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

Chelaru, Teodor-Viorel, E-mail: teodor.chelaru@upb.ro; Chelaru, Adrian, E-mail: achelaru@incas.ro

The paper purpose is to present some aspects regarding the control system of unmanned aerial vehicle - UAV, used to local observations, surveillance and monitoring interest area. The calculus methodology allows a numerical simulation of UAV evolution in bad atmospheric conditions by using nonlinear model, as well as a linear one for obtaining guidance command. The UAV model which will be presented has six DOF (degrees of freedom), and autonomous control system. This theoretical development allows us to build stability matrix, command matrix and control matrix and finally to analyse the stability of autonomous UAV flight. A robust guidance system,more » based on uncoupled state will be evaluated for different fly conditions and the results will be presented. The flight parameters and guidance will be analysed.« less

Apollo experience report: Development of guidance targeting techniques for the command module and launch vehicle

NASA Technical Reports Server (NTRS)

Yencharis, J. D.; Wiley, R. F.; Davis, R. S.; Holmes, Q. A.; Zeiler, K. T.

1972-01-01

The development of the guidance targeting techniques for the Apollo command module and launch vehicle is discussed for four types of maneuvers: (1) translunar injection, (2) translunar midcourse, (3) lunar orbit insertion, and (4) return to earth. The development of real-time targeting programs for these maneuvers and the targeting procedures represented are discussed. The material is intended to convey historically the development of the targeting techniques required to meet the defined target objectives and to illustrate the solutions to problems encountered during that development.

32 CFR 159.6 - Procedures.

Code of Federal Regulations, 2014 CFR

2014-07-01

... as country information and cultural training, and guidance on working with host country nationals and... geographic Combatant Commander shall develop and publish guidance and procedures for PSCs and PSC personnel....49, “Orchestrating, Synchronizing, and Integrating Program Management of Contingency Acquisition...

32 CFR 159.6 - Procedures.

Code of Federal Regulations, 2012 CFR

2012-07-01

... as country information and cultural training, and guidance on working with host country nationals and... geographic Combatant Commander shall develop and publish guidance and procedures for PSCs and PSC personnel....49, “Orchestrating, Synchronizing, and Integrating Program Management of Contingency Acquisition...

32 CFR 159.6 - Procedures.

Code of Federal Regulations, 2013 CFR

2013-07-01

... as country information and cultural training, and guidance on working with host country nationals and... geographic Combatant Commander shall develop and publish guidance and procedures for PSCs and PSC personnel....49, “Orchestrating, Synchronizing, and Integrating Program Management of Contingency Acquisition...

Guidance system operations plan for manned CSM earth orbital and lunar missions using program COLOSSUS 3. Section 7: Erasable memory programs

NASA Technical Reports Server (NTRS)

Hamilton, M. H.

1972-01-01

Erasable-memory programs designed for guidance computers used in command and lunar modules are presented. The purpose, functional description, assumptions, restrictions, and imitations are given for each program.

32 CFR 231.1 - Overview.

Code of Federal Regulations, 2010 CFR

2010-07-01

... guidance and procedures governing the establishment, support, operation, and termination of banks and... installations provide, and are provided, support consistent with the guidance and procedures stated herein. 1... Staff (JCS), the Joint Staff and the supporting Joint Agencies, the Combatant Commands, the Inspector...

32 CFR 159.4 - Policy.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 1 2011-07-01 2011-07-01 false Policy. 159.4 Section 159.4 National Defense...) Geographic Combatant Commanders will provide tailored PSC guidance and procedures for the operational... standards set forth by the geographic Combatant Commander in accordance with paragraph (b) of this section...

MCC level C formulation requirements. Shuttle TAEM guidance and flight control, STS-1 baseline

NASA Technical Reports Server (NTRS)

Carman, G. L.; Montez, M. N.

1980-01-01

The TAEM guidance and body rotational dynamics models required for the MCC simulation of the TAEM mission phase are defined. This simulation begins at the end of the entry phase and terminates at TAEM autoland interface. The logic presented is the required configuration for the first shuttle orbital flight (STS-1). The TAEM guidance is simulated in detail. The rotational dynamics simulation is a simplified model that assumes that the commanded rotational rates can be achieved in the integration interval. Thus, the rotational dynamics simulation is essentially a simulation of the autopilot commanded rates and integration of these rates to determine orbiter attitude. The rotational dynamics simulation also includes a simulation of the speedbrake deflection. The body flap and elevon deflections are computed in the orbiter aerodynamic simulation.

Onboard guidance system design for reusable launch vehicles in the terminal area energy management phase

NASA Astrophysics Data System (ADS)

Mu, Lingxia; Yu, Xiang; Zhang, Y. M.; Li, Ping; Wang, Xinmin

2018-02-01

A terminal area energy management (TAEM) guidance system for an unpowered reusable launch vehicle (RLV) is proposed in this paper. The mathematical model representing the RLV gliding motion is provided, followed by a transformation of extracting the required dynamics for reference profile generation. Reference longitudinal profiles are conceived based on the capability of maximum dive and maximum glide that a RLV can perform. The trajectory is obtained by iterating the motion equations at each node of altitude, where the angle of attack and the flight-path angle are regarded as regulating variables. An onboard ground-track predictor is constructed to generate the current range-to-go and lateral commands online. Although the longitudinal profile generation requires pre-processing using the RLV aerodynamics, the ground-track prediction can be executed online. This makes the guidance scheme adaptable to abnormal conditions. Finally, the guidance law is designed to track the reference commands. Numerical simulations demonstrate that the proposed guidance scheme is capable of guiding the RLV to the desired touchdown conditions.

32 CFR 806b.7 - Responsibilities.

Code of Federal Regulations, 2010 CFR

2010-07-01

... is the senior Air Force Privacy Official with overall responsibility for the Air Force Privacy Act... Data Integrity Board. (5) Provides guidance and assistance to Major Commands, field operating agencies... validate currency. (6) Evaluate the health of the program at regular intervals using this part as guidance...

Approach trajectory planning system for maximum concealment

NASA Technical Reports Server (NTRS)

Warner, David N., Jr.

1986-01-01

A computer-simulation study was undertaken to investigate a maximum concealment guidance technique (pop-up maneuver), which military aircraft may use to capture a glide path from masked, low-altitude flight typical of terrain following/terrain avoidance flight enroute. The guidance system applied to this problem is the Fuel Conservative Guidance System. Previous studies using this system have concentrated on the saving of fuel in basically conventional land and ship-based operations. Because this system is based on energy-management concepts, it also has direct application to the pop-up approach which exploits aircraft performance. Although the algorithm was initially designed to reduce fuel consumption, the commanded deceleration is at its upper limit during the pop-up and, therefore, is a good approximation of a minimum-time solution. Using the model of a powered-lift aircraft, the results of the study demonstrated that guidance commands generated by the system are well within the capability of an automatic flight-control system. Results for several initial approach conditions are presented.

No Guarantee of Success: Unity of Command and Effectiveness in Stability Operations

DTIC Science & Technology

2012-12-06

UN High Commissioner for Refugees in Geneva. Both of these organizations provided guidance to the UNPROFOR Headquarters in Zagreb . The operational...High Commissioner for Refugees Headquarters in Zagreb . In theory, the military chain of command ran from the UN Secretary-General and UN High

Sustaining Soldier Health and Performance in Southwest Asia: Guidance for Small Unit Leaders

DTIC Science & Technology

1994-10-01

SOUTHWEST ASIA: GUIDANCE FOR SMALL UNIT LEADERS Ace._o . ... Prepared by the Staff of . 1 , , ... U.S. Army Research Institute of Environmental Medicine...28 D. Diseases From People......................30 E. Diseases From Contact with Soil & Water...Army Medical Research and Materiel Command (USAMRMC) prepared this handbook of preventive medicine guidance to assist un’t leaders in Southwest Asia

Guidance, navigation, and control systems performance analysis: Apollo 13 mission report

NASA Technical Reports Server (NTRS)

1970-01-01

The conclusions of the analyses of the inflight performance of the Apollo 13 spacecraft guidance, navigation, and control equipment are presented. The subjects discussed are: (1) the command module systems, (2) the lunar module inertial measurement unit, (3) the lunar module digital autopilot, (4) the lunar module abort guidance system, (5) lunar module optical alignment checks, and (6) spacecraft component separation procedures.

Waypoints Following Guidance for Surface-to-Surface Missiles

NASA Astrophysics Data System (ADS)

Zhou, Hao; Khalil, Elsayed M.; Rahman, Tawfiqur; Chen, Wanchun

2018-04-01

The paper proposes waypoints following guidance law. In this method an optimal trajectory is first generated which is then represented through a set of waypoints that are distributed from the starting point up to the final target point using a polynomial. The guidance system then works by issuing guidance command needed to move from one waypoint to the next one. Here the method is applied for a surface-to-surface missile. The results show that the method is feasible for on-board application.

Controls for Reusable Launch Vehicles During Terminal Area Energy Management

NASA Technical Reports Server (NTRS)

Driessen, Brian J.

2005-01-01

During the terminal energy management phase of flight (last of three phases) for a reusable launch vehicle, it is common for the controller to receive guidance commands specifying desired values for (i) the roll angle roll q(sub roll), (ii) the acceleration a(sub n) in the body negative z direction, -k(sub A)-bar, and (iii) omega(sub 3), the projection of onto the body-fixed axis k(sub A)-bar, is always indicated by guidance to be zero. The objective of the controller is to regulate the actual values of these three quantities, i.e make them close to the commanded values, while maintaining system stability.

A Generic Guidance and Control Structure for Six-Degree-of-Freedom Conceptual Aircraft Design

NASA Technical Reports Server (NTRS)

Cotting, M. Christopher; Cox, Timothy H.

2005-01-01

A control system framework is presented for both real-time and batch six-degree-of-freedom simulation. This framework allows stabilization and control with multiple command options, from body rate control to waypoint guidance. Also, pilot commands can be used to operate the simulation in a pilot-in-the-loop environment. This control system framework is created by using direct vehicle state feedback with nonlinear dynamic inversion. A direct control allocation scheme is used to command aircraft effectors. Online B-matrix estimation is used in the control allocation algorithm for maximum algorithm flexibility. Primary uses for this framework include conceptual design and early preliminary design of aircraft, where vehicle models change rapidly and a knowledge of vehicle six-degree-of-freedom performance is required. A simulated airbreathing hypersonic vehicle and a simulated high performance fighter are controlled to demonstrate the flexibility and utility of the control system.

42nd Annual Armament Systems: Gun and Missile Systems

DTIC Science & Technology

2007-04-26

to compare the various contenders: • FCS • Aero and flight dynamics of rounds • Phit and lethality • Direct and indirect fire capability Defence R&D...each other). • Guidance: Unguided, Command Guidance, Lock on Before Launch, Autonomous (needs Phit analysis). • Fuzing: Proximity – RF or Optical

Command Climate: The Rise and the Decline of a Military Concept

DTIC Science & Technology

1988-04-29

understands the component parts and nuances of command climaate can change the tone of the climate through guidance and direction. Clearly, of the three...values, restore the vagueness of the Constitution, change leadership, and decide what to do with a military concept called command climate. The first...climate concept. Three were related to publications and the last was the change in leadership of the Army as GEN Carl E. Vuono became the new Chief of

Apollo experience report guidance and control systems: Primary guidance, navigation, and control system development

NASA Technical Reports Server (NTRS)

Holley, M. D.; Swingle, W. L.; Bachman, S. L.; Leblanc, C. J.; Howard, H. T.; Biggs, H. M.

1976-01-01

The primary guidance, navigation, and control systems for both the lunar module and the command module are described. Development of the Apollo primary guidance systems is traced from adaptation of the Polaris Mark II system through evolution from Block I to Block II configurations; the discussion includes design concepts used, test and qualification programs performed, and major problems encountered. The major subsystems (inertial, computer, and optical) are covered. Separate sections on the inertial components (gyroscopes and accelerometers) are presented because these components represent a major contribution to the success of the primary guidance, navigation, and control system.

Human-Robot Interaction Directed Research Project

NASA Technical Reports Server (NTRS)

Sandor, Aniko; Cross, Ernest V., II; Chang, M. L.

2014-01-01

Human-robot interaction (HRI) is a discipline investigating the factors affecting the interactions between humans and robots. It is important to evaluate how the design of interfaces and command modalities affect the human's ability to perform tasks accurately, efficiently, and effectively when working with a robot. By understanding the effects of interface design on human performance, workload, and situation awareness, interfaces can be developed to appropriately support the human in performing tasks with minimal errors and with appropriate interaction time and effort. Thus, the results of research on human-robot interfaces have direct implications for the design of robotic systems. This DRP concentrates on three areas associated with interfaces and command modalities in HRI which are applicable to NASA robot systems: 1) Video Overlays, 2) Camera Views, and 3) Command Modalities. The first study focused on video overlays that investigated how Augmented Reality (AR) symbology can be added to the human-robot interface to improve teleoperation performance. Three types of AR symbology were explored in this study, command guidance (CG), situation guidance (SG), and both (SCG). CG symbology gives operators explicit instructions on what commands to input, whereas SG symbology gives operators implicit cues so that operators can infer the input commands. The combination of CG and SG provided operators with explicit and implicit cues allowing the operator to choose which symbology to utilize. The objective of the study was to understand how AR symbology affects the human operator's ability to align a robot arm to a target using a flight stick and the ability to allocate attention between the symbology and external views of the world. The study evaluated the effects type of symbology (CG and SG) has on operator tasks performance and attention allocation during teleoperation of a robot arm. The second study expanded on the first study by evaluating the effects of the type of navigational guidance (CG and SG) on operator task performance and attention allocation during teleoperation of a robot arm through uplinked commands. Although this study complements the first study on navigational guidance with hand controllers, it is a separate investigation due to the distinction in intended operators (i.e., crewmembers versus ground-operators). A third study looked at superimposed and integrated overlays for teleoperation of a mobile robot using a hand controller. When AR is superimposed on the external world, it appears to be fixed onto the display and internal to the operators' workstation. Unlike superimposed overlays, integrated overlays often appear as three-dimensional objects and move as if part of the external world. Studies conducted in the aviation domain show that integrated overlays can improve situation awareness and reduce the amount of deviation from the optimal path. The purpose of the study was to investigate whether these results apply to HRI tasks, such as navigation with a mobile robot. HRP GAPS This HRI research contributes to closure of HRP gaps by providing information on how display and control characteristics - those related to guidance, feedback, and command modalities - affect operator performance. The overarching goals are to improve interface usability, reduce operator error, and develop candidate guidelines to design effective human-robot interfaces.

Apollo experience report. Guidance and control systems: Command and service module stabilization and control system

NASA Technical Reports Server (NTRS)

Littleton, O. P.

1974-01-01

The concepts, design, development, testing, and flight results of the command and service module stabilization and control system are discussed. The period of time covered was from November 1961 to December 1972. Also included are a functional description of the system, a discussion of the major problems, and recommendations for future programs.

4D BADA-based Trajectory Generator and 3D Guidance Algorithm

NASA Technical Reports Server (NTRS)

Palacios, Eduardo Sepulveda; Johnson, Marcus A.

2013-01-01

This paper presents a hybrid integration between aerodynamic, airline procedures and other BADA-based (Base of Aircraft Data) coefficients with a classical aircraft dynamic model. This paper also describes a three-dimensional guidance algorithm implemented in order to produce commands for the aircraft to follow a flight plan. The software chosen for this work is MATLAB.

Air Mobility Command’s Total Force Integration: A Critical Analysis

DTIC Science & Technology

2012-02-26

variety of techniques available to positively change culture . 9 Changing assumptions of in-group collectivist requires increasing breadth and open...there have been issues. Command structure, cultural differences and vague guidance for implementation have plagued Air Mobility Command’s...through the Governor and not the President of the United States. Cultural Considerations The purpose of this section is to identify and discuss

Apollo experience report: Guidance and control systems: Command and service module entry monitor subsystem

NASA Technical Reports Server (NTRS)

Reina, B., Jr.; Patterson, H. G.

1975-01-01

The conceptual aspects of the command and service module entry monitor subsystem, together with an interpretation of the displays and their associated relationship to entry trajectory control, are presented. The entry monitor subsystem is described, and the problems encountered during the developmental phase and the first five manned Apollo flights are discussed in conjunction with the design improvements implemented.

Rapid Radiochemical Methods for Selected Radionuclides

EPA Pesticide Factsheets

The rapid methods documents are supplement guidance in a planned series designed to present radioanalytical laboratory personnel, Incident Commanders (and their designees), and other field response personnel.

Guidance and Control of a Man-Portable Precision Munition Concept

DTIC Science & Technology

2014-06-01

challenges posed by characteristics of spin-stabilized flight dynamics such as limit cycles, center -of- gravity swerve, instability, and practical...Control Line-of-sight rate and closing velocity estimates are used to form proportional navigation commands in classical guidance schemes...Accelerometers and gyroscopes often supply additional necessary feedback. The accelerometers ensure that the airframe is maneuvering the center of gravity

Apollo Onboard Navigation Techniques

NASA Technical Reports Server (NTRS)

Interbartolo, Michael

2009-01-01

This viewgraph presentation reviews basic navigation concepts, describes coordinate systems and identifies attitude determination techniques including Primary Guidance, Navigation and Control System (PGNCS) IMU management and Command and Service Module Stabilization and Control System/Lunar Module (LM) Abort Guidance System (AGS) attitude management. The presentation also identifies state vector determination techniques, including PGNCS coasting flight navigation, PGNCS powered flight navigation and LM AGS navigation.

Human-Robot Interaction Directed Research Project

NASA Technical Reports Server (NTRS)

Rochlis, Jennifer; Ezer, Neta; Sandor, Aniko

2011-01-01

Human-robot interaction (HRI) is about understanding and shaping the interactions between humans and robots (Goodrich & Schultz, 2007). It is important to evaluate how the design of interfaces and command modalities affect the human s ability to perform tasks accurately, efficiently, and effectively (Crandall, Goodrich, Olsen Jr., & Nielsen, 2005) It is also critical to evaluate the effects of human-robot interfaces and command modalities on operator mental workload (Sheridan, 1992) and situation awareness (Endsley, Bolt , & Jones, 2003). By understanding the effects of interface design on human performance, workload, and situation awareness, interfaces can be developed that support the human in performing tasks with minimal errors and with appropriate interaction time and effort. Thus, the results of research on human-robot interfaces have direct implications for design. Because the factors associated with interfaces and command modalities in HRI are too numerous to address in 3 years of research, the proposed research concentrates on three manageable areas applicable to National Aeronautics and Space Administration (NASA) robot systems. These topic areas emerged from the Fiscal Year (FY) 2011 work that included extensive literature reviews and observations of NASA systems. The three topic areas are: 1) video overlays, 2) camera views, and 3) command modalities. Each area is described in detail below, along with relevance to existing NASA human-robot systems. In addition to studies in these three topic areas, a workshop is proposed for FY12. The workshop will bring together experts in human-robot interaction and robotics to discuss the state of the practice as applicable to research in space robotics. Studies proposed in the area of video overlays consider two factors in the implementation of augmented reality (AR) for operator displays during teleoperation. The first of these factors is the type of navigational guidance provided by AR symbology. In the proposed studies, participants performance during teleoperation of a robot arm will be compared when they are provided with command-guidance symbology (that is, directing the operator what commands to make) or situation-guidance symbology (that is, providing natural cues so that the operator can infer what commands to make). The second factor for AR symbology is the effects of overlays that are either superimposed or integrated into the external view of the world. A study is proposed in which the effects of superimposed and integrated overlays on operator task performance during teleoperated driving tasks are compared

Flight evaluation of advanced controls and displays for transition and landing on the NASA V/STOL systems research aircraft

NASA Technical Reports Server (NTRS)

Franklin, James A.; Stortz, Michael W.; Borchers, Paul F.; Moralez, Ernesto, III

1996-01-01

Flight experiments were conducted on Ames Research Center's V/STOL Systems Research Aircraft (VSRA) to assess the influence of advanced control modes and head-up displays (HUD's) on flying qualities for precision approach and landing operations. Evaluations were made for decelerating approaches to hover followed by a vertical landing and for slow landings for four control/display mode combinations: the basic YAV-8B stability augmentation system; attitude command for pitch, roll, and yaw; flightpath/acceleration command with translational rate command in the hover; and height-rate damping with translational-rate command. Head-up displays used in conjunction with these control modes provided flightpath tracking/pursuit guidance and deceleration commands for the decelerating approach and a mixed horizontal and vertical presentation for precision hover and landing. Flying qualities were established and control usage and bandwidth were documented for candidate control modes and displays for the approach and vertical landing. Minimally satisfactory bandwidths were determined for the translational-rate command system. Test pilot and engineer teams from the Naval Air Warfare Center, the Boeing Military Airplane Group, Lockheed Martin, McDonnell Douglas Aerospace, Northrop Grumman, Rolls-Royce, and the British Defense Research Agency participated in the program along with NASA research pilots from the Ames and Lewis Research Centers. The results, in conjunction with related ground-based simulation data, indicate that the flightpath/longitudinal acceleration command response type in conjunction with pursuit tracking and deceleration guidance on the HUD would be essential for operation to instrument minimums significantly lower than the minimums for the AV-8B. It would also be a superior mode for performing slow landings where precise control to an austere landing area such as a narrow road is demanded. The translational-rate command system would reduce pilot workload for demanding vertical landing tasks aboard ship and in confined land-based sites.

Guidance system operations plan for manned CM earth orbital missions using program Skylark 1. Section 2: Data links

NASA Technical Reports Server (NTRS)

Hamilton, M. H.

1972-01-01

A computer program to define the digital uplink and downlink for use in manned command module orbital missions is presented. The subjects discussed are: (1) digital uplink to command module, (2) CMC digital downlink, (3) downlist formats, (4) description of telemetered qualities, (5) flagbits, and (6) effects of Fresh Start (V36) and Hardware Restart on flagword and channel bits.

Federated Ground Station Network Model and Interface Specification

DTIC Science & Technology

2014-12-01

interface definition language JSON JavaScript Object Notation LEO low Earth orbit LNA low-noise amplifier MC3 Mobile CubeSat Command and Control...Naval Research Laboratory OQPSK offset quadrature phase-shift keying xviii P2P peer-to-peer PKI public key infrastructure REST Representational...enhanced our work being performed on the Mobile CubeSat Command and Control (MC3) ground station network. You also provided crucial guidance from

Air Force Technical Objective Document FY 87

DTIC Science & Technology

1985-12-01

Air Force Systems Command Edwards Air Force Base. Cal ifornia 93523-5000 NOTICES THIS DOCUMENT IS FOR INFORMATION AND GUIDANCE ONL Y This...acquisition of Air Foree weapon systems . Each Air Foree laboratory annually formulates Q Research and Technology (R& T) Pion in response to available...guidance based on USAF requirements, the identification of scientific and technological opportunities, and the needs of present and projected systems

Army Contracting: Training and Guidance Needed to Ensure Appropriate Use of the Option to Extend Services Clause

DTIC Science & Technology

2016-01-28

reproduce this material separately. The Government Accountability Office, the audit , evaluation, and investigative arm of...Executive Director Army Contracting Command-Redstone Arsenal Army Contracting: Training and Guidance Needed to Ensure Appropriate Use of the Option to...which this report is based in accordance with generally accepted government auditing standards. Those standards require that we plan and perform the

Guidance and Control Aspects of Tactical Air-Launched Missiles

DTIC Science & Technology

1980-10-01

information; - Continuously stimulating advances in the aerospace sciences relevant to strengthening the common defence pusture; -- Improving the co...Symposium on Precision Delivery Systems was held at Eglin Air Force Base , Florida. USA. Many important advances in guidance sensor technology, control system...paper concentrates primarily or the US Army Missile Command’s technology base for development of the precision pointing and tracking or fire control

32 CFR 705.18 - Authority and coordination.

Code of Federal Regulations, 2010 CFR

2010-07-01

... naval command will coordinate its community relations program with the senior authority having... exceptions to policy or regulations. This authority may be delegated. (1) Policy, direction and guidance for...

Design and Implementation of a Collision Avoidance System for the NPS autonomous Underwater Vehicle (AUV II) Utilizing Ultrasonic Sensors

DTIC Science & Technology

1991-09-01

exectti:n by providing geographic waypoints and tasks to the guidance system. The guidance system provides desired vehicle postures, ( x , y, z, 0), as...Maker Guidance System Patter ( x ,y,zlt) Recognition LOS Cross Track No Cubic Spiral Heading Spee Depth Mode Commands Navigation Autopilot System Systems...20log2r + 2otr (Eq 3.3) where ( x is the attenuation coefficient of sound in water at the frequency in use and r is the length of the transmission

U.S. Pacific Command > Leadership

Science.gov Websites

PACOM Professional Development Reading List History Defense Strategic Guidance (PDF) USPACOM Area of Speeches / Testimony Freedom of Information Act FOIA - Reading Room Submit FOIA Request Request Status FOIA

Control integration concept for hypersonic cruise-turn maneuvers

NASA Technical Reports Server (NTRS)

Raney, David L.; Lallman, Frederick J.

1992-01-01

Piloting difficulties associated with conducting aircraft maneuvers in hypersonic flight are caused in part by the nonintuitive nature of the aircraft response and the stringent constraints anticipated on allowable angle of attack and dynamic pressure variations. An approach is documented that provides precise, coordinated maneuver control during excursions from a hypersonic cruise flight path and the necessary flight condition constraints. The approach is to achieve specified guidance commands by resolving altitude and cross range errors into a load factor and bank angle command by using a coordinate transformation that acts as an interface between outer and inner loop flight controls. This interface, referred to as a 'resolver', applies constraints on angle of attack and dynamic pressure perturbations while prioritizing altitude regulation over cross range. An unpiloted test simulation, in which the resolver was used to drive inner loop flight controls, produced time histories of responses to guidance commands and atmospheric disturbances at Mach numbers of 6, 10, 15, and 20. Angle of attack and throttle perturbation constraints, combined with high speed flight effects and the desire to maintain constant dynamic pressure, significantly impact the maneuver envelope for a hypersonic vehicle.

Human-Robot Interaction Directed Research Project

NASA Technical Reports Server (NTRS)

Sandor, Aniko; Cross, Ernest V., II; Chang, Mai Lee

2014-01-01

Human-robot interaction (HRI) is a discipline investigating the factors affecting the interactions between humans and robots. It is important to evaluate how the design of interfaces and command modalities affect the human's ability to perform tasks accurately, efficiently, and effectively when working with a robot. By understanding the effects of interface design on human performance, workload, and situation awareness, interfaces can be developed to appropriately support the human in performing tasks with minimal errors and with appropriate interaction time and effort. Thus, the results of research on human-robot interfaces have direct implications for the design of robotic systems. This DRP concentrates on three areas associated with interfaces and command modalities in HRI which are applicable to NASA robot systems: 1) Video Overlays, 2) Camera Views, and 3) Command Modalities. The first study focused on video overlays that investigated how Augmented Reality (AR) symbology can be added to the human-robot interface to improve teleoperation performance. Three types of AR symbology were explored in this study, command guidance (CG), situation guidance (SG), and both (SCG). CG symbology gives operators explicit instructions on what commands to input, whereas SG symbology gives operators implicit cues so that operators can infer the input commands. The combination of CG and SG provided operators with explicit and implicit cues allowing the operator to choose which symbology to utilize. The objective of the study was to understand how AR symbology affects the human operator's ability to align a robot arm to a target using a flight stick and the ability to allocate attention between the symbology and external views of the world. The study evaluated the effects type of symbology (CG and SG) has on operator tasks performance and attention allocation during teleoperation of a robot arm. The second study expanded on the first study by evaluating the effects of the type of navigational guidance (CG and SG) on operator task performance and attention allocation during teleoperation of a robot arm through uplinked commands. Although this study complements the first study on navigational guidance with hand controllers, it is a separate investigation due to the distinction in intended operators (i.e., crewmembers versus ground-operators). A third study looked at superimposed and integrated overlays for teleoperation of a mobile robot using a hand controller. When AR is superimposed on the external world, it appears to be fixed onto the display and internal to the operators' workstation. Unlike superimposed overlays, integrated overlays often appear as three-dimensional objects and move as if part of the external world. Studies conducted in the aviation domain show that integrated overlays can improve situation awareness and reduce the amount of deviation from the optimal path. The purpose of the study was to investigate whether these results apply to HRI tasks, such as navigation with a mobile robot.

U.S. Pacific Command > Contact > Directory

Science.gov Websites

PACOM Professional Development Reading List History Defense Strategic Guidance (PDF) USPACOM Area of Speeches / Testimony Freedom of Information Act FOIA - Reading Room Submit FOIA Request Request Status FOIA

Apollo guidance, navigation and control: Guidance system operations plan for manned CM earth orbital and lunar missions using Program COLOSSUS 3. Section 3: Digital autopilots (revision 14)

NASA Technical Reports Server (NTRS)

1972-01-01

Digital autopilots for the manned command module earth orbital and lunar missions using program COLOSSUS 3 are discussed. Subjects presented are: (1) reaction control system digital autopilot, (2) thrust vector control autopilot, (3) entry autopilot and mission control programs, (4) takeover of Saturn steering, and (5) coasting flight attitude maneuver routine.

Processing Multiyear Procurement (MYP) Submissions - A Handbook for Air Force Program Offices

DTIC Science & Technology

1985-05-01

Contracting and Manufacturing Policy; "Policy Letter 84-1l - Multiyear Contracting Guidance" Headquarters, United States Air Force, Washington, D.C...supplement to Air Force FAR Sup No. 17.191: as enclosed in Thomas E. Lloyd, Colonel, USAF, Assistant DCS/Contracting , and Manufacturing , "DCS...Contracting and Manufacturing Policy Letter 84-16, Multiyear Contracting Guidance." Headquarters, Air Force Systems Command, Andrew Air Force Base

Effects of Budget Reductions on Army Acquisition Support of Equipping and Modernization Goals

DTIC Science & Technology

2015-04-16

overall Army budgets are significantly reduced (34% since 2008), maintaining the entire equipment portfolio reduces the funding available to meet...the Mission Command portfolio , examine their impact on equipping and modernization, and make recommendations on how to divest the equipment no longer... portfolio of equipment being managed and the link to the new Defense guidance and Army equipping guidance and modernization plans. Any systems or programs

U.S. Pacific Command > Organization > Organization Chart

Science.gov Websites

PACOM Professional Development Reading List History Defense Strategic Guidance (PDF) USPACOM Area of Speeches / Testimony Freedom of Information Act FOIA - Reading Room Submit FOIA Request Request Status FOIA

U.S. Pacific Command > Resources > Useful Links

Science.gov Websites

PACOM Professional Development Reading List History Defense Strategic Guidance (PDF) USPACOM Area of Speeches / Testimony Freedom of Information Act FOIA - Reading Room Submit FOIA Request Request Status FOIA

Flight evaluation of configuration management system concepts during transition to the landing approach for a powered-lift STOL aircraft

NASA Technical Reports Server (NTRS)

Franklin, J. A.; Innis, R. C.

1980-01-01

Flight experiments were conducted to evaluate two control concepts for configuration management during the transition to landing approach for a powered-lift STOL aircraft. NASA Ames' augmentor wing research aircraft was used in the program. Transitions from nominal level-flight configurations at terminal area pattern speeds were conducted along straight and curved descending flightpaths. Stabilization and command augmentation for attitude and airspeed control were used in conjunction with a three-cue flight director that presented commands for pitch, roll, and throttle controls. A prototype microwave system provided landing guidance. Results of these flight experiments indicate that these configuration management concepts permit the successful performance of transitions and approaches along curved paths by powered-lift STOL aircraft. Flight director guidance was essential to accomplish the task.

The Process of Sensemaking in Complex Human Endeavors

DTIC Science & Technology

2008-06-01

encompassing Joint, Interagency, and Multinational capabilities. The Art and Science of Battle Command LeadUnderstand CDR / Staff ART / Science In short, we...operations. Staff Running Estimates t ff i i Visualize CDR / Staff ART / Science •Planning guidance •Planning guidance •Cdr ’s Intent Describe CDR...Staff ART / Science •Plans & Orders •Preparation •Plans & Orders •Preparation •Execution WF • Intelligence •Maneuver •Fire Support • Protection

U.S. Pacific Command > About USPACOM > USPACOM Area of Responsibility

Science.gov Websites

PACOM Professional Development Reading List History Defense Strategic Guidance (PDF) USPACOM Area of Speeches / Testimony Freedom of Information Act FOIA - Reading Room Submit FOIA Request Request Status FOIA

U.S. Pacific Command > Contact > Directory > J0 > Office of Inspector

Science.gov Websites

PACOM Professional Development Reading List History Defense Strategic Guidance (PDF) USPACOM Area of Speeches / Testimony Freedom of Information Act FOIA - Reading Room Submit FOIA Request Request Status FOIA

Reconfigurable Software for Controlling Formation Flying

NASA Technical Reports Server (NTRS)

Mueller, Joseph B.

2006-01-01

Software for a system to control the trajectories of multiple spacecraft flying in formation is being developed to reflect underlying concepts of (1) a decentralized approach to guidance and control and (2) reconfigurability of the control system, including reconfigurability of the software and of control laws. The software is organized as a modular network of software tasks. The computational load for both determining relative trajectories and planning maneuvers is shared equally among all spacecraft in a cluster. The flexibility and robustness of the software are apparent in the fact that tasks can be added, removed, or replaced during flight. In a computational simulation of a representative formation-flying scenario, it was demonstrated that the following are among the services performed by the software: Uploading of commands from a ground station and distribution of the commands among the spacecraft, Autonomous initiation and reconfiguration of formations, Autonomous formation of teams through negotiations among the spacecraft, Working out details of high-level commands (e.g., shapes and sizes of geometrically complex formations), Implementation of a distributed guidance law providing autonomous optimization and assignment of target states, and Implementation of a decentralized, fuel-optimal, impulsive control law for planning maneuvers.

THE ONCE AND FUTURE AIR SUPPORT OPERATIONS CENTER: A CRITICAL REFLECTION ON DEVELOPMENTS IN AIR-TO-GROUND COMMAND AND CONTROL

DTIC Science & Technology

2017-02-01

call for an examination of ASOC history to provide clear guidance for leaders designing the contemporary ASOC. Research Question What does the...be combined in the design of the future ASOC and what is required to enhance and sustain its capability. 4 Finally, the research concludes by...DEVELOPMENTS IN AIR-TO- GROUND COMMAND AND CONTROL by Seth D. Spidahl, Capt, USAF A Research Report Submitted to the Faculty In Partial Fulfillment

An Alignment Analysis of the U.S. Navy Supply Corps Officer’s Career Guidance With Naval Supply Systems Command’s Strategic Publications

DTIC Science & Technology

2014-06-03

relationship to business outcomes such as customer satisfaction , turnover, safety, and productivity” (Shuck, 2011, p. 312). Follow-on studies using...during the analysis efforts of this research. The 339 Level 1 codes span a wide range of ideas from strategy execution to customer satisfaction and...not reflect the radical shift in corporate culture needed by Naval Supply Systems Command (NAVSUP) to better serve U.S. Navy customers . This research

Next Generation Molecular Histology Using Highly Multiplexed Ion Beam Imaging (MIBI) of Breast Cancer Tissue Specimens for Enhanced Clinical Guidance

DTIC Science & Technology

2016-07-01

AWARD NUMBER: W81XWH-14-1-0180 TITLE: Next-Generation Molecular Histology Using Highly Multiplexed Ion Beam Imaging (MIBI) of Breast Cancer Tissue...1212 REPORT DATE: July 2016 TYPE OF REPORT: Annual PREPARED FOR: U.S. Army Medical Research and Materiel Command Fort Detrick, Maryland 21702-5012...SPONSOR/MONITOR’S ACRONYM(S) U.S. Army Medical Research and Materiel Command Fort Detrick, Maryland 21702-5012 11. SPONSOR/MONITOR’S REPORT NUMBER

Resiliency in the Rear Detachment: Using the Rear Detachment (Provisional) as an Integral Part of Building Resiliency in Units at the Brigade and Below for Current and Future Deployments

DTIC Science & Technology

2010-12-10

from Army Community Services, Resiliency Campus, Family Morale Welfare and Recreation Command, to Develop Resiliency in the Families Left Behind... Development Guidance, FY 10-11 Washington, DC: Government Printing Office, 2009. Department the Army. Family Morale Welare and Recreation Command Programs...is used, does not address building family resiliency. These are the gaps that will be examined (1) development of Rear Detachment leaders, (2

Commanders and Cyber Chat: Should More Guidance be Provided for Social Networking Sites

DTIC Science & Technology

2011-04-01

his favorite book is Mein Kampf, his favorite movie is the Nazi propaganda film, Triumph of the Will, his interests are “white women, and his...service member wearing a Navy uniform and holding a Confederate insignia is on a commander’s friends list? Is that commander responsible for...Cybervetting and Posting. January 10, 2011. www.inamecheck.com. 18 Ibid. 19 Ibid. 20 Baron, Kevin. "Watchdog group: Dozens of active-duty found on neo- Nazi

Impact Angle and Time Control Guidance Under Field-of-View Constraints and Maneuver Limits

NASA Astrophysics Data System (ADS)

Shim, Sang-Wook; Hong, Seong-Min; Moon, Gun-Hee; Tahk, Min-Jea

2018-04-01

This paper proposes a guidance law which considers the constraints of seeker field-of-view (FOV) as well as the requirements on impact angle and time. The proposed guidance law is designed for a constant speed missile against a stationary target. The guidance law consists of two terms of acceleration commands. The first one is to achieve zero-miss distance and the desired impact angle, while the second is to meet the desired impact time. To consider the limits of FOV and lateral maneuver capability, a varying-gain approach is applied on the second term. Reduction of realizable impact times due to these limits is then analyzed by finding the longest course among the feasible ones. The performance of the proposed guidance law is demonstrated by numerical simulation for various engagement conditions.

Apollo experience report: Guidance and control systems. Mission control programmer for unmanned missions AS-202, Apollo 4, and Apollo 6

NASA Technical Reports Server (NTRS)

Holloway, G. F.

1975-01-01

An unmanned test flight program required to evaluate the command module heat shield and the structural integrity of the command and service module/Saturn launch vehicle is described. The mission control programer was developed to provide the unmanned interface between the guidance and navigation computer and the other spacecraft systems for mission event sequencing and real-time ground control during missions AS-202, Apollo 4, and Apollo 6. The development of this unmanned programer is traced from the initial concept through the flight test phase. Detailed discussions of hardware development problems are given with the resulting solutions. The mission control programer functioned correctly without any flight anomalies for all missions. The Apollo 4 mission control programer was reused for the Apollo 6 flight, thus being one of the first subsystems to be reflown on an Apollo space flight.

Post-Flight EDL Entry Guidance Performance of the 2011 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; McGrew, Lynn Craig

2012-01-01

The 2011 Mars Science Laboratory was the first successful Mars mission to attempt a guided entry which safely delivered the rover to a final position approximately 2 km from its target within a touchdown ellipse of 19.1 km x 6.9 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range error while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Key dispersions driving deploy ellipse and altitude performance are identified. Performance sensitivities including attitude initialization error and the velocity of transition from range control to heading alignment are presented. Just prior to the entry and landing of MSL in August 2012, the EDL team examined minute tuning of the reference trajectory for the selected landing site, analyzed whether adjustment of bank reversal deadbands were necessary, the heading alignment velocity trigger was in union with other parameters to balance the EDL risks, and the vertical L/D command limits. This paper details a preliminary postflight assessment of the telemetry and trajectory reconstruction that is being performed, and updates the information presented in the former paper Entry Guidance for the 2011 Mars Science Laboratory Mission (AIAA Atmospheric Flight Mechanics Conference; 8-11 Aug. 2011; Portland, OR; United States)

A Combat Search and Rescue (CSAR) Role for the CV-22: It’s Coming, Get Ready

DTIC Science & Technology

2008-04-01

STUDY SHOULD INCLUDE THE FOREGOING STATEMENT. QUOTATION FROM, ABSTRACTION FROM, OR REPRODUCTION OF ALL OR ANY PART OF THIS DOCUMENT IS PERMITTED...naval-technology.com. IInaval-technology.com. 1I CH-53E Super Stallion - Heavy-Lift Helicopter. 2007. http://www.naval-technology.com/projects/ch-53e...accessed March 19,2008). Olson, Eric. AFSOC Mission Guidanc.e Letter. U.S. Special Operations Command, October 2007. Pike, John. IICH-53E Super Stallion

Development of guidance laws for a variable-speed missile

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

Gazit, R.; Gutman, S.

1991-05-01

The most used guidance law for short-range homing missiles is proportional navigation (PN). In PN, the acceleration command is proportional to the line-of-sight (LOS) angular velocity. Indeed, if a missile and a target move on a collision course with constant speeds, the LOS rate is zero. The speed of a highly maneuverable modern missile varies considerably during flight. The performance of PN is far from being satisfactory in that case. In this article the collision course for a variable-speed missile is analyzed and a guidance law that steers the heading of the missile to the collision course is defined. Guidancemore » laws based on optimal control and differential game formulations are developed, and note that both optimal laws coincide with the Guidance to Collision law at impact. The performance improvement of the missile using the new guidance law as compared to PN is demonstrated. 19 refs.« less

Defense transportation : more reliable information key to managing airlift services more efficiently

DOT National Transportation Integrated Search

2000-02-01

The Department of Defense's (DOD) guidance provides that the Air Mobility Command's airlift costs associated with its peacetime mission (operations and maintenance) are to be funded through a transportation working capital fund. Under the working cap...

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

Pasquale, David A.; Hansen, Richard G.

This paper discusses command and control issues relating to the operation of Incident Command Posts (ICPs) and Emergency Operations Centers (EOCs) in the surrounding area jurisdictions following the detonation of an Improvised Nuclear Device (IND). Although many aspects of command and control will be similar to what is considered to be normal operations using the Incident Command System (ICS) and the National Incident Management System (NIMS), the IND response will require many new procedures and associations in order to design and implement a successful response. The scope of this white paper is to address the following questions: • Would themore » current command and control framework change in the face of an IND incident? • What would the management of operations look like as the event unfolded? • How do neighboring and/or affected jurisdictions coordinate with the state? • If the target area’s command and control infrastructure is destroyed or disabled, how could neighboring jurisdictions assist with command and control of the targeted jurisdiction? • How would public health and medical services fit into the command and control structure? • How can pre-planning and common policies improve coordination and response effectiveness? • Where can public health officials get federal guidance on radiation, contamination and other health and safety issues for IND response planning and operations?« less

User's guide to programming fault injection and data acquisition in the SIFT environment

NASA Technical Reports Server (NTRS)

Elks, Carl R.; Green, David F.; Palumbo, Daniel L.

1987-01-01

Described are the features, command language, and functional design of the SIFT (Software Implemented Fault Tolerance) fault injection and data acquisition interface software. The document is also intended to assist and guide the SIFT user in defining, developing, and executing SIFT fault injection experiments and the subsequent collection and reduction of that fault injection data. It is also intended to be used in conjunction with the SIFT User's Guide (NASA Technical Memorandum 86289) for reference to SIFT system commands, procedures and functions, and overall guidance in SIFT system programming.

The Weakest Pillar: U.S. Northern Command’s Role in Solving the Federal Government’s Domestic Consequence Management Problem

DTIC Science & Technology

2008-10-31

frame a set of confusing guidance on the federal response posture to the threat of WMD in the homeland. Figure 2, although a little dated, depicts the...20 “Coast Guard History Corner,” 3. 21 Susie Moncla, “The Texas City Disaster – April 16 & 17, 1947”, Texas City Library, 1 April 2008...through a unified command. A close review of the two figures and the National Response Framework shows there is little or no coordination between the

Supporting Command and Control (C2) of an Embarked Commander: Tunneling SIPRNet Data Across an UNCLAS Wireless LAN

DTIC Science & Technology

2011-09-01

that you did to help me through this process. Your efforts and guidance truly made this a success. To SPAWAR SCTD expert Stephanie Koontz , your...ty%20and%20Safety%20Services/05– 500%20Security%20Services/5510.36A.pdf [accessed June 19, 2011]. [28] S. Koontz . “Secret client tunneling...devices - KOV-26 talon user procedures.” Unpublished survey, SPAWAR, Point Loma, CA. [29] S. Koontz . “Secret client tunneling devices - KIV-54 user

Defense Department Cyber Efforts: More Detailed Guidance Needed to Ensure Military Services Develop Appropriate Cyberspace Capabilities

DTIC Science & Technology

2011-05-01

communications and on computer networks—its Global Information Grid—which are potentially jeopardized by the millions of denial-of-service attacks, hacking ...Director,a National Security Agency Chief of Staff Joint Operations Center Defense Information Systems Agency Command Center J1 J2 J3 J4 J5 J6 J7 J8...DC Joint Staff • J39, Operations, Pentagon, Washington, DC • J5 , Strategic Plans and Policy, Pentagon, Washington, DC U.S. Strategic Command • J882

Commandant Instruction 1020.11A: Coast Guard Hot Weather Boat Outfit

DOT National Transportation Integrated Search

1997-06-09

Authorizes the Coast Guard Hot Weather Boat Crew Outfit as organizational : clothing. It also provides-up-to date guidance identifying when the Coast Guard : Hot Weather Boat Crew Outfit is appropriate for wear; the outfit's components; : and where t...

An Investigation of Operational Decision Making in Situ: Incident Command in the U.K. Fire and Rescue Service.

PubMed

Cohen-Hatton, Sabrina R; Butler, Philip C; Honey, Robert C

2015-08-01

The aim of this study was to better understand the nature of decision making at operational incidents in order to inform operational guidance and training. Normative models of decision making have been adopted in the guidance and training for emergency services. In these models, it is assumed that decision makers assess the current situation, formulate plans, and then execute the plans. However, our understanding of how decision making unfolds at operational incidents remains limited. Incident commanders, attending 33 incidents across six U.K. Fire and Rescue Services, were fitted with helmet-mounted cameras, and the resulting video footage was later independently coded and used to prompt participants to provide a running commentary concerning their decisions. The analysis revealed that assessment of the operational situation was most often followed by plan execution rather than plan formulation, and there was little evidence of prospection about the potential consequences of actions. This pattern of results was consistent across different types of incident, characterized by level of risk and time pressure, but was affected by the operational experience of the participants. Decision making did not follow the sequence of phases assumed by normative models and conveyed in current operational guidance but instead was influenced by both reflective and reflexive processes. These results have clear implications for understanding operational decision making as it occurs in situ and suggest a need for future guidance and training to acknowledge the role of reflexive processes. © 2015, Human Factors and Ergonomics Society.

On-Board Entry Trajectory Planning Expanded to Sub-orbital Flight

NASA Technical Reports Server (NTRS)

Lu, Ping; Shen, Zuojun

2003-01-01

A methodology for on-board planning of sub-orbital entry trajectories is developed. The algorithm is able to generate in a time frame consistent with on-board environment a three-degree-of-freedom (3DOF) feasible entry trajectory, given the boundary conditions and vehicle modeling. This trajectory is then tracked by feedback guidance laws which issue guidance commands. The current trajectory planning algorithm complements the recently developed method for on-board 3DOF entry trajectory generation for orbital missions, and provides full-envelope autonomous adaptive entry guidance capability. The algorithm is validated and verified by extensive high fidelity simulations using a sub-orbital reusable launch vehicle model and difficult mission scenarios including failures and aborts.

Simulation of automatic precision departures and missed approaches using the microwave landing system

NASA Technical Reports Server (NTRS)

Feather, J. B.

1987-01-01

Results of simulated precision departures and missed approaches using MLS guidance concepts are presented. The study was conducted under the Terminal Configured Vehicle (TCV) Program, and is an extension of previous work by DAC under the Advanced Transport Operating System (ATOPS) Technology Studies Program. The study model included simulation of an MD-80 aircraft, an autopilot, and a MLS guidance computer that provided lateral and vertical steering commands. Precision departures were evaluated using a noise abatement procedure. Several curved path departures were simulated with MLS noise and under various environmental conditions. Missed approaches were considered for the same runway, where lateral MLS guidance maintained the aircraft along the extended runway centerline. In both the departures and the missed approach cases, pitch autopilot takeoff and go-around modes of operation were used in conjunction with MLS lateral guidance.

VTOL shipboard letdown guidance system analysis

NASA Technical Reports Server (NTRS)

Phatak, A. V.; Karmali, M. S.

1983-01-01

Alternative letdown guidance strategies are examined for landing of a VTOL aircraft onboard a small aviation ship under adverse environmental conditions. Off line computer simulation of shipboard landing task is utilized for assessing the relative merits of the proposed guidance schemes. The touchdown performance of a nominal constant rate of descent (CROD) letdown strategy serves as a benchmark for ranking the performance of the alternative letdown schemes. Analysis of ship motion time histories indicates the existence of an alternating sequence of quiescent and rough motions called lulls and swells. A real time algorithms lull/swell classification based upon ship motion pattern features is developed. The classification algorithm is used to command a go/no go signal to indicate the initiation and termination of an acceptable landing window. Simulation results show that such a go/no go pattern based letdown guidance strategy improves touchdown performance.

Kennedy Space Center, Space Shuttle Processing, and International Space Station Program Overview

NASA Technical Reports Server (NTRS)

Higginbotham, Scott Alan

2011-01-01

Topics include: International Space Station assembly sequence; Electrical power substation; Thermal control substation; Guidance, navigation and control; Command data and handling; Robotics; Human and robotic integration; Additional modes of re-supply; NASA and International partner control centers; Space Shuttle ground operations.

Conceptual design study of a Harrier V/STOL research aircraft

NASA Technical Reports Server (NTRS)

Bode, W. E.; Berger, R. L.; Elmore, G. A.; Lacey, T. R.

1978-01-01

MCAIR recently completed a conceptual design study to define modification approaches to, and derive planning prices for the conversion of a two place Harrier to a V/STOL control, display and guidance research aircraft. Control concepts such as rate damping, attitude stabilization, velocity command, and cockpit controllers are to be demonstrated. Display formats will also be investigated, and landing, navigation and guidance systems flight tested. The rear cockpit is modified such that it can be quickly adapted to faithfully simulate the controls, displays and handling qualities of a Type A or Type B V/STOL. The safety pilot always has take command capability. The modifications studied fall into two categories: basic modifications and optional modifications. Technical descriptions of the basic modifications and of the optional modifications are presented. The modification plan and schedule as well as the test plan and schedule are presented. The failure mode and effects analysis, aircraft performance, aircraft weight, and aircraft support are discussed.

Guidance, steering, load relief and control of an asymmetric launch vehicle. M.S. Thesis - MIT

NASA Technical Reports Server (NTRS)

Boelitz, Frederick W.

1989-01-01

A new guidance, steering, and control concept is described and evaluated for the Third Phase of an asymmetrical configuration of the Advanced Launch System (ALS). The study also includes the consideration of trajectory shaping issues and trajectory design as well as the development of angular rate, angular acceleration, angle of attack, and dynamic pressure estimators. The Third Phase guidance, steering and control system is based on controlling the acceleration-direction of the vehicle after an initial launch maneuver. Unlike traditional concepts, the alignment of the estimated and commanded acceleration-directions is unimpaired by an add-on load relief. Instead, the acceleration-direction steering-control system features a control override that limits the product of estimated dynamic pressure and estimated angle of attack. When this product is not being limited, control is based exclusively on the commanded acceleration-direction without load relief. During limiting, control is based on nulling the error between the limited angle of attack and the estimated angle of attack. This limiting feature provides full freedom to the acceleration-direction steering and control to shape the trajectory within the limit, and also gives full priority to the limiting of angle of attack when necessary. The flight software concepts were analyzed on the basis of their effects on pitch plane motion.

Flight software operation of the Hubble Space Telescope fine guidance sensor

NASA Technical Reports Server (NTRS)

Rodden, J. J.; Dougherty, H. J.; Cormier, D. J.

1988-01-01

The Hubble Space Telescope (HST) is to carry five major scientific instruments to collect imagery, spectrographic, and photometric astronomical data. The Pointing Control System is designed to achieve pointing accuracies and line of sight jitter levels an order of magnitude less than can be achieved with ground mounted telescopes. This paper describes the operation of the pointing control system flight software in targeting a celestial object in a science instrument aperture and in performing the coordinate transformations necessary for commanding the fine guidance sensor and determining the attitude-error corrections.

United States Air Force Infrastructure Energy Strategic Plan

DTIC Science & Technology

2008-09-01

sulfur diesel ( LSD ) fuel to ultra-low sulfur diesel (ULSD) fuel throughout the Air Force. As bases converted from LSD to ULSD, 820 tracking had to be...direction; develops initiatives, ideas, and poten- tial strategies; and further develops command policy, guidance, and execution strategies. Shaw AFB

Natural Disaster & Crisis Management in School Districts and Community Colleges.

ERIC Educational Resources Information Center

Florida State Dept. of Education, Tallahassee. Office of Educational Facilities.

This document provides school districts and community colleges in Florida with guidance on disaster preparedness planning and management for all types of disasters. Procedures include those for insurance coverage, emergency shelters, command centers and disaster team organization, emergency communications, security, preparation prior to disaster,…

32 CFR 159.4 - Policy.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 1 2012-07-01 2012-07-01 false Policy. 159.4 Section 159.4 National Defense... contingency operation. (b) Geographic Combatant Commanders will provide tailored PSC guidance and procedures... instructions for non-DoD PSCs and their personnel consistent with the standards set forth by the geographic...

32 CFR 159.4 - Policy.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 1 2014-07-01 2014-07-01 false Policy. 159.4 Section 159.4 National Defense... contingency operation. (b) Geographic Combatant Commanders will provide tailored PSC guidance and procedures... instructions for non-DoD PSCs and their personnel consistent with the standards set forth by the geographic...

32 CFR 159.4 - Policy.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 1 2013-07-01 2013-07-01 false Policy. 159.4 Section 159.4 National Defense... contingency operation. (b) Geographic Combatant Commanders will provide tailored PSC guidance and procedures... instructions for non-DoD PSCs and their personnel consistent with the standards set forth by the geographic...

Optimizing Global Force Management for Special Operations Forces

DTIC Science & Technology

2016-12-01

5323 10. SPONSORING / MONITORING AGENCY REPORT NUMBER 11. SUPPLEMENTARY NOTES The views expressed in this thesis are those of the author and do not...plans and apportions forces to combatant commands based on SecDef’s contingency planning guidance (GFM Division 2016) (Figure 1). 3 The image

Neural Network Assisted Inverse Dynamic Guidance for Terminally Constrained Entry Flight

PubMed Central

Chen, Wanchun

2014-01-01

This paper presents a neural network assisted entry guidance law that is designed by applying Bézier approximation. It is shown that a fully constrained approximation of a reference trajectory can be made by using the Bézier curve. Applying this approximation, an inverse dynamic system for an entry flight is solved to generate guidance command. The guidance solution thus gotten ensures terminal constraints for position, flight path, and azimuth angle. In order to ensure terminal velocity constraint, a prediction of the terminal velocity is required, based on which, the approximated Bézier curve is adjusted. An artificial neural network is used for this prediction of the terminal velocity. The method enables faster implementation in achieving fully constrained entry flight. Results from simulations indicate improved performance of the neural network assisted method. The scheme is expected to have prospect for further research on automated onboard control of terminal velocity for both reentry and terminal guidance laws. PMID:24723821

Helicopter Approach Capability Using the Differential Global Positioning System

NASA Technical Reports Server (NTRS)

Kaufmann, David N.

1994-01-01

The results of flight tests to determine the feasibility of using the Global Positioning System (GPS) in the Differential mode (DGPS) to provide high accuracy, precision navigation and guidance for helicopter approaches to landing are presented. The airborne DGPS receiver and associated equipment is installed in a NASA UH-60 Black Hawk helicopter. The ground-based DGPS reference receiver is located at a surveyed test site and is equipped with a real-time VHF data link to transmit correction information to the airborne DGPS receiver. The corrected airborne DGPS information, together with the preset approach geometry, is used to calculate guidance commands which are sent to the aircraft's approach guidance instruments. The use of DGPS derived guidance for helicopter approaches to landing is evaluated by comparing the DGPS data with the laser tracker truth data. The errors indicate that the helicopter position based on DGPS guidance satisfies the International Civil Aviation Organization (ICAO) Category 1 (CAT 1) lateral and vertical navigational accuracy requirements.

Spacecraft intercept guidance using zero effort miss steering

NASA Astrophysics Data System (ADS)

Newman, Brett

The suitability of proportional navigation, or an equivalent zero effort miss formulation, for spacecraft intercepts during midcourse guidance, followed by a ballistic coast to the endgame, is addressed. The problem is formulated in terms of relative motion in a general 3D framework. The proposed guidance law for the commanded thrust vector orientation consists of the sum of two terms: (1) along the line of sight unit direction and (2) along the zero effort miss component perpendicular to the line of sight and proportional to the miss itself and a guidance gain. If the guidance law is to be suitable for longer range targeting applications with significant ballistic coasting after burnout, determination of the zero effort miss must account for the different gravitational accelerations experienced by each vehicle. The proposed miss determination techniques employ approximations for the true differential gravity effect. Theoretical results are applied to a numerical engagement scenario and the resulting performance is evaluated in terms of the miss distances determined from nonlinear simulation.

Apollo experience report: Guidance and control systems. Engineering simulation program

NASA Technical Reports Server (NTRS)

Gilbert, D. W.

1973-01-01

The Apollo Program experience from early 1962 to July 1969 with respect to the engineering-simulation support and the problems encountered is summarized in this report. Engineering simulation in support of the Apollo guidance and control system is discussed in terms of design analysis and verification, certification of hardware in closed-loop operation, verification of hardware/software compatibility, and verification of both software and procedures for each mission. The magnitude, time, and cost of the engineering simulations are described with respect to hardware availability, NASA and contractor facilities (for verification of the command module, the lunar module, and the primary guidance, navigation, and control system), and scheduling and planning considerations. Recommendations are made regarding implementation of similar, large-scale simulations for future programs.

Apollo LM guidance computer software for the final lunar descent.

NASA Technical Reports Server (NTRS)

Eyles, D.

1973-01-01

In all manned lunar landings to date, the lunar module Commander has taken partial manual control of the spacecraft during the final stage of the descent, below roughly 500 ft altitude. This report describes programs developed at the Charles Stark Draper Laboratory, MIT, for use in the LM's guidance computer during the final descent. At this time computational demands on the on-board computer are at a maximum, and particularly close interaction with the crew is necessary. The emphasis is on the design of the computer software rather than on justification of the particular guidance algorithms employed. After the computer and the mission have been introduced, the current configuration of the final landing programs and an advanced version developed experimentally by the author are described.

The design of digital-adaptive controllers for VTOL aircraft

NASA Technical Reports Server (NTRS)

Stengel, R. F.; Broussard, J. R.; Berry, P. W.

1976-01-01

Design procedures for VTOL automatic control systems have been developed and are presented. Using linear-optimal estimation and control techniques as a starting point, digital-adaptive control laws have been designed for the VALT Research Aircraft, a tandem-rotor helicopter which is equipped for fully automatic flight in terminal area operations. These control laws are designed to interface with velocity-command and attitude-command guidance logic, which could be used in short-haul VTOL operations. Developments reported here include new algorithms for designing non-zero-set-point digital regulators, design procedures for rate-limited systems, and algorithms for dynamic control trim setting.

Entry Guidance for the 2011 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; Craig, Lynn E.

2011-01-01

The 2011 Mars Science Laboratory will be the first Mars mission to attempt a guided entry to safely deliver the rover to a touchdown ellipse of 25 km x 20 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range error while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last nine years. Key dispersions driving deploy ellipse and altitude performance are identified. Performance sensitivities including attitude initialization error and the velocity of transition from range control to heading alignment are presented.

Real-time piloted simulation of fully automatic guidance and control for rotorcraft nap-of-the-earth (NOE) flight following planned profiles

NASA Technical Reports Server (NTRS)

Clement, Warren F.; Gorder, Pater J.; Jewell, Wayne F.; Coppenbarger, Richard

1990-01-01

Developing a single-pilot all-weather NOE capability requires fully automatic NOE navigation and flight control. Innovative guidance and control concepts are being investigated to (1) organize the onboard computer-based storage and real-time updating of NOE terrain profiles and obstacles; (2) define a class of automatic anticipative pursuit guidance algorithms to follow the vertical, lateral, and longitudinal guidance commands; (3) automate a decision-making process for unexpected obstacle avoidance; and (4) provide several rapid response maneuvers. Acquired knowledge from the sensed environment is correlated with the recorded environment which is then used to determine an appropriate evasive maneuver if a nonconformity is observed. This research effort has been evaluated in both fixed-base and moving-base real-time piloted simulations thereby evaluating pilot acceptance of the automated concepts, supervisory override, manual operation, and reengagement of the automatic system.

Moving-Base Simulation Evaluation of Control/Display Integration Issues for ASTOVL Aircraft

NASA Technical Reports Server (NTRS)

Franklin, James A.

1997-01-01

A moving-base simulation has been conducted on the Vertical Motion Simulator at Ames Research Center using a model of an advanced, short takeoff and vertical landing (STOVL) lift fan fighter aircraft. This experiment expanded on investigations during previous simulations with this STOVL configuration with the objective of evaluating (1) control law modifications over the low speed flight envelope, (2) integration of the throttle inceptor with flight control laws that provide direct thrust command for conventional flight, vertical and short takeoff, and flightpath or vertical velocity command for transition, hover, and vertical landing, (3) control mode blending for pitch, roll, yaw, and flightpath control during transition from wing-borne to jet-borne flight, and (4) effects of conformal versus nonconformal presentation of flightpath and pursuit guidance symbology on the out-the-window display for low speed STOVL operations. Assessments were made for takeoff, transition, hover, and landing, including precision hover and landing aboard an LPH-type amphibious assault ship in the presence of winds and rough seas. Results yielded Level 1 pilot ratings for the flightpath and vertical velocity command modes for a range of land-based and shipboard operation and were consistent with previous experience with earlier control laws and displays for this STOVL concept. Control mode blending was performed over speed ranges in accord with the pilot's tasks and with the change of the basic aircraft's characteristics between wing-borne and hover flight. Blending of yaw control from heading command in hover to sideslip command in wing-borne flight performed over a broad speed range helped reduce yaw transients during acceleration through the low speed regime. Although the pilots appreciated conformality of flightpath and guidance symbols with the external scene during the approach, increased sensitivity of the symbols for lateral path tracking elevated the pilots' control activity in the presence of turbulence. The pilots preferred the choice of scaling that was originally established during the display development and in-flight evaluations.

42. Upper level, electronic racks, left to rightguidance and control ...

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

42. Upper level, electronic racks, left to right--guidance and control coupler rack, programmer group, status command message processing group, UHF radio - Ellsworth Air Force Base, Delta Flight, Launch Facility, On County Road T512, south of Exit 116 off I-90, Interior, Jackson County, SD

78 FR 76822 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-19

... missiles, containers, spare and repair parts, support equipment, tools and test equipment, publications and... missiles, 7 Fly-to-Buy TOW2A missiles, containers, spare and repair parts, support equipment, tools and... thermal) for the launcher to track and guide the missile in flight. Guidance commands from the launcher...

32 CFR 621.4 - Issues, loans, and donations for scouting.

Code of Federal Regulations, 2011 CFR

2011-07-01

... to commodity command or military deparment property loaned to (Boy Scouts of America). Upon... of America and the Girl Scouts of America. (b) Guidance. (1) Issues are made under the provisions of... Equipment and Providing of Transportation and Other Services to the Boy Scouts of America for World and...

32 CFR 621.4 - Issues, loans, and donations for scouting.

Code of Federal Regulations, 2012 CFR

2012-07-01

... to commodity command or military deparment property loaned to (Boy Scouts of America). Upon... of America and the Girl Scouts of America. (b) Guidance. (1) Issues are made under the provisions of... Equipment and Providing of Transportation and Other Services to the Boy Scouts of America for World and...

32 CFR 621.4 - Issues, loans, and donations for scouting.

Code of Federal Regulations, 2013 CFR

2013-07-01

... to commodity command or military department property loaned to (Boy Scouts of America). Upon... of America and the Girl Scouts of America. (b) Guidance. (1) Issues are made under the provisions of... Equipment and Providing of Transportation and Other Services to the Boy Scouts of America for World and...

32 CFR 621.4 - Issues, loans, and donations for scouting.

Code of Federal Regulations, 2010 CFR

2010-07-01

... to commodity command or military deparment property loaned to (Boy Scouts of America). Upon... of America and the Girl Scouts of America. (b) Guidance. (1) Issues are made under the provisions of... Equipment and Providing of Transportation and Other Services to the Boy Scouts of America for World and...

32 CFR 621.4 - Issues, loans, and donations for scouting.

Code of Federal Regulations, 2014 CFR

2014-07-01

... to commodity command or military department property loaned to (Boy Scouts of America). Upon... of America and the Girl Scouts of America. (b) Guidance. (1) Issues are made under the provisions of... Equipment and Providing of Transportation and Other Services to the Boy Scouts of America for World and...

Installation Management Command: Preparing Civilians for the Army of 2020

DTIC Science & Technology

2013-03-01

fewer people who remain are asked to do more. The White Paper identified the Civilian Work Force Transformation ( CWT ), a program initiative for a...6-22, ADRP 7-0, CWT and the Army Strategic Planning Guidance of 2013. Development should occur in alignment with the leader development pillars and

Mission Management Computer and Sequencing Hardware for RLV-TD HEX-01 Mission

NASA Astrophysics Data System (ADS)

Gupta, Sukrat; Raj, Remya; Mathew, Asha Mary; Koshy, Anna Priya; Paramasivam, R.; Mookiah, T.

2017-12-01

Reusable Launch Vehicle-Technology Demonstrator Hypersonic Experiment (RLV-TD HEX-01) mission posed some unique challenges in the design and development of avionics hardware. This work presents the details of mission critical avionics hardware mainly Mission Management Computer (MMC) and sequencing hardware. The Navigation, Guidance and Control (NGC) chain for RLV-TD is dual redundant with cross-strapped Remote Terminals (RTs) interfaced through MIL-STD-1553B bus. MMC is Bus Controller on the 1553 bus, which does the function of GPS aided navigation, guidance, digital autopilot and sequencing for the RLV-TD launch vehicle in different periodicities (10, 20, 500 ms). Digital autopilot execution in MMC with a periodicity of 10 ms (in ascent phase) is introduced for the first time and successfully demonstrated in the flight. MMC is built around Intel i960 processor and has inbuilt fault tolerance features like ECC for memories. Fault Detection and Isolation schemes are implemented to isolate the failed MMC. The sequencing hardware comprises Stage Processing System (SPS) and Command Execution Module (CEM). SPS is `RT' on the 1553 bus which receives the sequencing and control related commands from MMCs and posts to downstream modules after proper error handling for final execution. SPS is designed as a high reliability system by incorporating various fault tolerance and fault detection features. CEM is a relay based module for sequence command execution.

KSC-2009-3103

NASA Image and Video Library

2009-05-11

CAPE CANAVERAL, Fla. – The mini-convoy is lined up on the Shuttle Landing Facility runway at NASA's Kennedy Space Center in Florida awaiting space shuttle Atlantis' launch on the STS-125 mission to service NASA's Hubble Space Telescope. The convoy is prepared to act should the shuttle need to return to the launch site in the event of an emergency. At left is the Convoy Command Vehicle which is the command post for the convoy commander. Atlantis launched successfully on time at 2:01 p.m. EDT. Atlantis' 11-day flight will include five spacewalks to refurbish and upgrade the telescope with state-of-the-art science instruments that will expand Hubble's capabilities and extend its operational lifespan through at least 2014. The payload includes a Wide Field Camera 3, Fine Guidance Sensor and the Cosmic Origins Spectrograph. Photo credit: NASA/Jack Pfaller

A robust and high precision optimal explicit guidance scheme for solid motor propelled launch vehicles with thrust and drag uncertainty

NASA Astrophysics Data System (ADS)

Maity, Arnab; Padhi, Radhakant; Mallaram, Sanjeev; Mallikarjuna Rao, G.; Manickavasagam, M.

2016-10-01

A new nonlinear optimal and explicit guidance law is presented in this paper for launch vehicles propelled by solid motors. It can ensure very high terminal precision despite not having the exact knowledge of the thrust-time curve apriori. This was motivated from using it for a carrier launch vehicle in a hypersonic mission, which demands an extremely narrow terminal accuracy window for the launch vehicle for successful initiation of operation of the hypersonic vehicle. The proposed explicit guidance scheme, which computes the optimal guidance command online, ensures the required stringent final conditions with high precision at the injection point. A key feature of the proposed guidance law is an innovative extension of the recently developed model predictive static programming guidance with flexible final time. A penalty function approach is also followed to meet the input and output inequality constraints throughout the vehicle trajectory. In this paper, the guidance law has been successfully validated from nonlinear six degree-of-freedom simulation studies by designing an inner-loop autopilot as well, which enhances confidence of its usefulness significantly. In addition to excellent nominal results, the proposed guidance has been found to have good robustness for perturbed cases as well.

Continuous Improvements to East Coast Abort Landings for Space Shuttle Aborts

NASA Technical Reports Server (NTRS)

Butler, Kevin D.

2003-01-01

Improvement initiatives in the areas of guidance, flight control, and mission operations provide increased capability for successful East Coast Abort Landings (ECAL). Automating manual crew procedures in the Space Shuttle's onboard guidance allows faster and more precise commanding of flight control parameters needed for successful ECALs. Automation also provides additional capability in areas not possible with manual control. Operational changes in the mission concept allow for the addition of new landing sites and different ascent trajectories that increase the regions of a successful landing. The larger regions of ECAL capability increase the safety of the crew and Orbiter.

Post-Flight EDL Entry Guidance Performance of the 2011 Mars Science Laboratory Mission

NASA Technical Reports Server (NTRS)

Mendeck, Gavin F.; McGrew, Lynn Craig

2013-01-01

The 2011 Mars Science Laboratory was the first Mars guided entry which safely delivered the rover to a landing within a touchdown ellipse of 19.1 km x 6.9 km. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control the range flown. The guided entry performed as designed without any significant exceptions. The Curiosity rover was delivered about 2.2 km from the expected touchdown. This miss distance is attributed to little time to correct the downrange drift from the final bank reversal and a suspected tailwind during heading alignment. The successful guided entry for the Mars Science Laboratory lays the foundation for future Mars missions to improve upon.

Commanders Guidance and Campaign Planning - The Falkland Islands War 1982

DTIC Science & Technology

Since the end of the Second World War , only one conflict has seen the use of aircraft carriers, submarines, anti-ship missiles, an opposed amphibious...seventy- two hours and conduct an opposed amphibious assault with little training. The fact that they were able to do so is a testament to their

Electromagnetic Radiation Hazards Testing for Non-Ionizing Radio Frequency Transmitting Equipment

DTIC Science & Technology

2012-12-19

Hazards of Electromagnetic Radiation to Ordnance (HERO), Personnel (HERP), and Fuel (HERF) protection guidance for intentional non-ionizing Radio...HERO Hazards of Electromagnetic Radiation to Ordnance HERP Hazards of Electromagnetic Radiation to Personnel IEEE Institute of Electrical and...Systems Command Technical Manual, Electromagnetic Radiation Hazards ( Hazards to Ordnance ), 1 July 2008.

Protection of Shipping: A Forgotten Mission with Many New Challenges

DTIC Science & Technology

2006-10-10

changed the name of the mission (and the NTTP manual) from “Naval Control and Protection of Shipping ( NCAPS ),” to “Naval Cooperation and Guidance for...level. For tactical tasks updated for new NCAGS (vice NCAPS ) doctrine, see Naval Warfare Development Command, Naval Tactical Task List (NTTL) 3.0

78 FR 76825 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-19

... RF missiles, 91 TOW-2A Fly-to-Buy missiles, 49 TOW-2B Fly-to-Buy missiles, containers, spare and... missiles, containers, spare and repair parts, support equipment, tools and test equipment, publications and... launcher to track and guide the missile in flight. Guidance commands from the launcher are provided to the...

Time-Tag Generation Script

NASA Technical Reports Server (NTRS)

Jackson, Dan E.

2010-01-01

Time-Tag Generation Script (TTaGS) is an application program, written in the AWK scripting language, for generating commands for aiming one Ku-band antenna and two S-band antennas for communicating with spacecraft. TTaGS saves between 2 and 4 person-hours per every 24 hours by automating the repetitious process of building between 150 and 180 antenna-control commands. TTaGS reads a text database of communication satellite schedules and a text database of satellite rise and set times and cross-references items in the two databases. It then compares the scheduled start and stop with the geometric rise and set to compute the times to execute antenna control commands. While so doing, TTaGS determines whether to generate commands for guidance, navigation, and control computers to tell them which satellites to track. To help prevent Ku-band irradiation of the Earth, TTaGS accepts input from the user about horizon tolerance and accordingly restricts activation and effects deactivation of the transmitter. TTaGS can be modified easily to enable tracking of additional satellites and for such other tasks as reading Sun-rise/set tables to generate commands to point the solar photovoltaic arrays of the International Space Station at the Sun.

Joint Forward Operating Base Elements of Command and Control

NASA Astrophysics Data System (ADS)

Summers, William C.

2002-01-01

Since the 1986 Goldwater-Nichols Act directed the Chairman of the Joint Chiefs of Staff to develop doctrine for the joint employment of the armed forces, tactics, techniques, and procedures have evolved at different rates depending on the competency. Whereas the command of joint air forces is well prescribed within the structure of the air operations center and its associated leadership, command of air assets at a joint forward operating base lacks guidance. Today, the United States prosecutes an air war over Afghanistan from bases in Uzbekistan, Pakistan, and Afghanistan. Elements of the United States Army, Air Force, and Marines combine at these geographically minute locations, each bringing a certain complement of support and command and control. Evidence from operations during the 1999 air war for Kosovo at Tirana Rinas Airport in Albania suggests that when these service elements meet at the airfield for the first time, there are problems associated with local procedure. At best, time is wasted creating local joint systems to overcome the difficulties. At worst, safety and mission accomplishment are jeopardized. This thesis will address the need to develop doctrine and a jointly integrated organization to support the command and control function at a forward operating base.

Joint Interoperability of Tactical Command and Control Systems (JINTACCS) Technical Interface Design Plan (Test Edition). Appendix C. Glossary

DTIC Science & Technology

1981-03-01

m u z r- Z > H < m ff -< C 2 C) 2 3 r- c is o 1 L_ • o > • en • • • Ŕ O > 00 o 30 n 30 T r- 1> - n o > IDE N T S E LIN E D IT...responsibilities to the Defense Intelligence Agency ( DIA ), the Services, and the unified and specified commands for carrying out that guidance. 3 - JCS...Testing 1-2 1.4 JINTACCS Message Text Eorinats (MTF) and TADIL Messages 1-2 1.4.1 JINTACCS Message Text Formats (MTF) 1- 3 1.4.2 Developmental TADIL

Modern digital flight control system design for VTOL aircraft

NASA Technical Reports Server (NTRS)

Broussard, J. R.; Berry, P. W.; Stengel, R. F.

1979-01-01

Methods for and results from the design and evaluation of a digital flight control system (DFCS) for a CH-47B helicopter are presented. The DFCS employed proportional-integral control logic to provide rapid, precise response to automatic or manual guidance commands while following conventional or spiral-descent approach paths. It contained altitude- and velocity-command modes, and it adapted to varying flight conditions through gain scheduling. Extensive use was made of linear systems analysis techniques. The DFCS was designed, using linear-optimal estimation and control theory, and the effects of gain scheduling are assessed by examination of closed-loop eigenvalues and time responses.

U.S. Army weapon systems human-computer interface style guide. Version 2

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

Avery, L.W.; O`Mara, P.A.; Shepard, A.P.

1997-12-31

A stated goal of the US Army has been the standardization of the human computer interfaces (HCIs) of its system. Some of the tools being used to accomplish this standardization are HCI design guidelines and style guides. Currently, the Army is employing a number of HCI design guidance documents. While these style guides provide good guidance for the command, control, communications, computers, and intelligence (C4I) domain, they do not necessarily represent the more unique requirements of the Army`s real time and near-real time (RT/NRT) weapon systems. The Office of the Director of Information for Command, Control, Communications, and Computers (DISC4),more » in conjunction with the Weapon Systems Technical Architecture Working Group (WSTAWG), recognized this need as part of their activities to revise the Army Technical Architecture (ATA), now termed the Joint Technical Architecture-Army (JTA-A). To address this need, DISC4 tasked the Pacific Northwest National Laboratory (PNNL) to develop an Army weapon systems unique HCI style guide, which resulted in the US Army Weapon Systems Human-Computer Interface (WSHCI) Style Guide Version 1. Based on feedback from the user community, DISC4 further tasked PNNL to revise Version 1 and publish Version 2. The intent was to update some of the research and incorporate some enhancements. This document provides that revision. The purpose of this document is to provide HCI design guidance for the RT/NRT Army system domain across the weapon systems subdomains of ground, aviation, missile, and soldier systems. Each subdomain should customize and extend this guidance by developing their domain-specific style guides, which will be used to guide the development of future systems within their subdomains.« less

MSL EDL Entry Guidance using the Entry Terminal Point Controller

NASA Technical Reports Server (NTRS)

2006-01-01

The Mars Science Laboratory will be the first Mars mission to attempt a guided entry with the objective of safely delivering the entry vehicle to a survivable parachute deploy state within 10 km of the pre-designated landing site. The Entry Terminal Point Controller guidance algorithm is derived from the final phase Apollo Command Module guidance and, like Apollo, modulates the bank angle to control range based on deviations in range, altitude rate, and drag acceleration from a reference trajectory. For application to Mars landers which must make use of the tenuous Martian atmosphere, it is critical to balance the lift of the vehicle to minimize the range while still ensuring a safe deploy altitude. An overview of the process to generate optimized guidance settings is presented, discussing improvements made over the last four years. Performance tradeoffs between ellipse size and deploy altitude will be presented, along with imposed constraints of entry acceleration and heating. Performance sensitivities to the bank reversal deadbands, heading alignment, attitude initialization error, and atmospheric delivery errors are presented. Guidance settings for contingency operations, such as those appropriate for severe dust storm scenarios, are evaluated.

MATE standardization

NASA Astrophysics Data System (ADS)

Farmer, R. E.

1982-11-01

The MATE (Modular Automatic Test Equipment) program was developed to combat the proliferation of unique, expensive ATE within the Air Force. MATE incorporates a standard management approach and a standard architecture designed to implement a cradle-to-grave approach to the acquisition of ATE and to significantly reduce the life cycle cost of weapons systems support. These standards are detailed in the MATE Guides. The MATE Guides assist both the Air Force and Industry in implementing the MATE concept, and provide the necessary tools and guidance required for successful acquisition of ATE. The guides also provide the necessary specifications for industry to build MATE-qualifiable equipment. The MATE architecture provides standards for all key interfaces of an ATE system. The MATE approach to the acquisition and management of ATE has been jointly endorsed by the commanders of Air Force Systems Command and Air Force Logistics Command as the way of doing business in the future.

Apollo 13 MCC - MSC

NASA Image and Video Library

1970-04-14

S70-34986 (14 April 1970) --- A group of six astronauts and two flight controllers monitor the console activity in the Mission Operations Control Room (MOCR) of the Mission Control Center (MCC) during the problem-plagued Apollo 13 lunar landing mission. Seated, left to right, are MOCR Guidance Officer Raymond F. Teague; astronaut Edgar D. Mitchell, Apollo 14 prime crew lunar module pilot; and astronaut Alan B. Shepard Jr., Apollo 14 prime crew commander. Standing, left to right, are scientist-astronaut Anthony W. England; astronaut Joe H. Engle, Apollo 14 backup crew lunar module pilot; astronaut Eugene A. Cernan, Apollo 14 backup crew commander; astronaut Ronald E. Evans, Apollo 14 backup crew command module pilot; and M.P. Frank, a flight controller. When this picture was made, the Apollo 13 moon landing had already been canceled, and the Apollo 13 crew men were in trans-Earth trajectory attempting to bring their damaged spacecraft back home.

Sliding mode control based impact angle control guidance considering the seeker׳s field-of-view constraint.

PubMed

Wang, Xingliang; Zhang, Youan; Wu, Huali

2016-03-01

The problem of impact angle control guidance for a field-of-view constrained missile against non-maneuvering or maneuvering targets is solved by using the sliding mode control theory. The existing impact angle control guidance laws with field-of-view constraint are only applicable against stationary targets and most of them suffer abrupt-jumping of guidance command due to the application of additional guidance mode switching logic. In this paper, the field-of-view constraint is handled without using any additional switching logic. In particular, a novel time-varying sliding surface is first designed to achieve zero miss distance and zero impact angle error without violating the field-of-view constraint during the sliding mode phase. Then a control integral barrier Lyapunov function is used to design the reaching law so that the sliding mode can be reached within finite time and the field-of-view constraint is not violated during the reaching phase as well. A nonlinear extended state observer is constructed to estimate the disturbance caused by unknown target maneuver, and the undesirable chattering is alleviated effectively by using the estimation as a compensation item in the guidance law. The performance of the proposed guidance law is illustrated with simulations. Copyright © 2016 ISA. Published by Elsevier Ltd. All rights reserved.

Development of an integrated spacecraft Guidance, Navigation, & Control subsystem for automated proximity operations

NASA Astrophysics Data System (ADS)

Schulte, Peter Z.; Spencer, David A.

2016-01-01

This paper describes the development and validation process of a highly automated Guidance, Navigation, & Control subsystem for a small satellite on-orbit inspection application, enabling proximity operations without human-in-the-loop interaction. The paper focuses on the integration and testing of Guidance, Navigation, & Control software and the development of decision logic to address the question of how such a system can be effectively implemented for full automation. This process is unique because a multitude of operational scenarios must be considered and a set of complex interactions between subsystem algorithms must be defined to achieve the automation goal. The Prox-1 mission is currently under development within the Space Systems Design Laboratory at the Georgia Institute of Technology. The mission involves the characterization of new small satellite component technologies, deployment of the LightSail 3U CubeSat, entering into a trailing orbit relative to LightSail using ground-in-the-loop commands, and demonstration of automated proximity operations through formation flight and natural motion circumnavigation maneuvers. Operations such as these may be utilized for many scenarios including on-orbit inspection, refueling, repair, construction, reconnaissance, docking, and debris mitigation activities. Prox-1 uses onboard sensors and imaging instruments to perform Guidance, Navigation, & Control operations during on-orbit inspection of LightSail. Navigation filters perform relative orbit determination based on images of the target spacecraft, and guidance algorithms conduct automated maneuver planning. A slew and tracking controller sends attitude actuation commands to a set of control moment gyroscopes, and other controllers manage desaturation, detumble, thruster firing, and target acquisition/recovery. All Guidance, Navigation, & Control algorithms are developed in a MATLAB/Simulink six degree-of-freedom simulation environment and are integrated using decision logic to autonomously determine when actions should be performed. The complexity of this decision logic is the primary challenge of the automated process, and the Stateflow tool in Simulink is used to establish logical relationships and manage data flow between each of the individual hardware and software components. Once the integrated simulation is fully developed in MATLAB/Simulink, the algorithms are autocoded to C/C++ and integrated into flight software. Hardware-in-the-loop testing provides validation of the Guidance, Navigation, & Control subsystem performance.

Effects of a Velocity-Vector Based Command Augmentation System and Synthetic Vision System Terrain Portrayal and Guidance Symbology Concepts on Single-Pilot Performance

NASA Technical Reports Server (NTRS)

Liu, Dahai; Goodrich, Kenneth H.; Peak, Bob

2010-01-01

This study investigated the effects of synthetic vision system (SVS) concepts and advanced flight controls on the performance of pilots flying a light, single-engine general aviation airplane. We evaluated the effects and interactions of two levels of terrain portrayal, guidance symbology, and flight control response type on pilot performance during the conduct of a relatively complex instrument approach procedure. The terrain and guidance presentations were evaluated as elements of an integrated primary flight display system. The approach procedure used in the study included a steeply descending, curved segment as might be encountered in emerging, required navigation performance (RNP) based procedures. Pilot performance measures consisted of flight technical performance, perceived workload, perceived situational awareness and subjective preference. The results revealed that an elevation based generic terrain portrayal significantly improved perceived situation awareness without adversely affecting flight technical performance or workload. Other factors (pilot instrument rating, control response type, and guidance symbology) were not found to significantly affect the performance measures.

Guidance and Control of an Autonomous Soaring UAV

NASA Technical Reports Server (NTRS)

Allen, Michael J.; Lin, Victor

2007-01-01

Thermals caused by convection in the lower atmosphere are commonly used by birds and glider pilots to extend flight duration, increase cross-country speed, improve range, or simply to conserve energy. Uninhabited Aerial Vehicles (UAVs) can also increase performance and reduce energy consumption by exploiting atmospheric convection. An autonomous soaring research project was conducted at the NASA Dryden Flight Research Center to evaluate the concept through flight test of an electric-powered motorglider with a wingspan of 4.27 m (14 ft). The UAV's commercial autopilot software was modified to include outer-loop soaring guidance and control. The aircraft total energy state was used to detect and soar within thermals. Estimated thermal size and position were used to calculate guidance commands for soaring flight. Results from a total of 23 thermal encounters show good performance of the guidance and control algorithms to autonomously detect and exploit thermals. The UAV had an average climb of 172 m (567 ft) during these encounters.

Guidance and Control of an Autonomous Soaring UAV

NASA Technical Reports Server (NTRS)

Allen, Michael J.

2007-01-01

Thermals caused by convection in the lower atmosphere are commonly used by birds and glider pilots to extend flight duration, increase cross-country speed, improve range, or simply to conserve energy. Uninhabited Aerial Vehicles (UAVs) can also increase performance and reduce energy consumption by exploiting atmospheric convection. An autonomous soaring research project was conducted at the NASA Dryden Flight Research Center to evaluate the concept through flight test of an electric-powered motor-glider with a wingspan of 4.27 m (14 ft). The UAV's commercial autopilot software was modified to include outer-loop soaring guidance and control. The aircraft total energy state was used to detect and soar within thermals. Estimated thermal size and position were used to calculate guidance commands for soaring flight. Results from a total of 23 thermal encounters show good performance of the guidance and control algorithms to autonomously detect and exploit thermals. The UAV had an average climb of 172 m (567 ft) during these encounters.

Analytical Design of Terminally Guided Missiles.

DTIC Science & Technology

1980-01-02

Equivalent Dominant Poles and Zeros Using Industrial Specifications," Trans. on Industrial Electronics and Control Instrumentation, Vol. IECI-26, No...The relaxation of the sampling period requirement and the flexibility of our new method facilitate the practical industrial implementation and...with the Guidance and Control Directorate, U.S. Army Missile Command, Redstone Arsenal, Alabama 35809. I. INTRODUCTION Most practical industrial circuits

Prevention and Management of Cold-Weather Injuries

DTIC Science & Technology

2005-04-01

HEADQUARTERS MEDICAL 508* DEPARTMENT OF THE ARMY Washington, DC, 1 April 2005...4-2 42 Hypothermia 4-3 47 Frostbite 4-4 53 Nonfreezing cold injury 4-5 60 Profiles and medical board 4-6 65...INTRODUCTION 1-1. Purpose This bulletin provides guidance to military and civilian health care providers, allied medical personnel, and unit commanders

Saturn Apollo Program

NASA Image and Video Library

2004-04-15

This undated chart provides a description of the Saturn IB and Saturn V's Instrument Unit (IU) and its major components. Designed by NASA at the Marshall Space Flight Center (MSFC), the Instrument Unit, sandwiched between the S-IVB stage and the Apollo spacecraft, served as the Saturn's "nerve center" providing guidance and control, command and sequence of vehicle functions, telemetry, and environmental control.

Small caliber guided projectile

DOEpatents

Jones, James F [Albuquerque, NM; Kast, Brian A [Albuquerque, NM; Kniskern, Marc W [Albuquerque, NM; Rose, Scott E [Albuquerque, NM; Rohrer, Brandon R [Albuquerque, NM; Woods, James W [Albuquerque, NM; Greene, Ronald W [Albuquerque, NM

2010-08-24

A non-spinning projectile that is self-guided to a laser designated target and is configured to be fired from a small caliber smooth bore gun barrel has an optical sensor mounted in the nose of the projectile, a counterbalancing mass portion near the fore end of the projectile and a hollow tapered body mounted aft of the counterbalancing mass. Stabilizing strakes are mounted to and extend outward from the tapered body with control fins located at the aft end of the strakes. Guidance and control electronics and electromagnetic actuators for operating the control fins are located within the tapered body section. Output from the optical sensor is processed by the guidance and control electronics to produce command signals for the electromagnetic actuators. A guidance control algorithm incorporating non-proportional, "bang-bang" control is used to steer the projectile to the target.

Terminal area automatic navigation, guidance, and control research using the Microwave Landing System (MLS). Part 2: RNAV/MLS transition problems for aircraft

NASA Technical Reports Server (NTRS)

Pines, S.

1982-01-01

The problems in navigation and guidance encountered by aircraft in the initial transition period in changing from distance measuring equipment, VORTAC, and barometric instruments to the more precise microwave landing system data type navaids in the terminal area are investigated. The effects of the resulting discontinuities on the estimates of position and velocity for both optimal (Kalman type navigation schemes) and fixed gain (complementary type) navigation filters, and the effects of the errors in cross track, track angle, and altitude on the guidance equation and control commands during the critical landing phase are discussed. A method is presented to remove the discontinuities from the navigation loop and to reconstruct an RNAV path designed to land the aircraft with minimal turns and altitude changes.

High angle of attack flying qualities criteria for longitudinal rate command systems

NASA Technical Reports Server (NTRS)

Wilson, David J.; Citurs, Kevin D.; Davidson, John B.

1994-01-01

This study was designed to investigate flying qualities requirements of alternate pitch command systems for fighter aircraft at high angle of attack. Flying qualities design guidelines have already been developed for angle of attack command systems at 30, 45, and 60 degrees angle of attack, so this research fills a similar need for rate command systems. Flying qualities tasks that require post-stall maneuvering were tested during piloted simulations in the McDonnell Douglas Aerospace Manned Air Combat Simulation facility. A generic fighter aircraft model was used to test angle of attack rate and pitch rate command systems for longitudinal gross acquisition and tracking tasks at high angle of attack. A wide range of longitudinal dynamic variations were tested at 30, 45, and 60 degrees angle of attack. Pilot comments, Cooper-Harper ratings, and pilot induced oscillation ratings were taken from five pilots from NASA, USN, CAF, and McDonnell Douglas Aerospace. This data was used to form longitudinal design guidelines for rate command systems at high angle of attack. These criteria provide control law design guidance for fighter aircraft at high angle of attack, low speed flight conditions. Additional time history analyses were conducted using the longitudinal gross acquisition data to look at potential agility measures of merit and correlate agility usage to flying qualities boundaries. This paper presents an overview of this research.

Fault Tolerant Design Concepts for Highly Integrated Flight Critical Guidance and Control Systems: Conference Proceedings Held at the Guidance and Control Panel Symposium (49th) Held in Toulouse, France on 10-13 October 1989

DTIC Science & Technology

1990-04-01

conception des postes de pilotage et les r6les des pilotes doivent itre difinis avec soin en face des tiches automatis6es ainsi que les pcifications de...from USA and Canada: Commandant M.Mouhamad. FAF AGARD-NATO Executive, GCP Attention : GCP Executive AGARD-OTAN APO New York 09777 7 rue Ancelle F-92200...G.Manfeld 54 UN SYSTEME DE REFERENCES PRIMAIRES DE HAUTE INTEGRITE (A High Integrity Flight Data System) par J.L.Roch et J.Contet 55 ..... 4- K- ’-I

Vision-based guidance for an automated roving vehicle

NASA Technical Reports Server (NTRS)

Griffin, M. D.; Cunningham, R. T.; Eskenazi, R.

1978-01-01

A controller designed to guide an automated vehicle to a specified target without external intervention is described. The intended application is to the requirements of planetary exploration, where substantial autonomy is required because of the prohibitive time lags associated with closed-loop ground control. The guidance algorithm consists of a set of piecewise-linear control laws for velocity and steering commands, and is executable in real time with fixed-point arithmetic. The use of a previously-reported object tracking algorithm for the vision system to provide position feedback data is described. Test results of the control system on a breadboard rover at the Jet Propulsion Laboratory are included.

US Army Weapon Systems Human-Computer Interface (WSHCI) style guide, Version 1

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

Avery, L.W.; O`Mara, P.A.; Shepard, A.P.

1996-09-30

A stated goal of the U.S. Army has been the standardization of the human computer interfaces (HCIS) of its system. Some of the tools being used to accomplish this standardization are HCI design guidelines and style guides. Currently, the Army is employing a number of style guides. While these style guides provide good guidance for the command, control, communications, computers, and intelligence (C4I) domain, they do not necessarily represent the more unique requirements of the Army`s real time and near-real time (RT/NRT) weapon systems. The Office of the Director of Information for Command, Control, Communications, and Computers (DISC4), in conjunctionmore » with the Weapon Systems Technical Architecture Working Group (WSTAWG), recognized this need as part of their activities to revise the Army Technical Architecture (ATA). To address this need, DISC4 tasked the Pacific Northwest National Laboratory (PNNL) to develop an Army weapon systems unique HCI style guide. This document, the U.S. Army Weapon Systems Human-Computer Interface (WSHCI) Style Guide, represents the first version of that style guide. The purpose of this document is to provide HCI design guidance for RT/NRT Army systems across the weapon systems domains of ground, aviation, missile, and soldier systems. Each domain should customize and extend this guidance by developing their domain-specific style guides, which will be used to guide the development of future systems within their domains.« less

NASA OFFICIALS - MISSION OPERATIONS CONROL ROOM (MOCR) - MONITORING PROBLEMS - SKYLAB (SL)-3 COMMAND MODULE (CM) - JSC

NASA Image and Video Library

1973-08-02

S73-31875 (2 Aug. 1973) --- After learning of a problem in the Command/Service Module which was used to transport the Skylab 3 crew to the orbiting Skylab space station cluster, NASA officials held various meetings to discuss the problem. Here, four men monitor the current status of the problem in the Mission Operations Control Room (MOCR) of the Mission Control Center (MCC) at the Johnson Space Center (JSC). From the left are Gary E. Coen, Guidance and Navigation System flight controller; Howard W. Tindall Jr., Director of Flight Operations at JSC; Dr. Christopher C. Kraft Jr., JSC Director; and Sigurd A. Sjoberg, JSC Deputy Director. Photo credit: NASA

Digital controllers for VTOL aircraft

NASA Technical Reports Server (NTRS)

Stengel, R. F.; Broussard, J. R.; Berry, P. W.

1976-01-01

Using linear-optimal estimation and control techniques, digital-adaptive control laws have been designed for a tandem-rotor helicopter which is equipped for fully automatic flight in terminal area operations. Two distinct discrete-time control laws are designed to interface with velocity-command and attitude-command guidance logic, and each incorporates proportional-integral compensation for non-zero-set-point regulation, as well as reduced-order Kalman filters for sensor blending and noise rejection. Adaptation to flight condition is achieved with a novel gain-scheduling method based on correlation and regression analysis. The linear-optimal design approach is found to be a valuable tool in the development of practical multivariable control laws for vehicles which evidence significant coupling and insufficient natural stability.

Advanced Transport Operating System (ATOPS) Flight Management/Flight Controls (FM/FC) software description

NASA Technical Reports Server (NTRS)

Wolverton, David A.; Dickson, Richard W.; Clinedinst, Winston C.; Slominski, Christopher J.

1993-01-01

The flight software developed for the Flight Management/Flight Controls (FM/FC) MicroVAX computer used on the Transport Systems Research Vehicle for Advanced Transport Operating Systems (ATOPS) research is described. The FM/FC software computes navigation position estimates, guidance commands, and those commands issued to the control surfaces to direct the aircraft in flight. Various modes of flight are provided for, ranging from computer assisted manual modes to fully automatic modes including automatic landing. A high-level system overview as well as a description of each software module comprising the system is provided. Digital systems diagrams are included for each major flight control component and selected flight management functions.

Human-Robot Interaction

NASA Technical Reports Server (NTRS)

Rochlis-Zumbado, Jennifer; Sandor, Aniko; Ezer, Neta

2012-01-01

Risk of Inadequate Design of Human and Automation/Robotic Integration (HARI) is a new Human Research Program (HRP) risk. HRI is a research area that seeks to understand the complex relationship among variables that affect the way humans and robots work together to accomplish goals. The DRP addresses three major HRI study areas that will provide appropriate information for navigation guidance to a teleoperator of a robot system, and contribute to the closure of currently identified HRP gaps: (1) Overlays -- Use of overlays for teleoperation to augment the information available on the video feed (2) Camera views -- Type and arrangement of camera views for better task performance and awareness of surroundings (3) Command modalities -- Development of gesture and voice command vocabularies

Department of Defense High Power Laser Program Guidance

DTIC Science & Technology

1994-06-06

Air Force Phillips Laboratory . Through FY94, laboratory operational funding, including civilian... Laboratory Effort and Air Materiel Command Ground-Based Laser (GBL) - Space Control USSPACECOM AF Phillips Laboratory Effort Point Defense Demonstration - Anti...ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING I.GANIZATION Phi 1l i ps Laboratory /LID REPORT numP•R 3550 Aberdeen Avenue, S.E. Kirtland AFB, NM

Transforming Joint Warfighting Capabilities

DTIC Science & Technology

2004-01-01

Certification guidance covers Internet or Web compatibility and the layout to include window size, color, typography , and graphic format. Further require...developed the JMF concept, defined as a package of 20,000 personnel from designated component ready forces. It is aug- mented by supporting commands...trust and confidence in joint warfighting. PACOM established standing com- mand and control relationships for cri- sis response by designating primary

Apollo guidance, navigation and control: Guidance system operations plans for manned LM earth orbital and lunar missions using Program COLOSSUS 3. Section 7: Erasable memory programs

NASA Technical Reports Server (NTRS)

Hamilton, M. H.

1972-01-01

Erasable-memory programs (EMPs) designed for the guidance computers used in the command (CMC) and lunar modules (LGC) are described. CMC programs are designated COLOSSUS 3, and the associated EMPs are identified by a three-digit number beginning with 5. LGC programs are designated LUMINARY 1E, and the associated EMPs are identified, with one exception, by a three-digit number beginning with 1. The exception is EMP 99. The EMPs vary in complexity from a simple flagbit setting to a long and intricate logical structure. They all, however, cause the computer to behave in a way not intended in the original design of the programs; they accomplish this off-nominal behavior by some alteration of erasable memory to interface with existing fixed-memory programs to effect a desired result.

Entry Guidance for the Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Lu, Ping

1999-01-01

The X-33 Advanced Technology Demonstrator is a half-scale prototype developed to test the key technologies needed for a full-scale single-stage reusable launch vehicle (RLV). The X-33 is a suborbital vehicle that will be launched vertically, and land horizontally. The goals of this research were to develop an alternate entry guidance scheme for the X-33 in parallel to the actual X-33 entry guidance algorithms, provide comparative and complementary study, and identify potential new ways to improve entry guidance performance. Toward these goals, the nominal entry trajectory is defined by a piecewise linear drag-acceleration-versus-energy profile, which is in turn obtained by the solution of a semi-analytical parameter optimization problem. The closed-loop guidance is accomplished by tracking the nominal drag profile with primarily bank-angle modulation on-board. The bank-angle is commanded by a single full-envelope nonlinear trajectory control law. Near the end of the entry flight, the guidance logic is switched to heading control in order to meet strict conditions at the terminal area energy management interface. Two methods, one on ground-track control and the other on heading control, were proposed and examined for this phase of entry guidance where lateral control is emphasized. Trajectory dispersion studies were performed to evaluate the effectiveness of the entry guidance algorithms against a number of uncertainties including those in propulsion system, atmospheric properties, winds, aerodynamics, and propellant loading. Finally, a new trajectory-regulation method is introduced at the end as a promising precision entry guidance method. The guidance principle is very different and preliminary application in X-33 entry guidance simulation showed high precision that is difficult to achieve by existing methods.

Exoatmospheric intercepts using zero effort miss steering for midcourse guidance

NASA Astrophysics Data System (ADS)

Newman, Brett

The suitability of proportional navigation, or an equivalent zero effort miss formulation, for exatmospheric intercepts during midcourse guidance, followed by a ballistic coast to the endgame, is addressed. The problem is formulated in terms of relative motion in a general, three dimensional framework. The proposed guidance law for the commanded thrust vector orientation consists of the sum of two terms: (1) along the line of sight unit direction and (2) along the zero effort miss component perpendicular to the line of sight and proportional to the miss itself and a guidance gain. If the guidance law is to be suitable for longer range targeting applications with significant ballistic coasting after burnout, determination of the zero effort miss must account for the different gravitational accelerations experienced by each vehicle. The proposed miss determination techniques employ approximations for the true differential gravity effect and thus, are less accurate than a direct numerical propagation of the governing equations, but more accurate than a baseline determination, which assumes equal accelerations for both vehicles. Approximations considered are constant, linear, quadratic, and linearized inverse square models. Theoretical results are applied to a numerical engagement scenario and the resulting performance is evaluated in terms of the miss distances determined from nonlinear simulation.

Improved Lunar Lander Handling Qualities Through Control Response Type and Display Enhancements

NASA Technical Reports Server (NTRS)

Mueller, Eric Richard; Bilimoria, Karl D.; Frost, Chad Ritchie

2010-01-01

A piloted simulation that studied the handling qualities for a precision lunar landing task from final approach to touchdown is presented. A vehicle model based on NASA's Altair Lunar Lander was used to explore the design space around the nominal vehicle configuration to determine which combination of factors provides satisfactory pilot-vehicle performance and workload; details of the control and propulsion systems not available for that vehicle were derived from Apollo Lunar Module data. The experiment was conducted on a large motion base simulator. Eight Space Shuttle and Apollo pilot astronauts and three NASA test pilots served as evaluation pilots, providing Cooper-Harper ratings, Task Load Index ratings and qualitative comments. Each pilot flew seven combinations of control response types and three sets of displays, including two varieties of guidance and a nonguided approach. The response types included Rate Command with Attitude Hold, which was used in the original Apollo Moon landings, a Velocity Increment Command response type designed for up-and-away flight, three response types designed specifically for the vertical descent portion of the trajectory, and combinations of these. It was found that Velocity Increment Command significantly improved handling qualities when compared with the baseline Apollo design, receiving predominantly Level 1 ratings. This response type could be flown with or without explicit guidance cues, something that was very difficult with the baseline design, and resulted in approximately equivalent touchdown accuracies and propellant burn as the baseline response type. The response types designed to be used exclusively in the vertical descent portion of the trajectory did not improve handling qualities.

Resourcing interventions enhance psychology support capabilities in special operations forces.

PubMed

Myatt, Craig A; Auzenne, J W

2012-01-01

This study provides an examination of approaches to United States Government (USG) resourcing interventions on a national scale that enhance psychology support capabilities in the Special Operations Forces (SOF) community. A review of Congressional legislation and resourcing trends in the form of authorizations and appropriations since 2006 demonstrates how Congress supported enhanced psychology support capabilities throughout the Armed Forces and in SOF supporting innovative command interests that address adverse affects of operations tempo behavioral effects (OTBE). The formulation of meaningful metrics to address SOF specific command interests led to a personnel tempo (PERSTEMPO) analysis in response to findings compiled by the Preservation of the Force and Families (POTFF) Task Force. The review of PERSTEMPO data at subordinate command and unit levels enhances the capability of SOF leaders to develop policy and guidance on training and operational planning that mitigates OTBE and maximizes resourcing authorizations. A major challenge faced by the DoD is in providing behavioral healthcare that meets public and legislative demands while proving suitable and sustainable at all levels of military operations: strategic, operational, and tactical. Current legislative authorizations offer a mechanism of command advocacy for resourced multi-functional program development that enhances psychology support capabilities while reinforcing SOF readiness and performance. 2012.

Analysis of a flare-director concept for an externally blown flap STOL aircraft

NASA Technical Reports Server (NTRS)

Middleton, D. B.

1974-01-01

A flare-director concept involving a thrust-required flare-guidance equation was developed and tested on a moving-base simulator. The equation gives a signal to command thrust as a linear function of the errors between the variables thrust, altitude, and altitude rate and corresponding values on a desired reference flare trajectory. During the simulator landing tests this signal drove either the horizontal command bar of the aircraft's flight director or a thrust-command dot on a head-up virtual-image display of a flare director. It was also used as the input to a simple autoflare system. An externally blown flap STOL (short take-off and landing) aircraft (with considerable stability and control augmentation) was modeled for the landing tests. The pilots considered the flare director a valuable guide for executing a proper flare-thrust program under instrument-landing conditions, but were reluctant to make any use of the head-up display when they were performing the landings visually.

Reusable Launch Vehicle Attitude Control Using a Time-Varying Sliding Mode Control Technique

NASA Technical Reports Server (NTRS)

Shtessel, Yuri B.; Zhu, J. Jim; Daniels, Dan; Jackson, Scott (Technical Monitor)

2002-01-01

In this paper we present a time-varying sliding mode control (TVSMC) technique for reusable launch vehicle (RLV) attitude control in ascent and entry flight phases. In ascent flight the guidance commands Euler roll, pitch and yaw angles, and in entry flight it commands the aerodynamic angles of bank, attack and sideslip. The controller employs a body rate inner loop and the attitude outer loop, which are separated in time-scale by the singular perturbation principle. The novelty of the TVSMC is that both the sliding surface and the boundary layer dynamics can be varied in real time using the PD-eigenvalue assignment technique. This salient feature is used to cope with control command saturation and integrator windup in the presence of severe disturbance or control effector failure, which enhances the robustness and fault tolerance of the controller. The TV-SMC ascent and descent designs are currently being tested with high fidelity, 6-DOF dispersion simulations. The test results will be presented in the final version of this paper.

Cognitive load of navigating without vision when guided by virtual sound versus spatial language.

PubMed

Klatzky, Roberta L; Marston, James R; Giudice, Nicholas A; Golledge, Reginald G; Loomis, Jack M

2006-12-01

A vibrotactile N-back task was used to generate cognitive load while participants were guided along virtual paths without vision. As participants stepped in place, they moved along a virtual path of linear segments. Information was provided en route about the direction of the next turning point, by spatial language ("left," "right," or "straight") or virtual sound (i.e., the perceived azimuth of the sound indicated the target direction). The authors hypothesized that virtual sound, being processed at direct perceptual levels, would have lower load than even simple language commands, which require cognitive mediation. As predicted, whereas the guidance modes did not differ significantly in the no-load condition, participants showed shorter distance traveled and less time to complete a path when performing the N-back task while navigating with virtual sound as guidance. Virtual sound also produced better N-back performance than spatial language. By indicating the superiority of virtual sound for guidance when cognitive load is present, as is characteristic of everyday navigation, these results have implications for guidance systems for the visually impaired and others.

Reliability history of the Apollo guidance computer

NASA Technical Reports Server (NTRS)

Hall, E. C.

1972-01-01

The Apollo guidance computer was designed to provide the computation necessary for guidance, navigation and control of the command module and the lunar landing module of the Apollo spacecraft. The computer was designed using the technology of the early 1960's and the production was completed by 1969. During the development, production, and operational phase of the program, the computer has accumulated a very interesting history which is valuable for evaluating the technology, production methods, system integration, and the reliability of the hardware. The operational experience in the Apollo guidance systems includes 17 computers which flew missions and another 26 flight type computers which are still in various phases of prelaunch activity including storage, system checkout, prelaunch spacecraft checkout, etc. These computers were manufactured and maintained under very strict quality control procedures with requirements for reporting and analyzing all indications of failure. Probably no other computer or electronic equipment with equivalent complexity has been as well documented and monitored. Since it has demonstrated a unique reliability history, it is important to evaluate the techniques and methods which have contributed to the high reliability of this computer.

Prox-1 Automated Proximity Operations

DTIC Science & Technology

2016-01-13

K.J., and Veto, M., "Automated Trajectory Control for On-Orbit Inspection in the Prox-1 Mission," Journal of Spacecraft and Rockets , in review...the operability of all commands needed for the minimum mission. A Simulated Communications Test was performed that demonstrated long-range uplink...Guidance, Navigation and Control subsystem 6 DOF simulation , and delivered for flight coding. Validation of the system’s capability to meet full

From National to Theater: Developing Strategy

DTIC Science & Technology

2013-01-01

operational planning as it guides the development of the Theater Campaign Plan ( TCP ). Theater strategy, and the TCP that operationalizes it, should offer...doctrine or other guidance on developing it. Perhaps this is a contributing factor in Charles Bouchat’s observation that “No two combatant commands...approach to TCPs and country-level planning that considers ongoing security cooperation efforts, current operations, the Phase 0 component of con

Turning Battlefield Victories into Strategic Success

DTIC Science & Technology

2008-03-17

the Secretary of Defense (OSD) that promotes “speed, jointness, knowledge, and precision”.12 Of great concern is that both models clearly lack an...with Commanders on the ground until January 20, 2003.15 Furthermore, inadequate funding, a lack of personnel, and no clear mission guidance hindered...2-4. 42 Condoleezza Rice, Henrietta H. Fore, Transformational Diplomacy, Strategic Plan Fiscal Years 2007-2012, (Washington D.C.: Department of

Countering Air and Missile Threats

DTIC Science & Technology

2012-03-23

information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources , gathering... apportionment guidance by the JFC. Functional component commands serve to ease the burden on the theater and joint task force staffs, free the JFC to focus...action (COA) to attain the desired objectives. Counterair requires a combination of OCA and DCA operations based on the JFC’s air apportionment

Suicide Postvention in the Department of Defense: Evidence, Policies and Procedures, and Perspectives of Loss Survivors

DTIC Science & Technology

2015-01-01

Primarily based on expert opinions, the evidence provides guidance to medical examiners in making cause-of-death determinations, determining which core...military suicides derive from military criminal investigations, autopsies con- ducted by the Armed Forces Medical Examiner System, and command...Their contributions were invaluable and will inform future response efforts. xix Abbreviations AFMES Armed Forces Medical Examiner System ATSM

A manned maneuvering unit proximity operations planning and flight guidance display and control system

NASA Technical Reports Server (NTRS)

Gershzohn, Gary R.; Sirko, Robert J.; Zimmerman, K.; Jones, A. D.

1990-01-01

This task concerns the design, development, testing, and evaluation of a new proximity operations planning and flight guidance display and control system for manned space operations. A forecast, derivative manned maneuvering unit (MMU) was identified as a candidate for the application of a color, highway-in-the-sky display format for the presentation of flight guidance information. A silicon graphics 4D/20-based simulation is being developed to design and test display formats and operations concepts. The simulation includes the following: (1) real-time color graphics generation to provide realistic, dynamic flight guidance displays and control characteristics; (2) real-time graphics generation of spacecraft trajectories; (3) MMU flight dynamics and control characteristics; (4) control algorithms for rotational and translational hand controllers; (5) orbital mechanics effects for rendezvous and chase spacecraft; (6) inclusion of appropriate navigation aids; and (7) measurement of subject performance. The flight planning system under development provides for: (1) selection of appropriate operational modes, including minimum cost, optimum cost, minimum time, and specified ETA; (2) automatic calculation of rendezvous trajectories, en route times, and fuel requirements; (3) and provisions for manual override. Man/machine function allocations in planning and en route flight segments are being evaluated. Planning and en route data are presented on one screen composed of two windows: (1) a map display presenting a view perpendicular to the orbital plane, depicting flight planning trajectory and time data attitude display presenting attitude and course data for use en route; and (2) an attitude display presenting local vertical-local horizontal attitude data superimposed on a highway-in-the-sky or flight channel representation of the flight planned course. Both display formats are presented while the MMU is en route. In addition to these displays, several original display elements are being developed, including a 3DOF flight detector for attitude commanding, a different flight detector for translation commands, and a pictorial representation of velocity deviations.

Literature review on medical incident command.

PubMed

Rimstad, Rune; Braut, Geir Sverre

2015-04-01

It is not known what constitutes the optimal emergency management system, nor is there a consensus on how effectiveness and efficiency in emergency response should be measured or evaluated. Literature on the role and tasks of commanders in the prehospital emergency services in the setting of mass-casualty incidents has not been summarized and published. This comprehensive literature review addresses some of the needs for future research in emergency management through three research questions: (1) What are the basic assumptions underlying incident command systems (ICSs)? (2) What are the tasks of ambulance and medical commanders in the field? And (3) How can field commanders' performances be measured and assessed? A systematic literature search in MEDLINE, PubMed, PsycINFO, Embase, Cochrane Central Register of Controlled Trials, Cochrane Library, ISI Web of Science, Scopus, International Security & Counter Terrorism Reference Center, Current Controlled Trials, and PROSPERO covering January 1, 1990 through March 1, 2014 was conducted. Reference lists of included literature were hand searched. Included papers were analyzed using Framework synthesis. The literature search identified 6,049 unique records, of which, 76 articles and books where included in qualitative synthesis. Most ICSs are described commonly as hierarchical, bureaucratic, and based on military principles. These assumptions are contested strongly, as is the applicability of such systems. Linking of the chains of command in cooperating agencies is a basic difficulty. Incident command systems are flexible in the sense that the organization may be expanded as needed. Commanders may command by direction, by planning, or by influence. Commanders' tasks may be summarized as: conducting scene assessment, developing an action plan, distributing resources, monitoring operations, and making decisions. There is considerable variation between authors in nomenclature and what tasks are included or highlighted. There are no widely acknowledged measurement tools of commanders' performances, though several performance indicators have been suggested. The competence and experience of the commanders, upon which an efficient ICS has to rely, cannot be compensated significantly by plans and procedures, or even by guidance from superior organizational elements such as coordination centers. This study finds that neither a certain system or structure, or a specific set of plans, are better than others, nor can it conclude what system prerequisites are necessary or sufficient for efficient incident management. Commanders need to be sure about their authority, responsibility, and the functional demands posed upon them.

Development of a digital automatic control law for steep glideslope capture and flare

NASA Technical Reports Server (NTRS)

Halyo, N.

1977-01-01

A longitudinal digital guidance and control law for steep glideslopes using MLS (Microwave Landing System) data is developed for CTOL aircraft using modern estimation and control techniques. The control law covers the final approach phases of glideslope capture, glideslope tracking, and flare to touchdown for automatic landings under adverse weather conditions. The control law uses a constant gain Kalman filter to process MLS and body-mounted accelerometer data to form estimates of flight path errors and wind velocities including wind shear. The flight path error estimates and wind estimates are used for feedback in generating control surface commands. Results of a digital simulation of the aircraft dynamics and the guidance and control law are presented for various wind conditions.

Study of Synthetic Vision Systems (SVS) and Velocity-vector Based Command Augmentation System (V-CAS) on Pilot Performance

NASA Technical Reports Server (NTRS)

Liu, Dahai; Goodrich, Ken; Peak, Bob

2006-01-01

This study investigated the effects of synthetic vision system (SVS) concepts and advanced flight controls on single pilot performance (SPP). Specifically, we evaluated the benefits and interactions of two levels of terrain portrayal, guidance symbology, and control-system response type on SPP in the context of lower-landing minima (LLM) approaches. Performance measures consisted of flight technical error (FTE) and pilot perceived workload. In this study, pilot rating, control type, and guidance symbology were not found to significantly affect FTE or workload. It is likely that transfer from prior experience, limited scope of the evaluation task, specific implementation limitations, and limited sample size were major factors in obtaining these results.

Building the Plane Inflight: Observations from Case Studies in Wartime Flight Training for Partner Nations

DTIC Science & Technology

2016-05-26

guidance on how to build an effective SC program. Whether used as pre-decisional guides or ex post facto evaluation tools, they fall short of...Building the Plane Inflight: Observations from Case Studies in Wartime Flight Training for Partner...Nations A Monograph by Major Timothy J. Day United States Air Force School of Advanced Military Studies United States Army Command and General

Budgeting for National Defense Acquisition: Assessing System Linkage and the Impact of Transformation

DTIC Science & Technology

2005-06-30

which develops the Strategic Planning Guidance (SPG). The SPC is led by SECDEF and made up of the Senior Leaders Review Group (SLRG) and the...ASSESSING SYSTEM LINKAGE AND THE IMPACT OF TRANSFORMATION 30 JUNE 2005 by Lawrence R. Jones, Professor, Wagner Chair Graduate School of Business ...Public Policy Jerry McCaffery, Professor Graduate School of Business & Public Policy Kory L. Fierstine, Commander, United States Navy

Naval Sea Systems Command Did Not Properly Apply Guidance Regarding Contracting Officers Representatives

DTIC Science & Technology

2016-03-18

Contract _______________________________ 10 PCO and ACO Did Not Ensure Appointment of COR ________________________________________ 12 NAVSEA Did Not Properly...sample was selected, NAVSEA had issued work for 36 availabilities on the contract—obligating $102.5M. { The procuring contracting officer ( PCO ) at...Responsibilities,” Section 1.602-2, “Responsibilities,” May 29, 2014. 3 The contracting officers for the contract reviewed are the PCO at NAVSEA

Theater Land Attack Cruise Missile Defense: Guarding the Back Door

DTIC Science & Technology

1999-06-01

employ radio command, laser, anti- radiation homing, or electro-optical guidance systems. TASMs will benefit from the same technological developments...mile-range Al-Husayn missile within range of all major Israeli cities, and its nuclear facilities in the Negev desert. The existence of these sites...solutions (“engage on remote”), or simply launch missiles without radiating , and allow the AFCR to guide the missiles to the target

An Alignment Analysis of the U.S. Navy Supply Corps Officers Career Guidance with Naval Supply Systems Commands Strategic Publications

DTIC Science & Technology

2014-06-01

financial processes…, 7) Develop strategies…to identify solutions to improve quality -of-life services …, 8) Partnering with internal and external...organizational communications and individual development, advertising what the organization viewed as important for career progress at that time. Other military...while leadership and reward/recognition each fall under the cognitive level and emotional level, respectively. Employee communication , development

Knowledge-based processing for aircraft flight control

NASA Technical Reports Server (NTRS)

Painter, John H.

1991-01-01

The purpose is to develop algorithms and architectures for embedding artificial intelligence in aircraft guidance and control systems. With the approach adopted, AI-computing is used to create an outer guidance loop for driving the usual aircraft autopilot. That is, a symbolic processor monitors the operation and performance of the aircraft. Then, based on rules and other stored knowledge, commands are automatically formulated for driving the autopilot so as to accomplish desired flight operations. The focus is on developing a software system which can respond to linguistic instructions, input in a standard format, so as to formulate a sequence of simple commands to the autopilot. The instructions might be a fairly complex flight clearance, input either manually or by data-link. Emphasis is on a software system which responds much like a pilot would, employing not only precise computations, but, also, knowledge which is less precise, but more like common-sense. The approach is based on prior work to develop a generic 'shell' architecture for an AI-processor, which may be tailored to many applications by describing the application in appropriate processor data bases (libraries). Such descriptions include numerical models of the aircraft and flight control system, as well as symbolic (linguistic) descriptions of flight operations, rules, and tactics.

Handling Qualities of a Capsule Spacecraft During Atmospheric Entry

NASA Technical Reports Server (NTRS)

Bilimoria, Karl D.; Mueller, Eric R.

2010-01-01

A piloted simulation was conducted to study handling qualities for capsule spacecraft entering the Earth s atmosphere. Eight evaluation pilots, including six pilot astronauts, provided Cooper-Harper ratings, workload ratings, and qualitative comments. The simulation began after descending through the atmospheric entry interface point and continued until the drogue parachutes deployed. There were two categories of piloting tasks, both of which required bank angle control. In one task category, the pilot followed a closed-loop bank angle command computed by the backup guidance system to manage g-loads during entry. In the other task category, the pilot used intuitive rules to determine the desired bank angle independently, based on an open-loop schedule of vertical speed, Mach, and total energy specified at several range-to-target gates along the entry trajectory. Pilots were able to accurately track the bank angle guidance commands and steered the capsule toward the recovery site with essentially the same range error as the benchmark autopilot trajectory albeit with substantially higher propellant usage, and the handling qualities for this task were satisfactory. Another key result was that the complex piloting task of atmospheric entry could be performed satisfactorily, even in the presence of large dispersions, by controlling bank angle to follow a simple open-loop schedule.

The impact of command signal power distribution, processing delays, and speed scaling on neurally-controlled devices.

PubMed

Marathe, A R; Taylor, D M

2015-08-01

Decoding algorithms for brain-machine interfacing (BMI) are typically only optimized to reduce the magnitude of decoding errors. Our goal was to systematically quantify how four characteristics of BMI command signals impact closed-loop performance: (1) error magnitude, (2) distribution of different frequency components in the decoding errors, (3) processing delays, and (4) command gain. To systematically evaluate these different command features and their interactions, we used a closed-loop BMI simulator where human subjects used their own wrist movements to command the motion of a cursor to targets on a computer screen. Random noise with three different power distributions and four different relative magnitudes was added to the ongoing cursor motion in real time to simulate imperfect decoding. These error characteristics were tested with four different visual feedback delays and two velocity gains. Participants had significantly more trouble correcting for errors with a larger proportion of low-frequency, slow-time-varying components than they did with jittery, higher-frequency errors, even when the error magnitudes were equivalent. When errors were present, a movement delay often increased the time needed to complete the movement by an order of magnitude more than the delay itself. Scaling down the overall speed of the velocity command can actually speed up target acquisition time when low-frequency errors and delays are present. This study is the first to systematically evaluate how the combination of these four key command signal features (including the relatively-unexplored error power distribution) and their interactions impact closed-loop performance independent of any specific decoding method. The equations we derive relating closed-loop movement performance to these command characteristics can provide guidance on how best to balance these different factors when designing BMI systems. The equations reported here also provide an efficient way to compare a diverse range of decoding options offline.

The impact of command signal power distribution, processing delays, and speed scaling on neurally-controlled devices

NASA Astrophysics Data System (ADS)

Marathe, A. R.; Taylor, D. M.

2015-08-01

Objective. Decoding algorithms for brain-machine interfacing (BMI) are typically only optimized to reduce the magnitude of decoding errors. Our goal was to systematically quantify how four characteristics of BMI command signals impact closed-loop performance: (1) error magnitude, (2) distribution of different frequency components in the decoding errors, (3) processing delays, and (4) command gain. Approach. To systematically evaluate these different command features and their interactions, we used a closed-loop BMI simulator where human subjects used their own wrist movements to command the motion of a cursor to targets on a computer screen. Random noise with three different power distributions and four different relative magnitudes was added to the ongoing cursor motion in real time to simulate imperfect decoding. These error characteristics were tested with four different visual feedback delays and two velocity gains. Main results. Participants had significantly more trouble correcting for errors with a larger proportion of low-frequency, slow-time-varying components than they did with jittery, higher-frequency errors, even when the error magnitudes were equivalent. When errors were present, a movement delay often increased the time needed to complete the movement by an order of magnitude more than the delay itself. Scaling down the overall speed of the velocity command can actually speed up target acquisition time when low-frequency errors and delays are present. Significance. This study is the first to systematically evaluate how the combination of these four key command signal features (including the relatively-unexplored error power distribution) and their interactions impact closed-loop performance independent of any specific decoding method. The equations we derive relating closed-loop movement performance to these command characteristics can provide guidance on how best to balance these different factors when designing BMI systems. The equations reported here also provide an efficient way to compare a diverse range of decoding options offline.

Back-stepping active disturbance rejection control design for integrated missile guidance and control system via reduced-order ESO.

PubMed

Xingling, Shao; Honglun, Wang

2015-07-01

This paper proposes a novel composite integrated guidance and control (IGC) law for missile intercepting against unknown maneuvering target with multiple uncertainties and control constraint. First, by using back-stepping technique, the proposed IGC law design is separated into guidance loop and control loop. The unknown target maneuvers and variations of aerodynamics parameters in guidance and control loop are viewed as uncertainties, which are estimated and compensated by designed model-assisted reduced-order extended state observer (ESO). Second, based on the principle of active disturbance rejection control (ADRC), enhanced feedback linearization (FL) based control law is implemented for the IGC model using the estimates generated by reduced-order ESO. In addition, performance analysis and comparisons between ESO and reduced-order ESO are examined. Nonlinear tracking differentiator is employed to construct the derivative of virtual control command in the control loop. Third, the closed-loop stability for the considered system is established. Finally, the effectiveness of the proposed IGC law in enhanced interception performance such as smooth interception course, improved robustness against multiple uncertainties as well as reduced control consumption during initial phase are demonstrated through simulations. Copyright © 2015 ISA. Published by Elsevier Ltd. All rights reserved.

Energy management of three-dimensional minimum-time intercept. [for aircraft flight optimization

NASA Technical Reports Server (NTRS)

Kelley, H. J.; Cliff, E. M.; Visser, H. G.

1985-01-01

A real-time computer algorithm to control and optimize aircraft flight profiles is described and applied to a three-dimensional minimum-time intercept mission. The proposed scheme has roots in two well known techniques: singular perturbations and neighboring-optimal guidance. Use of singular-perturbation ideas is made in terms of the assumed trajectory-family structure. A heading/energy family of prestored point-mass-model state-Euler solutions is used as the baseline in this scheme. The next step is to generate a near-optimal guidance law that will transfer the aircraft to the vicinity of this reference family. The control commands fed to the autopilot (bank angle and load factor) consist of the reference controls plus correction terms which are linear combinations of the altitude and path-angle deviations from reference values, weighted by a set of precalculated gains. In this respect the proposed scheme resembles neighboring-optimal guidance. However, in contrast to the neighboring-optimal guidance scheme, the reference control and state variables as well as the feedback gains are stored as functions of energy and heading in the present approach. Some numerical results comparing open-loop optimal and approximate feedback solutions are presented.

Orion Capsule Handling Qualities for Atmospheric Entry

NASA Technical Reports Server (NTRS)

Tigges, Michael A.; Bihari, Brian D.; Stephens, John-Paul; Vos, Gordon A.; Bilimoria, Karl D.; Mueller, Eric R.; Law, Howard G.; Johnson, Wyatt; Bailey, Randall E.; Jackson, Bruce

2011-01-01

Two piloted simulations were conducted at NASA's Johnson Space Center using the Cooper-Harper scale to study the handling qualities of the Orion Command Module capsule during atmospheric entry flight. The simulations were conducted using high fidelity 6-DOF simulators for Lunar Return Skip Entry and International Space Station Return Direct Entry flight using bank angle steering commands generated by either the Primary (PredGuid) or Backup (PLM) guidance algorithms. For both evaluations, manual control of bank angle began after descending through Entry Interface into the atmosphere until drogue chutes deployment. Pilots were able to use defined bank management and reversal criteria to accurately track the bank angle commands, and stay within flight performance metrics of landing accuracy, g-loads, and propellant consumption, suggesting that the pilotability of Orion under manual control is both achievable and provides adequate trajectory performance with acceptable levels of pilot effort. Another significant result of these analyses is the applicability of flying a complex entry task under high speed entry flight conditions relevant to the next generation Multi Purpose Crew Vehicle return from Mars and Near Earth Objects.

Flight test experience and controlled impact of a remotely piloted jet transport aircraft

NASA Technical Reports Server (NTRS)

Horton, Timothy W.; Kempel, Robert W.

1988-01-01

The Dryden Flight Research Center Facility of NASA Ames Research Center (Ames-Dryden) and the FAA conducted the controlled impact demonstration (CID) program using a large, four-engine, remotely piloted jet transport airplane. Closed-loop primary flight was controlled through the existing onboard PB-20D autopilot which had been modified for the CID program. Uplink commands were sent from a ground-based cockpit and digital computer in conjunction with an up-down telemetry link. These uplink commands were received aboard the airplane and transferred through uplink interface systems to the modified PB-20D autopilot. Both proportional and discrete commands were produced by the ground system. Prior to flight tests, extensive simulation was conducted during the development of ground-based digital control laws. The control laws included primary control, secondary control, and racetrack and final approach guidance. Extensive ground checks were performed on all remotely piloted systems; however, piloted flight tests were the primary method and validation of control law concepts developed from simulation. The design, development, and flight testing of control laws and systems required to accomplish the remotely piloted mission are discussed.

Systems Engineering Approach To Ground Combat Vehicle Survivability In Urban Operations

DTIC Science & Technology

2016-09-01

extinguishing system (AFES), which uses fire wires to detect the presence of fires. The detection of fire automatically triggers the activation of the fire...corresponding wires and connection points also means that it can be more difficult for engineers to integrate distributed architecture systems onto...command signals to the missile via wires trailing behind the missile or via RF signals. See Figure 29 for an illustration of CLOS guidance. Since CLOS

Flaw Detection and Evaluation of Composite Cylinders Using Laser Speckle Interferometry and Holography

DTIC Science & Technology

1979-11-23

Entered) ACKNOWLEDGMENTS The author hereby expresses his appreciation to Mr. J. A. Schaeffel Jr. for his guidance on interferometry and the computer...were collected by an automated laser speckle interferometry displacement contour analyzer developed by John A. Schaeffel , Jr. [3]. The new method of 10...Fringe Patterns, US Army Missile Command, Redstone Arsenal, Alabama, Technical Report RL-76-18, 20 April 1976. 3. Schaeffel , J. A., Automated Laser

Proceedings of the Meeting of the Coordinating Group on Modern Control Theory (3rd) (20-21 October 1981) US Army Missile Command, Redstone Arsenal, AL. Part I

DTIC Science & Technology

1981-11-01

Systems Direc- "torate, Gen. Thomas J. Rodman Laboratory, Rock Island, IL, June 1976. 93 Next page is blank. _ _l7 - " - ON DESIGNING ROBUST PREDICTORS...34Optimal Terminal Guidance with Constraints at Final Time" Journal of Spacecraft and Rockets, Vol 14, No. 6, June 77, pp 381-383 [7] Adler , F. P. "Missile

A smart telerobotic system driven by monocular vision

NASA Technical Reports Server (NTRS)

Defigueiredo, R. J. P.; Maccato, A.; Wlczek, P.; Denney, B.; Scheerer, J.

1994-01-01

A robotic system that accepts autonomously generated motion and control commands is described. The system provides images from the monocular vision of a camera mounted on a robot's end effector, eliminating the need for traditional guidance targets that must be predetermined and specifically identified. The telerobotic vision system presents different views of the targeted object relative to the camera, based on a single camera image and knowledge of the target's solid geometry.

Redesign and Rehost of the BIG STICK Nuclear Wargame Simulation

DTIC Science & Technology

1988-12-01

described by Pressman [16]. The 4GT soft- ware development approach consists of four iterative phases: the requirements gathering phase, the design strategy...2. BIG STICK Instructions and Planning Guidance. Air Command and Staff College, Air University, Maxwell AFB AL, 1987. Unpublished Manual. 3. Barry W...Software Engineering Notes, 7:29-32, April 1982. 81 17. Roger S. Pressman . Software Engineering: A Practitioner’s Approach. Mc-Craw-llill Book

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

Frequency Diverse Tracking/Guidance Millimeter Radar Adapted to Target Acquisition,

DTIC Science & Technology

1980-06-01

resolution offered by electro- optical and infrared systems and the adverse environment (fog, battle- field smokes) penetrability which is characteristic of...Reflectors (&1 > 2). 63 ALEXANDER whereAis the transmitted wavelength. It shall also be assumed for this analysis that 2*a4 ’ ( optical region), and that the...and J. L. Brown, "A Preliminary Assessment of Target Classification using Noncoherent Radar Waveforms," US Army Missile Command, Technical Report T-79

Fully automatic guidance and control for rotorcraft nap-of-the-Earth flight following planned profiles. Volume 1: Real-time piloted simulation

NASA Technical Reports Server (NTRS)

Clement, Warren F.; Gorder, Peter J.; Jewell, Wayne F.

1991-01-01

Developing a single-pilot, all-weather nap-of-the-earth (NOE) capability requires fully automatic NOE (ANOE) navigation and flight control. Innovative guidance and control concepts are investigated in a four-fold research effort that: (1) organizes the on-board computer-based storage and real-time updating of NOE terrain profiles and obstacles in course-oriented coordinates indexed to the mission flight plan; (2) defines a class of automatic anticipative pursuit guidance algorithms and necessary data preview requirements to follow the vertical, lateral, and longitudinal guidance commands dictated by the updated flight profiles; (3) automates a decision-making process for unexpected obstacle avoidance; and (4) provides several rapid response maneuvers. Acquired knowledge from the sensed environment is correlated with the forehand knowledge of the recorded environment (terrain, cultural features, threats, and targets), which is then used to determine an appropriate evasive maneuver if a nonconformity of the sensed and recorded environments is observed. This four-fold research effort was evaluated in both fixed-based and moving-based real-time piloted simulations, thereby, providing a practical demonstration for evaluating pilot acceptance of the automated concepts, supervisory override, manual operation, and re-engagement of the automatic system. Volume one describes the major components of the guidance and control laws as well as the results of the piloted simulations. Volume two describes the complete mathematical model of the fully automatic guidance system for rotorcraft NOE flight following planned flight profiles.

Fully Automatic Guidance and Control for Rotorcraft Nap-of-the-earth Flight Following Planned Profiles. Volume 2: Mathematical Model

NASA Technical Reports Server (NTRS)

Clement, Warren F.; Gorder, Peter J.; Jewell, Wayne F.

1991-01-01

Developing a single-pilot, all-weather nap-of-the-earth (NOE) capability requires fully automatic NOE (ANOE) navigation and flight control. Innovative guidance and control concepts are investigated in a four-fold research effort that: (1) organizes the on-board computer-based storage and real-time updating of NOE terrain profiles and obstacles in course-oriented coordinates indexed to the mission flight plan; (2) defines a class of automatic anticipative pursuit guidance algorithms and necessary data preview requirements to follow the vertical, lateral, and longitudinal guidance commands dictated by the updated flight profiles; (3) automates a decision-making process for unexpected obstacle avoidance; and (4) provides several rapid response maneuvers. Acquired knowledge from the sensed environment is correlated with the forehand knowledge of the recorded environment (terrain, cultural features, threats, and targets), which is then used to determine an appropriate evasive maneuver if a nonconformity of the sensed and recorded environments is observed. This four-fold research effort was evaluated in both fixed-base and moving-base real-time piloted simulations; thereby, providing a practical demonstration for evaluating pilot acceptance of the automated concepts, supervisory override, manual operation, and re-engagement of the automatic system. Volume one describes the major components of the guidance and control laws as well as the results of the piloted simulations. Volume two describes the complete mathematical model of the fully automatic guidance system for rotorcraft NOE flight following planned flight profiles.

Ground Simulation of an Autonomous Satellite Rendezvous and Tracking System Using Dual Robotic Systems

NASA Technical Reports Server (NTRS)

Trube, Matthew J.; Hyslop, Andrew M.; Carignan, Craig R.; Easley, Joseph W.

2012-01-01

A hardware-in-the-loop ground system was developed for simulating a robotic servicer spacecraft tracking a target satellite at short range. A relative navigation sensor package "Argon" is mounted on the end-effector of a Fanuc 430 manipulator, which functions as the base platform of the robotic spacecraft servicer. Machine vision algorithms estimate the pose of the target spacecraft, mounted on a Rotopod R-2000 platform, relay the solution to a simulation of the servicer spacecraft running in "Freespace", which performs guidance, navigation and control functions, integrates dynamics, and issues motion commands to a Fanuc platform controller so that it tracks the simulated servicer spacecraft. Results will be reviewed for several satellite motion scenarios at different ranges. Key words: robotics, satellite, servicing, guidance, navigation, tracking, control, docking.

Analytical impact time and angle guidance via time-varying sliding mode technique.

PubMed

Zhao, Yao; Sheng, Yongzhi; Liu, Xiangdong

2016-05-01

To concretely provide a feasible solution for homing missiles with the precise impact time and angle, this paper develops a novel guidance law, based on the nonlinear engagement dynamics. The guidance law is firstly designed with the prior assumption of a stationary target, followed by the practical extension to a moving target scenario. The time-varying sliding mode (TVSM) technique is applied to fulfill the terminal constraints, in which a specific TVSM surface is constructed with two unknown coefficients. One is tuned to meet the impact time requirement and the other one is targeted with a global sliding mode, so that the impact angle constraint as well as the zero miss distance can be satisfied. Because the proposed law possesses three guidance gain as design parameters, the intercept trajectory can be shaped according to the operational conditions and missile׳s capability. To improve the tolerance of initial heading errors and broaden the application, a new frame of reference is also introduced. Furthermore, the analytical solutions of the flight trajectory, heading angle and acceleration command can be totally expressed for the prediction and offline parameter selection by solving a first-order linear differential equation. Numerical simulation results for various scenarios validate the effectiveness of the proposed guidance law and demonstrate the accuracy of the analytic solutions. Copyright © 2016 ISA. Published by Elsevier Ltd. All rights reserved.

Image-based global registration system for bronchoscopy guidance

NASA Astrophysics Data System (ADS)

Khare, Rahul; Higgins, William E.

2011-03-01

Previous studies have shown that bronchoscopy guidance systems improve accuracy and reduce skill variation among physicians during bronchoscopy. In the past, we presented an image-based bronchoscopy guidance system that has been extensively validated in live bronchoscopic procedures. However, this system cannot actively recover from adverse events, such as patient coughing or dynamic airway collapses. After such events, the bronchoscope position is recovered only by moving back to a previously seen and easily identifiable bifurcation such as the main carina. Furthermore, the system requires an attending technician to closely follow the physician's movement of the bronchoscope to avoid misguidance. Also, when the physician is forced to advance the bronchoscope across multiple bifurcations, the system is not able to detect faulty maneuvers. We propose two system-level solutions. The first solution is a system-level guidance strategy that incorporates a global-registration algorithm to provide the physician with updated navigational and guidance information during bronchoscopy. The system can handle general navigation to a region of interest (ROI), as well as adverse events, and it requires minimal commands so that it can be directly controlled by the physician. The second solution visualizes the global picture of all the bifurcations and their relative orientations in advance and suggests the maneuvers needed by the bronchoscope to approach the ROI. Guided bronchoscopy results using human airway-tree phantoms demonstrate the potential of the two solutions.

MEF and MEB Red Teams: Required Conditions and Placement Options

DTIC Science & Technology

2013-04-16

aids decision making and influences how the organization views the problems it is facing. Discussion : The 2010 Commandant’s Planning Guidance...the Regional Command (South West) Red Team. Throughout this time, ‘discovery learning ’ and trial and error were the means in which I gained an...who I had the pleasure of working with and learning from during my time as a red teamer. Most importantly, I would like to thank my family for their

Status of the JWST Science Instrument Payload

NASA Technical Reports Server (NTRS)

Greenhouse, Matt

2016-01-01

The James Webb Space Telescope (JWST) Integrated Science Instrument Module (ISIM) system consists of five sensors (4 science): Mid-Infrared Instrument (MIRI), Near Infrared Imager and Slitless Spectrograph (NIRISS), Fine Guidance Sensor (FGS), Near InfraRed Camera (NIRCam), Near InfraRed Spectrograph (NIRSpec); and nine instrument support systems: Optical metering structure system, Electrical Harness System; Harness Radiator System, ISIM Electronics Compartment, ISIM Remote Services Unit, Cryogenic Thermal Control System, Command and Data Handling System, Flight Software System, Operations Scripts System.

Defense Management. DOD Needs to Reexamine Its Extensive Reliance on Contractors and Continue to Improve Management and Oversight

DTIC Science & Technology

2008-03-11

guidance dealing with contractors who support deployed forces in October 2005. However, as we recently testified , DOD’s leadership needs to ensure...GAO-08-572T may be “ borderline inherently governmental.”14 We have also found problems with contractors having too much control at other...contract oversight personnel, lessons learned, and training of military commanders and contract oversight personnel. More recently, we testified that DOD’s

Army Training Study: Training Effectiveness Analysis (TEA) Summary. Volume 4. Ordnance, Signal, CAMMS (Computer Assisted Map Maneuver System).

DTIC Science & Technology

1978-08-08

learning can be reinforced on the job because individuals at all aptitude and experience levels investigated have the ability to be successful ...both game board and brigade controllers provided realistic feedback and guidance to the command group players . A second major function of the brigade...and experimental measures. The brigade level data collectors and game board players were controllers provided by the participating units’ parent

Flight Control Design - Best Practices

DTIC Science & Technology

2000-12-01

n’était pas universellement disponible à l’époque. La première partie du rapport donne quelques exemples de problèmes de commandes de vol. Ils...pitch axis. We can infer a lesson learned in the form of design guidance for control allocation or priority. Rigorous analysis is required to define...flight excitation and data gathering manoeuvres are safe and are sufficient to produce the required information. BP9.5 Time must be allocated in the

Emerging Threat to America: Non-State Entities Fighting Fourth Generation Warfare in Mexico

DTIC Science & Technology

2010-09-01

has become embedded into towns and cities, as is the case in Juarez, Mexico. The resources dedicated to supporting the Mexican government efforts...date plans from Southern Command (SOUTHCOM) in regards to policies for dealing with Mexico.3 In the case of Mexico, only the North America Free...guidance is used in development of the theater engagement plan for other nations to include: Colombia, Iraq, Afghanistan, and Sudan. In these cases

The Civilian Uplift and Unified Action: Organizing for Stability Operations in Regional Command-East

DTIC Science & Technology

2012-03-01

Intelligence Relevant in Afghanistan,”18 began sending capabilities to SOIC –East to flesh out the organization , and provided guidance for synthesizing...military organizations throughout the area of operations. This “civilian uplift” represented the largest deployment of U.S. agencies to a combat zone since...the Vietnam War.1 The CJTF–82/RC–E headquarters was organized around the headquarters, tactical opera- tions centers, and the special troops

A Study of the Program Management Responsibility Transfer Process for the F-16.

DTIC Science & Technology

1975-09-01

Guidance . . . ... 19 Subjective Criteria. .......... 21 Criteria Based on the Principles of Management ....... ........... ... 27 Planning...26 GSM/SM/75S-8 and then they will be fitted to the management structure of the two commands and IIQ USAF. Criteria Based on the Principles Of Management From...with each of these ýunc- tional areas with emphasis on some of the principles of management that are (in the writer’s opinion) important to the PMRT

Ares-I Bending Filter Design using a Constrained Optimization Approach

NASA Technical Reports Server (NTRS)

Hall, Charles; Jang, Jiann-Woei; Hall, Robert; Bedrossian, Nazareth

2008-01-01

The Ares-I launch vehicle represents a challenging flex-body structural environment for control system design. Software filtering of the inertial sensor output is required to ensure adequate stable response to guidance commands while minimizing trajectory deviations. This paper presents a design methodology employing numerical optimization to develop the Ares-I bending filters. The design objectives include attitude tracking accuracy and robust stability with respect to rigid body dynamics, propellant slosh, and flex. Under the assumption that the Ares-I time-varying dynamics and control system can be frozen over a short period of time, the bending filters are designed to stabilize all the selected frozen-time launch control systems in the presence of parameter uncertainty. To ensure adequate response to guidance command, step response specifications are introduced as constraints in the optimization problem. Imposing these constrains minimizes performance degradation caused by the addition of the bending filters. The first stage bending filter design achieves stability by adding lag to the first structural frequency to phase stabilize the first flex mode while gain stabilizing the higher modes. The upper stage bending filter design gain stabilizes all the flex bending modes. The bending filter designs provided here have been demonstrated to provide stable first and second stage control systems in both Draper Ares Stability Analysis Tool (ASAT) and the MSFC MAVERIC 6DOF nonlinear time domain simulation.

Apollo Guidance, Navigation, and Control (GNC) Hardware Overview

NASA Technical Reports Server (NTRS)

Interbartolo, Michael

2009-01-01

This viewgraph presentation reviews basic guidance, navigation and control (GNC) concepts, examines the Command and Service Module (CSM) and Lunar Module (LM) GNC organization and discusses the primary GNC and the CSM Stabilization and Control System (SCS), as well as other CSM-specific hardware. The LM Abort Guidance System (AGS), Control Electronics System (CES) and other LM-specific hardware are also addressed. Three subsystems exist on each vehicle: the computer subsystem (CSS), the inertial subsystem (ISS) and the optical subsystem (OSS). The CSS and ISS are almost identical between CSM and LM and each is designed to operate independently. CSM SCS hardware are highlighted, including translation control, rotation controls, gyro assemblies, a gyro display coupler and flight director attitude indicators. The LM AGS hardware are also highlighted and include the abort electronics assembly and the abort sensor assembly; while the LM CES hardware includes the attitude controller assembly, thrust/translation controller assemblies and the ascent engine arming assemble. Other common hardware including the Orbital Rate Display - Earth and Lunar (ORDEAL) and the Crewman Optical Alignment Sight (COAS), a docking aid, are also highlighted.

Formation Flying for Distributed InSAR

NASA Technical Reports Server (NTRS)

Scharf, Daniel P.; Murray, Emmanuell A.; Ploen, Scott R.; Gromov, Konstantin G.; Chen, Curtis W.

2006-01-01

We consider two spacecraft flying in formation to create interferometric synthetic aperture radar (InSAR). Several candidate orbits for such in InSar formation have been previously determined based on radar performance and Keplerian orbital dynamics. However, with out active control, disturbance-induced drift can degrade radar performance and (in the worst case) cause a collision. This study evaluates the feasibility of operating the InSAR spacecraft as a formation, that is, with inner-spacecraft sensing and control. We describe the candidate InSAR orbits, design formation guidance and control architectures and algorithms, and report the (Delta)(nu) and control acceleration requirements for the candidate orbits for several tracking performance levels. As part of determining formation requirements, a formation guidance algorithm called Command Virtual Structure is introduced that can reduce the (Delta)(nu) requirements compared to standard Leader/Follower formation approaches.

Entry, Descent, and Landing Guidance and Control Approaches to Satisfy Mars Human Mission Landing Criteria

NASA Technical Reports Server (NTRS)

Dwyer Cianciolo, Alicia; Powell, Richard W.

2017-01-01

Precision landing on Mars is a challenge. All Mars lander missions prior to the 2012 Mars Science Laboratory (MSL) had landing location uncertainty ellipses on the order of hundreds of kilometers. Sending humans to the surface of Mars will likely require multiple landers delivered in close proximity, which will in turn require orders of magnitude improvement in landing accuracy. MSL was the first Mars mission to use an Apollo-derived bank angle guidance to reduce the size of the landing ellipse. It utilized commanded bank angle magnitude to control total range and bank angle reversals to control cross range. A shortcoming of this bank angle guidance is that the open loop phase of flight created by use of bank reversals increases targeting errors. This paper presents a comparison of entry, descent and landing performance for a vehicle with a low lift-to-drag ratio using both bank angle control and an alternative guidance called Direct Force Control (DFC). DFC eliminates the open loop flight errors by directly controlling two forces independently, lift and side force. This permits independent control of down range and cross range. Performance results, evaluated using the Program to Optimize Simulated Trajectories (POST2), including propellant use and landing accuracy, are presented.

Roadrunner: a novel radar guidance concept

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

Kelsey, J.R.

1979-01-01

Soviet breakthrough tactics require the movement of a large number of vehicles from assembly areas to the forward edge of the battle area. The time requirements of this tactic indicate that the road network must be used extensively, if not exclusively. This paper describes an exploratory development (technology demonstration) program aimed at demonstrating a novel radar navigation/guidance scheme which enables a small unmanned aircraft (drone) to follow roads. Since vehicles on the road can be easily detected, this aircraft could be used as either a strike vehicle itself or as a reconnaissance adjunct to another strike system. The guidance schememore » involves on-board radar measurements of the backscatter response of the terrain beneath the aircraft. The differences in reflectivity between road and roadside surfaces are processed by a small on-board computer to generate guidance commands to keep the vehicle over the road. Preliminary system definition includes a 17-GHz radar aboard a subsonic, propeller-driven unmanned aircraft. Estimated operational altitude and speed are 30 m and 100 km/h, respectively. The drone could be either ground or air launched, and would be expendable. Payload capabilities of 50 to 100 kg are envisioned, with an operational range of 50 to 100 km. 5 figures, 1 table.« less

General purpose simulation system of the data management system for Space Shuttle mission 18

NASA Technical Reports Server (NTRS)

Bengtson, N. M.; Mellichamp, J. M.; Smith, O. C.

1976-01-01

A simulation program for the flow of data through the Data Management System of Spacelab and Space Shuttle was presented. The science, engineering, command and guidance, navigation and control data were included. The programming language used was General Purpose Simulation System V (OS). The science and engineering data flow was modeled from its origin at the experiments and subsystems to transmission from Space Shuttle. Command data flow was modeled from the point of reception onboard and from the CDMS Control Panel to the experiments and subsystems. The GN&C data flow model handled data between the General Purpose Computer and the experiments and subsystems. Mission 18 was the particular flight chosen for simulation. The general structure of the program is presented, followed by a user's manual. Input data required to make runs are discussed followed by identification of the output statistics. The appendices contain a detailed model configuration, program listing and results.

The Impact of Recent Federal Administrative Rules on Army Dental Care. Volume 1. A Cost Analysis of Bloodborne Pathogens: A Report of Consultation

DTIC Science & Technology

1992-12-31

procedure codes 9973 and 9974), and the unit cost to the Fort Sam Houston DENTAC ($.79). Expenditures on dental handpieces were estimated using the guidance...life span after which it is due for replacement. The effects of steam sterilization on dental handpieces decreases their life span substantially... handpieces should be sterilized between patients. ADA 18 May, 1992. 12. Reddy, T.G. Director, Dental Services, US Army Health Services Command

U.S. Reserve Component Training in U.S. Southern Command - An Example of Total Army Concept.

DTIC Science & Technology

1988-03-22

contention from the very 6eginning is what happens in Central aria South America is that it prov± des art opportunity to test all the elements of...of tne best examples of our commitnment to the region is the recently completed exercise in Ecuador-Abriendo Rutas (Opening Roads). This exercise...to recovery is to restore Ecuador’s transportation network, roaas and bridges are absolutely essential as the first stepo.6 So under guidance from JCS

Guidance, Navigation and Control Digital Emulation Technology Laboratory. Volume 1. Part 2. Task 1: Digital Emulation Technology Laboratory

DTIC Science & Technology

1991-09-27

AD-A241 692 II I] II I11 ANNUAL REPORT VOLUME 1 PART 2 TASK 1: DIGITAL EMULATION TECHNOLOGY LABORATOIRY REPORT NO. AR-0142-91-001 September 27, 1991... DIGITAL EMULATION TECHNOLOGY LABORATORY Contract No. DASG60-89-C-0142 Sponsored By The United States Army ? trategic Defense Command COMPUTER...ANNUAL REPORT VOLUME 1 PART 2 TASK 1: DIGITAL EMULATION TECHNOLOGY LABORATORY September 27, 1991 Authors Thomas R. Collins and Stephen R. Wachtel

Design Guidance for Command, Control, Communications, and Intelligence (C3I) Facility Cooling Systems

DTIC Science & Technology

1989-05-01

Typical ranges are from 50 to 70 OF. If a chiller is dedicated to serving water-cooled electronic equipment, the chilled water temperature setpoint can...can be satisfied with 50 OF chilled water. The COP of the dedicated chiller is improved by raising the chilled water setpoint , and the total life-cycle...USACERL TECHNICAL REPORT E-89/10 May 1989 Studies in Optimizing HVAC Hardware for C31 Facilities US Army Corps of Engineers Construction Engineering

To Enable and Sustain: Pacific Air Forces’ Theater Security Cooperation as a Line of Operation

DTIC Science & Technology

2015-02-01

security cooperation mechanisms already in place are evolving into a more sequenced and deliberate plan towards a defined cooperative end state. This...alignment of higher guidance and is designed to advise and guide the command’s activities in the region. Joint in its es- sence , it communicates and...face of crises, it is far better to prevent them from occurring in the first place , establish cooperative arrangements ahead of time, and reduce

Defense Civil Support: DOD, HHS, and DHS Should Use Existing Coordination Mechanisms to Improve Their Pandemic Preparedness

DTIC Science & Technology

2017-02-01

could be almost twice the total number of battlefield fatalities in all of America’s wars since the American Revolution in 1776. A pandemic...since the American Revolution in 1776.1 In comparison, the number of U.S. fatalities (approximately 650,000) from the 1918-1919 “Spanish flu” pandemic... French Polynesia and the Cook Islands. U.S. Pacific Command recently issued guidance to service members and DOD civilians to take precautions when

A Near Term Approach to Embedded Training: Battle Command Visualization 101

DTIC Science & Technology

2006-05-01

Example of Task Guidance area at the end of Module 1, Exercise 1 (Level 1) ...... 26 Figure 9 Example of Robo -Scout information, accessed through the...unmanned ground vehicle (UGV) sensor, the Robo -Scout. They will be equipped with both passive and active systems to provide target acquisition, real...PIR# Track of Update RqieTemplated Required 1 Tracked & NAI 1, 2 S, T S200 synthetic L 2 hrs Vehicle type, Intel, Fires (PIR 1) Wheeled aperture radar

Aligning the Mountain and the Molehill: How the Combatant Commander Coordinates his Theater Security Cooperation Plan with the State Department

DTIC Science & Technology

2005-02-14

hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed , and...the national level, the National Security Act of 1947 (NSA 47) mandates the need for interagency cooperation.6 In this regard, the National Security...within DoD, it lacks a central body or mechanism to provide the overarching, truly ’global’ oversight and guidance needed to ensure adequate interagency

Command History. 1967. Volume 1. Sanitized

DTIC Science & Technology

1967-01-01

the Politburo of the Lao Dong Party. This top political control center included Le Duan, General Vo Nguyen Glap, Truong Chinh , Le Duc Tho, and until...the support area Naval Support Activity (NSA) Da Nang’s vital intra- coastal trans -shipment route from the deep water port at Da Nang northward to...under the energetic guidance of MG Nguyen Duc Thang, reviewed PAGE 6 OF 1340 PAGES I% the entire process of RD and set to the task of revitalizing the

Stochastic Feedforward Control Technique

NASA Technical Reports Server (NTRS)

Halyo, Nesim

1990-01-01

Class of commanded trajectories modeled as stochastic process. Advanced Transport Operating Systems (ATOPS) research and development program conducted by NASA Langley Research Center aimed at developing capabilities for increases in capacities of airports, safe and accurate flight in adverse weather conditions including shear, winds, avoidance of wake vortexes, and reduced consumption of fuel. Advances in techniques for design of modern controls and increased capabilities of digital flight computers coupled with accurate guidance information from Microwave Landing System (MLS). Stochastic feedforward control technique developed within context of ATOPS program.

A Simple Two Aircraft Conflict Resolution Algorithm

NASA Technical Reports Server (NTRS)

Chatterji, Gano B.

2006-01-01

Conflict detection and resolution methods are crucial for distributed air-ground traffic management in which the crew in, the cockpit, dispatchers in operation control centers sad and traffic controllers in the ground-based air traffic management facilities share information and participate in the traffic flow and traffic control functions. This paper describes a conflict detection, and a conflict resolution method. The conflict detection method predicts the minimum separation and the time-to-go to the closest point of approach by assuming that both the aircraft will continue to fly at their current speeds along their current headings. The conflict resolution method described here is motivated by the proportional navigation algorithm, which is often used for missile guidance during the terminal phase. It generates speed and heading commands to rotate the line-of-sight either clockwise or counter-clockwise for conflict resolution. Once the aircraft achieve a positive range-rate and no further conflict is predicted, the algorithm generates heading commands to turn back the aircraft to their nominal trajectories. The speed commands are set to the optimal pre-resolution speeds. Six numerical examples are presented to demonstrate the conflict detection, and the conflict resolution methods.

Improved Re-Configurable Sliding Mode Controller for Reusable Launch Vehicle of Second Generation Addressing Aerodynamic Surface Failures and Thrust Deficiencies

NASA Technical Reports Server (NTRS)

Shtessel, Yuri B.

2002-01-01

In this report we present a time-varying sliding mode control (TV-SMC) technique for reusable launch vehicle (RLV) attitude control in ascent and entry flight phases. In ascent flight the guidance commands Euler roll, pitch and yaw angles, and in entry flight it commands the aerodynamic angles of bank, attack and sideslip. The controller employs a body rate inner loop and the attitude outer loop, which are separated in time-scale by the singular perturbation principle. The novelty of the TVSMC is that both the sliding surface and the boundary layer dynamics can be varied in real time using the PD-eigenvalue assignment technique. This salient feature is used to cope with control command saturation and integrator windup in the presence of severe disturbance or control effector failure, which enhances the robustness and fault tolerance of the controller. The TV-SMC is developed and tuned up for the X-33 sub-orbital technology demonstration vehicle in launch and re-entry modes. A variety of nominal, dispersion and failure scenarios have tested via high fidelity 6DOF simulations using MAVERIC/SLIM simulation software.

Health Hazard Assessment and Toxicity Clearances in the Army Acquisition Process

NASA Technical Reports Server (NTRS)

Macko, Joseph A., Jr.

2000-01-01

The United States Army Materiel Command, Army Acquisition Pollution Prevention Support Office (AAPPSO) is responsible for creating and managing the U.S. Army Wide Acquisition Pollution Prevention Program. They have established Integrated Process Teams (IPTs) within each of the Major Subordinate Commands of the Army Materiel Command. AAPPSO provides centralized integration, coordination, and oversight of the Army Acquisition Pollution Prevention Program (AAPPP) , and the IPTs provide the decentralized execution of the AAPPSO program. AAPPSO issues policy and guidance, provides resources and prioritizes P2 efforts. It is the policy of the (AAPPP) to require United States Army Surgeon General approval of all materials or substances that will be used as an alternative to existing hazardous materials, toxic materials and substances, and ozone-depleting substances. The Army has a formal process established to address this effort. Army Regulation 40-10 requires a Health Hazard Assessment (HHA) during the Acquisition milestones of a new Army system. Army Regulation 40-5 addresses the Toxicity Clearance (TC) process to evaluate new chemicals and materials prior to acceptance as an alternative. U.S. Army Center for Health Promotion and Preventive Medicine is the Army's matrixed medical health organization that performs the HHA and TC mission.

Adaptive Guidance and Control Algorithms applied to the X-38 Reentry Mission

NASA Astrophysics Data System (ADS)

Graesslin, M.; Wallner, E.; Burkhardt, J.; Schoettle, U.; Well, K. H.

International Space Station's Crew Return/Rescue Vehicle (CRV) is planned to autonomously return the complete crew of 7 astronauts back to earth in case of an emergency. As prototype of such a vehicle, the X-38, is being developed and built by NASA with European participation. The X-38 is a lifting body with a hyper- sonic lift to drag ratio of about 0.9. In comparison to the Space Shuttle Orbiter, the X-38 has less aerodynamic manoeuvring capability and less actuators. Within the German technology programme TETRA (TEchnologies for future space TRAnsportation systems) contributing to the X-38 program, guidance and control algorithms have been developed and applied to the X-38 reentry mission. The adaptive guidance concept conceived combines an on-board closed-loop predictive guidance algorithm with flight load control that temporarily overrides the attitude commands of the predictive component if the corre- sponding load constraints are violated. The predictive guidance scheme combines an optimization step and a sequence of constraint restoration cycles. In order to satisfy on-board computation limitations the complete scheme is performed only during the exo-atmospheric flight coast phase. During the controlled atmospheric flight segment the task is reduced to a repeatedly solved targeting problem based on the initial optimal solution, thus omitting in-flight constraints. To keep the flight loads - especially the heat flux, which is in fact a major concern of the X-38 reentry flight - below their maximum admissible values, a flight path controller based on quadratic minimization techniques may override the predictive guidance command for a flight along the con- straint boundary. The attitude control algorithms developed are based on dynamic inversion. This methodology enables the designer to straightforwardly devise a controller structure from the system dynamics. The main ad- vantage of this approach with regard to reentry control design lies in the fact that inversion renders a scheduled controller. Throughout the reentry, varying sets of actuators are available for control. Depending on which set is available, different inversion schemes are applied. With at least three controls effectors, decoupled control of the attitude angles can be achieved via a successive inversion which exploits the time-scale separation inherent in the attitude dynamics. However, during a flight phase where control needs to be achieved with only two body flaps, internal dynamics must be taken into account. To this end, a redefinition of the controlled variables is carried out so that the internal dynamics are stabilized while satisfactory tracking performance is achieved. The objectives of the present paper are to discuss the guidance and control approach taken, and asses the per- formance of the concepts by numerical flight simulations. For this purpose results obtained by means of a nu- merical flight simulator (CREDITS), that accurately models the characteristics of the X-38 vehicle, are presented to demonstrate the performance and effectiveness of the guidance and control design. Sensitivities to non- nominal flight conditions have been evaluated by Monte-Carlo analyses comprising motion simulations in both three and six degree of freedom. The results show that the mission requirements are met.

Maneuver Algorithm for Bearings-Only Target Tracking with Acceleration and Field of View Constraints

NASA Astrophysics Data System (ADS)

Roh, Heekun; Shim, Sang-Wook; Tahk, Min-Jea

2018-05-01

This paper proposes a maneuver algorithm for the agent performing target tracking with bearing angle information only. The goal of the agent is to estimate the target position and velocity based only on the bearing angle data. The methods of bearings-only target state estimation are outlined. The nature of bearings-only target tracking problem is then addressed. Based on the insight from above-mentioned properties, the maneuver algorithm for the agent is suggested. The proposed algorithm is composed of a nonlinear, hysteresis guidance law and the estimation accuracy assessment criteria based on the theory of Cramer-Rao bound. The proposed guidance law generates lateral acceleration command based on current field of view angle. The accuracy criteria supply the expected estimation variance, which acts as a terminal criterion for the proposed algorithm. The aforementioned algorithm is verified with a two-dimensional simulation.

Physics-based simulations of aerial attacks by peregrine falcons reveal that stooping at high speed maximizes catch success against agile prey.

PubMed

Mills, Robin; Hildenbrandt, Hanno; Taylor, Graham K; Hemelrijk, Charlotte K

2018-04-01

The peregrine falcon Falco peregrinus is renowned for attacking its prey from high altitude in a fast controlled dive called a stoop. Many other raptors employ a similar mode of attack, but the functional benefits of stooping remain obscure. Here we investigate whether, when, and why stooping promotes catch success, using a three-dimensional, agent-based modeling approach to simulate attacks of falcons on aerial prey. We simulate avian flapping and gliding flight using an analytical quasi-steady model of the aerodynamic forces and moments, parametrized by empirical measurements of flight morphology. The model-birds' flight control inputs are commanded by their guidance system, comprising a phenomenological model of its vision, guidance, and control. To intercept its prey, model-falcons use the same guidance law as missiles (pure proportional navigation); this assumption is corroborated by empirical data on peregrine falcons hunting lures. We parametrically vary the falcon's starting position relative to its prey, together with the feedback gain of its guidance loop, under differing assumptions regarding its errors and delay in vision and control, and for three different patterns of prey motion. We find that, when the prey maneuvers erratically, high-altitude stoops increase catch success compared to low-altitude attacks, but only if the falcon's guidance law is appropriately tuned, and only given a high degree of precision in vision and control. Remarkably, the optimal tuning of the guidance law in our simulations coincides closely with what has been observed empirically in peregrines. High-altitude stoops are shown to be beneficial because their high airspeed enables production of higher aerodynamic forces for maneuvering, and facilitates higher roll agility as the wings are tucked, each of which is essential to catching maneuvering prey at realistic response delays.

Is Naval Hospital Bremerton as Prepared as They Should be to Respond to a Man-Made or Natural Disaster

DTIC Science & Technology

2006-12-18

11 Bremerton Preparedness through a pandemic and have drafted influenza pandemic preparedness plans (Assistant Secretary of Defense, 2006). The...includes 7 Gurney/beds (3 APU/4 PACU) Isolation Breakdown: Active Inactive 2/5MS 2/Blbg 17 Rms C3313, C3309 2/Bldg 17 Rms C2111, C2117 4/ ICU 1/40B 1/ER... influenza and Naval Hospital Bremerton (2005) needs to be tailored and revised to relay the latest guidance. Commander Crescenzi, Naval Hospital

Goal-oriented training affects decision-making processes in virtual and simulated fire and rescue environments.

PubMed

Cohen-Hatton, Sabrina R; Honey, R C

2015-12-01

Decisions made by operational commanders at emergency incidents have been characterized as involving a period of information gathering followed by courses of action that are often generated without explicit plan formulation. We examined the efficacy of goal-oriented training in engendering explicit planning that would enable better communication at emergency incidents. While standard training mirrored current operational guidance, goal-oriented training incorporated "decision controls" that highlighted the importance of evaluating goals, anticipated consequences, and risk/benefit analyses once a potential course of action has been identified. In Experiment 1, 3 scenarios (a house fire, road traffic collision, and skip fire) were presented in a virtual environment, and in Experiment 2 they were recreated on the fireground. In Experiment 3, the house fire was recreated as a "live burn," and incident commanders and their crews responded to this scenario as an emergency incident. In all experiments, groups given standard training showed the reported tendency to move directly from information gathering to action, whereas those given goal-oriented training were more likely to develop explicit plans and show anticipatory situational awareness. These results indicate that training can be readily modified to promote explicit plan formulation that could facilitate plan sharing between incident commanders and their teams. (c) 2015 APA, all rights reserved).

STS-103 Payload Commander Smith and his wife DEPART PAFB for Houston

NASA Technical Reports Server (NTRS)

1999-01-01

STS-103 Payload Commander Steven L. Smith and his wife, Peggy, smile for the camera on the runway at Patrick Air Force Base in Cocoa Beach, Fla. The STS-103 crew and their families are preparing to board an airplane that will return them to their home base at the Johnson Space Center in Houston following the successful completion of their mission. Discovery landed in darkness the previous evening, Dec. 27, on runway 33 at KSC's Shuttle Landing Facility at 7:00:47 p.m. EST. This was the first time that a Shuttle crew spent the Christmas holiday in space. The other STS-103 crew members are Commander Curtis L. Brown Jr.; Pilot Scott J. Kelly; and Mission Specialists C. Michael Foale (Ph.D.), John M. Grunsfeld (Ph.D.), Claude Nicollier of Switzerland and Jean-Frangois Clervoy of France. The STS-103 mission accomplished outfitting the Hubble Space Telescope with six new gyroscopes, six new voltage/temperature improvement kits, a new onboard computer, a new solid state recorder and new data transmitter, a new fine guidance sensor along with new insulation on parts of the orbiting telescope. This was the 96th flight in the Space Shuttle program and the 27th for the orbiter Discovery.

Knowledge representation system for assembly using robots

NASA Technical Reports Server (NTRS)

Jain, A.; Donath, M.

1987-01-01

Assembly robots combine the benefits of speed and accuracy with the capability of adaptation to changes in the work environment. However, an impediment to the use of robots is the complexity of the man-machine interface. This interface can be improved by providing a means of using a priori-knowledge and reasoning capabilities for controlling and monitoring the tasks performed by robots. Robots ought to be able to perform complex assembly tasks with the help of only supervisory guidance from human operators. For such supervisory quidance, it is important to express the commands in terms of the effects desired, rather than in terms of the motion the robot must undertake in order to achieve these effects. A suitable knowledge representation can facilitate the conversion of task level descriptions into explicit instructions to the robot. Such a system would use symbolic relationships describing the a priori information about the robot, its environment, and the tasks specified by the operator to generate the commands for the robot.

A Sensory-Motor Control Model of Animal Flight Explains Why Bats Fly Differently in Light Versus Dark

PubMed Central

Bar, Nadav S.; Skogestad, Sigurd; Marçal, Jose M.; Ulanovsky, Nachum; Yovel, Yossi

2015-01-01

Animal flight requires fine motor control. However, it is unknown how flying animals rapidly transform noisy sensory information into adequate motor commands. Here we developed a sensorimotor control model that explains vertebrate flight guidance with high fidelity. This simple model accurately reconstructed complex trajectories of bats flying in the dark. The model implies that in order to apply appropriate motor commands, bats have to estimate not only the angle-to-target, as was previously assumed, but also the angular velocity (“proportional-derivative” controller). Next, we conducted experiments in which bats flew in light conditions. When using vision, bats altered their movements, reducing the flight curvature. This change was explained by the model via reduction in sensory noise under vision versus pure echolocation. These results imply a surprising link between sensory noise and movement dynamics. We propose that this sensory-motor link is fundamental to motion control in rapidly moving animals under different sensory conditions, on land, sea, or air. PMID:25629809

Control Program for an Optical-Calibration Robot

NASA Technical Reports Server (NTRS)

Johnston, Albert

2005-01-01

A computer program provides semiautomatic control of a moveable robot used to perform optical calibration of video-camera-based optoelectronic sensor systems that will be used to guide automated rendezvous maneuvers of spacecraft. The function of the robot is to move a target and hold it at specified positions. With the help of limit switches, the software first centers or finds the target. Then the target is moved to a starting position. Thereafter, with the help of an intuitive graphical user interface, an operator types in coordinates of specified positions, and the software responds by commanding the robot to move the target to the positions. The software has capabilities for correcting errors and for recording data from the guidance-sensor system being calibrated. The software can also command that the target be moved in a predetermined sequence of motions between specified positions and can be run in an advanced control mode in which, among other things, the target can be moved beyond the limits set by the limit switches.

Flight test experience and controlled impact of a large, four-engine, remotely piloted airplane

NASA Technical Reports Server (NTRS)

Kempel, R. W.; Horton, T. W.

1985-01-01

A controlled impact demonstration (CID) program using a large, four engine, remotely piloted transport airplane was conducted. Closed loop primary flight control was performed from a ground based cockpit and digital computer in conjunction with an up/down telemetry link. Uplink commands were received aboard the airplane and transferred through uplink interface systems to a highly modified Bendix PB-20D autopilot. Both proportional and discrete commands were generated by the ground pilot. Prior to flight tests, extensive simulation was conducted during the development of ground based digital control laws. The control laws included primary control, secondary control, and racetrack and final approach guidance. Extensive ground checks were performed on all remotely piloted systems. However, manned flight tests were the primary method of verification and validation of control law concepts developed from simulation. The design, development, and flight testing of control laws and the systems required to accomplish the remotely piloted mission are discussed.

KENNEDY SPACE CENTER, FLA. - The Rotating Service Structure has been retracted at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-10

KENNEDY SPACE CENTER, FLA. - The Rotating Service Structure has been retracted at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

Terminal attack trajectories of peregrine falcons are described by the proportional navigation guidance law of missiles

PubMed Central

Brighton, Caroline H.; Thomas, Adrian L. R.

2017-01-01

The ability to intercept uncooperative targets is key to many diverse flight behaviors, from courtship to predation. Previous research has looked for simple geometric rules describing the attack trajectories of animals, but the underlying feedback laws have remained obscure. Here, we use GPS loggers and onboard video cameras to study peregrine falcons, Falco peregrinus, attacking stationary targets, maneuvering targets, and live prey. We show that the terminal attack trajectories of peregrines are not described by any simple geometric rule as previously claimed, and instead use system identification techniques to fit a phenomenological model of the dynamical system generating the observed trajectories. We find that these trajectories are best—and exceedingly well—modeled by the proportional navigation (PN) guidance law used by most guided missiles. Under this guidance law, turning is commanded at a rate proportional to the angular rate of the line-of-sight between the attacker and its target, with a constant of proportionality (i.e., feedback gain) called the navigation constant (N). Whereas most guided missiles use navigation constants falling on the interval 3 ≤ N ≤ 5, peregrine attack trajectories are best fitted by lower navigation constants (median N < 3). This lower feedback gain is appropriate at the lower flight speed of a biological system, given its presumably higher error and longer delay. This same guidance law could find use in small visually guided drones designed to remove other drones from protected airspace. PMID:29203660

Terminal attack trajectories of peregrine falcons are described by the proportional navigation guidance law of missiles.

PubMed

Brighton, Caroline H; Thomas, Adrian L R; Taylor, Graham K

2017-12-19

The ability to intercept uncooperative targets is key to many diverse flight behaviors, from courtship to predation. Previous research has looked for simple geometric rules describing the attack trajectories of animals, but the underlying feedback laws have remained obscure. Here, we use GPS loggers and onboard video cameras to study peregrine falcons, Falco peregrinus , attacking stationary targets, maneuvering targets, and live prey. We show that the terminal attack trajectories of peregrines are not described by any simple geometric rule as previously claimed, and instead use system identification techniques to fit a phenomenological model of the dynamical system generating the observed trajectories. We find that these trajectories are best-and exceedingly well-modeled by the proportional navigation (PN) guidance law used by most guided missiles. Under this guidance law, turning is commanded at a rate proportional to the angular rate of the line-of-sight between the attacker and its target, with a constant of proportionality (i.e., feedback gain) called the navigation constant ( N ). Whereas most guided missiles use navigation constants falling on the interval 3 ≤ N ≤ 5, peregrine attack trajectories are best fitted by lower navigation constants (median N < 3). This lower feedback gain is appropriate at the lower flight speed of a biological system, given its presumably higher error and longer delay. This same guidance law could find use in small visually guided drones designed to remove other drones from protected airspace. Copyright © 2017 the Author(s). Published by PNAS.

Control Method for Video Guidance Sensor System

NASA Technical Reports Server (NTRS)

Howard, Richard T. (Inventor); Book, Michael L. (Inventor); Bryan, Thomas C. (Inventor)

2005-01-01

A method is provided for controlling operations in a video guidance sensor system wherein images of laser output signals transmitted by the system and returned from a target are captured and processed by the system to produce data used in tracking of the target. Six modes of operation are provided as follows: (i) a reset mode; (ii) a diagnostic mode; (iii) a standby mode; (iv) an acquisition mode; (v) a tracking mode; and (vi) a spot mode wherein captured images of returned laser signals are processed to produce data for all spots found in the image. The method provides for automatic transition to the standby mode from the reset mode after integrity checks are performed and from the diagnostic mode to the reset mode after diagnostic operations are commands is permitted only when the system is in the carried out. Further, acceptance of reset and diagnostic standby mode. The method also provides for automatic transition from the acquisition mode to the tracking mode when an acceptable target is found.

A Low Cost Approach to the Design of Autopilot for Hypersonic Glider

NASA Astrophysics Data System (ADS)

Liang, Wang; Weihua, Zhang; Ke, Peng; Donghui, Wang

2017-12-01

This paper proposes a novel integrated guidance and control (IGC) approach to improve the autopilot design with low cost for hypersonic glider in dive and pull-up phase. The main objective is robust and adaptive tracking of flight path angle (FPA) under severe flight scenarios. Firstly, the nonlinear IGC model is developed with a second order actuator dynamics. Then the adaptive command filtered back-stepping control is implemented to deal with the large aerodynamics coefficient uncertainties, control surface uncertainties and unmatched time-varying disturbances. For the autopilot, a back-stepping sliding mode control is designed to track the control surface deflection, and a nonlinear differentiator is used to avoid direct differentiating the control input. Through a series of 6-DOF numerical simulations, it’s shown that the proposed scheme successfully cancels out the large uncertainties and disturbances in tracking different kinds of FPA trajectory. The contribution of this paper lies in the application and determination of nonlinear integrated design of guidance and control system for hypersonic glider.

An analysis of the Hubble Space Telescope fine guidance sensor fine lock mode

NASA Technical Reports Server (NTRS)

Taff, L. G.

1991-01-01

There are two guiding modes of the Hubble Space Telescope (HST) used for the acquisition of astronomical data by one of its six scientific instruments. The more precise one is called Fine Lock. Command and control problems in the onboard electronics has limited Fine Lock to brighter stars, V less than 13.0 mag, instead of fulfilling its goal of V = 14.5 mag. Consequently, the less precise guiding mode of Coarse Track (approximately 40 milli-arc seconds) has to be used fairly frequently. Indeed, almost half of the scientific observations to have been made with the HST will be compromised. The only realistic or extensive simulations of the Fine Lock guidance mode are reported. The theoretical analysis underlying the Monte Carlo experiments and the numerical computations clearly show both that the control electronics are severely under-engineered and how to adjust the various control parameters to successfully extend Fine Lock guiding performance back to V = 14.0 mag and sometimes beyond.

A Verbal Guidance System for Severe Disabled People

NASA Astrophysics Data System (ADS)

Redjati, Abdelghani; Bousbia-Salah, Mounir

2008-06-01

The recent development in rehabilitation technology allows to significantly broaden the range of possible applications that support handicapped people in their daily lives. This paper presents a moral and physical support for the disabled. It consists in the development of a verbal guidance system based on a speech recognition development kit `VD364'. This aid is intended to control a wheelchair and a manipulator arm for people with severe disabilities and who can speak. The study and design, conducted in the framework of this contribution have enabled an adaptation for a possible application and maximum exploitation of words that can be generated by a vocal module. The problem addressed is to allow a manipulator arm to compensate mechanically arm movements to give the handicapped satisfaction of his needs (for instance, drinking a glass of water). The objective is then to put forward a vocal command system that allows the arm to move in a well determined area to accomplish tasks that must be given by the user in addition to the displacement of the wheelchair.

Control method for video guidance sensor system

NASA Technical Reports Server (NTRS)

Howard, Richard T. (Inventor); Book, Michael L. (Inventor); Bryan, Thomas C. (Inventor)

2005-01-01

A method is provided for controlling operations in a video guidance sensor system wherein images of laser output signals transmitted by the system and returned from a target are captured and processed by the system to produce data used in tracking of the target. Six modes of operation are provided as follows: (i) a reset mode; (ii) a diagnostic mode; (iii) a standby mode; (iv) an acquisition mode; (v) a tracking mode; and (vi) a spot mode wherein captured images of returned laser signals are processed to produce data for all spots found in the image. The method provides for automatic transition to the standby mode from the reset mode after integrity checks are performed and from the diagnostic mode to the reset mode after diagnostic operations are carried out. Further, acceptance of reset and diagnostic commands is permitted only when the system is in the standby mode. The method also provides for automatic transition from the acquisition mode to the tracking mode when an acceptable target is found.

[Intensity in the neurorehabilitation of spastic paresis].

PubMed

Meimoun, M; Bayle, N; Baude, M; Gracies, J-M

2015-02-01

Neurorestoration of motor command in spastic paresis requires a double action of stimulation and guidance of central nervous system plasticity. Beyond drug therapies, electrical stimulation and cell therapies, which may stimulate plasticity without precisely guiding it, two interventions seem capable of driving plasticity with a double stimulation and guidance component: the lesion itself (lesion-induced plasticity) and durable behavior modifications (behavior-induced plasticity). Modern literature makes it clear that the intensity of the neuronal and physical training is a primary condition to foster behavior-induced plasticity. When it comes to working on movement, intensity can be achieved by the combination of two key components, one is the difficulty of the trained movement, the other is the number of repetitions or the daily duration of the practice. A number of recent studies shed light on promising recovery prospects, particularly using the emergence of new technologies such as robot-assisted therapy and concepts such as guided self-rehabilitation contracts. Copyright © 2014 Elsevier Masson SAS. All rights reserved.

Proving the correctness of the flight director program EADIFD, volume 1

NASA Technical Reports Server (NTRS)

Lee, F. J.; Maurer, W. D.

1977-01-01

EADIFD is written in symbolic assembly language for execution on the C4000 airborne computer. It is a subprogram of an aircraft navigation and guidance program and is used to generate pitch and roll command signals for use in terminal airspace. The proof of EADIFD was carried out by an inductive assertion method consisting of two parts, a verification condition generator and a source language independent proof checker. With the specifications provided by NASA, EADIFD was proved correct. The termination of the program is guaranteed and the program contains no instructions that can modify it under any conditions.

Integrated Collision Avoidance System for Air Vehicle

NASA Technical Reports Server (NTRS)

Lin, Ching-Fang (Inventor)

2013-01-01

Collision with ground/water/terrain and midair obstacles is one of the common causes of severe aircraft accidents. The various data from the coremicro AHRS/INS/GPS Integration Unit, terrain data base, and object detection sensors are processed to produce collision warning audio/visual messages and collision detection and avoidance of terrain and obstacles through generation of guidance commands in a closed-loop system. The vision sensors provide more information for the Integrated System, such as, terrain recognition and ranging of terrain and obstacles, which plays an important role to the improvement of the Integrated Collision Avoidance System.

Computer Simulated Development of Improved Command to Line-of-Sight Missile Guidance Techniques

DTIC Science & Technology

1979-03-01

INaval Postgraduate School Ma//MW Monterey, CA 93940 C -" 10 6 -VA. MONITORING A41INCY MAMIE 6 AOORESS(it 011f.,.t frau Cdfltt.I01gg 01HOS). IS. SECURITY...States Navy B.S., United States Naval Academy, 1967 Submitted in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE IN SYSTEM4S...i i i it +P~4 to i if 1 . 1 - ztnco C3i.- Z-, a O.) Z (~VI- (M CWn4 Ul% 103 4-7 A BIBLIOGRAPHY 1. U.S. Army Foreign Science and Technology Center

A Study to Determine Command Guidance Required by Registered Nurses in the Management of Terminally Ill Patients during Pre-Death When Non- Resuscitative Measures are Implied

DTIC Science & Technology

1984-05-01

fact, no longer in the best interest of the patient . Many factors are involved in making the medical determination that resuscitation is not to be a...8217 However, CPR is ordinary medical care and only the patient has the right to refuse this care if he is able to do so. Failure to obtain the patient’s...attempt resuscitation, could be an appropriate course of medical treatment for a comatose patient if the attending physician determined that the

Titan 3E/Centaur D-1T Systems Summary

NASA Technical Reports Server (NTRS)

1973-01-01

A systems and operational summary of the Titan 3E/Centaur D-1T program is presented which describes vehicle assembly facilities, launch facilities, and management responsibilities, and also provides detailed information on the following separate systems: (1) mechanical systems, including structural components, insulation, propulsion units, reaction control, thrust vector control, hydraulic systems, and pneumatic equipment; (2) astrionics systems, such as instrumentation and telemetry, navigation and guidance, C-Band tracking system, and range safety command system; (3) digital computer unit software; (4) flight control systems; (5) electrical/electronic systems; and (6) ground support equipment, including checkout equipment.

Models for interrupted monitoring of a stochastic process

NASA Technical Reports Server (NTRS)

Palmer, E.

1977-01-01

As computers are added to the cockpit, the pilot's job is changing from of manually flying the aircraft, to one of supervising computers which are doing navigation, guidance and energy management calculations as well as automatically flying the aircraft. In this supervisorial role the pilot must divide his attention between monitoring the aircraft's performance and giving commands to the computer. Normative strategies are developed for tasks where the pilot must interrupt his monitoring of a stochastic process in order to attend to other duties. Results are given as to how characteristics of the stochastic process and the other tasks affect the optimal strategies.

HSI Guidelines Outline for the Air Vehicle Control Station. Version 2

NASA Technical Reports Server (NTRS)

2006-01-01

This document provides guidance to the FAA and manufacturers on how to develop UAS Pilot Vehicle Interfaces to safely and effectively integrate UASs into the NAS. Preliminary guidelines are provided for Aviate, Communicate, Navigate and Avoid Hazard functions. The pilot shall have information and control capability so that pilot-UA interactions are not adverse, unfavorable, nor compromise safety. Unfavorable interactions include anomalous aircraft-pilot coupling (APC) interactions (closed loop), pilot-involved oscillations (categories I, II or III), and non-oscillatory APC events (e.g., divergence). - Human Systems Integration Pilot-Technology Interface Requirements for Command, Control, and Communications (C3)

Physics-based simulations of aerial attacks by peregrine falcons reveal that stooping at high speed maximizes catch success against agile prey

PubMed Central

Hildenbrandt, Hanno

2018-01-01

The peregrine falcon Falco peregrinus is renowned for attacking its prey from high altitude in a fast controlled dive called a stoop. Many other raptors employ a similar mode of attack, but the functional benefits of stooping remain obscure. Here we investigate whether, when, and why stooping promotes catch success, using a three-dimensional, agent-based modeling approach to simulate attacks of falcons on aerial prey. We simulate avian flapping and gliding flight using an analytical quasi-steady model of the aerodynamic forces and moments, parametrized by empirical measurements of flight morphology. The model-birds’ flight control inputs are commanded by their guidance system, comprising a phenomenological model of its vision, guidance, and control. To intercept its prey, model-falcons use the same guidance law as missiles (pure proportional navigation); this assumption is corroborated by empirical data on peregrine falcons hunting lures. We parametrically vary the falcon’s starting position relative to its prey, together with the feedback gain of its guidance loop, under differing assumptions regarding its errors and delay in vision and control, and for three different patterns of prey motion. We find that, when the prey maneuvers erratically, high-altitude stoops increase catch success compared to low-altitude attacks, but only if the falcon’s guidance law is appropriately tuned, and only given a high degree of precision in vision and control. Remarkably, the optimal tuning of the guidance law in our simulations coincides closely with what has been observed empirically in peregrines. High-altitude stoops are shown to be beneficial because their high airspeed enables production of higher aerodynamic forces for maneuvering, and facilitates higher roll agility as the wings are tucked, each of which is essential to catching maneuvering prey at realistic response delays. PMID:29649207

Independent Orbiter Assessment (IOA): Analysis of the guidance, navigation, and control subsystem

NASA Technical Reports Server (NTRS)

Trahan, W. H.; Odonnell, R. A.; Pietz, K. C.; Hiott, J. M.

1986-01-01

The results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) is presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items. To preserve independence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. The independent analysis results corresponding to the Orbiter Guidance, Navigation, and Control (GNC) Subsystem hardware are documented. The function of the GNC hardware is to respond to guidance, navigation, and control software commands to effect vehicle control and to provide sensor and controller data to GNC software. Some of the GNC hardware for which failure modes analysis was performed includes: hand controllers; Rudder Pedal Transducer Assembly (RPTA); Speed Brake Thrust Controller (SBTC); Inertial Measurement Unit (IMU); Star Tracker (ST); Crew Optical Alignment Site (COAS); Air Data Transducer Assembly (ADTA); Rate Gyro Assemblies; Accelerometer Assembly (AA); Aerosurface Servo Amplifier (ASA); and Ascent Thrust Vector Control (ATVC). The IOA analysis process utilized available GNC hardware drawings, workbooks, specifications, schematics, and systems briefs for defining hardware assemblies, components, and circuits. Each hardware item was evaluated and analyzed for possible failure modes and effects. Criticality was assigned based upon the severity of the effect for each failure mode.

Orion Entry Flight Control Stability and Performance

NASA Technical Reports Server (NTRS)

Strahan, Alan L.; Loe, Greg R.; Seiler, Pete

2007-01-01

The Orion Spacecraft will be required to perform entry and landing functions for both Low Earth Orbit (LEO) and Lunar return missions, utilizing only the Command Module (CM) with its unique systems and GN&C design. This paper presents the current CM Flight Control System (FCS) design to support entry and landing, with a focus on analyses that have supported its development to date. The CM FCS will have to provide for spacecraft stability and control while following guidance or manual commands during exo-atmospheric flight, after Service Module separation, translational powered flight required of the CM, atmospheric flight supporting both direct entry and skip trajectories down to drogue chute deploy, and during roll attitude reorientation just prior to touchdown. Various studies and analyses have been performed or are on-going supporting an overall FCS design with reasonably sized Reaction Control System (RCS) jets, that minimizes fuel usage, that provides appropriate command following but with reasonable stability and control margin. Results from these efforts to date are included, with particular attention on design issues that have emerged, such as the struggle to accommodate sub-sonic pitch and yaw control without using excessively large jets that could have a detrimental impact on vehicle weight. Apollo, with a similar shape, struggled with this issue as well. Outstanding CM FCS related design and analysis issues, planned for future effort, are also briefly be discussed.

Direct Fault Tolerant RLV Altitude Control: A Singular Perturbation Approach

NASA Technical Reports Server (NTRS)

Zhu, J. J.; Lawrence, D. A.; Fisher, J.; Shtessel, Y. B.; Hodel, A. S.; Lu, P.; Jackson, Scott (Technical Monitor)

2002-01-01

In this paper, we present a direct fault tolerant control (DFTC) technique, where by "direct" we mean that no explicit fault identification is used. The technique will be presented for the attitude controller (autopilot) for a reusable launch vehicle (RLV), although in principle it can be applied to many other applications. Any partial or complete failure of control actuators and effectors will be inferred from saturation of one or more commanded control signals generated by the controller. The saturation causes a reduction in the effective gain, or bandwidth of the feedback loop, which can be modeled as an increase in singular perturbation in the loop. In order to maintain stability, the bandwidth of the nominal (reduced-order) system will be reduced proportionally according to the singular perturbation theory. The presented DFTC technique automatically handles momentary saturations and integrator windup caused by excessive disturbances, guidance command or dispersions under normal vehicle conditions. For multi-input, multi-output (MIMO) systems with redundant control effectors, such as the RLV attitude control system, an algorithm is presented for determining the direction of bandwidth cutback using the method of minimum-time optimal control with constrained control in order to maintain the best performance that is possible with the reduced control authority. Other bandwidth cutback logic, such as one that preserves the commanded direction of the bandwidth or favors a preferred direction when the commanded direction cannot be achieved, is also discussed. In this extended abstract, a simplistic example is proved to demonstrate the idea. In the final paper, test results on the high fidelity 6-DOF X-33 model with severe dispersions will be presented.

KENNEDY SPACE CENTER, FLA. - The White Room is seen at the upper left where the astronauts enter the Space Shuttle for flight. The Rotating Service Structure has been retracted at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-10

KENNEDY SPACE CENTER, FLA. - The White Room is seen at the upper left where the astronauts enter the Space Shuttle for flight. The Rotating Service Structure has been retracted at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

KENNEDY SPACE CENTER, FLA. - At the KSC Launch Pad 39A, two members of the payload closeout crew check equipment as the doors are just about ready to be closed. The Payload inside the bay of Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-07

KENNEDY SPACE CENTER, FLA. - At the KSC Launch Pad 39A, two members of the payload closeout crew check equipment as the doors are just about ready to be closed. The Payload inside the bay of Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope and provide a reboost to the optimum altitude.

KENNEDY SPACE CENTER, FLA. - The Payload is seen inside of the Bay just before the doors are closed for flight at Pad 39A, Kennedy Space Center, Fla. Discovery, the orbiter for STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-07

KENNEDY SPACE CENTER, FLA. - The Payload is seen inside of the Bay just before the doors are closed for flight at Pad 39A, Kennedy Space Center, Fla. Discovery, the orbiter for STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

KENNEDY SPACE CENTER, FLA. - The Payload is seen inside of the Bay just before the doors are closed for flight at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-07

KENNEDY SPACE CENTER, FLA. - The Payload is seen inside of the Bay just before the doors are closed for flight at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

A Generic Inner-Loop Control Law Structure for Six-Degree-of-Freedom Conceptual Aircraft Design

NASA Technical Reports Server (NTRS)

Cox, Timothy H.; Cotting, M. Christopher

2005-01-01

A generic control system framework for both real-time and batch six-degree-of-freedom simulations is presented. This framework uses a simplified dynamic inversion technique to allow for stabilization and control of any type of aircraft at the pilot interface level. The simulation, designed primarily for the real-time simulation environment, also can be run in a batch mode through a simple guidance interface. Direct vehicle-state acceleration feedback is required with the simplified dynamic inversion technique. The estimation of surface effectiveness within real-time simulation timing constraints also is required. The generic framework provides easily modifiable control variables, allowing flexibility in the variables that the pilot commands. A direct control allocation scheme is used to command aircraft effectors. Primary uses for this system include conceptual and preliminary design of aircraft, when vehicle models are rapidly changing and knowledge of vehicle six-degree-of-freedom performance is required. A simulated airbreathing hypersonic vehicle and simulated high-performance fighter aircraft are used to demonstrate the flexibility and utility of the control system.

A Generic Inner-Loop Control Law Structure for Six-Degree-of-Freedom Conceptual Aircraft Design

NASA Technical Reports Server (NTRS)

Cox, Timothy H.; Cotting, Christopher

2005-01-01

A generic control system framework for both real-time and batch six-degree-of-freedom (6-DOF) simulations is presented. This framework uses a simplified dynamic inversion technique to allow for stabilization and control of any type of aircraft at the pilot interface level. The simulation, designed primarily for the real-time simulation environment, also can be run in a batch mode through a simple guidance interface. Direct vehicle-state acceleration feedback is required with the simplified dynamic inversion technique. The estimation of surface effectiveness within real-time simulation timing constraints also is required. The generic framework provides easily modifiable control variables, allowing flexibility in the variables that the pilot commands. A direct control allocation scheme is used to command aircraft effectors. Primary uses for this system include conceptual and preliminary design of aircraft, when vehicle models are rapidly changing and knowledge of vehicle 6-DOF performance is required. A simulated airbreathing hypersonic vehicle and simulated high-performance fighter aircraft are used to demonstrate the flexibility and utility of the control system.

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

Michael Schmitt; Juan Deaton; Curt Papke

In the event of large-scale natural or manmade catastrophic events, access to reliable and enduring commercial communication systems is critical. Hurricane Katrina provided a recent example of the need to ensure communications during a national emergency. To ensure that communication demands are met during these critical times, Idaho National Laboratory (INL) under the guidance of United States Strategic Command has studied infrastructure issues, concerns, and vulnerabilities associated with an airborne wireless communications capability. Such a capability could provide emergency wireless communications until public/commercial nodes can be systematically restored. This report focuses on the airborne cellular restoration concept; analyzing basic infrastructuremore » requirements; identifying related infrastructure issues, concerns, and vulnerabilities and offers recommended solutions.« less

Radio astronomy Explorer-B in-flight mission control system development effort

NASA Technical Reports Server (NTRS)

Lutsky, D. A.; Bjorkman, W. S.; Uphoff, C.

1973-01-01

A description is given of the development for the Mission Analysis Evaluation and Space Trajectory Operations (MAESTRO) program to be used for the in-flight decision making process during the translunar and lunar orbit adjustment phases of the flight of the Radio Astronomy Explorer-B. THe program serves two functions: performance and evaluation of preflight mission analysis, and in-flight support for the midcourse and lunar insertion command decisions that must be made by the flight director. The topics discussed include: analysis of program and midcourse guidance capabilities; methods for on-line control; printed displays of the MAESTRO program; and in-flight operational logistics and testing.

Nonlinear system guidance in the presence of transmission zero dynamics

NASA Technical Reports Server (NTRS)

Meyer, G.; Hunt, L. R.; Su, R.

1995-01-01

An iterative procedure is proposed for computing the commanded state trajectories and controls that guide a possibly multiaxis, time-varying, nonlinear system with transmission zero dynamics through a given arbitrary sequence of control points. The procedure is initialized by the system inverse with the transmission zero effects nulled out. Then the 'steady state' solution of the perturbation model with the transmission zero dynamics intact is computed and used to correct the initial zero-free solution. Both time domain and frequency domain methods are presented for computing the steady state solutions of the possibly nonminimum phase transmission zero dynamics. The procedure is illustrated by means of linear and nonlinear examples.

An integrated autonomous rendezvous and docking system architecture using Centaur modern avionics

NASA Technical Reports Server (NTRS)

Nelson, Kurt

1991-01-01

The avionics system for the Centaur upper stage is in the process of being modernized with the current state-of-the-art in strapdown inertial guidance equipment. This equipment includes an integrated flight control processor with a ring laser gyro based inertial guidance system. This inertial navigation unit (INU) uses two MIL-STD-1750A processors and communicates over the MIL-STD-1553B data bus. Commands are translated into load activation through a Remote Control Unit (RCU) which incorporates the use of solid state relays. Also, a programmable data acquisition system replaces separate multiplexer and signal conditioning units. This modern avionics suite is currently being enhanced through independent research and development programs to provide autonomous rendezvous and docking capability using advanced cruise missile image processing technology and integrated GPS navigational aids. A system concept was developed to combine these technologies in order to achieve a fully autonomous rendezvous, docking, and autoland capability. The current system architecture and the evolution of this architecture using advanced modular avionics concepts being pursued for the National Launch System are discussed.

Preliminary design features of the RASCAL - A NASA/Army rotorcraft in-flight simulator

NASA Technical Reports Server (NTRS)

Aiken, Edwin W.; Jacobsen, Robert A.; Eshow, Michelle M.; Hindson, William S.; Doane, Douglas H.

1992-01-01

Salient design features of a new NASA/Army research rotorcraft - the Rotorcraft Aircrew Systems Concepts Airborne Laboratory (RASCAL) - are described. Using a UH-60A Black Hawk helicopter as a baseline vehicle, the RASCAL will be a flying laboratory capable of supporting the research requirements of major NASA and Army guidance, control, and display research programs. The paper describes the research facility requirements of these programs together with other critical constraints on the design of the research system, including safety-of-flight. Research program schedules demand a phased development approach, wherein specific research capability milestones are met and flight research projects are flown throughout the complete development cycle of the RASCAL. This development approach is summarized, and selected features of the research system are described. The research system includes a full-authority, programmable, fault-tolerant/fail-safe, fly-by-wire flight control system and a real-time obstacle detection and avoidance system which will generate low-latitude guidance commands to the pilot on a wide field-of-view, color helmet-mounted display.

A high-fidelity, six-degree-of-freedom batch simulation environment for tactical guidance research and evaluation

NASA Technical Reports Server (NTRS)

Goodrich, Kenneth H.

1993-01-01

A batch air combat simulation environment, the tactical maneuvering simulator (TMS), is presented. The TMS is a tool for developing and evaluating tactical maneuvering logics, but it can also be used to evaluate the tactical implications of perturbations to aircraft performance or supporting systems. The TMS can simulate air combat between any number of engagement participants, with practical limits imposed by computer memory and processing power. Aircraft are modeled using equations of motion, control laws, aerodynamics, and propulsive characteristics equivalent to those used in high-fidelity piloted simulations. Data bases representative of a modern high-performance aircraft with and without thrust-vectoring capability are included. To simplify the task of developing and implementing maneuvering logics in the TMS, an outer-loop control system, the tactical autopilot (TA), is implemented in the aircraft simulation model. The TA converts guidance commands by computerized maneuvering logics from desired angle of attack and wind-axis bank-angle inputs to the inner loop control augmentation system of the aircraft. The capabilities and operation of the TMS and the TA are described.

Technology transfer: Imaging tracker to robotic controller

NASA Technical Reports Server (NTRS)

Otaguro, M. S.; Kesler, L. O.; Land, Ken; Erwin, Harry; Rhoades, Don

1988-01-01

The transformation of an imaging tracker to a robotic controller is described. A multimode tracker was developed for fire and forget missile systems. The tracker locks on to target images within an acquisition window using multiple image tracking algorithms to provide guidance commands to missile control systems. This basic tracker technology is used with the addition of a ranging algorithm based on sizing a cooperative target to perform autonomous guidance and control of a platform for an Advanced Development Project on automation and robotics. A ranging tracker is required to provide the positioning necessary for robotic control. A simple functional demonstration of the feasibility of this approach was performed and described. More realistic demonstrations are under way at NASA-JSC. In particular, this modified tracker, or robotic controller, will be used to autonomously guide the Man Maneuvering Unit (MMU) to targets such as disabled astronauts or tools as part of the EVA Retriever efforts. It will also be used to control the orbiter's Remote Manipulator Systems (RMS) in autonomous approach and positioning demonstrations. These efforts will also be discussed.

Preliminary design features of the RASCAL: A NASA /Army rotorcraft in-flight simulator

NASA Technical Reports Server (NTRS)

Aiken, Edwin W.; Jacobsen, Robert A.; Eshow, Michelle M.; Hindson, William S.; Doane, Douglas H.

1993-01-01

Salient design features of a new NASA/Army research rotorcraft - the Rotorcraft-Aircrew Systems Concepts Airborne Laboratory (RASCAL) - are described. Using a UH-60A Black Hawk helicopter as a baseline vehicle, the RASCAL will be a flying laboratory capable of supporting the research requirements of major NASA and Army guidance, control, and display research programs. The paper describes the research facility requirements of these programs together with other critical constraints on the design of the research system, including safety-of-flight. Research program schedules demand a phased development approach, wherein specific research capability milestones are met and flight research projects are flown throughout the complete development cycle of the RASCAL. This development approach is summarized, and selected features of the research system are described. The research system includes a full-authority, programmable, fault-tolerant/fail-safe, fly-by-wire flight control system and a real-time obstacle detection and avoidance system which will generate low-altitude guidance commands to the pilot on a wide field-of-view, color helmet-mounted display.

An adaptive guidance algorithm for an aerodynamically assisted orbital plane change maneuver. M.S. Thesis

NASA Technical Reports Server (NTRS)

Blissit, J. A.

1986-01-01

Using analysis results from the post trajectory optimization program, an adaptive guidance algorithm is developed to compensate for density, aerodynamic and thrust perturbations during an atmospheric orbital plane change maneuver. The maneuver offers increased mission flexibility along with potential fuel savings for future reentry vehicles. Although designed to guide a proposed NASA Entry Research Vehicle, the algorithm is sufficiently generic for a range of future entry vehicles. The plane change analysis provides insight suggesting a straight-forward algorithm based on an optimized nominal command profile. Bank angle, angle of attack, and engine thrust level, ignition and cutoff times are modulated to adjust the vehicle's trajectory to achieve the desired end-conditions. A performance evaluation of the scheme demonstrates a capability to guide to within 0.05 degrees of the desired plane change and five nautical miles of the desired apogee altitude while maintaining heating constraints. The algorithm is tested under off-nominal conditions of + or -30% density biases, two density profile models, + or -15% aerodynamic uncertainty, and a 33% thrust loss and for various combinations of these conditions.

Design, Implementation and Evaluation of an Indoor Navigation System for Visually Impaired People

PubMed Central

Martinez-Sala, Alejandro Santos; Losilla, Fernando; Sánchez-Aarnoutse, Juan Carlos; García-Haro, Joan

2015-01-01

Indoor navigation is a challenging task for visually impaired people. Although there are guidance systems available for such purposes, they have some drawbacks that hamper their direct application in real-life situations. These systems are either too complex, inaccurate, or require very special conditions (i.e., rare in everyday life) to operate. In this regard, Ultra-Wideband (UWB) technology has been shown to be effective for indoor positioning, providing a high level of accuracy and low installation complexity. This paper presents SUGAR, an indoor navigation system for visually impaired people which uses UWB for positioning, a spatial database of the environment for pathfinding through the application of the A* algorithm, and a guidance module. The interaction with the user takes place using acoustic signals and voice commands played through headphones. The suitability of the system for indoor navigation has been verified by means of a functional and usable prototype through a field test with a blind person. In addition, other tests have been conducted in order to show the accuracy of different relevant parts of the system. PMID:26703610

Helicopter approach capability using the differential global positioning system. M.S. Thesis

NASA Technical Reports Server (NTRS)

Kaufmann, David N.

1993-01-01

The results of flight tests to determine the feasibility of using the Global Positioning System (GPS) in the differential mode (DGPS) to provide high accuracy, precision navigation, and guidance for helicopter approaches to landing are presented. The airborne DGPS receiver and associated equipment is installed in a NASA UH-60 Black Hawk helicopter. The ground-based DGPS reference receiver is located at a surveyed test site and is equipped with a real-time VHF data link to transmit correction information to the airborne DGPS receiver. The corrected airborne DGPS information, together with the preset approach geometry, is used to calculate guidance commands which are sent to the aircraft's approach guidance instruments. The use of DGPS derived guidance for helicopter approaches to landing is evaluated by comparing the DGPS data with the laser tracker truth data. Both standard (3 deg) and steep (6 deg and 9 deg) glideslope straight-in approaches were flown. DGPS positioning accuracy based on a time history analysis of the entire approach was 0.2 m (mean) +/- 1.8 m (2 sigma) laterally and -2.0 m (mean) +/- 3.5 m (2 sigma) vertically for 3 deg glideslope approaches, -0.1 m (mean) +/- 1.5 m (2 sigma) laterally and -1.1 m (mean) +/- 3.5 m (2 sigma) vertically for 6 deg glideslope approaches and 0.2 m (mean) +/- 1.3 m (2 sigma) laterally and -1.0 m (mean) +/- 2.8 m (2 sigma) vertically for 9 deg glideslope approaches. DGPS positioning accuracy at the 200 ft decision height (DH) on a standard 3 deg slideslope approach was 0.3 m (mean) +/- 1.5 m (2 sigma) laterally and -2.3 m (mean) +/- 1.6 m (2 sigma) vertically. These errors indicate that the helicopter position based on DGPS guidance satisfies the International Civil Aviation Organization (ICAO) Category 1 (CAT 1) lateral and vertical navigational accuracy requirements.

Helicopter approach capability using the differential Global Positioning System

NASA Technical Reports Server (NTRS)

Kaufmann, David N.

1993-01-01

The results of flight tests to determine the feasibility of using the Global Positioning System (GPS) in the differential mode (DGPS) to provide high accuracy, precision navigation and guidance for helicopter approaches to landing are presented. The airborne DGPS receiver and associated equipment is installed in a NASA UH-60 Black Hawk helicopter. The ground-based DGPS reference receiver is located at a surveyed test site and is equipped with a real-time VHF data link to transmit correction information to the airborne DGPS receiver. The corrected airborne DGPS information, together with the preset approach geometry, is used to calculate guidance commands which are sent to the aircraft's approach guidance instruments. The use of DGPS derived guidance for helicopter approaches to landing is evaluated by comparing the DGPS data with the laser tracker truth data. Both standard (3 degrees) and steep (6 degrees and 9 degrees) glidescope straight-in approaches were flown. DGPS positioning accuracy based on a time history analysis of the entire approach was 0.2 m (mean) +/- 1.8 m (2 sigma) laterally and -2.0 m (mean) +/- 3.5 m (2 sigma) vertically for 3 degree glidescope approaches, -0.1 m (mean) +/- 1.5 m (2 sigma) laterally and -1.1 m (mean) +/- 3.5 m (2 sigma) vertically for 6 degree glidescope approaches, and 0.2 m (mean) +/- 1.3 m (2 sigma) laterally and -1.0 m (mean) +/- 2.8 (2 sigma) vertically for 9 degree glidescope approaches. DGPS positioning accuracy at the 200 ft decision height on a standard 3 degree glidescope approach was 0.3 m (mean) +/- 1.5 m (2 sigma) laterally and -2.3 m (mean) +/- 1.6 m (2 sigma) vertically. These errors indicate that the helicopter position based on DGPS guidance satisfies the International Civil Aviation Organization Category 1 lateral and vertical accuracy requirements.

Singularity-free extraction of a quaternion from a direction-cosine matrix. [for spacecraft control and guidance

NASA Technical Reports Server (NTRS)

Klumpp, A. R.

1976-01-01

A computer algorithm for extracting a quaternion from a direction-cosine matrix (DCM) is described. The quaternion provides a four-parameter representation of rotation, as against the nine-parameter representation afforded by a DCM. Commanded attitude in space shuttle steering is conveniently computed by DCM, while actual attitude is computed most compactly as a quaternion, as is attitude error. The unit length of the rotation quaternion, and interchangeable of a quaternion and its negative, are used to advantage in the extraction algorithm. Protection of the algorithm against square root failure and division overflow are considered. Necessary and sufficient conditions for handling the rotation vector element of largest magnitude are discussed

Saturn Apollo Program

NASA Image and Video Library

1967-03-01

The Saturn V configuration is shown in inches and meters as illustrated by the Boeing Company. The Saturn V vehicle consisted of three stages: the S-IC (first) stage powered by five F-1 engines, the S-II (second) stage powered by five J-2 engines, the S-IVB (third) stage powered by one J-2 engine. A top for the first three stages was designed to contain the instrument unit, the guidance system, the Apollo spacecraft, and the escape system. The Apollo spacecraft consisted of the lunar module, the service module, and the command module. The Saturn V was designed perform lunar and planetary missions and it was capable of placing 280,000 pounds into Earth orbit.

OAO-3 end of mission tests report

NASA Technical Reports Server (NTRS)

Kalil, F.; Kull, F. J.; Mcintosh, R.; Ollendorf, S.; Margolies, D. L.; Gemmell, J.; Tasevoli, C. M.; Polidan, R. S.; Kochevar, H.; Chapman, C.

1981-01-01

Twelve engineering type tests were performed on several subsystems and experiment(s) of the OAO 3 spacecraft near its end of mission. The systems tested include: Princeton experiment package (PEP), fine error system guidance, inertial reference unit, star trackers, heat pipes, thermal control coatings, command and data handling, solar array; batteries, and onboard processor/power boost regulator. Generally, the systems performed well for the 8 1/2 years life of OAO 3, although some degradation was noted in the sensitivity of PEP and in the absorptivity of the skin coatings. Battery life was prolonged during the life of the mission in large part by carefully monitoring the charge-discharge cycle with careful attention not to overcharge.

Wide Field X-Ray Telescope Mission Concept Study Results

NASA Technical Reports Server (NTRS)

Hopkins, R. C.; Thomas, H. D.; Fabisinski, L. L.; Baysinger, M.; Hornsby, L. S.; Maples, C. D.; Purlee, T. E.; Capizzo, P. D.; Percy, T. K.

2014-01-01

The Wide Field X-Ray Telescope (WFXT) is an astrophysics mission concept for detecting and studying extra-galactic x-ray sources, including active galactic nuclei and clusters of galaxies, in an effort to further understand cosmic evolution and structure. This Technical Memorandum details the results of a mission concept study completed by the Advanced Concepts Office at NASA Marshall Space Flight Center in 2012. The design team analyzed the mission and instrument requirements, and designed a spacecraft that enables the WFXT mission while using high heritage components. Design work included selecting components and sizing subsystems for power, avionics, guidance, navigation and control, propulsion, structures, command and data handling, communications, and thermal control.

IntelliTable: Inclusively-Designed Furniture with Robotic Capabilities.

PubMed

Prescott, Tony J; Conran, Sebastian; Mitchinson, Ben; Cudd, Peter

2017-01-01

IntelliTable is a new proof-of-principle assistive technology system with robotic capabilities in the form of an elegant universal cantilever table able to move around by itself, or under user control. We describe the design and current capabilities of the table and the human-centered design methodology used in its development and initial evaluation. The IntelliTable study has delivered robotic platform programmed by a smartphone that can navigate around a typical home or care environment, avoiding obstacles, and positioning itself at the user's command. It can also be configured to navigate itself to pre-ordained places positions within an environment using ceiling tracking, responsive optical guidance and object-based sonar navigation.

Users manual for flight control design programs

NASA Technical Reports Server (NTRS)

Nalbandian, J. Y.

1975-01-01

Computer programs for the design of analog and digital flight control systems are documented. The program DIGADAPT uses linear-quadratic-gaussian synthesis algorithms in the design of command response controllers and state estimators, and it applies covariance propagation analysis to the selection of sampling intervals for digital systems. Program SCHED executes correlation and regression analyses for the development of gain and trim schedules to be used in open-loop explicit-adaptive control laws. A linear-time-varying simulation of aircraft motions is provided by the program TVHIS, which includes guidance and control logic, as well as models for control actuator dynamics. The programs are coded in FORTRAN and are compiled and executed on both IBM and CDC computers.

Preliminary Assessment of Optimal Longitudinal-Mode Control for Drag Reduction through Distributed Aeroelastic Shaping

NASA Technical Reports Server (NTRS)

Ippolito, Corey; Nguyen, Nhan; Lohn, Jason; Dolan, John

2014-01-01

The emergence of advanced lightweight materials is resulting in a new generation of lighter, flexible, more-efficient airframes that are enabling concepts for active aeroelastic wing-shape control to achieve greater flight efficiency and increased safety margins. These elastically shaped aircraft concepts require non-traditional methods for large-scale multi-objective flight control that simultaneously seek to gain aerodynamic efficiency in terms of drag reduction while performing traditional command-tracking tasks as part of a complete guidance and navigation solution. This paper presents results from a preliminary study of a notional multi-objective control law for an aeroelastic flexible-wing aircraft controlled through distributed continuous leading and trailing edge control surface actuators. This preliminary study develops and analyzes a multi-objective control law derived from optimal linear quadratic methods on a longitudinal vehicle dynamics model with coupled aeroelastic dynamics. The controller tracks commanded attack-angle while minimizing drag and controlling wing twist and bend. This paper presents an overview of the elastic aircraft concept, outlines the coupled vehicle model, presents the preliminary control law formulation and implementation, presents results from simulation, provides analysis, and concludes by identifying possible future areas for research

Flight tests of the 4D flight guidance display

NASA Astrophysics Data System (ADS)

Below, Christian; von Viebahn, Harro; Purpus, Matthias

1997-06-01

A perspective primary flight and a navigation display format were evaluated in a flying testbed. The flight tests comprised ILS- and standard approaches as well as low level operations utilizing the depiction of a spatial channel, and demonstrations of the inherent ground proximity warning function. In the cockpit of the VFW614, the left seat was equipped with a sidestick and a flat panel display, which showed both the 4D-display an the Navigation Display format. Airline and airforce pilots flew several missions each. Although most of the pilots criticizes that a typical flight director commanding the aircraft's attitude was missing, they could follow the channel precisely. However, some airline pilots stated a lack of vertical guidance information during the final approach. Leaving and re- entering the channel could be easily accomplished form any direction. In summary pilots' assessment of the display concept yielded an overall improvement of SA. In particular it was stated that displays are an appropriate means to avoid CFIT accidents. With the fist prototypes of 3D- graphics generators designed for avionics available the flight evaluation will continue including feasibility demonstrations of high-performance graphics for civil and military aircraft applications.

NGST fine guidance sensor

NASA Astrophysics Data System (ADS)

Rowlands, Neil; Hutchings, John; Murowinski, Richard G.; Alexander, Russ

2003-03-01

Instrumentation for the Next Generation Space Telescope (NGST) is currently in the Phase A definition stage. We have developed a concept for the NGST Fine Guidance Sensor or FGS. The FGS is a detector array based imager which resides in the NGST focal plane. We report here on tradeoff studies aimed at defining an overall configuration of the FGS which will meet the performance and interface requirements. A key performance requirement is a noise equivalent angle of 3 milli-arcseconds to be achieved with 95% probability for any pointing of the observatory in the celestial sphere. A key interface requirement is compatibility with the architecture of the Integrated Science Instrument Module (ISIM). The concept developed consists of two independent and redundant FGS modules, each with a 4' x 2' field of view covered by two 2048 x 2048 infrared detector arrays, providing 60 milli-arcsecond sampling. Performance modeling supporting the choice of this architecture and the trade space considered is presented. Each module has a set of readout electronics which perform star detection, pixel-by-pixel correction, and in fine guiding mode, centroid calculation. These readout electronics communicate with the ISIM Command &Data Handling Units where the FGS control software is based. Rationale for this choice of architecture is also presented.

Priorities for a 21st-century defense: aligning u.s. Army environmental science and engineering officer resources with the department of defense strategic guidance.

PubMed

Licina, Derek; Rufolo, Dennis; Story, Mike

2013-01-01

The recently published Department of Defense (DoD) strategic guidance highlights the need to ?shape a joint force for the future.? Supporting requirements to shape the joint force while the overall DoD force structure is reduced will be challenging. Fortunately, based on its unique training and experience, the Army Environmental Science and Engineering Officer (ESEO) profession is positioned today to fill anticipated joint public health requirements. Obtaining the U.S. Army Medical Department (AMEDD) approval to meet these requirements will have near-term consequences for the ESEO profession as some existing (albeit antiquated) authorizations may go unfilled. However, long-term dividends for the Medical Service Corps (MSC), AMEDD, Army, and DoD will be achieved by realigning critical resources to future joint and interagency requirements. Assigning ESEOs now to organizations such as the Theater Special Operations Commands (TSOCs), U.S. Agency for International Development (USAID), and the North Atlantic Treaty Organization (NATO) with perceived and real joint force health protection/public health requirements through unique means will ensure our profession remains relevant today and supports the joint force of tomorrow. 2013.

Detection technique of targets for missile defense system

NASA Astrophysics Data System (ADS)

Guo, Hua-ling; Deng, Jia-hao; Cai, Ke-rong

2009-11-01

Ballistic missile defense system (BMDS) is a weapon system for intercepting enemy ballistic missiles. It includes ballistic-missile warning system, target discrimination system, anti-ballistic-missile guidance systems, and command-control communication system. Infrared imaging detection and laser imaging detection are widely used in BMDS for surveillance, target detection, target tracking, and target discrimination. Based on a comprehensive review of the application of target-detection techniques in the missile defense system, including infrared focal plane arrays (IRFPA), ground-based radar detection technology, 3-dimensional imaging laser radar with a photon counting avalanche photodiode (APD) arrays and microchip laser, this paper focuses on the infrared and laser imaging detection techniques in missile defense system, as well as the trends for their future development.

Discovery with RSS retracted

NASA Technical Reports Server (NTRS)

1997-01-01

The Rotating Service Structure has been retracted at Pad 39A. Discovery, the Space Shuttle for STS-82 Mission is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) Which will be installed, the Fine Guidance Sensor #1 (FGS-1) and the Space Telescope Imaging Spectrograph (STIS) which will be installed. STS-82 will launch with a crew of seven at 3:54 a.m. February 11, 1997. The launch window is 65 minutes. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope and provide a reboost to the optimum altitude.

Guidance and Control of a Small Unmanned Aerial Vehicle and Autonomous Flight Experiments

NASA Astrophysics Data System (ADS)

Fujinaga, Jin; Tokutake, Hiroshi; Sunada, Shigeru

This paper describes the development of a fixed-wing small-size UAV and the design of its flight controllers. The developed UAV’s wing span is 0.6m, and gross weight is 0.27kg. In order to ensure robust performances of the longitudinal and lateral-directional motions of the UAV, flight controllers are designed for these motions with μ-synthesis. Numerical simulations show that the designed controllers attain good robust stabilities and performances, and have good tracking performance for command. After an order-reduction and discretization, the designed flight controllers were implemented in the UAV. A flight test was performed, and the ability of the UAV to fly autonomously, passing over waypoints, was demonstrated.

Application of Incident Command Structure to clinical trial management in the academic setting: principles and lessons learned.

PubMed

Reynolds, Penny S; Michael, Mary J; Spiess, Bruce D

2017-02-09

Clinical trial success depends on appropriate management, but practical guidance to trial organisation and planning is lacking. The Incident Command System (ICS) is the 'gold standard' management system developed for managing diverse operations in major incident and public health arenas. It enables effective and flexible management through integration of personnel, procedures, resources, and communications within a common hierarchical organisational structure. Conventional ICS organisation consists of five function modules: Command, Planning, Operations, Logistics, and Finance/Administration. Large clinical trials will require a separate Regulatory Administrative arm, and an Information arm, consisting of dedicated data management and information technology staff. We applied ICS principles to organisation and management of the Prehospital Use of Plasma in Traumatic Haemorrhage (PUPTH) trial. This trial was a multidepartmental, multiagency, randomised clinical trial investigating prehospital administration of thawed plasma on mortality and coagulation response in severely injured trauma patients. We describe the ICS system as it would apply to large clinical trials in general, and the benefits, barriers, and lessons learned in utilising ICS principles to reorganise and coordinate the PUPTH trial. Without a formal trial management structure, early stages of the trial were characterised by inertia and organisational confusion. Implementing ICS improved organisation, coordination, and communication between multiple agencies and service groups, and greatly streamlined regulatory compliance administration. However, unfamiliarity of clinicians with ICS culture, conflicting resource allocation priorities, and communication bottlenecks were significant barriers. ICS is a flexible and powerful organisational tool for managing large complex clinical trials. However, for successful implementation the cultural, psychological, and social environment of trial participants must be accounted for, and personnel need to be educated in the basics of ICS. ClinicalTrials.gov, NCT02303964 . Registered on 28 November 2014.

Search and Determine Integrated Environment (SADIE)

NASA Astrophysics Data System (ADS)

Sabol, C.; Schumacher, P.; Segerman, A.; Coffey, S.; Hoskins, A.

2012-09-01

A new and integrated high performance computing software applications package called the Search and Determine Integrated Environment (SADIE) is being jointly developed and refined by the Air Force and Naval Research Laboratories (AFRL and NRL) to automatically resolve uncorrelated tracks (UCTs) and build a more complete space object catalog for improved Space Situational Awareness (SSA). The motivation for SADIE is to respond to very challenging needs identified and guidance received from Air Force Space Command (AFSPC) and other senior leaders to develop this technology to support the evolving Joint Space Operations Center (JSpOC) and Alternate Space Control Center (ASC2)-Dahlgren. The JSpOC and JMS SSA mission requirements and threads flow down from the United States Strategic Command (USSTRATCOM). The SADIE suite includes modification and integration of legacy applications and software components that include Search And Determine (SAD), Satellite Identification (SID), and Parallel Catalog (Parcat), as well as other utilities and scripts to enable end-to-end catalog building and maintenance in a parallel processing environment. SADIE is being developed to handle large catalog building challenges in all orbit regimes and includes the automatic processing of radar, fence, and optical data. Real data results are provided for the processing of Air Force Space Surveillance System fence observations and for the processing of Space Surveillance Telescope optical data.

Accelerated Training at Mach 20: A Brief Communication Submitted from the International Space Station

NASA Technical Reports Server (NTRS)

Foale, C. Michael; Kaleri, Alexander Y.; Sargsyan, Ashot E.; Hamilton, Douglas R.; Melton, Shannon; Martin, David; Dulchavsky, Scott A.

2004-01-01

The performance of complex tasks on the International Space Station (ISS) requires significant preflight crew training commitments and frequent skill and knowledge refreshment. This report documents a recently developed just-in-time training methodology, which integrates preflight hardware familiarization and procedure training with an on-orbit CD-ROM-based skill enhancement. This just-in-time concept was used to support real-time remote expert guidance to complete medical examinations using the ISS Human Research Facility (HRF). An American and Russian ISS crewmember received 2-hours of hands on ultrasound training 8 months prior to the on-orbit ultrasound exam. A CD-ROM-based Onboard Proficiency Enhancement (OPE) interactive multimedia program consisting of memory enhancing tutorials, and skill testing exercises, was completed by the crewmember six days prior to the on-orbit ultrasound exam. The crewmember was then remotely guided through a thoracic, vascular, and echocardiographic examination by ultrasound imaging experts. Results of the CD ROM based OPE session were used to modify the instructions during a complete 35 minute real-time thoracic, cardiac, and carotid/jugular ultrasound study. Following commands from the ground-based expert, the crewmember acquired all target views and images without difficulty. The anatomical content and fidelity of ultrasound video were excellent and adequate for clinical decision-making. Complex ultrasound experiments with expert guidance were performed with high accuracy following limited pre-flight training and CD-ROM-based in-flight review, despite a 2-second communication latency. In-flight application of multimedia proficiency enhancement software, coupled with real-time remote expert guidance, can facilitate the performance of complex demanding tasks.

KSC-01pp1481

NASA Image and Video Library

2001-08-10

KENNEDY SPACE CENTER, Fla. - Expedition Three crew member Vladimir Dezhurov (left) is ready for his first space flight, under the guidance of STS-105 Commander Scott Horowitz (center). Helping with flight equipment before launch is (right) USA Mechanical Technician Al Schmidt. The payload on the STS-105 mission to the International Space Station includes the third flight of the Italian-built Multi-Purpose Logistics Module Leonardo, delivering additional scientific racks, equipment and supplies for the Space Station, and the Early Ammonia Servicer (EAS) tank. The EAS, which will be attached to the Station during two spacewalks, contains spare ammonia for the Station’s cooling system. Also, the Expedition Three crew is aboard to replace the Expedition Two crew on the International Space Station, who will be returning to Earth aboard Discovery after a five-month stay on the Station

Ares I Static Tests Design

NASA Technical Reports Server (NTRS)

Carson, William; Lindemuth, Kathleen; Mich, John; White, K. Preston; Parker, Peter A.

2009-01-01

Probabilistic engineering design enhances safety and reduces costs by incorporating risk assessment directly into the design process. In this paper, we assess the format of the quantitative metrics for the vehicle which will replace the Space Shuttle, the Ares I rocket. Specifically, we address the metrics for in-flight measurement error in the vector position of the motor nozzle, dictated by limits on guidance, navigation, and control systems. Analyses include the propagation of error from measured to derived parameters, the time-series of dwell points for the duty cycle during static tests, and commanded versus achieved yaw angle during tests. Based on these analyses, we recommend a probabilistic template for specifying the maximum error in angular displacement and radial offset for the nozzle-position vector. Criteria for evaluating individual tests and risky decisions also are developed.

Evaluation of a Guideline by Formal Modelling of Cruise Control System in Event-B

NASA Technical Reports Server (NTRS)

Yeganefard, Sanaz; Butler, Michael; Rezazadeh, Abdolbaghi

2010-01-01

Recently a set of guidelines, or cookbook, has been developed for modelling and refinement of control problems in Event-B. The Event-B formal method is used for system-level modelling by defining states of a system and events which act on these states. It also supports refinement of models. This cookbook is intended to systematize the process of modelling and refining a control problem system by distinguishing environment, controller and command phenomena. Our main objective in this paper is to investigate and evaluate the usefulness and effectiveness of this cookbook by following it throughout the formal modelling of cruise control system found in cars. The outcomes are identifying the benefits of the cookbook and also giving guidance to its future users.

A microprocessor-based position control system for a telescope secondary mirror

NASA Technical Reports Server (NTRS)

Lorell, K. R.; Barrows, W. F.; Clappier, R. R.; Lee, G. K.

1983-01-01

The pointing requirements for the Shuttle IR Telescope Facility (SIRTF), which consists of an 0.85-m cryogenically cooled IR telescope, call for an image stability of 0.25 arcsec. Attention is presently given to a microprocessor-based position control system developed for the control of the SIRTF secondary mirror, employing a special control law (to minimize energy dissipation), a precision capacitive position sensor, and a specially designed power amplifier/actuator combination. The microprocessor generates the command angular position and rate waveforms in order to maintain a 90 percent dwell time/10 percent transition time ratio independently of chop frequency or amplitude. Performance and test results of a prototype system designed for use with a demonstration model of the SIRTF focal plane fine guidance sensor are presented.

Design of Launch Vehicle Flight Control Systems Using Ascent Vehicle Stability Analysis Tool

NASA Technical Reports Server (NTRS)

Jang, Jiann-Woei; Alaniz, Abran; Hall, Robert; Bedossian, Nazareth; Hall, Charles; Jackson, Mark

2011-01-01

A launch vehicle represents a complicated flex-body structural environment for flight control system design. The Ascent-vehicle Stability Analysis Tool (ASAT) is developed to address the complicity in design and analysis of a launch vehicle. The design objective for the flight control system of a launch vehicle is to best follow guidance commands while robustly maintaining system stability. A constrained optimization approach takes the advantage of modern computational control techniques to simultaneously design multiple control systems in compliance with required design specs. "Tower Clearance" and "Load Relief" designs have been achieved for liftoff and max dynamic pressure flight regions, respectively, in the presence of large wind disturbances. The robustness of the flight control system designs has been verified in the frequency domain Monte Carlo analysis using ASAT.

Automated design and optimization of flexible booster autopilots via linear programming, volume 1

NASA Technical Reports Server (NTRS)

Hauser, F. D.

1972-01-01

A nonlinear programming technique was developed for the automated design and optimization of autopilots for large flexible launch vehicles. This technique, which resulted in the COEBRA program, uses the iterative application of linear programming. The method deals directly with the three main requirements of booster autopilot design: to provide (1) good response to guidance commands; (2) response to external disturbances (e.g. wind) to minimize structural bending moment loads and trajectory dispersions; and (3) stability with specified tolerances on the vehicle and flight control system parameters. The method is applicable to very high order systems (30th and greater per flight condition). Examples are provided that demonstrate the successful application of the employed algorithm to the design of autopilots for both single and multiple flight conditions.

Visual guidance in control of grasping.

PubMed

Janssen, Peter; Scherberger, Hansjörg

2015-07-08

Humans and other primates possess a unique capacity to grasp and manipulate objects skillfully, a facility pervasive in everyday life that has undoubtedly contributed to the success of our species. When we reach and grasp an object, various cortical areas in the parietal and frontal lobes work together effortlessly to analyze object shape and position, transform this visual information into useful motor commands, and implement these motor representations to preshape the hand before contact with the object is made. In recent years, a growing number of studies have investigated the neural circuits underlying object grasping in both the visual and motor systems of the macaque monkey. The accumulated knowledge not only helps researchers understand how object grasping is implemented in the primate brain but may also contribute to the development of novel neural interfaces and neuroprosthetics.

Computer architecture for efficient algorithmic executions in real-time systems: New technology for avionics systems and advanced space vehicles

NASA Technical Reports Server (NTRS)

Carroll, Chester C.; Youngblood, John N.; Saha, Aindam

1987-01-01

Improvements and advances in the development of computer architecture now provide innovative technology for the recasting of traditional sequential solutions into high-performance, low-cost, parallel system to increase system performance. Research conducted in development of specialized computer architecture for the algorithmic execution of an avionics system, guidance and control problem in real time is described. A comprehensive treatment of both the hardware and software structures of a customized computer which performs real-time computation of guidance commands with updated estimates of target motion and time-to-go is presented. An optimal, real-time allocation algorithm was developed which maps the algorithmic tasks onto the processing elements. This allocation is based on the critical path analysis. The final stage is the design and development of the hardware structures suitable for the efficient execution of the allocated task graph. The processing element is designed for rapid execution of the allocated tasks. Fault tolerance is a key feature of the overall architecture. Parallel numerical integration techniques, tasks definitions, and allocation algorithms are discussed. The parallel implementation is analytically verified and the experimental results are presented. The design of the data-driven computer architecture, customized for the execution of the particular algorithm, is discussed.

Computer architecture for efficient algorithmic executions in real-time systems: new technology for avionics systems and advanced space vehicles

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

Carroll, C.C.; Youngblood, J.N.; Saha, A.

1987-12-01

Improvements and advances in the development of computer architecture now provide innovative technology for the recasting of traditional sequential solutions into high-performance, low-cost, parallel system to increase system performance. Research conducted in development of specialized computer architecture for the algorithmic execution of an avionics system, guidance and control problem in real time is described. A comprehensive treatment of both the hardware and software structures of a customized computer which performs real-time computation of guidance commands with updated estimates of target motion and time-to-go is presented. An optimal, real-time allocation algorithm was developed which maps the algorithmic tasks onto the processingmore » elements. This allocation is based on the critical path analysis. The final stage is the design and development of the hardware structures suitable for the efficient execution of the allocated task graph. The processing element is designed for rapid execution of the allocated tasks. Fault tolerance is a key feature of the overall architecture. Parallel numerical integration techniques, tasks definitions, and allocation algorithms are discussed. The parallel implementation is analytically verified and the experimental results are presented. The design of the data-driven computer architecture, customized for the execution of the particular algorithm, is discussed.« less

Latency in Visionic Systems: Test Methods and Requirements

NASA Technical Reports Server (NTRS)

Bailey, Randall E.; Arthur, J. J., III; Williams, Steven P.; Kramer, Lynda J.

2005-01-01

A visionics device creates a pictorial representation of the external scene for the pilot. The ultimate objective of these systems may be to electronically generate a form of Visual Meteorological Conditions (VMC) to eliminate weather or time-of-day as an operational constraint and provide enhancement over actual visual conditions where eye-limiting resolution may be a limiting factor. Empirical evidence has shown that the total system delays or latencies including the imaging sensors and display systems, can critically degrade their utility, usability, and acceptability. Definitions and measurement techniques are offered herein as common test and evaluation methods for latency testing in visionics device applications. Based upon available data, very different latency requirements are indicated based upon the piloting task, the role in which the visionics device is used in this task, and the characteristics of the visionics cockpit display device including its resolution, field-of-regard, and field-of-view. The least stringent latency requirements will involve Head-Up Display (HUD) applications, where the visionics imagery provides situational information as a supplement to symbology guidance and command information. Conversely, the visionics system latency requirement for a large field-of-view Head-Worn Display application, providing a Virtual-VMC capability from which the pilot will derive visual guidance, will be the most stringent, having a value as low as 20 msec.

Entry Abort Determination Using Non-Adaptive Neural Networks for Mars Precision Landers

NASA Technical Reports Server (NTRS)

Graybeal, Sarah R.; Kranzusch, Kara M.

2005-01-01

The 2009 Mars Science Laboratory (MSL) will attempt the first precision landing on Mars using a modified version of the Apollo Earth entry guidance program. The guidance routine, Entry Terminal Point Controller (ETPC), commands the deployment of a supersonic parachute after converging the range to the landing target. For very dispersed cases, ETPC may not converge the range to the target and safely command parachute deployment within Mach number and dynamic pressure constraints. A full-lift up abort can save 85% of these failed trajectories while abandoning the precision landing objective. Though current MSL requirements do not call for an abort capability, an autonomous abort capability may be desired, for this mission or future Mars precision landers, to make the vehicle more robust. The application of artificial neural networks (NNs) as an abort determination technique was evaluated by personnel at the National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC). In order to implement an abort, a failed trajectory needs to be recognized in real time. Abort determination is dependent upon several trajectory parameters whose relationships to vehicle survival are not well understood, and yet the lander must be trained to recognize unsafe situations. Artificial neural networks (NNs) provide a way to model these parameters and can provide MSL with the artificial intelligence necessary to independently declare an abort. Using the 2009 Mars Science Laboratory (MSL) mission as a case study, a non-adaptive NN was designed, trained and tested using Monte Carlo simulations of MSL descent and incorporated into ETPC. Neural network theory, the development history of the MSL NN, and initial testing with severe dust storm entry trajectory cases are discussed in Reference 1 and will not be repeated here. That analysis demonstrated that NNs are capable of recognizing failed descent trajectories and can significantly increase the survivability of MSL for very dispersed cases. NN testing was then broadened to evaluate fully dispersed entry trajectories. The NN correctly classified 99.7% of descent trajectories as abort or nonabort and reduced the probability of an unsafe parachute deployment by 83%. This second, broader testing phase is discussed in this paper.

Diagnostic instrumentation aboard ISS: just-in-time training for non-physician crewmembers.

PubMed

Foale, C Michael; Kaleri, Alexander Y; Sargsyan, Ashot E; Hamilton, Douglas R; Melton, Shannon; Martin, David; Dulchavsky, Scott A

2005-06-01

The performance of complex tasks on the International Space Station (ISS) requires significant preflight crew training commitments and frequent skill and knowledge refreshment. This report documents a recently developed "just-in-time" training methodology, which integrates preflight hardware familiarization and procedure training with an on-orbit CD-ROM-based skill enhancement. This "just-in-time" concept was used to support real-time remote expert guidance to complete ultrasound examinations using the ISS Human Research Facility (HRF). An American and Russian ISS crewmember received 2 h of "hands on" ultrasound training 8 mo prior to the on-orbit ultrasound exam. A CD-ROM-based Onboard Proficiency Enhancement (OPE) interactive multimedia program consisting of memory enhancing tutorials, and skill testing exercises, was completed by the crewmember 6 d prior to the on-orbit ultrasound exam. The crewmember was then remotely guided through a thoracic, vascular, and echocardiographic examination by ultrasound imaging experts. Results of the CD-ROM-based OPE session were used to modify the instructions during a complete 35-min real-time thoracic, cardiac, and carotid/jugular ultrasound study. Following commands from the ground-based expert, the crewmember acquired all target views and images without difficulty. The anatomical content and fidelity of ultrasound video were adequate for clinical decision making. Complex ultrasound experiments with expert guidance were performed with high accuracy following limited preflight training and multimedia based in-flight review, despite a 2-s communication latency. In-flight application of multimedia proficiency enhancement software, coupled with real-time remote expert guidance, facilitates the successful performance of ultrasound examinations on orbit and may have additional terrestrial and space applications.

Diagnostic ultrasound at MACH 20: retroperitoneal and pelvic imaging in space.

PubMed

Jones, J A; Sargsyan, A E; Barr, Y R; Melton, S; Hamilton, D R; Dulchavsky, S A; Whitson, P A

2009-07-01

An operationally available diagnostic imaging capability augments spaceflight medical support by facilitating the diagnosis, monitoring and treatment of medical or surgical conditions, by improving medical outcomes and, thereby, by lowering medical mission impacts and the probability of crew evacuation due to medical causes. Microgravity-related physiological changes occurring during spaceflight can affect the genitourinary system and potentially cause conditions such as urinary retention or nephrolithiasis for which ultrasonography (U/S) would be a useful diagnostic tool. This study describes the first genitourinary ultrasound examination conducted in space, and evaluates image quality, frame rate, resolution requirements, real-time remote guidance of nonphysician crew medical officers and evaluation of on-orbit tools that can augment image acquisition. A nonphysician crew medical officer (CMO) astronaut, with minimal training in U/S, performed a self-examination of the genitourinary system onboard the International Space Station, using a Philips/ATL Model HDI-5000 ultrasound imaging unit located in the International Space Station Human Research Facility. The CMO was remotely guided by voice commands from experienced, earth-based sonographers stationed in Mission Control Center in Houston. The crewmember, with guidance, was able to acquire all of the target images. Real-time and still U/S images received at Mission Control Center in Houston were of sufficient quality for the images to be diagnostic for multiple potential genitourinary applications. Microgravity-based ultrasound imaging can provide diagnostic quality images of the retroperitoneum and pelvis, offering improved diagnosis and treatment for onboard medical contingencies. Successful completion of complex sonographic examinations can be obtained even with minimally trained nonphysician ultrasound operators, with the assistance of ground-based real-time guidance.

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

Mooij, E.

Application of simple adaptive control (SAC) theory to the design of guidance and control systems for winged re-entry vehicles has been proven successful. To apply SAC to these non-linear and non-stationary systems, it needs to be Almost Strictly Passive (ASP), which is an extension of the Almost Strictly Positive Real (ASPR) condition for linear, time-invariant systems. To fulfill the ASP condition, the controlled, non-linear system has to be minimum-phase (i.e., the zero dynamics is stable), and there is a specific condition for the product of output and input matrix. Earlier studies indicate that even the linearised system is not ASPR.more » The two problems at hand are: 1) the system is non-minimum phase when flying with zero bank angle, and 2) whenever there is hybrid control, e.g., yaw control is established by combined reaction and aerodynamic control for the major part of flight, the second ASPR condition cannot be met. In this paper we look at both issues, the former related to the guidance system and the latter to the attitude-control system. It is concluded that whenever the nominal bank angle is zero, the passivity conditions can never be met, and guidance should be based on nominal commands and a redefinition of those whenever the error becomes too large. For the remaining part of the trajectory, the passivity conditions are marginally met, but it is proposed to add feedforward compensators to alleviate these conditions. The issue of hybrid control is avoided by redefining the controls with total control moments and adding a so-called control allocator. Deriving the passivity conditions for rotational motion, and evaluating these conditions along the trajectory shows that the (non-linear) winged entry vehicle is ASP. The sufficient conditions to apply SAC for attitude control are thus met.« less

Diagnostic instrumentation aboard ISS: just-in-time training for non-physician crewmembers

NASA Technical Reports Server (NTRS)

Foale, C. Michael; Kaleri, Alexander Y.; Sargsyan, Ashot E.; Hamilton, Douglas R.; Melton, Shannon; Martin, David; Dulchavsky, Scott A.

2005-01-01

INTRODUCTION: The performance of complex tasks on the International Space Station (ISS) requires significant preflight crew training commitments and frequent skill and knowledge refreshment. This report documents a recently developed "just-in-time" training methodology, which integrates preflight hardware familiarization and procedure training with an on-orbit CD-ROM-based skill enhancement. This "just-in-time" concept was used to support real-time remote expert guidance to complete ultrasound examinations using the ISS Human Research Facility (HRF). METHODS: An American and Russian ISS crewmember received 2 h of "hands on" ultrasound training 8 mo prior to the on-orbit ultrasound exam. A CD-ROM-based Onboard Proficiency Enhancement (OPE) interactive multimedia program consisting of memory enhancing tutorials, and skill testing exercises, was completed by the crewmember 6 d prior to the on-orbit ultrasound exam. The crewmember was then remotely guided through a thoracic, vascular, and echocardiographic examination by ultrasound imaging experts. RESULTS: Results of the CD-ROM-based OPE session were used to modify the instructions during a complete 35-min real-time thoracic, cardiac, and carotid/jugular ultrasound study. Following commands from the ground-based expert, the crewmember acquired all target views and images without difficulty. The anatomical content and fidelity of ultrasound video were adequate for clinical decision making. CONCLUSIONS: Complex ultrasound experiments with expert guidance were performed with high accuracy following limited preflight training and multimedia based in-flight review, despite a 2-s communication latency. In-flight application of multimedia proficiency enhancement software, coupled with real-time remote expert guidance, facilitates the successful performance of ultrasound examinations on orbit and may have additional terrestrial and space applications.

STS-103 Crew Training

NASA Technical Reports Server (NTRS)

1999-01-01

The Hubble Space Telescope (HST) team is preparing for NASA's third scheduled service call to Hubble. This mission, STS-103, will launch from Kennedy Space Center aboard the Space Shuttle Discovery. The seven flight crew members are Commander Curtis L. Brown, Pilot Scott J. Kelly, European Space Agency (ESA) astronaut Jean-Francois Clervoy who will join space walkers Steven L. Smith, C. Michael Foale, John M. Grunsfeld, and ESA astronaut Claude Nicollier. The objectives of the HST Third Servicing Mission (SM3A) are to replace the telescope's six gyroscopes, a Fine-Guidance Sensor, an S-Band Single Access Transmitter, a spare solid-state recorder and a high-voltage/temperature kit for protecting the batteries from overheating. In addition, the crew plans to install an advanced computer that is 20 times faster and has six times the memory of the current Hubble Space Telescope computer. To prepare for these extravehicular activities (EVAs), the SM3A astronauts participated in Crew Familiarization sessions with the actual SM3A flight hardware. During these sessions the crew spent long hours rehearsing their space walks in the Guidance Navigation Simulator and NBL (Neutral Buoyancy Laboratory). Using space gloves, flight Space Support Equipment (SSE), and Crew Aids and Tools (CATs), the astronauts trained with and verified flight orbital replacement unit (ORU) hardware. The crew worked with a number of trainers and simulators, such as the High Fidelity Mechanical Simulator, Guidance Navigation Simulator, System Engineering Simulator, the Aft Shroud Door Trainer, the Forward Shell/Light Shield Simulator, and the Support Systems Module Bay Doors Simulator. They also trained and verified the flight Orbital Replacement Unit Carrier (ORUC) and its ancillary hardware. Discovery's planned 10-day flight is scheduled to end with a night landing at Kennedy.

Applications of Capstone depleted uranium aerosol risk data to military combat risk management.

PubMed

Daxon, Eric G; Parkhurst, Mary Ann; Melanson, Mark A; Roszell, Laurie E

2009-03-01

Risks to personnel engaged in military operations include not only the threat of enemy firepower but also risks from exposure to other hazards such as radiation. Combatant commanders of the U.S. Army carefully weigh risks of casualties before implementing battlefield actions using an established paradigm that takes these risks into consideration. As a result of the inclusion of depleted uranium (DU) anti-armor ammunition in the conventional (non-nuclear) weapons arsenal, the potential for exposure to DU aerosols and its associated chemical and radiological effects becomes an element of the commanders' risk assessment. The Capstone DU Aerosol Study measured the range of likely DU oxide aerosol concentrations created inside a combat vehicle perforated with a DU munition, and the Capstone Human Health Risk Assessment (HHRA) estimated the associated doses and calculated risks. This paper focuses on the development of a scientific approach to adapt the risks from DU's non-uniform dose distribution within the body using the current U.S. Department of Defense radiation risk management approach. The approach developed equates the Radiation Exposure Status categories to the estimated radiological risks of DU and makes use of the Capstone-developed Renal Effects Group as a measure of chemical risk from DU intake. Recommendations are provided for modifying Army guidance and policy in order to better encompass the potential risks from DU aerosol inhalation during military operations.

Revised Simulation Model of the Control System, Displays, and Propulsion System for a ASTOVL Lift Fan Aircraft

NASA Technical Reports Server (NTRS)

Franklin, James A.

1997-01-01

This report describes revisions to a simulation model that was developed for use in piloted evaluations of takeoff, transition, hover, and landing characteristics of an advanced short takeoff and vertical landing lift fan fighter aircraft. These revisions have been made to the flight/propulsion control system, head-up display, and propulsion system to reflect recent flight and simulation experience with short takeoff and vertical landing operations. They include nonlinear inverse control laws in all axes (eliminating earlier versions with state rate feedback), throttle scaling laws for flightpath and thrust command, control selector commands apportioned based on relative effectiveness of the individual controls, lateral guidance algorithms that provide more flexibility for terminal area operations, and a simpler representation of the propulsion system. The model includes modes tailored to the phases of the aircraft's operation, with several response types which are coupled to the aircraft's aerodynamic and propulsion system effectors through a control selector tailored to the propulsion system. Head-up display modes for approach and hover are integrated with the corresponding control modes. Propulsion system components modeled include a remote lift fan and a lift-cruise engine. Their static performance and dynamic responses are represented by the model. A separate report describes the subsonic, power-off aerodynamics and jet induced aerodynamics in hover and forward flight, including ground effects.

Control-oriented modeling and adaptive backstepping control for a nonminimum phase hypersonic vehicle.

PubMed

Ye, Linqi; Zong, Qun; Tian, Bailing; Zhang, Xiuyun; Wang, Fang

2017-09-01

In this paper, the nonminimum phase problem of a flexible hypersonic vehicle is investigated. The main challenge of nonminimum phase is the prevention of dynamic inversion methods to nonlinear control design. To solve this problem, we make research on the relationship between nonminimum phase and backstepping control, finding that a stable nonlinear controller can be obtained by changing the control loop on the basis of backstepping control. By extending the control loop to cover the internal dynamics in it, the internal states are directly controlled by the inputs and simultaneously serve as virtual control for the external states, making it possible to guarantee output tracking as well as internal stability. Then, based on the extended control loop, a simplified control-oriented model is developed to enable the applicability of adaptive backstepping method. It simplifies the design process and releases some limitations caused by direct use of the no simplified control-oriented model. Next, under proper assumptions, asymptotic stability is proved for constant commands, while bounded stability is proved for varying commands. The proposed method is compared with approximate backstepping control and dynamic surface control and is shown to have superior tracking accuracy as well as robustness from the simulation results. This paper may also provide a beneficial guidance for control design of other complex systems. Copyright © 2017 ISA. Published by Elsevier Ltd. All rights reserved.

Design and evaluation of an autonomous, obstacle avoiding, flight control system using visual sensors

NASA Astrophysics Data System (ADS)

Crawford, Bobby Grant

In an effort to field smaller and cheaper Uninhabited Aerial Vehicles (UAVs), the Army has expressed an interest in an ability of the vehicle to autonomously detect and avoid obstacles. Current systems are not suitable for small aircraft. NASA Langley Research Center has developed a vision sensing system that uses small semiconductor cameras. The feasibility of using this sensor for the purpose of autonomous obstacle avoidance by a UAV is the focus of the research presented in this document. The vision sensor characteristics are modeled and incorporated into guidance and control algorithms designed to generate flight commands based on obstacle information received from the sensor. The system is evaluated by simulating the response to these flight commands using a six degree-of-freedom, non-linear simulation of a small, fixed wing UAV. The simulation is written using the MATLAB application and runs on a PC. Simulations were conducted to test the longitudinal and lateral capabilities of the flight control for a range of airspeeds, camera characteristics, and wind speeds. Results indicate that the control system is suitable for obstacle avoiding flight control using the simulated vision system. In addition, a method for designing and evaluating the performance of such a system has been developed that allows the user to easily change component characteristics and evaluate new systems through simulation.

Intrepid: A Mission to Pluto

NASA Technical Reports Server (NTRS)

Behling, Michael; Buchman, Donald; Marcus, Andres; Procopis, Stephanie; Wassgren, Carl; Ziemer, Sarah

1990-01-01

A proposal for an exploratory spacecraft mission to Pluto/Charon system was written in response to the request for proposal for an unmannned probe to pluto (RFP). The design requirements of the RFP are presented and under the guidance of these requirements, the spacecraft Intrepid was designed. The RPF requirement that was of primary importance is the minimization of cost. Also, the reduction of flight time was of extreme importance because the atmosphere of Pluto is expected to collapse close to the Year 2020. If intrepid should arrive after the collapse, the mission would be a failure; for Pluto would be only a solid rock of ice. The topics presented include: (1) scientific instrumentation; (2) mission management, planning, and costing; (3) power and propulsion subsystem; (4) structural subsystem; (5) command, control, and communications; and (6) attitude and articulation control.

Flight evaluations of several hover control and display combinations for precise blind vertical landings

NASA Technical Reports Server (NTRS)

Schroeder, J. A.; Merrick, V. K.

1990-01-01

Several control and display concepts were evaluated on a variable-stability helicopter prior to future evaluations on a modified Harrier. The control and display concepts had been developed to enable precise hover maneuvers, station keeping, and vertical landings in simulated zero-visibility conditions and had been evaluated extensively in previous piloted simulations. Flight evaluations early in the program revealed several inadequacies in the display drive laws that were later corrected using an alternative design approach that integrated the control and display characteristics with the desired guidance law. While hooded, three pilots performed landing-pad captures followed by vertical landings with attitude-rate, attitude, and translation-velocity-command control systems. The latter control system incorporated a modified version of state-rate-feedback implicit-model following. Precise landing within 2 ft of the desired touchdown point were achieved.

Counter-balanced, multiple cable construction crane

NASA Astrophysics Data System (ADS)

Mikulas, Martin M., Jr.; Yang, Li-Farn

1991-11-01

The invention is a counter-balanced, multiple cable construction crane. The apparatus for hoisting payloads comprises a crane having a lifting means, the lifting means comprising an end effector means and three suspension means or cables. One end of each cable attaches to a different winding means located on the lifting means, and the other end of each cable attaches to a different point on the end effector, such that the three cables have a theoretical point of convergence with this point corresponding to the center of mass of the payload. Three controls command rotation of the winding means to a predetermined position. Accordingly, the crane provides precise and autonomous positioning of the payload without human guidance. The crane further comprises a counter-balancing means. Two controls position the counter-balancing means to offset the overturning moment which arises during the lifting of heavy payloads.

Counter-balanced, multiple cable construction crane

NASA Astrophysics Data System (ADS)

Mikulas, Martin M., Jr.; Yang, Li-Farn

1993-10-01

The invention is a counter-balanced, multiple cable construction crane. The apparatus for hoisting payloads comprises a crane having a lifting means, the lifting means comprising an end effector means and three suspension means or cables. One end of each cable attaches to a different winding means located on the lifting means, and the other end of each cable attaches to a different point on the end effector, such that the three cables have a theoretical point of convergence with this point corresponding to the center of mass of the payload. Three controls command rotation of the winding means to a predetermined position. Accordingly, the crane provides precise and autonomous positioning of the payload without human guidance. The crane further comprises a counter-balancing means. Two controls position the counter-balancing means to offset the overturning moment which arises during the lifting of heavy payloads.

Counter-balanced, multiple cable construction crane

NASA Technical Reports Server (NTRS)

Mikulas, Martin M., Jr. (Inventor); Yang, Li-Farn (Inventor)

1993-01-01

The invention is a counter-balanced, multiple cable construction crane. The apparatus for hoisting payloads comprises a crane having a lifting means, the lifting means comprising an end effector means and three suspension means or cables. One end of each cable attaches to a different winding means located on the lifting means, and the other end of each cable attaches to a different point on the end effector, such that the three cables have a theoretical point of convergence with this point corresponding to the center of mass of the payload. Three controls command rotation of the winding means to a predetermined position. Accordingly, the crane provides precise and autonomous positioning of the payload without human guidance. The crane further comprises a counter-balancing means. Two controls position the counter-balancing means to offset the overturning moment which arises during the lifting of heavy payloads.

CNES-NASA Studies of the Mars Sample Return Orbiter Aerocapture Phase

NASA Technical Reports Server (NTRS)

Fraysse, H.; Powell, R.; Rousseau, S.; Striepe, S.

2000-01-01

A Mars Sample Return (MSR) mission has been proposed as a joint CNES (Centre National d'Etudes Spatiales) and NASA effort in the ongoing Mars Exploration Program. The MSR mission is designed to return the first samples of Martian soil to Earth. The primary elements of the mission are a lander, rover, ascent vehicle, orbiter, and an Earth entry vehicle. The Orbiter has been allocated only 2700 kg on the launch phase to perform its part of the mission. This mass restriction has led to the decision to use an aerocapture maneuver at Mars for the orbiter. Aerocapture replaces the initial propulsive capture maneuver with a single atmospheric pass. This atmospheric pass will result in the proper apoapsis, but a periapsis raise maneuver is required at the first apoapsis. The use of aerocapture reduces the total mass requirement by approx. 45% for the same payload. This mission will be the first to use the aerocapture technique. Because the spacecraft is flying through the atmosphere, guidance algorithms must be developed that will autonomously provide the proper commands to reach the desired orbit while not violating any of the design parameters (e.g. maximum deceleration, maximum heating rate, etc.). The guidance algorithm must be robust enough to account for uncertainties in delivery states, atmospheric conditions, mass properties, control system performance, and aerodynamics. To study this very critical phase of the mission, a joint CNES-NASA technical working group has been formed. This group is composed of atmospheric trajectory specialists from CNES, NASA Langley Research Center and NASA Johnson Space Center. This working group is tasked with developing and testing guidance algorithms, as well as cross-validating CNES and NASA flight simulators for the Mars atmospheric entry phase of this mission. The final result will be a recommendation to CNES on the algorithm to use, and an evaluation of the flight risks associated with the algorithm. This paper will describe the aerocapture phase of the MSR mission, the main principles of the guidance algorithms that are under development, the atmospheric entry simulators developed for the evaluations, the process for the evaluations, and preliminary results from the evaluations.

Case ascertainment of heat illness in the British Army: evidence of under-reporting from analysis of Medical and Command notifications, 2009-2013.

PubMed

Stacey, Michael J; Brett, S; Woods, D; Jackson, S; Ross, D

2016-12-01

Heat illness in the Armed Forces is considered preventable. The UK military relies upon dual Command and Medical reporting for case ascertainment, investigation of serious incidents and improvement of preventive practices and policy. This process could be vulnerable to under-reporting. To establish whether heat illness in the British Army has been under-reported, by reviewing concordance of reporting to the Army Incident Notification Cell (AINC) and the Army Health Unit (AHU) and to characterise the burden of heat illness reported by these means. Analysis of anonymised reporting databases held by the AHU and AINC, for the period 2009-2013. 565 unique cases of heat illness were identified. Annual concordance of reporting ranged from 9.6% to 16.5%. The overall rate was 13.3%. July was the month with the greatest number of heat illness reports (24.4% of total reporting) and the highest concordance rate (30%). Reports of heat illness from the UK (n=343) exceeded overseas notifications (n=221) and showed better concordance (17.1% vs 12.8%). The annual rate of reported heat illness varied widely, being greater in full-time than reservist personnel (87 vs 23 per100 000) and highest in full-time untrained personnel (223 per100 000). The risk of heat illness was global, year-round and showed dynamic local variation. Failure to dual-report casualties impaired case ascertainment of heat illness across Command and Medical chains. Current preventive guidance, as applied in training and on operations, should be critically evaluated to ensure that risk of heat illness is reduced as low as possible. Clear procedures for casualty notification and surveillance are required in support of this and should incorporate communication within and between the two reporting chains. Published by the BMJ Publishing Group Limited. For permission to use (where not already granted under a licence) please go to http://www.bmj.com/company/products-services/rights-and-licensing/.

Case ascertainment of heat illness in the British Army: evidence of under-reporting from analysis of Medical and Command notifications, 2009–2013

PubMed Central

Stacey, Michael J; Brett, S; Woods, D; Jackson, S; Ross, D

2016-01-01

Background Heat illness in the Armed Forces is considered preventable. The UK military relies upon dual Command and Medical reporting for case ascertainment, investigation of serious incidents and improvement of preventive practices and policy. This process could be vulnerable to under-reporting. Objectives To establish whether heat illness in the British Army has been under-reported, by reviewing concordance of reporting to the Army Incident Notification Cell (AINC) and the Army Health Unit (AHU) and to characterise the burden of heat illness reported by these means. Methods Analysis of anonymised reporting databases held by the AHU and AINC, for the period 2009–2013. Results 565 unique cases of heat illness were identified. Annual concordance of reporting ranged from 9.6% to 16.5%. The overall rate was 13.3%. July was the month with the greatest number of heat illness reports (24.4% of total reporting) and the highest concordance rate (30%). Reports of heat illness from the UK (n=343) exceeded overseas notifications (n=221) and showed better concordance (17.1% vs 12.8%). The annual rate of reported heat illness varied widely, being greater in full-time than reservist personnel (87 vs 23 per100 000) and highest in full-time untrained personnel (223 per100 000). Conclusions The risk of heat illness was global, year-round and showed dynamic local variation. Failure to dual-report casualties impaired case ascertainment of heat illness across Command and Medical chains. Current preventive guidance, as applied in training and on operations, should be critically evaluated to ensure that risk of heat illness is reduced as low as possible. Clear procedures for casualty notification and surveillance are required in support of this and should incorporate communication within and between the two reporting chains. PMID:25717054

Human Space Flight

NASA Technical Reports Server (NTRS)

Woolford, Barbara

2006-01-01

The performance of complex tasks on the International Space Station (ISS) requires significant preflight crew training commitments and frequent skill and knowledge refreshment. This report documents a recently developed just-in-time training methodology, which integrates preflight hardware familiarization and procedure training with an on-orbit CD-ROM-based skill enhancement. This just-in-time concept was used to support real-time remote expert guidance to complete medical examinations using the ISS Human Research Facility (HRF). An American md Russian ISS crewmember received 2-hours of hands on ultrasound training 8 months prior to the on-orbit ultrasound exam. A CD-ROM-based Onboard Proficiency Enhancement (OPE) interactive multimedia program consisting of memory enhancing tutorials, and skill testing exercises, was completed by the crewmember six days prior to the on-orbit ultrasound exam. The crewmember was then remotely guided through a thoracic, vascular, and echocardiographic examination by ultrasound imaging experts. Results of the CD ROM based OPE session were used to modify the instructions during a complete 35 minute real-time thoracic, cardiac, and carotid/jugular ultrasound study. Following commands from the ground-based expert, the crewmember acquired all target views and images without difficulty. The anatomical content and fidelity of ultrasound video were excellent and adequate for clinical decision-making. Complex ultrasound experiments with expert guidance were performed with high accuracy following limited pre-flight training and CD-ROM-based in-flight review, despite a 2-second communication latency.

An Enhanced Convective Forecast (ECF) for the New York TRACON Area

NASA Technical Reports Server (NTRS)

Wheeler, Mark; Stobie, James; Gillen, Robert; Jedlovec, Gary; Sims, Danny

2008-01-01

In an effort to relieve summer-time congestion in the NY Terminal Radar Approach Control (TRACON) area, the FAA is testing an enhanced convective forecast (ECF) product. The test began in June 2008 and is scheduled to run through early September. The ECF is updated every two hours, right before the Air Traffic Control System Command Center (ATCSCC) national planning telcon. It is intended to be used by traffic managers throughout the National Airspace System (NAS) and airlines dispatchers to supplement information from the Collaborative Convective Forecast Product (CCFP) and the Corridor Integrated Weather System (CIWS). The ECF begins where the current CIWS forecast ends at 2 hours and extends out to 12 hours. Unlike the CCFP it is a detailed deterministic forecast with no aerial coverage limits. It is created by an ENSCO forecaster using a variety of guidance products including, the Weather Research and Forecast (WRF) model. This is the same version of the WRF that ENSCO runs over the Florida peninsula in support of launch operations at the Kennedy Space Center. For this project, the WRF model domain has been shifted to the Northeastern US. Several products from the NASA SPoRT group are also used by the ENSCO forecaster. In this paper we will provide examples of the ECF products and discuss individual cases of traffic management actions using ECF guidance.

AERCam Autonomy: Intelligent Software Architecture for Robotic Free Flying Nanosatellite Inspection Vehicles

NASA Technical Reports Server (NTRS)

Fredrickson, Steven E.; Duran, Steve G.; Braun, Angela N.; Straube, Timothy M.; Mitchell, Jennifer D.

2006-01-01

The NASA Johnson Space Center has developed a nanosatellite-class Free Flyer intended for future external inspection and remote viewing of human spacecraft. The Miniature Autonomous Extravehicular Robotic Camera (Mini AERCam) technology demonstration unit has been integrated into the approximate form and function of a flight system. The spherical Mini AERCam Free Flyer is 7.5 inches in diameter and weighs approximately 10 pounds, yet it incorporates significant additional capabilities compared to the 35-pound, 14-inch diameter AERCam Sprint that flew as a Shuttle flight experiment in 1997. Mini AERCam hosts a full suite of miniaturized avionics, instrumentation, communications, navigation, power, propulsion, and imaging subsystems, including digital video cameras and a high resolution still image camera. The vehicle is designed for either remotely piloted operations or supervised autonomous operations, including automatic stationkeeping, point-to-point maneuvering, and waypoint tracking. The Mini AERCam Free Flyer is accompanied by a sophisticated control station for command and control, as well as a docking system for automated deployment, docking, and recharge at a parent spacecraft. Free Flyer functional testing has been conducted successfully on both an airbearing table and in a six-degree-of-freedom closed-loop orbital simulation with avionics hardware in the loop. Mini AERCam aims to provide beneficial on-orbit views that cannot be obtained from fixed cameras, cameras on robotic manipulators, or cameras carried by crewmembers during extravehicular activities (EVA s). On Shuttle or International Space Station (ISS), for example, Mini AERCam could support external robotic operations by supplying orthogonal views to the intravehicular activity (IVA) robotic operator, supply views of EVA operations to IVA and/or ground crews monitoring the EVA, and carry out independent visual inspections of areas of interest around the spacecraft. To enable these future benefits with minimal impact on IVA operators and ground controllers, the Mini AERCam system architecture incorporates intelligent systems attributes that support various autonomous capabilities. 1) A robust command sequencer enables task-level command scripting. Command scripting is employed for operations such as automatic inspection scans over a region of interest, and operator-hands-off automated docking. 2) A system manager built on the same expert-system software as the command sequencer provides detection and smart-response capability for potential system-level anomalies, like loss of communications between the Free Flyer and control station. 3) An AERCam dynamics manager provides nominal and off-nominal management of guidance, navigation, and control (GN&C) functions. It is employed for safe trajectory monitoring, contingency maneuvering, and related roles. This paper will describe these architectural components of Mini AERCam autonomy, as well as the interaction of these elements with a human operator during supervised autonomous control.

Terminal configured vehicle program: Test facilities guide

NASA Technical Reports Server (NTRS)

1980-01-01

The terminal configured vehicle (TCV) program was established to conduct research and to develop and evaluate aircraft and flight management system technology concepts that will benefit conventional take off and landing operations in the terminal area. Emphasis is placed on the development of operating methods for the highly automated environment anticipated in the future. The program involves analyses, simulation, and flight experiments. Flight experiments are conducted using a modified Boeing 737 airplane equipped with highly flexible display and control equipment and an aft flight deck for research purposes. The experimental systems of the Boeing 737 are described including the flight control computer systems, the navigation/guidance system, the control and command panel, and the electronic display system. The ground based facilities used in the program are described including the visual motion simulator, the fixed base simulator, the verification and validation laboratory, and the radio frequency anechoic facility.

Launch of Space Shuttle Atlantis / STS-125 Mission

NASA Image and Video Library

2009-05-11

STS125-S-050 (11 May 2009) --- The launch of Space Shuttle Atlantis from launch pad 39A at NASA's Kennedy Space Center in Florida is viewed from behind launch pad 39B. On pad 39B is Space Shuttle Endeavour, which can launch, if needed, for rescue of Atlantis? crew during its STS-125 mission to service NASA?s Hubble Space Telescope. Liftoff of Atlantis was on time at 2:01 p.m. (EDT) on May 11, 2009. Onboard are astronauts Scott Altman, commander; Gregory C. Johnson, pilot; Michael Good, Megan McArthur, John Grunsfeld, Mike Massimino and Andrew Feustel, all mission specialists. Atlantis' 11-day flight will include five spacewalks to refurbish and upgrade the telescope with state-of-the-art science instruments that will expand Hubble's capabilities and extend its operational lifespan through at least 2014. The payload includes a Wide Field Camera 3, Fine Guidance Sensor and the Cosmic Origins Spectrograph.

Launch of Space Shuttle Atlantis / STS-125 Mission

NASA Image and Video Library

2009-05-11

STS125-S-057 (11 May 2009) --- The launch of Space Shuttle Atlantis from launch pad 39A at NASA's Kennedy Space Center in Florida is viewed from behind launch pad 39B. On pad 39B is Space Shuttle Endeavour, which can launch, if needed, for rescue of Atlantis? crew during its STS-125 mission to service NASA?s Hubble Space Telescope. Liftoff of Atlantis was on time at 2:01 p.m. (EDT) on May 11, 2009. Onboard are astronauts Scott Altman, commander; Gregory C. Johnson, pilot; Michael Good, Megan McArthur, John Grunsfeld, Mike Massimino and Andrew Feustel, all mission specialists. Atlantis' 11-day flight will include five spacewalks to refurbish and upgrade the telescope with state-of-the-art science instruments that will expand Hubble's capabilities and extend its operational lifespan through at least 2014. The payload includes a Wide Field Camera 3, Fine Guidance Sensor and the Cosmic Origins Spectrograph.

Bio-robots automatic navigation with electrical reward stimulation.

PubMed

Sun, Chao; Zhang, Xinlu; Zheng, Nenggan; Chen, Weidong; Zheng, Xiaoxiang

2012-01-01

Bio-robots that controlled by outer stimulation through brain computer interface (BCI) suffer from the dependence on realtime guidance of human operators. Current automatic navigation methods for bio-robots focus on the controlling rules to force animals to obey man-made commands, with animals' intelligence ignored. This paper proposes a new method to realize the automatic navigation for bio-robots with electrical micro-stimulation as real-time rewards. Due to the reward-seeking instinct and trial-and-error capability, bio-robot can be steered to keep walking along the right route with rewards and correct its direction spontaneously when rewards are deprived. In navigation experiments, rat-robots learn the controlling methods in short time. The results show that our method simplifies the controlling logic and realizes the automatic navigation for rat-robots successfully. Our work might have significant implication for the further development of bio-robots with hybrid intelligence.

The MITy micro-rover: Sensing, control, and operation

NASA Technical Reports Server (NTRS)

Malafeew, Eric; Kaliardos, William

1994-01-01

The sensory, control, and operation systems of the 'MITy' Mars micro-rover are discussed. It is shown that the customized sun tracker and laser rangefinder provide internal, autonomous dead reckoning and hazard detection in unstructured environments. The micro-rover consists of three articulated platforms with sensing, processing and payload subsystems connected by a dual spring suspension system. A reactive obstacle avoidance routine makes intelligent use of robot-centered laser information to maneuver through cluttered environments. The hazard sensors include a rangefinder, inclinometers, proximity sensors and collision sensors. A 486/66 laptop computer runs the graphical user interface and programming environment. A graphical window displays robot telemetry in real time and a small TV/VCR is used for real time supervisory control. Guidance, navigation, and control routines work in conjunction with the mapping and obstacle avoidance functions to provide heading and speed commands that maneuver the robot around obstacles and towards the target.

Propulsive Reaction Control System Model

NASA Technical Reports Server (NTRS)

Brugarolas, Paul; Phan, Linh H.; Serricchio, Frederick; San Martin, Alejandro M.

2011-01-01

This software models a propulsive reaction control system (RCS) for guidance, navigation, and control simulation purposes. The model includes the drive electronics, the electromechanical valve dynamics, the combustion dynamics, and thrust. This innovation follows the Mars Science Laboratory entry reaction control system design, and has been created to meet the Mars Science Laboratory (MSL) entry, descent, and landing simulation needs. It has been built to be plug-and-play on multiple MSL testbeds [analysis, Monte Carlo, flight software development, hardware-in-the-loop, and ATLO (assembly, test and launch operations) testbeds]. This RCS model is a C language program. It contains two main functions: the RCS electronics model function that models the RCS FPGA (field-programmable-gate-array) processing and commanding of the RCS valve, and the RCS dynamic model function that models the valve and combustion dynamics. In addition, this software provides support functions to initialize the model states, set parameters, access model telemetry, and access calculated thruster forces.

Intelligent guidance and control for wind shear encounter

NASA Technical Reports Server (NTRS)

Stengel, Robert F.

1988-01-01

The principal objective is to develop methods for assessing the likelihood of wind shear encounter, for deciding what flight path to pursue, and for using the aircraft's full potential for combating wind shear. This study requires the definition of both deterministic and statistical techniques for fusing internal and external information, for making go/no-go decisions, and for generating commands to the aircraft's cockpit displays and autopilot for both manually controlled and automatic flight. The program has begun with the development of a real-time expert system for pilot aiding that is based on the results of the FAA Windshear Training Aids Program. A two-volume manual that presents an overview, pilot guide, training program, and substantiating data provides guidelines for this initial development. The Expert System to Avoid Wind Shear (ESAWS) currently contains over 140 rules and is coded in the LISP programming language for implementation on a Symbolics 3670 LISP machine.

Manned Venus Flyby

NASA Technical Reports Server (NTRS)

Feldman, M. S.; Ferrara, L. A.; Havenstein, P. L.; Volonte, J. E.; Whipple, P. H.

1967-01-01

This study is one of several being conducted at Bellcomm and in Manned Space Flight whose purpose is to give guidance to the Apollo Applications Program's technical objectives by focusing on a longer range goal. The assumed mission in this case is a three-man flyby of Venus launched in November, 1973 on a single standard Saturn V. The selected flight configuration includes a Command and Service Module similar in some respects to Apollo, an Environmental Support Module which occupies the adapter area and a spent S-IVB stage which is utilized for habitable volume and structural support of a solar cell electrical power system. The total injected weight, 106,775 lbs., is within the capability of a single Saturn V of the early 1970's. The study is focused on the selection of subsystem technologies appropriate to long duration flight. The conclusions are reported in terms of the technical characteristics to be achieved as part of the Apollo Applications Program's long duration objectives.

KSC-2011-7863

NASA Image and Video Library

2011-11-10

VANDENBERG AIR FORCE BASE, Calif. -- At a Pegasus booster processing facility at Vandenberg Air Force Base in California, technicians install the avionic shelf on the Pegasus XL rocket. The avionics contained in this module will issue the guidance and flight control commands for the rocket. The Orbital Sciences Corp. Pegasus rocket will launch the Nuclear Spectroscopic Telescope Array (NuSTAR) into space. After the rocket and spacecraft are processed at Vandenberg, they will be flown on the Orbital Sciences’ L-1011 carrier aircraft to the Ronald Reagan Ballistic Missile Defense Test Site at the Pacific Ocean’s Kwajalein Atoll for launch. The high-energy x-ray telescope will conduct a census for black holes, map radioactive material in young supernovae remnants, and study the origins of cosmic rays and the extreme physics around collapsed stars. For more information, visit science.nasa.gov/missions/nustar/. Photo credit: NASA/Randy Beaudoin, VAFB

Preliminary input to the space shuttle reaction control subsystem failure detection and identification software requirements (uncontrolled)

NASA Technical Reports Server (NTRS)

Bergmann, E.

1976-01-01

The current baseline method and software implementation of the space shuttle reaction control subsystem failure detection and identification (RCS FDI) system is presented. This algorithm is recommended for conclusion in the redundancy management (RM) module of the space shuttle guidance, navigation, and control system. Supporting software is presented, and recommended for inclusion in the system management (SM) and display and control (D&C) systems. RCS FDI uses data from sensors in the jets, in the manifold isolation valves, and in the RCS fuel and oxidizer storage tanks. A list of jet failures and fuel imbalance warnings is generated for use by the jet selection algorithm of the on-orbit and entry flight control systems, and to inform the crew and ground controllers of RCS failure status. Manifold isolation valve close commands are generated in the event of failed on or leaking jets to prevent loss of large quantities of RCS fuel.

Aircraft measurements of electrified clouds at Kennedy Space Center, part 3

NASA Technical Reports Server (NTRS)

Jones, J. J.; Winn, W. P.; Hunyady, S. J.; Moore, C. B.; Bullock, J. W.; Fleischhacker, P.

1990-01-01

Flights made by the Special Purpose Test Vehicle for Atmospheric Research (SPTVAR) airplane during a second deployment to Florida during the summer of 1989 are discussed. The findings based on the data gathered are presented. The progress made during the second year of the project is discussed. The summer 1989 study was carried out with the support and guidance of Col. John Madura, Commander of Detachment 11, 2nd Weather Squadron, USAF, at Patrick Air Force Base (PAFB) and Cape Canaveral Air Force Station. The project goals were to develop and demonstrate techniques for measuring the electric field aloft and locating regions of charge during flight within and near clouds; to characterize the electric conditions that are presently identified as a threat to space launch vehicles; and to study the correlation between the electric field aloft and that at Kennedy Space Center's ground-based electric field mill array for a variety of electrified clouds.

A comparison of results from two simulators used for studies of astronaut maneuvering units. [with application to Skylab program

NASA Technical Reports Server (NTRS)

Stewart, E. C.; Cannaday, R. L.

1973-01-01

A comparison of the results from a fixed-base, six-degree-of -freedom simulator and a moving-base, three-degree-of-freedom simulator was made for a close-in, EVA-type maneuvering task in which visual cues of a target spacecraft were used for guidance. The maneuvering unit (the foot-controlled maneuvering unit of Skylab Experiment T020) employed an on-off acceleration command control system operated entirely by the feet. Maneuvers by two test subjects were made for the fixed-base simulator in six and three degrees of freedom and for the moving-base simulator in uncontrolled and controlled, EVA-type visual cue conditions. Comparisons of pilot ratings and 13 different quantitative parameters from the two simulators are made. Different results were obtained from the two simulators, and the effects of limited degrees of freedom and uncontrolled visual cues are discussed.

In Flight Evaluation of Active Inceptor Force-Feel Characteristics and Handling Qualities

NASA Technical Reports Server (NTRS)

Lusardi, Jeff A.; Blanken, Chris L.; Ott, Carl Raymond; Malpica, Carlos A.; von Gruenhagen, Wolfgang

2012-01-01

The effect of inceptor feel-system characteristics on piloted handling qualities has been a research topic of interest for many years. Most of the research efforts have focused on advanced fly-by-wire fixed-wing aircraft with only a few studies investigating the effects on rotorcraft. Consequently, only limited guidance is available on how cyclic force-feel characteristics should be set to obtain optimal handling qualities for rotorcraft. To study this effect, the U.S. Army Aeroflightdynamics Directorate working with the DLR Institute of Flight Systems in Germany under Task X of the U.S. German Memorandum of Understanding have been conducting flight test evaluations. In the U.S., five experimental test pilots have completed evaluations of two Mission Task Elements (MTEs) from ADS-33E-PRF and two command/response types for a matrix of center-stick cyclic force-feel characteristics at Moffett Field. In Germany, three experimental test Pilots have conducted initial evaluations of the two MTEs with two command/response types for a parallel matrix of side-stick cyclic force-feel characteristics at WTD-61 in Manching. The resulting data set is used to correlate the effect of changes in natural frequency and damping ratio of the cyclic inceptor on the piloted handling qualities. Existing criteria in ADS-33E and a proposed Handling Qualities Sensitivity Function that includes the effects of the cyclic force-feel characteristics are also evaluated against the data set and discussed.

FPGA for Power Control of MSL Avionics

NASA Technical Reports Server (NTRS)

Wang, Duo; Burke, Gary R.

2011-01-01

A PLGT FPGA (Field Programmable Gate Array) is included in the LCC (Load Control Card), GID (Guidance Interface & Drivers), TMC (Telemetry Multiplexer Card), and PFC (Pyro Firing Card) boards of the Mars Science Laboratory (MSL) spacecraft. (PLGT stands for PFC, LCC, GID, and TMC.) It provides the interface between the backside bus and the power drivers on these boards. The LCC drives power switches to switch power loads, and also relays. The GID drives the thrusters and latch valves, as well as having the star-tracker and Sun-sensor interface. The PFC drives pyros, and the TMC receives digital and analog telemetry. The FPGA is implemented both in Xilinx (Spartan 3- 400) and in Actel (RTSX72SU, ASX72S). The Xilinx Spartan 3 part is used for the breadboard, the Actel ASX part is used for the EM (Engineer Module), and the pin-compatible, radiation-hardened RTSX part is used for final EM and flight. The MSL spacecraft uses a FC (Flight Computer) to control power loads, relays, thrusters, latch valves, Sun-sensor, and star-tracker, and to read telemetry such as temperature. Commands are sent over a 1553 bus to the MREU (Multi-Mission System Architecture Platform Remote Engineering Unit). The MREU resends over a remote serial command bus c-bus to the LCC, GID TMC, and PFC. The MREU also sends out telemetry addresses via a remote serial telemetry address bus to the LCC, GID, TMC, and PFC, and the status is returned over the remote serial telemetry data bus.

KSC-99pp1100

NASA Image and Video Library

1999-09-03

In the Orbiter Processing Facility (OPF) bay 1, STS-103 Commander Curtis L. Brown Jr. sits in the command seat of the orbiter Discovery, inspecting the window. Brown and other crew members are at KSC to take part in a Crew Equipment Interface Test. The rest of the crew are Pilot Scott J. Kelly, and Mission Specialists Steven L. Smith, C. Michael Foale (Ph.D.), John M. Grunsfeld (Ph.D.), Claude Nicollier of Switzerland, and Jean-François Clervoy of France. Nicollier and Clervoy are with the European Space Agency. Mission STS-103 is a "call-up" due to the need to replace portions of the pointing system, the gyros, which have begun to fail on the Hubble Space Telescope. Although Hubble is operating normally and conducting its scientific observations, only three of its six gyroscopes are working properly. The gyroscopes allow the telescope to point at stars, galaxies and planets. The STS-103 crew will not only replace gyroscopes, it will also replace a Fine Guidance Sensor and an older computer with a new enhanced model, an older data tape recorder with a solid-state digital recorder, a failed spare transmitter with a new one, and degraded insulation on the telescope with new thermal insulation. The crew will also install a Battery Voltage/Temperature Improvement Kit to protect the spacecraft batteries from overcharging and overheating when the telescope goes into a safe mode. The scheduled launch date in October is under review

Interagency Evaluation of the Section 1206 Global Train and Equip Program

DTIC Science & Technology

2009-08-31

Capabilities, Joint Staff, U.S. Africa Command, U.S. Central Command, U.S Joint Forces Command, U.S. Pacific Command, U.S. Southern Command, U.S. Special...Intensity Conflict & Interdependent Capabilities; Commanders of U.S. Africa Command, U.S. Central Command, U.S. Joint Forces Command, U.S. Pacific... Central Command, commented that coordinating the Section 1206 project proposal with the partner nation prior to submission would inflate the

SPARTAN: A High-Fidelity Simulation for Automated Rendezvous and Docking Applications

NASA Technical Reports Server (NTRS)

Turbe, Michael A.; McDuffie, James H.; DeKock, Brandon K.; Betts, Kevin M.; Carrington, Connie K.

2007-01-01

bd Systems (a subsidiary of SAIC) has developed the Simulation Package for Autonomous Rendezvous Test and ANalysis (SPARTAN), a high-fidelity on-orbit simulation featuring multiple six-degree-of-freedom (6DOF) vehicles. SPARTAN has been developed in a modular fashion in Matlab/Simulink to test next-generation automated rendezvous and docking guidance, navigation,and control algorithms for NASA's new Vision for Space Exploration. SPARTAN includes autonomous state-based mission manager algorithms responsible for sequencing the vehicle through various flight phases based on on-board sensor inputs and closed-loop guidance algorithms, including Lambert transfers, Clohessy-Wiltshire maneuvers, and glideslope approaches The guidance commands are implemented using an integrated translation and attitude control system to provide 6DOF control of each vehicle in the simulation. SPARTAN also includes high-fidelity representations of a variety of absolute and relative navigation sensors that maybe used for NASA missions, including radio frequency, lidar, and video-based rendezvous sensors. Proprietary navigation sensor fusion algorithms have been developed that allow the integration of these sensor measurements through an extended Kalman filter framework to create a single optimal estimate of the relative state of the vehicles. SPARTAN provides capability for Monte Carlo dispersion analysis, allowing for rigorous evaluation of the performance of the complete proposed AR&D system, including software, sensors, and mechanisms. SPARTAN also supports hardware-in-the-loop testing through conversion of the algorithms to C code using Real-Time Workshop in order to be hosted in a mission computer engineering development unit running an embedded real-time operating system. SPARTAN also contains both runtime TCP/IP socket interface and post-processing compatibility with bdStudio, a visualization tool developed by bd Systems, allowing for intuitive evaluation of simulation results. A description of the SPARTAN architecture and capabilities is provided, along with details on the models and algorithms utilized and results from representative missions.

5. Command center doors at command center entry, building 501, ...

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

5. Command center doors at command center entry, building 501, looking north - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

Network, system, and status software enhancements for the autonomously managed electrical power system breadboard. Volume 3: Commands specification

NASA Technical Reports Server (NTRS)

Mckee, James W.

1990-01-01

This volume (3 of 4) contains the specification for the command language for the AMPS system. The volume contains a requirements specification for the operating system and commands and a design specification for the operating system and command. The operating system and commands sits on top of the protocol. The commands are an extension of the present set of AMPS commands in that the commands are more compact, allow multiple sub-commands to be bundled into one command, and have provisions for identifying the sender and the intended receiver. The commands make no change to the actual software that implement the commands.

Autonomous safety and reliability features of the K-1 avionics system

NASA Astrophysics Data System (ADS)

Mueller, George E.; Kohrs, Dick; Bailey, Richard; Lai, Gary

2004-03-01

Kistler Aerospace Corporation is developing the K-1, a fully reusable, two-stage-to-orbit launch vehicle. Both stages return to the launch site using parachutes and airbags. Initial flight operations will occur from Woomera, Australia. K-1 guidance is performed autonomously. Each stage of the K-1 employs a triplex, fault tolerant avionics architecture, including three fault tolerant computers and three radiation hardened Embedded GPS/INS units with a hardware voter. The K-1 has an Integrated Vehicle Health Management (IVHM) system on each stage residing in the three vehicle computers based on similar systems in commercial aircraft. During first-stage ascent, the IVHM system performs an Instantaneous Impact Prediction (IIP) calculation 25 times per second, initiating an abort in the event the vehicle is outside a predetermined safety corridor for at least 3 consecutive calculations. In this event, commands are issued to terminate thrust, separate the stages, dump all propellant in the first-stage, and initiate a normal landing sequence. The second-stage flight computer calculates its ability to reach orbit along its state vector, initiating an abort sequence similar to the first stage if it cannot. On a nominal mission, following separation, the second-stage also performs calculations to assure its impact point is within a safety corridor. The K-1's guidance and control design is being tested through simulation with hardware-in-the-loop at Draper Laboratory. Kistler's verification strategy assures reliable and safe operation of the K-1.

Integrated G and C Implementation within IDOS: A Simulink Based Reusable Launch Vehicle Simulation

NASA Technical Reports Server (NTRS)

Fisher, Joseph E.; Bevacqua, Tim; Lawrence, Douglas A.; Zhu, J. Jim; Mahoney, Michael

2003-01-01

The implementation of multiple Integrated Guidance and Control (IG&C) algorithms per flight phase within a vehicle simulation poses a daunting task to coordinate algorithm interactions with the other G&C components and with vehicle subsystems. Currently being developed by Universal Space Lines LLC (USL) under contract from NASA, the Integrated Development and Operations System (IDOS) contains a high fidelity Simulink vehicle simulation, which provides a means to test cutting edge G&C technologies. Combining the modularity of this vehicle simulation and Simulink s built-in primitive blocks provide a quick way to implement algorithms. To add discrete-event functionality to the unfinished IDOS simulation, Vehicle Event Manager (VEM) and Integrated Vehicle Health Monitoring (IVHM) subsystems were created to provide discrete-event and pseudo-health monitoring processing capabilities. Matlab's Stateflow is used to create the IVHM and Event Manager subsystems and to implement a supervisory logic controller referred to as the Auto-commander as part of the IG&C to coordinate the control system adaptation and reconfiguration and to select the control and guidance algorithms for a given flight phase. Manual creation of the Stateflow charts for all of these subsystems is a tedious and time-consuming process. The Stateflow Auto-builder was developed as a Matlab based software tool for the automatic generation of a Stateflow chart from information contained in a database. This paper describes the IG&C, VEM and IVHM implementations in IDOS. In addition, this paper describes the Stateflow Auto-builder.

Joint Chiefs of Staff > Media > Photos

Science.gov Websites

U.S. Army Gen. Curtis M. Scaparrotti, left, Commander of U.S. European Command and Supreme Allied , Commander of U.S. European Command and Supreme Allied Commander, Europe; speaks after receiving the . U.S. Army Gen. Curtis M. Scaparrotti, Commander of U.S. European Command and Supreme Allied Commander

32 CFR 700.1053 - Commander of a task force.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Commander of a task force. 700.1053 Section 700... Command Detail to Duty § 700.1053 Commander of a task force. (a) A geographic fleet commander, and any other naval commander, may detail in command of a task force, or other task command, any eligible...

The C3-System User. Volume II. Workshop Notes

DTIC Science & Technology

1977-02-01

system that provides the means for operational direction and technical administrative support involved in the function of command and control of U.S...information systems of the Headquarters of the Military Depart- ments; the command and control systems of the Headquarters of the Service Component Commands...the Service Component Commands - Military Airlift Command - Military Sealift Command - Military Traffic Management Command - 3.2.5 Command and

32 CFR 700.703 - To announce assumption of command.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false To announce assumption of command. 700.703... Chief and Other Commanders Titles and Duties of Commanders § 700.703 To announce assumption of command. (a) Upon assuming command, commanders shall so advise appropriate superiors, and the units of their...

32 CFR 700.703 - To announce assumption of command.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false To announce assumption of command. 700.703... Chief and Other Commanders Titles and Duties of Commanders § 700.703 To announce assumption of command. (a) Upon assuming command, commanders shall so advise appropriate superiors, and the units of their...

32 CFR 536.8 - Responsibilities and operations of command claims services.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 3 2010-07-01 2010-07-01 true Responsibilities and operations of command claims... operations of command claims services. (a) Chiefs of command claims services. Chiefs of command claims... Commander USARCS, and assigned an office code. However, the chief of a command claims service may...

32 CFR 700.703 - To announce assumption of command.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false To announce assumption of command. 700.703... Chief and Other Commanders Titles and Duties of Commanders § 700.703 To announce assumption of command. (a) Upon assuming command, commanders shall so advise appropriate superiors, and the units of their...

32 CFR 700.703 - To announce assumption of command.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false To announce assumption of command. 700.703... Chief and Other Commanders Titles and Duties of Commanders § 700.703 To announce assumption of command. (a) Upon assuming command, commanders shall so advise appropriate superiors, and the units of their...

32 CFR 700.703 - To announce assumption of command.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false To announce assumption of command. 700.703... Chief and Other Commanders Titles and Duties of Commanders § 700.703 To announce assumption of command. (a) Upon assuming command, commanders shall so advise appropriate superiors, and the units of their...

32 CFR 536.8 - Responsibilities and operations of command claims services.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 3 2011-07-01 2009-07-01 true Responsibilities and operations of command claims... operations of command claims services. (a) Chiefs of command claims services. Chiefs of command claims... Commander USARCS, and assigned an office code. However, the chief of a command claims service may...

32 CFR 536.8 - Responsibilities and operations of command claims services.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 3 2012-07-01 2009-07-01 true Responsibilities and operations of command claims... operations of command claims services. (a) Chiefs of command claims services. Chiefs of command claims... Commander USARCS, and assigned an office code. However, the chief of a command claims service may...

A simple behaviour provides accuracy and flexibility in odour plume tracking--the robotic control of sensory-motor coupling in silkmoths.

PubMed

Ando, Noriyasu; Kanzaki, Ryohei

2015-12-01

Odour plume tracking is an essential behaviour for animal survival. A fundamental strategy for this is to move upstream and then across-stream. Male silkmoths, Bombyx mori, display this strategy as a pre-programmed sequential behaviour. They walk forward (surge) in response to the female sex pheromone and perform a zigzagging 'mating dance'. Though pre-programmed, the surge direction is modulated by bilateral olfactory input and optic flow. However, the nature of the interaction between these two sensory modalities and contribution of the resultant motor command to localizing an odour source are still unknown. We evaluated the ability of the silkmoth to localize an odour source under conditions of disturbed sensory-motor coupling, using a silkmoth-driven mobile robot. The significance of the bilateral olfaction of the moth was confirmed by inverting the olfactory input to the antennae, or its motor output. Inversion of the motor output induced consecutive circling, which was inhibited by covering the visual field of the moth. This suggests that the corollary discharge from the motor command and the reafference of self-generated optic flow generate compensatory signals to guide the surge accurately. Additionally, after inverting the olfactory input, the robot successfully tracked the odour plume by using a combination of behaviours. These results indicate that accurate guidance of the reflexive surge by integrating bilateral olfactory and visual information with innate pre-programmed behaviours increases the flexibility to track an odour plume even under disturbed circumstances. © 2015. Published by The Company of Biologists Ltd.

Interfacing and Verifying ALHAT Safe Precision Landing Systems with the Morpheus Vehicle

NASA Technical Reports Server (NTRS)

Carson, John M., III; Hirsh, Robert L.; Roback, Vincent E.; Villalpando, Carlos; Busa, Joseph L.; Pierrottet, Diego F.; Trawny, Nikolas; Martin, Keith E.; Hines, Glenn D.

2015-01-01

The NASA Autonomous precision Landing and Hazard Avoidance Technology (ALHAT) project developed a suite of prototype sensors to enable autonomous and safe precision landing of robotic or crewed vehicles under any terrain lighting conditions. Development of the ALHAT sensor suite was a cross-NASA effort, culminating in integration and testing on-board a variety of terrestrial vehicles toward infusion into future spaceflight applications. Terrestrial tests were conducted on specialized test gantries, moving trucks, helicopter flights, and a flight test onboard the NASA Morpheus free-flying, rocket-propulsive flight-test vehicle. To accomplish these tests, a tedious integration process was developed and followed, which included both command and telemetry interfacing, as well as sensor alignment and calibration verification to ensure valid test data to analyze ALHAT and Guidance, Navigation and Control (GNC) performance. This was especially true for the flight test campaign of ALHAT onboard Morpheus. For interfacing of ALHAT sensors to the Morpheus flight system, an adaptable command and telemetry architecture was developed to allow for the evolution of per-sensor Interface Control Design/Documents (ICDs). Additionally, individual-sensor and on-vehicle verification testing was developed to ensure functional operation of the ALHAT sensors onboard the vehicle, as well as precision-measurement validity for each ALHAT sensor when integrated within the Morpheus GNC system. This paper provides some insight into the interface development and the integrated-systems verification that were a part of the build-up toward success of the ALHAT and Morpheus flight test campaigns in 2014. These campaigns provided valuable performance data that is refining the path toward spaceflight infusion of the ALHAT sensor suite.

Controlling Herds of Cooperative Robots

NASA Technical Reports Server (NTRS)

Quadrelli, Marco B.

2006-01-01

A document poses, and suggests a program of research for answering, questions of how to achieve autonomous operation of herds of cooperative robots to be used in exploration and/or colonization of remote planets. In a typical scenario, a flock of mobile sensory robots would be deployed in a previously unexplored region, one of the robots would be designated the leader, and the leader would issue commands to move the robots to different locations or aim sensors at different targets to maximize scientific return. It would be necessary to provide for this hierarchical, cooperative behavior even in the face of such unpredictable factors as terrain obstacles. A potential-fields approach is proposed as a theoretical basis for developing methods of autonomous command and guidance of a herd. A survival-of-the-fittest approach is suggested as a theoretical basis for selection, mutation, and adaptation of a description of (1) the body, joints, sensors, actuators, and control computer of each robot, and (2) the connectivity of each robot with the rest of the herd, such that the herd could be regarded as consisting of a set of artificial creatures that evolve to adapt to a previously unknown environment. A distributed simulation environment has been developed to test the proposed approaches in the Titan environment. One blimp guides three surface sondes via a potential field approach. The results of the simulation demonstrate that the method used for control is feasible, even if significant uncertainty exists in the dynamics and environmental models, and that the control architecture provides the autonomy needed to enable surface science data collection.

The United States Navy Arctic Roadmap for 2014 to 2030

DTIC Science & Technology

2014-02-01

of the Oceanographer of the Navy; the Chief of Naval Research; Commander, Naval Meteorology and Oceanography Command; Commander, Office of Naval...Q3, FY14 Q3, FY15 FY15-18 FY18 2.3.4: Improve traditional meteorological forecast capability in the polar regions through the...CNE Commander Naval Forces Europe CNIC Commander Navy Installations Command CNMOC Commander Naval Meteorology and Oceanography Command CNO Chief

32 CFR 536.12 - Commanding General, U.S. Army Medical Command.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 3 2011-07-01 2009-07-01 true Commanding General, U.S. Army Medical Command... AND ACCOUNTS CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.12 Commanding General, U.S. Army Medical Command. (a) After consulting with the Commander USARCS on the selection of medical claims...

32 CFR 536.14 - Commanders of major Army commands.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 3 2012-07-01 2009-07-01 true Commanders of major Army commands. 536.14 Section... CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.14 Commanders of major Army commands... respective commands for compliance with the responsibilities assigned in §§ 536.9 and 536.10. (b) Assist...

32 CFR 536.12 - Commanding General, U.S. Army Medical Command.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 3 2012-07-01 2009-07-01 true Commanding General, U.S. Army Medical Command... AND ACCOUNTS CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.12 Commanding General, U.S. Army Medical Command. (a) After consulting with the Commander USARCS on the selection of medical claims...

32 CFR 536.14 - Commanders of major Army commands.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 3 2010-07-01 2010-07-01 true Commanders of major Army commands. 536.14 Section... CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.14 Commanders of major Army commands... respective commands for compliance with the responsibilities assigned in §§ 536.9 and 536.10. (b) Assist...

32 CFR 536.14 - Commanders of major Army commands.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 3 2013-07-01 2013-07-01 false Commanders of major Army commands. 536.14... ACCOUNTS CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.14 Commanders of major Army commands... respective commands for compliance with the responsibilities assigned in §§ 536.9 and 536.10. (b) Assist...

32 CFR 536.14 - Commanders of major Army commands.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 3 2011-07-01 2009-07-01 true Commanders of major Army commands. 536.14 Section... CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.14 Commanders of major Army commands... respective commands for compliance with the responsibilities assigned in §§ 536.9 and 536.10. (b) Assist...

32 CFR 536.12 - Commanding General, U.S. Army Medical Command.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 3 2014-07-01 2014-07-01 false Commanding General, U.S. Army Medical Command... AND ACCOUNTS CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.12 Commanding General, U.S. Army Medical Command. (a) After consulting with the Commander USARCS on the selection of medical claims...

32 CFR 536.12 - Commanding General, U.S. Army Medical Command.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 3 2010-07-01 2010-07-01 true Commanding General, U.S. Army Medical Command... AND ACCOUNTS CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.12 Commanding General, U.S. Army Medical Command. (a) After consulting with the Commander USARCS on the selection of medical claims...

32 CFR 536.14 - Commanders of major Army commands.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 3 2014-07-01 2014-07-01 false Commanders of major Army commands. 536.14... ACCOUNTS CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.14 Commanders of major Army commands... respective commands for compliance with the responsibilities assigned in §§ 536.9 and 536.10. (b) Assist...

32 CFR 536.12 - Commanding General, U.S. Army Medical Command.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 3 2013-07-01 2013-07-01 false Commanding General, U.S. Army Medical Command... AND ACCOUNTS CLAIMS AGAINST THE UNITED STATES The Army Claims System § 536.12 Commanding General, U.S. Army Medical Command. (a) After consulting with the Commander USARCS on the selection of medical claims...

The SAS-3 delayed command system

NASA Technical Reports Server (NTRS)

Hoffman, E. J.

1975-01-01

To meet the requirements arising from the increased complexity of the power, attitude control and telemetry systems, a full redundant high-performance control section with delayed command capability was designed for the Small Astronomy Satellite-3 (SAS-3). The relay command system of SAS-3 is characterized by 56 bystate relay commands, with capability for handling up to 64 commands in future versions. The 'short' data command service of SAS-1 and SAS-2 consisting of shifting 24-bit words to two users was expanded to five users and augmented with a 'long load' data command service (up to 4080 bits) used to program the telemetry system and the delayed command subsystem. The inclusion of a delayed command service ensures a program of up to 30 relay or short data commands to be loaded for execution at designated times. The design and system operation of the SAS-3 command section are analyzed, with special attention given to the delayed command subsystem.

14 CFR 91.1031 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 2 2011-01-01 2011-01-01 false Pilot in command or second in command... RULES Fractional Ownership Operations Program Management § 91.1031 Pilot in command or second in command: Designation required. (a) Each program manager must designate a— (1) Pilot in command for each program flight...

32 CFR 724.405 - Commandant of the Marine Corps or the Commander, Naval Military Personnel Command.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false Commandant of the Marine Corps or the Commander, Naval Military Personnel Command. 724.405 Section 724.405 National Defense Department of Defense... Personnel Command. Personnel managers of the Marine Corps and the Navy; responsible for providing limited...

32 CFR 700.1058 - Command of a submarine.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false Command of a submarine. 700.1058 Section 700... Command Detail to Duty § 700.1058 Command of a submarine. The officer detailed to command a submarine shall be an officer of the line in the Navy, eligible for command at sea and qualified for command of...

14 CFR 135.109 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Pilot in command or second in command... ON BOARD SUCH AIRCRAFT Flight Operations § 135.109 Pilot in command or second in command: Designation required. (a) Each certificate holder shall designate a— (1) Pilot in command for each flight; and (2...

32 CFR 724.405 - Commandant of the Marine Corps or the Commander, Naval Military Personnel Command.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Commandant of the Marine Corps or the Commander, Naval Military Personnel Command. 724.405 Section 724.405 National Defense Department of Defense... Personnel Command. Personnel managers of the Marine Corps and the Navy; responsible for providing limited...

14 CFR 1214.703 - Chain of command.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 5 2010-01-01 2010-01-01 false Chain of command. 1214.703 Section 1214.703... Shuttle Commander § 1214.703 Chain of command. (a) The Commander is a career NASA astronaut who has been... particular flight and is second in command of the flight. If the commander is unable to carry out the...

14 CFR 135.109 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Pilot in command or second in command... ON BOARD SUCH AIRCRAFT Flight Operations § 135.109 Pilot in command or second in command: Designation required. (a) Each certificate holder shall designate a— (1) Pilot in command for each flight; and (2...

32 CFR 724.405 - Commandant of the Marine Corps or the Commander, Naval Military Personnel Command.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false Commandant of the Marine Corps or the Commander, Naval Military Personnel Command. 724.405 Section 724.405 National Defense Department of Defense... Personnel Command. Personnel managers of the Marine Corps and the Navy; responsible for providing limited...

32 CFR 724.405 - Commandant of the Marine Corps or the Commander, Naval Military Personnel Command.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false Commandant of the Marine Corps or the Commander, Naval Military Personnel Command. 724.405 Section 724.405 National Defense Department of Defense... Personnel Command. Personnel managers of the Marine Corps and the Navy; responsible for providing limited...

14 CFR 91.1031 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 2 2012-01-01 2012-01-01 false Pilot in command or second in command... RULES Fractional Ownership Operations Program Management § 91.1031 Pilot in command or second in command: Designation required. (a) Each program manager must designate a— (1) Pilot in command for each program flight...

32 CFR 700.1058 - Command of a submarine.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Command of a submarine. 700.1058 Section 700... Command Detail to Duty § 700.1058 Command of a submarine. The officer detailed to command a submarine shall be an officer of the line in the Navy, eligible for command at sea and qualified for command of...

14 CFR 1214.703 - Chain of command.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Chain of command. 1214.703 Section 1214.703... Shuttle Commander § 1214.703 Chain of command. (a) The Commander is a career NASA astronaut who has been... particular flight and is second in command of the flight. If the commander is unable to carry out the...

14 CFR 91.1031 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Pilot in command or second in command... RULES Fractional Ownership Operations Program Management § 91.1031 Pilot in command or second in command: Designation required. (a) Each program manager must designate a— (1) Pilot in command for each program flight...

32 CFR 700.1058 - Command of a submarine.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false Command of a submarine. 700.1058 Section 700... Command Detail to Duty § 700.1058 Command of a submarine. The officer detailed to command a submarine shall be an officer of the line in the Navy, eligible for command at sea and qualified for command of...

32 CFR 700.1058 - Command of a submarine.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false Command of a submarine. 700.1058 Section 700... Command Detail to Duty § 700.1058 Command of a submarine. The officer detailed to command a submarine shall be an officer of the line in the Navy, eligible for command at sea and qualified for command of...

14 CFR 135.109 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Pilot in command or second in command... ON BOARD SUCH AIRCRAFT Flight Operations § 135.109 Pilot in command or second in command: Designation required. (a) Each certificate holder shall designate a— (1) Pilot in command for each flight; and (2...

14 CFR 135.109 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Pilot in command or second in command... ON BOARD SUCH AIRCRAFT Flight Operations § 135.109 Pilot in command or second in command: Designation required. (a) Each certificate holder shall designate a— (1) Pilot in command for each flight; and (2...

32 CFR 700.1058 - Command of a submarine.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false Command of a submarine. 700.1058 Section 700... Command Detail to Duty § 700.1058 Command of a submarine. The officer detailed to command a submarine shall be an officer of the line in the Navy, eligible for command at sea and qualified for command of...

32 CFR 724.405 - Commandant of the Marine Corps or the Commander, Naval Military Personnel Command.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false Commandant of the Marine Corps or the Commander, Naval Military Personnel Command. 724.405 Section 724.405 National Defense Department of Defense... Personnel Command. Personnel managers of the Marine Corps and the Navy; responsible for providing limited...

14 CFR 1214.703 - Chain of command.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false Chain of command. 1214.703 Section 1214.703... Shuttle Commander § 1214.703 Chain of command. (a) The Commander is a career NASA astronaut who has been... particular flight and is second in command of the flight. If the commander is unable to carry out the...

14 CFR 1214.703 - Chain of command.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Chain of command. 1214.703 Section 1214.703... Shuttle Commander § 1214.703 Chain of command. (a) The Commander is a career NASA astronaut who has been... particular flight and is second in command of the flight. If the commander is unable to carry out the...

14 CFR 135.109 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Pilot in command or second in command... ON BOARD SUCH AIRCRAFT Flight Operations § 135.109 Pilot in command or second in command: Designation required. (a) Each certificate holder shall designate a— (1) Pilot in command for each flight; and (2...

14 CFR 91.1031 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 2 2014-01-01 2014-01-01 false Pilot in command or second in command... RULES Fractional Ownership Operations Program Management § 91.1031 Pilot in command or second in command: Designation required. (a) Each program manager must designate a— (1) Pilot in command for each program flight...

14 CFR 91.1031 - Pilot in command or second in command: Designation required.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 2 2013-01-01 2013-01-01 false Pilot in command or second in command... RULES Fractional Ownership Operations Program Management § 91.1031 Pilot in command or second in command: Designation required. (a) Each program manager must designate a— (1) Pilot in command for each program flight...

Re-engineering the Multimission Command System at the Jet Propulsion Laboratory

NASA Technical Reports Server (NTRS)

Alexander, Scott; Biesiadecki, Jeff; Cox, Nagin; Murphy, Susan C.; Reeve, Tim

1994-01-01

The Operations Engineering Lab (OEL) at JPL has developed the multimission command system as part of JPL's Advanced Multimission Operations System. The command system provides an advanced multimission environment for secure, concurrent commanding of multiple spacecraft. The command functions include real-time command generation, command translation and radiation, status reporting, some remote control of Deep Space Network antenna functions, and command file management. The mission-independent architecture has allowed easy adaptation to new flight projects and the system currently supports all JPL planetary missions (Voyager, Galileo, Magellan, Ulysses, Mars Pathfinder, and CASSINI). This paper will discuss the design and implementation of the command software, especially trade-offs and lessons learned from practical operational use. The lessons learned have resulted in a re-engineering of the command system, especially in its user interface and new automation capabilities. The redesign has allowed streamlining of command operations with significant improvements in productivity and ease of use. In addition, the new system has provided a command capability that works equally well for real-time operations and within a spacecraft testbed. This paper will also discuss new development work including a multimission command database toolkit, a universal command translator for sequencing and real-time commands, and incorporation of telecommand capabilities for new missions.

14 CFR § 1214.703 - Chain of command.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 5 2014-01-01 2014-01-01 false Chain of command. § 1214.703 Section Â... of the Space Shuttle Commander § 1214.703 Chain of command. (a) The Commander is a career NASA... the pilot on a particular flight and is second in command of the flight. If the commander is unable to...

Evaluation of Organisational Interoperabiity in a Network Centric Warfare Environment

DTIC Science & Technology

2004-09-01

understanding developed. Command and Coordination examines issues related to command structure, command and leadership styles . Ethos covers socio...harmonisation of command arrangements and the accommodation of differences in command and leadership styles . 3.2.4 Ethos Future warfare will... leadership styles . • changes to give less emphasis to hierarchy and command and more to coordination. Any reference to a single chain of command has been

Fuel cell system logic for differentiating between rapid and normal shutdown commands

DOEpatents

Keskula, Donald H.; Doan, Tien M.; Clingerman, Bruce J.

2000-01-01

A method of controlling the operation of a fuel cell system wherein each shutdown command for the system is subjected to decision logic which determines whether the command should be a normal shutdown command or rapid shutdown command. If the logic determines that the shutdown command should be a normal shutdown command, then the system is shutdown in a normal step-by-step process in which the hydrogen stream is consumed within the system. If the logic determines that the shutdown command should be a rapid shutdown command, the hydrogen stream is removed from the system either by dumping to atmosphere or routing to storage.

Image-based tracking and sensor resource management for UAVs in an urban environment

NASA Astrophysics Data System (ADS)

Samant, Ashwin; Chang, K. C.

2010-04-01

Coordination and deployment of multiple unmanned air vehicles (UAVs) requires a lot of human resources in order to carry out a successful mission. The complexity of such a surveillance mission is significantly increased in the case of an urban environment where targets can easily escape from the UAV's field of view (FOV) due to intervening building and line-of-sight obstruction. In the proposed methodology, we focus on the control and coordination of multiple UAVs having gimbaled video sensor onboard for tracking multiple targets in an urban environment. We developed optimal path planning algorithms with emphasis on dynamic target prioritizations and persistent target updates. The command center is responsible for target prioritization and autonomous control of multiple UAVs, enabling a single operator to monitor and control a team of UAVs from a remote location. The results are obtained using extensive 3D simulations in Google Earth using Tangent plus Lyapunov vector field guidance for target tracking.

Current trends in small vocabulary speech recognition for equipment control

NASA Astrophysics Data System (ADS)

Doukas, Nikolaos; Bardis, Nikolaos G.

2017-09-01

Speech recognition systems allow human - machine communication to acquire an intuitive nature that approaches the simplicity of inter - human communication. Small vocabulary speech recognition is a subset of the overall speech recognition problem, where only a small number of words need to be recognized. Speaker independent small vocabulary recognition can find significant applications in field equipment used by military personnel. Such equipment may typically be controlled by a small number of commands that need to be given quickly and accurately, under conditions where delicate manual operations are difficult to achieve. This type of application could hence significantly benefit by the use of robust voice operated control components, as they would facilitate the interaction with their users and render it much more reliable in times of crisis. This paper presents current challenges involved in attaining efficient and robust small vocabulary speech recognition. These challenges concern feature selection, classification techniques, speaker diversity and noise effects. A state machine approach is presented that facilitates the voice guidance of different equipment in a variety of situations.

ISS GN and C - First Year Surprises

NASA Technical Reports Server (NTRS)

Begley, Michael

2002-01-01

Assembly of the International Space Station (ISS) began in late 1998 with the joining of the first two US and Russ ian elements. For more than two years, the outpost was served by two Russian Guidance, Navigation, and Control (GN&C) systems. The station requires orbital translation and attitude control functions for its 100+ configurations, from the nascent two-module station to the half million kilogram completed station owned and operated by seventeen nations. With the launch of the US Laboratory module in February 2001, the integration of the US GN&C system with its Russian counterpart laid the foundation for such a robust system. In its first year of combined operation, the ISS GN&C system has performed admirably, even better than many expected, but there have been surprises. Loss of command capability, loss of communication between segments, a control system force-fight, and "non-propulsive vents" that weren't - such events have repeatedly underscored the importance of thorough program integration, testing, and operation, both across subsystem boundaries and across international borders.

Spaceport Command and Control System Software Development

NASA Technical Reports Server (NTRS)

Kessluk, Jonathan

2017-01-01

During the course of this internship, software was developed to ensure the efficient management and allocation of an employee to an area of their expertise or experience that may otherwise have gone unnoticed. This directly affects any future missions prescribed to the SLS by allowing management to easily see where employees can be re-allocated to different mission specific projects or assist a project that may be lacking in a specific field. This software is intended to provide proof of NASA's diligence and deliberation in hiring new employees and in providing training and guidance to employees who may have fallen short of expectations. Allowing management to more easily statistically track and monitor the supply and demand of employees with specific experience will help introduce a beneficial culture where employees are given the ability to grow and hone skills which might otherwise atrophy over time. With this new system in place, NASA can prove the employees they hire and already have are exemplary and will remain exemplary to serve the nation as a whole.

Vibrotactile pattern recognition: a portable compact tactile matrix.

PubMed

Thullier, Francine; Bolmont, Benoît; Lestienne, Francis G

2012-02-01

Compact tactile matrix (CTM) is a vibrotactile device composed of a seven-by-seven array of electromechanical vibrators "tactip" used to represent tactile patterns applied to a small skin area. The CTM uses a dynamic feature to generate spatiotemporal tactile patterns. The design requirements focus particularly on maximizing the transmission of the vibration from one tactip to the others as well as to the skin over a square area of 16 cm (2) while simultaneously minimizing the transmission of vibrations throughout the overall structure of the CTM. Experiments were conducted on 22 unpracticed subjects to evaluate how the CTM could be used to develop a tactile semantics for communication of instructions in order to test the ability of the subjects to identify: 1) directional prescriptors for gesture guidance and 2) instructional commands for operational task requirements in a military context. The results indicate that, after familiarization, recognition accuracies in the tactile patterns were remarkably precise for more 80% of the subjects. © 2011 IEEE

A Uniform Ontology for Software Interfaces

NASA Technical Reports Server (NTRS)

Feyock, Stefan

2002-01-01

It is universally the case that computer users who are not also computer specialists prefer to deal with computers' in terms of a familiar ontology, namely that of their application domains. For example, the well-known Windows ontology assumes that the user is an office worker, and therefore should be presented with a "desktop environment" featuring entities such as (virtual) file folders, documents, appointment calendars, and the like, rather than a world of machine registers and machine language instructions, or even the DOS command level. The central theme of this research has been the proposition that the user interacting with a software system should have at his disposal both the ontology underlying the system, as well as a model of the system. This information is necessary for the understanding of the system in use, as well as for the automatic generation of assistance for the user, both in solving the problem for which the application is designed, and for providing guidance in the capabilities and use of the system.

Evaluation of a Tool for Airborne-Managed In-Trail Approach Spacing

NASA Technical Reports Server (NTRS)

Oseguera-Lohr, Rosa M.; Lohr, Gary W.; Abbott, Terence S.; Nadler, Eric D.; Eischeid, Todd

2005-01-01

The Advanced Terminal Area Approach Spacing (ATAAS) tool uses Automatic Dependent Surveillance-Broadcast aircraft state data to compute a speed command for an ATAAS-equipped aircraft to follow and obtain a required time interval behind another aircraft. The ATAAS tool and candidate operational procedures were tested in a high-fidelity, full mission simulator with active airline subject pilots flying an arrival scenario to obtain pilot perceptions of acceptability and workload for the concept. The aircraft consistently achieved the target spacing interval within 1 s when the ATAAS speed guidance was autothrottle-coupled and a slightly greater (4 - 5 s) but consistent interval with pilot-controlled speed changes. The subject pilots rated the ATAAS workload as similar to one with standard procedures for a nominal Instrument Landing System (ILS) approach. They also rated highly various procedural aspects (including amount of head-down time required). Eyetracker data showed only slight changes in instrument scan patterns for ATAAS versus standard ILS procedures.

Local health department 2009 H1N1 influenza vaccination clinics-CDC staffing model comparison and other best practices.

PubMed

Porter, Dayna; Hall, Mark; Hartl, Brian; Raevsky, Cathy; Peacock, Roberta; Kraker, David; Walls, Sandra; Brink, Gail

2011-01-01

Mass vaccination clinic staffing models, such as the Centers for Disease Control and Prevention Large-Scale Vaccination Clinic Output and Staff Estimates: An Example, provide guidance on appropriate roles and number of staff for successful mass vaccination clinics within local and state health departments. The Kent County Health Department used this model as a starting point for mass vaccination clinics in response to 2009 H1N1 influenza. In addition to discussion of successful modification of the Centers for Disease Control and Prevention model to maximize local health department mass vaccination clinic efficiency, additional best practices including use of the Incident Command System and a reservation system are provided. Use of the provided modified staffing model and additional best practices will increase the success of health department mass vaccination clinics, and should be considered not only for future public health emergencies, but also for seasonal influenza vaccination campaigns.

75 FR 19627 - Privacy Act of 1974; System of Records

Federal Register 2010, 2011, 2012, 2013, 2014

2010-04-15

... address: Delete entry and replace with ``Commander, Navy Personnel Command (PERS-31), 5720 Integrity Drive... to the Commander, Navy Personnel Command (PERS-312), 5720 Integrity Drive, Millington, TN 38055-3120... should address written inquiries to Commander, Navy Personnel Command (PERS- 312), 5720 Integrity Drive...

32 CFR 700.860 - Customs and immigration inspections.

Code of Federal Regulations, 2010 CFR

2010-07-01

... Commanding Officer Commanding Officers Afloat § 700.860 Customs and immigration inspections. (a) The commanding officer or aircraft commander shall facilitate any proper examination which it may be the duty of.... The commanding officer or air craft commander shall not permit a foreign customs officer or an...

32 CFR 700.860 - Customs and immigration inspections.

Code of Federal Regulations, 2012 CFR

2012-07-01

... Commanding Officer Commanding Officers Afloat § 700.860 Customs and immigration inspections. (a) The commanding officer or aircraft commander shall facilitate any proper examination which it may be the duty of.... The commanding officer or air craft commander shall not permit a foreign customs officer or an...

32 CFR 700.860 - Customs and immigration inspections.

Code of Federal Regulations, 2013 CFR

2013-07-01

... Commanding Officer Commanding Officers Afloat § 700.860 Customs and immigration inspections. (a) The commanding officer or aircraft commander shall facilitate any proper examination which it may be the duty of.... The commanding officer or air craft commander shall not permit a foreign customs officer or an...

32 CFR 700.860 - Customs and immigration inspections.

Code of Federal Regulations, 2014 CFR

2014-07-01

... Commanding Officer Commanding Officers Afloat § 700.860 Customs and immigration inspections. (a) The commanding officer or aircraft commander shall facilitate any proper examination which it may be the duty of.... The commanding officer or air craft commander shall not permit a foreign customs officer or an...

32 CFR 700.860 - Customs and immigration inspections.

Code of Federal Regulations, 2011 CFR

2011-07-01

... Commanding Officer Commanding Officers Afloat § 700.860 Customs and immigration inspections. (a) The commanding officer or aircraft commander shall facilitate any proper examination which it may be the duty of.... The commanding officer or air craft commander shall not permit a foreign customs officer or an...

32 CFR 700.804 - Organization of commands.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false Organization of commands. 700.804 Section 700... REGULATIONS AND OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers in General § 700.804 Organization of commands. All commands and other activities of the...

32 CFR 700.804 - Organization of commands.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Organization of commands. 700.804 Section 700... REGULATIONS AND OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers in General § 700.804 Organization of commands. All commands and other activities of the...

32 CFR 700.804 - Organization of commands.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false Organization of commands. 700.804 Section 700... REGULATIONS AND OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers in General § 700.804 Organization of commands. All commands and other activities of the...

32 CFR 700.804 - Organization of commands.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false Organization of commands. 700.804 Section 700... REGULATIONS AND OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers in General § 700.804 Organization of commands. All commands and other activities of the...

32 CFR 700.804 - Organization of commands.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false Organization of commands. 700.804 Section 700... REGULATIONS AND OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers in General § 700.804 Organization of commands. All commands and other activities of the...

7. General view of command center, building 501, looking west ...

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

7. General view of command center, building 501, looking west - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

6. General view of command center, building 501, looking east ...

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

6. General view of command center, building 501, looking east - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

32 CFR 724.306 - Functions of the Commander, Naval Medical Command.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false Functions of the Commander, Naval Medical Command. 724.306 Section 724.306 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... § 724.306 Functions of the Commander, Naval Medical Command. Under the CNO the COMNAVMEDCOM shall...

32 CFR 755.6 - Action where offenders are members of one command.

Code of Federal Regulations, 2011 CFR

2011-07-01

... command. 755.6 Section 755.6 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... Action where offenders are members of one command. (a) Action by commanding officer. The commanding... declines to submit information, he shall so state in writing within the 20 day period. The commanding...

32 CFR 724.306 - Functions of the Commander, Naval Medical Command.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false Functions of the Commander, Naval Medical Command. 724.306 Section 724.306 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... § 724.306 Functions of the Commander, Naval Medical Command. Under the CNO the COMNAVMEDCOM shall...

14 CFR 1215.106 - User command and tracking data.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 5 2010-01-01 2010-01-01 false User command and tracking data. 1215.106... User command and tracking data. (a) User command data may enter the TDRSS via the NASCOM interface at one of three locations: (1) For Shuttle payloads which utilize the Shuttle commanding system, command...

32 CFR 755.6 - Action where offenders are members of one command.

Code of Federal Regulations, 2013 CFR

2013-07-01

... command. 755.6 Section 755.6 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... Action where offenders are members of one command. (a) Action by commanding officer. The commanding... declines to submit information, he shall so state in writing within the 20 day period. The commanding...

32 CFR 755.6 - Action where offenders are members of one command.

Code of Federal Regulations, 2014 CFR

2014-07-01

... command. 755.6 Section 755.6 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... Action where offenders are members of one command. (a) Action by commanding officer. The commanding... declines to submit information, he shall so state in writing within the 20 day period. The commanding...

32 CFR 755.6 - Action where offenders are members of one command.

Code of Federal Regulations, 2012 CFR

2012-07-01

... command. 755.6 Section 755.6 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... Action where offenders are members of one command. (a) Action by commanding officer. The commanding... declines to submit information, he shall so state in writing within the 20 day period. The commanding...

32 CFR 724.306 - Functions of the Commander, Naval Medical Command.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false Functions of the Commander, Naval Medical Command. 724.306 Section 724.306 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... § 724.306 Functions of the Commander, Naval Medical Command. Under the CNO the COMNAVMEDCOM shall...

32 CFR 724.306 - Functions of the Commander, Naval Medical Command.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Functions of the Commander, Naval Medical Command. 724.306 Section 724.306 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... § 724.306 Functions of the Commander, Naval Medical Command. Under the CNO the COMNAVMEDCOM shall...

14 CFR 1215.106 - User command and tracking data.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false User command and tracking data. 1215.106... User command and tracking data. (a) User command data may enter the TDRSS via the NASCOM interface at one of three locations: (1) For Shuttle payloads which utilize the Shuttle commanding system, command...

14 CFR 1215.106 - User command and tracking data.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true User command and tracking data. 1215.106... User command and tracking data. (a) User command data may enter the TDRSS via the NASCOM interface at one of three locations: (1) For Shuttle payloads which utilize the Shuttle commanding system, command...

32 CFR 755.6 - Action where offenders are members of one command.

Code of Federal Regulations, 2010 CFR

2010-07-01

... command. 755.6 Section 755.6 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... Action where offenders are members of one command. (a) Action by commanding officer. The commanding... declines to submit information, he shall so state in writing within the 20 day period. The commanding...

32 CFR 724.306 - Functions of the Commander, Naval Medical Command.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false Functions of the Commander, Naval Medical Command. 724.306 Section 724.306 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY... § 724.306 Functions of the Commander, Naval Medical Command. Under the CNO the COMNAVMEDCOM shall...

11. SAC command center, main operations area, underground structure, building ...

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

11. SAC command center, main operations area, underground structure, building 501, undated - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

4. Sac shield at entry of command center, building 501, ...

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

4. Sac shield at entry of command center, building 501, looking west - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

9. SAC command center, main operations area, underground structure, building ...

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

9. SAC command center, main operations area, underground structure, building 501, undated - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

13. SAC command center, weather center, underground structure, building 501, ...

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

13. SAC command center, weather center, underground structure, building 501, undated - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

Navy Operational Planner

DTIC Science & Technology

2015-03-01

wine warfare NCC naval component commander NFC numbered fleet commander NM nautical mile NMP Navy mission planner NOP Navy...principles for naval component commanders ( NCCs ), numbered fleet commanders (NFCs) or joint force maritime component commanders (JFMCCs) and their

Torque shudder protection device and method

DOEpatents

King, Robert D.; De Doncker, Rik W. A. A.; Szczesny, Paul M.

1997-01-01

A torque shudder protection device for an induction machine includes a flux command generator for supplying a steady state flux command and a torque shudder detector for supplying a status including a negative status to indicate a lack of torque shudder and a positive status to indicate a presence of torque shudder. A flux adapter uses the steady state flux command and the status to supply a present flux command identical to the steady state flux command for a negative status and different from the steady state flux command for a positive status. A limiter can receive the present flux command, prevent the present flux command from exceeding a predetermined maximum flux command magnitude, and supply the present flux command to a field oriented controller. After determining a critical electrical excitation frequency at which a torque shudder occurs for the induction machine, a flux adjuster can monitor the electrical excitation frequency of the induction machine and adjust a flux command to prevent the monitored electrical excitation frequency from reaching the critical electrical excitation frequency.

Torque shudder protection device and method

DOEpatents

King, R.D.; Doncker, R.W.A.A. De.; Szczesny, P.M.

1997-03-11

A torque shudder protection device for an induction machine includes a flux command generator for supplying a steady state flux command and a torque shudder detector for supplying a status including a negative status to indicate a lack of torque shudder and a positive status to indicate a presence of torque shudder. A flux adapter uses the steady state flux command and the status to supply a present flux command identical to the steady state flux command for a negative status and different from the steady state flux command for a positive status. A limiter can receive the present flux command, prevent the present flux command from exceeding a predetermined maximum flux command magnitude, and supply the present flux command to a field oriented controller. After determining a critical electrical excitation frequency at which a torque shudder occurs for the induction machine, a flux adjuster can monitor the electrical excitation frequency of the induction machine and adjust a flux command to prevent the monitored electrical excitation frequency from reaching the critical electrical excitation frequency. 5 figs.

10. SAC command center, main operations area, underground structure, building ...

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

10. SAC command center, main operations area, underground structure, building 501, circa 1980 - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

12. SAC command center, main operations area, underground structure, building ...

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

12. SAC command center, main operations area, underground structure, building 501, circa 1960 - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

Decentralized robust nonlinear model predictive controller for unmanned aerial systems

NASA Astrophysics Data System (ADS)

Garcia Garreton, Gonzalo A.

The nonlinear and unsteady nature of aircraft aerodynamics together with limited practical range of controls and state variables make the use of the linear control theory inadequate especially in the presence of external disturbances, such as wind. In the classical approach, aircraft are controlled by multiple inner and outer loops, designed separately and sequentially. For unmanned aerial systems in particular, control technology must evolve to a point where autonomy is extended to the entire mission flight envelope. This requires advanced controllers that have sufficient robustness, track complex trajectories, and use all the vehicles control capabilities at higher levels of accuracy. In this work, a robust nonlinear model predictive controller is designed to command and control an unmanned aerial system to track complex tight trajectories in the presence of internal and external perturbance. The Flight System developed in this work achieves the above performance by using: 1. A nonlinear guidance algorithm that enables the vehicle to follow an arbitrary trajectory shaped by moving points; 2. A formulation that embeds the guidance logic and trajectory information in the aircraft model, avoiding cross coupling and control degradation; 3. An artificial neural network, designed to adaptively estimate and provide aerodynamic and propulsive forces in real-time; and 4. A mixed sensitivity approach that enhances the robustness for a nonlinear model predictive controller overcoming the effect of un-modeled dynamics, external disturbances such as wind, and measurement additive perturbations, such as noise and biases. These elements have been integrated and tested in simulation and with previously stored flight test data and shown to be feasible.

32 CFR 700.1054 - Command of a naval base.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false Command of a naval base. 700.1054 Section 700... Command Detail to Duty § 700.1054 Command of a naval base. The officer detailed to command a naval base shall be an officer of the line in the Navy, eligible for command at sea. ...

32 CFR 700.1054 - Command of a naval base.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false Command of a naval base. 700.1054 Section 700... Command Detail to Duty § 700.1054 Command of a naval base. The officer detailed to command a naval base shall be an officer of the line in the Navy, eligible for command at sea. ...

32 CFR 700.1056 - Command of a ship.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false Command of a ship. 700.1056 Section 700.1056... Command Detail to Duty § 700.1056 Command of a ship. (a) The officer detailed to command a commissioned ship shall be an officer of the line in the Navy eligible for command at sea. (b) The officer detailed...

32 CFR 700.1054 - Command of a naval base.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false Command of a naval base. 700.1054 Section 700... Command Detail to Duty § 700.1054 Command of a naval base. The officer detailed to command a naval base shall be an officer of the line in the Navy, eligible for command at sea. ...

32 CFR 700.1054 - Command of a naval base.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false Command of a naval base. 700.1054 Section 700... Command Detail to Duty § 700.1054 Command of a naval base. The officer detailed to command a naval base shall be an officer of the line in the Navy, eligible for command at sea. ...

32 CFR 700.1054 - Command of a naval base.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Command of a naval base. 700.1054 Section 700... Command Detail to Duty § 700.1054 Command of a naval base. The officer detailed to command a naval base shall be an officer of the line in the Navy, eligible for command at sea. ...

32 CFR 700.1056 - Command of a ship.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false Command of a ship. 700.1056 Section 700.1056... Command Detail to Duty § 700.1056 Command of a ship. (a) The officer detailed to command a commissioned ship shall be an officer of the line in the Navy eligible for command at sea. (b) The officer detailed...

32 CFR 700.1056 - Command of a ship.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Command of a ship. 700.1056 Section 700.1056... Command Detail to Duty § 700.1056 Command of a ship. (a) The officer detailed to command a commissioned ship shall be an officer of the line in the Navy eligible for command at sea. (b) The officer detailed...

32 CFR 700.1056 - Command of a ship.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false Command of a ship. 700.1056 Section 700.1056... Command Detail to Duty § 700.1056 Command of a ship. (a) The officer detailed to command a commissioned ship shall be an officer of the line in the Navy eligible for command at sea. (b) The officer detailed...

32 CFR 700.1056 - Command of a ship.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false Command of a ship. 700.1056 Section 700.1056... Command Detail to Duty § 700.1056 Command of a ship. (a) The officer detailed to command a commissioned ship shall be an officer of the line in the Navy eligible for command at sea. (b) The officer detailed...

NASIS data base management system: IBM 360 TSS implementation. Volume 5: Retrieval command system reference manual

NASA Technical Reports Server (NTRS)

1973-01-01

The retrieval command subsystem reference manual for the NASA Aerospace Safety Information System (NASIS) is presented. The command subsystem may be operated conversationally or in the batch mode. Retrieval commands are categorized into search-oriented and output-oriented commands. The characteristics of ancillary commands and their application are reported.

8. SAC command center underground structure, building 501, basement entry, ...

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

8. SAC command center underground structure, building 501, basement entry, machine room, April 11, 1955 - Offutt Air Force Base, Strategic Air Command Headquarters & Command Center, Command Center, 901 SAC Boulevard, Bellevue, Sarpy County, NE

Squad-Level Soldier-Robot Dynamics: Exploring Future Concepts Involving Intelligent Autonomous Robots

DTIC Science & Technology

2015-02-01

unanimous for the run and duck commands as other commands commonly used. The verbal commands surveyed, as well as other suggested verbal commands that...stop, and duck . Additional verbal commands suggested were shut down, follow, destroy, status, and move out. The verbal commands surveyed and the...identify the verbal commands you would use to control the squad and the ASM: Phrase Yes No Halt 9 3 Stop 9 3 Move 11 1 Run 7 5 Duck 6 6 Other

Defense.gov - Special Report - Travels With Mullen

Science.gov Websites

European Command’s change of command ceremony. Top Stories Stavridis Assumes Top European Command Post the top post at U.S. European Command. He will also serve as NATO's supreme allied commander for

32 CFR 700.1057 - Command of an air activity.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false Command of an air activity. 700.1057 Section 700... Command Detail to Duty § 700.1057 Command of an air activity. (a) The officer detailed to command a naval... for command at sea. (b) For the purposes of Title 10 U.S.C. § 5942, a naval air training squadron is...

78 FR 72025 - Security Zones; Naval Base Point Loma; Naval Mine Anti Submarine Warfare Command; San Diego Bay...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-12-02

...-AA87 Security Zones; Naval Base Point Loma; Naval Mine Anti Submarine Warfare Command; San Diego Bay... establishing a new security zone at the Naval Mine and Anti-Submarine Warfare Command to protect the relocated... Commander of Naval Base Point Loma, the Commander of the Naval Mine Anti Submarine Warfare Command, and the...

32 CFR 700.1057 - Command of an air activity.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false Command of an air activity. 700.1057 Section 700... Command Detail to Duty § 700.1057 Command of an air activity. (a) The officer detailed to command a naval... for command at sea. (b) For the purposes of Title 10 U.S.C. § 5942, a naval air training squadron is...

32 CFR 700.1057 - Command of an air activity.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false Command of an air activity. 700.1057 Section 700... Command Detail to Duty § 700.1057 Command of an air activity. (a) The officer detailed to command a naval... for command at sea. (b) For the purposes of Title 10 U.S.C. § 5942, a naval air training squadron is...

32 CFR 700.1057 - Command of an air activity.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false Command of an air activity. 700.1057 Section 700... Command Detail to Duty § 700.1057 Command of an air activity. (a) The officer detailed to command a naval... for command at sea. (b) For the purposes of Title 10 U.S.C. § 5942, a naval air training squadron is...

32 CFR 700.1057 - Command of an air activity.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Command of an air activity. 700.1057 Section 700... Command Detail to Duty § 700.1057 Command of an air activity. (a) The officer detailed to command a naval... for command at sea. (b) For the purposes of Title 10 U.S.C. § 5942, a naval air training squadron is...

14 CFR 417.303 - Command control system requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... flight termination system used for each launch. (f) Electromagnetic interference. Each command control system component must function within the electromagnetic environment to which it is exposed. A command... must prevent electromagnetic interference. (g) Command transmitter failover. A command control system...

14 CFR 417.303 - Command control system requirements.

Code of Federal Regulations, 2010 CFR

2010-01-01

... flight termination system used for each launch. (f) Electromagnetic interference. Each command control system component must function within the electromagnetic environment to which it is exposed. A command... must prevent electromagnetic interference. (g) Command transmitter failover. A command control system...

14 CFR 417.303 - Command control system requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... flight termination system used for each launch. (f) Electromagnetic interference. Each command control system component must function within the electromagnetic environment to which it is exposed. A command... must prevent electromagnetic interference. (g) Command transmitter failover. A command control system...

14 CFR 417.303 - Command control system requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... flight termination system used for each launch. (f) Electromagnetic interference. Each command control system component must function within the electromagnetic environment to which it is exposed. A command... must prevent electromagnetic interference. (g) Command transmitter failover. A command control system...

14 CFR 417.303 - Command control system requirements.

Code of Federal Regulations, 2011 CFR

2011-01-01

... flight termination system used for each launch. (f) Electromagnetic interference. Each command control system component must function within the electromagnetic environment to which it is exposed. A command... must prevent electromagnetic interference. (g) Command transmitter failover. A command control system...

Defense Headquarters: Geographic Combatant Commands Rely on Subordinate Commands for Mission Management and Execution

DTIC Science & Technology

2016-06-30

These figures do not include personnel performing contract services. The service component commands , subordinate unified commands , and joint task forces...GAO has previously found that the combatant commands do not have oversight or visibility over authorized manpower or assigned personnel at the...Jack Reed Ranking Member Committee on Armed Services United States Senate Defense Headquarters: Geographic Combatant Commands Rely on Subordinate

United States Forces Korea > Home

Science.gov Websites

commander; Gen. Leem Ho Young, Combined Forces Command deputy commander; and Gen. Lee Sun-jin, Gen. Lee, Sun Forces Command deputy commander; and Gen. Lee Sun-jin, Gen. Lee, Sun-Jin, Chairman of the Republic of deputy commander; and Gen. Lee Sun-jin, Gen. Lee, Sun-Jin, Chairman of the Republic of Korea Joint Chiefs

Incomplete Victory: General Allenby and Mission Command in Palestine, 1917-1918

DTIC Science & Technology

2012-12-14

challenges in mission command. While General Allenby, commanding the Allied Egyptian Expeditionary Force (EEF), gained several victories in the...challenges in mission command. While General Allenby, commanding the Allied Egyptian Expeditionary Force (EEF), gained several victories in the early stages...

The Fabric of Air Warfare; Doctrine, Operational Experience, and Integration of Strategic and Tactical Air Power From World War I Through World War II

DTIC Science & Technology

1991-04-01

African Air Forces, Middle East Air Command, based in Cairo, and RAP Malta Air Command. This, in effect, was a �theater� command in a larger sense, for...Force, under the command of AVM Sir Hugh Lloyd, and absorbed Malta Air Command and US XII Fighter Command, then under Pete Quesada, later commander...trained pilots, that exchange ratio steadily worsened for the enemy. In fact, the 5th Air Force could boast the two highest scoring American aces early

Numerical Electromagnetic Code (NEC)-Basic Scattering Code. Part I. User’s Manual.

DTIC Science & Technology

1979-09-01

Command RT : 29 I. Command PG: 32 J. Command GP: 35 K. Command CG: 36 L. Command SG: 39 M. Command AM: 44 N. Conumand PR: 48 0. Command NP: 49 P...these points and con- firm the validity of the solution. 1 0 1 -.- ’----.- ... The source presently considered in the computer code is an Plec - tric...Range Input 28 * RT : Translate and/or Rotate Coordinates 29 SG: Source Geometry Input IQ TO: Test Data Generation Options 17 [IN: Units of Input U)S

IT Security Support for Spaceport Command and Control System

NASA Technical Reports Server (NTRS)

McLain, Jeffrey

2013-01-01

During the fall 2013 semester, I worked at the Kennedy Space Center as an IT Security Intern in support of the Spaceport Command and Control System under the guidance of the IT Security Lead Engineer. Some of my responsibilities included assisting with security plan documentation collection, system hardware and software inventory, and malicious code and malware scanning. Throughout the semester, I had the opportunity to work on a wide range of security related projects. However, there are three projects in particular that stand out. The first project I completed was updating a large interactive spreadsheet that details the SANS Institutes Top 20 Critical Security Controls. My task was to add in all of the new commercial of the shelf (COTS) software listed on the SANS website that can be used to meet their Top 20 controls. In total, there are 153 unique security tools listed by SANS that meet one or more of their 20 controls. My second project was the creation of a database that will allow my mentor to keep track of the work done by the contractors that report to him in a more efficient manner by recording events as they occur throughout the quarter. Lastly, I expanded upon a security assessment of the Linux machines being used on center that I began last semester. To do this, I used a vulnerability and configuration tool that scans hosts remotely through the network and presents the user with an abundance of information detailing each machines configuration. The experience I gained from working on each of these projects has been invaluable, and I look forward to returning in the spring semester to continue working with the IT Security team.

Evolution of International Space Station GN&C System Across ISS Assembly Stages

NASA Technical Reports Server (NTRS)

Lee, Roscoe; Frank, K. D. (Technical Monitor)

1999-01-01

The Guidance Navigation and Control (GN&C) system for the International Space Station is initially implemented by the Functional Cargo Block (FGB) which was built by the Khrunichev Space Center under direct contract to Boeing. This element (Stage 1A/R) was launched on 20 November 1998 and is currently operating on-orbit. The components and capabilities of the FGB Motion Control System (MCS) are described. The next ISS element, which has GN&C functionality will be the Service Module (SM) built by Rocket Space Corporation-Energia. This module is scheduled for launch (Stage 1R) in early 2000. Following activation of the SM GN&C system, the FGB MCS is deactivated and no longer used. The components and capabilities of the SM GN&C system are described. When a Progress vehicle is attached to the ISS it can be used for reboost operations, based on commands provided by the Mission Control Center-Moscow. When a data connection is implemented between the SM and the Progress, the SM can command the Progress thrusters for attitude control and reboosts. On Stage 5A, the U.S. GN&C system will become activated when the U.S. Laboratory is de loyed and installed (launch schedule is currently TBD). The U.S. GN&C system provides non-propulsive control capabilities to support micro-gravity operations and minimize the use of propellant for attitude control, and an independent capability for determining the ISS state vector, attitude, attitude rate. and time.. The components and capabilities of the U.S. GN&C system are described and the interactions between the U.S. and Russian Segment GN&C systems are also described.

NORAD

Science.gov Websites

TERRENCE J. O'SHAUGHNESSY, USAF Command, United States Northern Command VIEW BIO LIEUTENANT GENERAL REYNOLD N. HOOVER, USA Deputy Commander, United States Northern Command VIEW BIO MAJOR GENERAL PEGGY C . COMBS, USA Chief of Staff, United States Northern Command VIEW BIO SERGEANT MAJOR PAUL MCKENNA, USMC

32 CFR 700.856 - Pilotage.

Code of Federal Regulations, 2012 CFR

2012-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.856 Pilotage. (a) The commanding officer shall: (1) Pilot the ship under all ordinary... to the commanding officer. The presence on board of a pilot shall not relieve the commanding officer...

32 CFR 700.856 - Pilotage.

Code of Federal Regulations, 2014 CFR

2014-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.856 Pilotage. (a) The commanding officer shall: (1) Pilot the ship under all ordinary... to the commanding officer. The presence on board of a pilot shall not relieve the commanding officer...

32 CFR 700.859 - Quarantine.

Code of Federal Regulations, 2013 CFR

2013-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.859 Quarantine. (a) The commanding officer or aircraft commander of a ship or... port or area within which the ship or aircraft is located. (b) The commanding officer shall give all...

32 CFR 700.856 - Pilotage.

Code of Federal Regulations, 2010 CFR

2010-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.856 Pilotage. (a) The commanding officer shall: (1) Pilot the ship under all ordinary... to the commanding officer. The presence on board of a pilot shall not relieve the commanding officer...

32 CFR 700.859 - Quarantine.

Code of Federal Regulations, 2010 CFR

2010-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.859 Quarantine. (a) The commanding officer or aircraft commander of a ship or... port or area within which the ship or aircraft is located. (b) The commanding officer shall give all...

32 CFR 700.859 - Quarantine.

Code of Federal Regulations, 2011 CFR

2011-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.859 Quarantine. (a) The commanding officer or aircraft commander of a ship or... port or area within which the ship or aircraft is located. (b) The commanding officer shall give all...

32 CFR 700.859 - Quarantine.

Code of Federal Regulations, 2012 CFR

2012-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.859 Quarantine. (a) The commanding officer or aircraft commander of a ship or... port or area within which the ship or aircraft is located. (b) The commanding officer shall give all...

32 CFR 700.856 - Pilotage.

Code of Federal Regulations, 2013 CFR

2013-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.856 Pilotage. (a) The commanding officer shall: (1) Pilot the ship under all ordinary... to the commanding officer. The presence on board of a pilot shall not relieve the commanding officer...

32 CFR 700.856 - Pilotage.

Code of Federal Regulations, 2011 CFR

2011-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.856 Pilotage. (a) The commanding officer shall: (1) Pilot the ship under all ordinary... to the commanding officer. The presence on board of a pilot shall not relieve the commanding officer...

32 CFR 700.859 - Quarantine.

Code of Federal Regulations, 2014 CFR

2014-07-01

... OFFICIAL RECORDS UNITED STATES NAVY REGULATIONS AND OFFICIAL RECORDS The Commanding Officer Commanding Officers Afloat § 700.859 Quarantine. (a) The commanding officer or aircraft commander of a ship or... port or area within which the ship or aircraft is located. (b) The commanding officer shall give all...

32 CFR 724.406 - Commander, Naval Medical Command.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 32 National Defense 5 2012-07-01 2012-07-01 false Commander, Naval Medical Command. 724.406 Section 724.406 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY PERSONNEL NAVAL..., Naval Medical Command. Custodian of Navy and Marine Corps health records. (See subpart C). ...

32 CFR 724.406 - Commander, Naval Medical Command.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 5 2010-07-01 2010-07-01 false Commander, Naval Medical Command. 724.406 Section 724.406 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY PERSONNEL NAVAL..., Naval Medical Command. Custodian of Navy and Marine Corps health records. (See subpart C). ...

32 CFR 724.406 - Commander, Naval Medical Command.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 5 2013-07-01 2013-07-01 false Commander, Naval Medical Command. 724.406 Section 724.406 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY PERSONNEL NAVAL..., Naval Medical Command. Custodian of Navy and Marine Corps health records. (See subpart C). ...

32 CFR 724.406 - Commander, Naval Medical Command.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 5 2011-07-01 2011-07-01 false Commander, Naval Medical Command. 724.406 Section 724.406 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY PERSONNEL NAVAL..., Naval Medical Command. Custodian of Navy and Marine Corps health records. (See subpart C). ...

32 CFR 724.406 - Commander, Naval Medical Command.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 32 National Defense 5 2014-07-01 2014-07-01 false Commander, Naval Medical Command. 724.406 Section 724.406 National Defense Department of Defense (Continued) DEPARTMENT OF THE NAVY PERSONNEL NAVAL..., Naval Medical Command. Custodian of Navy and Marine Corps health records. (See subpart C). ...

48 CFR 202.101 - Definitions.

Code of Federal Regulations, 2012 CFR

2012-10-01

... Command Air Force Materiel Command Air Force Reserve Command Air Combat Command Air Mobility Command Air... agencies have been delegated authority to act as head of the agency for their respective agencies (i.e., to... offers, means a procedure used in negotiated acquisitions, when market research is inconclusive for...

75 FR 49482 - Privacy Act of 1974; System of Records

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-13

... replace with ``Incident Report Records.'' System location: Delete entry and replace with ``Command Support... may be accessed only by the Commander, Deputy Commander, Chief, Command Support Division, or other... and replace with ``Command Support Division, EU1, Defense Information Systems Agency-Europe, APO AE...

75 FR 42719 - Privacy Act of 1974; System of Records

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-22

...: Commander, Navy Expeditionary Combat Command, 1575 Gator Blvd, Joint Expeditionary Base Little Creek... Expeditionary Combat Command, Code (N8), 1575 Gator Blvd, Joint Expeditionary Base Little Creek, Virginia Beach... to the Commander, Navy Expeditionary Combat Command, Code (N8), 1575 Gator Blvd, Joint Expeditionary...

Evaluation of shoulder integrity in space: first report of musculoskeletal US on the International Space Station.

PubMed

Fincke, E Michael; Padalka, Gennady; Lee, Doohi; van Holsbeeck, Marnix; Sargsyan, Ashot E; Hamilton, Douglas R; Martin, David; Melton, Shannon L; McFarlin, Kellie; Dulchavsky, Scott A

2005-02-01

Investigative procedures were approved by Henry Ford Human Investigation Committee and NASA Johnson Space Center Committee for Protection of Human Subjects. Informed consent was obtained. Authors evaluated ability of nonphysician crewmember to obtain diagnostic-quality musculoskeletal ultrasonographic (US) data of the shoulder by following a just-in-time training algorithm and using real-time remote guidance aboard the International Space Station (ISS). ISS Expedition-9 crewmembers attended a 2.5-hour didactic and hands-on US training session 4 months before launch. Aboard the ISS, they completed a 1-hour computer-based Onboard Proficiency Enhancement program 7 days before examination. Crewmembers did not receive specific training in shoulder anatomy or shoulder US techniques. Evaluation of astronaut shoulder integrity was done by using a Human Research Facility US system. Crew used special positioning techniques for subject and operator to facilitate US in microgravity environment. Common anatomic reference points aided initial probe placement. Real-time US video of shoulder was transmitted to remote experienced sonologists in Telescience Center at Johnson Space Center. Probe manipulation and equipment adjustments were guided with verbal commands from remote sonologists to astronaut operators to complete rotator cuff evaluation. Comprehensive US of crewmember's shoulder included transverse and longitudinal images of biceps and supraspinatus tendons and articular cartilage surface. Total examination time required to guide astronaut operator to acquire necessary images was approximately 15 minutes. Multiple arm and probe positions were used to acquire dynamic video images that were of excellent quality to allow evaluation of shoulder integrity. Postsession download and analysis of high-fidelity US images collected onboard demonstrated additional anatomic detail that could be used to exclude subtle injury. Musculoskeletal US can be performed in space by minimally trained operators by using remote guidance. This technique can be used to evaluate shoulder integrity in symptomatic crewmembers after strenuous extravehicular activities or to monitor microgravity-associated changes in musculoskeletal anatomy. Just-in-time training, combined with remote experienced physician guidance, may provide a useful approach to complex medical tasks performed by nonexperienced personnel in a variety of remote settings, including current and future space programs. (c) RSNA, 2004.

Evaluation of shoulder integrity in space: first report of musculoskeletal US on the International Space Station

NASA Technical Reports Server (NTRS)

Fincke, E. Michael; Padalka, Gennady; Lee, Doohi; van Holsbeeck, Marnix; Sargsyan, Ashot E.; Hamilton, Douglas R.; Martin, David; Melton, Shannon L.; McFarlin, Kellie; Dulchavsky, Scott A.

2005-01-01

Investigative procedures were approved by Henry Ford Human Investigation Committee and NASA Johnson Space Center Committee for Protection of Human Subjects. Informed consent was obtained. Authors evaluated ability of nonphysician crewmember to obtain diagnostic-quality musculoskeletal ultrasonographic (US) data of the shoulder by following a just-in-time training algorithm and using real-time remote guidance aboard the International Space Station (ISS). ISS Expedition-9 crewmembers attended a 2.5-hour didactic and hands-on US training session 4 months before launch. Aboard the ISS, they completed a 1-hour computer-based Onboard Proficiency Enhancement program 7 days before examination. Crewmembers did not receive specific training in shoulder anatomy or shoulder US techniques. Evaluation of astronaut shoulder integrity was done by using a Human Research Facility US system. Crew used special positioning techniques for subject and operator to facilitate US in microgravity environment. Common anatomic reference points aided initial probe placement. Real-time US video of shoulder was transmitted to remote experienced sonologists in Telescience Center at Johnson Space Center. Probe manipulation and equipment adjustments were guided with verbal commands from remote sonologists to astronaut operators to complete rotator cuff evaluation. Comprehensive US of crewmember's shoulder included transverse and longitudinal images of biceps and supraspinatus tendons and articular cartilage surface. Total examination time required to guide astronaut operator to acquire necessary images was approximately 15 minutes. Multiple arm and probe positions were used to acquire dynamic video images that were of excellent quality to allow evaluation of shoulder integrity. Postsession download and analysis of high-fidelity US images collected onboard demonstrated additional anatomic detail that could be used to exclude subtle injury. Musculoskeletal US can be performed in space by minimally trained operators by using remote guidance. This technique can be used to evaluate shoulder integrity in symptomatic crewmembers after strenuous extravehicular activities or to monitor microgravity-associated changes in musculoskeletal anatomy. Just-in-time training, combined with remote experienced physician guidance, may provide a useful approach to complex medical tasks performed by nonexperienced personnel in a variety of remote settings, including current and future space programs. (c) RSNA, 2004.

32 CFR 700.723 - Administration and discipline: Separate and detached command.

Code of Federal Regulations, 2010 CFR

2010-07-01

... detached command. 700.723 Section 700.723 National Defense Department of Defense (Continued) DEPARTMENT OF... Administration and discipline: Separate and detached command. Any flag or general officer in command, any officer... are separate or detached commands. Such officer shall state in writing that it is a separate or...

32 CFR 700.722 - Administration and discipline: Staff unassigned to an administrative command.

Code of Federal Regulations, 2012 CFR

2012-07-01

... to an administrative command. 700.722 Section 700.722 National Defense Department of Defense....722 Administration and discipline: Staff unassigned to an administrative command. (a) When it is not... administration and discipline, the commander may designate an officer of the staff to act as the commanding...

32 CFR 536.8 - Responsibilities and operations of command claims services.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 3 2013-07-01 2013-07-01 false Responsibilities and operations of command... Responsibilities and operations of command claims services. (a) Chiefs of command claims services. Chiefs of command claims services shall: (1) Exercise claims settlement authority as specified in this part...

32 CFR 700.723 - Administration and discipline: Separate and detached command.

Code of Federal Regulations, 2014 CFR

2014-07-01

... detached command. 700.723 Section 700.723 National Defense Department of Defense (Continued) DEPARTMENT OF... Administration and discipline: Separate and detached command. Any flag or general officer in command, any officer... are separate or detached commands. Such officer shall state in writing that it is a separate or...

32 CFR 700.722 - Administration and discipline: Staff unassigned to an administrative command.

Code of Federal Regulations, 2010 CFR

2010-07-01

... to an administrative command. 700.722 Section 700.722 National Defense Department of Defense....722 Administration and discipline: Staff unassigned to an administrative command. (a) When it is not... administration and discipline, the commander may designate an officer of the staff to act as the commanding...

32 CFR 700.722 - Administration and discipline: Staff unassigned to an administrative command.

Code of Federal Regulations, 2011 CFR

2011-07-01

... to an administrative command. 700.722 Section 700.722 National Defense Department of Defense....722 Administration and discipline: Staff unassigned to an administrative command. (a) When it is not... administration and discipline, the commander may designate an officer of the staff to act as the commanding...