the NASA F-15 research airplane in the last three decades. One engine in particular, S/N P680063, has been used for the entire program and has been flown in many pioneering propulsion flight research activities. Included are detailed flight-to-ground facility tests; tests of the first production digital engine control system, the first active stall margin control system, the first performance-seeking control system; and the first use of computer-controlled engine thrust for emergency flight control. The flight research has been supplemented with altitude facility tests at key times. This paper presents a review of the tests of engine P680063, the F-15 airplanes in which it flew, and the role of the flight test in maturing propulsion technology.

Synthetic and Enhanced Vision Systems for NextGen (SEVS) Simulation and Flight Test Performance Evaluation

NASA Technical Reports Server (NTRS)

Shelton, Kevin J.; Kramer, Lynda J.; Ellis,Kyle K.; Rehfeld, Sherri A.

2012-01-01

The Synthetic and Enhanced Vision Systems for NextGen (SEVS) simulation and flight tests are jointly sponsored by NASA's Aviation Safety Program, Vehicle Systems Safety Technology project and the Federal Aviation Administration (FAA). The flight tests were conducted by a team of Honeywell, Gulfstream Aerospace Corporation and NASA personnel with the goal of obtaining pilot-in-the-loop test data for flight validation, verification, and demonstration of selected SEVS operational and system-level performance capabilities. Nine test flights (38 flight hours) were conducted over the summer and fall of 2011. The evaluations were flown in Gulfstream.s G450 flight test aircraft outfitted with the SEVS technology under very low visibility instrument meteorological conditions. Evaluation pilots flew 108 approaches in low visibility weather conditions (600 ft to 2400 ft visibility) into various airports from Louisiana to Maine. In-situ flight performance and subjective workload and acceptability data were collected in collaboration with ground simulation studies at LaRC.s Research Flight Deck simulator.

Hyper-X Flight Engine Ground Testing for X-43 Flight Risk Reduction

NASA Technical Reports Server (NTRS)

Huebner, Lawrence D.; Rock, Kenneth E.; Ruf, Edward G.; Witte, David W.; Andrews, Earl H., Jr.

2001-01-01

Airframe-integrated scramjet engine testing has been completed at Mach 7 flight conditions in the NASA Langley 8-Foot High Temperature Tunnel as part of the NASA Hyper-X program. This test provided engine performance and operability data, as well as design and database verification, for the Mach 7 flight tests of the Hyper-X research vehicle (X-43), which will provide the first-ever airframe-integrated scramjet data in flight. The Hyper-X Flight Engine, a duplicate Mach 7 X-43 scramjet engine, was mounted on an airframe structure that duplicated the entire three-dimensional propulsion flowpath from the vehicle leading edge to the vehicle trailing edge. This model was also tested to verify and validate the complete flight-like engine system. This paper describes the subsystems that were subjected to flight-like conditions and presents supporting data. The results from this test help to reduce risk for the Mach 7 flights of the X-43.

Hubble Space Telescope nickel-hydrogen battery testing: An update

NASA Technical Reports Server (NTRS)

Whitt, Thomas H.; Brewer, Jeffrey C.

1995-01-01

The Marshall Space Flight Center (MSFC) began testing the HST Ni-H2 Six Battery Test and the 'Flight Spare Battery' Tests approximately one year before the launch of the HST. These tests are operated and reported on by the MSFC, but are managed and funded by Goddard Space Flight Center in direct support of the HST program. The HST Ni-H2 batteries are built from Eagle Picher RNH-90-3 cells. The HST EPS (electrical power system) is a direct energy transfer power system. The HST Ni-H2 Six Battery Test is a breadboard of the HST EPS. The batteries in the test are composed of test module cells and packaged into three battery modules identical to the flight modules. This test is the HST EPS testbed. The 'Flight Spare Battery' Test is a simulation of one of the six battery channels on the HST. The cells in the test are from the flight spare lot of cells, which are the same lot of cells that three of the six HST flight batteries are made from. This test is the battery life test for the HST program.

Asset Analysis and Operational Concepts for Separation Assurance Flight Testing at Dryden Flight Research Center

NASA Technical Reports Server (NTRS)

Costa, Guillermo J.; Arteaga, Ricardo A.

2011-01-01

A preliminary survey of existing separation assurance and collision avoidance advancements, technologies, and efforts has been conducted in order to develop a concept of operations for flight testing autonomous separation assurance at Dryden Flight Research Center. This effort was part of the Unmanned Aerial Systems in the National Airspace System project. The survey focused primarily on separation assurance projects validated through flight testing (including lessons learned), however current forays into the field were also examined. Comparisons between current Dryden flight and range assets were conducted using House of Quality matrices in order to allow project management to make determinations regarding asset utilization for future flight tests. This was conducted in order to establish a body of knowledge of the current collision avoidance landscape, and thus focus Dryden s efforts more effectively towards the providing of assets and test ranges for future flight testing within this research field.

Supersonic Flight Dynamics Test 2: Trajectory, Atmosphere, and Aerodynamics Reconstruction

NASA Technical Reports Server (NTRS)

Karlgaard, Christopher D.; O'Farrell, Clara; Ginn, Jason M.; Van Norman, John W.

2016-01-01

The Supersonic Flight Dynamics Test is a full-scale flight test of aerodynamic decelerator technologies developed by the Low Density Supersonic Decelerator technology demonstration project. The purpose of the project is to develop and mature aerodynamic decelerator technologies for landing large-mass payloads on the surface of Mars. The technologies include a Supersonic Inflatable Aerodynamic Decelerator and supersonic parachutes. The first Supersonic Flight Dynamics Test occurred on June 28th, 2014 at the Pacific Missile Range Facility. The purpose of this test was to validate the test architecture for future tests. The flight was a success and, in addition, was able to acquire data on the aerodynamic performance of the supersonic inflatable decelerator. The Supersonic Disksail parachute developed a tear during deployment. The second flight test occurred on June 8th, 2015, and incorporated a Supersonic Ringsail parachute which was redesigned based on data from the first flight. Again, the inflatable decelerator functioned as predicted but the parachute was damaged during deployment. This paper describes the instrumentation, analysis techniques, and acquired flight test data utilized to reconstruct the vehicle trajectory, main motor thrust, atmosphere, and aerodynamics.

NASA Crew Launch Vehicle Flight Test Options

NASA Technical Reports Server (NTRS)

Cockrell, Charles E., Jr.; Davis, Stephan R.; Robonson, Kimberly; Tuma, Margaret L.; Sullivan, Greg

2006-01-01

Options for development flight testing (DFT) of the Ares I Crew Launch Vehicle (CLV) are discussed. The Ares-I Crew Launch Vehicle (CLV) is being developed by the U.S. National Aeronautics and Space Administration (NASA) to launch the Crew Exploration Vehicle (CEV) into low Earth Orbit (LEO). The Ares-I implements one of the components of the Vision for Space Exploration (VSE), providing crew and cargo access to the International Space Station (ISS) after retirement of the Space Shuttle and, eventually, forming part of the launch capability needed for lunar exploration. The role of development flight testing is to demonstrate key sub-systems, address key technical risks, and provide flight data to validate engineering models in representative flight environments. This is distinguished from certification flight testing, which is designed to formally validate system functionality and achieve flight readiness. Lessons learned from Saturn V, Space Shuttle, and other flight programs are examined along with key Ares-I technical risks in order to provide insight into possible development flight test strategies. A strategy for the first test flight of the Ares I, known as Ares I-1, is presented.

In-Flight Vibration Environment of the NASA F-15B Flight Test Fixture

NASA Technical Reports Server (NTRS)

Corda, Stephen; Franz, Russell J.; Blanton, James N.; Vachon, M. Jake; DeBoer, James B.

2002-01-01

Flight vibration data are analyzed for the NASA F-15B/Flight Test Fixture II test bed. Understanding the in-flight vibration environment benefits design and integration of experiments on the test bed. The power spectral density (PSD) of accelerometer flight data is analyzed to quantify the in-flight vibration environment from a frequency of 15 Hz to 1325 Hz. These accelerometer data are analyzed for typical flight conditions and maneuvers. The vibration data are compared to flight-qualification random vibration test standards. The PSD levels in the lateral axis generally are greater than in the longitudinal and vertical axes and decrease with increasing frequency. At frequencies less than approximately 40 Hz, the highest PSD levels occur during takeoff and landing. Peaks in the PSD data for the test fixture occur at approximately 65, 85, 105-110, 200, 500, and 1000 Hz. The pitch-pulse and 2-g turn maneuvers produce PSD peaks at 115 Hz. For cruise conditions, the PSD level of the 85-Hz peak is greatest for transonic flight at Mach 0.9. From 400 Hz to 1325 Hz, the takeoff phase has the highest random vibration levels. The flight-measured vibration levels generally are substantially lower than the random vibration test curve.

Integration of optical measurement methods with flight parameter measurement systems

NASA Astrophysics Data System (ADS)

Kopecki, Grzegorz; Rzucidlo, Pawel

2016-05-01

During the AIM (advanced in-flight measurement techniques) and AIM2 projects, innovative modern techniques were developed. The purpose of the AIM project was to develop optical measurement techniques dedicated for flight tests. Such methods give information about aircraft elements deformation, thermal loads or pressure distribution, etc. In AIM2 the development of optical methods for flight testing was continued. In particular, this project aimed at the development of methods that could be easily applied in flight tests in an industrial setting. Another equally important task was to guarantee the synchronization of the classical measuring system with cameras. The PW-6U glider used in flight tests was provided by the Rzeszów University of Technology. The glider had all the equipment necessary for testing the IPCT (image pattern correlation technique) and IRT (infrared thermometry) methods. Additionally, equipment adequate for the measurement of typical flight parameters, registration and analysis has been developed. This article describes the designed system, as well as presenting the system’s application during flight tests. Additionally, the results obtained in flight tests show certain limitations of the IRT method as applied.

AGARD Flight Test Techniques Series. Volume 18. Flight Testing of Radio Navigation Systems. (Les Essais en Vol des Systemes de Radionavigation)

DTIC Science & Technology

2000-04-01

18 Flight Testing of Radio Navigation Systems (les Essais en vol des systemes de radionavigation) This AGARDograph has been sponsored by the Systems...Techniques Series - Volume 18 Flight Testing of Radio Navigation Systems (les Essais en vol des syst~mes de radionavigation) Edited by H. Bothe H.J...Landing Test and Other Short-Range 19853 Applications by P. de Benquoe D’Agut, H. Rieheek and A. Pool 17. Analogue Signal Conditioning for Flight Test

Post Flight Analysis Of SHEFEX I: Shock Tunnel Testing And Related CFD Analysis

NASA Astrophysics Data System (ADS)

Schramm, Jan Martinez; Barth, Tarik; Wagner, Alexander; Hannemann, Klaus

2011-05-01

The SHarp Edge Flight EXperiment (SHEFEX) program of the German Aerospace Center (DLR) is primarily focused on the investigation of the potential to utilise improved shapes for space vehicles by considering sharp edges and facetted surfaces. One goal is to set up a sky based test facility to gain knowledge of the physics of hypersonic flow, complemented by numerical analysis and ground based testing. Further, the series of SHEFEX flight experiments is an excellent test bed for new technological concepts and flight instrumentation, and it is a source of motivation for young scientist and engineers providing an excellent school for future space-program engineers and managers. After the successful first SHEFEX flight in October 2005, a second flight is scheduled for September 2011 and additional flights are planned for 2015 ff. With the SHEFEX-I flight and the subsequent numerical and experimental post flight analysis, DLR could for the first time close the loop between the three major disciplines of aerothermodynamic research namely CFD, ground based testing and flight.

Ares I-X Flight Test Vehicle Modal Test

NASA Technical Reports Server (NTRS)

Buehrle, Ralph D.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Bartolotta, Paul A.; Parks, Russel A.; Lazor, Daniel R.

2010-01-01

The first test flight of NASA's Ares I crew launch vehicle, called Ares I-X, was launched on October 28, 2009. Ares I-X used a 4-segment reusable solid rocket booster from the Space Shuttle heritage with mass simulators for the 5th segment, upper stage, crew module and launch abort system. Flight test data will provide important information on ascent loads, vehicle control, separation, and first stage reentry dynamics. As part of hardware verification, a series of modal tests were designed to verify the dynamic finite element model (FEM) used in loads assessments and flight control evaluations. Based on flight control system studies, the critical modes were the first three free-free bending mode pairs. Since a test of the free-free vehicle was not practical within project constraints, modal tests for several configurations during vehicle stacking were defined to calibrate the FEM. Test configurations included two partial stacks and the full Ares I-X flight test vehicle on the Mobile Launcher Platform. This report describes the test requirements, constraints, pre-test analysis, test execution and results for the Ares I-X flight test vehicle modal test on the Mobile Launcher Platform. Initial comparisons between pre-test predictions and test data are also presented.

Flight Test of an L(sub 1) Adaptive Controller on the NASA AirSTAR Flight Test Vehicle

NASA Technical Reports Server (NTRS)

Gregory, Irene M.; Xargay, Enric; Cao, Chengyu; Hovakimyan, Naira

2010-01-01

This paper presents results of a flight test of the L-1 adaptive control architecture designed to directly compensate for significant uncertain cross-coupling in nonlinear systems. The flight test was conducted on the subscale turbine powered Generic Transport Model that is an integral part of the Airborne Subscale Transport Aircraft Research system at the NASA Langley Research Center. The results presented are for piloted tasks performed during the flight test.

Conversion of Propellant Grade Picrite to Spherical Nitroguanidine, an Insensitive Filler for Melt-Cast TNT Formulations

DTIC Science & Technology

1991-09-01

problem with the solvent/non-solvent process reported by ICT is the inability to recycle the mother liquors. Apparently "strawberries" or " sea urchins ...inevitable for the foreseeable future. Exceptions could include lower production rate items such as sea mines or missile warheads, or speLfic nunitions where...Leitz Orthomat 35 mm automatic camera on polaroid film type 667, Magnification ranged up to X42. 14K 1* Scanning Electron Microscopy ( SEM ) SEM was

Defense Policy in the Reagan Administration

DTIC Science & Technology

1988-09-01

308X SS-9 "hcax\\* y (’BIi, but MultipliedI the allowable number of inldepen~dentl tarcetable countersilo-capable warheads h\\ at factor of It). Stilli...despite the fact that Beijing con- tinued to view Moscow as the only major militar) threat to its security. A number of factors contributed to the...Japan’s potential value as a more active partner in American coalition strategy was to be found in a variet\\ of factors which. although it faced some

U.S. Strategic Nuclear Forces: Background, Developments, and Issues

DTIC Science & Technology

2015-03-18

5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Congressional Research Service,The...extend the life of the missiles and warheads so that they and the submarines can remain in the fleet past 2020. It is designing a new submarine and...modifying and extending the life of the B61 bomb carried on B-2 bombers and fighter aircraft. The Obama Administration completed a review of the size and

Nuclear Successor States of the Soviet Union, Nuclear Weapon and Sensitive Export Status Report

DTIC Science & Technology

1994-05-01

EXPORT STATUS REPORT S I VIE T U N il] N A COOPERATIVE PROJECT OF THE CARNEGIE ENDOWMENT FOR INTERNATIONAL PEACE, WASHINGTON, DC, AND MOSCOW NUMBER 1...Launch Periodic Report on Nuclear Successor States Leonard S . Spector of the Carnegie Endowment for N U C L E A R International Peace and William C...range, translated in FBIS-SOV-92-232, December 2, 1992, p. 22. 5 Table I-C. -- N -Weapon Systems and Warheads on Territory, con’t. S

Decision Factors for Cooperative Multiple Warhead UAV Target Classification and Attack with Control Applications

DTIC Science & Technology

2004-10-01

Jeffrey P. Kharoufeh Committee Member Date /signed/ 22 Oct 04 Dr. Alan V. Lair Dean’s Representative Date /signed/ Robert A. Calico, Jr Dean...who also provided great comments on my drafts. As far as the drafts go, thanks to all the committee and the Dean’s Representative (Dr. Alan Lair ) for...11. Cozzolino, J.M. “Sequential Search for an Unknown Number of Objects of Nonuniform Size,” Operations Research, 20 :293–308 (1972). 12. de Guenin

7. Photocopy of photograph, U.S. Army, ca. 1955 (original print ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

7. Photocopy of photograph, U.S. Army, ca. 1955 (original print located at Rocky Mountain Arsenal, Commerce City, Colorado). INTERIOR OF BUILDING 1611. 'THE M139 BOMBLETS ARE MANUALLY DOWNLOADED FROM THE WARHEAD SECTION ONTO THE CONVEYORS, EQUIPPED WITH FIXTURES TO POSITION THE BOMBLETS FOR THE SUBSEQUENT PUNCH, DRAIN AND RINSE OPERATIONS.' - Rocky Mountain Arsenal, Ammunition Demolition Building-Tail Fin Storage & Assembly, 2750 feet South of Ninth Avenue; 3480 feet East of D Street, Commerce City, Adams County, CO

Comparison of Two Railgun Power Supply Architectures to Quantify the Energy Dissipated After the Projectile Leaves the Railgun

DTIC Science & Technology

2016-06-01

inch gun on impact [1]. The potential of the EM railgun renders the need to store dangerous explosives associated with the conventional warheads...leaves the gun . The simulation will outline some critical performance characteristics of a buck-boost power supply as compared to a thyristor-based...between the rails and from the projectile position along the length of the gun x [5]: 3 1 2 𔃻 2 2 w o

The Effects of Warhead-Induced Damage on the Aeroelastic Characteristics of Lifting Surfaces. Volume I. Aeroelastic Effects.

DTIC Science & Technology

1980-07-01

Arnold. Some further insight into the problem is obtained here, however, when it is demonstrated that highly optimized structural designs may...aircraft of this type are normally designed to withstand loads up to 1.5 times the maximum limit load (load factor 8.0 to 8.67), the structure should...on the wing, for example, give rise to concentrated drag and chordwise loadings as does the recoil from firing wing mounted gun systems . The drag on

Converting the Minuteman missile into a small satellite launch system

NASA Technical Reports Server (NTRS)

Alexander, Bill; Gonzalez, Rodolfo; Humble, Greg; Mackay, Gordon; Mchaty, Rod; Pham, VU

1993-01-01

Due to the Strategic Arms Reduction Talks (START) treaty between the United States and Ex-Soviet Union, 450 Minuteman 2 (MM 2) missiles were recently taken out of service. Minotaur Designs Incorporated (MDI) intends to convert the MM 2 ballistic missile from a nuclear warhead carrier into a small satellite launcher. MDI will perform this conversion by acquiring the Minuteman stages, purchasing currently available control wafers, and designing a new shroud and interfaces for the satellite. MDI is also responsible for properly integrating all systems.

7. Photographic copy of photograph, date unknown (original print in ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

7. Photographic copy of photograph, date unknown (original print in possession of James E. Zielinski Earth Tech, Huntsville, AL). Pan American World Airways, photographer. Aerial view (north to south) of missile launch area. Warhead handling building can be seen at the bottom center of the picture and the universal missile building in the middle right. In the distance can be seen the missile site control building and related structures - Stanley R. Mickelsen Safeguard Complex, Missile Launch Area, Within Exclusion Area, Nekoma, Cavalier County, ND

"To Be...or Not To Be": The U.S. Response to the Cuban Missile Crisis. Eleventh Grade Activity. Schools of California Online Resources for Education (SCORE): Connecting California's Classrooms to the World.

ERIC Educational Resources Information Center

Krup, Carol

During the post-World War II era, the relationship between the United States and the Soviet Union became strained. Both countries feared that one would target the other with atomic warheads placed on missiles. Fear of a nuclear holocaust occupied the thinking of many people as they went about their daily activities. As a member of the Executive…

History of the Chaparral/FAAR Air Defense System

DTIC Science & Technology

1977-05-31

i s t ed of t h e AN/DAW-1 guidance s e c t i o n ; t h e M817 t a r g e t d e t e c t i o n device (DIDO f u z e ) ; t h e M250 b l a s t...19n, 21-22, 25, 25n, 27-28, 30-32, 51, 88-89, 107-109, 175 Warhead Blast Fragmentation (BF), 92, 118 M250 (XM-250), 116, 119 continuous rod, 12

Proceedings of the Special Course on Missile Aerodynamics, Held in Rhode-Saint-Genese, Belgium on 30 March-3 April 1987, Held in Athens, Greece on 18-19 May 1987 Held in Ankara, Turkey on 21-22 May 1987

DTIC Science & Technology

1988-04-01

organized at VKI: 1974 IVKI LS67). 1970 (VKI LS88) and 1979 (AGARI) LS98). This course was intended for practical engineers and researchers, beginners ...TYPICAL SUBSYSTEM INTERNAL LAYOUTS FIGURE 6. FLOWCHART OF SHAPING LOGIC Ml 1-0 7624 SINGLE ENGINE TWIN ENGINE TOP VIEW TOP VIEW WARHEAD / _ SKEW -- ftG

Sandia/NM Available Mock Warhead Container Inventory

DOE Office of Scientific and Technical Information (OSTI.GOV)

Brotz, Jay Kristoffer

The real H1514 Shipping and Storage Container is an environmentally sealed and desiccated aluminum drum-type container designed to transport the W88/Mk5 Reentry Body Assembly. The H1514 is cylindrical except for a portion of its base, which is 36" square and 3" high and contains the forklift openings. Our mock H1514 retains the dimensions and shape of the real H1514 in a lighter form that is not sealed and does not have ports for desiccation.

What Happens to Deterrence as Nuclear Weapons Decrease Toward Zero?

NASA Astrophysics Data System (ADS)

Drell, Sidney

2011-04-01

Steps reducing reliance on deployed nuclear weapons en route to zero will be discussed. They include broadly enhancing cooperation and transparency agreements beyond the provisions for verifying limits on deployed strategic nuclear warheads and delivery systems in the New START treaty. Two questions that will be addressed are: What conditions would have to be established in order to maintain strategic stability among nations as nuclear weapons recede in importance? What would nuclear deterrence be like in a world without nuclear weapons?

A History of the Huntsville Division U.S. Army Corps of Engineers 15 October 1967 - 31 December 1976

DTIC Science & Technology

1978-09-06

discriminate between decoys and armed warheads until the slowing effect of denser air in the lower atmosphere had helped sort out heavy projectiles...would have to keep up by enlarging her forces, and the arms race would be accelerated at the expense of detente. The knowledgeable called this "the...perhaps because of Vietnam, the Soviets showed themselves reluctant to talk about arms limitations in general and BMD in particular, despite

Effects of Sensing Capability on Ground Platform Survivability During Ground Forces Maneuver Operations

DTIC Science & Technology

2014-09-01

Hellfire missiles, Hydra -70mm rockets, and M230 30mm automatic cannon (Boeing 2014). Hellfire missiles have shaped-charge HEAT warheads and are...capable of destroying an MBT. These missiles have an operational range between 500 m to 8,000 m (AeroWeb 2014). The Hydra -70mm rocket is also capable of...platforms, but it lacks precision (Army Technology 2014). Similar to the Hydra -70mm rocket, the M230 30mm cannon is effective against soft skin

National Symposium: Surface Navy Leading the Way (5th) Held at Washington, DC on 26-29 October 1992

DTIC Science & Technology

1992-10-29

nation. We all hope that in the days and years ahead a grateful nation continues to be grateful, and will not forget the price we paid for this... skimming threats. The Outlaw Bandit Program will continue. This program reduces the radar cross section of combatants significantly and increases the...Weapon Systems to provide a precision, multi-mode strike Cruise missile with an imaging seeker and hard target penetrator warhead. 22 With the

Modern Weapon-Guided Missile (Xiandai Wugi-Daodan)

DTIC Science & Technology

1981-11-27

mind - . . f b ... . " i• -- 4 a . f l - . a ..••’•’:,’ • ’ 2m • LIN The destructive power of a nucler payload comrea Crom the nuclear-energy...rest due of firework gradually descends as the power - is lost. This fact shows that the ascending firework is propelled by the " reaction of combustion...vehicle powered by thrust provided by a rocket engine. In different usage.’, a rocket can have different effective payloads. If a warhead is installed

Advanced Warheads Concepts: An Advanced Equation of State for Overdriven Detonation

DTIC Science & Technology

1991-05-01

equation of state (Jones-Wilkens Lee-Baker ( JWLB )] for high explosive detonation products. JWLB is suitable for overdriven detonation and material...In order to achieve a suitable equation of state, an appropriate equation of state form ( JWLB ) was derived. A standard explosive (octol 75/25) was...resulting equation of slate form, named Jones-Wilkens-Lcc-Baker ( JWLB ), is as follows: L ’L RiVJ .RiV+AJE + C(1.W(oH-l) -RoV X-JA^VC’V + O) The

North Korea’s Military Threat: Pyongyang’s Conventional Forces, Weapons of Mass Destruction, and Ballistic Missiles

DTIC Science & Technology

2007-04-01

that some 40 percent of the populace serve in some military or paramilitary formation . In short, the DPRK is undoubtedly the “most militarized...reportedly supplied North Korea with “ uranium enrichment equipment and perhaps even warhead designs.”301 In the first decade of the 21st century...Taechon (construction frozen under the Agreed Framework), as well as uranium ore processing at Pyongsan and Pakchon.305 However, “it is impossible

NASA Tests 2nd RS-25 Flight Engine for Space Launch System

NASA Image and Video Library

2018-01-16

On Jan. 16, 2018, engineers at NASA’s Stennis Space Center in Mississippi conducted a certification test of another RS-25 engine flight controller on the A-1 Test Stand at Stennis Space Center. The 365-second, full-duration test came a month after the space agency capped a year of RS-25 testing with a flight controller test in mid-December. For the “green run” test the flight controller was installed on RS-25 developmental engine E0528 and fired just as during an actual launch. Once certified, the flight controller will be removed and installed on a flight engine for use by NASA’s new deep-space rocket, the Space Launch System (SLS).

Ares I-X Flight Test Vehicle Similitude to the Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Huebner, Lawrence D.; Smith, R. Marshall; Campbell, John R., Jr.; Taylor, Terry L.

2008-01-01

The Ares I-X Flight Test Vehicle is the first in a series of flight test vehicles that will take the Ares I Crew Launch Vehicle design from development to operational capability. The test flight is scheduled for April 2009, relatively early in the Ares I design process so that data obtained from the flight can impact the design of Ares I before its Critical Design Review. Because of the short time frame (relative to new launch vehicle development) before the Ares I-X flight, decisions about the flight test vehicle design had to be made in order to complete analysis and testing in time to manufacture the Ares I-X vehicle hardware elements. This paper describes the similarities and differences between the Ares I-X Flight Test Vehicle and the Ares I Crew Launch Vehicle. Areas of comparison include the outer mold line geometry, aerosciences, trajectory, structural modes, flight control architecture, separation sequence, and relevant element differences. Most of the outer mold line differences present between Ares I and Ares I-X are minor and will not have a significant effect on overall vehicle performance. The most significant impacts are related to the geometric differences in Orion Crew Exploration Vehicle at the forward end of the stack. These physical differences will cause differences in the flow physics in these areas. Even with these differences, the Ares I-X flight test is poised to meet all five primary objectives and six secondary objectives. Knowledge of what the Ares I-X flight test will provide in similitude to Ares I as well as what the test will not provide is important in the continued execution of the Ares I-X mission leading to its flight and the continued design and development of Ares I.

Selected Flight Test Results for Online Learning Neural Network-Based Flight Control System

NASA Technical Reports Server (NTRS)

Williams-Hayes, Peggy S.

2004-01-01

The NASA F-15 Intelligent Flight Control System project team developed a series of flight control concepts designed to demonstrate neural network-based adaptive controller benefits, with the objective to develop and flight-test control systems using neural network technology to optimize aircraft performance under nominal conditions and stabilize the aircraft under failure conditions. This report presents flight-test results for an adaptive controller using stability and control derivative values from an online learning neural network. A dynamic cell structure neural network is used in conjunction with a real-time parameter identification algorithm to estimate aerodynamic stability and control derivative increments to baseline aerodynamic derivatives in flight. This open-loop flight test set was performed in preparation for a future phase in which the learning neural network and parameter identification algorithm output would provide the flight controller with aerodynamic stability and control derivative updates in near real time. Two flight maneuvers are analyzed - pitch frequency sweep and automated flight-test maneuver designed to optimally excite the parameter identification algorithm in all axes. Frequency responses generated from flight data are compared to those obtained from nonlinear simulation runs. Flight data examination shows that addition of flight-identified aerodynamic derivative increments into the simulation improved aircraft pitch handling qualities.

Flight Test of an Adaptive Controller and Simulated Failure/Damage on the NASA NF-15B

NASA Technical Reports Server (NTRS)

Buschbacher, Mark; Maliska, Heather

2006-01-01

The method of flight-testing the Intelligent Flight Control System (IFCS) Second Generation (Gen-2) project on the NASA NF-15B is herein described. The Gen-2 project objective includes flight-testing a dynamic inversion controller augmented by a direct adaptive neural network to demonstrate performance improvements in the presence of simulated failure/damage. The Gen-2 objectives as implemented on the NASA NF-15B created challenges for software design, structural loading limitations, and flight test operations. Simulated failure/damage is introduced by modifying control surface commands, therefore requiring structural loads measurements. Flight-testing began with the validation of a structural loads model. Flight-testing of the Gen-2 controller continued, using test maneuvers designed in a sequenced approach. Success would clear the new controller with respect to dynamic response, simulated failure/damage, and with adaptation on and off. A handling qualities evaluation was conducted on the capability of the Gen-2 controller to restore aircraft response in the presence of a simulated failure/damage. Control room monitoring of loads sensors, flight dynamics, and controller adaptation, in addition to postflight data comparison to the simulation, ensured a safe methodology of buildup testing. Flight-testing continued without major incident to accomplish the project objectives, successfully uncovering strengths and weaknesses of the Gen-2 control approach in flight.

Development Overview of the Revised NASA Ultra Long Duration Balloon

NASA Technical Reports Server (NTRS)

Cathey, H. M.; Gregory, D; Young, L.; Pierce, D.

2006-01-01

The development of the National Aeronautics and Space Administration s (NASA) Ultra Long Duration Balloon (ULDB) has made significant strides in addressing the deployment issues experienced in the scaling up of the balloon structure. This paper concentrates on the super-pressure balloon developments that have been, and are currently being planned by the NASA Balloon Program Office at Goddard Space Flight Center s Wallops Flight Facility. The goal of the NASA ULDB development project is to attempt to extend the potential flight durations for large scientific balloon payloads. A summary of the February 2005 test flight from Ft. Sumner, New Mexico will be presented. This test flight spurred a number of investigations and advancements for this project. The development path has pursued some new approaches in the design, analysis, and testing of the balloons. New issues have been ideEti6ed throu& both analysis md testing. These have been addressed in the design stage before the next balloon construction was begun. This paper will give an overview of the recent history for this effort and the development approach pursued for ULDB. A description of the balloon design, including the modifications made as a result of the lessons learned, will be presented. Areas to be presented include the design approach, deployment issues that have been encountered and the proposed solutions, ground testing, photogrammetry, and an analysis overview. Test flight planning and considerations will be presented including test flight safety. An extended duration test flight of the National Aeronautics and Space Administration s Ultra Long Duration Balloon is planned for the May/June 2006 time frame. This flight is expected to fly from Sweden to either Canada or Alaska. Preliminary results of this flight will be presented as available. Future plans for both ground testing and additional test flights will also be presented. Goals of the future test flights, which are staged in increments of increasing suspended load and altitude, will be presented. This will include the projected balloon volumes, payload capabilities, test flight locations, and proposed flight schedule.

Supersonic Flight Dynamics Test 1 - Post-Flight Assessment of Simulation Performance

NASA Technical Reports Server (NTRS)

Dutta, Soumyo; Bowes, Angela L.; Striepe, Scott A.; Davis, Jody L.; Queen, Eric M.; Blood, Eric M.; Ivanov, Mark C.

2015-01-01

NASA's Low Density Supersonic Decelerator (LDSD) project conducted its first Supersonic Flight Dynamics Test (SFDT-1) on June 28, 2014. Program to Optimize Simulated Trajectories II (POST2) was one of the flight dynamics codes used to simulate and predict the flight performance and Monte Carlo analysis was used to characterize the potential flight conditions experienced by the test vehicle. This paper compares the simulation predictions with the reconstructed trajectory of SFDT-1. Additionally, off-nominal conditions seen during flight are modeled in post-flight simulations to find the primary contributors that reconcile the simulation with flight data. The results of these analyses are beneficial for the pre-flight simulation and targeting of the follow-on SFDT flights currently scheduled for summer 2015.

Machine on Trial

DTIC Science & Technology

2012-06-01

executed a concerted effort to employ reliability standards and testing from the design phase through fielding. Reliability programs remain standard...performed flight test engineer duties on several developmental flight test programs and served as Chief Engineer for a flight test squadron. Major...Quant is an acquisition professional with over 250 flight test hours in various aircraft, including the F-16, Airborne Laser, and HH-60. She holds a

Flight flutter testing of multi-jet aircraft

NASA Technical Reports Server (NTRS)

Bartley, J.

1975-01-01

Extensive flight flutter tests were conducted by BAC on B-52 and KC-135 prototype airplanes. The need for and importance of these flight flutter programs to Boeing airplane design are discussed. Basic concepts of flight flutter testing of multi-jet aircraft and analysis of the test data will be presented. Exciter equipment and instrumentation employed in these tests will be discussed.

Aerodynamic Models for the Low Density Supersonic Declerator (LDSD) Supersonic Flight Dynamics Test (SFDT)

NASA Technical Reports Server (NTRS)

Van Norman, John W.; Dyakonov, Artem; Schoenenberger, Mark; Davis, Jody; Muppidi, Suman; Tang, Chun; Bose, Deepak; Mobley, Brandon; Clark, Ian

2015-01-01

An overview of pre-flight aerodynamic models for the Low Density Supersonic Decelerator (LDSD) Supersonic Flight Dynamics Test (SFDT) campaign is presented, with comparisons to reconstructed flight data and discussion of model updates. The SFDT campaign objective is to test Supersonic Inflatable Aerodynamic Decelerator (SIAD) and large supersonic parachute technologies at high altitude Earth conditions relevant to entry, descent, and landing (EDL) at Mars. Nominal SIAD test conditions are attained by lifting a test vehicle (TV) to 36 km altitude with a large helium balloon, then accelerating the TV to Mach 4 and and 53 km altitude with a solid rocket motor. The first flight test (SFDT-1) delivered a 6 meter diameter robotic mission class decelerator (SIAD-R) to several seconds of flight on June 28, 2014, and was successful in demonstrating the SFDT flight system concept and SIAD-R. The trajectory was off-nominal, however, lofting to over 8 km higher than predicted in flight simulations. Comparisons between reconstructed flight data and aerodynamic models show that SIAD-R aerodynamic performance was in good agreement with pre-flight predictions. Similar comparisons of powered ascent phase aerodynamics show that the pre-flight model overpredicted TV pitch stability, leading to underprediction of trajectory peak altitude. Comparisons between pre-flight aerodynamic models and reconstructed flight data are shown, and changes to aerodynamic models using improved fidelity and knowledge gained from SFDT-1 are discussed.

The continuing risk of nuclear war.

PubMed

McCoy, Ronald

2007-01-01

Climate change and nuclear war are currently the most dangerous challenges to human civilisation and survival. The effects of climate change are now sufficient to persuade many governments to take effective measures to reduce greenhouse gas emissions. Today there are about 27,000 nuclear warheads, many at least ten times more powerful than the Hiroshima and Nagasaki bombs, and a meaningful medical response to a nuclear attack is impossible. Nevertheless, the threat of nuclear war does not raise public concern, and indeed the nuclear-weapon states are upgrading their capability. The only effective preventive measure is the abolition of nuclear weapons. Steps towards this include: a Fissile Material Cut-off Treaty, for the nuclear weapon states to observe their obligations under the Nuclear Non-Proliferation Treaty, and for the Comprehensive Test Ban Treaty to enter into force. The ultimate need is for a Nuclear Weapons Convention; International Physicians for the Prevention of Nuclear War have launched an International Campaign to Abolish Nuclear weapons (ICAN) to promote a NWC.

Medical implications of enhanced radiation weapons.

PubMed

Reeves, Glen I

2010-12-01

During the 1960s through 1980s the United States and several other nations developed, and even considered deploying, enhanced-radiation warheads (ERWs). The main effect of ERWs (sometimes called "neutron bombs"), as compared to other types of nuclear weapons, is to enhance radiation casualties while reducing blast and thermal damage to the infrastructure. Five nations were reported to have developed and tested ERWs during this period, but since the termination of the "Cold War" there have been no threats of development, deployment, or use of such weapons. However, if the technology of a quarter of a century ago has been developed, maintained, or even advanced since then, it is conceivable that the grim possibility of future ERW use exists. The type of destruction, initial triage of casualties, distribution of patterns of injury, and medical management of ERWs will be shown to significantly differ from that of fission weapons. Emergency response planners and medical personnel, civilian or military, must be aware of these differences to reduce the horrible consequences of ERW usage and appropriately treat casualties.

A Sandia weapon review bulletin : defense programs, Autumn 1992.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1992-09-01

Topics in this issue: (1) Focal Point and STEP. Sandia National Laboratories has always focused its advanced weapon development not only on future weapon needs, but also on the engineering and manufacturing sciences needed to meet them. Both areas are changing dramatically. As the nation dismantles many of its warheads, it becomes essential that those that remain are increasingly reliable, secure, capable, and safe. And as development resources diminish, it becomes vital that they are applied to the most critical technologies in a disciplined manner. The mission of the Focal Point program and the Stockpile Transition Enabling Program (STEP) ismore » to develop processes for meeting these challenges. Focal Point offers a decision-making process for allocating Sandia's resources to meets its defense programs strategic goals. (2) Defense Programs news in brief. (3) Dismantling the nuclear stockpile. (4) W88/MK5: Arming, Fuzing, and Firing system meets all requirements and goals. (5) The Common Radar Fuze. (6) Insertable-explosive arming of firing sets. (7) Preparing for fewer underground tests.« less

High Stability Engine Control (HISTEC) Flight Test Results

NASA Technical Reports Server (NTRS)

Southwick, Robert D.; Gallops, George W.; Kerr, Laura J.; Kielb, Robert P.; Welsh, Mark G.; DeLaat, John C.; Orme, John S.

1998-01-01

The High Stability Engine Control (HISTEC) Program, managed and funded by the NASA Lewis Research Center, is a cooperative effort between NASA and Pratt & Whitney (P&W). The program objective is to develop and flight demonstrate an advanced high stability integrated engine control system that uses real-time, measurement-based estimation of inlet pressure distortion to enhance engine stability. Flight testing was performed using the NASA Advanced Controls Technologies for Integrated Vehicles (ACTIVE) F-15 aircraft at the NASA Dryden Flight Research Center. The flight test configuration, details of the research objectives, and the flight test matrix to achieve those objectives are presented. Flight test results are discussed that show the design approach can accurately estimate distortion and perform real-time control actions for engine accommodation.

14 CFR 21.37 - Flight test pilot.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 1 2014-01-01 2014-01-01 false Flight test pilot. 21.37 Section 21.37... PROCEDURES FOR PRODUCTS AND PARTS Type Certificates § 21.37 Flight test pilot. Each applicant for a normal... holding an appropriate pilot certificate to make the flight tests required by this part. [Doc. No. 5085...

14 CFR 21.37 - Flight test pilot.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 1 2010-01-01 2010-01-01 false Flight test pilot. 21.37 Section 21.37... PROCEDURES FOR PRODUCTS AND PARTS Type Certificates § 21.37 Flight test pilot. Each applicant for a normal... holding an appropriate pilot certificate to make the flight tests required by this part. [Doc. No. 5085...

14 CFR 21.35 - Flight tests.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Flight tests. 21.35 Section 21.35... PROCEDURES FOR PRODUCTS AND PARTS Type Certificates § 21.35 Flight tests. (a) Each applicant for an aircraft...) That the aircraft conforms with the type design; and (4) That the Administrator received a flight test...

14 CFR 21.35 - Flight tests.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 1 2012-01-01 2012-01-01 false Flight tests. 21.35 Section 21.35... PROCEDURES FOR PRODUCTS AND PARTS Type Certificates § 21.35 Flight tests. (a) Each applicant for an aircraft...) That the aircraft conforms with the type design; and (4) That the FAA received a flight test report...

14 CFR 21.37 - Flight test pilot.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 1 2011-01-01 2011-01-01 false Flight test pilot. 21.37 Section 21.37... PROCEDURES FOR PRODUCTS AND PARTS Type Certificates § 21.37 Flight test pilot. Each applicant for a normal... holding an appropriate pilot certificate to make the flight tests required by this part. [Doc. No. 5085...

National remote computational flight research facility

NASA Technical Reports Server (NTRS)

Rediess, Herman A.

1989-01-01

The extension of the NASA Ames-Dryden remotely augmented vehicle (RAV) facility to accommodate flight testing of a hypersonic aircraft utilizing the continental United States as a test range is investigated. The development and demonstration of an automated flight test management system (ATMS) that uses expert system technology for flight test planning, scheduling, and execution is documented.

Thematic mapper flight model preshipment review data package. Volume 4: Appendix. Part B: Scan mirror assembly data

NASA Technical Reports Server (NTRS)

1982-01-01

Data from the thematic mapper scan mirror assembly (SMA) acceptance test are presented. Documentation includes: (1) a list of the acceptance test discrepancies; (2) flight 1 SMA test data book; (3) flight 1 SMA environmental report; (4) the configuration verification index; (5) the flight 1 SMA test failure reports; (6) the flight 1 data tapes log; and (7) the requests for deviation/waivers.

Small-scale fixed wing airplane software verification flight test

NASA Astrophysics Data System (ADS)

Miller, Natasha R.

The increased demand for micro Unmanned Air Vehicles (UAV) driven by military requirements, commercial use, and academia is creating a need for the ability to quickly and accurately conduct low Reynolds Number aircraft design. There exist several open source software programs that are free or inexpensive that can be used for large scale aircraft design, but few software programs target the realm of low Reynolds Number flight. XFLR5 is an open source, free to download, software program that attempts to take into consideration viscous effects that occur at low Reynolds Number in airfoil design, 3D wing design, and 3D airplane design. An off the shelf, remote control airplane was used as a test bed to model in XFLR5 and then compared to flight test collected data. Flight test focused on the stability modes of the 3D plane, specifically the phugoid mode. Design and execution of the flight tests were accomplished for the RC airplane using methodology from full scale military airplane test procedures. Results from flight test were not conclusive in determining the accuracy of the XFLR5 software program. There were several sources of uncertainty that did not allow for a full analysis of the flight test results. An off the shelf drone autopilot was used as a data collection device for flight testing. The precision and accuracy of the autopilot is unknown. Potential future work should investigate flight test methods for small scale UAV flight.

Space Shuttle stability and control test plan

NASA Technical Reports Server (NTRS)

Cooke, D. R.

1982-01-01

The development of a completely automatic flight test program to test different aspects of the Shuttle flight capability during reentries is described. Data from each flight to date has been employed to devise a sequence of maneuvers which will be keyboard-punched into the Orbiter control system by the astronauts during entry phases of flight. Details of the interaction and cooperation of the Orbiter elevons and bodyflap to provide the vehicle with latitudinal and longitudinal directional control and trim are outlined. Uncertainties predicted for the control of the Orbiter during wind tunnel testing prior to actual flights have been adjusted to actual flight data, leading to the identification of actual flight regimes which need further investigation. Maneuvers scheduled for flights 5-9 are reviewed.

Real-Time Onboard Global Nonlinear Aerodynamic Modeling from Flight Data

NASA Technical Reports Server (NTRS)

Brandon, Jay M.; Morelli, Eugene A.

2014-01-01

Flight test and modeling techniques were developed to accurately identify global nonlinear aerodynamic models onboard an aircraft. The techniques were developed and demonstrated during piloted flight testing of an Aermacchi MB-326M Impala jet aircraft. Advanced piloting techniques and nonlinear modeling techniques based on fuzzy logic and multivariate orthogonal function methods were implemented with efficient onboard calculations and flight operations to achieve real-time maneuver monitoring and analysis, and near-real-time global nonlinear aerodynamic modeling and prediction validation testing in flight. Results demonstrated that global nonlinear aerodynamic models for a large portion of the flight envelope were identified rapidly and accurately using piloted flight test maneuvers during a single flight, with the final identified and validated models available before the aircraft landed.

Design and utilization of a Flight Test Engineering Database Management System at the NASA Dryden Flight Research Facility

NASA Technical Reports Server (NTRS)

Knighton, Donna L.

1992-01-01

A Flight Test Engineering Database Management System (FTE DBMS) was designed and implemented at the NASA Dryden Flight Research Facility. The X-29 Forward Swept Wing Advanced Technology Demonstrator flight research program was chosen for the initial system development and implementation. The FTE DBMS greatly assisted in planning and 'mass production' card preparation for an accelerated X-29 research program. Improved Test Plan tracking and maneuver management for a high flight-rate program were proven, and flight rates of up to three flights per day, two times per week were maintained.

Predicting hypoxaemia during flights in children with cystic fibrosis

PubMed Central

Buchdahl, R; Babiker, A; Bush, A; Cramer, D

2001-01-01

BACKGROUND—We have previously suggested that it is possible to predict oxygen desaturation during flight in children with cystic fibrosis and chronic lung disease by non-invasive measurement of oxygen saturation following inhalation of 15% oxygen—the pre-flight hypoxic challenge. This study reports on the results of measurements over 5years.
METHODS—The study comprised a pre-flight hypoxic challenge measuring oxygen saturation by finger tip pulse oximetry (SpO2) during tidal breathing of 15% oxygen in nitrogen and spirometric testing 1 month before the flight followed by SpO2 measurements during intercontinental flights to and from holidays abroad with children in wake and sleep states.
RESULTS—Pre-flight tests were completed on 87 children with cystic fibrosis. Desaturation of <90% occurred in 10 children at some stage during the flight, three of whom received supplementary oxygen. Using a cut off SpO2 of 90%, the pre-flight hypoxic challenge correctly predicted desaturation in only two of these children. The sensitivity and specificity of the pre-flight hypoxic challenge were 20% and 99%, respectively, compared with 70% and 96% for spirometric tests (using a cut off for forced expiratory volume in 1 second (FEV1) of <50% predicted). Overall, pre-flight spirometric tests were a better predictor of desaturation during flight with the area under the Receiver Operating Characteristic (ROC) curve of 0.89 compared with 0.73 for the hypoxic challenge test.
CONCLUSIONS—In this group of subjects pre-flight spirometric testing was a better predictor of desaturation during flight than the pre-flight hypoxic challenge.

 PMID:11641514

Convection Weather Detection by General Aviation Pilots with Convectional and Data-Linked Graphical Weather Information Sources

NASA Technical Reports Server (NTRS)

Chamberlain, James P.; Latorella, Kara A.

2001-01-01

This study compares how well general aviation (GA) pilots detect convective weather in flight with different weather information sources. A flight test was conducted in which GA pilot test subjects were given different in-flight weather information cues and flown toward convective weather of moderate or greater intensity. The test subjects were not actually flying the aircraft, but were given pilot tasks representative of the workload and position awareness requirements of the en route portion of a cross country GA flight. On each flight, one test subject received weather cues typical of a flight in visual meteorological conditions (VMC), another received cues typical of flight in instrument meteorological conditions (IMC), and a third received cues typical of flight in IMC but augmented with a graphical weather information system (GWIS). The GWIS provided the subject with near real time data-linked weather products, including a weather radar mosaic superimposed on a moving map with a symbol depicting the aircraft's present position and direction of track. At several points during each flight, the test subjects completed short questionnaires which included items addressing their weather situation awareness and flight decisions. In particular, test subjects were asked to identify the location of the nearest convective cells. After the point of nearest approach to convective weather, the test subjects were asked to draw the location of convective weather on an aeronautical chart, along with the aircraft's present position. This paper reports preliminary results on how accurately test subjects provided with these different weather sources could identify the nearest cell of moderate or greater intensity along their route of flight. Additional flight tests are currently being conducted to complete the data set.

An overview of the F-117A avionics flight test program

DOE Office of Scientific and Technical Information (OSTI.GOV)

Silz, R.

1992-02-01

This paper is an overview of the history of the F-117A avionics flight test program. System design concepts and equipment selections are explored followed by a review of full scale development and full capability development testing. Flight testing the Weapon System Computational Subsystem upgrade and the Offensive Combat Improvement Program are reviewed. Current flight test programs and future system updates are highlighted.

An Overview of Controls and Flying Qualities Technology on the F/A-18 High Alpha Research Vehicle

NASA Technical Reports Server (NTRS)

Pahle, Joseph W.; Wichman, Keith D.; Foster, John V.; Bundick, W. Thomas

1996-01-01

The NASA F/A-18 High Alpha Research Vehicle (HARV) has been the flight test bed of a focused technology effort to significantly increase maneuvering capability at high angles of attack. Development and flight test of control law design methodologies, handling qualities metrics, performance guidelines, and flight evaluation maneuvers are described. The HARV has been modified to include two research control effectors, thrust vectoring, and actuated forebody strakes in order to provide increased control power at high angles of attack. A research flight control system has been used to provide a flexible, easily modified capability for high-angle-of-attack research controls. Different control law design techniques have been implemented and flight-tested, including eigenstructure assignment, variable gain output feedback, pseudo controls, and model-following. Extensive piloted simulation has been used to develop nonlinear performance guide-lines and handling qualities criteria for high angles of attack. This paper reviews the development and evaluation of technologies useful for high-angle-of-attack control. Design, development, and flight test of the research flight control system, control laws, flying qualities specifications, and flight test maneuvers are described. Flight test results are used to illustrate some of the lessons learned during flight test and handling qualities evaluations.

Aerodynamic Models for the Low Density Supersonic Decelerator (LDSD) Test Vehicles

NASA Technical Reports Server (NTRS)

Van Norman, John W.; Dyakonov, Artem; Schoenenberger, Mark; Davis, Jody; Muppidi, Suman; Tang, Chun; Bose, Deepak; Mobley, Brandon; Clark, Ian

2016-01-01

An overview of aerodynamic models for the Low Density Supersonic Decelerator (LDSD) Supersonic Flight Dynamics Test (SFDT) campaign test vehicle is presented, with comparisons to reconstructed flight data and discussion of model updates. The SFDT campaign objective is to test Supersonic Inflatable Aerodynamic Decelerator (SIAD) and large supersonic parachute technologies at high altitude Earth conditions relevant to entry, descent, and landing (EDL) at Mars. Nominal SIAD test conditions are attained by lifting a test vehicle (TV) to 36 km altitude with a helium balloon, then accelerating the TV to Mach 4 and 53 km altitude with a solid rocket motor. Test flights conducted in June of 2014 (SFDT-1) and 2015 (SFDT-2) each successfully delivered a 6 meter diameter decelerator (SIAD-R) to test conditions and several seconds of flight, and were successful in demonstrating the SFDT flight system concept and SIAD-R technology. Aerodynamic models and uncertainties developed for the SFDT campaign are presented, including the methods used to generate them and their implementation within an aerodynamic database (ADB) routine for flight simulations. Pre- and post-flight aerodynamic models are compared against reconstructed flight data and model changes based upon knowledge gained from the flights are discussed. The pre-flight powered phase model is shown to have a significant contribution to off-nominal SFDT trajectory lofting, while coast and SIAD phase models behaved much as predicted.

Instrument Pilot: Airplane. Flight Test Guide, Part 61 Revised 1973, AC 61-56.

ERIC Educational Resources Information Center

Federal Aviation Administration (DOT), Washington, DC. Flight Standards Service.

This flight test guide is designed to assist the applicant and his instructor in preparing for the flight test for Instrument Pilot Airplane Rating under Part 61 (revised) of Federal Aviation Regulations. It contains information concerning pilot operations, procedures, and maneuvers relevant to the flight test required for the Instrument Rating.…

Sierra Nevada Corporation's Dream Chaser Test Article Altitude T

NASA Image and Video Library

2017-08-30

Sierra Nevada Corporation’s Dream Chaser completed an important step toward orbital flight with a successful captive carry test at NASA’s Armstrong Flight Research Center in California, located on Edwards Air Force Base. A helicopter successfully carried a Dream Chaser test article, which has the same specifications as a flight-ready spacecraft, to the same altitude and flight conditions of an upcoming free flight test. The Dream Chaser is a lifting-body, winged spacecraft that will fly back to Earth in a manner similar to NASA’s space shuttles. The successful captive carry test clears the way for a free flight test of the spacecraft later this year in which the uncrewed Dream Chaser will be released to glide on its own and land.

Auxiliary propulsion system flight package

NASA Technical Reports Server (NTRS)

Collett, C. R.

1987-01-01

Hughes Aircraft Company developed qualified and integrated flight, a flight test Ion Auxiliary Propulsion System (IAPS), on an Air Force technology satellite. The IAPS Flight Package consists of two identical Thruster Subsystems and a Diagnostic Subsystem. Each thruster subsystem (TSS) is comprised of an 8-cm ion Thruster-Gimbal-Beam Shield Unit (TGBSU); Power Electronics Unit; Digital Controller and Interface Unit (DCIU); and Propellant Tank, Valve and Feed Unit (PTVFU) plus the requisite cables. The Diagnostic Subsystem (DSS) includes four types of sensors for measuring the effect of the ion thrusters on the spacecraft and the surrounding plasma. Flight qualifications of IAPS, prior to installation on the spacecraft, consisted of performance, vibration and thermal-vacuum testing at the unit level, and thermal-vacuum testing at the subsystem level. Mutual compatibility between IAPS and the host spacecraft was demonstrated during a series of performance and environmental tests after the IAPS Flight Package was installed on the spacecraft. After a spacecraft acoustic test, performance of the ion thrusters was reverified by removing the TGBSUs for a thorough performance test at Hughes Research Laboratories (HRL). The TGBSUs were then reinstalled on the spacecraft. The IAPS Flight Package is ready for flight testing when Shuttle flights are resumed.

Descent and Landing Triggers for the Orion Multi-Purpose Crew Vehicle Exploration Flight Test-1

NASA Technical Reports Server (NTRS)

Bihari, Brian D.; Semrau, Jeffrey D.; Duke, Charity J.

2013-01-01

The Orion Multi-Purpose Crew Vehicle (MPCV) will perform a flight test known as Exploration Flight Test-1 (EFT-1) currently scheduled for 2014. One of the primary functions of this test is to exercise all of the important Guidance, Navigation, Control (GN&C), and Propulsion systems, along with the flight software for future flights. The Descent and Landing segment of the flight is governed by the requirements levied on the GN&C system by the Landing and Recovery System (LRS). The LRS is a complex system of parachutes and flight control modes that ensure that the Orion MPCV safely lands at its designated target in the Pacific Ocean. The Descent and Landing segment begins with the jettisoning of the Forward Bay Cover and concludes with sensing touchdown. This paper discusses the requirements, design, testing, analysis and performance of the current EFT-1 Descent and Landing Triggers flight software.

An Assessment of Ares I-X Aeroacoustic Measurements with Comparisons to Pre-Flight Wind Tunnel Test Results

NASA Technical Reports Server (NTRS)

Nance, Donald K.; Reed, Darren K.

2011-01-01

During the recent successful launch of the Ares I-X Flight Test Vehicle, aeroacoustic data was gathered at fifty-seven locations along the vehicle as part of the Developmental Flight Instrumentation. Several of the Ares I-X aeroacoustic measurements were placed to duplicate measurement locations prescribed in pre-flight, sub-scale wind tunnel tests. For these duplicated measurement locations, comparisons have been made between aeroacoustic data gathered during the ascent phase of the Ares I-X flight test and wind tunnel test data. These comparisons have been made at closely matching flight conditions (Mach number and vehicle attitude) in order to preserve a one-to-one relationship between the flight and wind tunnel data. These comparisons and the current wind tunnel to flight scaling methodology are presented and discussed. The implications of using wind tunnel test data scaled under the current methodology to predict conceptual launch vehicle aeroacoustic environments are also discussed.

Orion Launch Abort System Performance During Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

McCauley, Rachel; Davidson, John; Gonzalez, Guillo

2015-01-01

The Orion Launch Abort System Office is taking part in flight testing to enable certification that the system is capable of delivering the astronauts aboard the Orion Crew Module to a safe environment during both nominal and abort conditions. Orion is a NASA program, Exploration Flight Test 1 is managed and led by the Orion prime contractor, Lockheed Martin, and launched on a United Launch Alliance Delta IV Heavy rocket. Although the Launch Abort System Office has tested the critical systems to the Launch Abort System jettison event on the ground, the launch environment cannot be replicated completely on Earth. During Exploration Flight Test 1, the Launch Abort System was to verify the function of the jettison motor to separate the Launch Abort System from the crew module so it can continue on with the mission. Exploration Flight Test 1 was successfully flown on December 5, 2014 from Cape Canaveral Air Force Station's Space Launch Complex 37. This was the first flight test of the Launch Abort System preforming Orion nominal flight mission critical objectives. The abort motor and attitude control motors were inert for Exploration Flight Test 1, since the mission did not require abort capabilities. Exploration Flight Test 1 provides critical data that enable engineering to improve Orion's design and reduce risk for the astronauts it will protect as NASA continues to move forward on its human journey to Mars. The Exploration Flight Test 1 separation event occurred at six minutes and twenty seconds after liftoff. The separation of the Launch Abort System jettison occurs once Orion is safely through the most dynamic portion of the launch. This paper will present a brief overview of the objectives of the Launch Abort System during a nominal Orion flight. Secondly, the paper will present the performance of the Launch Abort System at it fulfilled those objectives. The lessons learned from Exploration Flight Test 1 and the other Flight Test Vehicles will certainly contribute to the vehicle architecture of a human-rated space launch vehicle.

Full-Scaled Advanced Systems Testbed: Ensuring Success of Adaptive Control Research Through Project Lifecycle Risk Mitigation

NASA Technical Reports Server (NTRS)

Pavlock, Kate M.

2011-01-01

The National Aeronautics and Space Administration's Dryden Flight Research Center completed flight testing of adaptive controls research on the Full-Scale Advance Systems Testbed (FAST) in January of 2011. The research addressed technical challenges involved with reducing risk in an increasingly complex and dynamic national airspace. Specific challenges lie with the development of validated, multidisciplinary, integrated aircraft control design tools and techniques to enable safe flight in the presence of adverse conditions such as structural damage, control surface failures, or aerodynamic upsets. The testbed is an F-18 aircraft serving as a full-scale vehicle to test and validate adaptive flight control research and lends a significant confidence to the development, maturation, and acceptance process of incorporating adaptive control laws into follow-on research and the operational environment. The experimental systems integrated into FAST were designed to allow for flexible yet safe flight test evaluation and validation of modern adaptive control technologies and revolve around two major hardware upgrades: the modification of Production Support Flight Control Computers (PSFCC) and integration of two, fourth-generation Airborne Research Test Systems (ARTS). Post-hardware integration verification and validation provided the foundation for safe flight test of Nonlinear Dynamic Inversion and Model Reference Aircraft Control adaptive control law experiments. To ensure success of flight in terms of cost, schedule, and test results, emphasis on risk management was incorporated into early stages of design and flight test planning and continued through the execution of each flight test mission. Specific consideration was made to incorporate safety features within the hardware and software to alleviate user demands as well as into test processes and training to reduce human factor impacts to safe and successful flight test. This paper describes the research configuration, experiment functionality, overall risk mitigation, flight test approach and results, and lessons learned of adaptive controls research of the Full-Scale Advanced Systems Testbed.

An Overview of Flight Test Results for a Formation Flight Autopilot

NASA Technical Reports Server (NTRS)

Hanson, Curtis E.; Ryan, Jack; Allen, Michael J.; Jacobson, Steven R.

2002-01-01

The first flight test phase of the NASA Dryden Flight Research Center Autonomous Formation Flight project has successfully demonstrated precision autonomous station-keeping of an F/A-18 research airplane with a second F/A-18 airplane. Blended inertial navigation system (INS) and global positioning system (GPS) measurements have been communicated across an air-to-air telemetry link and used to compute relative-position estimates. A precision research formation autopilot onboard the trailing airplane controls lateral and vertical spacing while the leading airplane operates under production autopilot control. Four research autopilot gain sets have been designed and flight-tested, and each exceeds the project design requirement of steady-state tracking accuracy within 1 standard deviation of 10 ft. Performance also has been demonstrated using single- and multiple-axis inputs such as step commands and frequency sweeps. This report briefly describes the experimental formation flight systems employed and discusses the navigation, guidance, and control algorithms that have been flight-tested. An overview of the flight test results of the formation autopilot during steady-state tracking and maneuvering flight is presented.

Flight-Test Evaluation of Flutter-Prediction Methods

NASA Technical Reports Server (NTRS)

Lind, RIck; Brenner, Marty

2003-01-01

The flight-test community routinely spends considerable time and money to determine a range of flight conditions, called a flight envelope, within which an aircraft is safe to fly. The cost of determining a flight envelope could be greatly reduced if there were a method of safely and accurately predicting the speed associated with the onset of an instability called flutter. Several methods have been developed with the goal of predicting flutter speeds to improve the efficiency of flight testing. These methods include (1) data-based methods, in which one relies entirely on information obtained from the flight tests and (2) model-based approaches, in which one relies on a combination of flight data and theoretical models. The data-driven methods include one based on extrapolation of damping trends, one that involves an envelope function, one that involves the Zimmerman-Weissenburger flutter margin, and one that involves a discrete-time auto-regressive model. An example of a model-based approach is that of the flutterometer. These methods have all been shown to be theoretically valid and have been demonstrated on simple test cases; however, until now, they have not been thoroughly evaluated in flight tests. An experimental apparatus called the Aerostructures Test Wing (ATW) was developed to test these prediction methods.

Flight testing of airbreathing hypersonic vehicles

NASA Technical Reports Server (NTRS)

Hicks, John W.

1993-01-01

Using the scramjet engine as the prime example of a hypersonic airbreathing concept, this paper reviews the history of and addresses the need for hypersonic flight tests. It also describes how such tests can contribute to the development of airbreathing technology. Aspects of captive-carry and free-flight concepts are compared. An incremental flight envelope expansion technique for manned flight vehicles is also described. Such critical issues as required instrumentation technology and proper scaling of experimental devices are addressed. Lastly, examples of international flight test approaches, existing programs, or concepts currently under study, development, or both, are given.

F-16XL ship #1 (#849) during first flight of the Digital Flight Control System (DFCS)

NASA Technical Reports Server (NTRS)

1997-01-01

After completing its first flight with the Digital Flight Control System on December 16, 1997, the F-16XL #1 aircraft began a series of envelope expansion flights. On January 27 and 29, 1998, it successfully completed structural clearance tests, as well as most of the load testing Only flights at Mach 1.05 at 10,000 feet, Mach 1.1 at 15,000 feet, and Mach 1.2 at 20,000 feet remained. During the next flight, on February 4, an instrumentation problem cut short the planned envelope expansion tests. After the problem was corrected, the F-16XL returned to flight status, and on February 18 and 20, flight control and evaluation flights were made. Two more research flights were planned for the following week, but another problem appeared. During the ground start up, project personnel noticed that the leading edge flap moved without being commanded. The Digital Flight Control Computer was sent to the Lockheed-Martin facility at Fort Worth, where the problem was traced to a defective chip in the computer. After it was replaced, the F-16XL #1 flew a highly successful flight controls and handling qualities evaluation flight on March 26, clearing the way for the final tests. The final limited loads expansion flight occurred on March 31, and was fully successful. As a result, the on-site Lockheed-Martin loads engineer cleared the aircraft to Mach 1.8. The remaining two handling qualities and flight control evaluation flights were both made on April 3, 1998. These three flights concluded the flight test portion of the DFCS upgrade.

Comparison of theoretical and flight-measured local flow aerodynamics for a low-aspect-ratio fin

NASA Technical Reports Server (NTRS)

Johnson, J. B.; Sandlin, D. R.

1984-01-01

Flight test and theoretical aerodynamic data were obtained for a flight test fixture mounted on the underside of an F-104G aircraft. The theoretical data were generated using two codes, a two dimensional transonic code called Code H, and a three dimensional subsonic and supersonic code call wing-body. Pressure distributions generated by the codes for the flight test fixture as well as boundary layer displacement thickness generated by the two dimensional code were compared to the flight test data. The two dimensional code pressure distributions compared well except at the minimum pressure point and trailing edge. Shock locations compared well except at high transonic speeds. The three dimensional code pressure distributions compared well except at the trailing edge of the flight test fixture. The two dimensional code does not predict displacement thickness of the flight test fixture well.

47 CFR 87.303 - Frequencies.

Code of Federal Regulations, 2010 CFR

2010-10-01

... telecommand operations for flight testing of aircraft and missiles, or their major components. The bands 2310... expendable and re-usable launch vehicles, whether or not such operations involve flight testing: 2364.5, 2370... Flight Test Stations § 87.303 Frequencies. (a) These frequencies are available for assignment to flight...

Wet countdown demonstration and flight readiness firing

NASA Technical Reports Server (NTRS)

1981-01-01

The prelaunch tests for the Space Transportation System 1 flight are briefly described. Testing is divided into two major sections: the wet countdown demonstration test/flight readiness firing, which includes a 20 second test firing of the orbiter's three main engines, and a mission verification test, which is centered on flight and landing operations. The functions of the countdown sequence are listed and end of mission and mission abort exercises are described.

Development and Flight Test of an Augmented Thrust-Only Flight Control System on an MD-11 Transport Airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Maine, Trindel A.; Burken, John J.; Pappas, Drew

1996-01-01

An emergency flight control system using only engine thrust, called Propulsion-Controlled Aircraft (PCA), has been developed and flight tested on an MD-11 airplane. In this thrust-only control system, pilot flight path and track commands and aircraft feedback parameters are used to control the throttles. The PCA system was installed on the MD-11 airplane using software modifications to existing computers. Flight test results show that the PCA system can be used to fly to an airport and safely land a transport airplane with an inoperative flight control system. In up-and-away operation, the PCA system served as an acceptable autopilot capable of extended flight over a range of speeds and altitudes. The PCA approaches, go-arounds, and three landings without the use of any non-nal flight controls have been demonstrated, including instrument landing system-coupled hands-off landings. The PCA operation was used to recover from an upset condition. In addition, PCA was tested at altitude with all three hydraulic systems turned off. This paper reviews the principles of throttles-only flight control; describes the MD-11 airplane and systems; and discusses PCA system development, operation, flight testing, and pilot comments.

Flight test and evaluation of Omega navigation in a general aviation aircraft. Volume 2: Appendices

NASA Technical Reports Server (NTRS)

Howell, J. D.; Hoffman, W. C.; Hwoschinsky, P. V.; Wischmeyer, C. E.

1975-01-01

Detailed documentation for each flight of the Omega Flight Evaluation study is presented, including flight test description sheets and actual flight data plots. Computer programs used for data processing and flight planning are explained and the data formats utilized by the Custom Interface Unit are summarized.

Integrated Testing Approaches for the NASA Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Taylor, James L.; Cockrell, Charles E.; Tuma, Margaret L.; Askins, Bruce R.; Bland, Jeff D.; Davis, Stephan R.; Patterson, Alan F.; Taylor, Terry L.; Robinson, Kimberly L.

2008-01-01

The Ares I crew launch vehicle is being developed by the U.S. National Aeronautics and Space Administration (NASA) to provide crew and cargo access to the International Space Station (ISS) and, together with the Ares V cargo launch vehicle, serves as a critical component of NASA's future human exploration of the Moon. During the preliminary design phase, NASA defined and began implementing plans for integrated ground and flight testing necessary to achieve the first human launch of Ares I. The individual Ares I flight hardware elements - including the first stage five segment booster (FSB), upper stage, and J-2X upper stage engine - will undergo extensive development, qualification, and certification testing prior to flight. Key integrated system tests include the upper stage Main Propulsion Test Article (MPTA), acceptance tests of the integrated upper stage and upper stage engine assembly, a full-scale integrated vehicle ground vibration test (IVGVT), aerodynamic testing to characterize vehicle performance, and integrated testing of the avionics and software components. The Ares I-X development flight test will provide flight data to validate engineering models for aerodynamic performance, stage separation, structural dynamic performance, and control system functionality. The Ares I-Y flight test will validate ascent performance of the first stage, stage separation functionality, validate the ability of the upper stage to manage cryogenic propellants to achieve upper stage engine start conditions, and a high-altitude demonstration of the launch abort system (LAS) following stage separation. The Orion 1 flight test will be conducted as a full, un-crewed, operational flight test through the entire ascent flight profile prior to the first crewed launch.

Integrated System Test Approaches for the NASA Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Cockrell, Charles E., Jr.; Askins, Bruce R.; Bland, Jeffrey; Davis, Stephan; Holladay, Jon B.; Taylor, James L.; Taylor, Terry L.; Robinson, Kimberly F.; Roberts, Ryan E.; Tuma, Margaret

2007-01-01

The Ares I Crew Launch Vehicle (CLV) is being developed by the U.S. National Aeronautics and Space Administration (NASA) to provide crew access to the International Space Station (ISS) and, together with the Ares V Cargo Launch Vehicle (CaLV), serves as one component of a future launch capability for human exploration of the Moon. During the system requirements definition process and early design cycles, NASA defined and began implementing plans for integrated ground and flight testing necessary to achieve the first human launch of Ares I. The individual Ares I flight hardware elements: the first stage five segment booster (FSB), upper stage, and J-2X upper stage engine, will undergo extensive development, qualification, and certification testing prior to flight. Key integrated system tests include the Main Propulsion Test Article (MPTA), acceptance tests of the integrated upper stage and upper stage engine assembly, a full-scale integrated vehicle dynamic test (IVDT), aerodynamic testing to characterize vehicle performance, and integrated testing of the avionics and software components. The Ares I-X development flight test will provide flight data to validate engineering models for aerodynamic performance, stage separation, structural dynamic performance, and control system functionality. The Ares I-Y flight test will validate ascent performance of the first stage, stage separation functionality, and a highaltitude actuation of the launch abort system (LAS) following separation. The Orion-1 flight test will be conducted as a full, un-crewed, operational flight test through the entire ascent flight profile prior to the first crewed launch.

Post-Flight Analysis of the Guidance, Navigation, and Control Performance During Orion Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

Barth, Andrew; Mamich, Harvey; Hoelscher, Brian

2015-01-01

The first test flight of the Orion Multi-Purpose Crew Vehicle presented additional challenges for guidance, navigation and control as compared to a typical re-entry from the International Space Station or other Low Earth Orbit. An elevated re-entry velocity and steeper flight path angle were chosen to achieve aero-thermal flight test objectives. New IMU's, a GPS receiver, and baro altimeters were flight qualified to provide the redundant navigation needed for human space flight. The guidance and control systems must manage the vehicle lift vector in order to deliver the vehicle to a precision, coastal, water landing, while operating within aerodynamic load, reaction control system, and propellant constraints. Extensive pre-flight six degree-of-freedom analysis was performed that showed mission success for the nominal mission as well as in the presence of sensor and effector failures. Post-flight reconstruction analysis of the test flight is presented in this paper to show whether that all performance metrics were met and establish how well the pre-flight analysis predicted the in-flight performance.

Aerothermodynamic Insight From The HIFIRE Program

NASA Astrophysics Data System (ADS)

Kimmel, Roger L.; Adamczak, David; Dolvin, Douglas; Borg, Matthew; Stanfield, Scott

2011-05-01

The HIFiRE (Hypersonic International Flight Research and Experimentation) program is a joint venture of the United States Air Force Research Laboratory and Australian Defence Science and Technology Organisation to utilize economical flight research opportunities in the exploration of flight science issues for space access systems. Flights 1 and 5 focus on collecting high-resolution experimental data on critical aerothermodynamic phenomena, including laminar-turbulent transition and shock/boundary layer interactions. Flight 1, successfully flown in March 2010, employed a test article composed of a 7-deg right angle cone, followed by a cylinder and flare. The test article remained attached to the second-stage booster throughout the ballistic trajectory. Flight 5, to be launched in a similar fashion, will feature a 2:1 elliptic cross-section cone as the test article. For both flights significant resources have been invested in pre-flight aerothermodynamic analysis and testing. This manuscript will summarize the overall strategy of the HIFiRE program, review the pre-flight aerothermodynamic analysis for Flights 1 and 5, and present a brief look at preliminary results from the post-flight analysis of Flight 1.

Actuated forebody strake controls for the F-18 high alpha research vehicle

NASA Technical Reports Server (NTRS)

Murri, Daniel G.; Shah, Gautam H.; Dicarlo, Daniel J.; Trilling, Todd W.

1993-01-01

A series of ground-based studies have been conducted to develop actuated forebody strake controls for flight test evaluations using the NASA F-18 High-Alpha Research Vehicle. The actuated forebody strake concept has been designed to provide increased levels of yaw control at high angles of attack where conventional rudders become ineffective. Results are presented from tests conducted with the flight-test strake design, including static and dynamic wind-tunnel tests, transonic wind-tunnel tests, full-scale wind-tunnel tests, pressure surveys, and flow visualization tests. Results from these studies show that a pair of conformal actuated forebody strakes applied to the F-18 HARV can provide a powerful and precise yaw control device at high angles of attack. The preparations for flight testing are described, including the fabrication of flight hardware and the development of aircraft flight control laws. The primary objectives of the flight tests are to provide flight validation of the groundbased studies and to evaluate the use of this type of control to enhance fighter aircraft maneuverability.

Low-speed wind-tunnel investigation of the flight dynamic characteristics of an advanced turboprop business/commuter aircraft configuration

NASA Technical Reports Server (NTRS)

Coe, Paul L., Jr.; Turner, Steven G.; Owens, D. Bruce

1990-01-01

An investigation was conducted to determine the low-speed flight dynamic behavior of a representative advanced turboprop business/commuter aircraft concept. Free-flight tests were conducted in the NASA Langley Research Center's 30- by 60-Foot Tunnel. In support of the free-flight tests, conventional static, dynamic, and free-to-roll oscillation tests were performed. Tests were intended to explore normal operating and post stall flight conditions, and conditions simulating the loss of power in one engine.

HIFiRE Direct-Connect Rig (HDCR) Phase I Ground Test Results from the NASA Langley Arc-Heated Scramjet Test Facility

NASA Technical Reports Server (NTRS)

Hass, Neal E.; Cabell, Karen F.; Storch, Andrea M.

2010-01-01

The initial phase of hydrocarbon-fueled ground tests supporting Flight 2 of the Hypersonic International Flight Research Experiment (HIFiRE) Program has been conducted in the NASA Langley Arc-Heated Scramjet Test Facility (AHSTF). The HIFiRE Program, an Air Force-lead international cooperative program includes eight different flight test experiments designed to target specific challenges of hypersonic flight. The second of the eight planned flight experiments is a hydrocarbon-fueled scramjet flight test intended to demonstrate dual-mode to scramjet-mode operation and verify the scramjet performance prediction and design tools. A performance goal is the achievement of a combusted fuel equivalence ratio greater than 0.7 while in scramjet mode. The ground test rig, designated the HIFiRE Direct Connect Rig (HDCR), is a full-scale, heat sink, direct-connect ground test article that duplicates both the flowpath lines and the instrumentation layout of the isolator and combustor portion of the flight test hardware. The primary objectives of the HDCR Phase I tests are to verify the operability of the HIFiRE isolator/combustor across the Mach 6.0-8.0 flight regime and to establish a fuel distribution schedule to ensure a successful mode transition prior to the HiFIRE payload Critical Design Review. Although the phase I test plans include testing over the Mach 6 to 8 flight simulation range, only Mach 6 testing will be reported in this paper. Experimental results presented here include flowpath surface pressure, temperature, and heat flux distributions that demonstrate the operation of the flowpath over a small range of test conditions around the nominal Mach 6 simulation, as well as a range of fuel equivalence ratios and fuel injection distributions. Both ethylene and a mixture of ethylene and methane (planned for flight) were tested. Maximum back pressure and flameholding limits, as well as a baseline fuel schedule, that covers the Mach 5.84-6.5 test space have been identified.

Overview of recent aero-optics flight tests

NASA Technical Reports Server (NTRS)

Otten, L. J., III

1980-01-01

A chronological overview of aero-optics test flights is presented highlighting the objectives and conclusions from the tests. Flight tests performed in coordination with the PRESS reentry observation missions and the ALL Cycle 2 laser propagation and tracking demonstrations are described addressing the identification and quantification of distortion phenomena. Finally, current aero-optics flight investigations of an atmospheric turbulence probe are briefly discussed.

Development and Testing of a High Stability Engine Control (HISTEC) System

NASA Technical Reports Server (NTRS)

Orme, John S.; DeLaat, John C.; Southwick, Robert D.; Gallops, George W.; Doane, Paul M.

1998-01-01

Flight tests were recently completed to demonstrate an inlet-distortion-tolerant engine control system. These flight tests were part of NASA's High Stability Engine Control (HISTEC) program. The objective of the HISTEC program was to design, develop, and flight demonstrate an advanced integrated engine control system that uses measurement-based, real-time estimates of inlet airflow distortion to enhance engine stability. With improved stability and tolerance of inlet airflow distortion, future engine designs may benefit from a reduction in design stall-margin requirements and enhanced reliability, with a corresponding increase in performance and decrease in fuel consumption. This paper describes the HISTEC methodology, presents an aircraft test bed description (including HISTEC-specific modifications) and verification and validation ground tests. Additionally, flight test safety considerations, test plan and technique design and approach, and flight operations are addressed. Some illustrative results are presented to demonstrate the type of analysis and results produced from the flight test program.

The Role of Flight Experiments in the Development of Cryogenic Fluid Management Technologies

NASA Technical Reports Server (NTRS)

Chato, David J.

2006-01-01

This paper reviews the history of cryogenic fluid management technology development and infusion into both the Saturn and Centaur vehicles. Ground testing and analysis proved inadequate to demonstrate full scale performance. As a consequence flight demonstration with a full scale vehicle was required by both the Saturn and Centaur programs to build confidence that problems were addressed. However; the flight vehicles were highly limited on flight instrumentation and the flight demonstration locked-in the design without challenging the function of design elements. Projects reviewed include: the Aerobee Sounding Rocket Cryogenic Fluid Management (CFM) tests which served as a valuable stepping stone to flight demonstration and built confidence in the ability to handle hydrogen in low gravity; the Saturn IVB Fluid Management Qualification flight test; the Atlas Centaur demonstration flights to develop two burn capability; and finally the Titan Centaur two post mission flight tests.

Supersonic Flight Dynamics Test: Trajectory, Atmosphere, and Aerodynamics Reconstruction

NASA Technical Reports Server (NTRS)

Kutty, Prasad; Karlgaard, Christopher D.; Blood, Eric M.; O'Farrell, Clara; Ginn, Jason M.; Shoenenberger, Mark; Dutta, Soumyo

2015-01-01

The Supersonic Flight Dynamics Test is a full-scale flight test of a Supersonic Inflatable Aerodynamic Decelerator, which is part of the Low Density Supersonic Decelerator technology development project. The purpose of the project is to develop and mature aerodynamic decelerator technologies for landing large mass payloads on the surface of Mars. The technologies include a Supersonic Inflatable Aerodynamic Decelerator and Supersonic Parachutes. The first Supersonic Flight Dynamics Test occurred on June 28th, 2014 at the Pacific Missile Range Facility. This test was used to validate the test architecture for future missions. The flight was a success and, in addition, was able to acquire data on the aerodynamic performance of the supersonic inflatable decelerator. This paper describes the instrumentation, analysis techniques, and acquired flight test data utilized to reconstruct the vehicle trajectory, atmosphere, and aerodynamics. The results of the reconstruction show significantly higher lofting of the trajectory, which can partially be explained by off-nominal booster motor performance. The reconstructed vehicle force and moment coefficients fall well within pre-flight predictions. A parameter identification analysis indicates that the vehicle displayed greater aerodynamic static stability than seen in pre-flight computational predictions and ballistic range tests.

Flight Approach to Adaptive Control Research

NASA Technical Reports Server (NTRS)

Pavlock, Kate Maureen; Less, James L.; Larson, David Nils

2011-01-01

The National Aeronautics and Space Administration's Dryden Flight Research Center completed flight testing of adaptive controls research on a full-scale F-18 testbed. The testbed served as a full-scale vehicle to test and validate adaptive flight control research addressing technical challenges involved with reducing risk to enable safe flight in the presence of adverse conditions such as structural damage or control surface failures. This paper describes the research interface architecture, risk mitigations, flight test approach and lessons learned of adaptive controls research.

The development of an automated flight test management system for flight test planning and monitoring

NASA Technical Reports Server (NTRS)

Hewett, Marle D.; Tartt, David M.; Duke, Eugene L.; Antoniewicz, Robert F.; Brumbaugh, Randal W.

1988-01-01

The development of an automated flight test management system (ATMS) as a component of a rapid-prototyping flight research facility for AI-based flight systems concepts is described. The rapid-prototyping facility includes real-time high-fidelity simulators, numeric and symbolic processors, and high-performance research aircraft modified to accept commands for a ground-based remotely augmented vehicle facility. The flight system configuration of the ATMS includes three computers: the TI explorer LX and two GOULD SEL 32/27s.

Development of a Low-Cost Sub-Scale Aircraft for Flight Research: The FASER Project

NASA Technical Reports Server (NTRS)

Owens, Donald B.; Cox, David E.; Morelli, Eugene A.

2006-01-01

An inexpensive unmanned sub-scale aircraft was developed to conduct frequent flight test experiments for research and demonstration of advanced dynamic modeling and control design concepts. This paper describes the aircraft, flight systems, flight operations, and data compatibility including details of some practical problems encountered and the solutions found. The aircraft, named Free-flying Aircraft for Sub-scale Experimental Research, or FASER, was outfitted with high-quality instrumentation to measure aircraft inputs and states, as well as vehicle health parameters. Flight data are stored onboard, but can also be telemetered to a ground station in real time for analysis. Commercial-off-the-shelf hardware and software were used as often as possible. The flight computer is based on the PC104 platform, and runs xPC-Target software. Extensive wind tunnel testing was conducted with the same aircraft used for flight testing, and a six degree-of-freedom simulation with nonlinear aerodynamics was developed to support flight tests. Flight tests to date have been conducted to mature the flight operations, validate the instrumentation, and check the flight data for kinematic consistency. Data compatibility analysis showed that the flight data are accurate and consistent after corrections are made for estimated systematic instrumentation errors.

Space Shuttle Orbiter Approach and Landing Test: Final Evaluation Report

NASA Technical Reports Server (NTRS)

1978-01-01

The Approach and Landing Test Program consisted of a series of steps leading to the demonstration of the capability of the Space Shuttle orbiter to safely approach and land under conditions similar to those planned for the final phases of an orbital flight. The tests were conducted with the orbiter mounted on top of a specially modified carrier aircraft. The first step provided airworthiness and performance verification of the carrier aircraft after modification. The second step consisted of three taxi tests and five flight tests with an inert unmanned orbiter. The third step consisted of three mated tests with an active manned orbiter. The fourth step consisted of five flights in which the orbiter was separated from the carrier aircraft. For the final two flights, the orbiter tail cone was replaced by dummy engines to simulate the actual orbital configuration. Landing gear braking and steering tests were accomplished during rollouts following the free flight landings. Ferry testing was integrated into the Approach and Landing Test Program to the extent possible. In addition, four ferry test flights were conducted with the orbiter mated to the carrier aircraft in the ferry configuration after the free-flight tests were completed.

Thermal/vacuum vs. thermal atmospheric testing of space flight electronic assemblies

NASA Technical Reports Server (NTRS)

Gibbel, Mark

1990-01-01

For space flight hardware, the thermal vacuum environmental test is the best test of a system's flight worthiness. Substituting an atmospheric pressure thermal test for a thermal/vacuum test can effectively reduce piece part temperatures by 20 C or more, even for low power density designs. Similar reductions in test effectiveness can also result from improper assembly level T/V test boundary conditions. The net result of these changes may reduce the effective test temperatures to the point where there is zero or negative margin over the flight thermal environment.

Flight Testing the X-48B at the Dryden Flight Research Center

NASA Technical Reports Server (NTRS)

Cosenito, Gary B.

2010-01-01

Topics discussed include: a) UAV s at NASA Dryden, Past and Present; b) Why Do We Flight Test?; c) The Blended (or Hybrid) Wing-Body Advantage; d) Program Objectives; e) The X-48B Vehicle and Ground Control Station; and f) Flight Test Highlights & Video.

First Test Flight Thermal Performance of the Low Density Supersonic Decelerator (LDSD) Supersonic Flight Dynamics Test (SFDT) Vehicle

NASA Technical Reports Server (NTRS)

Mastropietro, A.J.; Kempenaar, Jason; Redmond, Matthew; Pauken, Michael; Ancarrow, Walt

2015-01-01

The thermal telemetry from the first test flight, an assessment of post-flight inspections of the recovered vehicle, and a review of the thermal design and model of the vehicle will be presented along with several lessons learned.

14 CFR 135.295 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... PERSONS ON BOARD SUCH AIRCRAFT Crewmember Testing Requirements § 135.295 Initial and recurrent flight attendant crewmember testing requirements. No certificate holder may use a flight attendant crewmember, nor... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Initial and recurrent flight attendant...

14 CFR 135.295 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... PERSONS ON BOARD SUCH AIRCRAFT Crewmember Testing Requirements § 135.295 Initial and recurrent flight attendant crewmember testing requirements. No certificate holder may use a flight attendant crewmember, nor... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Initial and recurrent flight attendant...

14 CFR 135.295 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2010 CFR

2010-01-01

... PERSONS ON BOARD SUCH AIRCRAFT Crewmember Testing Requirements § 135.295 Initial and recurrent flight attendant crewmember testing requirements. No certificate holder may use a flight attendant crewmember, nor... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Initial and recurrent flight attendant...

14 CFR 135.295 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... PERSONS ON BOARD SUCH AIRCRAFT Crewmember Testing Requirements § 135.295 Initial and recurrent flight attendant crewmember testing requirements. No certificate holder may use a flight attendant crewmember, nor... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Initial and recurrent flight attendant...

14 CFR 125.289 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... AIRCRAFT Flight Crewmember Requirements § 125.289 Initial and recurrent flight attendant crewmember testing... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Initial and recurrent flight attendant crewmember testing requirements. 125.289 Section 125.289 Aeronautics and Space FEDERAL AVIATION...

14 CFR 125.289 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2010 CFR

2010-01-01

... AIRCRAFT Flight Crewmember Requirements § 125.289 Initial and recurrent flight attendant crewmember testing... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Initial and recurrent flight attendant crewmember testing requirements. 125.289 Section 125.289 Aeronautics and Space FEDERAL AVIATION...

14 CFR 91.1067 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... recurrent flight attendant crewmember testing requirements. No program manager or owner may use a flight... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Initial and recurrent flight attendant crewmember testing requirements. 91.1067 Section 91.1067 Aeronautics and Space FEDERAL AVIATION...

14 CFR 135.295 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2011 CFR

2011-01-01

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14 CFR 125.289 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... AIRCRAFT Flight Crewmember Requirements § 125.289 Initial and recurrent flight attendant crewmember testing... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Initial and recurrent flight attendant crewmember testing requirements. 125.289 Section 125.289 Aeronautics and Space FEDERAL AVIATION...

14 CFR 91.1067 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2010 CFR

2010-01-01

... recurrent flight attendant crewmember testing requirements. No program manager or owner may use a flight... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Initial and recurrent flight attendant crewmember testing requirements. 91.1067 Section 91.1067 Aeronautics and Space FEDERAL AVIATION...

14 CFR 91.1067 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... recurrent flight attendant crewmember testing requirements. No program manager or owner may use a flight... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Initial and recurrent flight attendant crewmember testing requirements. 91.1067 Section 91.1067 Aeronautics and Space FEDERAL AVIATION...

14 CFR 125.289 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... AIRCRAFT Flight Crewmember Requirements § 125.289 Initial and recurrent flight attendant crewmember testing... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Initial and recurrent flight attendant crewmember testing requirements. 125.289 Section 125.289 Aeronautics and Space FEDERAL AVIATION...

14 CFR 125.289 - Initial and recurrent flight attendant crewmember testing requirements.

Code of Federal Regulations, 2011 CFR

2011-01-01

... AIRCRAFT Flight Crewmember Requirements § 125.289 Initial and recurrent flight attendant crewmember testing... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Initial and recurrent flight attendant crewmember testing requirements. 125.289 Section 125.289 Aeronautics and Space FEDERAL AVIATION...

The art and science of missile defense sensor design

NASA Astrophysics Data System (ADS)

McComas, Brian K.

2014-06-01

A Missile Defense Sensor is a complex optical system, which sits idle for long periods of time, must work with little or no on-­board calibration, be used to find and discriminate targets, and guide the kinetic warhead to the target within minutes of launch. A short overview of the Missile Defense problem will be discussed here, as well as, the top-level performance drivers, like Noise Equivalent Irradiance (NEI), Acquisition Range, and Dynamic Range. These top-level parameters influence the choice of optical system, mechanical system, focal plane array (FPA), Read Out Integrated Circuit (ROIC), and cryogenic system. This paper will not only discuss the physics behind the performance of the sensor, but it will also discuss the "art" of optimizing the performance of the sensor given the top level performance parameters. Balancing the sensor sub-­systems is key to the sensor's performance in these highly stressful missions. Top-­level performance requirements impact the choice of lower level hardware and requirements. The flow down of requirements to the lower level hardware will be discussed. This flow down directly impacts the FPA, where careful selection of the detector is required. The flow down also influences the ROIC and cooling requirements. The key physics behind the detector and cryogenic system interactions will be discussed, along with the balancing of subsystem performance. Finally, the overall system balance and optimization will be discussed in the context of missile defense sensors and expected performance of the overall kinetic warhead.

Enterprise - Free Flight after Separation from 747

NASA Technical Reports Server (NTRS)

1977-01-01

The Space Shuttle prototype Enterprise flies free after being released from NASA's 747 Shuttle Carrier Aircraft (SCA) over Rogers Dry Lake during the second of five free flights carried out at the Dryden Flight Research Center, Edwards, California, as part of the Shuttle program's Approach and Landing Tests (ALT) in 1977. The tests were conducted to verify orbiter aerodynamics and handling characteristics in preparation for orbital flights with the Space Shuttle Columbia. A tail cone over the main engine area of Enterprise smoothed out turbulent airflow during flight. It was removed on the two last free flights to accurately check approach and landing characteristics. A series of test flights during which Enterprise was taken aloft atop the SCA, but was not released, preceded the free flight tests. The Space Shuttle Approach and Landings Tests (ALT) program allowed pilots and engineers to learn how the Space Shuttle and the modified Boeing 747 Shuttle Carrier Aircraft (SCA) handled during low-speed flight and landing. The Enterprise, a prototype of the Space Shuttles, and the SCA were flown to conduct the approach and landing tests at the NASA Dryden Flight Research Center, Edwards, California, from February to October 1977. The first flight of the program consisted of the Space Shuttle Enterprise attached to the Shuttle Carrier Aircraft. These flights were to determine how well the two vehicles flew together. Five 'captive-inactive' flights were flown during this first phase in which there was no crew in the Enterprise. The next series of captive flights was flown with a flight crew of two on board the prototype Space Shuttle. Only three such flights proved necessary. This led to the free-flight test series. The free-flight phase of the ALT program allowed pilots and engineers to learn how the Space Shuttle handled in low-speed flight and landing attitudes. For these landings, the Enterprise was flown by a crew of two after it was released from the top of the SCA. The vehicle was released at altitudes ranging from 19,000 to 26,000 feet. The Enterprise had no propulsion system, but its first four glides to the Rogers Dry Lake runway provided realistic, in-flight simulations of how subsequent Space Shuttles would be flown at the end of an orbital mission. The fifth approach and landing test, with the Enterprise landing on the Edwards Air Force Base concrete runway, revealed a problem with the Space Shuttle flight control system that made it susceptible to Pilot-Induced Oscillation (PIO), a potentially dangerous control problem during a landing. Further research using other NASA aircraft, especially the F-8 Digital-Fly-By-Wire aircraft, led to correction of the PIO problem before the first orbital flight. The Enterprise's last free-flight was October 26, 1977, after which it was ferried to other NASA centers for ground-based flight simulations that tested Space Shuttle systems and structure.

Lateral and longitudinal aerodynamic stability and control parameters of the basic vortex flap research aircraft as determined from flight test data

NASA Technical Reports Server (NTRS)

Suit, W. T.; Batterson, J. G.

1986-01-01

The aerodynamics of the basic F-106B were determined at selected points in the flight envelope. The test aircraft and flight procedures were presented. Aircraft instrumentation and the data system were discussed. The parameter extraction procedure was presented along with a discussion of the test flight results. The results were used to predict the aircraft motions for maneuvers that were not used to determine the vehicle aerodynamics. The control inputs used to maneuver the aircraft to get data for the determination of the aerodynamic parameters were discussed in the flight test procedures. The results from the current flight tests were compared with the results from wind tunnel test of the basic F-106B.

Hypersonic Research Vehicle (HRV) real-time flight test support feasibility and requirements study. Part 2: Remote computation support for flight systems functions

NASA Technical Reports Server (NTRS)

Rediess, Herman A.; Hewett, M. D.

1991-01-01

The requirements are assessed for the use of remote computation to support HRV flight testing. First, remote computational requirements were developed to support functions that will eventually be performed onboard operational vehicles of this type. These functions which either cannot be performed onboard in the time frame of initial HRV flight test programs because the technology of airborne computers will not be sufficiently advanced to support the computational loads required, or it is not desirable to perform the functions onboard in the flight test program for other reasons. Second, remote computational support either required or highly desirable to conduct flight testing itself was addressed. The use is proposed of an Automated Flight Management System which is described in conceptual detail. Third, autonomous operations is discussed and finally, unmanned operations.

Modelling of XCO₂ Surfaces Based on Flight Tests of TanSat Instruments.

PubMed

Zhang, Li Li; Yue, Tian Xiang; Wilson, John P; Wang, Ding Yi; Zhao, Na; Liu, Yu; Liu, Dong Dong; Du, Zheng Ping; Wang, Yi Fu; Lin, Chao; Zheng, Yu Quan; Guo, Jian Hong

2016-11-01

The TanSat carbon satellite is to be launched at the end of 2016. In order to verify the performance of its instruments, a flight test of TanSat instruments was conducted in Jilin Province in September, 2015. The flight test area covered a total area of about 11,000 km² and the underlying surface cover included several lakes, forest land, grassland, wetland, farmland, a thermal power plant and numerous cities and villages. We modeled the column-average dry-air mole fraction of atmospheric carbon dioxide (XCO₂) surface based on flight test data which measured the near- and short-wave infrared (NIR) reflected solar radiation in the absorption bands at around 760 and 1610 nm. However, it is difficult to directly analyze the spatial distribution of XCO₂ in the flight area using the limited flight test data and the approximate surface of XCO₂, which was obtained by regression modeling, which is not very accurate either. We therefore used the high accuracy surface modeling (HASM) platform to fill the gaps where there is no information on XCO₂ in the flight test area, which takes the approximate surface of XCO₂ as its driving field and the XCO₂ observations retrieved from the flight test as its optimum control constraints. High accuracy surfaces of XCO₂ were constructed with HASM based on the flight's observations. The results showed that the mean XCO₂ in the flight test area is about 400 ppm and that XCO₂ over urban areas is much higher than in other places. Compared with OCO-2's XCO₂, the mean difference is 0.7 ppm and the standard deviation is 0.95 ppm. Therefore, the modelling of the XCO₂ surface based on the flight test of the TanSat instruments fell within an expected and acceptable range.

Selected Flight Test Results for Online Learning Neural Network-Based Flight Control System

NASA Technical Reports Server (NTRS)

Williams, Peggy S.

2004-01-01

The NASA F-15 Intelligent Flight Control System project team has developed a series of flight control concepts designed to demonstrate the benefits of a neural network-based adaptive controller. The objective of the team is to develop and flight-test control systems that use neural network technology to optimize the performance of the aircraft under nominal conditions as well as stabilize the aircraft under failure conditions. Failure conditions include locked or failed control surfaces as well as unforeseen damage that might occur to the aircraft in flight. This report presents flight-test results for an adaptive controller using stability and control derivative values from an online learning neural network. A dynamic cell structure neural network is used in conjunction with a real-time parameter identification algorithm to estimate aerodynamic stability and control derivative increments to the baseline aerodynamic derivatives in flight. This set of open-loop flight tests was performed in preparation for a future phase of flights in which the learning neural network and parameter identification algorithm output would provide the flight controller with aerodynamic stability and control derivative updates in near real time. Two flight maneuvers are analyzed a pitch frequency sweep and an automated flight-test maneuver designed to optimally excite the parameter identification algorithm in all axes. Frequency responses generated from flight data are compared to those obtained from nonlinear simulation runs. An examination of flight data shows that addition of the flight-identified aerodynamic derivative increments into the simulation improved the pitch handling qualities of the aircraft.

Flight Test Results on the Stability and Control of the F-15B Quiet Spike Aircraft

NASA Technical Reports Server (NTRS)

Moua, Cheng; McWherter, Shaun H.; Cox, Timothy H.; Gera, Joseph

2007-01-01

The Quiet Spike (QS) flight research program was an aerodynamic and structural proof-of-concept of a telescoping sonic-boom suppressing nose boom on an F-15 B aircraft. The program goal was to collect flight data for model validation up to 1.8 Mach. The primary test philosophy was maintaining safety of flight. In the area of stability and controls the primary concerns were to assess the potential destabilizing effect of the spike on the stability, controllability, and handling qualities of the aircraft and to ensure adequate stability margins across the entire QS flight envelop. This paper reports on the stability and control methods used for flight envelope clearance and flight test results of the F-15B Quiet Spike. Also discussed are the flight test approach, the criteria to proceed to the next flight condition, brief pilot commentary on typical piloting tasks, approach and landing, and refueling task, and air data sensitivity to the flight control system.

Flight Test Implementation of a Second Generation Intelligent Flight Control System

NASA Technical Reports Server (NTRS)

Williams-Hayes, Peggy S.

2005-01-01

The NASA F-15 Intelligent Flight Control System project team has developed a series of flight control concepts designed to demonstrate the benefits of a neural network-based adaptive controller. The objective of the team was to develop and flight-test control systems that use neural network technology, to optimize the performance of the aircraft under nominal conditions, and to stabilize the aircraft under failure conditions. Failure conditions include locked or failed control surfaces as well as unforeseen damage that might occur to the aircraft in flight. The Intelligent Flight Control System team is currently in the process of implementing a second generation control scheme, collectively known as Generation 2 or Gen 2, for flight testing on the NASA F-15 aircraft. This report describes the Gen 2 system as implemented by the team for flight test evaluation. Simulation results are shown which describe the experiment to be performed in flight and highlight the ways in which the Gen 2 system meets the defined objectives.

Production Support Flight Control Computers: Research Capability for F/A-18 Aircraft at Dryden Flight Research Center

NASA Technical Reports Server (NTRS)

Carter, John F.

1997-01-01

NASA Dryden Flight Research Center (DFRC) is working with the United States Navy to complete ground testing and initiate flight testing of a modified set of F/A-18 flight control computers. The Production Support Flight Control Computers (PSFCC) can give any fleet F/A-18 airplane an in-flight, pilot-selectable research control law capability. NASA DFRC can efficiently flight test the PSFCC for the following four reasons: (1) Six F/A-18 chase aircraft are available which could be used with the PSFCC; (2) An F/A-18 processor-in-the-loop simulation exists for validation testing; (3) The expertise has been developed in programming the research processor in the PSFCC; and (4) A well-defined process has been established for clearing flight control research projects for flight. This report presents a functional description of the PSFCC. Descriptions of the NASA DFRC facilities, PSFCC verification and validation process, and planned PSFCC projects are also provided.

Development of flying qualities criteria for single pilot instrument flight operations

NASA Technical Reports Server (NTRS)

Bar-Gill, A.; Nixon, W. B.; Miller, G. E.

1982-01-01

Flying qualities criteria for Single Pilot Instrument Flight Rule (SPIFR) operations were investigated. The ARA aircraft was modified and adapted for SPIFR operations. Aircraft configurations to be flight-tested were chosen and matched on the ARA in-flight simulator, implementing modern control theory algorithms. Mission planning and experimental matrix design were completed. Microprocessor software for the onboard data acquisition system was debugged and flight-tested. Flight-path reconstruction procedure and the associated FORTRAN program were developed. Algorithms associated with the statistical analysis of flight test results and the SPIFR flying qualities criteria deduction are discussed.

Cardiac arrhythmias during aerobatic flight and its simulation on a centrifuge.

PubMed

Zawadzka-Bartczak, Ewelina K; Kopka, Lech H

2011-06-01

It is well known that accelerations during centrifuge training and during flight can provoke cardiac arrhythmias. Our study was designed to investigate both the similarities and differences between heart rhythm disturbances during flights and centrifuge tests. There were 40 asymptomatic, healthy pilots who performed two training flights and were also tested in a human centrifuge according to a program of rapid onset rate acceleration (ROR) and of centrifuge simulation of the actual acceleration experienced in flight (Simulation). During the flight and centrifuge tests ECG was monitored with the Holter method. ECG was examined for heart rhythm changes and disturbances. During flights, premature ventricular contractions (PVCs) were found in 25% of the subjects, premature supraventricular contractions (PSVCs) and PVCs with bigeminy in 5%, and pairs of PVCs in 2.5% of subjects. During the centrifuge tests, PVCs were experienced by 45% of the subjects, PSVCs and pairs of PVCs by 7.5%, and PVCs with bigeminy by 2.5%. Sinus bradycardia was observed during flights and centrifuge tests in 7.5% of subjects. Comparative evaluation of electrocardiographic records in military pilots during flights and centrifuge tests demonstrated that: 1) there were no clinically significant arrhythmias recorded; and 2) the frequency and kind of heart rhythm disturbances during aerobatic flight and its simulation on a centrifuge were not identical and did not occur repetitively in the same persons during equal phases of the tests.

CIAM/NASA Mach 6.5 Scramjet Flight and Ground Test

NASA Technical Reports Server (NTRS)

Voland, R. T.; Auslender, A. H.; Smart, M. K.; Roudakov, A. S.; Semenov, V. L.; Kopchenov, V.

1999-01-01

The Russian Central Institute of Aviation Motors (CIAM) performed a flight test of a CIAM-designed, hydrogen-cooled/fueled dual-mode scramjet engine over a Mach number range of approximately 3.5 to 6.4 on February 12, 1998, at the Sary Shagan test range in Kazakhstan. This rocket-boosted, captive-carry test of the axisymmetric engine reached the highest Mach number of any scramjet engine flight test to date. The flight test and the accompanying ground test program, conducted in a CIAM test facility near Moscow, were performed under a NASA contract administered by the Dryden Flight Research Center with technical assistance from the Langley Research Center. Analysis of the flight and ground data by both CIAM and NASA resulted in the following preliminary conclusions. An unexpected control sensor reading caused non-optimal fueling of the engine, and flowpath modifications added to the engine inlet during manufacture caused markedly reduced inlet performance. Both of these factors appear to have contributed to the dual-mode scramjet engine operating primarily in a subsonic combustion mode. At the maximum Mach number test point, combustion caused transition from supersonic flow at the fuel injector station to primarily subsonic flow in the combustor. Ground test data were obtained at similar conditions to the flight test, allowing for a meaningful comparison between the ground and flight data. The results of this comparison indicate that the differences in engine performance are small.

Flight research and testing

NASA Technical Reports Server (NTRS)

Putnam, Terrill W.; Ayers, Theodore G.

1989-01-01

Flight research and testing form a critical link in the aeronautic research and development chain. Brilliant concepts, elegant theories, and even sophisticated ground tests of flight vehicles are not sufficient to prove beyond a doubt that an unproven aeronautical concept will actually perform as predicted. Flight research and testing provide the ultimate proof that an idea or concept performs as expected. Ever since the Wright brothers, flight research and testing were the crucible in which aeronautical concepts were advanced and proven to the point that engineers and companies are willing to stake their future to produce and design aircraft. This is still true today, as shown by the development of the experimental X-30 aerospace plane. The Dryden Flight Research Center (Ames-Dryden) continues to be involved in a number of flight research programs that require understanding and characterization of the total airplane in all the aeronautical disciplines, for example the X-29. Other programs such as the F-14 variable-sweep transition flight experiment have focused on a single concept or discipline. Ames-Dryden also continues to conduct flight and ground based experiments to improve and expand the ability to test and evaluate advanced aeronautical concepts. A review of significant aeronautical flight research programs and experiments is presented to illustrate both the progress being made and the challenges to come.

Flight research and testing

NASA Technical Reports Server (NTRS)

Putnam, Terrill W.; Ayers, Theodore G.

1988-01-01

Flight research and testing form a critical link in the aeronautic R and D chain. Brilliant concepts, elegant theories, and even sophisticated ground tests of flight vehicles are not sufficient to prove beyond doubt that an unproven aeronautical concept will actually perform as predicted. Flight research and testing provide the ultimate proof that an idea or concept performs as expected. Ever since the Wright brothers, flight research and testing have been the crucible in which aeronautical concepts have advanced and been proven to the point that engineers and companies have been willing to stake their future to produce and design new aircraft. This is still true today, as shown by the development of the experimental X-30 aerospace plane. The Dryden Flight Research Center (Ames-Dryden) continues to be involved in a number of flight research programs that require understanding and characterization of the total airplane in all the aeronautical disciplines, for example the X-29. Other programs such as the F-14 variable-sweep transition flight experiment have focused on a single concept or discipline. Ames-Dryden also continues to conduct flight and ground based experiments to improve and expand the ability to test and evaluate advanced aeronautical concepts. A review of significant aeronautical flight research programs and experiments is presented to illustrate both the progress made and the challenges to come.

Aerodynamic Flight-Test Results for the Adaptive Compliant Trailing Edge

NASA Technical Reports Server (NTRS)

Cumming, Stephen B.; Smith, Mark S.; Ali, Aliyah N.; Bui, Trong T.; Ellsworth, Joel C.; Garcia, Christian A.

2016-01-01

The aerodynamic effects of compliant flaps installed onto a modified Gulfstream III airplane were investigated. Analyses were performed prior to flight to predict the aerodynamic effects of the flap installation. Flight tests were conducted to gather both structural and aerodynamic data. The airplane was instrumented to collect vehicle aerodynamic data and wing pressure data. A leading-edge stagnation detection system was also installed. The data from these flights were analyzed and compared with predictions. The predictive tools compared well with flight data for small flap deflections, but differences between predictions and flight estimates were greater at larger deflections. This paper describes the methods used to examine the aerodynamics data from the flight tests and provides a discussion of the flight-test results in the areas of vehicle aerodynamics, wing sectional pressure coefficient profiles, and air data.

Neural Network Modeling of UH-60A Pilot Vibration

NASA Technical Reports Server (NTRS)

Kottapalli, Sesi

2003-01-01

Full-scale flight-test pilot floor vibration is modeled using neural networks and full-scale wind tunnel test data for low speed level flight conditions. Neural network connections between the wind tunnel test data and the tlxee flight test pilot vibration components (vertical, lateral, and longitudinal) are studied. Two full-scale UH-60A Black Hawk databases are used. The first database is the NASMArmy UH-60A Airloads Program flight test database. The second database is the UH-60A rotor-only wind tunnel database that was acquired in the NASA Ames SO- by 120- Foot Wind Tunnel with the Large Rotor Test Apparatus (LRTA). Using neural networks, the flight-test pilot vibration is modeled using the wind tunnel rotating system hub accelerations, and separately, using the hub loads. The results show that the wind tunnel rotating system hub accelerations and the operating parameters can represent the flight test pilot vibration. The six components of the wind tunnel N/rev balance-system hub loads and the operating parameters can also represent the flight test pilot vibration. The present neural network connections can significandy increase the value of wind tunnel testing.

AGARD Flight Test Techniques Series. Volume 12. The Principles of Flight Test Assessment of Flight-Safety-Critical Systems in Helicopters (Les Principes de l’Evaluation, dans le Cadre des Essais en Vol, des Systemes Indispensables a la Securite de Vol des Helicopteres)

DTIC Science & Technology

1994-08-01

AGARD-AG-300 Vol. 12 04 ADVISORY GROUP FOR AEROSPACE RESEARCH & DEVELOPMENT 7 RUE ANCELLE, 92200 NEUILLY-SUR-SEINE, FRANCE AUG 0195 AGARDograph 300...AGARD Flight Test Techniques Series Volume 12 on The Principles of Flight Test Assessment of Flight-Safety-Critical Systems in Helicopters (Les...and Availability on Back Cover AGARD-AG-300 Vol. 12 ADVISORY GROUP FOR AEROSPACE RESEARCH & DEVELOPMENT 7 RUE ANCELLE, 92200 NEUILLY-SUR-SEINE, FRANCE

Instrumentation and telemetry systems for free-flight drop model testing

NASA Technical Reports Server (NTRS)

Hyde, Charles R.; Massie, Jeffrey J.

1993-01-01

This paper presents instrumentation and telemetry system techniques used in free-flight research drop model testing at the NASA Langley Research Center. The free-flight drop model test technique is used to conduct flight dynamics research of high performance aircraft using dynamically scaled models. The free-flight drop model flight testing supplements research using computer analysis and wind tunnel testing. The drop models are scaled to approximately 20 percent of the size of the actual aircraft. This paper presents an introduction to the Free-Flight Drop Model Program which is followed by a description of the current instrumentation and telemetry systems used at the NASA Langley Research Center, Plum Tree Test Site. The paper describes three telemetry downlinks used to acquire the data, video, and radar tracking information from the model. Also described are two telemetry uplinks, one used to fly the model employing a ground-based flight control computer and a second to activate commands for visual tracking and parachute recovery of the model. The paper concludes with a discussion of free-flight drop model instrumentation and telemetry system development currently in progress for future drop model projects at the NASA Langley Research Center.

Hyper-X Research Vehicle (HXRV) Experimental Aerodynamics Test Program Overview

NASA Technical Reports Server (NTRS)

Holland, Scott D.; Woods, William C.; Engelund, Walter C.

2000-01-01

This paper provides an overview of the experimental aerodynamics test program to ensure mission success for the autonomous flight of the Hyper-X Research Vehicle (HXRV). The HXRV is a 12-ft long, 2700 lb lifting body technology demonstrator designed to flight demonstrate for the first time a fully airframe integrated scramjet propulsion system. Three flights are currently planned, two at Mach 7 and one at Mach 10, beginning in the fall of 2000. The research vehicles will be boosted to the prescribed scramjet engine test point where they will separate from the booster, stabilize. and initiate engine test. Following 5+ seconds of powered flight and 15 seconds of cowl-open tares, the cowl will close and the vehicle will fly a controlled deceleration trajectory which includes numerous control doublets for in-flight aerodynamic parameter identification. This paper reviews the preflight testing activities, wind tunnel models, test rationale. risk reduction activities, and sample results from wind tunnel tests supporting the flight trajectory of the HXRV from hypersonic engine test point through subsonic flight termination.

Executive Summary of Propulsion on the Orion Abort Flight-Test Vehicles

NASA Technical Reports Server (NTRS)

Jones, Daniel S.; Koelfgen, Syri J.; Barnes, Marvin W.; McCauley, Rachel J.; Wall, Terry M.; Reed, Brian D.; Duncan, C. Miguel

2012-01-01

The NASA Orion Flight Test Office was tasked with conducting a series of flight tests in several launch abort scenarios to certify that the Orion Launch Abort System is capable of delivering astronauts aboard the Orion Crew Module to a safe environment, away from a failed booster. The first of this series was the Orion Pad Abort 1 Flight-Test Vehicle, which was successfully flown on May 6, 2010 at the White Sands Missile Range in New Mexico. This paper provides a brief overview of the three propulsive subsystems used on the Pad Abort 1 Flight-Test Vehicle. An overview of the propulsive systems originally planned for future flight-test vehicles is also provided, which also includes the cold gas Reaction Control System within the Crew Module, and the Peacekeeper first stage rocket motor encased within the Abort Test Booster aeroshell. Although the Constellation program has been cancelled and the operational role of the Orion spacecraft has significantly evolved, lessons learned from Pad Abort 1 and the other flight-test vehicles could certainly contribute to the vehicle architecture of many future human-rated space launch vehicles.

Hyper-X Research Vehicle (HXRV) Experimental Aerodynamics Test Program Overview

NASA Technical Reports Server (NTRS)

Holland, Scott D.; Woods, William C.; Engelund, Walter C.

2000-01-01

This paper provides an overview of the experimental aerodynamics test program to ensure mission success for the autonomous flight of the Hyper-X Research Vehicle (HXRV). The HXRV is a 12-ft long, 2700 lb lifting body technology demonstrator designed to flight demonstrate for the first time a fully airframe integrated scramjet propulsion system. Three flights are currently planned, two at Mach 7 and one at Mach 10, beginning in the fall of 2000. The research vehicles will be boosted to the prescribed scramjet engine test point where they will separate from the booster, stabilize, and initiate engine test. Following 5+ seconds of powered flight and 15 seconds of cow-open tares, the cowl will close and the vehicle will fly a controlled deceleration trajectory which includes numerous control doublets for in-flight aerodynamic parameter identification. This paper reviews the preflight testing activities, wind tunnel models, test rationale, risk reduction activities, and sample results from wind tunnel tests supporting the flight trajectory of the HXRV from hypersonic engine test point through subsonic flight termination.

Surrounded by work platforms, the full-scale Orion AFT crew module (center) is undergoing preparations for the first flight test of Orion's launch abort system.

NASA Image and Video Library

2008-05-20

Surrounded by work platforms, NASA's first full-scale Orion abort flight test (AFT) crew module (center) is undergoing preparations at the NASA Dryden Flight Research Center in California for the first flight test of Orion's launch abort system.

The F-15B Lifting Insulating Foam Trajectory (LIFT) Flight Test

NASA Technical Reports Server (NTRS)

Corda, Stephen; Whiteman, Donald; Tseng, Ting; Machin, Ricardo

2006-01-01

A series of flight tests has been performed to assess the structural survivability of space shuttle external tank debris, known as divots, in a real flight environment. The NASA F-15B research test bed aircraft carried the Aerodynamic Flight Test Fixture configured with a shuttle foam divot ejection system. The divots were released in flight at subsonic and supersonic test conditions matching points on the shuttle ascent trajectory. Very high-speed digital video cameras recorded the divot trajectories. The objectives of the flight test were to determine the structural survivability of the divots in a real flight environment, assess the aerodynamic stability of the divots, and provide divot trajectory data for comparison with debris transport models. A total of 10 flights to Mach 2 were completed, resulting in 36 successful shuttle foam divot ejections. Highspeed video was obtained at 2,000 pictures per second for all of the divot ejections. The divots that were cleanly ejected remained structurally intact. The conical frustum-shaped divots tended to aerodynamically trim in both the subsonic and supersonic free-stream flow.

Planned flight test of a mercury ion auxiliary propulsion system. 1: Objectives, systems descriptions, and mission operations

NASA Technical Reports Server (NTRS)

Power, J. C.

1978-01-01

A planned flight test of an 8 cm diameter, electron-bombardment mercury ion thruster system is described. The primary objective of the test is to flight qualify the 5 mN (1 mlb.) thruster system for auxiliary propulsion applications. A seven year north-south stationkeeping mission was selected as the basis for the flight test operating profile. The flight test, which will employ two thruster systems, will also generate thruster system space performance data, measure thruster-spacecraft interactions, and demonstrate thruster operation in a number of operating modes. The flight test is designated as SAMSO-601 and will be flown aboard the shuttle-launched Air Force space test program P80-1 satellite in 1981. The spacecraft will be 3- axis stabilized in its final 740 km circular orbit, which will have an inclination of approximately greater than 73 degrees. The spacecraft design lifetime is three years.

Supersonic Retropropulsion Flight Test Concepts

NASA Technical Reports Server (NTRS)

Post, Ethan A.; Dupzyk, Ian C.; Korzun, Ashley M.; Dyakonov, Artem A.; Tanimoto, Rebekah L.; Edquist, Karl T.

2011-01-01

NASA's Exploration Technology Development and Demonstration Program has proposed plans for a series of three sub-scale flight tests at Earth for supersonic retropropulsion, a candidate decelerator technology for future, high-mass Mars missions. The first flight test in this series is intended to be a proof-of-concept test, demonstrating successful initiation and operation of supersonic retropropulsion at conditions that replicate the relevant physics of the aerodynamic-propulsive interactions expected in flight. Five sub-scale flight test article concepts, each designed for launch on sounding rockets, have been developed in consideration of this proof-of-concept flight test. Commercial, off-the-shelf components are utilized as much as possible in each concept. The design merits of the concepts are compared along with their predicted performance for a baseline trajectory. The results of a packaging study and performance-based trade studies indicate that a sounding rocket is a viable launch platform for this proof-of-concept test of supersonic retropropulsion.

Autonomous Soaring 2005 Flight Data Summary

NASA Technical Reports Server (NTRS)

Allen, Michael J.

2006-01-01

Flight testing of the 14ft span CloudSwift UAV was conducted during the summer of 2005. Test maneuvers included aircraft checkout, Piccolo gain tuning, FTS range tests, and thermal soaring research flights.

Initial Flight Tests of the NASA F-15B Propulsion Flight Test Fixture

NASA Technical Reports Server (NTRS)

Palumbo, Nathan; Moes, Timothy R.; Vachon, M. Jake

2002-01-01

Flights of the F-15B/Propulsion Flight Test Fixture (PFTF) with a Cone Drag Experiment (CDE) attached have been accomplished at NASA Dryden Flight Research Center. Mounted underneath the fuselage of an F-15B airplane, the PFTF provides volume for experiment systems and attachment points for propulsion experiments. A unique feature of the PFTF is the incorporation of a six-degree-of-freedom force balance. The force balance mounts between the PFTF and experiment and measures three forces and moments. The CDE has been attached to the force balance for envelope expansion flights. This experiment spatially and inertially simulates a large propulsion test article. This report briefly describes the F-15B airplane, the PFTF, and the force balance. A detailed description of the CDE is provided. Force-balance ground testing and stiffness modifications are described. Flight profiles and selected flight data from the envelope expansion flights are provided and discussed, including force-balance data, the internal PFTF thermal and vibration environment, a handling qualities assessment, and performance capabilities of the F-15B airplane with the PFTF installed.

Writing executable assertions to test flight software

NASA Technical Reports Server (NTRS)

Mahmood, A.; Andrews, D. M.; Mccluskey, E. J.

1984-01-01

An executable assertion is a logical statement about the variables or a block of code. If there is no error during execution, the assertion statement results in a true value. Executable assertions can be used for dynamic testing of software. They can be employed for validation during the design phase, and exception and error detection during the operation phase. The present investigation is concerned with the problem of writing executable assertions, taking into account the use of assertions for testing flight software. They can be employed for validation during the design phase, and for exception handling and error detection during the operation phase The digital flight control system and the flight control software are discussed. The considered system provides autopilot and flight director modes of operation for automatic and manual control of the aircraft during all phases of flight. Attention is given to techniques for writing and using assertions to test flight software, an experimental setup to test flight software, and language features to support efficient use of assertions.

Flight Test Evaluation of the ATD-1 Interval Management Application

NASA Technical Reports Server (NTRS)

Swieringa, Kurt A.; Wilson, Sara R.; Baxley, Brian T.; Roper, Roy D.; Abbott, Terence S.; Levitt, Ian; Scharl, Julien

2017-01-01

Interval Management (IM) is a concept designed to be used by air traffic controllers and flight crews to more efficiently and precisely manage inter-aircraft spacing. Both government and industry have been working together to develop the IM concept and standards for both ground automation and supporting avionics. NASA contracted with Boeing, Honeywell, and United Airlines to build and flight test an avionics prototype based on NASA's spacing algorithm and conduct a flight test. The flight test investigated four different types of IM operations over the course of nineteen days, and included en route, arrival, and final approach phases of flight. This paper examines the spacing accuracy achieved during the flight test and the rate of speed commands provided to the flight crew. Many of the time-based IM operations met or exceeded the operational design goals set out in the standards for the maintain operations and a subset of the achieve operations. Those operations which did not meet the goals were due to issues that are identified and will be further analyzed.

Optical Air Flow Measurements for Flight Tests and Flight Testing Optical Air Flow Meters

NASA Technical Reports Server (NTRS)

Jentink, Henk W.; Bogue, Rodney K.

2005-01-01

Optical air flow measurements can support the testing of aircraft and can be instrumental to in-flight investigations of the atmosphere or atmospheric phenomena. Furthermore, optical air flow meters potentially contribute as avionics systems to flight safety and as air data systems. The qualification of these instruments for the flight environment is where we encounter the systems in flight testing. An overview is presented of different optical air flow measurement techniques applied in flight and what can be achieved with the techniques for flight test purposes is reviewed. All in-flight optical airflow velocity measurements use light scattering. Light is scattered on both air molecules and aerosols entrained in the air. Basic principles of making optical measurements in flight, some basic optical concepts, electronic concepts, optoelectronic interfaces, and some atmospheric processes associated with natural aerosols are reviewed. Safety aspects in applying the technique are shortly addressed. The different applications of the technique are listed and some typical examples are presented. Recently NASA acquired new data on mountain rotors, mountain induced turbulence, with the ACLAIM system. Rotor position was identified using the lidar system and the potentially hazardous air flow profile was monitored by the ACLAIM system.

F-15B/Flight Test Fixture 2: A Test Bed for Flight Research

NASA Technical Reports Server (NTRS)

Richwine, David M.

1996-01-01

NASA Dryden Flight Research Center has developed a second-generation flight test fixture for use as a generic test bed for aerodynamic and fluid mechanics research. The Flight Test Fixture 2 (FTF-2) is a low-aspect-ratio vertical fin-like shape that is mounted on the centerline of the F-I5B lower fuselage. The fixture is designed for flight research at Mach numbers to a maximum of 2.0. The FTF-2 is a composite structure with a modular configuration and removable components for functional flexibility. This report documents the flow environment of the fixture, such as surface pressure distributions and boundary-layer profiles, throughout a matrix of conditions within the F-15B/FTF-2 flight envelope. Environmental conditions within the fixture are presented to assist in the design and testing of future avionics and instrumentation. The intent of this document is to serve as a user's guide and assist in the development of future flight experiments that use the FTF-2 as a test bed. Additional information enclosed in the appendices has been included to assist with more detailed analyses, if required.

Low Density Supersonic Decelerator (LDSD) Supersonic Flight Dynamics Test (SFDT) Plume Induced Environment Modelling

NASA Technical Reports Server (NTRS)

Mobley, B. L.; Smith, S. D.; Van Norman, J. W.; Muppidi, S.; Clark, I

2016-01-01

Provide plume induced heating (radiation & convection) predictions in support of the LDSD thermal design (pre-flight SFDT-1) Predict plume induced aerodynamics in support of flight dynamics, to achieve targeted freestream conditions to test supersonic deceleration technologies (post-flight SFDT-1, pre-flight SFDT-2)

Flight Instructor Practical Test Standards for Rotorcraft - Helicopter, Gyroplane

DOT National Transportation Integrated Search

1996-04-01

The Flight Instructor - Rotorcraft (Helicopter and Gyroplane) Practical Test : Standards (PTS) book has been published by the Federal Aviation : Administration (FAA) to establish the standards for flight instructor : certification practical tests for...

Flight Instructor Practical Test Standards for Glider

DOT National Transportation Integrated Search

1997-10-01

This Flight Instructor-Glider Practical Test Standards book has been : published by the Federal Aviation Administration to establish the : standards for the flight instructor certification practical tests for the : glider category. FAA inspectors and...

Ares I-X Flight Test Vehicle Similitude to the Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Huebner, Lawrence D.; Smith, R. Marshall; Campbell, John R.; Taylor, Terry L.

2009-01-01

The Ares I-X Flight Test Vehicle is the first in a series of flight test vehicles that will take the Ares I Crew Launch Vehicle design from development to operational capability. Ares I-X is scheduled for a 2009 flight date, early enough in the Ares I design and development process so that data obtained from the flight can impact the design of Ares I before its Critical Design Review. Decisions on Ares I-X scope, flight test objectives, and FTV fidelity were made prior to the Ares I systems requirements being baselined. This was necessary in order to achieve a development flight test to impact the Ares I design. Differences between the Ares I-X and the Ares I configurations are artifacts of formulating this experimental project at an early stage and the natural maturation of the Ares I design process. This paper describes the similarities and differences between the Ares I-X Flight Test Vehicle and the Ares I Crew Launch Vehicle. Areas of comparison include the outer mold line geometry, aerosciences, trajectory, structural modes, flight control architecture, separation sequence, and relevant element differences. Most of the outer mold line differences present between Ares I and Ares I-X are minor and will not have a significant effect on overall vehicle performance. The most significant impacts are related to the geometric differences in Orion Crew Exploration Vehicle at the forward end of the stack. These physical differences will cause differences in the flow physics in these areas. Even with these differences, the Ares I-X flight test is poised to meet all five primary objectives and six secondary objectives. Knowledge of what the Ares I-X flight test will provide in similitude to Ares I - as well as what the test will not provide - is important in the continued execution of the Ares I-X mission leading to its flight and the continued design and development of Ares I.

Cassini's Test Methodology for Flight Software Verification and Operations

NASA Technical Reports Server (NTRS)

Wang, Eric; Brown, Jay

2007-01-01

The Cassini spacecraft was launched on 15 October 1997 on a Titan IV-B launch vehicle. The spacecraft is comprised of various subsystems, including the Attitude and Articulation Control Subsystem (AACS). The AACS Flight Software (FSW) and its development has been an ongoing effort, from the design, development and finally operations. As planned, major modifications to certain FSW functions were designed, tested, verified and uploaded during the cruise phase of the mission. Each flight software upload involved extensive verification testing. A standardized FSW testing methodology was used to verify the integrity of the flight software. This paper summarizes the flight software testing methodology used for verifying FSW from pre-launch through the prime mission, with an emphasis on flight experience testing during the first 2.5 years of the prime mission (July 2004 through January 2007).

DARPA/USAF/USN J-UCAS X-45A System Demonstration Program: A Review of Flight Test Site Processes and Personnel

NASA Technical Reports Server (NTRS)

Cosentino, Gary B.

2008-01-01

The Joint Unmanned Combat Air Systems (J-UCAS) program is a collaborative effort between the Defense Advanced Research Project Agency (DARPA), the US Air Force (USAF) and the US Navy (USN). Together they have reviewed X-45A flight test site processes and personnel as part of a system demonstration program for the UCAV-ATD Flight Test Program. The goal was to provide a disciplined controlled process for system integration and testing and demonstration flight tests. NASA's Dryden Flight Research Center (DFRC) acted as the project manager during this effort and was tasked with the responsibilities of range and ground safety, the provision of flight test support and infrastructure and the monitoring of technical and engineering tasks. DFRC also contributed their engineering knowledge through their contributions in the areas of autonomous ground taxi control development, structural dynamics testing and analysis and the provision of other flight test support including telemetry data, tracking radars, and communications and control support equipment. The Air Force Flight Test Center acted at the Deputy Project Manager in this effort and was responsible for the provision of system safety support and airfield management and air traffic control services, among other supporting roles. The T-33 served as a J-UCAS surrogate aircraft and demonstrated flight characteristics similar to that of the the X-45A. The surrogate served as a significant risk reduction resource providing mission planning verification, range safety mission assessment and team training, among other contributions.

In-Flight System Identification

NASA Technical Reports Server (NTRS)

Morelli, Eugene A.

1998-01-01

A method is proposed and studied whereby the system identification cycle consisting of experiment design and data analysis can be repeatedly implemented aboard a test aircraft in real time. This adaptive in-flight system identification scheme has many advantages, including increased flight test efficiency, adaptability to dynamic characteristics that are imperfectly known a priori, in-flight improvement of data quality through iterative input design, and immediate feedback of the quality of flight test results. The technique uses equation error in the frequency domain with a recursive Fourier transform for the real time data analysis, and simple design methods employing square wave input forms to design the test inputs in flight. Simulation examples are used to demonstrate that the technique produces increasingly accurate model parameter estimates resulting from sequentially designed and implemented flight test maneuvers. The method has reasonable computational requirements, and could be implemented aboard an aircraft in real time.

A Flight Dynamics Perspective of the Orion Pad Abort One Flight Test

NASA Technical Reports Server (NTRS)

Idicula, Jinu; Williams-Hayes, Peggy S.; Stillwater, Ryan; Yates, Max

2009-01-01

The Orion Crew Exploration Vehicle is America s next generation of human rated spacecraft. The Orion Launch Abort System will take the astronauts away from the exploration vehicle in the event of an aborted launch. The pad abort mode of the Launch Abort System will be flight-tested in 2009 from the White Sands Missile Range in New Mexico. This paper examines some of the efforts currently underway at the NASA Dryden Flight Research Center by the Controls & Dynamics group in preparation for the flight test. The concept of operation for the pad abort flight is presented along with an overview of the guidance, control and navigation systems. Preparations for the flight test, such as hardware testing and development of the real-time displays, are examined. The results from the validation and verification efforts for the aerodynamic and atmospheric models are shown along with Monte Carlo analysis results.

Hyper-X Mach 7 Scramjet Design, Ground Test and Flight Results

NASA Technical Reports Server (NTRS)

Ferlemann, Shelly M.; McClinton, Charles R.; Rock, Ken E.; Voland, Randy T.

2005-01-01

The successful Mach 7 flight test of the Hyper-X (X-43) research vehicle has provided the major, essential demonstration of the capability of the airframe integrated scramjet engine. This flight was a crucial first step toward realizing the potential for airbreathing hypersonic propulsion for application to space launch vehicles. However, it is not sufficient to have just achieved a successful flight. The more useful knowledge gained from the flight is how well the prediction methods matched the actual test results in order to have confidence that these methods can be applied to the design of other scramjet engines and powered vehicles. The propulsion predictions for the Mach 7 flight test were calculated using the computer code, SRGULL, with input from computational fluid dynamics (CFD) and wind tunnel tests. This paper will discuss the evolution of the Mach 7 Hyper-X engine, ground wind tunnel experiments, propulsion prediction methodology, flight results and validation of design methods.

The experimental determination of atmospheric absorption from aircraft acoustic flight tests

NASA Technical Reports Server (NTRS)

Miller, R. L.; Oncley, P. B.

1971-01-01

A method for determining atmospheric absorption coefficients from acoustic flight test data is presented. Measurements from five series of acoustic flight tests were included in the study. The number of individual flights totaled 24: six Boeing 707 flights performed in May 1969 in connection with the turbofan nacelle modification program, eight flights from Boeing tests conducted during the same period, and 10 flights of the Boeing 747 airplane. The effects of errors in acoustic, meteorological, and aircraft performance and position measurements are discussed. Tabular data of the estimated sample variance of the data for each test are given for source directivity angles from 75 deg to 120 deg and each 1/3-octave frequency band. Graphic comparisons are made of absorption coefficients derived from ARP 866, using atmospheric profile data, with absorption coefficients determined by the experimental method described in the report.

Preparations for flight research to evaluate actuated forebody strakes on the F-18 high-alpha research vehicle

NASA Technical Reports Server (NTRS)

Murri, Daniel G.; Shah, Gautam H.; Dicarlo, Daniel J.

1994-01-01

As part of the NASA High-Angle-of-Attack Technology Program (HATP), flight tests are currently being conducted with a multi-axis thrust vectoring system applied to the NASA F-18 High Alpha Research Vehicle (HARV). A follow-on series of flight tests with the NASA F-18 HARV will be focusing on the application of actuated forebody strake controls. These controls are designed to provide increased levels of yaw control at high angles of attack where conventional aerodynamic controls become ineffective. The series of flight tests are collectively referred to as the Actuated Nose Strakes for Enhanced Rolling (ANSER) Flight Experiment. The development of actuated forebody strake controls for the F-18 HARV is discussed and a summary of the ground tests conducted in support of the flight experiment is provided. A summary of the preparations for the flight tests is also provided.

Evaluating the dynamic response of in-flight thrust calculation techniques during throttle transients

NASA Technical Reports Server (NTRS)

Ray, Ronald J.

1994-01-01

New flight test maneuvers and analysis techniques for evaluating the dynamic response of in-flight thrust models during throttle transients have been developed and validated. The approach is based on the aircraft and engine performance relationship between thrust and drag. Two flight test maneuvers, a throttle step and a throttle frequency sweep, were developed and used in the study. Graphical analysis techniques, including a frequency domain analysis method, were also developed and evaluated. They provide quantitative and qualitative results. Four thrust calculation methods were used to demonstrate and validate the test technique. Flight test applications on two high-performance aircraft confirmed the test methods as valid and accurate. These maneuvers and analysis techniques were easy to implement and use. Flight test results indicate the analysis techniques can identify the combined effects of model error and instrumentation response limitations on the calculated thrust value. The methods developed in this report provide an accurate approach for evaluating, validating, or comparing thrust calculation methods for dynamic flight applications.

Uncertainty of in-flight thrust determination

NASA Technical Reports Server (NTRS)

Abernethy, Robert B.; Adams, Gary R.; Steurer, John W.; Ascough, John C.; Baer-Riedhart, Jennifer L.; Balkcom, George H.; Biesiadny, Thomas

1986-01-01

Methods for estimating the measurement error or uncertainty of in-flight thrust determination in aircraft employing conventional turbofan/turbojet engines are reviewed. While the term 'in-flight thrust determination' is used synonymously with 'in-flight thrust measurement', in-flight thrust is not directly measured but is determined or calculated using mathematical modeling relationships between in-flight thrust and various direct measurements of physical quantities. The in-flight thrust determination process incorporates both ground testing and flight testing. The present text is divided into the following categories: measurement uncertainty methodoogy and in-flight thrust measurent processes.

Flight test results of the Strapdown hexad Inertial Reference Unit (SIRU). Volume 1: Flight test summary

NASA Technical Reports Server (NTRS)

Hruby, R. J.; Bjorkman, W. S.

1977-01-01

Flight test results of the strapdown inertial reference unit (SIRU) navigation system are presented. The fault-tolerant SIRU navigation system features a redundant inertial sensor unit and dual computers. System software provides for detection and isolation of inertial sensor failures and continued operation in the event of failures. Flight test results include assessments of the system's navigational performance and fault tolerance.

Final Environmental Assessment for Low-Level Flight Testing, Evaluation, and Training, Edwards Air Force Base

DTIC Science & Technology

2005-05-01

4. TITLE AND SUBTITLE Final Environmental Assessment for Low-Level Flight Testing, Evaluation, and Training, Edwards Air Force Base 5a. CONTRACT...NAME(S) AND ADDRESS(ES) Air Force Flight Test Center,Environmental Management Directorate,Edwards AFB,CA,93524 8. PERFORMING ORGANIZATION REPORT...DISTRIBUTION/AVAILABILITY STATEMENT Approved for public release; distribution unlimited 13. SUPPLEMENTARY NOTES 14. ABSTRACT The U.S. Air Force Flight Test

Posturography and locomotor tests of dynamic balance after long-duration spaceflight.

PubMed

Cohen, Helen S; Kimball, Kay T; Mulavara, Ajitkumar P; Bloomberg, Jacob J; Paloski, William H

2012-01-01

The currently approved objective clinical measure of standing balance in astronauts after space flight is the Sensory Organization Test battery of computerized dynamic posturography. No tests of walking balance are currently approved for standard clinical testing of astronauts. This study determined the sensitivity and specificity of standing and walking balance tests for astronauts before and after long-duration space flight. Astronauts were tested on an obstacle avoidance test known as the Functional Mobility Test (FMT) and on the Sensory Organization Test using sway-referenced support surface motion with eyes closed (SOT 5) before and six months after (n=15) space flight on the International Space Station. They were tested two to seven days after landing. Scores on SOT tests decreased and scores on FMT increased significantly from pre- to post-flight. In other words, post-flight scores were worse than pre-flight scores. SOT and FMT scores were not significantly related. ROC analyses indicated supra-clinical cut-points for SOT 5 and for FMT. The standard clinical cut-point for SOT 5 had low sensitivity to post-flight astronauts. Higher cut-points increased sensitivity to post-flight astronauts but decreased specificity to pre-flight astronauts. Using an FMT cut-point that was moderately highly sensitive and highly specific plus SOT 5 at the standard clinical cut-point was no more sensitive than SOT 5, alone. FMT plus SOT 5 at higher cut-points was more specific and more sensitive. The total correctly classified was highest for FMT, alone, and for FMT plus SOT 5 at the highest cut-point. These findings indicate that standard clinical comparisons are not useful for identifying problems. Testing both standing and walking balance will be more likely to identify balance deficits.

A preliminary correlation of the orbiter stability and control aerodynamics from the first two Space Shuttle flights /STS-1 & 2/ with preflight predictions

NASA Technical Reports Server (NTRS)

Underwood, J. M.; Cooke, D. R.

1982-01-01

A correlation of the stability and control derivatives from flight (STS-1 & 2) with preflight predictions is presented across the Mach range from 0.9 to 25. Flight data obtained from specially designed flight test maneuvers as well as from conventional bank maneuvers generally indicate good agreement with predicted data. However, the vehicle appears to be lateral-directionally more stable than predicted in the transonic regime. Aerodynamic 'reasonableness tests' are employed to test for validity of flight data. The importance of testing multiple models in multiple wind tunnels at the same test conditions is demonstrated.

Wireless Instrumentation Systems for Flight Testing at NASA AFRC

NASA Technical Reports Server (NTRS)

Hang, Richard

2017-01-01

NASA Armstrong Flight Research Center is revolutionizing its traditional wired instrumentation systems with wireless technologies. This effort faces many technical challenges, such as spectrum compliance, time synchronization, power distribution and airworthiness. This presentation summarizes NASA AFRC's flight test capabilities with current conventional instrumentation methodology and highlights the technical challenges of wireless systems used for flight test research applications.

Ares I-X Flight Test Philosophy

NASA Technical Reports Server (NTRS)

Davis, S. R.; Tuma, M. L.; Heitzman, K.

2007-01-01

In response to the Vision for Space Exploration, the National Aeronautics and Space Administration (NASA) has defined a new space exploration architecture to return humans to the Moon and prepare for human exploration of Mars. One of the first new developments will be the Ares I Crew Launch Vehicle (CLV), which will carry the Orion Crew Exploration Vehicle (CEV), into Low Earth Orbit (LEO) to support International Space Station (ISS) missions and, later, support lunar missions. As part of Ares I development, NASA will perform a series of Ares I flight tests. The tests will provide data that will inform the engineering and design process and verify the flight hardware and software. The data gained from the flight tests will be used to certify the new Ares/Orion vehicle for human space flight. The primary objectives of this first flight test (Ares I-X) are the following: Demonstrate control of a dynamically similar integrated Ares CLV/Orion CEV using Ares CLV ascent control algorithms; Perform an in-flight separation/staging event between an Ares I-similar First Stage and a representative Upper Stage; Demonstrate assembly and recovery of a new Ares CLV-like First Stage element at Kennedy Space Center (KSC); Demonstrate First Stage separation sequencing, and quantify First Stage atmospheric entry dynamics and parachute performance; and Characterize the magnitude of the integrated vehicle roll torque throughout the First Stage (powered) flight. This paper will provide an overview of the Ares I-X flight test process and details of the individual flight tests.

Flight and ground tests of a very low density elastomeric ablative material

NASA Technical Reports Server (NTRS)

Olsen, G. C.; Chapman, A. J., III

1972-01-01

A very low density ablative material, a silicone-phenolic composite, was flight tested on a recoverable spacecraft launched by a Pacemaker vehicle system; and, in addition, it was tested in an arc heated wind tunnel at three conditions which encompassed most of the reentry heating conditions of the flight tests. The material was composed, by weight, of 71 percent phenolic spheres, 22.8 percent silicone resin, 2.2 percent catalyst, and 4 percent silica fibers. The tests were conducted to evaluate the ablator performance in both arc tunnel and flight tests and to determine the predictability of the albator performance by using computed results from an existing one-dimensional numerical analysis. The flight tested ablator experienced only moderate surface recession and retained a smooth surface except for isolated areas where the char was completely removed, probably following reentry and prior to or during recovery. Analytical results show good agreement between arc tunnel and flight test results. The thermophysical properties used in the analysis are tabulated.

SSI-ARC Flight Test 3 Data Review

NASA Technical Reports Server (NTRS)

Gong, Chester; Wu, Minghong G.

2015-01-01

The "Unmanned Aircraft System (UAS) Integration into the National Airspace System (NAS)" Project conducted flight test program, referred to as Flight Test 3, at Armstrong Flight Research Center from June - August 2015. Four flight test days were dedicated to the NASA Ames-developed Detect and Avoid (DAA) System referred to as Autoresolver. The encounter scenarios, which involved NASA's Ikhana UAS and a manned intruder aircraft, were designed to collect data on DAA system performance in real-world conditions and uncertainties with four different surveillance sensor systems. Resulting flight test data and analysis results will be used to evaluate the DAA system performance (e.g., trajectory prediction accuracy, threat detection) and to add fidelity to simulation models used to inform Minimum Operating Performance Standards (MOPS) for integrating UAS into routine NAS operations.

A Concept for the HIFiRE 8 Flight Test

NASA Astrophysics Data System (ADS)

Alesi, H.; Paull, A.; Smart, M.; Bowcutt, K. G.

2015-09-01

HIFiRE 8 is a hypersonic flight test experiment scheduled for launch in late 2018 from the Woomera Test Center in Australia. This project aims to develop a Flight Test Vehicle that will, for the first time, complete 30 seconds of scramjet powered hypersonic flight at a Mach Number of 7.0. The engine used for this flight will be a rectangular to elliptic shape transition scramjet. It will be fuelled with gaseous hydrogen. The flight test engine configuration will be derived using scientific and engineering evaluation in the UQ shock tunnel T4 and other potential ground-based facilities. This paper presents current plans for the HIFiRE 8 trajectory, mission events, airframe and engine designs and also includes descriptions of critical subsystems and associated modelling, simulation and analysis activities.

A Preliminary Flight Investigation of Formation Flight for Drag Reduction on the C-17 Aircraft

NASA Technical Reports Server (NTRS)

Pahle, Joe; Berger, Dave; Venti, Michael W.; Faber, James J.; Duggan, Chris; Cardinal, Kyle

2012-01-01

Many theoretical and experimental studies have shown that aircraft flying in formation could experience significant reductions in fuel use compared to solo flight. To date, formation flight for aerodynamic benefit has not been thoroughly explored in flight for large transport-class vehicles. This paper summarizes flight data gathered during several two ship, C-17 formation flights at a single flight condition of 275 knots, at 25,000 ft MSL. Stabilized test points were flown with the trail aircraft at 1,000 and 3,000 ft aft of the lead aircraft at selected crosstrack and vertical offset locations within the estimated area of influence of the vortex generated by the lead aircraft. Flight data recorded at test points within the vortex from the lead aircraft are compared to data recorded at tare flight test points outside of the influence of the vortex. Since drag was not measured directly, reductions in fuel flow and thrust for level flight are used as a proxy for drag reduction. Estimated thrust and measured fuel flow reductions were documented at several trail test point locations within the area of influence of the leads vortex. The maximum average fuel flow reduction was approximately 7-8%, compared to the tare points flown before and after the test points. Although incomplete, the data suggests that regions with fuel flow and thrust reduction greater than 10% compared to the tare test points exist within the vortex area of influence.

Design and Flight Evaluation of a New Force-Based Flow Angle Probe

NASA Technical Reports Server (NTRS)

Corda, Stephen; Vachon, Michael Jacob

2006-01-01

A novel force-based flow angle probe was designed and flight tested on the NASA F-15B Research Testbed aircraft at NASA Dryden Flight Research Center. The prototype flow angle probe is a small, aerodynamic fin that has no moving parts. Forces on the prototype flow angle probe are measured with strain gages and correlated with the local flow angle. The flow angle probe may provide greater simplicity, greater robustness, and better access to flow measurements in confined areas relative to conventional moving vane-type flow angle probes. Flight test data were obtained at subsonic, transonic, and supersonic Mach numbers to a maximum of Mach 1.70. Flight conditions included takeoff, landing, straight and level flight, flight at higher aircraft angles of attack, and flight at elevated g-loadings. Flight test maneuvers included angle-of-attack and angle-of-sideslip sweeps. The flow angle probe-derived flow angles are compared with those obtained with a conventional moving vane probe. The flight tests validated the feasibility of a force-based flow angle measurement system.

Textbook of Military Medicine. Part 1. Warfare, Weaponry, and the Casualty. Part 5. Conventional Warfare. Ballistic, Blast, and Burn Injuries

DTIC Science & Technology

1991-01-01

United States. Because the vast majority of our patients are not active -duty military personnel, it may seem that our day-to-day ac- tivities are far... activated . A designated time-delay fuse uses an Source: Reference 8 15 Conventional Warfare: Ballistic, Blast, and Burn Injuries explosion and the...be found embedded and unexploded in tissue. The fuse is located at the tip of the warhead, and is activated and will deionate on contact only after

Flight Test of an Intelligent Flight-Control System

NASA Technical Reports Server (NTRS)

Davidson, Ron; Bosworth, John T.; Jacobson, Steven R.; Thomson, Michael Pl; Jorgensen, Charles C.

2003-01-01

The F-15 Advanced Controls Technology for Integrated Vehicles (ACTIVE) airplane (see figure) was the test bed for a flight test of an intelligent flight control system (IFCS). This IFCS utilizes a neural network to determine critical stability and control derivatives for a control law, the real-time gains of which are computed by an algorithm that solves the Riccati equation. These derivatives are also used to identify the parameters of a dynamic model of the airplane. The model is used in a model-following portion of the control law, in order to provide specific vehicle handling characteristics. The flight test of the IFCS marks the initiation of the Intelligent Flight Control System Advanced Concept Program (IFCS ACP), which is a collaboration between NASA and Boeing Phantom Works. The goals of the IFCS ACP are to (1) develop the concept of a flight-control system that uses neural-network technology to identify aircraft characteristics to provide optimal aircraft performance, (2) develop a self-training neural network to update estimates of aircraft properties in flight, and (3) demonstrate the aforementioned concepts on the F-15 ACTIVE airplane in flight. The activities of the initial IFCS ACP were divided into three Phases, each devoted to the attainment of a different objective. The objective of Phase I was to develop a pre-trained neural network to store and recall the wind-tunnel-based stability and control derivatives of the vehicle. The objective of Phase II was to develop a neural network that can learn how to adjust the stability and control derivatives to account for failures or modeling deficiencies. The objective of Phase III was to develop a flight control system that uses the neural network outputs as a basis for controlling the aircraft. The flight test of the IFCS was performed in stages. In the first stage, the Phase I version of the pre-trained neural network was flown in a passive mode. The neural network software was running using flight data inputs with the outputs provided to instrumentation only. The IFCS was not used to control the airplane. In another stage of the flight test, the Phase I pre-trained neural network was integrated into a Phase III version of the flight control system. The Phase I pretrained neural network provided realtime stability and control derivatives to a Phase III controller that was based on a stochastic optimal feedforward and feedback technique (SOFFT). This combined Phase I/III system was operated together with the research flight-control system (RFCS) of the F-15 ACTIVE during the flight test. The RFCS enables the pilot to switch quickly from the experimental- research flight mode back to the safe conventional mode. These initial IFCS ACP flight tests were completed in April 1999. The Phase I/III flight test milestone was to demonstrate, across a range of subsonic and supersonic flight conditions, that the pre-trained neural network could be used to supply real-time aerodynamic stability and control derivatives to the closed-loop optimal SOFFT flight controller. Additional objectives attained in the flight test included (1) flight qualification of a neural-network-based control system; (2) the use of a combined neural-network/closed-loop optimal flight-control system to obtain level-one handling qualities; and (3) demonstration, through variation of control gains, that different handling qualities can be achieved by setting new target parameters. In addition, data for the Phase-II (on-line-learning) neural network were collected, during the use of stacked-frequency- sweep excitation, for post-flight analysis. Initial analysis of these data showed the potential for future flight tests that will incorporate the real-time identification and on-line learning aspects of the IFCS.

Fatigue Tests with Random Flight Simulation Loading

NASA Technical Reports Server (NTRS)

Schijve, J.

1972-01-01

Crack propagation was studied in a full-scale wing structure under different simulated flight conditions. Omission of low-amplitude gust cycles had a small effect on the crack rate. Truncation of the infrequently occurring high-amplitude gust cycles to a lower level had a noticeably accelerating effect on crack growth. The application of fail-safe load (100 percent limit load) effectively stopped subsequent crack growth under resumed flight-simulation loading. In another flight-simulation test series on sheet specimens, the variables studied are the design stress level and the cyclic frequency of the random gust loading. Inflight mean stresses vary from 5.5 to 10.0 kg/sq mm. The effect of the stress level is larger for the 2024 alloy than for the 7075 alloy. Three frequencies were employed: namely, 10 cps, 1 cps, and 0.1 cps. The frequency effect was small. The advantages and limitations of flight-simulation tests are compared with those of alternative test procedures such as constant-amplitude tests, program tests, and random-load tests. Various testing purposes are considered. The variables of flight-simulation tests are listed and their effects are discussed. A proposal is made for performing systematic flight-simulation tests in such a way that the compiled data may be used as a source of reference.

Flight Instructor Practical Test Standards for Airplane - Single-engine, Multiengine

DOT National Transportation Integrated Search

1991-05-01

The Flight Instructor - Airplane Practical Test Standards book has been : published by the Federal Aviation Administration (FAA) to establish the : standards for the flight instructor certification practical tests for the : airplane category and the ...

Skylab rescue space vehicle flight readiness test

NASA Technical Reports Server (NTRS)

Jevitt, S. J.

1973-01-01

A Skylab Rescue Space Vehicle flight readiness test is described which ensures that space vehicle systems are in a state of flight readiness and are compatible with associated ground support equipment. The functions of propellant loading, umbilical ejection, ignition, holddown arm release, liftoff, and service arm and tail service mast retraction are simulated. The test outline is presented along with a list of references, intercommunications information, operations interface control chart, and flight test.

KC-135 Winglet Program Review

NASA Technical Reports Server (NTRS)

1982-01-01

The results of a joint NASA/USAF program to develop flight test winglets on a KC-135 aircraft are reviewed. The winglet development from concept through wind tunnel and flight tests is discussed. Predicted, wind tunnel, and flight test results are compared for the performance, loads and flutter characteristics of the winglets. The flight test winglets had a variable winglet cant and incidence angle capability which enabled a limited evaluation of the effects of these geometry changes.

Simulation to Flight Test for a UAV Controls Testbed

NASA Technical Reports Server (NTRS)

Motter, Mark A.; Logan, Michael J.; French, Michael L.; Guerreiro, Nelson M.

2006-01-01

The NASA Flying Controls Testbed (FLiC) is a relatively small and inexpensive unmanned aerial vehicle developed specifically to test highly experimental flight control approaches. The most recent version of the FLiC is configured with 16 independent aileron segments, supports the implementation of C-coded experimental controllers, and is capable of fully autonomous flight from takeoff roll to landing, including flight test maneuvers. The test vehicle is basically a modified Army target drone, AN/FQM-117B, developed as part of a collaboration between the Aviation Applied Technology Directorate (AATD) at Fort Eustis, Virginia and NASA Langley Research Center. Several vehicles have been constructed and collectively have flown over 600 successful test flights, including a fully autonomous demonstration at the Association of Unmanned Vehicle Systems International (AUVSI) UAV Demo 2005. Simulations based on wind tunnel data are being used to further develop advanced controllers for implementation and flight test.

Orbital Express Advanced Video Guidance Sensor: Ground Testing, Flight Results and Comparisons

NASA Technical Reports Server (NTRS)

Pinson, Robin M.; Howard, Richard T.; Heaton, Andrew F.

2008-01-01

Orbital Express (OE) was a successful mission demonstrating automated rendezvous and docking. The 2007 mission consisted of two spacecraft, the Autonomous Space Transport Robotic Operations (ASTRO) and the Next Generation Serviceable Satellite (NEXTSat) that were designed to work together and test a variety of service operations in orbit. The Advanced Video Guidance Sensor, AVGS, was included as one of the primary proximity navigation sensors on board the ASTRO. The AVGS was one of four sensors that provided relative position and attitude between the two vehicles. Marshall Space Flight Center was responsible for the AVGS software and testing (especially the extensive ground testing), flight operations support, and analyzing the flight data. This paper briefly describes the historical mission, the data taken on-orbit, the ground testing that occurred, and finally comparisons between flight data and ground test data for two different flight regimes.

Executive Summary of Propulsion on the Orion Abort Flight-Test Vehicles

NASA Technical Reports Server (NTRS)

Jones, Daniel S.; Brooks, Syri J.; Barnes, Marvin W.; McCauley, Rachel J.; Wall, Terry M.; Reed, Brian D.; Duncan, C. Miguel

2012-01-01

The National Aeronautics and Space Administration Orion Flight Test Office was tasked with conducting a series of flight tests in several launch abort scenarios to certify that the Orion Launch Abort System is capable of delivering astronauts aboard the Orion Crew Module to a safe environment, away from a failed booster. The first of this series was the Orion Pad Abort 1 Flight-Test Vehicle, which was successfully flown on May 6, 2010 at the White Sands Missile Range in New Mexico. This report provides a brief overview of the three propulsive subsystems used on the Pad Abort 1 Flight-Test Vehicle. An overview of the propulsive systems originally planned for future flight-test vehicles is also provided, which also includes the cold gas Reaction Control System within the Crew Module, and the Peacekeeper first stage rocket motor encased within the Abort Test Booster aeroshell. Although the Constellation program has been cancelled and the operational role of the Orion spacecraft has significantly evolved, lessons learned from Pad Abort 1 and the other flight-test vehicles could certainly contribute to the vehicle architecture of many future human-rated space launch vehicles

Orion Abort Flight Test

NASA Technical Reports Server (NTRS)

Hayes, Peggy Sue

2010-01-01

The purpose of NASA's Constellation project is to create the new generation of spacecraft for human flight to the International Space Station in low-earth orbit, the lunar surface, as well as for use in future deep-space exploration. One portion of the Constellation program was the development of the Orion crew exploration vehicle (CEV) to be used in spaceflight. The Orion spacecraft consists of a crew module, service module, space adapter and launch abort system. The crew module was designed to hold as many as six crew members. The Orion crew exploration vehicle is similar in design to the Apollo space capsules, although larger and more massive. The Flight Test Office is the responsible flight test organization for the launch abort system on the Orion crew exploration vehicle. The Flight Test Office originally proposed six tests that would demonstrate the use of the launch abort system. These flight tests were to be performed at the White Sands Missile Range in New Mexico and were similar in nature to the Apollo Little Joe II tests performed in the 1960s. The first flight test of the launch abort system was a pad abort (PA-1), that took place on 6 May 2010 at the White Sands Missile Range in New Mexico. Primary flight test objectives were to demonstrate the capability of the launch abort system to propel the crew module a safe distance away from a launch vehicle during a pad abort, to demonstrate the stability and control characteristics of the vehicle, and to determine the performance of the motors contained within the launch abort system. The focus of the PA-1 flight test was engineering development and data acquisition, not certification. In this presentation, a high level overview of the PA-1 vehicle is given, along with an overview of the Mobile Operations Facility and information on the White Sands tracking sites for radar & optics. Several lessons learned are presented, including detailed information on the lessons learned in the development of wind placards for flight. PA-1 flight data is shown, as well as a comparison of PA-1 flight data to nonlinear simulation Monte Carlo data.

Maximum Oxygen Uptake During Long-Duration Space Flight: Preliminary Results

NASA Technical Reports Server (NTRS)

Moore, A. D., Jr.; Evetts, S. N.; Feiveson, A.H.; Lee, S. M. C.; McCleary, F. A.; Platts, S. H.; Ploutz-Snyder, L.

2010-01-01

INTRODUCTION: Maximum oxygen uptake (VO2max) is maintained during space flight lasting <15 d, but has not been measured during long-duration missions. This abstract describes pre-flight and in-flight preliminary findings from the International Space Station (ISS) VO2max experiment. METHODS: Seven astronauts (4 M, 3 F: 47 +/- 5 yr, 174 +/- 7 cm, 74.1 +/- 14.7 kg [mean +/- SD]) performed cycle exercise tests to volitional maximum approx.45 d before flight and tests were scheduled every 30 d during flight beginning on flight day (FD) 14. Tests consisted of three 5-min stages designed to elicit 25%, 50%, and 75% of preflight VO2max, followed by 25 W/min increases. VO2 and heart rate (HR) were measured using the ISS Portable Pulmonary Function System (PPFS) (Damec, Odense, DK). Unfortunately the PPFS did not arrive at the ISS in time to support early test sessions for 3 crewmembers. Descriptive statistics are presented for pre-flight vs. late-flight (FD 147 +/- 33 d) comparisons for all subjects (n=7); and pre-flight, early (FD 18 +/- 3) and late-flight (FD 156 +/- 5) data are presented for subjects (n=4) who completed all of these test sessions. RESULTS: When all subjects are considered, average VO2max decreased from pre- to late in-flight (2.98 +/- 0.85 vs. 2.57 +/- 0.50 L/min) while maximum HR late-flight seemed unchanged (178 +/- 9 vs. 175 +/- 8 beats/min). Similarly, for subjects who completed pre-, early, and late flight measurements (n=4), mean VO2max declined from 3.19 +/- 0.75 L/min preflight to 2.43 +/- 0.43 and 2.62 +/- 0.38 L/min early and late-flight, respectively. Maximum HR was 183 +/- 8, 174 +/- 8, and 179 +/- 6 beats/min pre-, early- and late-flight. DISCUSSION: Average VO2max declined during flight and did not appreciably recover as flight duration increased; however much inter-subject variation occurred in these changes.

Orion flight test previewed on This Week @NASA - November 7, 2014

NASA Image and Video Library

2014-11-07

A NASA media briefing on Nov. 6 at Kennedy Space Center highlighted the fully assembled Orion spacecraft and details of its first test flight, scheduled for Dec. 4. The 4 and-a-half hour flight, called Exploration Flight Test-1, will send Orion 3,600 miles from Earth on a two-orbit flight to confirm its critical systems are ready for the challenges of eventually sending astronauts on deep space missions to an asteroid and Mars. Also, Delta IV Heavy wet dress test, Next ISS crew trains, Space agency leaders support ISS, Curiosity confirms orbital data and more!

Flight tests of IFR landing approach systems for helicopters

NASA Technical Reports Server (NTRS)

Bull, J. S.; Hegarty, D. M.; Peach, L. L.; Phillips, J. D.; Anderson, D. J.; Dugan, D. C.; Ross, V. L.

1981-01-01

Joint NASA/FAA helicopter flight tests were conducted to investigate airborne radar approaches (ARA) and microwave landing system (MLS) approaches. Flight-test results were utilized to prove NASA with a data base to be used as a performance measure for advanced guidance and navigation concepts, and to provide FAA with data for establishment of TERPS criteria. The first flight-test investigation consisted of helicopter IFR approaches to offshore oil rigs in the Gulf of Mexico, using weather/mapping radar, operational pilots, and a Bell 212 helicopter. The second flight-test investigation consisted of IFR MLS approaches at Crows Landing (near Ames Research Center), with a Bell UH-1H helicopter, using NASA, FAA, and operational industry pilots. Tests are described and results discussed.

Ares I-X Thermal Model Correlation and Lessons Learned

NASA Technical Reports Server (NTRS)

Amundsen, Ruth M.

2010-01-01

The Ares I-X vehicle launched and flew successfully on October 28, 2009. This paper will describe the correlation of the vehicle thermal model to both ground testing and flight data. A main purpose of the vehicle model and ground testing was to ensure that the avionics within the vehicle were held within their thermal limits prior to launch and during flight. The correlation of the avionics box temperatures will be shown. Also, the lessons learned in the thermal discipline during the modeling, test, correlation to test, and flight of the Ares I-X flight test vehicle will be described. Lessons learned will cover thermal modeling, as well as management of the thermal discipline, thermal team, and thermal-related actions in design, testing, and flight.

In-flight rain damage tests of the shuttle thermal protection system

NASA Technical Reports Server (NTRS)

Meyer, Robert R., Jr.; Barneburg, Jack

1988-01-01

NASA conducted in-flight rain damage tests of the Shuttle thermal protection system (TPS). Most of the tests were conducted on an F-104 aircraft at the Dryden Flight Research Facility of NASA's Ames Research Center, although some tests were conducted by NOAA on a WP-3D aircraft off the eastern coast of southern Florida. The TPS components tested included LI900 and LI2200 tiles, advanced flexible reusable surface insulation, reinforced carbon-carbon, and an advanced tufi tile. The objective of the test was to define the damage threshold of various thermal protection materials during flight through rain. The test hardware, test technique, and results from both F-104 and WP-3D aircraft are described. Results have shown that damage can occur to the Shuttle TPS during flight in rain.

Hypersonic Flight Test Windows for Technology Development Testing

DTIC Science & Technology

2013-11-01

used. 2.1 Propulsion and Controls Test Window The technologies dealing with scramjet propulsion (inlets, fuel injection, etc.) and hypersonic ...AFRL-RQ-WP-TM-2013-0260 HYPERSONIC FLIGHT TEST WINDOWS FOR TECHNOLOGY DEVELOPMENT TESTING Barry M. Hellman Vehicle Technology Branch...DATES COVERED (From - To) November 2013 Final 01 November 2013 – 25 November 2013 4. TITLE AND SUBTITLE HYPERSONIC FLIGHT TEST WINDOWS FOR

ER-2 High Altitude Solar Cell Calibration Flights

NASA Technical Reports Server (NTRS)

Myers, Matthew G.; Piszczor, Michael F.

2015-01-01

The first flights of the ER-2 solar cell calibration demonstration were conducted during September-October of 2014. Three flights were performed that not only tested out the equipment and operational procedures, but also demonstrated the capability of this unique facility by conducting the first short-circuit measurements on a variety of test solar cells. Very preliminary results of these first flights were presented at the 2014 Space Photovoltaic Research and Technology (SPRAT) Conference in Cleveland, OH shortly following these first flights. At the 2015 Space Power Workshop, a more detailed description of these first ER-2 flights will be presented, along with the final flight data from some of the test cells that were flown and has now been reduced and corrected for ER-2 atmospheric flight conditions. Plans for ER-2 flights during the summer of 2015 will also be discussed.

UAS Integration in the NAS Project: Flight Test 3 Data Analysis of JADEM-Autoresolver Detect and Avoid System

NASA Technical Reports Server (NTRS)

Gong, Chester; Wu, Minghong G.; Santiago, Confesor

2016-01-01

The Unmanned Aircraft Systems Integration in the National Airspace System project, or UAS Integration in the NAS, aims to reduce technical barriers related to safety and operational challenges associated with enabling routine UAS access to the NAS. The UAS Integration in the NAS Project conducted a flight test activity, referred to as Flight Test 3 (FT3), involving several Detect-and-Avoid (DAA) research prototype systems between June 15, 2015 and August 12, 2015 at the Armstrong Flight Research Center (AFRC). This report documents the flight testing and analysis results for the NASA Ames-developed JADEM-Autoresolver DAA system, referred to as 'Autoresolver' herein. Four flight test days (June 17, 18, 22, and July 22) were dedicated to Autoresolver testing. The objectives of this test were as follows: 1. Validate CPA prediction accuracy and detect-and-avoid (DAA, formerly known as self-separation) alerting logic in realistic flight conditions. 2. Validate DAA trajectory model including maneuvers. 3. Evaluate TCAS/DAA interoperability. 4. Inform final Minimum Operating Performance Standards (MOPS). Flight test scenarios were designed to collect data to directly address the objectives 1-3. Objective 4, inform final MOPS, was a general objective applicable to the UAS in the NAS project as a whole, of which flight test is a subset. This report presents analysis results completed in support of the UAS in the NAS project FT3 data review conducted on October 20, 2015. Due to time constraints and, to a lesser extent, TCAS data collection issues, objective 3 was not evaluated in this analysis.

COBALT Flight Demonstrations Fuse Technologies

NASA Image and Video Library

2017-06-07

This 5-minute, 50-second video shows how the CoOperative Blending of Autonomous Landing Technologies (COBALT) system pairs new landing sensor technologies that promise to yield the highest precision navigation solution ever tested for NASA space landing applications. The technologies included a navigation doppler lidar (NDL), which provides ultra-precise velocity and line-of-sight range measurements, and the Lander Vision System (LVS), which provides terrain-relative navigation. Through flight campaigns conducted in March and April 2017 aboard Masten Space Systems' Xodiac, a rocket-powered vertical takeoff, vertical landing (VTVL) platform, the COBALT system was flight tested to collect sensor performance data for NDL and LVS and to check the integration and communication between COBALT and the rocket. The flight tests provided excellent performance data for both sensors, as well as valuable information on the integrated performance with the rocket that will be used for subsequent COBALT modifications prior to follow-on flight tests. Based at NASA’s Armstrong Flight Research Center in Edwards, CA, the Flight Opportunities program funds technology development flight tests on commercial suborbital space providers of which Masten is a vendor. The program has previously tested the LVS on the Masten rocket and validated the technology for the Mars 2020 rover.

Modal parameter estimation and monitoring for on-line flight flutter analysis

NASA Astrophysics Data System (ADS)

Verboven, P.; Cauberghe, B.; Guillaume, P.; Vanlanduit, S.; Parloo, E.

2004-05-01

The clearance of the flight envelope of a new airplane by means of flight flutter testing is time consuming and expensive. Most common approach is to track the modal damping ratios during a number of flight conditions, and hence the accuracy of the damping estimates plays a crucial role. However, aircraft manufacturers desire to decrease the flight flutter testing time for practical, safety and economical reasons by evolving from discrete flight test points to a more continuous flight test pattern. Therefore, this paper presents an approach that provides modal parameter estimation and monitoring for an aircraft with a slowly time-varying structural behaviour that will be observed during a faster and more continuous exploration of the flight envelope. The proposed identification approach estimates the modal parameters directly from input/output Fourier data. This avoids the need for an averaging-based pre-processing of the data, which becomes inapplicable in the case that only short data records are measured. Instead of using a Hanning window to reduce effects of leakage, these transient effects are modelled simultaneously with the dynamical behaviour of the airplane. The method is validated for the monitoring of the system poles during flight flutter testing.

Free Enterprise: Contributions of the Approach and Landing Test (ALT) Program to the Development of the Space Shuttle Orbiter

NASA Technical Reports Server (NTRS)

Merlin, Peter W.

2006-01-01

The space shuttle orbiter was the first spacecraft designed with the aerodynamic characteristics and in-atmosphere handling qualities of a conventional airplane. In order to evaluate the orbiter's flight control systems and subsonic handling characteristics, a series of flight tests were undertaken at NASA Dryden Flight Research Center in 1977. A modified Boeing 747 Shuttle Carrier Aircraft carried the Enterprise, a prototype orbiter, during eight captive tests to determine how well the two vehicles flew together and to test some of the orbiter s systems. The free-flight phase of the ALT program allowed shuttle pilots to explore the orbiter's low-speed flight and landing characteristics. The Enterprise provided realistic, in-flight simulations of how subsequent space shuttles would be flown at the end of an orbital mission. The fifth free flight, with the Enterprise landing on a concrete runway for the first time, revealed a problem with the space shuttle flight control system that made it susceptible to pilot-induced oscillation, a potentially dangerous control problem. Further research using various aircraft, particularly NASA Dryden's F-8 Digital-Fly-By-Wire testbed, led to correction of the problem before the first Orbital Test Flight.

Development and Flight Test of an Emergency Flight Control System Using Only Engine Thrust on an MD-11 Transport Airplane

NASA Technical Reports Server (NTRS)

Burcham, Frank W., Jr.; Burken, John J.; Maine, Trindel A.; Fullerton, C. Gordon

1997-01-01

An emergency flight control system that uses only engine thrust, called the propulsion-controlled aircraft (PCA) system, was developed and flight tested on an MD-11 airplane. The PCA system is a thrust-only control system, which augments pilot flightpath and track commands with aircraft feedback parameters to control engine thrust. The PCA system was implemented on the MD-11 airplane using only software modifications to existing computers. Results of a 25-hr flight test show that the PCA system can be used to fly to an airport and safely land a transport airplane with an inoperative flight control system. In up-and-away operation, the PCA system served as an acceptable autopilot capable of extended flight over a range of speeds, altitudes, and configurations. PCA approaches, go-arounds, and three landings without the use of any normal flight controls were demonstrated, including ILS-coupled hands-off landings. PCA operation was used to recover from an upset condition. The PCA system was also tested at altitude with all three hydraulic systems turned off. This paper reviews the principles of throttles-only flight control, a history of accidents or incidents in which some or all flight controls were lost, the MD-11 airplane and its systems, PCA system development, operation, flight testing, and pilot comments.

Phoenix Missile Hypersonic Testbed (PMHT): Project Concept Overview

NASA Technical Reports Server (NTRS)

Jones, Thomas P.

2007-01-01

An over view of research into a low cost hypersonic research flight test capability to increase the amount of hypersonic flight data to help bridge the large developmental gap between ground testing/analysis and major flight demonstrator Xplanes is provided. The major objectives included: develop an air launched missile booster research testbed; accurately deliver research payloads through programmable guidance to hypersonic test conditions; low cost; a high flight rate minimum of two flights per year and utilize surplus air launched missiles and NASA aircraft.

Orion Pad Abort 1 Flight Test - Ground and Flight Operations

NASA Technical Reports Server (NTRS)

Hackenbergy, Davis L.; Hicks, Wayne

2011-01-01

This paper discusses the ground and flight operations aspects to the Pad Abort 1 launch. The paper details the processes used to plan all operations. The paper then discussions the difficulties of integration and testing, while detailing some of the lessons learned throughout the entire launch campaign. Flight operational aspects of the launc are covered in order to provide the listener with the full suite of operational issues encountered in preparation for the first flight test of the Orion Launch Abort System.

NASA Tests 2nd RS-25 Flight Engine for Space Launch System

NASA Image and Video Library

2017-10-19

Engineers at NASA’s Stennis Space Center in Mississippi on Oct. 19 completed a hot-fire test of RS-25 rocket engine E2063, a flight engine for NASA’s new Space Launch System (SLS) rocket. Engine E2063 is scheduled to help power SLS on its Exploration Mission-2 (EM-2), the first flight of the new rocket to carry humans. Flight engine E2059 was tested on March 10, 2016, also for use on the EM-2 flight.

NASA Tests 2nd RS-25 Flight Engine For Space Launch System

NASA Image and Video Library

2017-10-19

Engineers at NASA’s Stennis Space Center in Mississippi on Oct. 19 completed a hot-fire test of RS-25 rocket engine E2063, a flight engine for NASA’s new Space Launch System (SLS) rocket. Engine E2063 is scheduled to help power SLS on its Exploration Mission-2 (EM-2), the first flight of the new rocket to carry humans. Flight engine E2059 was tested on March 10, 2016, also for use on the EM-2 flight.

Video File - NASA Tests 2nd RS-25 Flight Engine for Space Launch System

NASA Image and Video Library

2017-10-19

Engineers at NASA’s Stennis Space Center in Mississippi on Oct. 19 completed a hot-fire test of RS-25 rocket engine E2063, a flight engine for NASA’s new Space Launch System (SLS) rocket. Engine E2063 is scheduled to help power SLS on its Exploration Mission-2 (EM-2), the first flight of the new rocket to carry humans. Flight engine E2059 was tested on March 10, 2016, also for use on the EM-2 flight.

Requirements for Flight Testing Automated Terminal Service

DOT National Transportation Integrated Search

1977-05-01

This report describes requirements for the flight tests of the baseline Automated Terminals Service (ATS) system. The overall objective of the flight test program is to evaluate the feasibility of the ATS concept. Within this objective there are two ...

Flight Instructor Practical Test Standards for Lighter-Than-Air: Balloon, Airship

DOT National Transportation Integrated Search

1995-03-01

The Flight Instructor - Lighter-Than-Air Practical Test Standards (PTS) : book has been published by the Federal Aviation Administration (FAA) to : establish the standards for flight instructor certification practical tests for : the lighter-than-air...

Mission Control Center (MCC) system specification for the shuttle Orbital Flight Test (OFT) timeframe

NASA Technical Reports Server (NTRS)

1978-01-01

The Mission Control Center Shuttle (MCC) Shuttle Orbital Flight Test (OFT) Data System (OFTDS) provides facilities for flight control and data systems personnel to monitor and control the Shuttle flights from launch (tower clear) to rollout (wheels stopped on runway). It also supports the preparation for flight (flight planning, flight controller and crew training, and integrated vehicle and network testing activities). The MCC Shuttle OFTDS is described in detail. Three major support systems of the OFTDS and the data types and sources of data entering or exiting the MCC were illustrated. These systems are the communication interface system, the data computation complex, and the display and control system.

Pre-Flight Testing of Spaceborne GPS Receivers using a GPS Constellation Simulator

NASA Technical Reports Server (NTRS)

Kizhner, Semion; Davis, Edward; Alonso, R.

1999-01-01

The NASA Goddard Space Flight Center (GSFC) Global Positioning System (GPS) applications test facility has been established within the GSFC Guidance Navigation and Control Center. The GPS test facility is currently housing the Global Simulation Systems Inc. (GSSI) STR2760 GPS satellite 40-channel attitude simulator and a STR4760 12-channel navigation simulator. The facility also contains a few other resources such as an atomic time standard test bed, a rooftop antenna platform and a radome. It provides a new capability for high dynamics GPS simulations of space flight that is unique within the aerospace community. The GPS facility provides a critical element for the development and testing of GPS based technologies i.e. position, attitude and precise time determination used on-board a spacecraft, suborbital rocket balloon. The GPS simulation system is configured in a transportable rack and is available for GPS component development as well as for component, spacecraft subsystem and system level testing at spacecraft integration and tests sites. The GPS facility has been operational since early 1996 and has utilized by space flight projects carrying GPS experiments, such as the OrbView-2 and the Argentine SAC-A spacecrafts. The SAC-A pre-flight test data obtained by using the STR2760 simulator and the comparison with preliminary analysis of the GPS data from SAC-A telemetry are summarized. This paper describes pre-flight tests and simulations used to support a unique spaceborne GPS experiment. The GPS experiment mission objectives and the test program are described, as well as the GPS test facility configuration needed to verify experiment feasibility. Some operational and critical issues inherent in GPS receiver pre-flight tests and simulations using this GPS simulation, and test methodology are described. Simulation and flight data are presented. A complete program of pre-flight testing of spaceborne GPS receivers using a GPS constellation simulator is detailed.

Pre-Flight Testing of Spaceborne GPS Receivers Using a GPS Constellation Simulator

NASA Technical Reports Server (NTRS)

Kizhner, Semion; Davis, Edward; Alonso, Roberto

1999-01-01

The NASA Goddard Space Flight Center (GSFC) Global Positioning System (GPS) applications test facility has been established within the GSFC Guidance Navigation and Control Center. The GPS test facility is currently housing the Global Simulation Systems Inc. (GSSI) STR2760 GPS satellite 40-channel attitude simulator and a STR4760 12-channel navigation simulator. The facility also contains a few other resources such as an atomic time standard test bed, a rooftop antenna platform and a radome. It provides a new capability for high dynamics GPS simulations of space flight that is unique within the aerospace community. The GPS facility provides a critical element for the development and testing of GPS based technologies i.e. position, attitude and precise time determination used on-board a spacecraft, suborbital rocket or balloon. The GPS simulator system is configured in a transportable rack and is available for GPS component development as well as for component, spacecraft subsystem and system level testing at spacecraft integration and test sites. The GPS facility has been operational since early 1996 and has been utilized by space flight projects carrying GPS experiments, such as the OrbView-2 and the Argentine SAC-A spacecrafts. The SAC-A pre-flight test data obtained by using the STR2760 simulator and the comparison with preliminary analysis of the GPS data from SAC-A telemetry are summarized. This paper describes pre-flight tests and simulations used to support a unique spaceborne GPS experiment. The GPS experiment mission objectives and the test program are described, as well as the GPS test facility configuration needed to verify experiment feasibility. Some operational and critical issues inherent in GPS receiver pre-flight tests and simulations using this GPS simulator, and test methodology are described. Simulation and flight data are presented. A complete program of pre-flight testing of spaceborne GPS receivers using a GPS constellation simulator is detailed.

Stability and control flight test results of the space transportation system's orbiter

NASA Technical Reports Server (NTRS)

Culp, M. A.; Cooke, D. R.

1982-01-01

Flight testing of the Space Shuttle Orbiter is in progress and current results of the post-flight aerodynamic analyses are discussed. The purpose of these analyses is to reduce the pre-flight aerodynamic uncertainties, thereby leading to operational certification of the Orbiter flight envelope relative to the integrated airframe and flight control system. Primary data reduction is accomplished with a well documented maximum likelihood system identification techniques.

Highly Maneuverable Aircraft Technology (HiMAT) flight-flutter test program

NASA Technical Reports Server (NTRS)

Kehoe, M. W.

1984-01-01

The highly maneuverable aircraft technology (HiMAT) vehicle was evaluated in a joint NASA and Air Force flight test program. The HiMAT vehicle is a remotely piloted research vehicle. Its design incorporates the use of advanced composite materials in the wings, and canards for aeroelastic tailoring. A flight-flutter test program was conducted to clear a sufficient flight envelope to allow for performance, stability and control, and loads testing. Testing was accomplished with and without flight control-surface dampers. Flutter clearance of the vehicle indicated satisfactory damping and damping trends for the structural modes of the HiMAT vehicle. The data presented include frequency and damping plotted as a function of Mach number.

14 CFR 61.64 - Use of a flight simulator and flight training device.

Code of Federal Regulations, 2011 CFR

2011-01-01

... test. (e) Use of a flight simulator for the powered-lift rating. If an applicant uses a flight simulator for training or the practical test for the powered-lift category or type rating— (1) The flight simulator— (i) Must represent the category and type of powered-lift rating (if a type rating is applicable...

14 CFR 61.64 - Use of a flight simulator and flight training device.

Code of Federal Regulations, 2010 CFR

2010-01-01

... test. (e) Use of a flight simulator for the powered-lift rating. If an applicant uses a flight simulator for training or the practical test for the powered-lift category or type rating— (1) The flight simulator— (i) Must represent the category and type of powered-lift rating (if a type rating is applicable...

Apollo experience report: Development flight instrumentation. [telemetry equipment for space flight test program

NASA Technical Reports Server (NTRS)

Farmer, N. B.

1974-01-01

Development flight instrumentation was delivered for 25 Apollo vehicles as Government-furnished equipment. The problems and philosophies of an activity that was concerned with supplying telemetry equipment to a space-flight test program are discussed. Equipment delivery dates, system-design details, and flight-performance information for each mission also are included.

Space Shuttle stability and control flight test techniques

NASA Technical Reports Server (NTRS)

Cooke, D. R.

1980-01-01

A unique approach for obtaining vehicle aerodynamic characteristics during entry has been developed for the Space Shuttle. This is due to the high cost of Shuttle testing, the need to open constraints for operational flights, and the fact that all flight regimes are flown starting with the first flight. Because of uncertainties associated with predicted aerodynamic coefficients, nine flight conditions have been identified at which control problems could occur. A detailed test plan has been developed for testing at these conditions and is presented. Due to limited testing, precise computer initiated maneuvers are implemented. These maneuvers are designed to optimize the vehicle motion for determining aerodynamic coefficients. Special sensors and atmospheric measurements are required to provide stability and control flight data during an entire entry. The techniques employed in data reduction are proven programs developed and used at NASA/DFRC.

Shuttle avionics software development trials: Tribulations and successes, the backup flight system

NASA Technical Reports Server (NTRS)

Chevers, E. S.

1985-01-01

The development and verification of the Backup Flight System software (BFS) is discussed. The approach taken for the BFS was to develop a very simple and straightforward software program and then test it in every conceivable manner. The result was a program that contained approximately 12,000 full words including ground checkout and the built in test program for the computer. To perform verification, a series of tests was defined using the actual flight type hardware and simulated flight conditions. Then simulated flights were flown and detailed performance analysis was conducted. The intent of most BFS tests was to demonstrate that a stable flightpath could be obtained after engagement from an anomalous initial condition. The extention of the BFS to meet the requirements of the orbital flight test phase is also described.

Flight Tests of a Ministick Controller in an F/A-18 Airplane

NASA Technical Reports Server (NTRS)

Stoliker, Patrick C.; Carter, John

2003-01-01

In March of 1999, five pilots performed flight tests to evaluate the handling qualities of an F/A-18 research airplane equipped with a small-displacement center stick (ministick) controller that had been developed for the JAS 39 Gripen airplane (a fighter/attack/ reconnaissance airplane used by the Swedish air force). For these tests, the ministick was installed in the aft cockpit (see figure) and production support flight control computers (PSFCCs) were used as interfaces between the controller hardware and the standard F/A-18 flight-control laws. The primary objective of the flight tests was to assess any changes in handling qualities of the F/A-18 airplane attributable to the mechanical characteristics of the ministick. The secondary objective was to demonstrate the capability of the PSFCCs to support flight-test experiments.

Mission definition study for Stanford relativity satellite. Volume 2: Engineering flight test program

NASA Technical Reports Server (NTRS)

1971-01-01

The need is examined for orbital flight tests of gyroscope, dewar, and other components, in order to reduce the technical and financial risk in performing the relativity experiment. A program is described that would generate engineering data to permit prediction of final performance. Two flight tests are recommended. The first flight would test a dewar smaller than that required for the final flight, but of size and form sufficient to allow extrapolation to the final design. The second flight would use the same dewar design to carry a set of three gyroscopes, which would be evaluated for spinup and drift characteristics for a period of a month or more. A proportional gas control system using boiloff helium gas from the dewar, and having the ability to prevent sloshing of liquid helium, would also be tested.

Enterprise - Free Flight after Separation from 747

NASA Technical Reports Server (NTRS)

1977-01-01

The Space Shuttle prototype Enterprise flies free of NASA's 747 Shuttle Carrier Aircraft (SCA) during one of five free flights carried out at the Dryden Flight Research Facility, Edwards, California in 1977 as part of the Shuttle program's Approach and Landing Tests (ALT). The tests were conducted to verify orbiter aerodynamics and handling characteristics in preparation for orbital flights with the Space Shuttle Columbia. A tail cone over the main engine area of Enterprise smoothed out turbulent airflow during flight. It was removed on the two last free flights to accurately check approach and landing characteristics. The Space Shuttle Approach and Landings Tests (ALT) program allowed pilots and engineers to learn how the Space Shuttle and the modified Boeing 747 Shuttle Carrier Aircraft (SCA) handled during low-speed flight and landing. The Enterprise, a prototype of the Space Shuttles, and the SCA were flown to conduct the approach and landing tests at the NASA Dryden Flight Research Center, Edwards, California, from February to October 1977. The first flight of the program consisted of the Space Shuttle Enterprise attached to the Shuttle Carrier Aircraft. These flights were to determine how well the two vehicles flew together. Five 'captive-inactive' flights were flown during this first phase in which there was no crew in the Enterprise. The next series of captive flights was flown with a flight crew of two on board the prototype Space Shuttle. Only three such flights proved necessary. This led to the free-flight test series. The free-flight phase of the ALT program allowed pilots and engineers to learn how the Space Shuttle handled in low-speed flight and landing attitudes. For these landings, the Enterprise was flown by a crew of two after it was released from the top of the SCA. The vehicle was released at altitudes ranging from 19,000 to 26,000 feet. The Enterprise had no propulsion system, but its first four glides to the Rogers Dry Lake runway provided realistic, in-flight simulations of how subsequent Space Shuttles would be flown at the end of an orbital mission. The fifth approach and landing test, with the Enterprise landing on the Edwards Air Force Base concrete runway, revealed a problem with the Space Shuttle flight control system that made it susceptible to Pilot-Induced Oscillation (PIO), a potentially dangerous control problem during a landing. Further research using other NASA aircraft, especially the F-8 Digital-Fly-By-Wire aircraft, led to correction of the PIO problem before the first orbital flight. The Enterprise's last free-flight was October 26, 1977, after which it was ferried to other NASA centers for ground-based flight simulations that tested Space Shuttle systems and structure.

Enterprise - Free Flight after Separation from 747

NASA Technical Reports Server (NTRS)

1977-01-01

The Space Shuttle prototype Enterprise flies free after being released from NASA's 747 Shuttle Carrier Aircraft (SCA) during one of five free flights carried out at the Dryden Flight Research Center, Edwards, California in 1977, as part of the Shuttle program's Approach and Landing Tests (ALT). The tests were conducted to verify orbiter aerodynamics and handling characteristics in preparation for orbital flights with the Space Shuttle Columbia. A tail cone over the main engine area of Enterprise smoothed out turbulent airflow during flight. It was removed on the two last free flights to accurately check approach and landing characteristics. The Space Shuttle Approach and Landings Tests (ALT) program allowed pilots and engineers to learn how the Space Shuttle and the modified Boeing 747 Shuttle Carrier Aircraft (SCA) handled during low-speed flight and landing. The Enterprise, a prototype of the Space Shuttles, and the SCA were flown to conduct the approach and landing tests at the NASA Dryden Flight Research Center, Edwards, California, from February to October 1977. The first flight of the program consisted of the Space Shuttle Enterprise attached to the Shuttle Carrier Aircraft. These flights were to determine how well the two vehicles flew together. Five 'captive-inactive' flights were flown during this first phase in which there was no crew in the Enterprise. The next series of captive flights was flown with a flight crew of two on board the prototype Space Shuttle. Only three such flights proved necessary. This led to the free-flight test series. The free-flight phase of the ALT program allowed pilots and engineers to learn how the Space Shuttle handled in low-speed flight and landing attitudes. For these landings, the Enterprise was flown by a crew of two after it was released from the top of the SCA. The vehicle was released at altitudes ranging from 19,000 to 26,000 feet. The Enterprise had no propulsion system, but its first four glides to the Rogers Dry Lake runway provided realistic, in-flight simulations of how subsequent Space Shuttles would be flown at the end of an orbital mission. The fifth approach and landing test, with the Enterprise landing on the Edwards Air Force Base concrete runway, revealed a problem with the Space Shuttle flight control system that made it susceptible to Pilot-Induced Oscillation (PIO), a potentially dangerous control problem during a landing. Further research using other NASA aircraft, especially the F-8 Digital-Fly-By-Wire aircraft, led to correction of the PIO problem before the first orbital flight. The Enterprise's last free-flight was October 26, 1977, after which it was ferried to other NASA centers for ground-based flight simulations that tested Space Shuttle systems and structure.

X-48B Flight Test Progress Overview

NASA Technical Reports Server (NTRS)

Risch, Timoth K.; Cosentino, Gary B.; Regan, Christopher D.; Kisska, Michael; Princen, Norman

2009-01-01

The results of a series of 39 flight tests of the X-48B Low Speed Vehicle (LSV) performed at the NASA Dryden Flight Research Center from July 2007 through December 2008 are reported here. The goal of these tests is to evaluate the aerodynamic and controls and dynamics performance of the subscale LSV aircraft, eventually leading to the development of a control system for a full-scale vehicle. The X-48B LSV is an 8.5%-scale aircraft of a potential, full-scale Blended Wing Body (BWB) type aircraft and is flown remotely from a ground control station using a computerized flight control system located onboard the aircraft. The flight tests were the first two phases of a planned three-phase research program aimed at ascertaining the flying characteristics of this type of aircraft. The two test phases reported here are: 1) envelope expansion, during which the basic flying characteristics of the airplane were examined, and 2) parameter identification, stalls, and engine-out testing, during which further information on the aircraft performance was obtained and the airplane was tested to the limits of controlled flight. The third phase, departure limiter assaults, has yet to be performed. Flight tests in two different wing leading edge configurations (slats extended and slats retracted) as well as three weight and three center of gravity positions were conducted during each phase. Data gathered in the test program included measured airplane performance parameters such as speed, acceleration, and control surface deflections along with qualitative flying evaluations obtained from pilot and crew observations. Flight tests performed to-date indicate the aircraft exhibits good handling qualities and performance, consistent with pre-flight simulations.

KSC-2014-4177

NASA Image and Video Library

2014-10-01

CAPE CANAVERAL, Fla. – The United Launch Alliance Delta IV Heavy rocket for Exploration Flight Test-1 is being lifted to the vertical position at the pad at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida. The Delta IV Heavy is being readied to launch Orion on its first flight test. During its first flight test, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Daniel Casper

EFT-1 Delta IV Heavy lift to vertical

NASA Image and Video Library

2014-10-01

This close-up view shows the United Launch Alliance Delta IV Heavy rocket for Exploration Flight Test-1 being raised into the vertical position at the pad at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida. The Delta IV Heavy is being readied to launch Orion on its first flight test. During its first flight test, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014.

EFT-1 Delta IV Heavy lift to vertical

NASA Image and Video Library

2014-10-01

The United Launch Alliance Delta IV Heavy rocket for Exploration Flight Test-1 is lifted to the vertical position in the mobile service tower on the pad at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida. The Delta IV Heavy is being readied to launch Orion on its first flight test. During its first flight test, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014.

KSC-2014-4176

NASA Image and Video Library

2014-10-01

CAPE CANAVERAL, Fla. – The United Launch Alliance Delta IV Heavy rocket for Exploration Flight Test-1 is being lifted to the vertical position at the pad at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida. The Delta IV Heavy is being readied to launch Orion on its first flight test. During its first flight test, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Daniel Casper