Science.gov

Sample records for air launch carrier

  1. The influence of the elastic vibration of the carrier to the aerodynamics of the external store in air-launch-to-orbit process

    NASA Astrophysics Data System (ADS)

    Yang, Lei; Ye, Zheng-Yin; Wu, Jie

    2016-11-01

    The separation between the carrier and store is one of the most important and difficult phases in Air-launch-to-orbit technology. Based on the previous researches, the interference aerodynamic forces of the store caused by the carrier are obvious in the earlier time during the separation. And the interference aerodynamics will be more complex when considering the elastic deformation of the carrier. Focusing on the conditions that in the earlier time during the separation, the steady and unsteady interference aerodynamic forces of the store are calculated at different angle of attacks and relative distances between the carrier and store. During the calculation, the elastic vibrations of the carrier are considered. According to the cause of formations of the interference aerodynamics, the interference aerodynamic forces of the store are divided into several components. The relative magnitude, change rule, sphere of influence and mechanism of interference aerodynamic forces components of the store are analyzed quantitatively. When the relative distance between the carrier and store is small, the interference aerodynamic forces caused by the elastic vibration of the carrier is about half of the total aerodynamic forces of the store. And as the relative distance increases, the value of interference aerodynamic forces decrease. When the relative distance is larger than twice the mean aerodynamic chord of the carrier, the values of interference aerodynamic forces of the store can be ignored. Besides, under the influence of the steady interference aerodynamic forces, the lift characteristics of the store are worse and the static stability margin is poorer.

  2. Athena: Advanced air launched space booster

    NASA Technical Reports Server (NTRS)

    Booker, Corey G.; Ziemer, John; Plonka, John; Henderson, Scott; Copioli, Paul; Reese, Charles; Ullman, Christopher; Frank, Jeremy; Breslauer, Alan; Patonis, Hristos

    1994-01-01

    The infrastructure for routine, reliable, and inexpensive access of space is a goal that has been actively pursued over the past 50 years, but has yet not been realized. Current launch systems utilize ground launching facilities which require the booster vehicle to plow up through the dense lower atmosphere before reaching space. An air launched system on the other hand has the advantage of being launched from a carrier aircraft above this dense portion of the atmosphere and hence can be smaller and lighter compared to its ground based counterpart. The goal of last year's Aerospace Engineering Course 483 (AE 483) was to design a 227,272 kg (500,000 lb.) air launched space booster which would beat the customer's launch cost on existing launch vehicles by at least 50 percent. While the cost analysis conducted by the class showed that this goal could be met, the cost and size of the carrier aircraft make it appear dubious that any private company would be willing to invest in such a project. To avoid this potential pitfall, this year's AE 483 class was to design as large an air launched space booster as possible which can be launched from an existing or modification to an existing aircraft. An initial estimate of the weight of the booster is 136,363 kg (300,000 lb.) to 159,091 kg (350,000 lb.).

  3. The Crossbow Air Launch Trade Space

    NASA Technical Reports Server (NTRS)

    Bonometti, Joseph A.; Sorensen, Kirk F.

    2006-01-01

    Effective air launching of a rocket is approached from a broad systems engineering viewpoint. The elementary reasons for why and how a rocket might be launched from a carrier aircraft are examined. From this, a carefully crafted set of guiding principles is presented. Rules are generated from a fundamental foundation, derived from NASA systems study analyses and from an academic vantage point. The Appendix includes the derivation of a revised Mass Multiplier Equation, useful in understanding the rocket equation as it applies to real vehicles, without the need of complicated weight and sizing programs. The rationale for air launching, being an enormously advantageous Earth-To-Orbit (ETO) methodology, is presented along with the realization that the appropriate air launch solution may lie in a very large class of carrier aircraft; the pod-hauler. Finally, a unique area of the system trade space is defined and branded Crossbow. Crossbow is not a specific hardware design for air launch, but represents a comprehensive vision for commercial, military and space transportation. This document serves as a starting point for future technical papers that evaluate the air launch hypotheses and assertions produced during the past several years of study on the subject.

  4. Design of an airborne launch vehicle for an air launched space booster

    NASA Technical Reports Server (NTRS)

    Chao, Chin; Choi, Rich; Cohen, Scott; Dumont, Brian; Gibin, Mauricius; Jorden, Rob; Poth, Stefan

    1993-01-01

    A conceptual design is presented for a carrier vehicle for an air launched space booster. This airplane is capable of carrying a 500,000 pound satellite launch system to an altitude over 40,000 feet for launch. The airplane features a twin fuselage configuration for improved payload and landing gear integration, a high aspect ratio wing for maneuverability at altitude, and is powered by six General Electric GE-90 engines. The analysis methods used and the systems employed in the airplane are discussed. Launch costs are expected to be competitive with existing launch systems.

  5. GRYPHON: Air launched space booster

    NASA Technical Reports Server (NTRS)

    1993-01-01

    The project chosen for the winter semester Aero 483 class was the design of a next generation Air Launched Space Booster. Based on Orbital Sciences Corporation's Pegasus concept, the goal of Aero 483 was to design a 500,000 pound air launched space booster capable of delivering 17,000 pounds of payload to Low Earth Orbit and 8,000 pounds of payload to Geosynchronous Earth Orbit. The resulting launch vehicle was named the Gryphon. The class of forty senior aerospace engineering students was broken down into eight interdependent groups. Each group was assigned a subsystem or responsibility which then became their field of specialization. Spacecraft Integration was responsible for ensuring compatibility between subsystems. This group kept up to date on subsystem redesigns and informed those parties affected by the changes, monitored the vehicle's overall weight and dimensions, and calculated the mass properties of the booster. This group also performed the cost/profitability analysis of the Gryphon and obtained cost data for competing launch systems. The Mission Analysis Group was assigned the task of determining proper orbits, calculating the vehicle's flight trajectory for those orbits, and determining the aerodynamic characteristics of the vehicle. The Propulsion Group chose the engines that were best suited to the mission. This group also set the staging configurations for those engines and designed the tanks and fuel feed system. The commercial satellite market, dimensions and weights of typical satellites, and method of deploying satellites was determined by the Payloads Group. In addition, Payloads identified possible resupply packages for Space Station Freedom and identified those packages that were compatible with the Gryphon. The guidance, navigation, and control subsystems were designed by the Mission Control Group. This group identified required tracking hardware, communications hardware telemetry systems, and ground sites for the location of the Gryphon

  6. GRYPHON: Air launched space booster

    NASA Astrophysics Data System (ADS)

    1993-06-01

    The project chosen for the winter semester Aero 483 class was the design of a next generation Air Launched Space Booster. Based on Orbital Sciences Corporation's Pegasus concept, the goal of Aero 483 was to design a 500,000 pound air launched space booster capable of delivering 17,000 pounds of payload to Low Earth Orbit and 8,000 pounds of payload to Geosynchronous Earth Orbit. The resulting launch vehicle was named the Gryphon. The class of forty senior aerospace engineering students was broken down into eight interdependent groups. Each group was assigned a subsystem or responsibility which then became their field of specialization. Spacecraft Integration was responsible for ensuring compatibility between subsystems. This group kept up to date on subsystem redesigns and informed those parties affected by the changes, monitored the vehicle's overall weight and dimensions, and calculated the mass properties of the booster. This group also performed the cost/profitability analysis of the Gryphon and obtained cost data for competing launch systems. The Mission Analysis Group was assigned the task of determining proper orbits, calculating the vehicle's flight trajectory for those orbits, and determining the aerodynamic characteristics of the vehicle. The Propulsion Group chose the engines that were best suited to the mission. This group also set the staging configurations for those engines and designed the tanks and fuel feed system. The commercial satellite market, dimensions and weights of typical satellites, and method of deploying satellites was determined by the Payloads Group. In addition, Payloads identified possible resupply packages for Space Station Freedom and identified those packages that were compatible with the Gryphon. The guidance, navigation, and control subsystems were designed by the Mission Control Group. This group identified required tracking hardware, communications hardware telemetry systems, and ground sites for the location of the Gryphon

  7. 14 CFR Section 04 - Air Carrier Groupings

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Air Carrier Groupings Section 04 Section 04... REGULATIONS UNIFORM SYSTEM OF ACCOUNTS AND REPORTS FOR LARGE CERTIFICATED AIR CARRIERS Section 04 Air Carrier Groupings (a) All large certificated air carriers are placed into three basic air carrier groupings...

  8. 14 CFR Section 04 - Air Carrier Groupings

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Air Carrier Groupings Section 04 Section 04... REGULATIONS UNIFORM SYSTEM OF ACCOUNTS AND REPORTS FOR LARGE CERTIFICATED AIR CARRIERS Section 04 Air Carrier Groupings (a) All large certificated air carriers are placed into three basic air carrier groupings...

  9. Launch Vehicle/Carrier Interaction, Improving the Analytical Integration Process

    NASA Technical Reports Server (NTRS)

    Shariett, Charles A.; McClendon, Randy (Technical Monitor)

    2002-01-01

    A goal of the aerospace industry is to reduce the cost of space transportation by a significant within the next decade. The present cost of launching a space transportation system which includes propulsion system, vehicle, carrier, and payload integrated together to form a system, encompasses much more than the design of the propulsion system and vehicle. The total cost includes the recurring cost of the process of integrating carriers, and payloads into the vehicle for each flight. The recurring cost of the integration of carrier/payloads systems is driven by the interaction of the vehicle. If the interaction can be well characterized and made to be very predictable for a range of payloads, or if it can be minimized then the cost of integrating a payload can be reduced significantly from today's levels. The Space Shuttle is very interactive with the payload. The interaction has been well characterized through finite element modeling and is reasonably predictable for a specific payload. Experience has shown, however, that the interaction is very manifest dependent, and small changes in one portion of a payload complement can change the interaction significantly in another portion. That is the affects of one on the other are such that if one or the other is changed slightly the environment at the interfaces can change significantly. To date the Shuttle has made in excess of one hundred flights. For each of these flights several iterations of dynamic analyses have been required in the development of each vehicle/carrier/payload system. The iterative analyses are needed because of the sensitivity of the interaction of the launch vehicle to the attached carrier/payload. The Multi Purpose Logistics Module (MPLM) is a carrier designed for flight in the Space Shuttle carrying a wide variation of cargo, supplies, and experiments to and from Space Station. Its integration process provides a unique area for improvement in the template in use today for transporting items to

  10. Overview of the Pegasus Air-Launched Space Booster

    NASA Astrophysics Data System (ADS)

    Lindberg, Robert E.

    1989-09-01

    The Pegasus Air-Launched Space Booster is an innovative new space launch vehicle now under full-scale development in a privately-funded joint venture by Orbital Sciences Corporation (OSC) and Hercules Aerospace Company. Pegasus is a three-stage, solid-propellant, inertially-guided, all-composite winged vehicle that is launched at an altitude of 40,000 ft from its carrier aircraft. The 41,000 lb vehicle can deliver payloads as massive as 900 lb to low earth orbit. This status report on the Pegasus developemt program first details the advantages of the airborne launch concept, then describes the design and performance of the Pegasus vehicle and conlcludes with a review of the progress of the program from its conception in April 1987 through September 1989. First launch of Pegasus is scheduled for October 31, 1989, under contract to the Defense Advanced Research Projects Agency (DARPA). The second flight under the DARPA contract will be held several months later.

  11. NASA Dryden Towed Glider Air-Launch Concept

    NASA Video Gallery

    NASA Dryden Flight Research Center is developing a novel space access, rocket launching technique called the Towed Glider Air-Launch Concept. The idea is to build a relatively inexpensive, remotely...

  12. 29 CFR 1202.13 - Air carriers.

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ... terms of title II of the Railway Labor Act, which was approved April 10, 1936, all of title I, except section 3, which relates to the National Railroad Adjustment Board, was extended to cover every common carrier by air engaged in interstate or foreign commerce, and every carrier by air transporting mail...

  13. 29 CFR 1202.13 - Air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... terms of title II of the Railway Labor Act, which was approved April 10, 1936, all of title I, except section 3, which relates to the National Railroad Adjustment Board, was extended to cover every common carrier by air engaged in interstate or foreign commerce, and every carrier by air transporting mail...

  14. Pegasus air-launched space booster

    NASA Astrophysics Data System (ADS)

    Lindberg, Robert E.; Mosier, Marty R.

    The launching of small satellites with the mother- aircraft-launched Pegasus booster yields substantial cost improvements over ground launching and enhances operational flexibility, since it allows launches to be conducted into any orbital inclination. The Pegasus launch vehicle is a three-stage solid-rocket-propelled system with delta-winged first stage. The major components of airborne support equipment, located on the mother aircraft, encompass a launch panel operator console, an electronic pallet, and a pylon adapter. Alternatives to the currently employed B-52 launch platform aircraft have been identified for future use. Attention is given to the dynamic, thermal, and acoustic environments experienced by the payload.

  15. Cape Canaveral Air Force Station, Launch Complex 39, Solid Rocket ...

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

    Cape Canaveral Air Force Station, Launch Complex 39, Solid Rocket Booster Disassembly & Refurbishment Complex, Thrust Vector Control Deservicing Facility, Hangar Road, Cape Canaveral, Brevard County, FL

  16. Commercial Air Carrier Vulnerabilities to Information Operations

    DTIC Science & Technology

    2007-11-02

    GMO /ENS/02E-11 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base, Ohio...AFIT/ GMO /ENS/02E-11 COMMERCIAL AIR CARRIER VULNERABILITIES TO INFORMATION OPERATIONS...networks that without them, “there is no water coming out of your tap; there is no electricity lighting your room; there is no food being transported to

  17. 36. Launch Control Center, air vent above entrance. Lyon ...

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

    36. Launch Control Center, air vent above entrance. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  18. Artist's Concept of Magnetic Launch Assisted Air-Breathing Rocket

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This artist's concept depicts a Magnetic Launch Assist vehicle in orbit. Formerly referred to as the Magnetic Levitation (Maglev) system, the Magnetic Launch Assist system is a launch system developed and tested by engineers at the Marshall Space Flight Center (MSFC) that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using electricity and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. The system is similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway. A full-scale, operational track would be about 1.5-miles long, capable of accelerating a vehicle to 600 mph in 9.5 seconds, and the vehicle would then shift to rocket engines for launch into orbit. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  19. Low Earth Orbit Raider (LER) winged air launch vehicle concept

    NASA Technical Reports Server (NTRS)

    Feaux, Karl; Jordan, William; Killough, Graham; Miller, Robert; Plunk, Vonn

    1989-01-01

    The need to launch small payloads into low earth orbit has increased dramatically during the past several years. The Low Earth orbit Raider (LER) is an answer to this need. The LER is an air-launched, winged vehicle designed to carry a 1500 pound payload into a 250 nautical mile orbit. The LER is launched from the back of a 747-100B at 35,000 feet and a Mach number of 0.8. Three staged solid propellant motors offer safe ground and flight handling, reliable operation, and decreased fabrication cost. The wing provides lift for 747 separation and during the first stage burn. Also, aerodynamic controls are provided to simplify first stage maneuvers. The air-launch concept offers many advantages to the consumer compared to conventional methods. Launching at 35,000 feet lowers atmospheric drag and other loads on the vehicle considerably. Since the 747 is a mobile launch pad, flexibility in orbit selection and launch time is unparalleled. Even polar orbits are accessible with a decreased payload. Most importantly, the LER launch service can come to the customer, satellites and experiments need not be transported to ground based launch facilities. The LER is designed to offer increased consumer freedom at a lower cost over existing launch systems. Simplistic design emphasizing reliability at low cost allows for the light payloads of the LER.

  20. Air Launch: Examining Performance Potential of Various Configurations and Growth Options

    NASA Technical Reports Server (NTRS)

    Waters, Eric D.; Creech, Dennis M.; Philips, Alan D.

    2013-01-01

    The Advanced Concepts Office at NASA's George C. Marshall Space Flight Center conducted a high-level analysis of various air launch vehicle configurations, objectively determining maximum launch vehicle payload while considering carrier aircraft capabilities and given dimensional constraints. With the renewed interest in aerial launch of low-earth orbit payloads, referenced by programs such as Stratolaunch and Spaceship2, there exists a need to qualify the boundaries of the trade space, identify performance envelopes, and understand advantages and limiting factors of designing for maximum payload capability. Using the NASA/DARPA Horizontal Launch Study (HLS) Point Design 2 (PD-2) as a pointof- departure configuration, two independent design actions were undertaken. Both designs utilized a Boeing 747-400F as the carrier aircraft, LOX/RP-1 first stage and LOX/LH2 second stage. Each design was sized to meet dimensional and mass constraints while optimizing propellant loads and stage delta V splits. All concepts, when fully loaded, exceeded the allowable Gross Takeoff Weight (GTOW) of the aircraft platform. This excess mass was evaluated as propellant/fuel offload available for a potential in-flight propellant loading scenario. Results indicate many advantages such as payload delivery of approximately 47,000 lbm and significant mission flexibility including variable launch site inclination and launch window. However, in-flight cryogenic fluid transfer and carrier aircraft platform integration are substantial technical hurdles to the realization of such a system configuration.

  1. Air Launch: Examining Performance Potential of Various Configurations and Growth Options

    NASA Technical Reports Server (NTRS)

    Waters, Eric D.; Creech, Dennis M.; Philips, Alan

    2013-01-01

    The Advanced Concepts Office at NASA's George C. Marshall Space Flight Center conducted a high-level analysis of various air launch vehicle configurations, objectively determining maximum launch vehicle payload while considering carrier aircraft capabilities and given dimensional constraints. With the renewed interest in aerial launch of low-earth orbit payloads, referenced by programs such as Stratolaunch and Spaceship2, there existed a need to qualify the boundaries of the trade space, identify performance envelopes, and understand advantages and limiting factors of designing for maximum payload capability. Using the NASA/DARPA Horizontal Launch Study (HLS) Point Design 2 (PD-2) as a point-of-departure configuration, two independent design actions were undertaken. Both configurations utilized a Boeing 747-400F as the carrier aircraft, LOX/RP-1 first stage and LOX/LH2 second stage. Each design was sized to meet dimensional and mass constraints while optimizing propellant loads and stage delta V (?V) splits. All concepts, when fully loaded, exceeded the allowable Gross Takeoff Weight (GTOW) of the aircraft platform. This excess mass was evaluated as propellant/fuel offload available for a potential in-flight refueling scenario. Results indicate many advantages such as large, relative payload delivery of approximately 47,000 lbm and significant mission flexibility, such as variable launch site inclination and launch window; however, in-flight cryogenic fluid transfer and carrier aircraft platform integration are substantial technical hurdles to the realization of such a system configuration.

  2. 41. Launch Control Equipment Room, interior. Thalheimer Whiteman Air ...

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

    41. Launch Control Equipment Room, interior. Thalheimer - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  3. Cape Canaveral Air Force Station, Launch Complex 39, The Solid ...

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

    Cape Canaveral Air Force Station, Launch Complex 39, The Solid Rocket Booster Assembly and Refurbishment Facility Manufacturing Building, Southeast corner of Schwartz Road and Contractors Road, Cape Canaveral, Brevard County, FL

  4. 14 CFR 389.24 - Foreign air carriers.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Foreign air carriers. 389.24 Section 389.24...) ORGANIZATION FEES AND CHARGES FOR SPECIAL SERVICES Filing and Processing License Fees § 389.24 Foreign air carriers. A foreign air carrier, or such carriers, if from the same country, acting jointly, may apply...

  5. Throttleable GOX/ABS launch assist hybrid rocket motor for small scale air launch platform

    NASA Astrophysics Data System (ADS)

    Spurrier, Zachary S.

    Aircraft-based space-launch platforms allow operational flexibility and offer the potential for significant propellant savings for small-to-medium orbital payloads. The NASA Armstrong Flight Research Center's Towed Glider Air-Launch System (TGALS) is a small-scale flight research project investigating the feasibility for a remotely-piloted, towed, glider system to act as a versatile air launch platform for nano-scale satellites. Removing the crew from the launch vehicle means that the system does not have to be human rated, and offers a potential for considerable cost savings. Utah State University is developing a small throttled launch-assist system for the TGALS platform. This "stage zero" design allows the TGALS platform to achieve the required flight path angle for the launch point, a condition that the TGALS cannot achieve without external propulsion. Throttling is required in order to achieve and sustain the proper launch attitude without structurally overloading the airframe. The hybrid rocket system employs gaseous-oxygen and acrylonitrile butadiene styrene (ABS) as propellants. This thesis summarizes the development and testing campaign, and presents results from the clean-sheet design through ground-based static fire testing. Development of the closed-loop throttle control system is presented.

  6. 14 CFR 296.3 - Indirect cargo air carrier.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Indirect cargo air carrier. 296.3 Section... PROCEEDINGS) ECONOMIC REGULATIONS INDIRECT AIR TRANSPORTATION OF PROPERTY General § 296.3 Indirect cargo air carrier. An indirect cargo air carrier is any U.S. citizen who undertakes to engage indirectly in...

  7. 14 CFR 296.3 - Indirect cargo air carrier.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Indirect cargo air carrier. 296.3 Section... PROCEEDINGS) ECONOMIC REGULATIONS INDIRECT AIR TRANSPORTATION OF PROPERTY General § 296.3 Indirect cargo air carrier. An indirect cargo air carrier is any U.S. citizen who undertakes to engage indirectly in...

  8. Shuttle Orbiter-like Cargo Carrier on Crew Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Martinovic, Zoran

    2009-01-01

    The following document summarizes the results of a conceptual design study for which the goal was to investigate the possibility of using a crew launch vehicle to deliver the remaining International Space Station elements should the Space Shuttle orbiter not be available to complete that task. Conceptual designs and structural weight estimates for two designs are presented. A previously developed systematic approach that was based on finite-element analysis and structural sizing was used to estimate growth of structural weight from analytical to "as built" conditions.

  9. 14 CFR 298.52 - Air taxi operations by commuter air carriers.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Air taxi operations by commuter air... (AVIATION PROCEEDINGS) ECONOMIC REGULATIONS EXEMPTIONS FOR AIR TAXI AND COMMUTER AIR CARRIER OPERATIONS Commuter Air Carrier Authorizations § 298.52 Air taxi operations by commuter air carriers. (a) A...

  10. 14 CFR 298.52 - Air taxi operations by commuter air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Air taxi operations by commuter air... (AVIATION PROCEEDINGS) ECONOMIC REGULATIONS EXEMPTIONS FOR AIR TAXI AND COMMUTER AIR CARRIER OPERATIONS Commuter Air Carrier Authorizations § 298.52 Air taxi operations by commuter air carriers. (a) A...

  11. Project MAKS air-launched spaceplane

    NASA Astrophysics Data System (ADS)

    Skorodelov, V. A.

    1992-01-01

    The U.S. Space Shuttle and the U.S.S.R. Buran are large spacecraft that are designed to carry large payloads. Obviously, these powerful, expensive systems are no good for tasks that require taking small to medium sized cargoes to and from orbit. Such tasks need a reusable, orbital airplane that has a smaller cargo capacity and costs less to operate. A design involving a multipurpose aerospace system, called by its developers MAKS, satisfies those requirements entirely. The Spiral-Buran-MAKS represents a coherent, continuous chain of designs involving reusable space transportation systems. It is a two-stage complex in which the modified AN-225 Mriya carrier aircraft is employed as the first reusable stage. The second stage consists of the reusable orbital airplane and an expendable external fuel tank filled with fuel for the sustainer engines of the orbiter.

  12. 14 CFR 252.3 - Smoking ban: air carriers.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Smoking ban: air carriers. 252.3 Section... PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.3 Smoking ban: air carriers. Air carriers shall prohibit smoking on all scheduled passenger flights....

  13. 14 CFR 252.3 - Smoking ban: air carriers.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Smoking ban: air carriers. 252.3 Section... PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.3 Smoking ban: air carriers. Air carriers shall prohibit smoking on all scheduled passenger flights....

  14. 14 CFR 252.5 - Smoking ban: foreign air carriers.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Smoking ban: foreign air carriers. 252.5... PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.5 Smoking ban: foreign air carriers. (a) Foreign air carriers shall prohibit smoking on all scheduled passenger flight segments: (1) Between...

  15. 14 CFR 252.5 - Smoking ban: foreign air carriers.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Smoking ban: foreign air carriers. 252.5... PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.5 Smoking ban: foreign air carriers. (a) Foreign air carriers shall prohibit smoking on all scheduled passenger flight segments: (1) Between...

  16. 14 CFR 252.5 - Smoking ban: foreign air carriers.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Smoking ban: foreign air carriers. 252.5... PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.5 Smoking ban: foreign air carriers. (a) Foreign air carriers shall prohibit smoking on all scheduled passenger flight segments: (1) Between...

  17. 14 CFR 252.5 - Smoking ban: foreign air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Smoking ban: foreign air carriers. 252.5... PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.5 Smoking ban: foreign air carriers. (a) Foreign air carriers shall prohibit smoking on all scheduled passenger flight segments: (1) Between...

  18. 14 CFR 252.5 - Smoking ban: foreign air carriers.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Smoking ban: foreign air carriers. 252.5... PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.5 Smoking ban: foreign air carriers. (a) Foreign air carriers shall prohibit smoking on all scheduled passenger flight segments: (1) Between...

  19. 14 CFR 252.3 - Smoking ban: air carriers.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Smoking ban: air carriers. 252.3 Section... PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.3 Smoking ban: air carriers. Air carriers shall prohibit smoking on all scheduled passenger flights....

  20. 14 CFR 399.83 - Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in orally...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Unfair or deceptive practice of air carrier... Enforcement § 399.83 Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in... confirmed reserved space, to be an unfair or deceptive practice and an unfair method of competition in...

  1. 14 CFR 399.83 - Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in orally...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Unfair or deceptive practice of air carrier... Enforcement § 399.83 Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in... confirmed reserved space, to be an unfair or deceptive practice and an unfair method of competition in...

  2. 14 CFR 399.83 - Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in orally...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Unfair or deceptive practice of air carrier... Enforcement § 399.83 Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in... confirmed reserved space, to be an unfair or deceptive practice and an unfair method of competition in...

  3. 14 CFR 399.83 - Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in orally...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Unfair or deceptive practice of air carrier... Enforcement § 399.83 Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in... confirmed reserved space, to be an unfair or deceptive practice and an unfair method of competition in...

  4. 14 CFR 252.3 - Smoking ban: air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Smoking ban: air carriers. 252.3 Section 252.3 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.3 Smoking ban: air carriers. Air...

  5. 14 CFR 252.3 - Smoking ban: air carriers.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Smoking ban: air carriers. 252.3 Section 252.3 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS) ECONOMIC REGULATIONS SMOKING ABOARD AIRCRAFT § 252.3 Smoking ban: air carriers. Air...

  6. Definition of air quality measurements for monitoring space shuttle launches

    NASA Technical Reports Server (NTRS)

    Thorpe, R. D.

    1978-01-01

    A description of a recommended air quality monitoring network to characterize the impact on ambient air quality in the Kennedy Space Center (KSC) (area) of space shuttle launch operations is given. Analysis of ground cloud processes and prevalent meteorological conditions indicates that transient HCl depositions can be a cause for concern. The system designed to monitor HCl employs an extensive network of inexpensive detectors combined with a central analysis device. An acid rain network is also recommended. A quantitative measure of projected minimal long-term impact involves the limited monitoring of NOx and particulates. All recommended monitoring is confined ti KSC property.

  7. RADEM: An Air Launched, Rocket Demonstrator for Future Advanced Launch Systems

    NASA Astrophysics Data System (ADS)

    Parkinson, R. C.; Skorodelov, V. A.; Serdijk, I. I.; Neiland, V. Ya.

    1995-10-01

    Critical features associated with future reusable launch vehicles include reduction of turn around effort, use of integral liquid hydrogen tanks, advanced structures and thermal protection, and re-usable LOx-hydrogen propulsion with low maintenance overheads. Many doubts associated with such designs could be removed by a sub-orbital demonstrator. An air launched vehicle would fulfil many of the objectives for such demonstration. British Aerospace, NPO Molnija, TsAGI and DB Antonov have made an initial study for ESA for such a demonstrator (RADEM), using earlier studies of operational launch systems with the An-225 /Hotol and MAKS proposals. The paper describes the results of this study, including the selection of two potential vehicle designs, and an approach to sub-system design and vehicle development to minimize the costs. It appears that such a vheicle, capable of flying to Mach 12 or beyond using currently available technology, could have a cost an order of magnitude less than that required for development of an operational vehicle.

  8. 77 FR 67584 - Air Carrier Contract Maintenance Requirements

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-11-13

    ... Stations, Report No. AV-2003-047 (July 8, 2003). In 2005, the IG issued a second report on air carriers...). \\4\\ Air Carrier's Outsourcing Use of Non-Certificated Repair Facilities, Report No. AV-2006-031 (Dec... Outsourcing of Aircraft Maintenance, Report No. AV-2008-090 (Sept. 30, 2008). \\7\\ The report noted...

  9. Vandenberg Air Force Base Upper Level Wind Launch Weather Constraints

    NASA Technical Reports Server (NTRS)

    Shafer, Jaclyn A.; Wheeler, Mark M.

    2012-01-01

    The 30th Operational Support Squadron Weather Flight (30 OSSWF) provides comprehensive weather services to the space program at Vandenberg Air Force Base (VAFB) in California. One of their responsibilities is to monitor upper-level winds to ensure safe launch operations of the Minuteman III ballistic missile. The 30 OSSWF tasked the Applied Meteorology Unit (AMU) to analyze VAFB sounding data with the goal of determining the probability of violating (PoV) their upper-level thresholds for wind speed and shear constraints specific to this launch vehicle, and to develop a tool that will calculate the PoV of each constraint on the day of launch. In order to calculate the probability of exceeding each constraint, the AMU collected and analyzed historical data from VAFB. The historical sounding data were retrieved from the National Oceanic and Atmospheric Administration Earth System Research Laboratory archive for the years 1994-2011 and then stratified into four sub-seasons: January-March, April-June, July-September, and October-December. The maximum wind speed and 1000-ft shear values for each sounding in each subseason were determined. To accurately calculate the PoV, the AMU determined the theoretical distributions that best fit the maximum wind speed and maximum shear datasets. Ultimately it was discovered that the maximum wind speeds follow a Gaussian distribution while the maximum shear values follow a lognormal distribution. These results were applied when calculating the averages and standard deviations needed for the historical and real-time PoV calculations. In addition to the requirements outlined in the original task plan, the AMU also included forecast sounding data from the Rapid Refresh model. This information provides further insight for the launch weather officers (LWOs) when determining if a wind constraint violation will occur over the next few hours on day of launch. The interactive graphical user interface (GUI) for this project was developed in

  10. 14 CFR 399.83 - Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in orally...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Unfair or deceptive practice of air carrier, foreign air carrier, or ticket agent in orally confirming to prospective passenger reserved space on... confirmed reserved space, to be an unfair or deceptive practice and an unfair method of competition in...

  11. Dyess Air Force Base, Atlas F Missle Site S8, Launch ...

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

    Dyess Air Force Base, Atlas F Missle Site S-8, Launch Control Center (LCC), Approximately 3 miles east of Winters, 500 feet southwest of Highway 17700, northwest of Launch Facility, Winters, Runnels County, TX

  12. Air liquefaction and enrichment system propulsion in reusable launch vehicles

    NASA Astrophysics Data System (ADS)

    Bond, W. H.; Yi, A. C.

    1994-07-01

    A concept is shown for a fully reusable, Earth-to-orbit launch vehicle with horizontal takeoff and landing, employing an air-turborocket for low speed and a rocket for high-speed acceleration, both using liquid hydrogen for fuel. The turborocket employs a modified liquid air cycle to supply the oxidizer. The rocket uses 90% pure liquid oxygen as its oxidizer that is collected from the atmosphere, separated, and stored during operation of the turborocket from about Mach 2 to 5 or 6. The takeoff weight and the thrust required at takeoff are markedly reduced by collecting the rocket oxidizer in-flight. This article shows an approach and the corresponding technology needs for using air liquefaction and enrichment system propulsion in a single-stage-to-orbit (SSTO) vehicle. Reducing the trajectory altitude at the end of collection reduces the wing area and increases payload. The use of state-of-the-art materials, such as graphite polyimide, in a direct substitution for aluminum or aluminum-lithium alloy, is critical to meet the structure weight objective for SSTO. Configurations that utilize 'waverider' aerodynamics show great promise to reduce the vehicle weight.

  13. Air liquefaction and enrichment system propulsion in reusable launch vehicles

    SciTech Connect

    Bond, W.H.; Yi, A.C.

    1994-07-01

    A concept is shown for a fully reusable, Earth-to-orbit launch vehicle with horizontal takeoff and landing, employing an air-turborocket for low speed and a rocket for high-speed acceleration, both using liquid hydrogen for fuel. The turborocket employs a modified liquid air cycle to supply the oxidizer. The rocket uses 90% pure liquid oxygen as its oxidizer that is collected from the atmosphere, separated, and stored during operation of the turborocket from about Mach 2 to 5 or 6. The takeoff weight and the thrust required at takeoff are markedly reduced by collecting the rocket oxidizer in-flight. This article shows an approach and the corresponding technology needs for using air liquefaction and enrichment system propulsion in a single-stage-to-orbit (SSTO) vehicle. Reducing the trajectory altitude at the end of collection reduces the wing area and increases payload. The use of state-of-the-art materials, such as graphite polyimide, in a direct substitution for aluminum or aluminum-lithium alloy, is critical to meet the structure weight objective for SSTO. Configurations that utilize `waverider` aerodynamics show great promise to reduce the vehicle weight. 5 refs.

  14. Launch vehicle effluent measurements during the May 12, 1977, Titan 3 launch at Air Force Eastern Test Range

    NASA Technical Reports Server (NTRS)

    Gregory, G. L.; Bendura, R. J.; Woods, D. C.

    1979-01-01

    Airborne effluent measurements and cloud physical behavior for the May 21, 1977, Titan 3 launch from the Air Force Eastern Test Range, Fla. are presented. The monitoring program included airborne effluent measurements in situ in the launch cloud, visible and infrared photography of cloud growth and physical behavior, and limited surface collection of rain samples. Airborne effluent measurements included concentrations of HCl, NO, NOx, and aerosols as a function of time in the exhaust cloud. For the first time in situ particulate mass concentration and aerosol number density were measured as a function of time and size in the size range of 0.05 to 25 micro meters diameter. Measurement results were similar to those of earlier launch monitorings. Maximum HCl and NOx concentrations ranged from 10 ppm and 500 ppb, respectively, several minutes after launch to about 1 ppm and 100 ppb at 45 minutes after launch.

  15. 2016 SmartWay Air Carrier Tool Demonstration

    EPA Pesticide Factsheets

    This EPA presentation provides information on the SmartWay Air Carrier Tool: its background and development, participation in the program, application process, emission metrics, tool demonstration, data collection, and schedule for 2016.

  16. Air Launched Missile Systems, AFSC 466X0. Occupational Survey Report

    DTIC Science & Technology

    1993-07-01

    This is a report of an occupational survey of the Air Launched Missile Systems career ladder conducted by the Occupational Analysis Flight, USAF... Occupational Measurement Squadron. The Technical Training Operations Directorate of Headquarters, Air Education Training Command, Randolph AFB TX

  17. 77 FR 72432 - Application of Boutique Air, Inc. for Commuter Air Carrier Authority

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-12-05

    ... Department of Transportation is directing all interested persons to show cause why it should not issue an order finding Boutique Air, Inc., fit, willing, and able, and awarding it commuter air carrier...

  18. Analysis of flight equipment purchasing practices of representative air carriers

    NASA Technical Reports Server (NTRS)

    1977-01-01

    The process through which representative air carriers decide whether or not to purchase flight equipment was investigated as well as their practices and policies in retiring surplus aircraft. An analysis of the flight equipment investment decision process in ten airlines shows that for the airline industry as a whole, the flight equipment investment decision is in a state of transition from a wholly informal process in earliest years to a much more organized and structured process in the future. Individual air carriers are in different stages with respect to the formality and sophistication associated with the flight equipment investment decision.

  19. Airline Transport Pilot-Airplane (Air Carrier) Written Test Guide.

    ERIC Educational Resources Information Center

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

    Presented is information useful to applicants who are preparing for the Airline Transport Pilot-Airplane (Air Carrier) Written Test. The guide describes the basic aeronautical knowledge and associated requirements for certification, as well as information on source material, instructions for taking the official test, and questions that are…

  20. 14 CFR 389.24 - Foreign air carriers.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Foreign air carriers. 389.24 Section 389.24 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS... Director, Bureau of International Aviation. The request should include applicable official government...

  1. 14 CFR 389.24 - Foreign air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Foreign air carriers. 389.24 Section 389.24 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS... Director, Bureau of International Aviation. The request should include applicable official government...

  2. 14 CFR 389.24 - Foreign air carriers.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Foreign air carriers. 389.24 Section 389.24 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS... Director, Bureau of International Aviation. The request should include applicable official government...

  3. 14 CFR 389.24 - Foreign air carriers.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Foreign air carriers. 389.24 Section 389.24 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS... Director, Bureau of International Aviation. The request should include applicable official government...

  4. X-24B launch - air drop from mothership

    NASA Technical Reports Server (NTRS)

    1974-01-01

    powered mission November 15, 1973. Among the final flights with the X-24B were two precise landings on the main concrete runway at Edwards, California, which showed that accurate unpowered reentry vehicle landings were operationally feasible. These missions were flown by Manke and Air Force Maj. Mike Love and represented the final milestone in a program that helped write the flight plan for the Space Shuttle program of today. After launch from the B-52 'mothership' at an altitude of about 45,000 feet, the XLR-11 rocket engine was ignited and the vehicle accelerated to speeds of more than 1,100 miles per hour and to altitudes of 60,000 to 70,000 feet. After the rocket engine was shut down, the pilots began steep glides towards the Edwards runway. As the pilots entered the final leg of their approach, they increased their rate of descent to build up speed and used this energy to perform a 'flare out' maneuver, which slowed their landing speed to about 200 miles per hour--the same basic approach pattern and landing speed of the Space Shuttles today. The final powered flight with the X-24B aircraft was on September 23, l975. The pilot was Bill Dana, and it was also the last rocket-powered flight flown at Dryden. It was also Dana who flew the last X-15 mission about seven years earlier. Top speed reached with the X-24B was 1,164 miles per hour (Mach 1.76) by Love on October 25, 1974. The highest altitude reached was 74,100 feet, by Manke on May 22, 1975. The X-24B is on public display at the Air Force Museum, Wright-Patterson AFB, Ohio. This roughly 20-second video clip shows the X-24B dropping from the B-52 mothership, after which the rocket engine ignites.

  5. Commuter Air Carrier Loan Guarantee Study.

    DTIC Science & Technology

    1980-01-01

    the heavy twin piston aircraft plus anti-ice, R- NAV , and full dual panels for both pilot and copilot. The equipped Blue Book prices were then compared...11,000 2 (3 ) o Glide Slope 700 800 1,300 2 (3 ) o Market Beacon 150 300 600 2 (3 ) o ADF 200 2,000 4,600 2 o Transponder 500 1,500 5,900 2 o DME 2,800...Flight Director 2,500 27,000 46,000 1 o Weather Radar 5,500 17,000 37,000 1 o R- Nav 1,900 16,000 80,000 1 o Anti-ice 1 o 02 70,000(2) o Air

  6. 33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a... Force, Headquarters 6th Weather Wing (MAC), Andrews Air Force Base, Washington, D.C. 20331. (40...

  7. 33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a... Force, Headquarters 6th Weather Wing (MAC), Andrews Air Force Base, Washington, D.C. 20331. (40...

  8. 33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

    Code of Federal Regulations, 2014 CFR

    2014-07-01

    ..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a... Force, Headquarters 6th Weather Wing (MAC), Andrews Air Force Base, Washington, D.C. 20331. (40...

  9. 33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

    Code of Federal Regulations, 2013 CFR

    2013-07-01

    ..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a... Force, Headquarters 6th Weather Wing (MAC), Andrews Air Force Base, Washington, D.C. 20331. (40...

  10. 33 CFR 334.1290 - In Bering Sea, Shemya Island Area, Alaska; meteorological rocket launching facility, Alaskan Air...

    Code of Federal Regulations, 2011 CFR

    2011-07-01

    ..., Alaska; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. 334.1290 Section...; meteorological rocket launching facility, Alaskan Air Command, U.S. Air Force. (a) The danger zone. An arc of a... Force, Headquarters 6th Weather Wing (MAC), Andrews Air Force Base, Washington, D.C. 20331. (40...

  11. School Indoor Air Quality Assessments Go Mobile / EPA Launches School IAQ Assessment Mobile App

    EPA Pesticide Factsheets

    WASHINGTON -- The U.S. Environmental Protection Agency (EPA) today launched a new mobile app to assist schools and school districts with performing comprehensive indoor air quality (IAQ) facility assessments to protect the health of children and sch

  12. 14 CFR 234.13 - Reports by air carriers on incidents involving animals during air transport.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... carrier that provides scheduled passenger air transportation shall, within 15 days of the end of the month... Consumer Protection Division a report on any incidents involving the loss, injury, or death of an...

  13. 14 CFR 234.13 - Reports by air carriers on incidents involving animals during air transport.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... carrier that provides scheduled passenger air transportation shall, within 15 days of the end of the month... Consumer Protection Division a report on any incidents involving the loss, injury, or death of an...

  14. 14 CFR 234.13 - Reports by air carriers on incidents involving animals during air transport.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... carrier that provides scheduled passenger air transportation shall, within 15 days of the end of the month... Consumer Protection Division a report on any incidents involving the loss, injury, or death of an...

  15. 14 CFR 234.13 - Reports by air carriers on incidents involving animals during air transport.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... carrier that provides scheduled passenger air transportation shall, within 15 days of the end of the month... Consumer Protection Division a report on any incidents involving the loss, injury, or death of an...

  16. 14 CFR 234.13 - Reports by air carriers on incidents involving animals during air transport.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... carrier that provides scheduled passenger air transportation shall, within 15 days of the end of the month... Consumer Protection Division a report on any incidents involving the loss, injury, or death of an...

  17. Design of experiments based variation mode and effect analysis of a conceptual air launched SLV

    NASA Astrophysics Data System (ADS)

    Rafique, Amer Farhan; Zeeshan, Qasim; Kamran, Ali

    2014-12-01

    Conceptual design stage is where the knowledge about the variation in system is still quite vague and herein we intend to analyze and compare various probable design concepts for Air Launched SLV by the use of basic variation mode and effect analysis. In this paper we present a methodology for the Variation Mode and Effect Analysis using Latin Hypercube Sampling based Design of Experiments for the conceptual Air launched Satellite Launch Vehicle. Variations are induced in the Control Variables based on knowledge and experience. The methodology is used to quantify the effect of Noise Factors on the performance of a conceptual Air Launched SLV. The insertion altitude of the Air Launched SLV is the Key Performance Indicator. Preliminary results of the performance and analysis for the simulated experiments are presented here. The performance of the proposed procedure has been tested and, thus, validated by the Air Launched SLV design problem. The Design of Experiment based Variation mode and effect analysis approach is intended for initial conceptual design purposes, thus, providing an immediate insight to the performance of the system in general and quantification of the sensitivity of the key performance indicator in particular, subject to the variations in noise factors prior to the detailed design phase.

  18. Supersonic Air-Breathing Stage For Commercial Launch Rocket

    NASA Technical Reports Server (NTRS)

    Martin, James A.

    1993-01-01

    Concept proposed to expand use of air-breathing, reusable stages to put more payload into orbit at less cost. Stage with supersonic air-breathing engines added to carry expendable stages from subsonic airplane to supersonic velocity. Carry payload to orbit. Expendable stages and payload placed in front of supersonic air-breathing stage. After releasing expendable stages, remotely piloted supersonic air-breathing stage returns to takeoff site and land for reuse. New concept extends use of low-cost reusable hardware and increases payload delivered from B-52.

  19. 78 FR 50138 - Applications for Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-16

    ... PanAir requesting a foreign air carrier permit to operate charter air transportation of property..., whether or not it constitutes part of a continuous operation that includes service to Panama. PanAir...

  20. The ASAC Air Carrier Investment Model (Second Generation)

    NASA Technical Reports Server (NTRS)

    Wingrove, Earl R., III; Johnson, Jesse P.; Sickles, Robin C.; Good, David H.

    1997-01-01

    To meet its objective of assisting the U.S. aviation industry with the technological challenges of the future, NASA must identify research areas that have the greatest potential for improving the operation of the air transportation system. To accomplish this, NASA is building an Aviation System Analysis Capability (ASAC). The ASAC differs from previous NASA modeling efforts in that the economic behavior of buyers and sellers in the air transportation and aviation industries is central to its conception. To link the economics of flight with the technology of flight, ASAC requires a parametrically based mode with extensions that link airline operations and investments in aircraft with aircraft characteristics. This model also must provide a mechanism for incorporating air travel demand and profitability factors into the airlines' investment decisions. Finally, the model must be flexible and capable of being incorporated into a wide-ranging suite of economic and technical models that are envisioned for ASAC. We describe a second-generation Air Carrier Investment Model that meets these requirements. The enhanced model incorporates econometric results from the supply and demand curves faced by U.S.-scheduled passenger air carriers. It uses detailed information about their fleets in 1995 to make predictions about future aircraft purchases. It enables analysts with the ability to project revenue passenger-miles flown, airline industry employment, airline operating profit margins, numbers and types of aircraft in the fleet, and changes in aircraft manufacturing employment under various user-defined scenarios.

  1. 77 FR 21834 - Airborne Radar Altimeter Equipment (For Air Carrier Aircraft)

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-04-11

    ... Federal Aviation Administration Airborne Radar Altimeter Equipment (For Air Carrier Aircraft) AGENCY..., Airborne Radar Altimeter Equipment (For Air Carrier Aircraft). SUMMARY: This is a confirmation notice of the cancellation of TSO-C67, Airborne Radar Altimeter Equipment (For Air Carrier Aircraft). The...

  2. 14 CFR 399.12 - Negotiation by air carriers for landing rights in foreign countries.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Negotiation by air carriers for landing... Relating to Operating Authority § 399.12 Negotiation by air carriers for landing rights in foreign..., landing rights abroad for United States flag air carriers will be acquired through negotiation by the...

  3. 14 CFR 399.12 - Negotiation by air carriers for landing rights in foreign countries.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Negotiation by air carriers for landing... Relating to Operating Authority § 399.12 Negotiation by air carriers for landing rights in foreign..., landing rights abroad for United States flag air carriers will be acquired through negotiation by the...

  4. Air-Breathing Launch Vehicle Technology Being Developed

    NASA Technical Reports Server (NTRS)

    Trefny, Charles J.

    2003-01-01

    Of the technical factors that would contribute to lowering the cost of space access, reusability has high potential. The primary objective of the GTX program is to determine whether or not air-breathing propulsion can enable reusable single-stage-to-orbit (SSTO) operations. The approach is based on maturation of a reference vehicle design with focus on the integration and flight-weight construction of its air-breathing rocket-based combined-cycle (RBCC) propulsion system.

  5. Squid rocket science: How squid launch into air

    NASA Astrophysics Data System (ADS)

    O'Dor, Ron; Stewart, Julia; Gilly, William; Payne, John; Borges, Teresa Cerveira; Thys, Tierney

    2013-10-01

    Squid not only swim, they can also fly like rockets, accelerating through the air by forcefully expelling water out of their mantles. Using available lab and field data from four squid species, Sthenoteuthis pteropus, Dosidicus gigas, Illex illecebrosus and Loligo opalescens, including sixteen remarkable photographs of flying S. pteropus off the coast of Brazil, we compared the cost of transport in both water and air and discussed methods of maximizing power output through funnel and mantle constriction. Additionally we found that fin flaps develop at approximately the same size range as flight behaviors in these squids, consistent with previous hypotheses that flaps could function as ailerons whilst aloft. S. pteropus acceleration in air (265 body lengths [BL]/s2; 24.5m/s2) was found to exceed that in water (79BL/s2) three-fold based on estimated mantle length from still photos. Velocities in air (37BL/s; 3.4m/s) exceed those in water (11BL/s) almost four-fold. Given the obvious advantages of this extreme mode of transport, squid flight may in fact be more common than previously thought and potentially employed to reduce migration cost in addition to predation avoidance. Clearly squid flight, the role of fin flaps and funnel, and the energetic benefits are worthy of extended investigation.

  6. Estimate of air carrier and air taxi crash frequencies from high altitude en route flight operations

    SciTech Connect

    Sanzo, D.; Kimura, C.Y.; Prassinos, P.G.

    1996-06-03

    In estimating the frequency of an aircraft crashing into a facility, it has been found convenient to break the problem down into two broad categories. One category estimates the aircraft crash frequency due to air traffic from nearby airports, the so-called near-airport environment. The other category estimates the aircraft crash frequency onto facilities due to air traffic from airways, jet routes, and other traffic flying outside the near-airport environment The total aircraft crash frequency is the summation of the crash frequencies from each airport near the facility under evaluation and from all airways, jet routes, and other traffic near the facility of interest. This paper will examine the problems associated with the determining the aircraft crash frequencies onto facilities outside the near-airport environment. This paper will further concentrate on the estimating the risk of aircraft crashes to ground facilities due to high altitude air carrier and air taxi traffic. High altitude air carrier and air taxi traffic will be defined as all air carrier and air taxi flights above 18,000 feet Mean Sea Level (MSL).

  7. 78 FR 49729 - Takes of Marine Mammals Incidental to Specified Activities; U.S. Air Force Launches, Aircraft and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-08-15

    ... Specified Activities; U.S. Air Force Launches, Aircraft and Helicopter Operations, and Harbor Activities Related to Launch Vehicles From Vandenberg Air Force Base (VAFB), California AGENCY: National Marine... has received a request from the U.S. Air Force (USAF) for authorization to take marine...

  8. Monitoring Direct Effects of Delta, Atlas, and Titan Launches from Cape Canaveral Air Station

    NASA Technical Reports Server (NTRS)

    Schmalzer, Paul A.; Boyle, Shannon R.; Hall, Patrice; Oddy, Donna M.; Hensley, Melissa A.; Stolen, Eric D.; Duncan, Brean W.

    1998-01-01

    Launches of Delta, Atlas, and Titan rockets from Cape Canaveral Air Station (CCAS) have potential environmental effects that could arise from direct impacts of the launch exhaust (e.g., blast, heat), deposition of exhaust products of the solid rocket motors (hydrogen chloride, aluminum oxide), or other effects such as noise. Here we: 1) review previous reports, environmental assessments, and environmental impact statements for Delta, Atlas, and Titan vehicles and pad areas to clarity the magnitude of potential impacts; 2) summarize observed effects of 15 Delta, 22 Atlas, and 8 Titan launches; and 3) develop a spatial database of the distribution of effects from individual launches and cumulative effects of launches. The review of previous studies indicated that impacts from these launches can occur from the launch exhaust heat, deposition of exhaust products from the solid rocket motors, and noise. The principal effluents from solid rocket motors are hydrogen chloride (HCl), aluminum oxide (Al2O3), water (H2O), hydrogen (H2), carbon monoxide (CO), and carbon dioxide (CO2). The exhaust plume interacts with the launch complex structure and water deluge system to generate a launch cloud. Fall out or rain out of material from this cloud can produce localized effects from acid or particulate deposition. Delta, Atlas, and Titan launch vehicles differ in the number and size of solid rocket boosters and in the amount of deluge water used. All are smaller and use less water than the Space Shuttle. Acid deposition can cause damage to plants and animals exposed to it, acidify surface water and soil, and cause long-term changes to community composition and structure from repeated exposure. The magnitude of these effects depends on the intensity and frequency of acid deposition.

  9. Monitoring biological impacts of space shuttle launches from Vandenberg Air Force Base: Establishment of baseline conditions

    NASA Technical Reports Server (NTRS)

    Schmaizer, Paul A.; Hinkle, C. Ross

    1987-01-01

    Space shuttle launches produce environmental impacts resulting from the formation of an exhaust cloud containing hydrogen chloride aerosols and aluminum oxide particulates. Studies have shown that most impacts occur near-field (within 1.5 km) of the launch site while deposition from launches occurs far-field (as distant as 22 km). In order to establish baseline conditions of vegetation and soils in the areas likely to be impacted by shuttle launches from Vandenberg Air Force Base (VAFB), vegetation and soils in the vicinity of Space Launch Complex-6 (SLC-6) were sampled and a vegetation map prepared. The areas likely to be impacted by launches were determined considering the structure of the launch complex, the prevailing winds, the terrain, and predictions of the Rocket Exhaust Effluent Diffusion Model (REEDM). Fifty vegetation transects were established and sampled in March 1986 and resampled in September 1986. A vegetation map was prepared for six Master Planning maps surrounding SLC-6 using LANDSAT Thematic Mapper imagery as well as color and color infrared aerial photography. Soil samples were collected form the 0 to 7.5 cm layer at all transects in the wet season and at a subsample of the transects in the dry season and analyzed for pH, organic matter, conductivity, cation exchange capacity, exchangeable Ca, Mg, Na, K, and Al, available NH3-N, PO4-P, Cu, Fe, Mn, Zn, and TKN.

  10. Air Data Boom System Development for the Max Launch Abort System (MLAS) Flight Experiment

    NASA Technical Reports Server (NTRS)

    Woods-Vedeler, Jessica A.; Cox, Jeff; Bondurant, Robert; Dupont, Ron; ODonnell, Louise; Vellines, Wesley, IV; Johnston, William M.; Cagle, Christopher M.; Schuster, David M.; Elliott, Kenny B.; Newman, John A.; Tyler, Erik D.; Sterling, William J.

    2010-01-01

    In 2007, the NASA Exploration Systems Mission Directorate (ESMD) chartered the NASA Engineering Safety Center (NESC) to demonstrate an alternate launch abort concept as risk mitigation for the Orion project's baseline "tower" design. On July 8, 2009, a full scale and passively, aerodynamically stabilized MLAS launch abort demonstrator was successfully launched from Wallops Flight Facility following nearly two years of development work on the launch abort concept: from a napkin sketch to a flight demonstration of the full-scale flight test vehicle. The MLAS flight test vehicle was instrumented with a suite of aerodynamic sensors. The purpose was to obtain sufficient data to demonstrate that the vehicle demonstrated the behavior predicted by Computational Fluid Dynamics (CFD) analysis and wind tunnel testing. This paper describes development of the Air Data Boom (ADB) component of the aerodynamic sensor suite.

  11. 77 FR 53779 - Reports by Air Carriers on Incidents Involving Animals During Air Transport

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-09-04

    .... DATES: Comments must be received by September 27, 2012. Comments received after this date will be... requirement for air carriers to report to the Department incidents involving the loss, injury, or death of an... be received 60 days after publication of the NPRM, or by August 28, 2012. Request for Comment...

  12. CloudSat Preps for Launch at Vandenberg Air Force Base, CA

    NASA Technical Reports Server (NTRS)

    2005-01-01

    The CloudSat spacecraft sits encapsulated within its Boeing Delta launch vehicle dual payload attach fitting at Vandenberg Air Force Base, Calif. CloudSat will share its ride to orbit late next month with NASA's CALIPSO spacecraft. The two spacecraft are designed to reveal the secrets of clouds and aerosols.

  13. TODAY: Secretary Kerry and EPA Administrator McCarthy to Launch International Air Quality Program

    EPA Pesticide Factsheets

    WASHINGTON- Today, Secretary of State John Kerry and U.S. Environmental Protection Agency Administrator Gina McCarthy will meet at 2 p.m. EST in the U.S. Department of State's Treaty Room for a signing ceremony to launch a joint air quality p

  14. Environmental Assessment, Balloon Launch and Landing Operations, Air Force Research Laboratory, Space Vehicles Directorate, Kirtland Air Force Base, New Mexico

    DTIC Science & Technology

    2012-06-01

    wetlands are in riparian zones and include oxbow lakes , marshes, cienegas, and bosques. Extreme aridity and seasonally varying precipitation are the...MAJOR RIVERS - LAKE RESERVOIR - TRIBAL LANDS D AFFECTED COUNTY IIBALDUR\\PROJIAFRL_396452\\MAPFILES\\EIS\\FIG2-2_EXCLUSION_ZONE MXD TMCBROOM 2117...ASSESSMENT, BALLOON LAUNCH AND LANDING OPERATIONS, AIR FORCE RESEARCH LABORATORY KIRTLAND AIR FORCE BASE - LAKE RESERVOIR MAJOR RIVERS

  15. 78 FR 32241 - U.S. Air Force Seeks Industry Input for National Security Space Launch Assessment

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-05-29

    ... Department of the Air Force U.S. Air Force Seeks Industry Input for National Security Space Launch Assessment AGENCY: Office of the Deputy Under Secretary of the Air Force for Space, Department of the Air Force, DOD..., Office of the Deputy Under Secretary of the Air Force for Space, seeks industry views and perspectives...

  16. 14 CFR 206.4 - Exemption of air carriers for military transportation.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Exemption of air carriers for military transportation. 206.4 Section 206.4 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION... AUTHORIZATIONS AND EXEMPTIONS § 206.4 Exemption of air carriers for military transportation. Air...

  17. 14 CFR 206.4 - Exemption of air carriers for military transportation.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Exemption of air carriers for military transportation. 206.4 Section 206.4 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION... AUTHORIZATIONS AND EXEMPTIONS § 206.4 Exemption of air carriers for military transportation. Air...

  18. 14 CFR 206.4 - Exemption of air carriers for military transportation.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Exemption of air carriers for military transportation. 206.4 Section 206.4 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION... AUTHORIZATIONS AND EXEMPTIONS § 206.4 Exemption of air carriers for military transportation. Air...

  19. New Air-Launched Small Missile (ALSM) Flight Testbed for Hypersonic Systems

    NASA Technical Reports Server (NTRS)

    Bui, Trong T.; Lux, David P.; Stenger, Michael T.; Munson, Michael J.; Teate, George F.

    2007-01-01

    The Phoenix Air-Launched Small Missile (ALSM) flight testbed was conceived and is proposed to help address the lack of quick-turnaround and cost-effective hypersonic flight research capabilities. The Phoenix ALSM testbed results from utilization of the United States Navy Phoenix AIM-54 (Hughes Aircraft Company, now Raytheon Company, Waltham, Massachusetts) long-range, guided air-to-air missile and the National Aeronautics and Space Administration (NASA) Dryden Flight Research Center (Edwards, California) F-15B (McDonnell Douglas, now the Boeing Company, Chicago, Illinois) testbed airplane. The retirement of the Phoenix AIM-54 missiles from fleet operation has presented an opportunity for converting this flight asset into a new flight testbed. This cost-effective new platform will fill the gap in the test and evaluation of hypersonic systems for flight Mach numbers ranging from 3 to 5. Preliminary studies indicate that the Phoenix missile is a highly capable platform; when launched from a high-performance airplane, the guided Phoenix missile can boost research payloads to low hypersonic Mach numbers, enabling flight research in the supersonic-to-hypersonic transitional flight envelope. Experience gained from developing and operating the Phoenix ALSM testbed will assist the development and operation of future higher-performance ALSM flight testbeds as well as responsive microsatellite-small-payload air-launched space boosters.

  20. New Air-Launched Small Missile (ALSM) Flight Testbed for Hypersonic Systems

    NASA Technical Reports Server (NTRS)

    Bui, Trong T.; Lux, David P.; Stenger, Mike; Munson, Mike; Teate, George

    2006-01-01

    A new testbed for hypersonic flight research is proposed. Known as the Phoenix air-launched small missile (ALSM) flight testbed, it was conceived to help address the lack of quick-turnaround and cost-effective hypersonic flight research capabilities. The Phoenix ALSM testbed results from utilization of two unique and very capable flight assets: the United States Navy Phoenix AIM-54 long-range, guided air-to-air missile and the NASA Dryden F-15B testbed airplane. The U.S. Navy retirement of the Phoenix AIM-54 missiles from fleet operation has presented an excellent opportunity for converting this valuable flight asset into a new flight testbed. This cost-effective new platform will fill an existing gap in the test and evaluation of current and future hypersonic systems for flight Mach numbers ranging from 3 to 5. Preliminary studies indicate that the Phoenix missile is a highly capable platform. When launched from a high-performance airplane, the guided Phoenix missile can boost research payloads to low hypersonic Mach numbers, enabling flight research in the supersonic-to-hypersonic transitional flight envelope. Experience gained from developing and operating the Phoenix ALSM testbed will be valuable for the development and operation of future higher-performance ALSM flight testbeds as well as responsive microsatellite small-payload air-launched space boosters.

  1. 78 FR 77106 - U.S. Air Force Reminder Re: United Launch Alliance (ULA) Consent Order and Recent Change in...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-20

    ... Secretary of the Air Force (Space). ACTION: Publicize Consent Order, Notify Public of New DOD Compliance... notice of solicitation issuance. The Deputy Under Secretary of the Air Force (Space), as the Compliance... Department of the Air Force U.S. Air Force Reminder Re: United Launch Alliance (ULA) Consent Order and...

  2. An Air-Breathing Launch Vehicle Concept for Single-Stage-to-Orbit

    NASA Technical Reports Server (NTRS)

    Trefny, Charles J.

    1999-01-01

    The "Trailblazer" is a 300-lb payload, single-stage-to-orbit launch vehicle concept that uses air-breathing propulsion to reduce the required propellant fraction. The integration of air-breathing propulsion is done considering performance, structural and volumetric efficiency, complexity, and design risk. The resulting configuration is intended to be viable using near-term materials and structures. The aeropropulsion performance goal for the Trailblazer launch vehicle is an equivalent effective specific impulse (I*) of 500 sec. Preliminary analysis shows that this requires flight in the atmosphere to about Mach 10, and that the gross lift-off weight is 130,000 lb. The Trailblazer configuration and proposed propulsion system operating modes are described. Preliminary performance results are presented, and key technical issues are highlighted. An overview of the proposed program plan is given.

  3. 32 CFR 861.6 - DOD review of foreign air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... the foreign air carrier must meet ICAO standards as determined by ICAO, or the FAA under the FAA's... the CAA is not in compliance with ICAO standards. Unless otherwise authorized, use by DOD personnel on official business of foreign air carriers from countries in which the CAA is not in compliance with...

  4. 14 CFR Section 10 - Functional Classification-Operating Expenses of Group I Air Carriers

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Functional Classification-Operating... REPORTS FOR LARGE CERTIFICATED AIR CARRIERS Profit and Loss Classification Section 10 Functional Classification—Operating Expenses of Group I Air Carriers 5100Flying Operations. (a) This function shall...

  5. 14 CFR 119.21 - Commercial operators engaged in intrastate common carriage and direct air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... common carriage and direct air carriers. 119.21 Section 119.21 Aeronautics and Space FEDERAL AVIATION... operators engaged in intrastate common carriage and direct air carriers. (a) Each person who conducts airplane operations as a commercial operator engaged in intrastate common carriage of persons or...

  6. Estimation of Soil Moisture Content Using Air-Launched GPR Techniques in Variable Soil Conditions

    NASA Astrophysics Data System (ADS)

    Hardel, B.; Kelly, B.

    2008-12-01

    Air-launched Ground Penetrating Radar (GPR) techniques have most frequently been used for infrastructure characterization, but these techniques show promise for soil moisture estimation in the near subsurface. Air- launched GPR data can be acquired very quickly, and data processing can be easily automated, so these techniques have potential for efficient estimation of water content in the shallow subsurface over large areas. In this experiment, we investigate the efficacy of air-launched GPR techniques for estimating soil water content under saturated and dry conditions in both sandy and organic-rich soils. Data were also acquired to investigate the depth of penetration of air-launched data in these soils using multiple GPR frequencies. The experiment was performed in a large tank under controlled climatic conditions. Initially, the tank was filled with wet sand to a depth of 24-cm, and GPR data were acquired over the sand using 250-, 500-, and 1000-MHz antennas. Then, a thin plastic tarp was placed on the wet sand, a 3-cm layer of dry sand was placed on the tarp, and data collection was repeated. Additional 3-cm layers of dry sand were placed in the tank, with data acquisition after each layer, until the dry sand layer was 15-cm thick. The tank was then excavated, and a basal layer of dry sand was added. Data were again acquired over the dry sand, and the incremental filling of the tank and data acquisition were repeated using 3-cm layers of wet sand. Finally, the entire process was repeated using a basal layer of wet organic soil overlain by dry organic soil and using a basal layer of dry organic soil overlain by wet organic soil. For all air-launch data, the dielectric constant was determined using the amplitudes of the reflection from the soil surface, and Topp's equation was used to convert the dielectric constant to water content. Data analysis is ongoing, but preliminary results indicate that water content can be estimated with reasonable accuracy in both

  7. Geographic Region, Weather, Pilot Age and Air Carrier Crashes: a Case-Control Study

    PubMed Central

    Li, Guohua; Pressley, Joyce C.; Qiang, Yandong; Grabowski, Jurek G.; Baker, Susan P.; Rebok, George W.

    2009-01-01

    Background Information about risk factors of aviation crashes is crucial for developing effective intervention programs. Previous studies assessing factors associated with crash risk were conducted primarily in general aviation, air taxis and commuter air carriers. Methods A matched case-control design was used to examine the associations of geographic region, basic weather condition, and pilot age with the risk of air carrier (14 CFR Part 121) crash involvement. Cases (n=373) were air carrier crashes involving aircraft made by Boeing, McDonnell Douglas, and Airbus, recorded in the National Transportation Safety Board’s aviation crash database during 1983 through 2002, and controls (n=746) were air carrier incidents involving aircraft of the same three makes selected at random from the Federal Aviation Administration’s aviation incident database. Each case was matched with two controls on the calendar year when the index crash occurred. Conditional logistic regression was used for statistical analysis. Results With adjustment for basic weather condition, pilot age, and total flight time, the risk of air carrier crashes in Alaska was more than three times the risk for other regions [adjusted odds ratio (OR) 3.18, 95% confidence interval (CI) 1.35 – 7.49]. Instrument meteorological conditions were associated with an increased risk for air carrier crashes involving pilot error (adjusted OR 2.26, 95% CI 1.15 – 4.44) and a decreased risk for air carrier crashes without pilot error (adjusted OR 0.57, 95% CI 0.40 – 0.87). Neither pilot age nor total flight time was significantly associated with the risk of air carrier crashes. Conclusions The excess risk of air carrier crashes in Alaska and the effect of adverse weather on pilot-error crashes underscore the importance of environmental hazards in flight safety. PMID:19378910

  8. Impact of combustion products from Space Shuttle launches on ambient air quality

    NASA Technical Reports Server (NTRS)

    Dumbauld, R. K.; Bowers, J. F.; Cramer, H. E.

    1974-01-01

    The present work describes some multilayer diffusion models and a computer program for these models developed to predict the impact of ground clouds formed during Space Shuttle launches on ambient air quality. The diffusion models are based on the Gaussian plume equation for an instantaneous volume source. Cloud growth is estimated on the basis of measurable meteorological parameters: standard deviation of the wind azimuth angle, standard deviation of wind elevation angle, vertical wind-speed shear, vertical wind-direction shear, and depth of the surface mixing layer. Calculations using these models indicate that Space Shuttle launches under a variety of meteorological regimes at Kennedy Space Center and Vandenberg AFB are unlikely to endanger the exposure standards for HCl; similar results have been obtained for CO and Al2O3. However, the possibility that precipitation scavenging of the ground cloud might result in an acidic rain that could damage vegetation has not been investigated.

  9. 14 CFR 221.201 - Statement of filing with foreign governments to be shown in air carrier's tariff filings.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... governments to be shown in air carrier's tariff filings. 221.201 Section 221.201 Aeronautics and Space OFFICE... Electronically Filed Tariffs § 221.201 Statement of filing with foreign governments to be shown in air carrier's tariff filings. (a) Every electronic tariff filed by or on behalf of an air carrier that contains...

  10. 78 FR 25352 - Agency Information Collection; Activity Under OMB Review; Preservation of Air carrier Records

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-30

    ... Research & Innovative Technology Administration Agency Information Collection; Activity Under OMB Review; Preservation of Air carrier Records AGENCY: Research & Innovative Technology Administration (RITA), Bureau of... techniques or other forms of information technology. Issued in Washington, DC, on April 23, 2013....

  11. Hydrogen disposal investigation for the Space Shuttle launch complex at Vandenberg Air Force Base

    NASA Technical Reports Server (NTRS)

    Breit, Terry J.; Elliott, George

    1987-01-01

    The concern of an overpressure condition on the aft end of the Space Shuttle caused by ignition of unburned hydrogen being trapped in the Space Shuttle Main Engine exhaust duct at the Vandenberg AFB launch complex has been investigated for fifteen months. Approximately twenty-five concepts have been reviewed, with four concepts being thoroughly investigated. The four concepts investigated were hydrogen burnoff ignitors (ignitors located throughout the exhaust duct to continuously ignite any unburned hydrogen), jet mixing (utilizing large volumes of high pressure air to ensure complete combustion of the hydrogen), steam inert (utilizing flashing hot water to inert the duct with steam) and open duct concept (design an open duct or above grade J-deflector to avoid trapping hydrogen gas). Extensive studies, analyses and testing were performed at six test sites with technical support from twenty-two major organizations. In December 1986, the Air Force selected the steam inert concept to be utilized at the Vandenberg launch complex and authorized the design effort.

  12. Airport Activity Statistics of Certificated Route Air Carriers

    DTIC Science & Technology

    1988-12-31

    INDIA ........................................ INTERNATIONAL S 392 388 38 120190 5134.50 1048 1.78 INDONESIA...TZ -A iCAI TRANS AIR ...................... DOMESTIC ... S 219 NS 946 AS 1165 UA . UNITED AIR LINES ............................ D ........... S

  13. 76 FR 2744 - Disclosure of Code-Share Service by Air Carriers and Sellers of Air Transportation

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-01-14

    ... Office of the Secretary Disclosure of Code-Share Service by Air Carriers and Sellers of Air... Department is publishing the following notice on the enforcement of its rules relating to disclosure of code... Transportation, Office of the Secretary, Washington, DC Guidance on Disclosure of Code-Share Service Under...

  14. Volatile organic components of air samples collected from Vertical Launch Missile capsules. Summary report

    SciTech Connect

    Tappan, D.V.; Knight, D.R.; Heyder, E.; Weathersby, P.K.

    1988-09-27

    Gas chromatographic/mass spectroscopic analyses are presented for the volatile organic components found in air samples collected from the inboard vents from Vertical Launch System (VLS) missile capsules aboard a 688 class submarine. Similar analyses were also conducted for a sample of the ship's high pressure air used to fill the missile tubes. A wide variety of organics was detected in the air from the missile capsules; and while no unique components have yet been identified, a significant contribution has been shown to be made by pressure-ventilation of the VLS capsules into the submarine atmosphere which is already heavily laden with volatile organic compounds. The most apparent conclusion from these preliminary analyses is that the mixtures of organic components in the air within VLS missile capsules vary greatly from capsule to capsule (and probably from time to time). Many such samples need to be investigated to provide sufficient information to judge the seriousness of the possibility of venting toxic components into the submarine atmosphere during the maintenance or firing of VLS missiles.

  15. Airport Activity Statistics of Certificated Route Air Carriers.

    DTIC Science & Technology

    1981-12-31

    between those centers and principal centers. schedules, including extra sections. medium air trafic hub. A community enplaning from 0.25 to small air...O1618C-800U1820 149684 lima $3 41.35 4017.10 1144.2S 51186 4949.01 AIR ooft6o.- 6 A 39 437.811 74.35 253.41 2314.41 3Mo.ŝ 5 AL $ Lima & 3698 48s .114324

  16. 14 CFR 10 - Functional Classification-Operating Expenses of Group I Air Carriers

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Functional Classification-Operating Expenses of Group I Air Carriers Section 10 Section Section 10 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS) ECONOMIC REGULATIONS UNIFORM SYSTEM OF ACCOUNTS AND REPORTS FOR LARGE CERTIFICATED AIR...

  17. Some aspects of user needs for an air-launched, expendable free-drifting buoy

    NASA Technical Reports Server (NTRS)

    Vukovich, F. M.

    1976-01-01

    Research objectives were determined based on user's needs in which an airlaunched, free-drifting buoy would significantly contribute to the accomplishment of these objectives. The objectives were formulated through discussions with individuals representing federal and state agencies and universities. The most immediate need was in continental shelf oceanography which required data to characterize circulation in a localized mesoscale region. A tentative plan for the North Carolina Outfall Study was presented. Data from air-launched, expendable free-drifting buoys would be used in this study not only to characterize the circulation off the North Carolina coast, but also to provide data by which a three-dimensional hydrodynamic model could be verified.

  18. Design of a Flush Airdata System (FADS) for the Hypersonic Air Launched Option (HALO) Vehicle

    NASA Technical Reports Server (NTRS)

    Whitmore, Stephen A.; Moes, Timothy R.; Deets, Dwain A. (Technical Monitor)

    1994-01-01

    This paper presents a design study for a pressure based Flush airdata system (FADS) on the Hypersonic Air Launched Option (HALO) Vehicle. The analysis will demonstrate the feasibility of using a pressure based airdata system for the HALO and provide measurement uncertainty estimates along a candidate trajectory. The HALO is a conceived as a man-rated vehicle to be air launched from an SR-71 platform and is proposed as a testbed for an airbreathing hydrogen scramjet. A feasibility study has been performed and indicates that the proposed trajectory is possible with minimal modifications to the existing SR71 vehicle. The mission consists of launching the HALO off the top of an SR-71 at Mach 3 and 80,000 ft. A rocket motor is then used to accelerate the vehicle to the test condition. After the scramjet test is completed the vehicle will glide to a lakebed runway landing. This option provides reusability of the vehicle and scramjet engine. The HALO design will also allow for various scramjet engine and flowpath designs to be flight tested. For the HALO flights, measurements of freestream airdata are considered to be a mission critical to perform gain scheduling and trajectory optimization. One approach taken to obtaining airdata involves measurement of certain parameters such as external atmospheric winds, temperature, etc to estimate the airdata quantities. This study takes an alternate approach. Here the feasibility of obtaining airdata using a pressure-based flush airdata system (FADS) methods is assessed. The analysis, although it is performed using the HALO configuration and trajectory, is generally applicable to other hypersonic vehicles. The method to be presented offers the distinct advantage of inferring total pressure, Mach number, and flow incidence angles, without stagnating the freestream flow. This approach allows for airdata measurements to be made using blunt surfaces and significantly diminishes the heating load at the sensor. In the FADS concept a

  19. 14 CFR 298.63 - Reporting of aircraft operating expenses and related statistics by small certificated air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Reporting of aircraft operating expenses and related statistics by small certificated air carriers. 298.63 Section 298.63 Aeronautics and Space... EXEMPTIONS FOR AIR TAXI AND COMMUTER AIR CARRIER OPERATIONS Reporting Requirements § 298.63 Reporting...

  20. 19 CFR 122.53 - Aircraft of foreign registry chartered or leased to U.S. air carriers.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... 19 Customs Duties 1 2011-04-01 2011-04-01 false Aircraft of foreign registry chartered or leased... Permit § 122.53 Aircraft of foreign registry chartered or leased to U.S. air carriers. Aircraft of foreign registry leased or chartered to a U.S. air carrier, while being operated by the U.S. air...

  1. 19 CFR 122.53 - Aircraft of foreign registry chartered or leased to U.S. air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... 19 Customs Duties 1 2010-04-01 2010-04-01 false Aircraft of foreign registry chartered or leased... Permit § 122.53 Aircraft of foreign registry chartered or leased to U.S. air carriers. Aircraft of foreign registry leased or chartered to a U.S. air carrier, while being operated by the U.S. air...

  2. 19 CFR 122.53 - Aircraft of foreign registry chartered or leased to U.S. air carriers.

    Code of Federal Regulations, 2014 CFR

    2014-04-01

    ... 19 Customs Duties 1 2014-04-01 2014-04-01 false Aircraft of foreign registry chartered or leased... Permit § 122.53 Aircraft of foreign registry chartered or leased to U.S. air carriers. Aircraft of foreign registry leased or chartered to a U.S. air carrier, while being operated by the U.S. air...

  3. 19 CFR 122.53 - Aircraft of foreign registry chartered or leased to U.S. air carriers.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... 19 Customs Duties 1 2013-04-01 2013-04-01 false Aircraft of foreign registry chartered or leased... Permit § 122.53 Aircraft of foreign registry chartered or leased to U.S. air carriers. Aircraft of foreign registry leased or chartered to a U.S. air carrier, while being operated by the U.S. air...

  4. 19 CFR 122.53 - Aircraft of foreign registry chartered or leased to U.S. air carriers.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... 19 Customs Duties 1 2012-04-01 2012-04-01 false Aircraft of foreign registry chartered or leased... Permit § 122.53 Aircraft of foreign registry chartered or leased to U.S. air carriers. Aircraft of foreign registry leased or chartered to a U.S. air carrier, while being operated by the U.S. air...

  5. 48 CFR 52.247-44 - F.o.b. Designated Air Carrier's Terminal, Point of Importation.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 48 Federal Acquisition Regulations System 2 2011-10-01 2011-10-01 false F.o.b. Designated Air... CLAUSES Text of Provisions and Clauses 52.247-44 F.o.b. Designated Air Carrier's Terminal, Point of... the delivery term is f.o.b. designated air carrier's terminal, point of importation: F.o.b....

  6. 48 CFR 47.303-15 - F.o.b. designated air carrier's terminal, point of exportation.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 48 Federal Acquisition Regulations System 1 2010-10-01 2010-10-01 false F.o.b. designated air... Contracts 47.303-15 F.o.b. designated air carrier's terminal, point of exportation. (a) Explanation of delivery term. F.o.b. designated air carrier's terminal, point of exportation means free of expense to...

  7. 48 CFR 47.303-16 - F.o.b. designated air carrier's terminal, point of importation.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 48 Federal Acquisition Regulations System 1 2010-10-01 2010-10-01 false F.o.b. designated air... Contracts 47.303-16 F.o.b. designated air carrier's terminal, point of importation. (a) Explanation of delivery term. F.o.b. designated air carrier's terminal, point of importation means free of expense to...

  8. 48 CFR 52.247-44 - F.o.b. Designated Air Carrier's Terminal, Point of Importation.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 48 Federal Acquisition Regulations System 2 2010-10-01 2010-10-01 false F.o.b. Designated Air... CLAUSES Text of Provisions and Clauses 52.247-44 F.o.b. Designated Air Carrier's Terminal, Point of... the delivery term is f.o.b. designated air carrier's terminal, point of importation: F.o.b....

  9. 48 CFR 52.247-43 - F.o.b. Designated Air Carrier's Terminal, Point of Exportation.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 48 Federal Acquisition Regulations System 2 2011-10-01 2011-10-01 false F.o.b. Designated Air... CLAUSES Text of Provisions and Clauses 52.247-43 F.o.b. Designated Air Carrier's Terminal, Point of... the delivery term is f.o.b. designated air carrier's terminal, point of exportation: F.o.b....

  10. 48 CFR 47.303-16 - F.o.b. designated air carrier's terminal, point of importation.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 48 Federal Acquisition Regulations System 1 2011-10-01 2011-10-01 false F.o.b. designated air... Contracts 47.303-16 F.o.b. designated air carrier's terminal, point of importation. (a) Explanation of delivery term. F.o.b. designated air carrier's terminal, point of importation means free of expense to...

  11. 48 CFR 47.303-15 - F.o.b. designated air carrier's terminal, point of exportation.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... 48 Federal Acquisition Regulations System 1 2011-10-01 2011-10-01 false F.o.b. designated air... Contracts 47.303-15 F.o.b. designated air carrier's terminal, point of exportation. (a) Explanation of delivery term. F.o.b. designated air carrier's terminal, point of exportation means free of expense to...

  12. 48 CFR 52.247-43 - F.o.b. Designated Air Carrier's Terminal, Point of Exportation.

    Code of Federal Regulations, 2010 CFR

    2010-10-01

    ... 48 Federal Acquisition Regulations System 2 2010-10-01 2010-10-01 false F.o.b. Designated Air... CLAUSES Text of Provisions and Clauses 52.247-43 F.o.b. Designated Air Carrier's Terminal, Point of... the delivery term is f.o.b. designated air carrier's terminal, point of exportation: F.o.b....

  13. First Commuter Air Carrier Safety Symposium, January 16 - 17, 1980.

    DTIC Science & Technology

    1980-01-01

    year. 96 a n ity; :..’ r " din tli •i 1 Ot’.-, it youi are e:,cirkini or’ an ambitio,:7 ~: ,:a t , >’’’.:, t: :x s . ume1s there can be good servicc...this technological breakthr ough . S )rnp , ; enthusiastic acceptance of these new aircraft by the r , travel ing public is test j’onv 1o the fact...carriers with relatively large markets wnici thi-v could integrate with hubs to form viable economic route system,) s . Tn’e r : -st these substitutions

  14. Performance Validation Approach for the GTX Air-Breathing Launch Vehicle

    NASA Technical Reports Server (NTRS)

    Trefny, Charles J.; Roche, Joseph M.

    2002-01-01

    The primary objective of the GTX effort is to determine whether or not air-breathing propulsion can enable a launch vehicle to achieve orbit in a single stage. Structural weight, vehicle aerodynamics, and propulsion performance must be accurately known over the entire flight trajectory in order to make a credible assessment. Structural, aerodynamic, and propulsion parameters are strongly interdependent, which necessitates a system approach to design, evaluation, and optimization of a single-stage-to-orbit concept. The GTX reference vehicle serves this purpose, by allowing design, development, and validation of components and subsystems in a system context. The reference vehicle configuration (including propulsion) was carefully chosen so as to provide high potential for structural and volumetric efficiency, and to allow the high specific impulse of air-breathing propulsion cycles to be exploited. Minor evolution of the configuration has occurred as analytical and experimental results have become available. With this development process comes increasing validation of the weight and performance levels used in system performance determination. This paper presents an overview of the GTX reference vehicle and the approach to its performance validation. Subscale test rigs and numerical studies used to develop and validate component performance levels and unit structural weights are outlined. The sensitivity of the equivalent, effective specific impulse to key propulsion component efficiencies is presented. The role of flight demonstration in development and validation is discussed.

  15. Prospects for utilization of air liquefaction and enrichment system (ALES) propulsion in fully reusable launch vehicles

    NASA Technical Reports Server (NTRS)

    Bond, W. H.; Yi, A. C.

    1993-01-01

    A concept is shown for a fully reusable, earth to orbit launch vehicle with horizontal takeoff and landing, employing an air-turborocket for low speed and a rocket for high speed acceleration, both using LH2 fuel. The turborocket employs a modified liquid air cycle to supply the oxidizer. The rocket uses 90 percent pure LOX that is collected from the atmosphere, separated, and stored during operation of the turborocket from about Mach 2 to Mach 5 or 6. The takeoff weight and the thrust required at takeoff are markedly reduced by collecting the rocket oxidizer in-flight. The paper shows an approach and the corresponding technology needs for using ALES propulsion in a SSTO vehicle. Reducing the trajectory altitude at the end of collection reduces the wing area and increases payload. The use of state-of-the-art materials, such as graphite polyimide, is critical to meet the structure weight objective for SSTO. Configurations that utilize 'waverider' aerodynamics show great promise to reduce the vehicle weight.

  16. The ASAC Air Carrier Investment Model (Third Generation)

    NASA Technical Reports Server (NTRS)

    Wingrove, Earl R., III; Gaier, Eric M.; Santmire, Tara E.

    1998-01-01

    To meet its objective of assisting the U.S. aviation industry with the technological challenges of the future, NASA must identify research areas that have the greatest potential for improving the operation of the air transportation system. To accomplish this, NASA is building an Aviation System Analysis Capability (ASAC). The ASAC differs from previous NASA modeling efforts in that the economic behavior of buyers and sellers in the air transportation and aviation industries is central to its conception. To link the economics of flight with the technology of flight, ASAC requires a parametrically based model with extensions that link airline operations and investments in aircraft with aircraft characteristics. This model also must provide a mechanism for incorporating air travel demand and profitability factors into the airlines' investment decisions. Finally, the model must be flexible and capable of being incorporated into a wide-ranging suite of economic and technical models flat are envisioned for ASAC.

  17. Aviation System Analysis Capability Air Carrier Investment Model-Cargo

    NASA Technical Reports Server (NTRS)

    Johnson, Jesse; Santmire, Tara

    1999-01-01

    The purpose of the Aviation System Analysis Capability (ASAC) Air Cargo Investment Model-Cargo (ACIMC), is to examine the economic effects of technology investment on the air cargo market, particularly the market for new cargo aircraft. To do so, we have built an econometrically based model designed to operate like the ACIM. Two main drivers account for virtually all of the demand: the growth rate of the Gross Domestic Product (GDP) and changes in the fare yield (which is a proxy of the price charged or fare). These differences arise from a combination of the nature of air cargo demand and the peculiarities of the air cargo market. The net effect of these two factors are that sales of new cargo aircraft are much less sensitive to either increases in GDP or changes in the costs of labor, capital, fuel, materials, and energy associated with the production of new cargo aircraft than the sales of new passenger aircraft. This in conjunction with the relatively small size of the cargo aircraft market means technology improvements to the cargo aircraft will do relatively very little to spur increased sales of new cargo aircraft.

  18. Considerations Relative to the Use of Canes by Blind Travelers in Air Carrier Aircraft Cabins,

    DTIC Science & Technology

    1980-07-01

    U) JUL 80 R F CHANDLER , J 0 GARNER, D L LOWREY UNCLASSIF lED FAAA-012EEEMEh EIEF’Tmom FAA-AM-80-12 CONSIDERATIONS RELATIVE TO THE USE OF CANES BY...BLIND TRAVELERS IN AIR CARRIER AIRCRAFT CABINS 0R. F. Chandler , J. D. Garner, D. L. Lowrey, qJ. G. Blethrow, and J. A. Anderson Civil Aeromedical...TRAVELERS IN AIR CARRIER AIRCRAFT CABINS 6 Perarming Organization Code .. PerformingOrgan ationReport No. 7.Au R. F. Chandler J. D./Garner D. L./Lowrey J

  19. Design Evolution and Performance Characterization of the GTX Air-Breathing Launch Vehicle Inlet

    NASA Technical Reports Server (NTRS)

    DeBonis, J. R.; Steffen, C. J., Jr.; Rice, T.; Trefny, C. J.

    2002-01-01

    The design and analysis of a second version of the inlet for the GTX rocket-based combine-cycle launch vehicle is discussed. The previous design did not achieve its predicted performance levels due to excessive turning of low-momentum comer flows and local over-contraction due to asymmetric end-walls. This design attempts to remove these problems by reducing the spike half-angle to 10- from 12-degrees and by implementing true plane of symmetry end-walls. Axisymmetric Reynolds-Averaged Navier-Stokes simulations using both perfect gas and real gas, finite rate chemistry, assumptions were performed to aid in the design process and to create a comprehensive database of inlet performance. The inlet design, which operates over the entire air-breathing Mach number range from 0 to 12, and the performance database are presented. The performance database, for use in cycle analysis, includes predictions of mass capture, pressure recovery, throat Mach number, drag force, and heat load, for the entire Mach range. Results of the computations are compared with experimental data to validate the performance database.

  20. 77 FR 3323 - Airborne Radar Altimeter Equipment (For Air Carrier Aircraft)

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-01-23

    ... Doc No: 2012-1243] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Airborne Radar...: Notice of intent to cancel Technical Standard Order (TSO)-C67, Airborne Radar Altimeter Equipment (For... Radar Altimeter Equipment (For Air Carrier Aircraft). The effect of the cancelled TSO will result in...

  1. 76 FR 38264 - Applications for Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-06-29

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION Office of the Secretary Applications for Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits Filed Under Subpart B (Formerly Subpart Q) During the Week Ending June 4, 2011 The following Applications for Certificates...

  2. 14 CFR 249.20 - Preservation of records by certificated air carriers.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Preservation of records by certificated air carriers. 249.20 Section 249.20 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION... internal reports on internal controls and other internal audits and procedural studies;...

  3. 76 FR 61245 - Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2011-10-03

    ... obtained on reasonable terms and conditions from any company authorized to conduct an insurance business in... October 3, 2011 Part VI The President Memorandum of September 28, 2011--Provision of Aviation Insurance... Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and International...

  4. 14 CFR 330.23 - To what address must air carriers send their applications?

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false To what address must air carriers send their applications? 330.23 Section 330.23 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF...) to the following address: U.S. Department of Transportation, Aviation Relief Desk (X-50), 1200...

  5. 14 CFR 330.23 - To what address must air carriers send their applications?

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false To what address must air carriers send their applications? 330.23 Section 330.23 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF...) to the following address: U.S. Department of Transportation, Aviation Relief Desk (X-50), 1200...

  6. 14 CFR 330.23 - To what address must air carriers send their applications?

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false To what address must air carriers send their applications? 330.23 Section 330.23 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF...) to the following address: U.S. Department of Transportation, Aviation Relief Desk (X-50), 1200...

  7. 75 FR 61485 - Regulatory Training Session With Air Carriers, EPA Regional Partners and Other Interested Parties...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-10-05

    ... for Implementation of the Aircraft Drinking Water Rule AGENCY: Environmental Protection Agency (EPA... on the regulatory requirements of the Aircraft Drinking Water Rule (ADWR). Under the ADWR, by April 19, 2011, air carriers who meet the definition of ``public water systems'' under the Safe...

  8. 3 CFR - Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 3 The President 1 2011-01-01 2011-01-01 false Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and International Operations Presidential Documents Other Presidential Documents Memorandum of September 29, 2010 Provision of Aviation Insurance Coverage for...

  9. 3 CFR - Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and...

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... 3 The President 1 2013-01-01 2013-01-01 false Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and International Operations Presidential Documents Other Presidential Documents Memorandum of September 27, 2012 Provision of Aviation Insurance Coverage for...

  10. 3 CFR - Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and...

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... 3 The President 1 2014-01-01 2014-01-01 false Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and International Operations Presidential Documents Other Presidential Documents Memorandum of December 27, 2013 Provision of Aviation Insurance Coverage for...

  11. 3 CFR - Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and...

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... 3 The President 1 2012-01-01 2012-01-01 false Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and International Operations Presidential Documents Other Presidential Documents Memorandum of September 28, 2011 Provision of Aviation Insurance Coverage for...

  12. 3 CFR - Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 3 The President 1 2010-01-01 2010-01-01 false Provision of Aviation Insurance Coverage for Commercial Air Carrier Service in Domestic and International Operations Presidential Documents Other Presidential Documents Memorandum of August 21, 2009 Provision of Aviation Insurance Coverage for...

  13. 75 FR 18255 - Passenger Facility Charge Database System for Air Carrier Reporting

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-04-09

    ... Federal Aviation Administration Passenger Facility Charge Database System for Air Carrier Reporting AGENCY... interested parties of the availability of the Passenger Facility Charge (PFC) database system to report PFC... public agency. The FAA has developed a national PFC database system in order to more easily track the...

  14. 14 CFR 204.3 - Applicants for new certificate or commuter air carrier authority.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... applicant for a type of certificate authority it does not currently hold or for commuter air carrier... interest in the applicant are related by blood or marriage, such relationship(s) shall be included in the... description of the applicant's fleet of aircraft, including: (1) The number of each type of aircraft...

  15. 14 CFR 204.3 - Applicants for new certificate or commuter air carrier authority.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... applicant for a type of certificate authority it does not currently hold or for commuter air carrier... interest in the applicant are related by blood or marriage, such relationship(s) shall be included in the... description of the applicant's fleet of aircraft, including: (1) The number of each type of aircraft...

  16. 14 CFR 204.3 - Applicants for new certificate or commuter air carrier authority.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... applicant for a type of certificate authority it does not currently hold or for commuter air carrier... interest in the applicant are related by blood or marriage, such relationship(s) shall be included in the... description of the applicant's fleet of aircraft, including: (1) The number of each type of aircraft...

  17. 14 CFR 204.3 - Applicants for new certificate or commuter air carrier authority.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... applicant for a type of certificate authority it does not currently hold or for commuter air carrier... interest in the applicant are related by blood or marriage, such relationship(s) shall be included in the... description of the applicant's fleet of aircraft, including: (1) The number of each type of aircraft...

  18. 78 FR 9865 - Air Carrier Contract Maintenance Requirements; Extension of Comment Period

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-02-12

    ... Federal Aviation Administration 14 CFR Parts 121 and 135 RIN 2120-AJ33 Air Carrier Contract Maintenance... maintenance regulations for domestic, flag, and supplemental operations, and commuter and on-demand operations... instructions for performing contract maintenance that are acceptable to the FAA and to include them in...

  19. An Analysis of Federal Airport and Air Carrier Employee Access Control, Screening. and Training Regulations

    DTIC Science & Technology

    1998-03-01

    traveling public, air carriers, and persons employed by or conducting business at public airports. 14. SUBJECT TERMS Airport Security , Federal...26 4. Sterile Area 28 5. Exclusive Area 28 E. SECURITY ALERT LEVELS 29 F. AIRPORT SECURITY TOOLS 30 1. Electronic Detection System 31 a... Security Coordinator ASP Airport Security Program BIS Biometrie Identification System CCTV Closed Circuit Television CJIS Criminal Justice Information

  20. The Air Force’s Evolved Expendable Launch Vehicle Competitive Procurement

    DTIC Science & Technology

    2014-03-04

    with ULA, committing the government to buy 35 launch vehicle booster cores over a five-year period, and the associated capability to launch them.2...EELV programmatic forecast dated June 2012. 2 The booster core is the main body of a launch vehicle. In the EELV program, common booster cores are...contributors to this report were Art Gallegos, Assistant Director; Peter Anderson, Claire Buck , Raj Chitikila, Desiree Cunningham, Laura Hook, John

  1. 14 CFR 298.63 - Reporting of aircraft operating expenses and related statistics by small certificated air carriers.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... and related statistics by small certificated air carriers. 298.63 Section 298.63 Aeronautics and Space... aircraft operating expenses and related statistics by small certificated air carriers. (a) Each small... Related Statistics.” This schedule shall be filed quarterly as prescribed in § 298.60. Data reported...

  2. 14 CFR 298.63 - Reporting of aircraft operating expenses and related statistics by small certificated air carriers.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... and related statistics by small certificated air carriers. 298.63 Section 298.63 Aeronautics and Space... aircraft operating expenses and related statistics by small certificated air carriers. (a) Each small... Related Statistics.” This schedule shall be filed quarterly as prescribed in § 298.60. Data reported...

  3. 14 CFR 298.63 - Reporting of aircraft operating expenses and related statistics by small certificated air carriers.

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... and related statistics by small certificated air carriers. 298.63 Section 298.63 Aeronautics and Space... aircraft operating expenses and related statistics by small certificated air carriers. (a) Each small... Related Statistics.” This schedule shall be filed quarterly as prescribed in § 298.60. Data reported...

  4. 14 CFR 298.63 - Reporting of aircraft operating expenses and related statistics by small certificated air carriers.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... and related statistics by small certificated air carriers. 298.63 Section 298.63 Aeronautics and Space... aircraft operating expenses and related statistics by small certificated air carriers. (a) Each small... Related Statistics.” This schedule shall be filed quarterly as prescribed in § 298.60. Data reported...

  5. 14 CFR 204.5 - Certificated and commuter air carriers undergoing or proposing to undergo substantial change in...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... undergoing or proposing to undergo substantial change in operations, ownership, or management. 204.5 Section..., ownership, or management. (a) A certificated or commuter air carrier proposing a substantial change in... operations, management, or ownership, including changes that may affect the air carrier's citizenship,...

  6. 14 CFR 204.5 - Certificated and commuter air carriers undergoing or proposing to undergo substantial change in...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... undergoing or proposing to undergo substantial change in operations, ownership, or management. 204.5 Section..., ownership, or management. (a) A certificated or commuter air carrier proposing a substantial change in... operations, management, or ownership, including changes that may affect the air carrier's citizenship,...

  7. 14 CFR Section 11 - Functional Classification-Operating Expenses of Group II and Group III Air Carriers

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Functional Classification-Operating... ACCOUNTS AND REPORTS FOR LARGE CERTIFICATED AIR CARRIERS Profit and Loss Classification Section 11 Functional Classification—Operating Expenses of Group II and Group III Air Carriers 5100Flying Operations....

  8. Environmental Conditions and Threatened and Endangered Species Populations near the Titan, Atlas, and Delta Launch Complexes, Cape Canaveral Air Station

    NASA Technical Reports Server (NTRS)

    Oddy, Donna M.; Stolen, Eric D.; Schmalzer, Paul A.; Hensley, Melissa A.; Hall, Patrice; Larson, Vickie L.; Turek, Shannon R.

    1999-01-01

    Launches of Delta, Atlas, and Titan rockets from Cape Canaveral Air Station (CCAS) have potential environmental effects. These could occur from direct impacts of launches or indirectly from habitat alterations. This report summarizes a three-year study (1 995-1 998) characterizing the environment, with particular attention to threatened and endangered species, near Delta, Atlas, and Titan launch facilities. Cape Canaveral has been modified by Air Force development and by 50 years of fire suppression. The dominant vegetation type around the Delta and Atlas launch complexes is coastal oak hammock forest. Oak scrub is the predominant upland vegetation type near the Titan launch complexes. Compositionally, these are coastal scrub communities that has been unburned for > 40 years and have developed into closed canopy, low-stature forests. Herbaceous vegetation around active and inactive facilities, coastal strand and dune vegetation near the Atlantic Ocean, and exotic vegetation in disturbed areas are common. Marsh and estuarine vegetation is most common west of the Titan complexes. Launch effects to vegetation include scorch, acid, and particulate deposition. Discernable, cumulative effects are limited to small areas near the launch complexes. Water quality samples were collected at the Titan, Atlas, and Delta launch complexes in September 1995 (wet season) and January 1996 (dry season). Samples were analyzed for heavy metals, chloride, total organic carbon, calcium, iron, magnesium, sodium, total alkalinity, pH, and conductivity. Differences between fresh, brackish, and saline surface waters were evident. The natural buffering capacity of the environment surrounding the CCAS launch complexes is adequate for neutralizing acid deposition in rainfall and launch deposition. Populations of the Florida Scrub-Jay (Aphelocoma coerulescens), a Federally-listed, threatened species, reside near the launch complexes. Thirty-seven to forty-one scrub-jay territories were located at

  9. Environmental Conditions and Threatened and Endangered Species Populations near the Titain, Atlas, and Delta Launch Complexes, Cape Canaveral Air Station

    NASA Technical Reports Server (NTRS)

    Oddy, Donna M.; Stolen, Eric D.; Schmalzer, Paul A.; Hensley, Melissa A.; Hall, Patrice; Larson, Vickie L.; Turek, Shannon R.

    1999-01-01

    Launches of Delta, Atlas, and Titan rockets from Cape Canaveral Air Station (CCAS) have potential environmental effects. These could occur from direct impacts of launches or indirectly from habitat alterations. This report summarizes a three-year study (1995-1998) characterizing the environment, with particular attention to threatened and endangered species, near Delta, Atlas, and Titan launch facilities. Cape Canaveral has been modified by Air Force development and by 50 years of fire suppression. The dominant vegetation type around the Delta and Atlas launch complexes is coastal oak hammock forest. Oak scrub is the predominant upland vegetation type near the Titan launch complexes. Compositionally, these are coastal scrub communities that has been unburned for greater than 40 years and have developed into closed canopy, low-stature forests. Herbaceous vegetation around active and inactive facilities, coastal strand and dune vegetation near the Atlantic Ocean, and exotic vegetation in disturbed areas are common. Marsh and estuarine vegetation is most common west of the Titan complexes. Launch effects to vegetation include scorch, acid, and particulate deposition. Discernable, cumulative effects are limited to small areas near the launch complexes. Water quality samples were collected at the Titan, Atlas, and Delta launch complexes in September 1995 (wet season) and January 1996 (dry season). Samples were analyzed for heavy metals, chloride, total organic carbon, calcium, iron, magnesium, sodium, total alkalinity, pH, and conductivity. Differences between fresh, brackish, and saline surface waters were evident. The natural buffering capacity of the environment surrounding the CCAS launch complexes is adequate for neutralizing acid deposition in rainfall and launch deposition. Populations of the Florida Scrub-Jay (Aphelocoma coerulescens), a Federally- listed, threatened species, reside near the launch complexes. Thirty-seven to forty-one scrub-jay territories were

  10. Environmental Impact Statement: Construction and Operation of Titan IV/Centaur Launch Complex, Vandenberg Air Force Base, California. Volume 3

    DTIC Science & Technology

    1990-08-01

    water resources would be affected by ground water withdrawal for direct project construction and operations needs and for domestic use by project...construction and operations personnel and their families. Increases in withdrawal from S-40 activities would not measurably affect local and regional air...However, the caliche plant fossils on San Miguel Island may be affected by the shock from launch-induced sonic booms, regardless of the chosen alternative

  11. The Aviation System Analysis Capability Air Carrier Cost-Benefit Model

    NASA Technical Reports Server (NTRS)

    Gaier, Eric M.; Edlich, Alexander; Santmire, Tara S.; Wingrove, Earl R.., III

    1999-01-01

    To meet its objective of assisting the U.S. aviation industry with the technological challenges of the future, NASA must identify research areas that have the greatest potential for improving the operation of the air transportation system. Therefore, NASA is developing the ability to evaluate the potential impact of various advanced technologies. By thoroughly understanding the economic impact of advanced aviation technologies and by evaluating how the new technologies will be used in the integrated aviation system, NASA aims to balance its aeronautical research program and help speed the introduction of high-leverage technologies. To meet these objectives, NASA is building the Aviation System Analysis Capability (ASAC). NASA envisions ASAC primarily as a process for understanding and evaluating the impact of advanced aviation technologies on the U.S. economy. ASAC consists of a diverse collection of models and databases used by analysts and other individuals from the public and private sectors brought together to work on issues of common interest to organizations in the aviation community. ASAC also will be a resource available to the aviation community to analyze; inform; and assist scientists, engineers, analysts, and program managers in their daily work. The ASAC differs from previous NASA modeling efforts in that the economic behavior of buyers and sellers in the air transportation and aviation industries is central to its conception. Commercial air carriers, in particular, are an important stakeholder in this community. Therefore, to fully evaluate the implications of advanced aviation technologies, ASAC requires a flexible financial analysis tool that credibly links the technology of flight with the financial performance of commercial air carriers. By linking technical and financial information, NASA ensures that its technology programs will continue to benefit the user community. In addition, the analysis tool must be capable of being incorporated into the

  12. Airport Activity Statistics of Certificated Route Air Carriers, 12 Months Ending December 31, 1984.

    DTIC Science & Technology

    1984-12-31

    influence a Convenience and Necessity issued by the Department of community’s ability to generate air carrier or general aviation Transportation (DOT...the hub . c ft GENERAL NOTES CwrDATA MINNG t - ’rd This publication don not include complete yearly data for the Horzon A r Dec. 164 following list of...in a certificated point, and a point may be served as a single community. through more than one airport.) Interlcopoerl operatios. In general

  13. 77 FR 38747 - Reports by Air Carriers on Incidents Involving Animals During Air Transport

    Federal Register 2010, 2011, 2012, 2013, 2014

    2012-06-29

    ... all cats and dogs transported by the carrier, regardless of whether the cat or dog is transported as a... required to report all incidents involving the loss, injury, or death of cats and dogs that occur while they are traveling in an airline's care, custody, or control, regardless of whether the cat or dog...

  14. LITERATURE SEARCH FOR METHODS FOR HAZARD ANALYSES OF AIR CARRIER OPERATIONS.

    SciTech Connect

    MARTINEZ - GURIDI,G.; SAMANTA,P.

    2002-07-01

    Representatives of the Federal Aviation Administration (FAA) and several air carriers under Title 14 of the Code of Federal Regulations (CFR) Part 121 developed a system-engineering model of the functions of air-carrier operations. Their analyses form the foundation or basic architecture upon which other task areas are based: hazard analyses, performance measures, and risk indicator design. To carry out these other tasks, models may need to be developed using the basic architecture of the Air Carrier Operations System Model (ACOSM). Since ACOSM encompasses various areas of air-carrier operations and can be used to address different task areas with differing but interrelated objectives, the modeling needs are broad. A literature search was conducted to identify and analyze the existing models that may be applicable for pursuing the task areas in ACOSM. The intent of the literature search was not necessarily to identify a specific model that can be directly used, but rather to identify relevant ones that have similarities with the processes and activities defined within ACOSM. Such models may provide useful inputs and insights in structuring ACOSM models. ACOSM simulates processes and activities in air-carrier operation, but, in a general framework, it has similarities with other industries where attention also has been paid to hazard analyses, emphasizing risk management, and in designing risk indicators. To assure that efforts in other industries are adequately considered, the literature search includes publications from other industries, e.g., chemical, nuclear, and process industries. This report discusses the literature search, the relevant methods identified and provides a preliminary assessment of their use in developing the models needed for the ACOSM task areas. A detailed assessment of the models has not been made. Defining those applicable for ACOSM will need further analyses of both the models and tools identified. The report is organized in four chapters

  15. An Autosampler and Field Sample Carrier for Maximizing Throughput Using an Open-Air, Surface Sampling Ion Source for MS

    EPA Science Inventory

    A recently developed, commercially available, open-air, surface sampling ion source for mass spectrometers provides individual analyses in several seconds. To realize its full throughput potential, an autosampler and field sample carrier were designed and built. The autosampler ...

  16. 33. Launch Control Center, close view of launch key inserted ...

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

    33. Launch Control Center, close view of launch key inserted in the launch panel. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  17. Level II Documentation of Launch Complex 31/32, Cape Canaveral Air Force Station, Florida

    DTIC Science & Technology

    2008-12-01

    two stories tall and a specially designed folding erector gantry that raised the missile from horizontal to vertical for mounting on the launch...attached to an 80-ton crane and either placed on the pad launcher, or low- ered into the silo (Figure 31). 139 Once in place, the missile’s...flatbed, crane , and cable system for load- ing the missile into the silo (Figure 34). This new system continued in use for the Min- uteman II and III

  18. 65. DETAIL OF ASSISTANT LAUNCH CONTROLLER AND LAUNCH CONTROLLER PANELS ...

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

    65. DETAIL OF ASSISTANT LAUNCH CONTROLLER AND LAUNCH CONTROLLER PANELS LOCATED NEAR CENTER OF SLC-3E CONTROL ROOM. NOTE 30-CHANNEL COMMUNICATIONS PANELS. PAYLOAD ENVIRONMENTAL CONTROL AND MONITORING PANELS (LEFT) AND LAUNCH OPERATORS PANEL (RIGHT) IN BACKGROUND. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  19. Structural Sizing of a 25,000-lb Payload, Air-Breathing Launch Vehicle For Single-Stage-To-Orbit

    NASA Technical Reports Server (NTRS)

    Roche, Joseph M.; Kosareo, Daniel N.; Palac, Don (Technical Monitor)

    2000-01-01

    In support of NASA's Air-Breathing Launch Vehicle (ABLV) study, a 25,000-lb payload version of the GTX (formerly Trailblazer) reference vehicle concept was developed. The GTX is a vertical lift-off, reusable, single-stage-to-orbit launch vehicle concept that uses hypersonic air-breathing propulsion in a rocket-based combined-cycle (RBCC) propulsion system to reduce the required propellant fraction. To achieve this goal the vehicle and propulsion system must be well integrated both aerodynamically and structurally to reduce weight. This study demonstrates the volumetric and structural efficiency of a vertical takeoff, horizontal landing, hypersonic vehicle with a circular cross section. A departure from the lifting body concepts, this design philosophy is even extended to the engines, which have semicircular nacelles symmetrically mounted on the vehicle. Material candidates with a potential for lightweight and simplicity have been selected from a set of near term technologies (5 to 10 years). To achieve the mission trajectory, preliminary weight estimates show the vehicle's gross lift-off weight is 1.26 x 10(exp 6) lb. The structural configuration of the GTX vehicle and its propulsion system are described. The vehicle design benefits are presented, and key technical issues are highlighted.

  20. Structural Sizing of a 25,000-lb Payload, Air-breathing Launch Vehicle for Single-stage-to-orbit

    NASA Technical Reports Server (NTRS)

    Roche, Joseph M.; Kosareo, Daniel N.

    2001-01-01

    In support of NASA's Air-Breathing Launch Vehicle (ABLV) study, a 25,000-lb payload version of the GTX (formerly Trailblazer) reference vehicle concept was developed. The GTX is a vertical lift-off, reusable, single-stage-to-orbit launch vehicle concept that uses hypersonic air-breathing propulsion in a rocket-based combined-cycle (RBCC) propulsion system to reduce the required propellant fraction. To achieve this goal the vehicle and propulsion system must be well integrated both aerodynamically and structurally to reduce weight. This study demonstrates the volumetric and structural efficiency of a vertical takeoff, horizontal landing, hypersonic vehicle with a circular cross section. A departure from the lifting body concepts, this design philosophy is even extended to the engines, which have semicircular nacelles symmetrically mounted on the vehicle. Material candidates with a potential for lightweight and simplicity have been selected from a set of near term technologies (five to ten years). To achieve the mission trajectory, preliminary weight estimates show the vehicle's gross lift-off weight is 1.26 x 10(exp 6) lb. The structural configuration of the GTX vehicle and its propulsion system are described. The vehicle design benefits are presented, and key technical issues are highlighted.

  1. 14 CFR 272.9 - Selection of a carrier to provide essential air service and payment of compensation.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... provide such essential air service shall be submitted to the President of the United States not less than... President of the Freely Associated State concerned and the Authorities designated by that Government(s) in... THE FREELY ASSOCIATED STATES § 272.9 Selection of a carrier to provide essential air service...

  2. 14 CFR Special Federal Aviation... - Prohibition Against Certain Flights by Syrian Air Carriers to the United States

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... Syrian Air Carriers to the United States Federal Special Federal Aviation Regulation No. 104 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Pt. 91, SFAR No. 104 Special Federal...

  3. 14 CFR Special Federal Aviation... - Prohibition Against Certain Flights by Syrian Air Carriers to the United States

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... Syrian Air Carriers to the United States Federal Special Federal Aviation Regulation No. 104 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Pt. 91, SFAR No. 104 Special Federal...

  4. 14 CFR Special Federal Aviation... - Prohibition Against Certain Flights by Syrian Air Carriers to the United States

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... Syrian Air Carriers to the United States Federal Special Federal Aviation Regulation No. 104 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Pt. 91, SFAR No. 104 Special Federal...

  5. 14 CFR Special Federal Aviation... - Prohibition Against Certain Flights by Syrian Air Carriers to the United States

    Code of Federal Regulations, 2012 CFR

    2012-01-01

    ... Syrian Air Carriers to the United States Federal Special Federal Aviation Regulation No. 104 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Pt. 91, SFAR No. 104 Special Federal...

  6. 14 CFR Special Federal Aviation... - Prohibition Against Certain Flights by Syrian Air Carriers to the United States

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... Syrian Air Carriers to the United States Federal Special Federal Aviation Regulation No. 104 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES GENERAL OPERATING AND FLIGHT RULES Pt. 91, SFAR No. 104 Special Federal...

  7. Downwind hazard calculations for space shuttle launches at Kennedy Space Center and Vandenberg Air Force Base

    NASA Technical Reports Server (NTRS)

    Susko, M.; Hill, C. K.; Kaufman, J. W.

    1974-01-01

    The quantitative estimates are presented of pollutant concentrations associated with the emission of the major combustion products (HCl, CO, and Al2O3) to the lower atmosphere during normal launches of the space shuttle. The NASA/MSFC Multilayer Diffusion Model was used to obtain these calculations. Results are presented for nine sets of typical meteorological conditions at Kennedy Space Center, including fall, spring, and a sea-breeze condition, and six sets at Vandenberg AFB. In none of the selected typical meteorological regimes studied was a 10-min limit of 4 ppm exceeded.

  8. The Carrier's Liability for Damage Caused by Delay in International Air Transport

    NASA Technical Reports Server (NTRS)

    Lee, Kang Bin

    2003-01-01

    Delay in the air transport occurs when passengers, baggage or cargo do not arrive at their destination at the time indicated in the contract of carriage. The causes of delay in the carriage of passengers are booking errors or double booking, delayed departure of aircraft, incorrect information regarding the time of departure, failure to land at the scheduled destination and changes in flight schedule or addition of extra landing stops. Delay in the carriage of baggage or cargo may have different causes: no reservation, lack of space, failure to load the baggage or cargo at the right place, or to deliver the covering documents at the right place. The Montreal Convention of 1999 Article 19 provides that 'The carrier is liable for damage occasioned by delay in the carriage by air of passengers, baggage or cargo. Nevertheless, the carder shall not be liable for damage occasioned by delay if it proves that it and its servants and agents took all measures that could reasonably be required to avoid the damage or that it was impossible for it or them to take such measures'. The Montreal Convention Article 22 provides liability limits of the carrier in case of delay for passengers and their baggage and for cargo. In the carriage of persons, the liability of the carrier for each passenger is limited to 4,150 SDR. In the carriage of baggage, the liability of the carrier is limited to 1,000 SDR for each passenger unless a special declaration as to the value of the baggage has been made. In the carriage of cargo, the liability of the carrier is limited to 17 SDR per kilogram unless a special declaration as to the value of the cargo has been made. The Montreal Convention Article 19 has shortcomings: it is silent on the duration of the liability for carriage,andit does not make any distinction between persons and good. It does not give any indication concerning the circumstances to be taken into account in cases of delay, and about the length of delay. In conclusion, it is

  9. Guidance and control of air-launched armaments: An aeroengineer's perspective

    NASA Astrophysics Data System (ADS)

    Pagniez, P.; Chivot, F.

    1987-12-01

    Aircraft armament engineers conceive and develop products of higher and higher sophistication. However, obtaining a total operational manner which results in the optimal performance of these arms is a consequence of the homogeneity of the aircraft-aircrew-weapons association. The engineer is faced with the task of solving an increasing number of problems whose severity increases with weapon sophistication. The aeroengineer must therefore make increasingly complex decisions regarding the compromise among weapon requirements, aircraft vulnerability, and crew workloads. The various constraints relating to the design and development of air/air missiles with passive, active and semi-active homing are examined along with specific design considerations for air/sea and air/ground missiles.

  10. Catapult launch-associated cardioversion of atrial fibrillation.

    PubMed

    Bohnker, B K; Feeks, E F; McEwen, G

    1993-10-01

    A patient is presented with new-onset atrial fibrillation. While being air-evacuated, he cardioverted during the acceleration associated with aircraft carrier catapult launch. This case suggests a possible myocardial response to the kinetic energy produced by the acceleration force, similar to the electrical energy commonly used for cardioversion. Cardioversion using acceleration forces is probably not a clinically useful modality; however, this case demonstrates the importance of acceleration forces on patients during medical evacuation from aircraft carriers.

  11. Determining the Probability of Violating Upper-Level Wind Constraints for the Launch of Minuteman Ill Ballistic Missiles At Vandenberg Air Force Base

    NASA Technical Reports Server (NTRS)

    Shafer, Jaclyn A.; Brock, Tyler M.

    2013-01-01

    The 30th Operational Support Squadron Weather Flight (30 OSSWF) provides comprehensive weather services to the space program at Vandenberg Air Force Base (VAFB) in California. One of their responsibilities is to monitor upper-level winds to ensure safe launch operations of the Minuteman Ill ballistic missile. The 30 OSSWF requested the Applied Meteorology Unit (AMU) analyze VAFB sounding data to determine the probability of violating (PoV) upper-level thresholds for wind speed and shear constraints specific to this launch vehicle, and to develop a graphical user interface (GUI) that will calculate the PoV of each constraint on the day of launch. The AMU suggested also including forecast sounding data from the Rapid Refresh (RAP) model. This would provide further insight for the launch weather officers (LWOs) when determining if a wind constraint violation will occur over the next few hours, and help to improve the overall upper winds forecast on launch day.

  12. Ascent performance of an air-breathing horizontal-takeoff launch vehicle

    NASA Technical Reports Server (NTRS)

    Powell, Richard W.; Shaughnessy, John D.; Cruz, Christopher I.; Naftel, J. C.

    1991-01-01

    Simulations are conducted to investigate a proposed NASA launch vehicle that is fully reusable, takes off horizontally, and uses airbreathing propulsion in a single stage. The propulsion model is based on a cycle analysis method, and the vehicle is assumed to be a rigid structure with distributed fuel, operating under a range of atmospheric conditions. The program to optimize simulated trajectories (POST) is modified to include a predictor-corrector guidance capability and then used to generate the trajectories. Significant errors are encountered during the unpowered coast phase due to uncertainty in the atmospheric density profile. The amount of ascent propellant needed is shown to be directly related to the thrust-vector angle and the location of the center of gravity of the vehicle because of the importance of aim-drag losses to total ideal velocity.

  13. Air-coupled seismic waves at long range from Apollo launchings.

    NASA Technical Reports Server (NTRS)

    Donn, W. L.; Dalins, I.; Mccarty, V.; Ewing, M.; Kaschak , G.

    1971-01-01

    Microphones and seismographs were co-located in arrays on Skidaway Island, Georgia, for the launchings of Apollo 13 and 14, 374 km to the south. Simultaneous acoustic and seismic waves were recorded for both events at times appropriate to the arrival of the acoustic waves from the source. The acoustic signal is relatively broadband compared to the nearly monochromatic seismic signal; the seismic signal is much more continuous than the more pulse-like acoustic signal; ground loading from the pressure variations of the acoustic waves is shown to be too small to account for the seismic waves; and the measured phase velocities of both acoustic and seismic waves across the local instrument arrays differ by less than 6 per cent and possibly 3 per cent if experimental error is included. It is concluded that the seismic waves are generated by resonant coupling to the acoustic waves along some 10 km of path on Skidaway Island.

  14. Assessment and forecasting of lightning potential and its effect on launch operations at Cape Canaveral Air Force Station and John F. Kennedy Space Center

    NASA Technical Reports Server (NTRS)

    Weems, J.; Wyse, N.; Madura, J.; Secrist, M.; Pinder, C.

    1991-01-01

    Lightning plays a pivotal role in the operation decision process for space and ballistic launches at Cape Canaveral Air Force Station and Kennedy Space Center. Lightning forecasts are the responsibility of Detachment 11, 4th Weather Wing's Cape Canaveral Forecast Facility. These forecasts are important to daily ground processing as well as launch countdown decisions. The methodology and equipment used to forecast lightning are discussed. Impact on a recent mission is summarized.

  15. Military Handbook: Management and Design Guidance Electromagnetic Radiation Hardness for Air Launched Ordnance Systems

    DTIC Science & Technology

    1981-01-15

    pD’kups. 23 15 JIUA 3981 The Air Force has available a family of EVC analysis computer programs to support both order-of-magnitude and detailed... FNP tyoe input transistors. The susceptibility criterion used for these measurements was the magnitude of v I. Figure E-17 shows the minimum power

  16. Let's talk sex on the air: ReachOut launches radio campaign.

    PubMed

    This article reports on the launching of the National Radio and Public Relations Campaign to Promote Modern Methods of Contraception by the ReachOut AIDS Foundation Incorporated in the Philippines. ReachOut has tapped radio veteran Tiya Dely Magpayo as the official campaign spokesperson, thus, putting a mother's touch to a serious promotional drive to reach the far-flung areas of the country. It is noted that the project promotes the wider use of modern methods of contraception as its contribution to the Philippines Population Program goals of controlling the population rate. Since radio is the most patronized media in the country, ReachOut hopes that the radio soap opera format will attract the listeners to use contraceptives. The campaign encourages men and women of reproductive age to seek information and services regarding modern methods of contraception from health service providers in their respective areas. The Department of Health will provide the technical support to ensure that the campaign is keeping with the government's programs.

  17. The use of total simulator training in transitioning air-carrier pilots: A field evaluation

    NASA Technical Reports Server (NTRS)

    Randle, R. J., Jr.; Tanner, T. A.; Hamerman, J. A.; Showalter, T. H.

    1981-01-01

    A field study was conducted in which the performance of air carrier transitioning pilots who had landing training in a landing maneuver approved simulator was compared with the performance of pilots who had landing training in the aircraft. Forty-eight trainees transitioning to the B-727 aircraft and eighty-seven trainees transitioning to the DC-10 were included in the study. The study results in terms of both objectively measured performance indicants and observer and check-pilot ratings did not demonstrate a clear distinction between the two training groups. The results suggest that, for these highly skilled transitioning pilots, a separate training module in the aircraft may be of dubious value.

  18. Pilot Error in Air Carrier Mishaps: Longitudinal Trends Among 558 Reports, 1983–2002

    PubMed Central

    Baker, Susan P.; Qiang, Yandong; Rebok, George W.; Li, Guohua

    2009-01-01

    Background Many interventions have been implemented in recent decades to reduce pilot error in flight operations. This study aims to identify longitudinal trends in the prevalence and patterns of pilot error and other factors in U.S. air carrier mishaps. Method National Transportation Safety Board investigation reports were examined for 558 air carrier mishaps during 1983–2002. Pilot errors and circumstances of mishaps were described and categorized. Rates were calculated per 10 million flights. Results The overall mishap rate remained fairly stable, but the proportion of mishaps involving pilot error decreased from 42% in 1983–87 to 25% in 1998–2002, a 40% reduction. The rate of mishaps related to poor decisions declined from 6.2 to 1.8 per 10 million flights, a 71% reduction; much of this decrease was due to a 76% reduction in poor decisions related to weather. Mishandling wind or runway conditions declined by 78%. The rate of mishaps involving poor crew interaction declined by 68%. Mishaps during takeoff declined by 70%, from 5.3 to 1.6 per 10 million flights. The latter reduction was offset by an increase in mishaps while the aircraft was standing, from 2.5 to 6.0 per 10 million flights, and during pushback, which increased from 0 to 3.1 per 10 million flights. Conclusions Reductions in pilot errors involving decision making and crew coordination are important trends that may reflect improvements in training and technological advances that facilitate good decisions. Mishaps while aircraft are standing and during push-back have increased and deserve special attention. PMID:18225771

  19. Application of 50 MHz doppler radar wind profiler to launch operations at Kennedy Space Center and Cape Canaveral Air Station

    NASA Technical Reports Server (NTRS)

    Schumann, Robin S.; Taylor, Gregory E.; Smith, Steve A.; Wilfong, Timothy L.

    1994-01-01

    This paper presents a case study where a significant wind shift, not detected by jimspheres, was detected by the 50 MHz DRWP (Doppler Radar Wind Profiler) and evaluated to be acceptable prior to the launch of a Shuttle. This case study illustrates the importance of frequent upper air wind measurements for detecting significant rapidly changing features as well as for providing confidence that the features really exist and are not due to instrumentation error. Had the release of the jimsphere been timed such that it would have detected the entire wind shift, there would not have been sufficient time to release another jimsphere to confirm the existence of the feature prior to the scheduled launch. We found that using a temporal median filter on the one minute spectral estimates coupled with a constraining window about a first guess velocity effectively removes nearly all spurious signals from the velocity profile generated by NASA's 50 MHz DRWP while boosting the temporal resolution to as high as one profile every 3 minutes. The higher temporal resolution of the 50 MHz DRWP using the signal processing algorithm described in this paper ensures the detection of rapidly changing features as well as provides the confidence that the features are genuine. Further benefit is gained when the profiles generated by the DRWP are examined in relation to the profiles measured by jimspheres and/or rawinsondes. The redundancy offered by using two independent measurements can dispel or confirm any suspicion regarding instrumentation error or malfunction and wind profiles can be examined in light of their respective instruments' strengths and weaknesses.

  20. Effluent monitoring of the December 10, 1974, Titan 3-E launch at Air Force Eastern Test Range, Florida

    NASA Technical Reports Server (NTRS)

    Wornom, D. E.; Woods, D. C.

    1978-01-01

    Surface and airborne field measurements of the cloud behavior and effluent dispersion from a solid rocket motor launch vehicle are presented. The measurements were obtained as part of a continuing launch vehicle effluent monitoring program to obtain experimental field measurements in order to evaluate a model used to predict launch vehicle environmental impact. Results show that the model tends to overpredict effluent levels.

  1. 41 CFR 301-10.135 - When must I travel using U.S. flag air carrier service?

    Code of Federal Regulations, 2012 CFR

    2012-07-01

    ... use of the U.S. flag air carrier would at least double your en route travel time; or (g) When the... 41 Public Contracts and Property Management 4 2012-07-01 2012-07-01 false When must I travel using... Management Federal Travel Regulation System TEMPORARY DUTY (TDY) TRAVEL ALLOWANCES ALLOWABLE TRAVEL...

  2. 75 FR 30776 - Exemption of Foreign Air Carriers From Excise Taxes; Review of Finding of Reciprocity (Ecuador...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-06-02

    ... From the Federal Register Online via the Government Publishing Office ] DEPARTMENT OF COMMERCE International Trade Administration Exemption of Foreign Air Carriers From Excise Taxes; Review of Finding of Reciprocity (Ecuador), 26 U.S.C. 4221 AGENCY: International Trade Administration, U.S. Department of...

  3. DEMONSTRATION OF IN SITU DEHALOGENATION OF DNAPL THROUGH INJECTION OF EMULSIFIED ZERO-VALIENT IRON AT LAUNCH COMPLEX 34 IN CAPE CANAVERAL AIR FORCE STATION, FLORIDA

    EPA Science Inventory

    The purpose of this project was to evaluate the technical and cost performance of emulsified zero-valent iron (EZVI) technology when applied to DNAPL contaminants in the saturated zone. This demonstration was conducted at Launch Complex 34, Cape Canaveral Air Force Station, FL, w...

  4. U.S. Department of State and U.S. Environmental Protection Agency Launch Innovative International Air Quality Program: FACT SHEET

    EPA Pesticide Factsheets

    WASHINGTON - Secretary of State John Kerry and EPA Administrator Gina McCarthy signed a statement of intent today to launch a new air quality partnership between the U.S. Department of State and the U.S. Environmental Protection Agency (EPA). The ef

  5. Evaluating network analysis and agent based modeling for investigating the stability of commercial air carrier schedules

    NASA Astrophysics Data System (ADS)

    Conway, Sheila Ruth

    For a number of years, the United States Federal Government has been formulating the Next Generation Air Transportation System plans for National Airspace System improvement. These improvements attempt to address air transportation holistically, but often address individual improvements in one arena such as ground or in-flight equipment. In fact, air transportation system designers have had only limited success using traditional Operations Research and parametric modeling approaches in their analyses of innovative operations. They need a systemic methodology for modeling of safety-critical infrastructure that is comprehensive, objective, and sufficiently concrete, yet simple enough to be deployed with reasonable investment. The methodology must also be amenable to quantitative analysis so issues of system safety and stability can be rigorously addressed. The literature suggests that both agent-based models and network analysis techniques may be useful for complex system development and analysis. The purpose of this research is to evaluate these two techniques as applied to analysis of commercial air carrier schedule (route) stability in daily operations, an important component of air transportation. Airline-like routing strategies are used to educe essential elements of applying the method. Two main models are developed, one investigating the network properties of the route structure, the other an Agent-based approach. The two methods are used to predict system properties at a macro-level. These findings are compared to observed route network performance measured by adherence to a schedule to provide validation of the results. Those interested in complex system modeling are provided some indication as to when either or both of the techniques would be applicable. For aviation policy makers, the results point to a toolset capable of providing insight into the system behavior during the formative phases of development and transformation with relatively low investment

  6. Comparison of air-launched and ground-coupled configurations of SFCW GPR in time, frequency and wavelet domain

    NASA Astrophysics Data System (ADS)

    Van De Vijver, Ellen; De Pue, Jan; Cornelis, Wim; Van Meirvenne, Marc

    2015-04-01

    A stepped frequency continuous wave (SFCW) ground penetrating radar (GPR) system produces waveforms consisting of a sequence of sine waves with linearly increasing frequency. By adopting a wide frequency bandwidth, SFCW GPR systems offer an optimal resolution at each achievable measurement depth. Furthermore, these systems anticipate an improved penetration depth and signal-to-noise ratio (SNR) as compared to time-domain impulse GPRs, because energy is focused in one single frequency at a time and the phase and amplitude of the reflected signal is recorded for each discrete frequency step. However, the search for the optimal practical implementation of SFCW GPR technology to fulfil these theoretical advantages is still ongoing. In this study we compare the performance of a SFCW GPR system for air-launched and ground-coupled antenna configurations. The first is represented by a 3d-Radar Geoscope GS3F system operated with a V1213 antenna array. This array contains 7 transmitting and 7 receiving antennae resulting in 13 measurement channels at a spacing of 0.075 m and providing a total scan width of 0.975 m. The ground-coupled configuration is represented by 3d-Radar's latest-generation SFCW system, GeoScope Mk IV, operated with a DXG1212 antenna array. With 6 transmitting and 5 receiving antennae this array provides 12 measurement channels and an effective scan width of 0.9 m. Both systems were tested on several sites representative of various application environments, including a test site with different road specimens (Belgian Road Research Centre) and two test areas in different agricultural fields in Flanders, Belgium. For each test, data acquisition was performed using the full available frequency bandwidth of the systems (50 to 3000 MHz). Other acquisition parameters such as the frequency step and dwell time were varied in different tests. Analyzing the data of the different tests in time, frequency and wavelet domain allows to evaluate different performance

  7. Computer graphic of Lockheed Martin X-33 Reusable Launch Vehicle (RLV) mounted on NASA 747 ferry air

    NASA Technical Reports Server (NTRS)

    1997-01-01

    This is an artist's conception of the NASA/Lockheed Martin X-33 Advanced Technology Demonstrator being carried on the back of the 747 Shuttle Carrier Aircraft. This was a concept for moving the X-33 from its landing site back to NASA's Dryden Flight Research Center, Edwards, California. The X-33 was a technology demonstrator vehicle for the Reusable Launch Vehicle (RLV). The RLV technology program was a cooperative agreement between NASA and industry. The goal of the RLV technology program was to enable significant reductions in the cost of access to space, and to promote the creation and delivery of new space services and other activities that will improve U.S. economic competitiveness. NASA Headquarter's Office of Space Access and Technology oversaw the RLV program, which was being managed by the RLV Office at NASA's Marshall Space Flight Center, located in Huntsville, Alabama. Responsibilities of other NASA Centers included: Johnson Space Center, Houston, Texas, guidance navigation and control technology, manned space systems, and health technology; Ames Research Center, Mountain View, CA., thermal protection system testing; Langley Research Center, Langley, Virginia, wind tunnel testing and aerodynamic analysis; and Kennedy Space Center, Florida, RLV operations and health management. Lockheed Martin's industry partners in the X-33 program are: Astronautics, Inc., Denver, Colorado, and Huntsville, Alabama; Engineering & Science Services, Houston, Texas; Manned Space Systems, New Orleans, LA; Sanders, Nashua, NH; and Space Operations, Titusville, Florida. Other industry partners are: Rocketdyne, Canoga Park, California; Allied Signal Aerospace, Teterboro, NJ; Rohr, Inc., Chula Vista, California; and Sverdrup Inc., St. Louis, Missouri.

  8. 32. Launch Control Center, commander's console. Note launch key at ...

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

    32. Launch Control Center, commander's console. Note launch key at right. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  9. 78 FR 14619 - Applications for Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-06

    .... (``United''), Continental Airlines, Inc. (``Continental''), Continental Micronesia, Inc. (``Continental Micronesia'') and Air Micronesia, Inc. ] (``Air Micronesia'') (collectively, the ``Joint...

  10. Environmental Impact Analysis Process, Final Environmental Assessment for U.S. Air Force Quick Reaction Launch Vehicle Program

    DTIC Science & Technology

    2007-11-02

    ait-2 to detect bioindicators of change attributable to the launches. Results from the ait-1 launch showed that total taxa richness measures and... bioindicator of change. 3.4.6 SPECIAL STATUS SPECIES A species is considered "special status" if it is federally- or state-listed or is a candidate

  11. "Aqua-space", a new headspace method for isolation of natural floral aromas using humidified air as a carrier gas.

    PubMed

    Ishikawa, Masashi; Honda, Tsutomu; Fujita, Akira; Kurobayashi, Yoshiko; Kitahara, Takeshi

    2004-02-01

    A new method called "Aqua-space" was developed for the isolation of the natural fragrances of plants. Living flowers were enclosed in a space under simulated natural conditions, and humidified air was pumped into the space as a fragrance carrier. In a comparison among three isolation methods, i.e., Aqua-space, headspace, and solvent extraction, the Aqua-space method proved to be the most effective in retaining natural fragrances with abundant oxygenated components key to floral fragrances.

  12. 25. Corridor between the Launch Control Center and the Launch ...

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

    25. Corridor between the Launch Control Center and the Launch Control Equipment Room, view from Launch Control Center. Thalheimer - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  13. Carving a Niche for the No-Frills Carrier, Air Arabia, in Oil-Rich Skies

    NASA Technical Reports Server (NTRS)

    McKechnie, Donelda S.; Grant, Jim; Fahmi, Mona

    2007-01-01

    The concept of introducing a no-frills airline to the wealthy Arab region presented its risks. This independent study sought to position the new airline in the marketplace. After three focus groups and 400 self-administered surveys, safety (#1) and price (#2) are low-fare carrier considerations whereas safety (#1), punctuality (#2) and price (#3) apply for full-fare airlines. Recommended ways for the no-frills carrier to reach the market include newspaper ads, travel agent sales, online bookings, and call centers. Additionally, respondents appeared to evaluate this low-fare carrier as if it is a full-service airline.

  14. 78 FR 56983 - Agency Information Collection; Activity Under OMB Review: Foreign Air Carrier Application for...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-09-16

    ... fourth-freedom flights conducted in the last twelve-month period, and certification of reciprocity from... that their homeland government will afford reciprocity to U.S. carriers seeking authority for...

  15. 14 CFR 204.4 - Carriers proposing to provide essential air service.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... instead identify the data and provide a citation for the date and place of filing. All carriers may... costs and revenues are allocated. (4) A traffic forecast including a load factor analysis on...

  16. 73. VIEW OF LAUNCH OPERATOR AND LAUNCH ANAYLST PANELS LOCATED ...

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

    73. VIEW OF LAUNCH OPERATOR AND LAUNCH ANAYLST PANELS LOCATED NEAR CENTER OF SOUTH WALL OF SLC-3E CONTROL ROOM. FROM LEFT TO RIGHT ON WALL IN BACKGROUND: COMMUNICATIONS HEADSET AND FOOT PEDAL IN FORGROUND. ACCIDENT REPORTING EMERGENCY NOTIFICATION SYSTEM TELEPHONE, ATLAS H FUEL COUNTER, AND DIGITAL COUNTDOWN CLOCK. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  17. Determining the Probability of Violating Upper-Level Wind Constraints for the Launch of Minuteman III Ballistic Missiles at Vandenberg Air Force Base

    NASA Technical Reports Server (NTRS)

    Shafer, Jaclyn A.; Brock, Tyler M.

    2012-01-01

    The 30th Operational Support Squadron Weather Flight (30 OSSWF) provides comprehensive weather services to the space program at Vandenberg Air Force Base (VAFB) in California. One of their responsibilities is to monitor upper-level winds to ensure safe launch operations of the Minuteman Ill ballistic missile. The 30 OSSWF tasked the Applied Meteorology Unit (AMU) to analyze VAFB sounding data with the goal of determining the probability of violating (PoV) their upper-level thresholds for wind speed and shear constraints specific to this launch vehicle, and to develop a tool that will calculate the PoV of each constraint on the day of launch. In order to calculate the probability of exceeding each constraint, the AMU collected and analyzed historical data from VAFB. The historical sounding data were retrieved from the National Oceanic and Atmospheric Administration Earth System Research Laboratory archive for the years 1994-2011 and then stratified into four sub-seasons: January-March, April-June, July-September, and October-December. The AMU determined the theoretical distributions that best fit the maximum wind speed and maximum wind shear datasets and applied this information when calculating the averages and standard deviations needed for the historical and real-time PoV calculations. In addition, the AMU included forecast sounding data from the Rapid Refresh model. This information provides further insight for the launch weather officers (LWOs) when determining if a wind constraint violation will occur over the next few hours on the day of launch. The AMU developed an interactive graphical user interface (GUI) in Microsoft Excel using Visual Basic for Applications. The GUI displays the critical sounding data easily and quickly for LWOs on day of launch. This tool will replace the existing one used by the 30 OSSWF, assist the LWOs in determining the probability of exceeding specific wind threshold values, and help to improve the overall upper winds forecast for

  18. Ground cloud effluent measurements during the May 30, 1974, Titan 3 launch at the Air Force eastern test range

    NASA Technical Reports Server (NTRS)

    Bendura, R. J.; Crumbly, K. H.

    1977-01-01

    Surface-level exhaust effluent measurements of HCl, CO, and particulates, ground-cloud behavior, and some comparisons with model predictions for the launch of a Titan 3 rocket are presented along with a limited amount of airborne sampling measurements of other cloud species (O3, NO, NOX). Values above background levels for these effluents were obtained at 20 of the 30 instrument sites; these values were lower than model predictions and did not exceed public health standards. Cloud rise rate, stabilization altitude, and volume are compared with results from previous launches.

  19. 78 FR 73794 - Taking and Importing Marine Mammals; Taking Marine Mammals Incidental to U.S. Air Force Launches...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-09

    ... the vehicle types and the sound exposure levels (SELs) produced by each missile or rocket are... digital audio tape (DAT) recorder during the launch. Since acoustic data was only gathered with the sound... noise. The A-weighted 1-hour average sound levels at VAFB in the Oil Well Canyon area typically...

  20. 78 FR 39435 - Applications for Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-07-01

    ... from any point or points behind any Member State of the European Union via any point or points in any... authorized by any additional route rights made available to European Union carriers in the future. Barbara J... United States and any point or points in any member of the European Common Aviation Area; (c)...

  1. 78 FR 20372 - Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits; Notice of...

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-04-04

    ... European Union carriers in the future. Docket Number: DOT-OST-2013-0057. Date Filed: March 20, 2013. Due... transportation of persons, property and mail from any point or points behind any Member State of the European Union, via any point or points in any Member State and via intermediate points to any point or points...

  2. Cloud Climatologies for Rocket Triggered Lightning from Launches at Cape Canaveral Air Force Station and Kennedy Space Center

    DTIC Science & Technology

    2012-03-01

    meteorological conditions near the site of the Apollo XII incident (From: Merceret et al. 2010) As the Saturn V rocket with the manned space capsule ascended... full set of LLCC evaluated during all launches from CCAFS/KSC is listed below. 1) Surface Electric Field Mill 2) Natural Lightning 3) Cumulus...equation. ∙ ∙ The specific derivations and details of the hypsometric equation can be located in numerous meteorological texts , but we referenced

  3. Peak Wind Forecasts for the Launch-Critical Wind Towers on Kennedy Space Center/Cape Canaveral Air Force Station, Phase IV

    NASA Technical Reports Server (NTRS)

    Crawford, Winifred

    2011-01-01

    This final report describes the development of a peak wind forecast tool to assist forecasters in determining the probability of violating launch commit criteria (LCC) at Kennedy Space Center (KSC) and Cape Canaveral Air Force Station (CCAFS). The peak winds arc an important forecast clement for both the Space Shuttle and Expendable Launch Vehicle (ELV) programs. The LCC define specific peak wind thresholds for each launch operation that cannot be exceeded in order to ensure the safety of the vehicle. The 45th Weather Squadron (45 WS) has found that peak winds are a challenging parameter to forecast, particularly in the cool season months of October through April. Based on the importance of forecasting peak winds, the 45 WS tasked the Applied Meteorology Unit (AMU) to update the statistics in the current peak-wind forecast tool to assist in forecasting LCC violations. The tool includes onshore and offshore flow climatologies of the 5-minute mean and peak winds and probability distributions of the peak winds as a function of the 5-minute mean wind speeds.

  4. Successful Demolition of Historic Cape Canaveral Air Force Station Launch Facilities: Managing the Process to Maximize Recycle Value to Fund Demolition

    SciTech Connect

    Jones, A.; Hambro, L.; Hooper, K.

    2008-07-01

    This paper will present the history of the Atlas 36 and Titan 40 Space Launch Complexes (SLC), the facility assessment process, demolition planning, recycle methodology, and actual facility demolition that resulted in a 40% reduction in baseline cost. These two SLC launched hundreds of payloads into space from Cape Canaveral Air Force Station (AFS), Florida. The Atlas-Centaur family of rockets could lift small- to medium-size satellites designed for communications, weather, or military use, placing them with near pinpoint accuracy into their intended orbits. The larger Titan family was relied upon for heavier lifting needs, including launching military satellites as well as interplanetary probes. But despite their efficiency and cost-effectiveness, the Titan rockets, as well as earlier generation Atlas models, were retired in 2005. Concerns about potential environmental health hazards from PCBs and lead-based paint chipping off the facilities also contributed to the Air Force's decision in 2005 to dismantle and demolish the Atlas and Titan missile-launching systems. Lockheed Martin secured the complex following the final launch, removed equipment and turned over the site to the Air Force for decommissioning and demolition (D and D). AMEC was retained by the Air Force to perform demolition planning and facility D and D in 2004. AMEC began with a review of historical information, interviews with past operations personnel, and 100% facility assessment of over 100 structures. There where numerous support buildings that due to their age contained asbestos containing material (ACM), PCB-impacted material, and universal material that had to be identified and removed prior to demolition. Environmental testing had revealed that the 36B mobile support tower (MST) exceeded the TSCA standard for polychlorinated biphenyls (PCB) paint (<50 ppm), as did the high bay sections of the Titan Vertical Integration Building (VIB). Thus, while most of the steel structures could be

  5. Magnetic Launch Assist System Demonstration

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This Quick Time movie demonstrates the Magnetic Launch Assist system, previously referred to as the Magnetic Levitation (Maglev) system, for space launch using a 5 foot model of a reusable Bantam Class launch vehicle on a 50 foot track that provided 6-g acceleration and 6-g de-acceleration. Overcoming the grip of Earth's gravity is a supreme challenge for engineers who design rockets that leave the planet. Engineers at the Marshall Space Flight Center have developed and tested Magnetic Launch Assist technologies that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using electricity and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the takeoff, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  6. 78 FR 76701 - Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-12-18

    ... permitted under the open skies U.S.-E.U.-Iceland-Norway Air Transport Agreement; Norwegian International... point or points in Norway, via intermediate points, and any point or points in the United States;...

  7. 78 FR 19354 - Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-03-29

    ... Modify Scope: March 26, 2013. Description: Application of AirBridgeCargo Airlines, LLC (``ABC..., Florida; Dallas/Fort Worth, Texas; and Los Angeles, California, on the other hand, and beyond. ABC...

  8. eLaunch Hypersonics: An Advanced Launch System

    NASA Technical Reports Server (NTRS)

    Starr, Stanley

    2010-01-01

    This presentation describes a new space launch system that NASA can and should develop. This approach can significantly reduce ground processing and launch costs, improve reliability, and broaden the scope of what we do in near earth orbit. The concept (not new) is to launch a re-usable air-breathing hypersonic vehicle from a ground based electric track. This vehicle launches a final rocket stage at high altitude/velocity for the final leg to orbit. The proposal here differs from past studies in that we will launch above Mach 1.5 (above transonic pinch point) which further improves the efficiency of air breathing, horizontal take-off launch systems. The approach described here significantly reduces cost per kilogram to orbit, increases safety and reliability of the boost systems, and reduces ground costs due to horizontal-processing. Finally, this approach provides significant technology transfer benefits for our national infrastructure.

  9. Launch vehicle

    NASA Astrophysics Data System (ADS)

    Rutledge, William S.

    1994-06-01

    Concentrated efforts by NASA and the DOD to begin development of a new large launch vehicle have been under way for over a decade. Options include the National Launch System, Advanced Launch System, a heavy lift vehicle, a Shuttle-derived vehicle, a Titan-derived vehicle, Single stage To Orbit, NASP and Spacelifter, to name a few. All initially promised low operations costs achieved at development costs in the $5 billion - $10 billion range. However, none has obtained approval for development, primarily because it became apparent that these cost goals could not realistically be met.

  10. A method for the determination of potentially profitable service patterns for commuter air carriers

    NASA Technical Reports Server (NTRS)

    Ransone, R. K.; Kuhlthau, A. R.; Deptula, D. A.

    1975-01-01

    A methodology for estimating market conception was developed as a part of the short-haul air transportation program. It is based upon an analysis of actual documents which provide a record of known travel history. Applying this methodology a forecast was made of the demand for an air feeder service between Charlottesville, Virginia and Dulles International Airport. Local business travel vouchers and local travel agent records were selected to provide the documentation. The market was determined to be profitable for an 8-passenger Cessna 402B aircraft flying a 2-hour daily service pattern designed to mesh to the best extent possible with the connecting schedules at Dulles. The Charlottesville - Dulles air feeder service market conception forecast and its methodology are documented.

  11. NPP Launch

    NASA Video Gallery

    NASA's National Polar-orbiting Operational Environmental Satellite System Preparatory Project (NPP) spacecraft was launched aboard a Delta II rocket at 5:48 a.m. EDT today, on a mission to measure ...

  12. An Integrated Framework for Modeling Air Carrier Behavior, Policy, and Impacts in the U.S. Air Transportation System

    NASA Technical Reports Server (NTRS)

    Horio, Brant M.; Kumar, Vivek; DeCicco, Anthony H.; Hasan, Shahab; Stouffer, Virginia L.; Smith, Jeremy C.; Guerreiro, Nelson M.

    2015-01-01

    The implementation of the Next Generation Air Transportation System (NextGen) in the United States is an ongoing challenge for policymakers due to the complexity of the air transportation system (ATS) with its broad array of stakeholders and dynamic interdependencies between them. The successful implementation of NextGen has a hard dependency on the active participation of U.S. commercial airlines. To assist policymakers in identifying potential policy designs that facilitate the implementation of NextGen, the National Aeronautics and Space Administration (NASA) and LMI developed a research framework called the Air Transportation System Evolutionary Simulation (ATS-EVOS). This framework integrates large empirical data sets with multiple specialized models to simulate the evolution of the airline response to potential future policies and explore consequential impacts on ATS performance and market dynamics. In the ATS-EVOS configuration presented here, we leverage the Transportation Systems Analysis Model (TSAM), the Airline Evolutionary Simulation (AIRLINE-EVOS), the Airspace Concept Evaluation System (ACES), and the Aviation Environmental Design Tool (AEDT), all of which enable this research to comprehensively represent the complex facets of the ATS and its participants. We validated this baseline configuration of ATS-EVOS against Airline Origin and Destination Survey (DB1B) data and subject matter expert opinion, and we verified the ATS-EVOS framework and agent behavior logic through scenario-based experiments that explored potential implementations of a carbon tax, congestion pricing policy, and the dynamics for equipage of new technology by airlines. These experiments demonstrated ATS-EVOS's capabilities in responding to a wide range of potential NextGen-related policies and utility for decision makers to gain insights for effective policy design.

  13. 78 FR 68134 - Certificates of Public Convenience and Necessity and Foreign Air Carrier Permits

    Federal Register 2010, 2011, 2012, 2013, 2014

    2013-11-13

    ... the European Union, via any point or points in any EU Member State and via intermediate points, to any...) charter transportation authorized by any additional route ] rights made available to European Union... of the European Common Aviation Area; (iii) foreign charter air transportation of cargo between...

  14. Equivalent ambipolar carrier injection of electrons and holes with Au electrodes in air-stable field effect transistors

    SciTech Connect

    Kanagasekaran, Thangavel E-mail: Shimotani@m.tohoku.ac.jp Ikeda, Susumu; Kumashiro, Ryotaro; Shimotani, Hidekazu E-mail: Shimotani@m.tohoku.ac.jp Shang, Hui; Tanigaki, Katsumi E-mail: Shimotani@m.tohoku.ac.jp

    2015-07-27

    Carrier injection from Au electrodes to organic thin-film active layers can be greatly improved for both electrons and holes by nano-structural surface control of organic semiconducting thin films using long-chain aliphatic molecules on a SiO{sub 2} gate insulator. In this paper, we demonstrate a stark contrast for a 2,5-bis(4-biphenylyl)bithiophene (BP2T) active semiconducting layer grown on a modified SiO{sub 2} dielectric gate insulator between two different modifications of tetratetracontane and poly(methyl methacrylate) thin films. Important evidence that the field effect transistor (FET) characteristics are independent of electrode metals with different work functions is given by the observation of a conversion of the metal-semiconductor contact from the Schottky limit to the Bardeen limit. An air-stable light emitting FET with an Au electrode is demonstrated.

  15. Statistical Analysis of Model Data for Operational Space Launch Weather Support at Kennedy Space Center and Cape Canaveral Air Force Station

    NASA Technical Reports Server (NTRS)

    Bauman, William H., III

    2010-01-01

    The 12-km resolution North American Mesoscale (NAM) model (MesoNAM) is used by the 45th Weather Squadron (45 WS) Launch Weather Officers at Kennedy Space Center (KSC) and Cape Canaveral Air Force Station (CCAFS) to support space launch weather operations. The 45 WS tasked the Applied Meteorology Unit to conduct an objective statistics-based analysis of MesoNAM output compared to wind tower mesonet observations and then develop a an operational tool to display the results. The National Centers for Environmental Prediction began running the current version of the MesoNAM in mid-August 2006. The period of record for the dataset was 1 September 2006 - 31 January 2010. The AMU evaluated MesoNAM hourly forecasts from 0 to 84 hours based on model initialization times of 00, 06, 12 and 18 UTC. The MesoNAM forecast winds, temperature and dew point were compared to the observed values of these parameters from the sensors in the KSC/CCAFS wind tower network. The data sets were stratified by model initialization time, month and onshore/offshore flow for each wind tower. Statistics computed included bias (mean difference), standard deviation of the bias, root mean square error (RMSE) and a hypothesis test for bias = O. Twelve wind towers located in close proximity to key launch complexes were used for the statistical analysis with the sensors on the towers positioned at varying heights to include 6 ft, 30 ft, 54 ft, 60 ft, 90 ft, 162 ft, 204 ft and 230 ft depending on the launch vehicle and associated weather launch commit criteria being evaluated. These twelve wind towers support activities for the Space Shuttle (launch and landing), Delta IV, Atlas V and Falcon 9 launch vehicles. For all twelve towers, the results indicate a diurnal signal in the bias of temperature (T) and weaker but discernable diurnal signal in the bias of dewpoint temperature (T(sub d)) in the MesoNAM forecasts. Also, the standard deviation of the bias and RMSE of T, T(sub d), wind speed and wind

  16. Free-flight Performance of a Rocket-boosted, Air-launched 16-inch-diameter Ram-jet Engine at Mach Numbers up to 2.20

    NASA Technical Reports Server (NTRS)

    Disher, John H; Kohl, Robert C; Jones, Merle L

    1953-01-01

    The investigation of air-launched ram-jet engines has been extended to include a study of models with a nominal design free-stream Mach number of 2.40. These models require auxiliary thrust in order to attain a flight speed at which the ram jet becomes self-accelerating. A rocket-boosting technique for providing this auxiliary thrust is described and time histories of two rocket-boosted ram-jet flights are presented. In one flight, the model attained a maximum Mach number of 2.20 before a fuel system failure resulted in the destruction of the engine. Performance data for this model are presented in terms of thrust and drag coefficients, diffuser pressure recovery, mass-flow ratio, combustion efficiency, specific fuel consumption, and over-all engine efficiency.

  17. Evolved Expendable Launch Vehicle: The Air Force Needs to Adopt an Incremental Approach to Future Acquisition Planning to Enable Incorporation of Lessons Learned

    DTIC Science & Technology

    2015-08-01

    expressed interest in competing for national security launches, including ULA, Space Exploration Technologies, Inc. ( SpaceX ), and Orbital Sciences...launch offices, and launch service providers including ULA, SpaceX , and Orbital Sciences Corporation. We also reviewed past GAO reports on EELV...launch until 2019 at the earliest, and will still have to become certified. SpaceX earned certification for its Falcon 9 launch vehicle in May 2015, but

  18. B-52 Launch Aircraft in Flight

    NASA Technical Reports Server (NTRS)

    2001-01-01

    NASA's venerable B-52 mothership is seen here photographed from a KC-135 Tanker aircraft. The X-43 adapter is visible attached to the right wing. The B-52, used for launching experimental aircraft and for other flight research projects, has been a familiar sight in the skies over Edwards for more than 40 years and is also both the oldest B-52 still flying and the aircraft with the lowest flight time of any B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported

  19. Agent Based Modeling of Air Carrier Behavior for Evaluation of Technology Equipage and Adoption

    NASA Technical Reports Server (NTRS)

    Horio, Brant M.; DeCicco, Anthony H.; Stouffer, Virginia L.; Hasan, Shahab; Rosenbaum, Rebecca L.; Smith, Jeremy C.

    2014-01-01

    As part of ongoing research, the National Aeronautics and Space Administration (NASA) and LMI developed a research framework to assist policymakers in identifying impacts on the U.S. air transportation system (ATS) of potential policies and technology related to the implementation of the Next Generation Air Transportation System (NextGen). This framework, called the Air Transportation System Evolutionary Simulation (ATS-EVOS), integrates multiple models into a single process flow to best simulate responses by U.S. commercial airlines and other ATS stakeholders to NextGen-related policies, and in turn, how those responses impact the ATS. Development of this framework required NASA and LMI to create an agent-based model of airline and passenger behavior. This Airline Evolutionary Simulation (AIRLINE-EVOS) models airline decisions about tactical airfare and schedule adjustments, and strategic decisions related to fleet assignments, market prices, and equipage. AIRLINE-EVOS models its own heterogeneous population of passenger agents that interact with airlines; this interaction allows the model to simulate the cycle of action-reaction as airlines compete with each other and engage passengers. We validated a baseline configuration of AIRLINE-EVOS against Airline Origin and Destination Survey (DB1B) data and subject matter expert opinion, and we verified the ATS-EVOS framework and agent behavior logic through scenario-based experiments. These experiments demonstrated AIRLINE-EVOS's capabilities in responding to an input price shock in fuel prices, and to equipage challenges in a series of analyses based on potential incentive policies for best equipped best served, optimal-wind routing, and traffic management initiative exemption concepts..

  20. Final Supplemental Environmental Assessment: Falcon I Launch Vehicle Program from SLC-4W Vandenberg Air Force Base, California

    DTIC Science & Technology

    2005-09-06

    necessary, with an adequate margin of safety to protect the public health . 5 . National Secondary Standards: The level of air quality necessary to protect...Program as analyzed in the Falcon EA. This EA considers the potential impacts of the Proposed Action on the natural and human environments, both as a...reference, found that there was no impact or less than significant impact to the natural or human environment from the operation of the Falcon

  1. 26 CFR 40.6071(a)-3 - Time for an eligible air carrier to file a return for the third calendar quarter of 2001.

    Code of Federal Regulations, 2010 CFR

    2010-04-01

    ... return for the third calendar quarter of 2001. 40.6071(a)-3 Section 40.6071(a)-3 Internal Revenue... calendar quarter of 2001. (a) In general. If, in the case of an eligible air carrier, the quarterly return required under § 40.6011(a)-1(a) for the third calendar quarter of 2001 includes tax imposed by...

  2. 26 CFR 40.6071(a)-3 - Time for an eligible air carrier to file a return for the third calendar quarter of 2001.

    Code of Federal Regulations, 2013 CFR

    2013-04-01

    ... return for the third calendar quarter of 2001. 40.6071(a)-3 Section 40.6071(a)-3 Internal Revenue... calendar quarter of 2001. (a) In general. If, in the case of an eligible air carrier, the quarterly return required under § 40.6011(a)-1(a) for the third calendar quarter of 2001 includes tax imposed by...

  3. 26 CFR 40.6071(a)-3 - Time for an eligible air carrier to file a return for the third calendar quarter of 2001.

    Code of Federal Regulations, 2011 CFR

    2011-04-01

    ... return for the third calendar quarter of 2001. 40.6071(a)-3 Section 40.6071(a)-3 Internal Revenue... calendar quarter of 2001. (a) In general. If, in the case of an eligible air carrier, the quarterly return required under § 40.6011(a)-1(a) for the third calendar quarter of 2001 includes tax imposed by...

  4. 26 CFR 40.6071(a)-3 - Time for an eligible air carrier to file a return for the third calendar quarter of 2001.

    Code of Federal Regulations, 2012 CFR

    2012-04-01

    ... return for the third calendar quarter of 2001. 40.6071(a)-3 Section 40.6071(a)-3 Internal Revenue... calendar quarter of 2001. (a) In general. If, in the case of an eligible air carrier, the quarterly return required under § 40.6011(a)-1(a) for the third calendar quarter of 2001 includes tax imposed by...

  5. Airport noise complaint patterns and interviews of frequent complainers at two major air carrier airports

    NASA Astrophysics Data System (ADS)

    Jaggers, Nicholas; Eiff, Gary

    2005-09-01

    The complex and highly sensitive topic of aircraft noise and population annoyance continues to be a major inhibitor to airport development plans. The projected growth of air travel necessitates expanded capacity at many existing airports and the development and construction of new airports in order to accommodate burgeoning traveler needs. Concerns by citizens near major airports about their economic, health, and social welfare continue to generate community and individual declarations of annoyance and concern which threaten timely solutions to airport expansion plans. A deeper understanding of the nature of these concerns is important to more effectively cope with airport expansion concerns among adjacent communities and surrounding neighbors. This study analyzed existing noise complaints registered at Denver International Airport (DEN) and Fort Lauderdale/Hollywood International Airport (FLL) in an attempt to gain greater understanding of noise complaint drivers and public annoyance. Interviews of frequent complainers were utilized in order to gain richer data concerning individual annoyance issues.

  6. The Division of Military Air Transportation between Civilian and Military Carriers,

    DTIC Science & Technology

    1969-05-01

    AO-AOAO 379 RAND CORP SANTA MONICA CA F/ B 15/5 THE DIVISION OF MILITARY AIR TRANSPORTATION BETWEEN CIVILIAN AN-ETC(U) MAY 69 L J KLEIGER UNCLASSIFIED...26.1 19b6 89.5 30.2 1967 90.8 33.7 1968 b 91.0 25.6 SOURCES: USAF, Military Airlift Command, Airl ift Service t.anagement Renort, 1959-1967; ibid...93,257 64.8 144,021 1965 87,326 45.0 106,630 55.0 193,956 L966 156,253 47.7 171,630 52.3 327,883 1967 328,441 55.0 269,132 45.0 597,573 1968 b 310,838

  7. KSC Vertical Launch Site Evaluation

    NASA Technical Reports Server (NTRS)

    Phillips, Lynne V.

    2007-01-01

    RS&H was tasked to evaluate the potential available launch sites for a combined two user launch pad. The Launch sites were to be contained entirely within current Kennedy Space Center property lines. The user launch vehicles to be used for evaluation are in the one million pounds of first stage thrust range. Additionally a second evaluation criterion was added early on in the study. A single user launch site was to be evaluated for a two million pound first stage thrust vehicle. Both scenarios were to be included in the report. To provide fidelity to the study criteria, a specific launch vehicle in the one million pound thrust range was chosen as a guide post or straw-man launch vehicle. The RpK K-1 vehicle is a current Commercial Orbital Transportation System (COTS), contract awardee along with the SpaceX Falcon 9 vehicle. SpaceX, at the time of writing, is planning to launch COTS and possibly other payloads from Cx-40 on Cape Canaveral Air Force Station property. RpK has yet to declare a specific launch site as their east coast US launch location. As such it was deemed appropriate that RpK's vehicle requirements be used as conceptual criteria. For the purposes of this study those criteria were marginally generalized to make them less specifiC.

  8. Launch vehicles

    NASA Astrophysics Data System (ADS)

    Moss, J. B.

    The basic principles which determine launcher design and hence constrain the spacecraft payload are determined. Some key features of the principal launcher alternatives in Europe and the U.S., namely, the unmanned, expendable Ariane and the manned, substantially reusable, Space Shuttle, are outlined. The equations of motion of the rocket are specialized to the vertical plane, parallel and normal to the flight direction, and to the motion of the center of mass and the pitch rotation. A typical Ariane 2 flight profile for transfer into GTO is illustrated. Some representative mission requirements for spacecraft launches are reviewed. Launch vehicle burnout velocities for spacecraft emplacement are given. Geostationary orbit emplacement, orbital mission performance, and configuration interactions are discussed.

  9. Small Space Launch: Origins & Challenges

    NASA Astrophysics Data System (ADS)

    Freeman, T.; Delarosa, J.

    2010-09-01

    The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft, and in the development of constellations of spacecraft. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by an old, unresponsive and relatively expensive set of launchers in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. The United States directed Air Force Space Command to develop the capability for operationally responsive access to space and use of space to support national security, including the ability to provide critical space capabilities in the event of a failure of launch or on-orbit capabilities. On 1 Aug 06, Air Force Space Command activated the Space Development & Test Wing (SDTW) to perform development, test and evaluation of Air Force space systems and to execute advanced space deployment and demonstration projects to exploit new concepts and technologies, and rapidly migrate capabilities to the warfighter. The SDTW charged the Launch Test Squadron (LTS) with the mission to develop the capability of small space launch, supporting government research and development space launches and missile defense target missions, with operationally responsive spacelift for Low-Earth-Orbit Space Situational Awareness assets as a future mission. This new mission created new challenges for LTS. The LTS mission tenets of developing space launches and missile defense target vehicles were an evolution from the squadrons previous mission of providing sounding rockets under the Rocket

  10. Performance characteristics of a new prototype for a portable GC using ambient air as carrier gas for on-site analysis.

    PubMed

    Sanchez, Juan M; Sacks, Richard D

    2007-05-01

    The performance characteristics of a portable GC instrument requiring no compressed gas supplies and using relatively lightweight transportable components for the analysis of volatile organic components in large-volume air samples are described. To avoid the need for compressed gas tanks, ambient air is used as the carrier gas, and a vacuum pump is used to pull the carrier gas and injected samples through the wall-coated capillary column and a photoionization detector (PID). At-column heating is used eliminating the need for a conventional oven. The fused silica column is wrapped with heater wire and sensor wire so that heating is provided directly at the column. A PID is used since it requires no external gas supplies and has high sensitivity for many compounds of interest in environmental air monitoring. In order to achieve detection limits in the ppb range, an online multibed preconcentrator containing beds of graphitized carbons and carbon molecular sieves is used. After sample collection, the flow direction through the preconcentrator is reversed, and the sample is thermally desorbed directly into the column. Decomposition of sensitive compounds during desorption is greater with air as the carrier gas than with hydrogen.

  11. X-2 launch from B-50 mothership

    NASA Technical Reports Server (NTRS)

    1950-01-01

    The X-2 was a swept-wing aircraft designed to fly three times as fast as the speed of sound. It was flown to investigate the problems of aerodynamic heating and stability and control effectiveness at high speeds and altitudes. The X-2 was a single-place airplane with wings swept back to 40 degrees. It was 37 ft., 10 in. long, 11 ft. high and had a wingspan of 32.3 ft. It wasc onstructed primarily of steel (K-monel) and incorporated a skid-type main landing gear to make more room for fuel. It had an ejectable nose capsule. The X-2 was powered by an XLR25-CW-3 two-chambered rocket engine. The Curtiss-Wright-manufactured engine was throttleable and had a thrust of from 2,500 to 15,000 lbs. Two X-2s were made for NACA and the Air Force by Bell Aircraft Co. They were air launched from a B-50 carrier aircraft. After one X-2 (no. 2 aircraft) was destroyed in an explosion on a captive flight before ever making any powered flights, the other X-2 (no. 1 aircraft) went on to perform as predicted including making a flight on Sept.7, 1956, with Air Force Captain Iven Kincheloe at the controls to an altitude of 126,200 ft. Twenty days later the X-2 program ended when Air Force Captain Milburn Apt piloted the X-2 to its highest speed of 2,094 mph(over three times the speed of sound) before it went out of control and crashed. Captain Apt was fatally injured in the crash. This 27-second video clip shows the launch of the X-2 from its B-50 mothership, ignition of its rocket engine, and flight. At the end of the clip, observers on the ground appear looking up at the X-2.

  12. Magnetic Launch Assist Experimental Track

    NASA Technical Reports Server (NTRS)

    1999-01-01

    In this photograph, a futuristic spacecraft model sits atop a carrier on the Magnetic Launch Assist System, formerly known as the Magnetic Levitation (MagLev) System, experimental track at the Marshall Space Flight Center (MSFC). Engineers at MSFC have developed and tested Magnetic Launch Assist technologies that would use magnetic fields to levitate and accelerate a vehicle along a track at very high speeds. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a Magnetic Launch Assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide, and about 1.5-feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  13. Magnetic Launch Assist Demonstration Test

    NASA Technical Reports Server (NTRS)

    2001-01-01

    This image shows a 1/9 subscale model vehicle clearing the Magnetic Launch Assist System, formerly referred to as the Magnetic Levitation (MagLev), test track during a demonstration test conducted at the Marshall Space Flight Center (MSFC). Engineers at MSFC have developed and tested Magnetic Launch Assist technologies. To launch spacecraft into orbit, a Magnetic Launch Assist System would use magnetic fields to levitate and accelerate a vehicle along a track at very high speeds. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a launch-assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide and about 1.5-feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  14. Advanced Launch Development Program status

    NASA Technical Reports Server (NTRS)

    Colgrove, Roger

    1990-01-01

    The Advanced Launch System is a joint NASA - Air Force program originally directed to define the concept for a modular family of launch vehicles, to continue development programs and preliminary design activities focused primarily on low cost to orbit, and to offer maturing technologies to existing systems. The program was restructed in the spring of 1990 as a result of funding reductions and renamed the Advanced Launch Development Program. This paper addresses the program's status following that restructuring and as NASA and the Air Force commence a period of deliberation over future space launch needs and the budgetary resources available to meet those needs. The program is currently poised to protect a full-scale development decision in the mid-1990's through the appropriate application of program resources. These resources are concentrated upon maintaining the phase II system contractor teams, continuing the Space Transportation Engine development activity, and refocusing the Advanced Development Program demonstrated activities.

  15. No Launch Before Its Time

    NASA Technical Reports Server (NTRS)

    Townsend, Bill

    2004-01-01

    Aura is an Earth-observing satellite developed to help us study the quality of the air we breathe. It will look at the state of the ozone and the atmospheric composition in regards to the Earth's changing climate. I headed to California on July 5, 2004. The plan was that the satellite would launch on the tenth, but we had a few problems getting it off. This was the fifty-ninth launch of my career, and it was also a little different than most of my previous launches. Most of the time it's weather that postpones a launch; there aren't usually that many technical issues this late in the game. This time. however, we had several problems, equally split between the launch vehicle and the spacecraft. I remember a member of the crew asking me, 'Is this normal?' And in my experience, it wasn't.

  16. 14 CFR 204.6 - Certificated and commuter air carriers proposing a change in operations, ownership, or management...

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... proposing a change in operations, ownership, or management which is not substantial. 204.6 Section 204.6... carriers proposing a change in operations, ownership, or management which is not substantial. Carriers proposing to make a change which would not substantially affect their operations, management, or...

  17. 14 CFR 204.6 - Certificated and commuter air carriers proposing a change in operations, ownership, or management...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... proposing a change in operations, ownership, or management which is not substantial. 204.6 Section 204.6... carriers proposing a change in operations, ownership, or management which is not substantial. Carriers proposing to make a change which would not substantially affect their operations, management, or...

  18. Tabletop Experimental Track for Magnetic Launch Assist

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Marshall Space Flight Center's (MSFC's) Advanced Space Transportation Program has developed the Magnetic Launch Assist System, formerly known as the Magnetic Levitation (MagLev) technology that could give a space vehicle a running start to break free from Earth's gravity. A Magnetic Launch Assist system would use magnetic fields to levitate and accelerate a vehicle along a track at speeds up to 600 mph. The vehicle would shift to rocket engines for launch into orbit. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a Magnetic Launch Assist system would electromagnetically propel a space vehicle along the track. The tabletop experimental track for the system shown in this photograph is 44-feet long, with 22-feet of powered acceleration and 22-feet of passive braking. A 10-pound carrier with permanent magnets on its sides swiftly glides by copper coils, producing a levitation force. The track uses a linear synchronous motor, which means the track is synchronized to turn the coils on just before the carrier comes in contact with them, and off once the carrier passes. Sensors are positioned on the side of the track to determine the carrier's position so the appropriate drive coils can be energized. MSFC engineers have conducted tests on the indoor track and a 50-foot outdoor track. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  19. Summary of airborne chlorine and hydrogen chloride gas measurements for August 20 and September 5, 1977 Voyager launches at Air Force Eastern Test Range, Florida

    NASA Technical Reports Server (NTRS)

    Gregory, G. L.; Emerson, B. R., Jr.; Hudgins, C. H.

    1978-01-01

    Airborne chlorine and hydrogen chloride measurements were made in the tropospheric ground cloud following the Voyager launches of August 20 and September 5, 1977. The maximum observed hydrogen chloride concentration for both launches was about 25 to 30 parts per million (ppm) occurring typically 2 to 6 minutes after launch. By completion of the sampling mission (1-1/2 hours for August, 4-1/2 hours for September), the maximum in-cloud concentration decayed to about 1 to 2 ppm. Maximum observed chlorine concentrations were about 40 to 55 parts per billion (ppb) about 2 to 8 minutes after launch; by about 15 minutes after launch, chlorine concentrations were less than 10 ppb (detection limit). In-cloud chlorine concentrations were well below 1 percent of hydrogen chloride concentrations. The appendix of the report discusses the chlorine instrument and the laboratory evaluation of the detector.

  20. STS-39 Launch

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Launched aboard the Space Shuttle Discovery on April 28, 1991 at 7:33:14 am (EDT), STS-39 was a Department of Defense (DOD) mission. The crew included seven astronauts: Michael L. Coats, commander; L. Blaine Hammond, pilot; Guion S. Buford, Jr., mission specialist 1; Gregory J. Harbaugh, mission specialist 2; Richard J. Hieb, mission specialist 3; Donald R. McMonagle, mission specialist 4; and Charles L. Veach, mission specialist 5. The primary unclassified payload included the Air Force Program 675 (AFP-675), the Infrared Background Signature Survey (IBSS), and the Shuttle Pallet Satellite II (SPAS II).

  1. Magnetic Launch Assist Vehicle-Artist's Concept

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This artist's concept depicts a Magnetic Launch Assist vehicle clearing the track and shifting to rocket engines for launch into orbit. The system, formerly referred as the Magnetic Levitation (MagLev) system, is a launch system developed and tested by Engineers at the Marshall Space Flight Center (MSFC) that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using an off-board electric energy source and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. The system is similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway. A full-scale, operational track would be about 1.5-miles long, capable of accelerating a vehicle to 600 mph in 9.5 seconds, and the vehicle would then shift to rocket engines for launch into orbit. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  2. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. VOLUME 29, LAUNCH CONTROL CENTER (LCC) TITLE AND LOCATION SHEET. Sheet 29-01 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  3. Magnetic Launch Assist

    NASA Technical Reports Server (NTRS)

    Jacobs, W. A.

    2000-01-01

    With the ever-increasing cost of getting to space and the need for safe, reliable, and inexpensive ways to access space, NASA is taking a look at technologies that will get us there. One of these technologies is Magnetic Launch Assist (MagLev). This is the concept of using both magnetic levitation and magnetic propulsion to provide an initial velocity by using electrical power from ground sources. The use of ground based power can significantly reduce operational costs over the consumables necessary to attain the same velocity. The technologies to accomplish this are both old and new. The concept of MagLev has been around for a long time and several MagLev Trains have already been made. Where NASA's MagLev diverges from the traditional train is in the immense power required to propel this vehicle to 600 feet per second in less than 10 seconds. New technologies or the upgrade of existing technologies will need to be investigated in areas of energy storage and power switching. Plus the separation of a very large mass (the space vehicle) and the aerodynamics of that vehicle while on the carrier are also of great concern and require considerable study and testing. NASA's plan is to mature these technologies in the next 10 years to achieve our goal of launching a full sized space vehicle off a MagLev rail.

  4. Carrier lifetime reduction in 1.5 μm AlGaAsSb saturable absorbers with air and AlAsSb barriers

    NASA Astrophysics Data System (ADS)

    Ostinelli, O.; Bächtold, W.; Haiml, H.; Grange, R.; Keller, U.; Gini, E.; Almuneau, G.

    2006-08-01

    The optical properties of different AlGaAsSb semiconductor saturable absorber mirrors and InP /AlGaAsSb heterostructures have been investigated by pump-probe and low temperature photoluminescence measurements. The results show that the type-II electron-hole recombination process at the InP-AlGaAsSb interface is responsible for the slow carrier decay time in the absorber. Nevertheless, this slow transition can be avoided by growing an AlAsSb barrier layer between InP and the absorber layer promoting the fast electron-hole recombination at the surface states on the absorber/air interface. This allows reducing the carrier decay time from several nanoseconds down to 20ps.

  5. Space Logistics: Launch Capabilities

    NASA Technical Reports Server (NTRS)

    Furnas, Randall B.

    1989-01-01

    The current maximum launch capability for the United States are shown. The predicted Earth-to-orbit requirements for the United States are presented. Contrasting the two indicates the strong National need for a major increase in Earth-to-orbit lift capability. Approximate weights for planned payloads are shown. NASA is studying the following options to meet the need for a new heavy-lift capability by mid to late 1990's: (1) Shuttle-C for near term (include growth versions); and (2) the Advanced Lauching System (ALS) for the long term. The current baseline two-engine Shuttle-C has a 15 x 82 ft payload bay and an expected lift capability of 82,000 lb to Low Earth Orbit. Several options are being considered which have expanded diameter payload bays. A three-engine Shuttle-C with an expected lift of 145,000 lb to LEO is being evaluated as well. The Advanced Launch System (ALS) is a potential joint development between the Air Force and NASA. This program is focused toward long-term launch requirements, specifically beyond the year 2000. The basic approach is to develop a family of vehicles with the same high reliability as the Shuttle system, yet offering a much greater lift capability at a greatly reduced cost (per pound of payload). The ALS unmanned family of vehicles will provide a low end lift capability equivalent to Titan IV, and a high end lift capability greater than the Soviet Energia if requirements for such a high-end vehicle are defined.In conclusion, the planning of the next generation space telescope should not be constrained to the current launch vehicles. New vehicle designs will be driven by the needs of anticipated heavy users.

  6. Nighttime Launch at NASA Wallops

    NASA Video Gallery

    A U.S. Air Force Minotaur 1 rocket carrying the Department of Defense Operationally Responsive Space office’s ORS-1 satellite was successfully launched at 11:09 p.m. EDT, June 29, 2011, from NASA...

  7. Venture Class Launch Services

    NASA Technical Reports Server (NTRS)

    Wiese, Mark

    2016-01-01

    Provide an introduction to the Launch Services Program, and specifically the strategic initiative that drove the Venture Class Launch Services contracts. Provide information from the VCLS request for proposals, as well as the Agency's CubeSat Launch Initiative.

  8. Launch summary for 1978

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1978-01-01

    Sounding rocket, satellite, and space probe launchings are presented. Time, date, and location of the launches are provided. The sponsoring countries and the institutions responsible for the launch are listed.

  9. Towers for Earth Launch

    NASA Technical Reports Server (NTRS)

    Landis, Geoffrey A.; Lyons, Valerie J. (Technical Monitor)

    2002-01-01

    This report lists some characteristics of a hypothetical 15 kilometer tower for launching spacecraft, the advantages of launching from high altitude, and some equations pertaining to launch from a 15 kilometer tower.

  10. Magnetic Launch Assist System-Artist's Concept

    NASA Technical Reports Server (NTRS)

    1999-01-01

    This illustration is an artist's concept of a Magnetic Launch Assist System, formerly referred as the Magnetic Levitation (Maglev) system, for space launch. Overcoming the grip of Earth's gravity is a supreme challenge for engineers who design rockets that leave the planet. Engineers at the Marshall Space Flight Center have developed and tested Magnetic Launch Assist System technologies that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using electricity and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, landing gear and the wing size, as well as the elimination of propellant weight resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  11. 29. Launch Control Center, view looking in, alert crew mannequin ...

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

    29. Launch Control Center, view looking in, alert crew mannequin at end of Launch Control Center. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  12. Towed Twin-Fuselage Glider Launch System (CGI Animation)

    NASA Video Gallery

    The towed glider is an element of the novel rocket-launching concept of the Towed Glider Air-Launch System (TGALS). The TGALS demonstration’s goal is to provide proof-of-concept of a towed, airborn...

  13. 6. ROOF DETAIL OF MIRROR MOUNTS FOR VIEWING LAUNCH FROM ...

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

    6. ROOF DETAIL OF MIRROR MOUNTS FOR VIEWING LAUNCH FROM INSIDE BLOCKHOUSE, PAD A IN BACKGROUND; VIEW TO EAST. - Cape Canaveral Air Station, Launch Complex 17, Facility 28401, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

  14. 25. View down launch tube, showing shock absorption system. Lyon ...

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

    25. View down launch tube, showing shock absorption system. Lyon - Whiteman Air Force Base, Minuteman Missile Launch Facility Trainer T-12, Northeast of Oscar-01 Missile Alert Facility, Knob Noster, Johnson County, MO

  15. 15. SOUTH SIDE OF LAUNCH DECK SHOWING NEW AUXILIARY FLAME ...

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

    15. SOUTH SIDE OF LAUNCH DECK SHOWING NEW AUXILIARY FLAME DUCTS UNDER CONSTRUCTION, UMBILICAL MAST AT RIGHT; VIEW TO NORTHEAST. - Cape Canaveral Air Station, Launch Complex 17, Facility 28402, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

  16. 83. Shock absorber attaching "egg" to the launch control center, ...

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

    83. Shock absorber attaching "egg" to the launch control center, southwest corner - Ellsworth Air Force Base, Delta Flight, Launch Control Facility, County Road CS23A, North of Exit 127, Interior, Jackson County, SD

  17. 48. Bottom of shock absorber, bottom of launch tube, soda ...

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

    48. Bottom of shock absorber, bottom of launch tube, soda bottle liter at right - Ellsworth Air Force Base, Delta Flight, Launch Facility, On County Road T512, south of Exit 116 off I-90, Interior, Jackson County, SD

  18. 86. Shock absorber, top of launch control center, southeast corner ...

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

    86. Shock absorber, top of launch control center, southeast corner - Ellsworth Air Force Base, Delta Flight, Launch Control Facility, County Road CS23A, North of Exit 127, Interior, Jackson County, SD

  19. Space-X Launches Falcon 9 on Demonstration Flight

    NASA Video Gallery

    SpaceX's Falcon 9 rocket and Dragon spacecraft launched from Launch Complex 40 at Cape Canaveral Air Force Station at 10:43 a.m. EST on Wednesday, Dec. 8. This is first demonstration flight for NAS...

  20. Experimental measurements of the ground cloud effluents and cloud growth for the May 20, 1975, Titan 3C launch at Air Force Eastern Test Range, Florida

    NASA Technical Reports Server (NTRS)

    Gregory, G. L.; Storey, R. W., Jr.

    1977-01-01

    The experiment included surface level and airborne in situ cloud measurements of the exhaust effluents from the Titan IIIC solid rocket boosters. Simultaneous visible spectrum photographic pictures of the ground cloud as well as infrared imaging of the cloud were obtained to study the cloud rise, growth, and direction of travel within the earth's surface mixing layer. The NASA multilayer diffusion model predictions of cloud growth, direction of travel, and expected surface level effluent concentrations were made prior to launch and after launch using measured meteorological conditions. Prelaunch predictions were used to position the effluent monitoring instruments, and the postlaunch predictions were compared with the measured data. Measurement results showed that surface level effluent values were low, often below the detection limits of the instrumentation. The maximum surface level hydrogen chloride concentration measured 50 parts per billion at about 8 km from the launch pad. The maximum observed in-cloud (airborne measurement) hydrogen chloride concentration was 7 per million.

  1. Understanding interdisciplinary health care teams: using simulation design processes from the Air Carrier Advanced Qualification Program to identify and train critical teamwork skills.

    PubMed

    Hamman, William R; Beaudin-Seiler, Beth M; Beaubien, Jeffrey M

    2010-09-01

    In the report "Five Years After 'To Err is Human' ", it was noted that "the combination of complexity, professional fragmentation, and a tradition of individualism, enhanced by a well-entrenched hierarchical authority structure and diffuse accountability, forms a daunting barrier to creating the habits and beliefs of common purpose, teamwork, and individual accountability for successful interdependence that a safe culture requires". Training physicians, nurses, and other professionals to work in teams is a concept that has been promoted by many patient safety experts. However the model of teamwork in healthcare is diffusely defined, no clear performance metrics have been established, and the use of simulation to train teams has been suboptimal. This paper reports on the first three years of work performed in the Michigan Economic Development Corporation (MEDC) Tri-Corridor life science grant to apply concepts and processes of simulation design that were developed in the air carrier industry to understand and train healthcare teams. This work has been monitored by the American Academy for the Advancement of Science (AAA) and is based on concepts designed in the Advanced Qualification Program (AQP) from the air carrier industry, which trains and assesses teamwork skills in the same manner as technical skills. This grant has formed the foundation for the Center of Excellence for Simulation Education and Research (CESR).

  2. Disorienting effects of aircraft catapult launchings: III. Cockpit displays and piloting performance.

    PubMed

    Cohen, M M

    1977-09-01

    Accelerations closely approximating those encountered in catapult launchings of carrier-based aircraft were generated on the Naval Air Development Center's human centrifuge Dynamic Flight Simulator. Flight instruments, controls, and flight dynamics of an A-7 aircraft were provided to four experienced Naval Aviators, who exercised closed-loop control of a simulated climbout immediately after they were exposed to the accelerations. Four experimental conditions were employed for each aviator: 1) no operational flight instruments, 2) conventional flight instruments, 3) a single carrier takeoff director display operating concurrently. Measures of flight parameters, including indicated airspeed, angle of attack, rate of climb, altitude, pitch attitude, and pitch trim adjustment were monitored throughout the simulation. Subjective reactions and piloting performance were examined under each of the four conditions. Results indicate that the carrier takeoff director display significantly reduced pilot workload and enhanced performance during the climbout.

  3. Dryden B-52 Launch Aircraft on Edwards AFB Runway

    NASA Technical Reports Server (NTRS)

    1996-01-01

    NASA's venerable workhorse, the B-52 mothership, rolls out on the Edwards AFB runway after a test flight in 1996. Over the course of more than 40 years, the B-52 launched numerous experimental aircraft, ranging from the X-15 to the X-38, and was also used as a flying testbed for a variety of other research projects. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket

  4. Dryden B-52 Launch Aircraft on Dryden Ramp

    NASA Technical Reports Server (NTRS)

    1996-01-01

    NASA's venerable B-52 mothership sits on the ramp in front of the Dryden Flight Research Center, Edwards, California. Over the course of more than 40 years, the B-52 launched numerous experimental aircraft, ranging from the X-15 to the X-38, and was also used as a flying testbed for a variety of other research projects. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of parachute recovery systems used to recover the space shuttle solid rocket

  5. Dryden B-52 Launch Aircraft in Flight over Dryden

    NASA Technical Reports Server (NTRS)

    1996-01-01

    NASA's venerable B-52 mothership flies over the main building at the Dryden Flight Research Center, Edwards, California. The B-52, used for launching experimental aircraft and for other flight research projects, has been a familiar sight in the skies over Edwards for more than 40 years and has also been both the oldest B-52 still flying and the aircraft with the lowest flight time of any B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the development of

  6. National Security Space Launch at a Crossroads

    DTIC Science & Technology

    2016-05-13

    questions over individual launch costs, along with legal challenges to the Air Force EELV program by SpaceX , have contributed to Congress recently taking...Russian RD-180 Main Engine ......................................................................... 7 SpaceX Challenges to the EELV Acquisition...unresolved questions over individual launch costs, along with legal challenges to the Air Force EELV program by SpaceX , have contributed to Congress recently

  7. Benefits and limitations of composites in carrier-based aircraft

    NASA Technical Reports Server (NTRS)

    Mcerlean, Donald P.

    1992-01-01

    There are many unique aspects of Navy air missions that lead to the differentiation between the design and performance of ship and shore-based aircraft. The major aspects are discussed from which essentially all Navy aircraft design requirements derive. (1) Navy aircraft operate from carriers at sea imposes a broad spectrum of physical conditions, constraints, and requirements ranging from the harsh sea environment, the space limitations of a carrier, takeoff and landing requirements as well as for endurance at long distances from the carrier. (2) Because the carrier and its airwing are intended to be capable of responding to a broad range of contingencies, mission flexibility is essential (maximum weapon carriage, rapid reconfiguration, multiple mission capability). (3) The embarked aircraft provides the long range defense of the battle group against air, surface and subsurface launched antiship missiles. (4) The carrier and its aircraft must operate independently and outside of normal supply lines. Taking into account these aspects, the use of composite materials in the design and performance of naval aircraft is outlined, also listing advantages and disadvantages.

  8. New Horizons Launch Contingency Effort

    NASA Astrophysics Data System (ADS)

    Chang, Yale; Lear, Matthew H.; McGrath, Brian E.; Heyler, Gene A.; Takashima, Naruhisa; Owings, W. Donald

    2007-01-01

    On 19 January 2006 at 2:00 PM EST, the NASA New Horizons spacecraft (SC) was launched from the Cape Canaveral Air Force Station (CCAFS), FL, onboard an Atlas V 551/Centaur/STAR™ 48B launch vehicle (LV) on a mission to explore the Pluto Charon planetary system and possibly other Kuiper Belt Objects. It carried a single Radioisotope Thermoelectric Generator (RTG). As part of the joint NASA/US Department of Energy (DOE) safety effort, contingency plans were prepared to address the unlikely events of launch accidents leading to a near-pad impact, a suborbital reentry, an orbital reentry, or a heliocentric orbit. As the implementing organization. The Johns Hopkins University Applied Physics Laboratory (JHU/APL) had expanded roles in the New Horizons launch contingency effort over those for the Cassini mission and Mars Exploration Rovers missions. The expanded tasks included participation in the Radiological Control Center (RADCC) at the Kennedy Space Center (KSC), preparation of contingency plans, coordination of space tracking assets, improved aerodynamics characterization of the RTG's 18 General Purpose Heat Source (GPHS) modules, and development of spacecraft and RTG reentry breakup analysis tools. Other JHU/APL tasks were prediction of the Earth impact footprints (ElFs) for the GPHS modules released during the atmospheric reentry (for purposes of notification and recovery), prediction of the time of SC reentry from a potential orbital decay, pre-launch dissemination of ballistic coefficients of various possible reentry configurations, and launch support of an Emergency Operations Center (EOC) on the JHU/APL campus. For the New Horizons launch, JHU/APL personnel at the RADCC and at the EOC were ready to implement any real-time launch contingency activities. A successful New Horizons launch and interplanetary injection precluded any further contingency actions. The New Horizons launch contingency was an interagency effort by several organizations. This paper

  9. Pilots' use of a traffic alert and collision-avoidance system (TCAS 2) in simulated air carrier operations. Volume 1: Methodology, summary and conclusions

    NASA Technical Reports Server (NTRS)

    Chappell, Sheryl L.; Billings, Charles E.; Scott, Barry C.; Tuttell, Robert J.; Olsen, M. Christine; Kozon, Thomas E.

    1989-01-01

    Pilots' use of and responses to a traffic alert and collision-avoidance system (TCAS 2) in simulated air carrier line operations are described in Volume 1. TCAS 2 monitors the positions of nearby aircraft by means of transponder interrogation, and it commands a climb or descent when conflicting aircraft are projected to reach an unsafe closest point-of-approach within 20 to 25 seconds. A different level of information about the location of other air traffic was presented to each of three groups of flight crews during their execution of eight simulated air carrier flights. A fourth group of pilots flew the same segments without TCAS 2 equipment. Traffic conflicts were generated at intervals during the flights; many of the conflict aircraft were visible to the flight crews. The TCAS equipment successfully ameliorated the seriousness of all conflicts; three of four non-TCAS crews had hazardous encounters. Response times to TCAS maneuver commands did not differ as a function of the amount of information provided, nor did response accuracy. Differences in flight experience did not appear to contribute to the small performance differences observed. Pilots used the displays of conflicting traffic to maneuver to avoid unseen traffic before maneuver advisories were issued by the TCAS equipment. The results indicate: (1) that pilots utilize TCAS effectively within the response times allocated by the TCAS logic, and (2) that TCAS 2 is an effective collision avoidance device. Volume II contains the appendices referenced in Volume I, providing details of the experiment and the results, and the text of two reports written in support of the program.

  10. Pilots' use of a traffic alert and collision-avoidance system (TCAS 2) in simulated air carrier operations. Volume 2: Appendices

    NASA Technical Reports Server (NTRS)

    Chappell, Sheryl L.; Billings, Charles E.; Scott, Barry C.; Tuttell, Robert J.; Olsen, M. Christine; Kozon, Thomas E.

    1989-01-01

    Pilots' use of and responses to a traffic alert and collision-avoidance system (TCAS 2) in simulated air carrier line operations are discribed in Volume 1. TCAS 2 monitors the positions of nearby aircraft by means of transponder interrogation, and it commands a climb or descent which conflicting aircraft are projected to reach an unsafe closest point-of-approach within 20 to 25 seconds. A different level of information about the location of other air traffic was presented to each of three groups of flight crews during their execution of eight simulated air carrier flights. A fourth group of pilots flew the same segments without TCAS 2 equipment. Traffic conflicts were generated at intervals during the flights; many of the conflict aircraft were visible to the flight crews. The TCAS equipment successfully ameliorated the seriousness of all conflicts; three of four non-TCAS crews had hazardous encounters. Response times to TCAS maneuver commands did not differ as a function of the amount of information provided, nor did response accuracy. Differences in flight experience did not appear to contribute to the small performance differences observed. Pilots used the displays of conflicting traffic to maneuver to avoid unseen traffic before maneuver advisories were issued by the TCAS equipment. The results indicate: (1) that pilots utilize TCAS effectively within the response times allocated by the TCAS logic, and (2) that TCAS 2 is an effective collision avoidance device. Volume 2 contains the appendices referenced in Volume 1, providing details of the experiment and the results, and the text of two reports written in support of the program.

  11. Air

    MedlinePlus

    ... do to protect yourself from dirty air . Indoor air pollution and outdoor air pollution Air can be polluted indoors and it can ... this chart to see what things cause indoor air pollution and what things cause outdoor air pollution! Indoor ...

  12. Final Environmental Assessment for the Deactivation and Turnover of Titan Space Launch Vehicle Capability at Cape Canaveral Air Force Station, Florida

    DTIC Science & Technology

    2005-05-01

    Management, Section 7.1.2. Although not anticipated, removal of scrub jay habitat would require compensation at a rate of 4:1 (four acres restored for...bladderwort (Utricularia spp.), common arrowhead (Sagittaria lancifolia), common cattail (Typha latifolia), common duckweed (Lemna minor), Curtis’ Reedgrass...space launch activities (in combination with nearby PAFB) stimulated economic growth in this region. This dominant economic force generates well over

  13. First geosynchronous weather satellite prepared for launch

    NASA Technical Reports Server (NTRS)

    1974-01-01

    The Synchronous Meteorological Satellite (SMS), which is scheduled for launch 16 May 1974 is described along with the data transmission system. The Carrier Balloon System is discussed. The primary type of data to be obtained in conjunction with SMS and Nimbus F are meteorological, oceanographic, seismic, and tsunami information. The Space Environment Monitoring System is also described.

  14. Fifth FLTSATCOM to be launched

    NASA Technical Reports Server (NTRS)

    1981-01-01

    Launch of the FLTSATOOM-E, into an elliptical orbit by the Atlas Centaur launch vehicle is announced. The launch and relevant launch operations are described. A chart of the launch sequence for FLTSATCOM-E communication satellite is given.

  15. 48 CFR 47.403-1 - Availability and unavailability of U.S.-flag air carrier service.

    Code of Federal Regulations, 2011 CFR

    2011-10-01

    ... the time in a travel status, including delay at origin and accelerated arrival at destination, by at... gateway airport in the United States would extend time in a travel status by at least 6 hours more than... the time in a travel status by at least 6 hours more than travel by a foreign-flag air...

  16. 48 CFR 47.403-1 - Availability and unavailability of U.S.-flag air carrier service.

    Code of Federal Regulations, 2013 CFR

    2013-10-01

    ... the time in a travel status, including delay at origin and accelerated arrival at destination, by at... gateway airport in the United States would extend time in a travel status by at least 6 hours more than... the time in a travel status by at least 6 hours more than travel by a foreign-flag air...

  17. 75 FR 8178 - Application of Rugby Aviation LLC D/B/A Northwest Sky Ferry for Commuter Air Carrier Authority

    Federal Register 2010, 2011, 2012, 2013, 2014

    2010-02-23

    ... From the Federal Register Online via the Government Publishing Office DEPARTMENT OF TRANSPORTATION Office of the Secretary Application of Rugby Aviation LLC D/B/A Northwest Sky Ferry for Commuter Air... persons to show cause why it should not issue an order finding Rugby ] Aviation, LLC d/b/a Northwest...

  18. Inflatable Launch and Recovery System

    DTIC Science & Technology

    2014-07-31

    and air line connections. Inflatable arch shaped tubes and spacer fabric form the ramp structure from which the tow body can be launched and...also includes power electronics and software controllers. [0015] Multiple, inflatable, arch shaped tubes and spacer fabric form the ramp structure...this manner maintain their shapes when inflated. The panel 36 can be fabricated of woven spacer fabrics, also known as drop stitch fabrics. Such

  19. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC DETAILS OF POWER OPERATED LOUVERS. Sheet 29-54 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  20. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC SECTIONS & DETAILS AT FLOOR 3 NORTH WALL WINDOWS. Sheet 29-53 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  1. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC TRANSVERSE SECTION AT LIEF ROOM AND VISITOR’S GALLERY VESTIBULE. Sheet 29-50 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  2. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC SECTIONS & DETAILS AT NORTH EXTERIOR WALL OF FIRING ROOMS. Sheet 29-52 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  3. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC FLOOR 3, LEVEL 38’-0”, AREA “P”. Sheet 29-39 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  4. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC FLOOR 3, LEVEL 38’-0”, AREA “R”. Sheet 29-42 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  5. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC FLOOR 4, LEVEL 57’-0”, AREA “P”. Sheet 29-41 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  6. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 75M05760, KSC-Launch Support Equipment Engineering Division, January 1967. GENERAL ARRANGEMENT. Sheet 1 of 4 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  7. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC ELEVATIONS. Sheet 29-44 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  8. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC FLOOR 3, LEVEL 38’-0”, AREA “R”. Sheet 29-40 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  9. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. LCC TRANSVERSE SECTIONS AA & BB. Sheet 29-45 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  10. 51. VIEW OF EAST SIDE OF LAUNCH DECK; MAIN PANEL ...

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

    51. VIEW OF EAST SIDE OF LAUNCH DECK; MAIN PANEL CONTAINS UMBILICAL MAST POWER CONNECTORS; RAIL AND FIRE SUPPRESSION NOZZLES IN FOREGROUND; TELEVISION CAMERA AND CAMERA TOWER IN BACKGROUND - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  11. 50. SOUTHEAST CORNER OF LAUNCH PAD. RAIL AND BUMPER IN ...

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

    50. SOUTHEAST CORNER OF LAUNCH PAD. RAIL AND BUMPER IN CENTER OF PHOTOGRAPH; FIRE SUPPRESSION NOZZLES ON RIGHT; THRUST SECTION HEATER DUCT ON LEFT. COMMUNICATIONS HOOKUP FOR THE MST LEFT OF DUCT. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  12. 49. VIEW OF EAST SIDE OF LAUNCH PAD. THRUST SECTION ...

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

    49. VIEW OF EAST SIDE OF LAUNCH PAD. THRUST SECTION HEATER AND DUCTS ON RIGHT; UMBILICAL MAST POWER CONNECTORS ON LEFT; RAIL SYSTEM AND FIRE SUPPRESSION NOZZLES IN FOREGROUND. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  13. 85. VIEW FROM SOUTHWEST OF FUEL PIPELINE TO LAUNCH DECK. ...

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

    85. VIEW FROM SOUTHWEST OF FUEL PIPELINE TO LAUNCH DECK. SOUTHEAST CORNER OF SKID 2 VISIBLE ON LEFT. DOORS OF ROOMS ON SOUTHWEST SIDE OF LSB (BLDG. 770) VISIBLE IN CENTER OF PHOTO. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 West, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  14. Photocopy of drawing. LAUNCH COMPLEX 39, LCC, SPACE AND WEIGHT ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, LCC, SPACE AND WEIGHT ALLOCATION. NASA, John F. Kennedy Space Center, Florida. Drawing 79K07549, Planning Research Corporation, August, 1977. FLOOR PLAN, FLOOR 3, AREA “P”. Sheet 15 of 24 - Cape Canaveral Air Force Station, Launch Complex 39, Launch Control Center, LCC Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  15. 2. VIEW OF WEST FACE OF LAUNCH OPERATIONS BUILDING. BUNKER ...

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

    2. VIEW OF WEST FACE OF LAUNCH OPERATIONS BUILDING. BUNKER PERISCOPE VISIBLE ON NORTH END OF ROOF. ESCAPE TUNNEL AND CABLE SHED VISIBLE ON NORTH FACE. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  16. 14. VIEW OF MST, FACING SOUTHEAST, AND LAUNCH PAD TAKEN ...

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

    14. VIEW OF MST, FACING SOUTHEAST, AND LAUNCH PAD TAKEN FROM NORTHEAST PHOTO TOWER WITH WINDOW OPEN. FEATURES LEFT TO RIGHT: SOUTH TELEVISION CAMERA TOWER, SOUTHWEST PHOTO TOWER, LAUNCHER, UMBILICAL MAST, MST, AND OXIDIZER APRON. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  17. IRIS Launch Animation

    NASA Video Gallery

    This animation demonstrates the launch and deployment of NASA's Interface Region Imaging Spectrograph (IRIS) mission satellite via a Pegasus rocket. The launch is scheduled for June 26, 2013 from V...

  18. Shuttle Era: Launch Directors

    NASA Video Gallery

    A space shuttle launch director is the leader of the complex choreography that goes into a shuttle liftoff. Ten people have served as shuttle launch directors, making the final decision whether the...

  19. Space Launch System Animation

    NASA Video Gallery

    NASA is ready to move forward with the development of the Space Launch System -- an advanced heavy-lift launch vehicle that will provide an entirely new national capability for human exploration be...

  20. Carrier Diagnosis

    MedlinePlus

    ... and Women with Hemophilia Inheritance of Hemophilia Definitions & Terminology Bleeding Symptoms Carrier Diagnosis When to Test for ... and Women with Hemophilia Inheritance of Hemophilia Definitions & Terminology Bleeding Symptoms Carrier Diagnosis When to Test for ...

  1. Launch Summary for 1979

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1980-01-01

    Spacecraft launching for 1979 are identified and listed under the categories of (1) sounding rockets, and (2) artificial Earth satellites and space probes. The sounding rockets section includes a listing of the experiments, index of launch sites and tables of the meanings and codes used in the launch listing.

  2. National Launch System comparative economic analysis

    NASA Technical Reports Server (NTRS)

    Prince, A.

    1992-01-01

    Results are presented from an analysis of economic benefits (or losses), in the form of the life cycle cost savings, resulting from the development of the National Launch System (NLS) family of launch vehicles. The analysis was carried out by comparing various NLS-based architectures with the current Shuttle/Titan IV fleet. The basic methodology behind this NLS analysis was to develop a set of annual payload requirements for the Space Station Freedom and LEO, to design launch vehicle architectures around these requirements, and to perform life-cycle cost analyses on all of the architectures. A SEI requirement was included. Launch failure costs were estimated and combined with the relative reliability assumptions to measure the effects of losses. Based on the analysis, a Shuttle/NLS architecture evolving into a pressurized-logistics-carrier/NLS architecture appears to offer the best long-term cost benefit.

  3. 5. TETHERED MINUTEMAN MISSILE LAUNCH, TEST AREA 1100. Original is ...

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

    5. TETHERED MINUTEMAN MISSILE LAUNCH, TEST AREA 1-100. Original is a color print. - Edwards Air Force Base, Air Force Rocket Propulsion Laboratory, Leuhman Ridge near Highways 58 & 395, Boron, Kern County, CA

  4. Launch summary for 1980

    NASA Technical Reports Server (NTRS)

    Vostreys, R. W.

    1981-01-01

    Sounding rockets, artificial Earth satellites, and space probes launched betweeen January 1 and December 31, 1980 are listed. Data tabulated for the rocket launchings show launching site, instruments carried, date of launch, agency rocket identification, sponsoring country, experiment discipline, peak altitude, and the experimenter or institution responsible. Tables for satellites and space probes show COSPAR designation, spacecraft name, country, launch date, epoch date, orbit type, apoapsis, periapsis and inclination period. The functions and responsibilities of the World Data Center and the areas of scientific interest at the seven subcenters are defined. An alphabetical listing of experimenters using the sounding rockets is also provided.

  5. Electron launching voltage monitor

    DOEpatents

    Mendel, Clifford W.; Savage, Mark E.

    1992-01-01

    An electron launching voltage monitor measures MITL voltage using a relationship between anode electric field and electron current launched from a cathode-mounted perturbation. An electron launching probe extends through and is spaced from the edge of an opening in a first MITL conductor, one end of the launching probe being in the gap between the MITL conductor, the other end being adjacent a first side of the first conductor away from the second conductor. A housing surrounds the launching probe and electrically connects the first side of the first conductor to the other end of the launching probe. A detector detects the current passing through the housing to the launching probe, the detected current being representative of the voltage between the conductors.

  6. Electron launching voltage monitor

    DOEpatents

    Mendel, C.W.; Savage, M.E.

    1992-03-17

    An electron launching voltage monitor measures MITL voltage using a relationship between anode electric field and electron current launched from a cathode-mounted perturbation. An electron launching probe extends through and is spaced from the edge of an opening in a first MITL conductor, one end of the launching probe being in the gap between the MITL conductor, the other end being adjacent a first side of the first conductor away from the second conductor. A housing surrounds the launching probe and electrically connects the first side of the first conductor to the other end of the launching probe. A detector detects the current passing through the housing to the launching probe, the detected current being representative of the voltage between the conductors. 5 figs.

  7. Preliminary Drag and Heat-transfer Data Obtained from Air-launched Cone-cylinder Test Vehicle over Mach Number Range from 1.5 to 5.18

    NASA Technical Reports Server (NTRS)

    Messing, Wesley E; Rabb, Leonard; Disher, John H

    1953-01-01

    An air-launched cone-cylinder test vehicle designed to obtain data at Mach numbers above 4.0 was rocket boosted from a release Mach number of 5.18. The vehicle was launched at an altitude of 35,000 feet and reached peak velocity of 5150 feet per second at 28,500 feet. The total-drag coefficient (based on maximum cross-sectional area) decreased gradually from 0.31 at a Mach number of 1.75 to 0.145 at a Mach number of 5.18, while the Reynold's number (based on body length) increased from 31 x 10 to the 6th power to 107 x 10 to the 6th power. The skin friction coefficients, in general, were slightly lower than Van Driest's theoretical values for similar wall-temperature conditions. Convective heat-transfer coefficients were obtained from a single skin-thermocouple measurement. The maximum wall temperature recorded was 1240 degrees r.

  8. Proposal of New Triggered Lightning Launch Commit Criteria for Japan's Safety Rocket Launch

    NASA Astrophysics Data System (ADS)

    Saito, Yasuhiro; Saito, Toshiya; Okita, Koichi

    2013-09-01

    Triggered lightning for rocket launch can cause the failure.The current Japanese criteria to postpone the launch opportunity is the thickness of cloud 1.8km with 0 -20 degrees Celsius. Of all H2A launches during these ten years, slipping launches have occurred over half of its flights. So, we have initiated a research on Triggered Lightning Launch Commit Criteria, two years ago.We present the overall activities with the observation campaign (RAIJIN*) in Feb/2012 and Jan-Feb/2013, by means of air-born field mill with airplane, X-band dual polarization radar, ground based field mill and Videosonde. Also, the analytical results and proposal of the new criteria will be shown.*) Raijin is originally a name for Thunder god in Japanese and here it stands for Rocket launch Atmospheric electricity Investigation by Jaxa IN cooperation with academia.

  9. Aqua 10 Years After Launch

    NASA Technical Reports Server (NTRS)

    Parkinson, Claire L.

    2013-01-01

    A little over ten years ago, in the early morning hours of May 4, 2002, crowds of spectators stood anxiously watching as the Delta II rocket carrying NASA's Aqua spacecraft lifted off from its launch pad at Vandenberg Air Force Base in California at 2:55 a.m. The rocket quickly went through a low-lying cloud cover, after which the main portion of the rocket fell to the waters below and the rockets second stage proceeded to carry Aqua south across the Pacific, onward over Antarctica, and north to Africa, where the spacecraft separated from the rocket 59.5 minutes after launch. Then, 12.5 minutes later, the solar array unfurled over Europe, and Aqua was on its way in the first of what by now have become over 50,000 successful orbits of the Earth.

  10. Environmental Assessment for the Operation and Launch of the Falcon 1 and Falcon 9 Space Vehicles at Cape Canaveral Air Force Station Florida

    DTIC Science & Technology

    2007-11-01

    particulate matter) and other common air pollutants (nitrogen oxides (NOx), carbon monoxide (CO) and sulfur dioxide (S02)). Orbital Debris : Lower...Upper stages going to higher orbits are not subject to controlled reentry and contribute to orbital debris . Their location would be tracked to permit...from orbital debris is not expected to have a significant impa.ct on the environment. 3 Hazardous Waste/Hazardous Materials: Applicable federal

  11. Space Launch Flight Termination System initial development

    NASA Astrophysics Data System (ADS)

    Ratkevich, B.; Brierley, S.; Lupia, D.; Leiker, T.

    This paper describes the studies, capabilities and challenges in initial development of a new digital encrypted termination system for space launch vehicles. This system is called the Space Launch Flight Termination System (SLFTS). Development of SLFTS is required to address an obsolescence issue and to improve the security of flight termination systems presently in use on the nation's space launch vehicles. SLFTS development was implemented in a four phase approach with the goal of producing a high secure, cost effective flight termination system for United Launch Alliance (ULA) and the United States Air Force (USAF) Evolved Expendable Launch Vehicle (EELV). These detailed study phases developed the requirements, design and implementation approach for a new high secure flight termination system. Studies led to a cost effective approach to replace the High Alphabet Command Receiver Decoders (HA-CRD) presently used on the EELV (Delta-IV & Atlas-V), with a common SLFTS unit. SLFTS is the next generation flight termination system for space launch vehicles, providing an assured high secure command destruct system for launch vehicles in flight. The unique capabilities and challenges to develop this technology for space launch use will be addressed in this paper in detail. This paper summarizes the current development status, design and capabilities of SLFTS for EELV.

  12. Magnetic Launch Assist System Demonstration Test

    NASA Technical Reports Server (NTRS)

    2001-01-01

    Engineers at the Marshall Space Flight Center (MSFC) have been testing Magnetic Launch Assist Systems, formerly known as Magnetic Levitation (MagLev) technologies. To launch spacecraft into orbit, a Magnetic Launch Assist system would use magnetic fields to levitate and accelerate a vehicle along a track at a very high speed. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, the launch-assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This photograph shows a subscale model of an airplane running on the experimental track at MSFC during the demonstration test. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide, and about 1.5- feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  13. Launch Services Safety Overview

    NASA Technical Reports Server (NTRS)

    Loftin, Charles E.

    2008-01-01

    NASA/KSC Launch Services Division Safety (SA-D) services include: (1) Assessing the safety of the launch vehicle (2) Assessing the safety of NASA ELV spacecraft (S/C) / launch vehicle (LV) interfaces (3) Assessing the safety of spacecraft processing to ensure resource protection of: - KSC facilities - KSC VAFB facilities - KSC controlled property - Other NASA assets (4) NASA personnel safety (5) Interfacing with payload organizations to review spacecraft for adequate safety implementation and compliance for integrated activities (6) Assisting in the integration of safety activities between the payload, launch vehicle, and processing facilities

  14. GPM: Waiting for Launch

    NASA Video Gallery

    The Global Precipitation Measurement mission's Core Observatory is poised for launch from the Japan Aerospace Exploration Agency's Tanegashima Space Center, scheduled for the afternoon of Feb. 27, ...

  15. Expedition 28 Launch

    NASA Video Gallery

    Three new Expedition 28 flight engineers -- NASA astronaut Mike Fossum, Russian cosmonaut Sergei Volkov and Japan Aerospace Exploration Agency astronaut Satoshi Furukawa -- launch from the Baikonur...

  16. Kestrel balloon launch system

    SciTech Connect

    Newman, M.J.

    1991-10-01

    Kestrel is a high-altitude, Helium-gas-filled-balloon system used to launch scientific payloads in winds up to 20 knots, from small platforms or ships, anywhere over land or water, with a minimal crew and be able to hold in standby conditions. Its major components consist of two balloons (a tow balloon and a main balloon), the main deployment system, helium measurement system, a parachute recovery unit, and the scientific payload package. The main scope of the launch system was to eliminate the problems of being dependent of launching on long airfield runways, low wind conditions, and long launch preparation time. These objectives were clearly met with Kestrel 3.

  17. Saturn IB Launch

    NASA Technical Reports Server (NTRS)

    1973-01-01

    The Saturn IB launch vehicle lifting off from Launch Complex 39B at 9:01 a.m. EST. The Skylab 4 astronauts Gerald P. Carr, Dr. Edward G. Gibson, and William R. Pogue, were onboard for the third and final mission to the orbiting space station.

  18. Saturn IB Launch Summary

    NASA Technical Reports Server (NTRS)

    1973-01-01

    This chart provides a launch summary of the Saturn IB launch vehicle as of 1973. Developed by the Marshall Space Flight Center (MSFC) as an interim vehicle in MSFC's 'building block' approach to the Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine the larger boosters and the Apollo spacecraft capabilities required for the marned lunar missions.

  19. Launch Collision Probability

    NASA Technical Reports Server (NTRS)

    Bollenbacher, Gary; Guptill, James D.

    1999-01-01

    This report analyzes the probability of a launch vehicle colliding with one of the nearly 10,000 tracked objects orbiting the Earth, given that an object on a near-collision course with the launch vehicle has been identified. Knowledge of the probability of collision throughout the launch window can be used to avoid launching at times when the probability of collision is unacceptably high. The analysis in this report assumes that the positions of the orbiting objects and the launch vehicle can be predicted as a function of time and therefore that any tracked object which comes close to the launch vehicle can be identified. The analysis further assumes that the position uncertainty of the launch vehicle and the approaching space object can be described with position covariance matrices. With these and some additional simplifying assumptions, a closed-form solution is developed using two approaches. The solution shows that the probability of collision is a function of position uncertainties, the size of the two potentially colliding objects, and the nominal separation distance at the point of closest approach. ne impact of the simplifying assumptions on the accuracy of the final result is assessed and the application of the results to the Cassini mission, launched in October 1997, is described. Other factors that affect the probability of collision are also discussed. Finally, the report offers alternative approaches that can be used to evaluate the probability of collision.

  20. 2011 Mars Science Laboratory Trajectory Reconstruction and Performance from Launch Through Landing

    NASA Technical Reports Server (NTRS)

    Abilleira, Fernando

    2013-01-01

    The Mars Science Laboratory (MSL) mission successfully launched on an Atlas V 541 Expendable Evolved Launch Vehicle (EELV) from the Eastern Test Range (ETR) at Cape Canaveral Air Force Station (CCAFS) in Florida at 15:02:00 UTC on November 26th, 2011. At 15:52:06 UTC, six minutes after the MSL spacecraft separated from the Centaur upper stage, the spacecraft transmitter was turned on and in less than 20 s spacecraft carrier lock was achieved at the Universal Space Network (USN) Dongara tracking station located in Western Australia. MSL, carrying the most sophisticated rover ever sent to Mars, entered the Martian atmosphere at 05:10:46 SpaceCraft Event Time (SCET) UTC, and landed inside Gale Crater at 05:17:57 SCET UTC on August 6th, 2012. Confirmation of nominal landing was received at the Deep Space Network (DSN) Canberra tracking station via the Mars Odyssey relay spacecraft at 05:31:45 Earth Received Time (ERT) UTC. This paper summarizes in detail the actual vs. predicted trajectory performance in terms of launch vehicle events, launch vehicle injection performance, actual DSN/USN spacecraft lockup, trajectory correction maneuver performance, Entry, Descent, and Landing events, and overall trajectory and geometry characteristics.

  1. Modeling Space Launch Process Delays to Improve Space Vehicle Acquisition Timelines

    DTIC Science & Technology

    2013-06-01

    evolution of the space launch process over the past 15 years is the Space Launch Vehicle Broad Area Review ( SLV BAR). The SLV BAR, led by Gen. Larry...to 9 in 51 launches, a 100% increase (US Air Force, 1999). The SLV BAR began a period of intense scrutiny related to launch vehicle mission

  2. STS-114: Discovery Launch Readiness Press Conference

    NASA Technical Reports Server (NTRS)

    2005-01-01

    Michael Griffin, NASA Administrator; Wayne Hale, Space Shuttle Deputy Program Manager; Mike Wetmore, Director of Shuttle Processing; and 1st Lieutenant Mindy Chavez, Launch Weather Officer-United States Air Force 45th Weather Squadron are in attendance for this STS-114 Discovery launch readiness press conference. The discussion begins with Wayne Hale bringing to the table a low level sensor device for everyone to view. He talks in detail about all of the extensive tests that were performed on these sensors and the completion of these ambient tests. Chavez presents her weather forecast for the launch day of July 26th 2005. Michael Griffin and Wayne Hale answer questions from the news media pertaining to the sensors and launch readiness. The video ends with footage of Pilot Jim Kelly and Commander Eileen Collins conducting test flights in a Shuttle Training Aircraft (STA) that simulates Space Shuttle landing.

  3. The second Ariane launch complex (ELA-2)

    NASA Astrophysics Data System (ADS)

    Dana, C.

    1985-05-01

    ELA-2 will, in 1986, become the primary Ariane launch complex, with ELA-1 being relegated to back-up roles. Both Ariane 3 and Ariane 4 vehicles can lift-off from ELA 2, but not ELA-1. In the Preparation Zone, spacecraft, launch vehicles and propellant are unloaded from shipment, stored and assembled in a one month process. The assembly building is equipped with stored ice to ensure continued air conditioning and cooling of electronic equipment and stored fuels in case of power outage. The launch gantry to which the Ariane is transported by rail is equipped with blast channels to redirect the rocket exhausts. The control center has remote cameras and sensors for monitoring launch pad activities and an underground, concrete bunker for the safety of up to 200 personnel.

  4. External tank aft cargo carrier

    NASA Technical Reports Server (NTRS)

    Mobley, T. B.

    1984-01-01

    The External Tank (ET) Aft Cargo Carrier (ACC) is a low cost, low risk augmentation of the Space Transportation System (STS). It almost doubles the cargo volume of the STS while minimally impacting other STS elements (orbiter, ET and solid rocket boosters SRBs, launch facilities and STS operations. In addition to increasing the potential volume of cargo carried on a Shuttle launch, the ACC provides the following additional benefits: (1) Increased STS competitiveness for payloads; (2) Increased cargo manifest flexibility; (3) Increased spacecraft design options; (4) Alternate manifesting for special payloads; and (5) Future space platform/station design options.

  5. STS-51 Launch

    NASA Technical Reports Server (NTRS)

    1993-01-01

    The Space Shuttle Discovery takes off from Launch Pad 39B at the Kennedy Space Center, Florida, to begin Mission STS-51 on 12 September 1993. The 57th shuttle mission began at 7:45 a.m. EDT, and lasted 9 days, 20 hours, 11 minutes, 11 seconds, while traveling a total distance of 4,106,411 miles. The Advanced Communications Technology Satellite (ACTS) was one of the projects deployed. This satellite serves as a test bed for advanced experimental communications satellite concepts and technology. Another payload on this mission was the Orbiting Retrievable Far and Extreme Ultraviolet Spectrometer (ORFEUS) telescope mounted on the Shuttle Pallet Satellite (SPAS) payload carrier. ORFEUS was designed to investigate very hot and very cold matter in the universe. Space Shuttles are the main element of America's Space Transportation System and are used for space research and other space applications. The shuttles are the first vehicles capable of being launched into space and returning to Earth on a routine basis. Space Shuttles are used as orbiting laboratories in which scientists and mission specialists conduct a wide variety of scientific experiments. Crews aboard shuttles place satellites in orbit, rendezvous with satellites to carry out repair missions and return them to space, and retrieve satellites and return them to Earth for refurbishment and reuse. Space Shuttles are true aerospace vehicles. They leave Earth and its atmosphere under rocket power provided by three liquid-propellant main engines with two solid-propellant boosters attached plus an external liquid-fuel tank. After their orbital missions, they streak back through the atmosphere and land like airplanes. The returning shuttles, however, land like gliders, without power and on runways. Other rockets can place heavy payloads into orbit, but, they can only be used once. Space Shuttles are designed to be continually reused. When Space Shuttles are used to transport complete scientific laboratories into

  6. Payload Isolation System for Launch Vehicles

    DTIC Science & Technology

    1997-03-01

    Payload Isolation System for Launch Vehicles Paul S. Wilke, Conor D. Johnson CSA Engineering Palo Alto, CA Eugene R. Fosness Air Force Phillips ... Laboratory , PL/VTVD Kirkland AFB, NM Spie Smart Structures and Materials San Diego, CA March 1997 Copyright 1997 Society of Photo-Optical Instrumentation

  7. Launch of Juno!

    NASA Video Gallery

    An Atlas V rocket lofted the Juno spacecraft toward Jupiter from Space Launch Complex-41. The 4-ton Juno spacecraft will take five years to reach Jupiter on a mission to study its structure and dec...

  8. IRVE 3 Launch

    NASA Video Gallery

    The Inflatable Reentry Vehicle Experiment, or IRVE-3, launched on July 23, 2012, from NASA's Wallops Flight Facility. The purpose of the IRVE-3 test was to show that a space capsule can use an infl...

  9. Hi-C Launch

    NASA Video Gallery

    The High resolution Coronal Imager (Hi-C) was launched on a NASA Black Brant IX two-stage rocket from White Sands Missile Range in New Mexico July 11, 2012. The experiment reached a maximum velocit...

  10. GPM Launch Coverage

    NASA Video Gallery

    A Japanese H-IIA rocket with the NASA-Japan Aerospace Exploration Agency (JAXA) Global Precipitation Measurement (GPM) Core Observatory aboard, launched from the Tanegashima Space Center in Japan o...

  11. NASA Now: Glory Launch

    NASA Video Gallery

    In this episode of NASA Now, Dr. Hal Maring joins us to explain why the upcoming launch of the Glory satellite is so important to further our understanding of climate change. He also will speak on ...

  12. Genomic Data Commons launches

    Cancer.gov

    The Genomic Data Commons (GDC), a unified data system that promotes sharing of genomic and clinical data between researchers, launched today with a visit from Vice President Joe Biden to the operations center at the University of Chicago.

  13. Anchor Trial Launch

    Cancer.gov

    NCI has launched a multicenter phase III clinical trial called the ANCHOR Study -- Anal Cancer HSIL (High-grade Squamous Intraepithelial Lesion) Outcomes Research Study -- to determine if treatment of HSIL in HIV-infected individuals can prevent anal canc

  14. First Accessible Boat Launch

    EPA Pesticide Factsheets

    This is a story about how the Northwest Indiana urban waters partnership location supported the process to create and open the first handicap accessible canoe and kayak launch in the state of Indiana.

  15. Experiences with Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Dumbacher, Daniel L.

    2006-01-01

    The presentation "NASA Experience with Launch Vehicles" is a compilation of Mr. Dumbacher's career experiences with the Space Shuttle Program, the Delta - Clipper Experimental flight test project, the X-33 demonstrator project, and recent experiences with the Orbital Spaceplane Program agd the current NASA effort on Exploration Launch Systems. Mr. Dumbacher will discuss his personal experiences and provide lessons learned from each program. The accounts provided by Mr. Dumbacher are his own and do not necessarily represent the official NASA position.

  16. STS-64 launch view

    NASA Technical Reports Server (NTRS)

    1994-01-01

    Passing through some of the trailer clouds of an overcast sky which temporarily postponed its launch, the Space Shuttle Discovery heads for its 19th Earth orbital flight. Several kilometers away, astronaut John H. Casper, Jr., who took this picture, was piloting the Shuttle Training Aircraft (STA) from which the launch and landing area weather was being monitored. Onboard Discovery were astronauts Richard N. Richards, L. Blaine Hammond, Jr., Mark C. Lee, Carl J. Meade, Susan J. Helms, and Jerry M. Linenger.

  17. Launch Vehicle Communications

    NASA Technical Reports Server (NTRS)

    Welch, Bryan; Greenfeld, Israel

    2005-01-01

    As the National Aeronautics and Space Administration's (NASA) planning for updated launch vehicle operations progresses, there is a need to consider improved methods. This study considers the use of phased array antennas mounted on launch vehicles and transmitting data to either NASA's Tracking and Data Relay Satellite System (TDRSS) satellites or to the commercial Iridium, Intelsat, or Inmarsat communications satellites. Different data rate requirements are analyzed to determine size and weight of resulting antennas.

  18. Electromagnetic Launch to Space

    NASA Astrophysics Data System (ADS)

    McNab, I. R.

    Many advances in electromagnetic (EM) propulsion technology have occurred in recent years. Linear motor technology for low-velocity and high-mass applications is being developed for naval catapults. Such technology could serve as the basis for a first-stage booster launch--as suggested by the US National Aeronautics and Space Administration (NASA) in the Maglifter concept. Using railguns, laboratory experiments have demonstrated launch velocities of 2-3 km/s and muzzle energies > 8 MJ. The extension of this technology to the muzzle velocities ( 7500 m/s) and energies ( 10 GJ) needed for the direct launch of payloads into orbit is very challenging but may not be impossible. For launch to orbit, even long launchers (> 1000 m) would need to operate at accelerations > 1000 G to reach the required velocities, so it would only be possible to launch rugged payloads, such as fuel, water, and materiel. Interest is being shown in such concepts by US, European, Russian, and Chinese researchers. An intermediate step proposed in France could be to launch payloads to sounding rocket altitudes for ionospheric research.

  19. 14 CFR 271.5 - Carrier revenues.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Carrier revenues. 271.5 Section 271.5 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS) ECONOMIC REGULATIONS GUIDELINES FOR SUBSIDIZING AIR CARRIERS PROVIDING ESSENTIAL AIR TRANSPORTATION § 271.5...

  20. 14 CFR 271.4 - Carrier costs.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Carrier costs. 271.4 Section 271.4 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS) ECONOMIC REGULATIONS GUIDELINES FOR SUBSIDIZING AIR CARRIERS PROVIDING ESSENTIAL AIR TRANSPORTATION § 271.4...

  1. 44. VIEW OF UMBILICAL MAST AND LAUNCH PAD FROM SOUTHWEST. ...

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

    44. VIEW OF UMBILICAL MAST AND LAUNCH PAD FROM SOUTHWEST. DOORS FOR THE UMBILICAL MAST TRENCH RAISED FOR MAINTENANCE POSITION OF 10 DEGREES. LAUNCHER IS RIGHT OF MAST; RAILS PARALLEL TO MAST. CONTROL PANELS LEFT TO RIGHT: ELECTRICAL PANEL, COMMUNICATIONS PANEL, AND MAST CONTROL PANEL. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  2. 70. VIEW OF FUEL APRON FROM EAST SIDE OF LAUNCH ...

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

    70. VIEW OF FUEL APRON FROM EAST SIDE OF LAUNCH PAD. ROCKET FUEL TANKS ON LEFT; GASEOUS NITROGEN AND HELIUM TANKS IN CENTER; AND A LARGE LIQUID NITROGEN TANK ON RIGHT. SKID 1 FOR GASEOUS NITROGEN TRANSFER AND SKID 5 FOR HELIUM TRANSFER IN THE CENTER RIGHT PORTION OF THE PHOTOGRAPH. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  3. Caribbean LNG project marks progress; LNG tanker launched

    SciTech Connect

    1997-10-20

    World LNG trade continues to expand as construction of a major LNG project in the Caribbean hits full stride this fall and another LNG carrier was launched earlier this year. Engineering is nearly complete and construction is nearing midway on Trinidad`s Atlantic LNG. In Japan, NKK Corp. launched another LNG tanker that employs the membrane-storage system. The 50-mile pipeline to move natural gas to the Atlantic LNG facility is also on track for completion by October 1998.

  4. Towed Twin-Fuselage Glider Launch System (CGI Animation Version 2)

    NASA Video Gallery

    The towed glider is an element of the novel rocket-launching concept of the Towed Glider Air-Launch System (TGALS). The TGALS demonstration’s goal is to provide proof-of-concept of a towed, airborn...

  5. GPM Core Observatory Launch Animation

    NASA Video Gallery

    This animation depicts the launch of the Global Precipitation Measurement (GPM) Core Observatory satellite from Tanegashima Space Center, Japan. The launch is currently scheduled for Feb. 27, 2014....

  6. 52. Interior of launch support building, hydraulic pumping unit at ...

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

    52. Interior of launch support building, hydraulic pumping unit at lower center, service disconnect at right, view towards south - Ellsworth Air Force Base, Delta Flight, Launch Facility, On County Road T512, south of Exit 116 off I-90, Interior, Jackson County, SD

  7. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 75M05770, Marion Power Shovel Company, February 1964. OPERATOR'S CAB ASSY. Sheet 1 of 1 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  8. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH BAY AREA, SOUTH ELEVATION. Sheet 14-20 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  9. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH & LOW BAY, SECTION A-A. Sheet 33-25 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  10. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH BAY AREA, TRAVERSE SECTION C-C. Sheet 14-26 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  11. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH BAY AREA, WEST ELEVATION. Sheet 14-17 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  12. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH BAY AREA, LONGINTUDINAL SECTION N-N. Sheet 14-33 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  13. Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA, John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October, 1963. VOLUME 14, HIGH BAY – ARCHITECTURAL, TITLE SHEET. Sheet 14-01 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  14. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH BAY AREA, NORTH ELEVATION. Sheet 14-18 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  15. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH BAY AREA, EAST ELEVATION. Sheet 14-19 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  16. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 75M05761, Marion Power Shovel Company, October 1963. CRAWLER TRUCK ASSEMBLY-FIELD WELDMENT SECTIONS & DETAILS. Sheet 4 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  17. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 75M05761, Marion Power Shovel Company, October 1963. CRAWLER TRUCK ASSEMBLY-PLAN VIEW. Sheet 2 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  18. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 75M05762, Marion Power Shovel Company, December 1964. CHASSIS STRUCTURE ASSEMBLY. Sheet 2 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  19. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH & LOW BAY, SECTION F-F. Sheet 33-30 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  20. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 75M05760, Marion Power Shovel Company, January 1965. GENERAL ARRANGEMENT. Sheet 3 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  1. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 75M05761, Marion Power Shovel Company, October 1963. CRAWLER TRUCK ASSEMBLY-SIDE VIEW. Sheet 3 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  2. 22. Photocopy of engineering drawing. MODIFICATION TO LAUNCH COMPLEX 17 ...

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

    22. Photocopy of engineering drawing. MODIFICATION TO LAUNCH COMPLEX 17 MOBILE SERVICE TOWER 'A'-MECHANICAL, PROPULSION DRIVE TRUCKS AND KEY PLAN, MARCH 1967. - Cape Canaveral Air Station, Launch Complex 17, Facility 28416, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

  3. 1. Launch facility, delta 6, approach road and gate, pole ...

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

    1. Launch facility, delta 6, approach road and gate, pole marking the hardened intersite cable system in right center, commercial power pole outside fence in left center, view towards south - Ellsworth Air Force Base, Delta Flight, Launch Facility D-6, 4 miles north of Badlands National Park Headquarters, 4.5 miles east of Jackson County line on county road, Interior, Jackson County, SD

  4. 51. Interior of launch support building, minuteman power processor at ...

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

    51. Interior of launch support building, minuteman power processor at lower left, power distribution panel at center, old diesel control panel at lower right, diesel battery at upper right, view towards west - Ellsworth Air Force Base, Delta Flight, Launch Facility, On County Road T512, south of Exit 116 off I-90, Interior, Jackson County, SD

  5. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 79K00088, John F. Kennedy Space Center, November 1969. SYS FUNCTIONAL DRAWING. Sheet 6 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  6. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 79K00081, John F. Kennedy Space Center, December 1969. SYS FUNCTIONAL DRAWING. Sheet 3 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  7. Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39, CRAWLER TRANSPORTER. NASA, John F. Kennedy Space Center, Florida. Drawing 79K00088, John F. Kennedy Space Center, November 1969. SYS FUNCTIONAL DRAWING. Sheet 5 - Cape Canaveral Air Force Station, Launch Complex 39, Crawler Transporters, Launcher Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  8. 28. Launch Control Center, view looking in from doorway. Thalheimer ...

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

    28. Launch Control Center, view looking in from doorway. Thalheimer - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  9. 10. Launch control center vents, view towards west. Lyon ...

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

    10. Launch control center vents, view towards west. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  10. 38. Shock isolator at right of Launch Control Center entrance. ...

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

    38. Shock isolator at right of Launch Control Center entrance. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  11. 30. Launch Control Center, view looking out. Thalheimer Whiteman ...

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

    30. Launch Control Center, view looking out. Thalheimer - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  12. 40. Launch Control Equipment Room, taken from entrance. Lyon ...

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

    40. Launch Control Equipment Room, taken from entrance. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  13. 43. Launch Control Equipment Room, generator and maintenance mannequin. Lyon ...

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

    43. Launch Control Equipment Room, generator and maintenance mannequin. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  14. 44. Launch Control Equipment Room, taken from rear of room. ...

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

    44. Launch Control Equipment Room, taken from rear of room. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  15. 42. Launch Control Equipment Room, rear of room. Lyon ...

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

    42. Launch Control Equipment Room, rear of room. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  16. 37. Shock isolator at left of Launch Control Center entrance. ...

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

    37. Shock isolator at left of Launch Control Center entrance. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  17. 35. Launch Control Center, ERCS panel at left of commander's ...

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

    35. Launch Control Center, ERCS panel at left of commander's console. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  18. 27. Launch Control Center, blast door at left, view from ...

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

    27. Launch Control Center, blast door at left, view from tunnel junction. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  19. 39. Launch Control Equipment Room, seen from tunnel junction. Lyon ...

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

    39. Launch Control Equipment Room, seen from tunnel junction. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  20. 31. Launch Control Center, deputy commander's console. Lyon Whiteman ...

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

    31. Launch Control Center, deputy commander's console. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  1. 45. Photographic reproduction of construction drawing: "Launch Control Facility, Isometric." ...

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

    45. Photographic reproduction of construction drawing: "Launch Control Facility, Isometric." - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  2. Canadian Space Launch: Exploiting Northern Latitudes For Efficient Space Launch

    DTIC Science & Technology

    2015-04-01

    launch. As such, it should be advantageous to move farther away from the equator. Plane changes which alter the orbital inclination of a...a plane change will not be as efficient as others. Launches Between the Equator and 45 o Launches for orbital inclinations which are less than the...highly inclined orbits (HIOs). Compared to launches which take place from facilities at lower latitudes, it is more efficient to launch HIOs from

  3. STS-56 Launch

    NASA Technical Reports Server (NTRS)

    1993-01-01

    The second try works like a charm as the Space Shuttle Discovery lifts off from Launch Pad 39B on Mission STS-56 at 1:29:00 a.m., EDT, April 8. First attempt to launch Discovery on its 16th space voyage was halted at T-11 seconds on April 6. Aboard for the second Space Shuttle mission of 1993 are a crew of five and the Atmospheric Laboratory for Applications and Science 2 (ATLAS 2), the second in a series of missions to study the sun's energy output and Earth's middle atmosphere chemical makeup, and how these factors affect levels of ozone.

  4. STS-64 launch view

    NASA Technical Reports Server (NTRS)

    1994-01-01

    With a crew of six NASA astronauts aboard, the Space Shuttle Discovery heads for its nineteenth Earth-orbital mission. Launch was delayed because of weather, but all systems were 'go,' and the spacecraft left the launch pad at 6:23 p.m. (EDT) on September 9, 1994. Onboard were astronauts Richard N. Richards, L. Blaine Hammond, Carl J. Meade, Mark C. Lee, Susan J. Helms, and Jerry M. Linenger (051-2); Making a bright reflection in nearby marsh waters, the Space Shuttle Discovery heads for its 19th mission in earth orbit (053).

  5. Launch of Vanguard

    NASA Technical Reports Server (NTRS)

    1955-01-01

    Launch of a three-stage Vanguard (SLV-7) from Cape Canaveral, Florida, September 18, 1959. Designated Vanguard III, the 100-pound satellite was used to study the magnetic field and radiation belt. In September 1955, the Department of Defense recommended and authorized the new program, known as Project Vanguard, to launch Vanguard booster to carry an upper atmosphere research satellite in orbit. The Vanguard vehicles were used in conjunction with later booster vehicle such as the Thor and Atlas, and the technique of gimbaled (movable) engines for directional control was adapted to other rockets.

  6. NASA Launch Services Program Overview

    NASA Technical Reports Server (NTRS)

    Higginbotham, Scott

    2016-01-01

    The National Aeronautics and Space Administration (NASA) has need to procure a variety of launch vehicles and services for its unmanned spacecraft. The Launch Services Program (LSP) provides the Agency with a single focus for the acquisition and management of Expendable Launch Vehicle (ELV) launch services. This presentation will provide an overview of the LSP and its organization, approach, and activities.

  7. Simulated Air Launch Environment. Volume 1

    DTIC Science & Technology

    1974-10-01

    temperature, deformations , stress, and strains in solids of revolution loaded axisymmetri- cally as a function of time and temperature. The effects...flexing "of ,he diaphragm, a temperature-compensated gage is produced. The diaphragm pressure transducer was developed at LPC . Subsequent analytical work...was evaluated during the STV and Bomb Dummy Unit Programs at LPC . Past experience with these gages suggests that they can measure stresses to with- in

  8. Air Launch Instrumented Vehicles Evaluation (ALIVE).

    DTIC Science & Technology

    1977-02-01

    Motor 7 108 52 Norma l Stress Gage Sen s i t i v i t y , Motor 4 10’) 53 Norma l Stress Gage Sensitivity, Motor 7 110 94 N ormal S t r e s s...Gage Pre— Cast No—L oad Data as ~~termined I~ Th iokol , Motor 4 111 55 Norma l St ress Gage Pre—C ast No—Load Data as De te rmined by T i t i u k o l...i FIGIJIIIS (Cont inued) 102 ~ j u t e 5weep 2 , Juiuu ’ l’)79 , Norma l Gage N7—5 ’) 169 103 ‘ i u t i Sweep 2 , June 1’) S , Norma l Gage N 7— 6 1

  9. Redstone Missile on Launch Pad

    NASA Technical Reports Server (NTRS)

    1958-01-01

    Redstone missile No. 1002 on the launch pad at Cape Canaveral, Florida, on May 16, 1958. The Redstone ballistic missile was a high-accuracy, liquid-propelled, surface-to-surface missile developed by the Army Ballistic Missile Agency, Redstone Arsenal, in Huntsville, Alabama, under the direction of Dr. von Braun. The Redstone engine was a modified and improved version of the Air Force's Navaho cruise missile engine of the late forties. The A-series, as this would be known, utilized a cylindrical combustion chamber as compared with the bulky, spherical V-2 chamber. By 1951, the Army was moving rapidly toward the design of the Redstone missile, and production was begun in 1952. Redstone rockets became the 'reliable workhorse' for America's early space program. As an example of the versatility, Redstone was utilized in the booster for Explorer 1, the first American satellite, with no major changes to the engine or missile

  10. NLS Advanced Development - Launch operations

    NASA Technical Reports Server (NTRS)

    Parrish, Carrie L.

    1992-01-01

    Attention is given to Autonomous Launch Operations (ALO), one of a number of the USAF's National Launch System (NLS) Launch Operations projects whose aim is to research, develop and apply new technologies and more efficient approaches toward launch operations. The goal of the ALO project is to develop generic control and monitor software for launch operation subsystems. The result is enhanced reliability of system design, and reduced software development and retention of expert knowledge throughout the life-cycle of the system.

  11. The Personnel Launch System

    NASA Technical Reports Server (NTRS)

    Piland, William M.; Talay, Theodore A.; Stone, Howard W.

    1990-01-01

    NASA has begun to study candidate vehicles for manned access to space in support of the Space Station or other future missions requiring on-demand transportation of people to and from earth orbit. One such system, which would be used to complement the present Shuttle or an upgraded version, is the Personnel Launch System (PLS), which is envisioned as a reusable priority vehicle to place people and small payloads into orbit using an experimental launch vehicle. The design of the PLS is based on a Space Station crew changeout requirement whereby eight passengers and two crew members are flown to the station and a like number are returned within a 72 hour mission duration. Experimental and computational aerothermodynamic heating studies have been conducted using a new two-color thermographic technique that involved coating the model with a phosphor that radiates at varying color intensities as a function of temperature when illuminated with UV light. A full-scale model, the HL-20, has been produced and will be used for man-machine research. Three launch vehicle concepts are being considered, a Titan IV, the Advanced Launch System, and a Shuttle equipped with liquid rocket boosters.

  12. AST Launch Vehicle Acoustics

    NASA Technical Reports Server (NTRS)

    Houston, Janice; Counter, D.; Giacomoni, D.

    2015-01-01

    The liftoff phase induces acoustic loading over a broad frequency range for a launch vehicle. These external acoustic environments are then used in the prediction of internal vibration responses of the vehicle and components which result in the qualification levels. Thus, predicting these liftoff acoustic (LOA) environments is critical to the design requirements of any launch vehicle. If there is a significant amount of uncertainty in the predictions or if acoustic mitigation options must be implemented, a subscale acoustic test is a feasible pre-launch test option to verify the LOA environments. The NASA Space Launch System (SLS) program initiated the Scale Model Acoustic Test (SMAT) to verify the predicted SLS LOA environments and to determine the acoustic reduction with an above deck water sound suppression system. The SMAT was conducted at Marshall Space Flight Center and the test article included a 5% scale SLS vehicle model, tower and Mobile Launcher. Acoustic and pressure data were measured by approximately 250 instruments. The SMAT liftoff acoustic results are presented, findings are discussed and a comparison is shown to the Ares I Scale Model Acoustic Test (ASMAT) results.

  13. Launch site radiological emergency response for the cassini mission

    NASA Astrophysics Data System (ADS)

    Marmaro, George M.

    1999-01-01

    Radiological emergency response planning and support for the 15 October 1997 Cassini Launch from the Eastern Launch Site (Kennedy Space Center/Cape Canaveral Air Station) is reviewed. Space Nuclear launches are multi-agency efforts and include support and participation from the National Aeronautics and Space Administration, the Dept. of Energy, the United States Air Force, the Environmental Protection Agency, the Federal Emergency Management Agency, and the State and surrounding counties of Florida. Supporting systems and elements, including mobile field radiological monitoring teams, computerized dispersion modeling, airborne monitoring, automated data management, and both active and passive sampling techniques are described. Communication, command and control, and interagency interfaces are also covered.

  14. Experimental Evaluation of the Effect of Angle-of-attack on the External Aerodynamics and Mass Capture of a Symmetric Three-engine Air-breathing Launch Vehicle Configuration at Supersonic Speeds

    NASA Technical Reports Server (NTRS)

    Kim, Hyun D.; Frate, Franco C.

    2001-01-01

    A subscale aerodynamic model of the GTX air-breathing launch vehicle was tested at NASA Glenn Research Center's 10- by 10-Foot Supersonic Wind Tunnel from Mach 2.0 to 3.5 at various angles-of-attack. The objective of the test was to investigate the effect of angle-of-attack on inlet mass capture, inlet diverter effectiveness, and the flowfield at the cowl lip plane. The flow-through inlets were tested with and without boundary-layer diverters. Quantitative measurements such as inlet mass flow rates and pitot-pressure distributions in the cowl lip plane are presented. At a 3deg angle-of-attack, the flow rates for the top and side inlets were within 8 percent of the zero angle-of-attack value, and little distortion was evident at the cowl lip plane. Surface oil flow patterns showing the shock/boundary-layer interaction caused by the inlet spikes are shown. In addition to inlet data, vehicle forebody static pressure distributions, boundary-layer profiles, and temperature-sensitive paint images to evaluate the boundary-layer transition are presented. Three-dimensional parabolized Navier-Stokes computational fluid dynamics calculations of the forebody flowfield are presented and show good agreement with the experimental static pressure distributions and boundary-layer profiles. With the boundary-layer diverters installed, no adverse aerodynamic phenomena were found that would prevent the inlets from operating at the required angles-of-attack. We recommend that phase 2 of the test program be initiated, where inlet contraction ratio and diverter geometry variations will be tested.

  15. The Delta IV launch table is transferred to CCAFS

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Looking somewhat like a medieval building, this launch table was built in support of the Delta Evolved Expendable Launch Vehicle (EELV) program, known as Delta IV. Fabricated by Jered Industries in Georgia, it was floated on a barge down the Intercoastal Waterway, through the Barge Canal to the turn basin in the Launch Complex 39 Area. In the background is the Vehicle Assembly Building. The table is approximately 70 feet long, 40 feet wide and 50 feet high, and weighs about 600,000 pounds. It is being transferred to Launch Complex 37B, Cape Canaveral Air Force Station, the site of the Delta IV launch complex under construction. Accompanying the launch table on the barge are flame deflectors, which are also to be erected on pad 37B.

  16. Cassini launch contingency effort

    NASA Astrophysics Data System (ADS)

    Chang, Yale; O'Neil, John M.; McGrath, Brian E.; Heyler, Gene A.; Brenza, Pete T.

    2002-01-01

    On 15 October 1997 at 4:43 AM EDT, the Cassini spacecraft was successfully launched on a Titan IVB/Centaur on a mission to explore the Saturnian system. It carried three Radioisotope Thermoelectric Generators (RTGs) and 117 Light Weight Radioisotope Heater Units (LWRHUs). As part of the joint National Aeronautics and Space Administration (NASA)/U.S. Department of Energy (DoE) safety effort, a contingency plan was prepared to address the unlikely events of an accidental suborbital reentry or out-of-orbital reentry. The objective of the plan was to develop procedures to predict, within hours, the Earth impact footprints (EIFs) for the nuclear heat sources released during the atmospheric reentry. The footprint predictions would be used in subsequent notification and recovery efforts. As part of a multi-agency team, The Johns Hopkins University Applied Physics Laboratory (JHU/APL) had the responsibility to predict the EIFs of the heat sources after a reentry, given the heat sources' release conditions from the main spacecraft. (No ablation burn-through of the heat sources' aeroshells was expected, as a result of earlier testing.) JHU/APL's other role was to predict the time of reentry from a potential orbital decay. The tools used were a three degree-of-freedom trajectory code, a database of aerodynamic coefficients for the heat sources, secure links to obtain tracking data, and a high fidelity special perturbation orbit integrator code to predict time of spacecraft reentry from orbital decay. In the weeks and days prior to launch, all the codes and procedures were exercised. Notional EIFs were derived from hypothetical reentry conditions. EIFs predicted by JHU/APL were compared to those by JPL and US SPACECOM, and were found to be in good agreement. The reentry time from orbital decay for a booster rocket for the Russian Progress M-36 freighter, a cargo ship for the Mir space station, was predicted to within 5 minutes more than two hours before reentry. For the

  17. Russian Soyuz in Launch Position

    NASA Technical Reports Server (NTRS)

    2000-01-01

    The Soyuz TM-31 launch vehicle is shown in the vertical position for its launch from Baikonur, carrying the first resident crew to the International Space Station. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960s until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

  18. STS-121 Launch

    NASA Technical Reports Server (NTRS)

    2006-01-01

    Space Shuttle Discovery and its seven-member crew launched at 2:38 p.m. (EDT) to begin the two-day journey to the International Space Station (ISS) on the historic Return to Flight STS-121 mission. The shuttle made history as it was the first human-occupying spacecraft to launch on Independence Day. During its 12-day mission, this utilization and logistics flight delivered a multipurpose logistics module (MPLM) to the ISS with several thousand pounds of new supplies and experiments. In addition, some new orbital replacement units (ORUs) were delivered and stowed externally on the ISS on a special pallet. These ORUs are spares for critical machinery located on the outside of the ISS. During this mission the crew also carried out testing of Shuttle inspection and repair hardware, as well as evaluated operational techniques and concepts for conducting on-orbit inspection and repair.

  19. 21. DETAIL OF AIR HANDLER 1 (MST AIRCONDITIONING SYSTEM) INTERIOR, ...

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

    21. DETAIL OF AIR HANDLER 1 (MST AIR-CONDITIONING SYSTEM) INTERIOR, SOUTHEAST CORNER, STATION 30, SLC-3W MST - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 West, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  20. Launch of Zoological Letters.

    PubMed

    Fukatsu, Takema; Kuratani, Shigeru

    2016-02-01

    A new open-access journal, Zoological Letters, was launched as a sister journal to Zoological Science, in January 2015. The new journal aims at publishing topical papers of high quality from a wide range of basic zoological research fields. This review highlights the notable reviews and research articles that have been published in the first year of Zoological Letters, providing an overview on the current achievements and future directions of the journal.

  1. Space Probe Launch

    NASA Technical Reports Server (NTRS)

    1970-01-01

    Managed by Marshall Space Flight Center, the Space Tug was a reusable multipurpose space vehicle designed to transport payloads to different orbital inclinations. Utilizing mission-specific combinations of its three primary modules (crew, propulsion, and cargo) and a variety of supplementary kits, the Space Tug was capable of numerous space applications. This 1970 artist's concept depicts the Tug's propulsion module launching a space probe into lunar orbit.

  2. Space Shuttle Endeavour launch

    NASA Technical Reports Server (NTRS)

    1992-01-01

    A smooth countdown culminated in a picture-perfect launch as the Space Shuttle Endeavour (STS-47) climbed skyward atop a ladder of billowing smoke. Primary payload for the plarned seven-day flight was Spacelab-J science laboratory. The second flight of Endeavour marks a number of historic firsts: the first space flight of an African-American woman, the first Japanese citizen to fly on a Space Shuttle, and the first married couple to fly in space.

  3. Expendable launch vehicle propulsion

    NASA Technical Reports Server (NTRS)

    Fuller, Paul N.

    1991-01-01

    The current status is reviewed of the U.S. Expendable Launch Vehicle (ELV) fleet, the international competition, and the propulsion technology of both domestic and foreign ELVs. The ELV propulsion technology areas where research, development, and demonstration are most needed are identified. These propulsion technology recommendations are based on the work performed by the Commercial Space Transportation Advisory Committee (COMSTAC), an industry panel established by the Dept. of Transportation.

  4. 64. VIEW OF SOUTH FACE OF SLC3W MST, LAUNCH DECK, ...

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

    64. VIEW OF SOUTH FACE OF SLC-3W MST, LAUNCH DECK, AND FLAME BUCKET FROM DELUGE CHANNEL. NOTE SQUARED CORNERS OF FLAME BUCKET. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 West, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  5. SMAP Launch and Deployment Sequence

    NASA Video Gallery

    This video combines file footage of a Delta II rocket and computer animation to depict the launch and deployment of NASA's Soil Moisture Active Passive satellite. SMAP is scheduled to launch on Nov...

  6. Launch Vehicle Control Center Architectures

    NASA Technical Reports Server (NTRS)

    Watson, Michael D.; Epps, Amy; Woodruff, Van; Vachon, Michael Jacob; Monreal, Julio; Williams, Randall; McLaughlin, Tom

    2014-01-01

    This analysis is a survey of control center architectures of the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures have similarities in basic structure, and differences in functional distribution of responsibilities for the phases of operations: (a) Launch vehicles in the international community vary greatly in configuration and process; (b) Each launch site has a unique processing flow based on the specific configurations; (c) Launch and flight operations are managed through a set of control centers associated with each launch site, however the flight operations may be a different control center than the launch center; and (d) The engineering support centers are primarily located at the design center with a small engineering support team at the launch site.

  7. STS-53 Pilot Cabana adjusts CCA during JSC launch emergency egress training

    NASA Technical Reports Server (NTRS)

    1992-01-01

    STS-53 Discovery, Orbiter Vehicle (OV) 103, Pilot Robert D. Cabana, wearing launch and entry suit (LES), adjusts communications carrier assembly (CCA) chin strap and microphones before donning his helmet. Cabana is preparing for launch emergency egress bailout procedures in JSC's Mockup and Integration Laboratory (MAIL) Bldg 9NE.

  8. STS-53 MS Clifford during launch emergency egress training at JSC

    NASA Technical Reports Server (NTRS)

    1992-01-01

    STS-53 Discovery, Orbiter Vehicle (OV) 103, Mission Specialist Michael R.U. Clifford, wearing launch and entry suit (LES), smiles from behind the communications carrier assembly (CCA) microphones. Clifford is preparing for launch emergency egress bailout procedures at JSC's Mockup and Integration Laboratory Bldg 9NE.

  9. 14 CFR 93.25 - Initial assignment of Arrival Authorizations to U.S. and Canadian air carriers for domestic and U...

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false Initial assignment of Arrival...) AIR TRAFFIC AND GENERAL OPERATING RULES SPECIAL AIR TRAFFIC RULES Congestion and Delay Reduction at... this rule, Arrival Authorizations for each scheduled arrival that it published for either domestic or...

  10. Evolution of the Florida Launch Site Architecture: Embracing Multiple Customers, Enhancing Launch Opportunities

    NASA Technical Reports Server (NTRS)

    Colloredo, Scott; Gray, James A.

    2011-01-01

    The impending conclusion of the Space Shuttle Program and the Constellation Program cancellation unveiled in the FY2011 President's budget created a large void for human spaceflight capability and specifically launch activity from the Florida launch Site (FlS). This void created an opportunity to re-architect the launch site to be more accommodating to the future NASA heavy lift and commercial space industry. The goal is to evolve the heritage capabilities into a more affordable and flexible launch complex. This case study will discuss the FlS architecture evolution from the trade studies to select primary launch site locations for future customers, to improving infrastructure; promoting environmental remediation/compliance; improving offline processing, manufacturing, & recovery; developing range interface and control services with the US Air Force, and developing modernization efforts for the launch Pad, Vehicle Assembly Building, Mobile launcher, and supporting infrastructure. The architecture studies will steer how to best invest limited modernization funding from initiatives like the 21 st elSe and other potential funding.

  11. Intelsat satellite scheduled for launch

    NASA Technical Reports Server (NTRS)

    1981-01-01

    The launch schedule for Intelsat 5-B, the prime Intelsat satellite to provide communications services between the Americas, Europe, the Middle East, and Africa, is presented. The planned placement of the satellite into an elliptical transfer orbit, and circularization of the orbit at geosynchronous altitude over the equator are described. Characteristics of the Atlas Centaur launch vehicle, AC-56, are given. The launch operation is summarized and the launch sequence presented. The Intelsat team and contractors are listed.

  12. Launch summary for 1978 - 1982

    NASA Astrophysics Data System (ADS)

    Hills, H. K.

    1984-01-01

    Data pertinent to the launching of space probes, soundings rockets, and satellites presented in tables include launch date, time, and site; agency rocket identification; sponsoring country or countries; instruments carried for experiments; the peak altitude achieved by the rockets; and the apoapsis and periapsis for satellites. The experimenter or institution involved in the launching is also cited.

  13. Launch Vehicle Control Center Architectures

    NASA Technical Reports Server (NTRS)

    Watson, Michael D.; Epps, Amy; Woodruff, Van; Vachon, Michael Jacob; Monreal, Julio; Levesque, Marl; Williams, Randall; Mclaughlin, Tom

    2014-01-01

    Launch vehicles within the international community vary greatly in their configuration and processing. Each launch site has a unique processing flow based on the specific launch vehicle configuration. Launch and flight operations are managed through a set of control centers associated with each launch site. Each launch site has a control center for launch operations; however flight operations support varies from being co-located with the launch site to being shared with the space vehicle control center. There is also a nuance of some having an engineering support center which may be co-located with either the launch or flight control center, or in a separate geographical location altogether. A survey of control center architectures is presented for various launch vehicles including the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures shares some similarities in basic structure while differences in functional distribution also exist. The driving functions which lead to these factors are considered and a model of control center architectures is proposed which supports these commonalities and variations.

  14. Demonstration/Validation of Hazardous Air Pollutant-Free Adhesive Replacement for Federal Specification MMM-A-121 on the Stryker Infantry Carrier Vehicle

    DTIC Science & Technology

    2013-06-01

    Inc. Patrice E. Dodson U.S. Army Tank-automotive Armaments Command, Anniston Army Depot John J. La Scala Weapons and Materials Research...Inc., 1003 Old Philadelphia Road, Aberdeen, MD 21001 † U.S. Army Tank-automotive Armaments Command, Anniston Army Depot, 7 Frankford Ave., Anniston ... Anniston Army Depot, AL, on a Stryker infantry carrier vehicle driver’s access hatch seal with successful results. In particular, technicians found

  15. Personnel emergency carrier vehicle

    NASA Technical Reports Server (NTRS)

    Owens, Lester J. (Inventor); Fedor, Otto H. (Inventor)

    1987-01-01

    A personnel emergency carrier vehicle is disclosed which includes a vehicle frame supported on steerable front wheels and driven rear wheels. A supply of breathing air is connected to quick connect face mask coupling and umbilical cord couplings for supplying breathing air to an injured worker or attendant either with or without a self-contained atmospheric protection suit for protection against hazardous gases at an accident site. A non-sparking hydraulic motion is utilized to drive the vehicle and suitable direction and throttling controls are provided for controlling the delivery of a hydraulic driving fluid from a pressurized hydraulic fluid accumulator. A steering axis is steerable through a handle to steer the front wheels through a linkage assembly.

  16. STS-115 Launch

    NASA Technical Reports Server (NTRS)

    2005-01-01

    The Space Shuttle Atlantis and its six-member crew launched at 11:15 a.m. (EDT) on September 9, 2006 to begin the two-day journey to the International Space Station (ISS) on the STS-115 mission. During the 11-day mission, the STS-115 crew of six, along with station crews and ground teams, resumed construction of the ISS with the installation of a girder-like structure, known as the P3/P4 truss. The 35,000-pound piece includes a set of giant solar arrays, batteries and associated electronics. The arrays eventually will double the power capability of the Station.

  17. Apollo 13 Launch

    NASA Technical Reports Server (NTRS)

    1970-01-01

    The third marned lunar landing mission, Apollo 13 (SA-508), with three astronauts: Mission commander James A. Lovell Jr., Lunar Module pilot Fred W. Haise Jr., and Command Module pilot John L. Swigert Jr., lifted off from the Kennedy Space Center launch complex 39A on April 11, 1970. The mission was aborted after 56 hours of flight, 205,000 miles from Earth, when an oxygen tank in the service module exploded. The Command Module, Odyssey, carrying the three astronauts, safely splashed down in the Pacific Ocean at 1:08 p.m. EST, April 17, 1970.

  18. Hydrogen carriers

    NASA Astrophysics Data System (ADS)

    He, Teng; Pachfule, Pradip; Wu, Hui; Xu, Qiang; Chen, Ping

    2016-12-01

    Hydrogen has the potential to be a major energy vector in a renewable and sustainable future energy mix. The efficient production, storage and delivery of hydrogen are key technical issues that require improvement before its potential can be realized. In this Review, we focus on recent advances in materials development for on-board hydrogen storage. We highlight the strategic design and optimization of hydrides of light-weight elements (for example, boron, nitrogen and carbon) and physisorbents (for example, metal-organic and covalent organic frameworks). Furthermore, hydrogen carriers (for example, NH3, CH3OH-H2O and cycloalkanes) for large-scale distribution and for on-site hydrogen generation are discussed with an emphasis on dehydrogenation catalysts.

  19. New Product Launching Ideas

    NASA Astrophysics Data System (ADS)

    Kiruthika, E.

    2012-09-01

    Launching a new product can be a tense time for a small or large business. There are those moments when you wonder if all of the work done to develop the product will pay off in revenue, but there are many things are can do to help increase the likelihood of a successful product launch. An open-minded consumer-oriented approach is imperative in todayís diverse global marketplace so a firm can identify and serve its target market, minimize dissatisfaction, and stay ahead of competitors. Final consumers purchase for personal, family, or household use. Finally, the kind of information that the marketing team needs to provide customers in different buying situations. In high-involvement decisions, the marketer needs to provide a good deal of information about the positive consequences of buying. The sales force may need to stress the important attributes of the product, the advantages compared with the competition; and maybe even encourage ìtrialî or ìsamplingî of the product in the hope of securing the sale. The final stage is the post-purchase evaluation of the decision. It is common for customers to experience concerns after making a purchase decision. This arises from a concept that is known as ìcognitive dissonance

  20. Micro, nano and pico satellites launched from the Romanian territory

    NASA Astrophysics Data System (ADS)

    Savu, G.

    2006-10-01

    In the frame of National Program "Aerospatial" The National Institute of Turbomachinery—COMOTI, Bucharest, Romania proposes a project of launching with minimum cost of microsatellites using the national territory. The geographical position of Romania is optimum for satellites launching due to the presence of the Black Sea in the eastern part of the country and due to its elongated shape, West-East, offering a launching surface of 1500 km (W-E) ×250km (N-S). Two modes of launching were analyzed: vertical, from the soil and horizontal, from a carrier aircraft. The second mode of launching doubtless has some advantages, particularly from the point of view of costs. It was analyzed the launching of a LEO satellite as a payload of a single stage rocket with solid propellant, launched from a fighter aircraft. The aerodynamic coefficients of the rocket, the equation of movement on the trajectory and the rocket engine thrust were calculated using a FORTRAN program—LSCS (language for the simulation the continuous systems). The shape of the trajectory was imposed (not optimized), finally resulting the performances, the main geometrical dimensions of the rocket and the mass of the satellite.

  1. Performance modeling of launch vehicle imaging telescopes

    NASA Astrophysics Data System (ADS)

    Harvey, James E.; Krywonos, Andrey; Houston, Joseph B., Jr.

    2005-09-01

    The implementation plan for the "return-to-flight" of the space shuttle after the spectacular Columbia disaster upon re-entering the earth's atmosphere on February 1, 2003 included significant upgrades to the Ground Camera Ascent Imagery assets at Kennedy Space Center (KSC) and Cape Canaveral Air Force Station. The accident was due to damage incurred when a piece if insulating foam debris from the external fuel tank struck the left wing during take-off. The Ground Camera Ascent Imagery Project encompasses a wide variety of launch vehicle tracking telescopes and cameras at the Eastern Range. Most of these launch vehicle imaging telescopes are manually tracked and fitted with video and 35 mm film cameras, and many of them are fixed-focus (i.e., focused at the hyperfocal distance for the duration of the launch). In this paper we describe a systems engineering analysis approach for obtaining performance predictions of these aging launch vehicle imaging telescopes. Recommendations for a continuing maintenance and refurbishment program that closes the loop around the KSC photo-interpreter are included.

  2. Launch vehicle selection model

    NASA Technical Reports Server (NTRS)

    Montoya, Alex J.

    1990-01-01

    Over the next 50 years, humans will be heading for the Moon and Mars to build scientific bases to gain further knowledge about the universe and to develop rewarding space activities. These large scale projects will last many years and will require large amounts of mass to be delivered to Low Earth Orbit (LEO). It will take a great deal of planning to complete these missions in an efficient manner. The planning of a future Heavy Lift Launch Vehicle (HLLV) will significantly impact the overall multi-year launching cost for the vehicle fleet depending upon when the HLLV will be ready for use. It is desirable to develop a model in which many trade studies can be performed. In one sample multi-year space program analysis, the total launch vehicle cost of implementing the program reduced from 50 percent to 25 percent. This indicates how critical it is to reduce space logistics costs. A linear programming model has been developed to answer such questions. The model is now in its second phase of development, and this paper will address the capabilities of the model and its intended uses. The main emphasis over the past year was to make the model user friendly and to incorporate additional realistic constraints that are difficult to represent mathematically. We have developed a methodology in which the user has to be knowledgeable about the mission model and the requirements of the payloads. We have found a representation that will cut down the solution space of the problem by inserting some preliminary tests to eliminate some infeasible vehicle solutions. The paper will address the handling of these additional constraints and the methodology for incorporating new costing information utilizing learning curve theory. The paper will review several test cases that will explore the preferred vehicle characteristics and the preferred period of construction, i.e., within the next decade, or in the first decade of the next century. Finally, the paper will explore the interaction

  3. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, LOW BAY, SECTIONS J-J, K-K, & L-L. Sheet 33-32 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  4. Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy ...

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

    Photocopy of drawing. LAUNCH COMPLEX 39. NASA John F. Kennedy Space Center, Florida. File Number 203-100, Urbahn-Roberts-Seelye-Moran, October 1963. VERTICAL ASSEMBLY BUILDING, HIGH AND LOW BAY AREA, MASTER PLAN FLOOR 1, LEVEL 0’:0”. Sheet 14-03 - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  5. The Launch of an Atlas/Centaur Launch Vehicle

    NASA Technical Reports Server (NTRS)

    1978-01-01

    The launch of an Atlas/Centaur launch vehicle is shown in this photograph. The Atlas/Centaur, launched on November 13, 1978, carried the High Energy Astronomy Observatory (HEAO)-2 into the required orbit. The second observatory, the HEAO-2 (nicknamed the Einstein Observatory in honor of the centernial of the birth of Albert Einstein) carried the first telescope capable of producing actual photographs of x-ray objects.

  6. Spacely's rockets: Personnel launch system/family of heavy lift launch vehicles

    NASA Astrophysics Data System (ADS)

    During 1990, numerous questions were raised regarding the ability of the current shuttle orbiter to provide reliable, on demand support of the planned space station. Besides being plagued by reliability problems, the shuttle lacks the ability to launch some of the heavy payloads required for future space exploration, and is too expensive to operate as a mere passenger ferry to orbit. Therefore, additional launch systems are required to complement the shuttle in a more robust and capable Space Transportation System. In December 1990, the Report of the Advisory Committee on the Future of the U.S. Space Program, advised NASA of the risks of becoming too dependent on the space shuttle as an all-purpose vehicle. Furthermore, the committee felt that reducing the number of shuttle missions would prolong the life of the existing fleet. In their suggestions, the board members strongly advocated the establishment of a fleet of unmanned, heavy lift launch vehicles (HLLV's) to support the space station and other payload-intensive enterprises. Another committee recommendation was that a space station crew rotation/rescue vehicle be developed as an alternative to the shuttle, or as a contingency if the shuttle is not available. The committee emphasized that this vehicle be designed for use as a personnel carrier, not a cargo carrier. This recommendation was made to avoid building another version of the existing shuttle, which is not ideally suited as a passenger vehicle only. The objective of this project was to design both a Personnel Launch System (PLS) and a family of HLLV's that provide low cost and efficient operation in missions not suited for the shuttle.

  7. STS-92 Discovery Launch

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Viewed from across the waters of Banana Creek, clouds of smoke and steam are illuminated by the flames from Space Shuttle Discovery'''s perfect on-time launch at 7:17 p.m. EDT. Discovery carries a crew of seven on a construction flight to the International Space Station. Discovery also carries a payload that includes the Integrated Truss Structure Z-1, first of 10 trusses that will form the backbone of the Space Station, and the third Pressurized Mating Adapter that will provide a Shuttle docking port for solar array installation on the sixth Station flight and Lab installation on the seventh Station flight. Discovery'''s landing is expected Oct. 22 at 2:10 p.m. EDT.

  8. STS-120 Launch

    NASA Technical Reports Server (NTRS)

    2007-01-01

    The Space Shuttle Discovery and its seven-member STS-120 crew headed toward Earth-orbit and a scheduled linkup with the International Space Station (ISS). Liftoff from Kennedy Space Center's launch pad 39A occurred at 11:38:19 a.m. (EDT) on October 23, 2007. Onboard were astronauts Pam Melroy, commander; George Zamka, pilot; Scott Parazynski, Stephanie Wilson, Doug Wheelock, European Space Agency's (ESA) Paolo Nespoli and Daniel Tani, all mission specialists. Discovery linked up with the station for a joint mission of continued construction, The mission delivered the Italian-built U.S. Node 2, named Harmony. During the 14-day mission, the crew installed Harmony, and moved and deployed the P6 solar arrays to their permanent position.

  9. STS-120 Launch

    NASA Technical Reports Server (NTRS)

    2007-01-01

    The Space Shuttle Discovery and its seven-member STS-120 crew headed toward Earth-orbit and a scheduled linkup with the International Space Station (ISS). Liftoff from Kennedy Space Center's launch pad 39A occurred at 11:38:19 a.m. (EDT) on October 23, 2007. Onboard were astronauts Pam Melroy, commander; George Zamka, pilot; Scott Parazynski, Stephanie Wilson, Doug Wheelock, European Space Agency's (ESA) Paolo Nespoli, and Daniel Tani, all mission specialists. Discovery linked up with the station for a joint mission of continued construction. The mission delivered the Italian-built U.S. Node 2, named Harmony. During the 14-day mission, the crew installed Harmony, and moved and deployed the P6 solar arrays to their permanent position.

  10. STS-120 Launch

    NASA Technical Reports Server (NTRS)

    2007-01-01

    The Space Shuttle Discovery and its seven-member STS-120 crew headed toward Earth-orbit and a scheduled linkup with the International Space Station (ISS). Liftoff from Kennedy Space Center's launch pad 39A occurred at 11:38:19 a.m. (EDT) on October 23, 2007. Onboard were astronauts Pam Melroy, commander; George Zamka, pilot; Scott Parazynski, Stephanie Wilson, Doug Wheelock, European Space Agency's (ESA) Paolo Nespoli and Daniel Tani, all mission specialists. Discovery linked up with the station for a joint mission of continued construction. The mission delivered the Italian-built U.S. Node 2, named Harmony. During the 14-day mission, the crew installed Harmony, moved and deployed the P6 solar arrays to their permanent position.

  11. STS-112 Launch

    NASA Technical Reports Server (NTRS)

    2002-01-01

    Space Shuttle Orbiter Atlantis hurdles toward space from Launch Pad 39B at Kennedy Space Center in Florida for the STS-112 mission. Liftoff occurred at 3:46pm EDT, October 7, 2002. Atlantis carried the Starboard-1 (S1) Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A. The S1 was the second truss structure installed on the International Space Station (ISS). It was attached to the S0 truss which was previously installed by the STS-110 mission. The CETA is the first of two human-powered carts that ride along the ISS railway, providing mobile work platforms for future space walking astronauts. The 11 day mission performed three space walks to attach the S1 truss.

  12. Payload Launch Lock Mechanism

    NASA Technical Reports Server (NTRS)

    Young, Ken (Inventor); Hindle, Timothy (Inventor)

    2014-01-01

    A payload launch lock mechanism includes a base, a preload clamp, a fastener, and a shape memory alloy (SMA) actuator. The preload clamp is configured to releasibly restrain a payload. The fastener extends, along an axis, through the preload clamp and into the base, and supplies a force to the preload clamp sufficient to restrain the payload. The SMA actuator is disposed between the base and the clamp. The SMA actuator is adapted to receive electrical current and is configured, upon receipt of the electrical current, to supply a force that causes the fastener to elongate without fracturing. The preload clamp, in response to the fastener elongation, either rotates or pivots to thereby release the payload.

  13. Personnel Launch System definition

    NASA Astrophysics Data System (ADS)

    Piland, William M.; Talay, Theodore A.; Stone, Howard W.

    1990-10-01

    A lifting-body Personnel Launch System (PLS) is defined for assured manned access to space for future U.S. space missions. The reusable craft described is configured for reliable and safe operations, maintainability, affordability, and improved operability, and could reduce life-cycle costs associated with placing personnel into orbit. Flight simulations show the PLS to be a very flyable vehicle with very little control and propellant expenditure required during entry. The attention to crew safety has resulted in the design of a system that provides protection for the crew throughout the mission profile. However, a new operations philosophy for manned space vehicles must be adopted to fully achieve low-cost, manned earth-to-orbit transportation.

  14. Personnel Launch System definition

    NASA Technical Reports Server (NTRS)

    Piland, William M.; Talay, Theodore A.; Stone, Howard W.

    1990-01-01

    A lifting-body Personnel Launch System (PLS) is defined for assured manned access to space for future U.S. space missions. The reusable craft described is configured for reliable and safe operations, maintainability, affordability, and improved operability, and could reduce life-cycle costs associated with placing personnel into orbit. Flight simulations show the PLS to be a very flyable vehicle with very little control and propellant expenditure required during entry. The attention to crew safety has resulted in the design of a system that provides protection for the crew throughout the mission profile. However, a new operations philosophy for manned space vehicles must be adopted to fully achieve low-cost, manned earth-to-orbit transportation.

  15. Launch area theodolite system

    NASA Astrophysics Data System (ADS)

    Bradley, Lester M.; Corriveau, John P.; Tindal, Nan E.

    1991-08-01

    White Sands Missile Range has developed a Launch Area Theodolite (LAT) optical tracking system that provides improved Time-Space-Position-Information (TSPI) for the new class of hyper-velocity missiles being developed by the Army. The LAT system consists of a high- performance optical tracking mount equipped with an 8-12 micrometers Forward Looking Infrared (FLIR) sensor, a newly designed full-frame pin-registered 35-mm film camera, and an auto- focused 50-in. focal length lens. The FLIR has been integrated with the WSMR in-house developed statistical based automatic video tracker to yield a powerful system for the automatic tracking of missiles from a short standoff distance. The LAT has been designed to replace large fixed-camera arrays for test programs on short-range anti-tank missiles. New tracking techniques have been developed to deal with angular tracking rates that exceed one radian in both velocity and acceleration. Special techniques have been developed to shock the tracking mount at the missile launch to match the target motion. An adaptive servo control technique allows a Type III servo to be used to compensate for the high angular accelerations that are generated by the placement of the LAT mounts along the missile flight path. An automated mode selection adjustment is employed as the missile passes a point perpendicular to the tracking mount to compensate for the requirement to rapidly decelerate the tracking mount and keep the target in the field-of-view of the data camera. This paper covers the design concept for a network of eight LAT mounts, the techniques of automatic video tracking using a FLIR sensor, and the architecture of the servo control algorithms that have allowed the LAT system to produce results to a degree never before achieved at White Sands Missile Range.

  16. Close-up of Wing Fit Check of Pylon to Carry the X-38 on B-52 Launch Aircraft

    NASA Technical Reports Server (NTRS)

    1997-01-01

    The new pylon for the X-38 following a fit-check on NASA's B-52 at the Dryden Flight Research Center, Edwards, California, in 1997. The fit-check was the first time the 1,200-pound steel pylon was mated to the B-52 following fabrication at Dryden by the Center's Experimental Fabrication Shop. The pylon was built as an 'adapter' to allow the X-38 research vehicle to be carried aloft and launched from the B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported the

  17. Spacecraft Power Source Installation at Launch Complex

    NASA Technical Reports Server (NTRS)

    Lytal, Paul; Hoffman, Pamela

    2010-01-01

    For certain space missions, an assembly must be integrated onto the spacecraft as late as possible in the launch vehicle processing flow. 12This late integration can be driven for a variety of reasons including thermal or hazardous materials constraints. This paper discusses the process of integrating an assembly onto a spacecraft as late as one week prior to the opening of the launch window. Consideration is given to achieving sufficient access for hardware integration, methods of remotely securing hardware to the spacecraft, maintaining spacecraft cleanliness throughout the integration process, and electrically integrating the component to the spacecraft. Specific examples are taken from the remote mechanical, electrical, and fluid cooling system integration of the power source onto the Mars Science Laboratory (MSL) Rover at the Atlas V Vertical Integration Facility (VIF) at Cape Canaveral Air Force Station, Florida.

  18. Advanced small launch vehicle study

    NASA Technical Reports Server (NTRS)

    Reins, G. E.; Alvis, J. F.

    1972-01-01

    A conceptual design study was conducted to determine the most economical (lowest cost/launch) approach for the development of an advanced small launch vehicle (ASLV) for use over the next decade. The ASLV design objective was to place a 340 kg (750 lb) payload into a 556 km (300 n.mi.) circular orbit when launched due east from Wallops Island, Virginia. The investigation encompassed improvements to the current Scout launch vehicle; use of existing military and NASA launch vehicle stages; and new, optionally staged vehicles. Staging analyses included use of liquid, solid, and hybrid propellants. Improvements in guidance, controls, interstages, telemetry, and payload shroud were also considered. It was concluded that the most economical approach is to progressively improve the Scout launch vehicle in three phased steps which are discussed.

  19. Peer Review of Launch Environments

    NASA Technical Reports Server (NTRS)

    Wilson, Timmy R.

    2011-01-01

    Catastrophic failures of launch vehicles during launch and ascent are currently modeled using equivalent trinitrotoluene (TNT) estimates. This approach tends to over-predict the blast effect with subsequent impact to launch vehicle and crew escape requirements. Bangham Engineering, located in Huntsville, Alabama, assembled a less-conservative model based on historical failure and test data coupled with physical models and estimates. This white paper summarizes NESC's peer review of the Bangham analytical work completed to date.

  20. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

    This wide lux image of the Space Shuttle Discovery as it began its race to catch up with Russia's Mir Space Station shows the base of the launch pad as well as the orbiter just clearing the gantry. Liftoff from Launch Pad 39B, Kennedy Space Center (KSC) occurred at 12:22:04 (EST) February 3, 1995. Discovery is the first in the current fleet of four space shuttle vehicles to make 20 launches.

  1. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

    A 35mm camera was used to expose this image of the Space Shuttle Discovery as it began its race to catch up with Russia's Mir Space Station. Liftoff from Launch Pad 39B, Kennedy Space Center (KSC) occurred at 12:22:04 (EST) February 3, 1995. Discovery is the first in the current fleet of four space shuttle vehicles to make 20 launches. The launch pad and orbiter can be seen reflected in the water directly in front of it.

  2. Launch of STS-63 Discovery

    NASA Technical Reports Server (NTRS)

    1995-01-01

    A 70mm camera was used to expose this image of the Space Shuttle Discovery as it began its race to catch up with Russia's Mir Space Station. Liftoff from Launch Pad 39B, Kennedy Space Center (KSC) occurred at 12:22:04 (EST) February 3, 1995. Discovery is the first in the current fleet of four space shuttle vehicles to make 20 launches. The launch pad and orbiter can be seen reflected in the water directly in front of it.

  3. Gala celebrates 50 years of launches from CCAFS

    NASA Technical Reports Server (NTRS)

    2000-01-01

    At a 50th anniversary gala capping a year-long celebration of 50 years of rocket launches from Cape Canaveral Air Force Station, Chris Bailey (left), president of the AFA Cape Canaveral Chapter, receives a rocket model from Maxwell King (right), former president of Brevard Community College. The first launch at CCAFS took place at 9:28 a.m. on July 24, 1950, with the liftoff of Bumper 8 from Launch Complex 3. The gala, hosted by the Cape Canaveral Chapter Air Force Association, featured such speakers as Center Director Roy Bridges; Vice Commander, Air Force Space Command, Lt. Gen. Roger DeKok; and the Honorable David Weldon, U.S. representative of Florida's 15th Congressional District.

  4. 14 CFR 415.121 - Launch schedule.

    Code of Federal Regulations, 2011 CFR

    2011-01-01

    ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Launch schedule. 415.121 Section 415.121... TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.121 Launch schedule. An applicant's safety review document...

  5. 14 CFR 415.121 - Launch schedule.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch schedule. 415.121 Section 415.121... TRANSPORTATION LICENSING LAUNCH LICENSE Safety Review and Approval for Launch of an Expendable Launch Vehicle From a Non-Federal Launch Site § 415.121 Launch schedule. An applicant's safety review document...

  6. Rocket Launch Trajectory Simulations Mechanism

    NASA Technical Reports Server (NTRS)

    Margasahayam, Ravi; Caimi, Raoul E.; Hauss, Sharon; Voska, N. (Technical Monitor)

    2002-01-01

    The design and development of a Trajectory Simulation Mechanism (TSM) for the Launch Systems Testbed (LST) is outlined. In addition to being one-of-a-kind facility in the world, TSM serves as a platform to study the interaction of rocket launch-induced environments and subsequent dynamic effects on the equipment and structures in the close vicinity of the launch pad. For the first time, researchers and academicians alike will be able to perform tests in a laboratory environment and assess the impact of vibroacoustic behavior of structures in a moving rocket scenario on ground equipment, launch vehicle, and its valuable payload or spacecraft.

  7. The Titan Space Launch System

    NASA Astrophysics Data System (ADS)

    Keeley, J. T.

    1981-04-01

    The Titan III Space Launch Vehicle (SLV) System providing reliable fast response booster capability is discussed. Early Titans, including Titans I and II and the Gemini launch vehicle are described, and the elements of the Titan III, including the upper stages, payload fairings, and launch facilities are presented. The liquid boost module for STS performance augmentation and the Titan 34D SLV System are also discussed. The Titan III SLV System demonstrates excellent versatility while maintaining a high reliability record during thirteen years of operational flights, and provides optional use of solid thrust augmentation and launch sites on both Coasts.

  8. Alkaline sodium borohydride gel as a hydrogen source for PEMFC or an energy carrier for NaBH 4-air battery

    NASA Astrophysics Data System (ADS)

    Liu, B. H.; Li, Z. P.; Chen, L. L.

    In this preliminary study, we tried to use sodium polyacrylate as the super absorbent polymer to form alkaline NaBH 4 gel and explored its possibilities for borohydride hydrolysis and borohydride electro-oxidation. It was found that the absorption capacity of sodium polyacrylate decreased with increasing NaBH 4 concentration. The formed gel was rather stable in the sealed vessel but tended to slowly decompose in open air. Hydrogen generation from the gel was carried out using CoCl 2 catalyst precursor solutions. Hydrogen generation rate from the alkaline NaBH 4 gel was found to be higher and impurities in hydrogen were less than that from the alkaline NaBH 4 solution. The NaBH 4 gel also successfully powered a NaBH 4-air battery.

  9. Launch Support Video Site

    NASA Technical Reports Server (NTRS)

    OFarrell, Zachary L.

    2013-01-01

    The goal of this project is to create a website that displays video, countdown clock, and event times to customers during launches, without needing to be connected to the internal operations network. The requirements of this project are to also minimize the delay in the clock and events to be less than two seconds. The two parts of this are the webpage, which will display the data and videos to the user, and a server to send clock and event data to the webpage. The webpage is written in HTML with CSS and JavaScript. The JavaScript is responsible for connecting to the server, receiving new clock data, and updating the webpage. JavaScript is used for this because it can send custom HTTP requests from the webpage, and provides the ability to update parts of the webpage without having to refresh the entire page. The server application will act as a relay between the operations network, and the open internet. On the operations network side, the application receives multicast packets that contain countdown clock and events data. It will then parse the data into current countdown times and events, and create a packet with that information that can be sent to webpages. The other part will accept HTTP requests from the webpage, and respond to them with current data. The server is written in C# with some C++ files used to define the structure of data packets. The videos for the webpage will be shown in an embedded player from UStream.

  10. Orion Launch Abort System Performance During Exploration Flight Test 1

    NASA Technical Reports Server (NTRS)

    McCauley, Rachel; Davidson, John; Gonzalez, Guillo

    2015-01-01

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

  11. ASTP (SA-210) Launch vehicle operational flight trajectory. Part 3: Final documentation

    NASA Technical Reports Server (NTRS)

    Carter, A. B.; Klug, G. W.; Williams, N. W.

    1975-01-01

    Trajectory data are presented for a nominal and two launch window trajectory simulations. These trajectories are designed to insert a manned Apollo spacecraft into a 150/167 km. (81/90 n. mi.) earth orbit inclined at 51.78 degrees for rendezvous with a Soyuz spacecraft, which will be orbiting at approximately 225 km. (121.5 n. mi.). The launch window allocation defined for this launch is 500 pounds of S-IVB stage propellant. The launch window opening trajectory simulation depicts the earliest launch time deviation from a planar flight launch which conforms to this constraint. The launch window closing trajectory simulation was developed for the more stringent Air Force Eastern Test Range (AFETR) flight azimuth restriction of 37.4 degrees east-of-north. These trajectories enclose a 12.09 minute launch window, pertinent features of which are provided in a tabulation. Planar flight data are included for mid-window reference.

  12. Launch Vehicle Dynamics Demonstrator Model

    NASA Technical Reports Server (NTRS)

    1963-01-01

    Launch Vehicle Dynamics Demonstrator Model. The effect of vibration on launch vehicle dynamics was studied. Conditions included three modes of instability. The film includes close up views of the simulator fuel tank with and without stability control. [Entire movie available on DVD from CASI as Doc ID 20070030984. Contact help@sti.nasa.gov

  13. Commercial expendable launch vehicle liability

    NASA Astrophysics Data System (ADS)

    Hearings before a subcommittee of the House Committee on Commerce, Science, and Transportation are presented. Cost and availability of insurance for commercial launch providers was discussed. The contribution of the domestic launch industry to the Space Program is examined. All written testimony and submittals for the record are also included.

  14. Laser Powered Launch Vehicle Performance Analyses

    NASA Technical Reports Server (NTRS)

    Chen, Yen-Sen; Liu, Jiwen; Wang, Ten-See (Technical Monitor)

    2001-01-01

    The purpose of this study is to establish the technical ground for modeling the physics of laser powered pulse detonation phenomenon. Laser powered propulsion systems involve complex fluid dynamics, thermodynamics and radiative transfer processes. Successful predictions of the performance of laser powered launch vehicle concepts depend on the sophisticate models that reflects the underlying flow physics including the laser ray tracing the focusing, inverse Bremsstrahlung (IB) effects, finite-rate air chemistry, thermal non-equilibrium, plasma radiation and detonation wave propagation, etc. The proposed work will extend the base-line numerical model to an efficient design analysis tool. The proposed model is suitable for 3-D analysis using parallel computing methods.

  15. Dynamic issues in launch vehicle design

    NASA Technical Reports Server (NTRS)

    Ryan, Robert S.; Jewell, Ronald E.

    1993-01-01

    Launch vehicles, in general, have been defined using performance requirements and generic payload characteristics which dictated the propulsion system and the payload carrier. The vehicle concept is then selected using these requirements in conjunction with basic criteria and standards. During the design phase, the selected concept must be modified in order to cope with the numerous dynamic and other problems that occur during design and development. This is costly and is, to some extent, unnecessary. The purpose of this paper is to propose an approach for bringing the dynamic issues into focus during concept selection, where the greatest payoff exists. Delaying consideration of the issues to the design phases creates many problems, not the least of which are the impacts levied against the payload community. Volumes of information exist from prior programs on these dynamic issues and serve as the guidelines for this paper.

  16. Pioneer Launch on Delta Vehicle

    NASA Technical Reports Server (NTRS)

    1969-01-01

    NASA launches the last in the series of interplanetary Pioneer spacecraft, Pioneer 10 from Cape Kennedy, Florida. The long-tank Delta launch vehicle placed the spacecraft in a solar orbit along the path of Earth's orbit. The spacecraft then passed inside and outside Earth's orbit, alternately speeding up and slowing down relative to Earth. The Delta launch vehicle family started development in 1959. The Delta was composed of parts from the Thor, an intermediate-range ballistic missile, as its first stage, and the Vanguard as its second. The first Delta was launched from Cape Canaveral on May 13, 1960 and was powerful enough to deliver a 100-pound spacecraft into geostationary transfer orbit. Delta has been used to launch civil, commercial, and military satellites into orbit. For more information about Delta, please see Chapter 3 in Roger Launius and Dennis Jenkins' book To Reach the High Frontier published by The University Press of Kentucky in 2002.

  17. 14 CFR 271.3 - Carrier subsidy need.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Carrier subsidy need. 271.3 Section 271.3 Aeronautics and Space OFFICE OF THE SECRETARY, DEPARTMENT OF TRANSPORTATION (AVIATION PROCEEDINGS) ECONOMIC REGULATIONS GUIDELINES FOR SUBSIDIZING AIR CARRIERS PROVIDING ESSENTIAL AIR TRANSPORTATION § 271.3...

  18. Aircraft Disinsection: A Guide for Military and Civilian Air Carriers (Desinsectisation des aeronefs: Un guide a l’intention des responsables des transports aeriens civils et militaires)

    DTIC Science & Technology

    1996-04-01

    D.K. Hayes, K. Stalker, and R. Pal, 1978. A comparison of Freon- and water -based insecticidal aerosols for air- craft disinsection. Bull. WHO 56(1):129...Chemical Pest Management Decision-making 32 12.2 Scheduling Insecticide Treatments 33 vi 12.3 Insecticide Selection 34 12.4 Equipment and Materials...walk to Aircraft Connections 42 12.7 Use of Insecticidal Baits 42 12.8 Fumigation 42 12.8.1 Fumigation with Methyl Bromide 42 12.8.2 Fumigation

  19. 78. PIPING CHANNEL FOR FUEL LOADING, FUEL TOPPING, COMPRESSED AIR, ...

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

    78. PIPING CHANNEL FOR FUEL LOADING, FUEL TOPPING, COMPRESSED AIR, GASEOUS NITROGEN, AND HELIUM - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  20. Specialized common carriers: Long distance alternatives for military installations

    NASA Astrophysics Data System (ADS)

    Klingler, S. L.

    1984-03-01

    Specialized Common Carriers, communications carriers which came into existence offering private line microwave service, are now significant competitors in the long distance telecommunications industry. This thesis provides military installation telecommunications managers with a basic knowledge of how Specialized Common Carriers entered the telecommunications market, what services Specialized Common Carriers offer, and how to obtain these services for a military installation. It includes a case study evaluation of the potential use of long distance services of two of these competing common carriers at Naval Air Station Moffett Field, California. A computer program used to calculate the costs of using these two alternative long distance carriers is included as part of the case study.

  1. Aerogel Insulation Systems for Space Launch Applications

    NASA Technical Reports Server (NTRS)

    Fesmire, James E.

    2005-01-01

    New developments in materials science in the areas of solution gelation processes and nanotechnology have led to the recent commercial production of aerogels. Concurrent with these advancements has been the development of new approaches to cryogenic thermal insulation systems. For example, thermal and physical characterizations of aerogel beads under cryogenic-vacuum conditions have been performed at the Cryogenics Test Laboratory of the NASA Kennedy Space Center. Aerogel-based insulation system demonstrations have also been conducted to improve performance for space launch applications. Subscale cryopumping experiments show the thermal insulating ability of these fully breathable nanoporous materials. For a properly executed thermal insulation system, these breathable aerogel systems are shown to not cryopump beyond the initial cooldown and thermal stabilization phase. New applications are being developed to augment the thermal protection systems of space launch vehicles, including the Space Shuttle External Tank. These applications include a cold-boundary temperature of 90 K with an ambient air environment in which both weather and flight aerodynamics are important considerations. Another application is a nitrogen-purged environment with a cold-boundary temperature of 20 K where both initial cooldown and launch ascent profiles must be considered. Experimental results and considerations for these flight system applications are discussed.

  2. MARS PATHFINDER LAUNCH AT LC-17B

    NASA Technical Reports Server (NTRS)

    1996-01-01

    The Mars Pathfinder begins the journey to Mars with liftoff atop a Delta II expendable launch vehicle at 1:58 a.m. EST, Dec. 4, 1996, from Launch Complex 17B on Cape Canaveral Air Station. The Mars Pathfinder will travel on a direct trajectory to the Red Planet, arriving there in July 1997. Mars Pathfinder will send a lander and small robotic rover, Sojourner, to the surface of Mars. The primary objective of the mission is to demonstrate a low-cost way of delivering a science package to the surface of the Red Planet using a direct entry, descent and landing with the aid of small rocket engines, a parachute, airbags and other techniques. In addition, landers and rovers of the future will share the heritage of Mars Pathfinder designs and technologies first tested in this mission. Pathfinder also will collect invaluable data about the Martian surface. The Jet Propulsion Laboratory manages the Mars Pathfinder mission for NASA's Office of Space Science. McDonnell Douglas Aerospace builds the Delta II launch vehicle.

  3. Aerogel insulation systems for space launch applications

    NASA Astrophysics Data System (ADS)

    Fesmire, J. E.

    2006-02-01

    New developments in materials science in the areas of solution gelation processes and nanotechnology have led to the recent commercial production of aerogels. Concurrent with these advancements has been the development of new approaches to cryogenic thermal insulation systems. For example, thermal and physical characterizations of aerogel beads under cryogenic-vacuum conditions have been performed at the Cryogenics Test Laboratory of the NASA Kennedy Space Center. Aerogel-based insulation system demonstrations have also been conducted to improve performance for space launch applications. Subscale cryopumping experiments show the thermal insulating ability of these fully breathable nanoporous materials. For a properly executed thermal insulation system, these breathable aerogel systems are shown to not cryopump beyond the initial cooldown and thermal stabilization phase. New applications are being developed to augment the thermal protection systems of space launch vehicles, including the Space Shuttle External Tank. These applications include a cold-boundary temperature of 90 K with an ambient air environment in which both weather and flight aerodynamics are important considerations. Another application is a nitrogen-purged environment with a cold-boundary temperature of 20 K where both initial cooldown and launch ascent profiles must be considered. Experimental results and considerations for these flight system applications are discussed.

  4. Protein carriers of conjugate vaccines

    PubMed Central

    Pichichero, Michael E

    2013-01-01

    The immunogenicity of polysaccharides as human vaccines was enhanced by coupling to protein carriers. Conjugation transformed the T cell-independent polysaccharide vaccines of the past to T cell-dependent antigenic vaccines that were much more immunogenic and launched a renaissance in vaccinology. This review discusses the conjugate vaccines for prevention of infections caused by Hemophilus influenzae type b, Streptococcus pneumoniae, and Neisseria meningitidis. Specifically, the characteristics of the proteins used in the construction of the vaccines including CRM, tetanus toxoid, diphtheria toxoid, Neisseria meningitidis outer membrane complex, and Hemophilus influenzae protein D are discussed. The studies that established differences among and key features of conjugate vaccines including immunologic memory induction, reduction of nasopharyngeal colonization and herd immunity, and antibody avidity and avidity maturation are presented. Studies of dose, schedule, response to boosters, of single protein carriers with single and multiple polysaccharides, of multiple protein carriers with multiple polysaccharides and conjugate vaccines administered concurrently with other vaccines are discussed along with undesirable consequences of conjugate vaccines. The clear benefits of conjugate vaccines in improving the protective responses of the immature immune systems of young infants and the senescent immune systems of the elderly have been made clear and opened the way to development of additional vaccines using this technology for future vaccine products. PMID:23955057

  5. Launch Order, Launch Separation, and Loiter in the Constellation 1 1/2-Launch Solution

    NASA Technical Reports Server (NTRS)

    Stromgren, Chel; Cates, Grant; Cirillo, William

    2009-01-01

    The NASA Constellation Program (CxP) is developing a two-element Earth-to-Orbit launch system to enable human exploration of the Moon. The first element, Ares I, is a human-rated system that consists of a first stage based on the Space Shuttle Program's solid rocket booster (SRB) and an upper stage that consists of a four-crew Orion capsule, a service module, and a Launch Escape System. The second element, Ares V, is a Saturn V-plus category launch system that consists of the core stage with a cluster of six RS-68B engines and augmented with two 5.5-segment SRBs, a Saturn-derived J-2X engine powering an Earth Departure Stage (EDS), and the lunar-lander vehicle payload, Altair. Initial plans called for the Ares V to be launched first, followed the next day by the Ares I. After the EDS performs the final portion of ascent and subsequent orbit circularization, the Orion spacecraft then performs a rendezvous and docks with the EDS and its Altair payload. Following checkout, the integrated stack loiters in low Earth orbit (LEO) until the appropriate Trans-Lunar Injection (TLI) window opportunity opens, at which time the EDS propels the integrated Orion Altair to the Moon. Successful completion of this 1 1/2-launch solution carries risks related to both the orbital lifetime of the assets and the probability of achieving the launch of the second vehicle within the orbital lifetime of the first. These risks, which are significant in terms of overall system design choices and probability of mission success, dictated a thorough reevaluation of the launch strategy, including the order of vehicle launch and the planned time period between launches. The goal of the effort described in this paper was to select a launch strategy that would result in the greatest possible expected system performance, while accounting for launch risks and the cost of increased orbital lifetime. Discrete Event Simulation (DES) model of the launch strategies was created to determine the probability

  6. Assessing Upper-Level Winds on Day-of-Launch

    NASA Technical Reports Server (NTRS)

    Bauman, William H., III; Wheeler, Mark M.

    2012-01-01

    On the day-or-launch. the 45th Weather Squadron Launch Weather Officers (LWOS) monitor the upper-level winds for their launch customers to include NASA's Launch Services Program (LSP). During launch operations, the payload launch team sometimes asks the LWO if they expect the upper level winds to change during the countdown but the LWOs did not have the capability to quickly retrieve or display the upper-level observations and compare them to the numerical weather prediction model point forecasts. The LWOs requested the Applied Meteorology Unit (AMU) develop a capability in the form of a graphical user interface (GUI) that would allow them to plot upper-level wind speed and direction observations from the Kennedy Space Center Doppler Radar Wind Profilers and Cape Canaveral Air Force Station rawinsondes and then overlay model point forecast profiles on the observation profiles to assess the performance of these models and graphically display them to the launch team. The AMU developed an Excel-based capability for the LWOs to assess the model forecast upper-level winds and compare them to observations. They did so by creating a GUI in Excel that allows the LWOs to first initialize the models by comparing the O-hour model forecasts to the observations and then to display model forecasts in 3-hour intervals from the current time through 12 hours.

  7. Assessment of candidate-expendable launch vehicles for large payloads

    NASA Technical Reports Server (NTRS)

    1984-01-01

    In recent years the U.S. Air Force and NASA conducted design studies of 3 expendable launch vehicle configurations that could serve as a backup to the space shuttle--the Titan 34D7/Centaur, the Atlas II/Centaur, and the shuttle-derived SRB-X--as well as studies of advanced shuttle-derived launch vehicles with much larger payload capabilities than the shuttle. The 3 candidate complementary launch vehicles are judged to be roughly equivalent in cost, development time, reliability, and payload-to-orbit performance. Advanced shuttle-derived vehicles are considered viable candidates to meet future heavy lift launch requirements; however, they do not appear likely to result in significant reduction in cost-per-pound to orbit.

  8. STS Derived Exploration Launch Operations

    NASA Technical Reports Server (NTRS)

    Best, Joel; Sorge, L.; Siders, J.; Sias, Dave

    2004-01-01

    A key aspect of the new space exploration programs will be the approach to optimize launch operations. A STS Derived Launch Vehicle (SDLV) Program can provide a cost effective, low risk, and logical step to launch all of the elements of the exploration program. Many benefits can be gained by utilizing the synergy of a common launch site as an exploration spaceport as well as evolving the resources of the current Space Shuttle Program (SSP) to meet the challenges of the Vision for Space Exploration. In particular, the launch operation resources of the SSP can be transitioned to the exploration program and combined with the operations efficiencies of unmanned EELVs to obtain the best of both worlds, resulting in lean launch operations for crew and cargo missions of the exploration program. The SDLV Program would then not only capture the extensive human space flight launch operations knowledge, but also provide for the safe fly-out of the SSP through continuity of system critical skills, manufacturing infrastructure, and ability to maintain and attract critical skill personnel. Thus, a SDLV Program can smoothly transition resources from the SSP and meet the transportation needs to continue the voyage of discovery of the space exploration program.

  9. 33 CFR 334.770 - Gulf of Mexico and St. Andrew Sound, south of East Bay, Fla., Tyndall Drone Launch Corridor...

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... Sound, south of East Bay, Fla., Tyndall Drone Launch Corridor, Tyndall Air Force Base, Fla.; restricted.... Andrew Sound, south of East Bay, Fla., Tyndall Drone Launch Corridor, Tyndall Air Force Base, Fla... referred to as the “Tyndall Drone Launch Corridor.” (b) The regulations. (1) Military usage of areas...

  10. Mars Pathfinder Status at Launch

    NASA Technical Reports Server (NTRS)

    Spear, A. J.; Freeman, Delma C., Jr.; Braun, Robert D.

    1996-01-01

    The Mars Pathfinder Flight System is in final test, assembly and launch preparations at the Kennedy Space Center in Florida. Launch is scheduled for 2 Dec. 1996. The Flight System development, in particular the Entry, Descent, and Landing (EDL) system, was a major team effort involving JPL, other NASA centers and industry. This paper provides a summary Mars Pathfinder description and status at launch. In addition, a section by NASA's Langley Research Center, a key EDL contributor, is provided on their support to Mars Pathfinder. This section is included as an example of the work performed by Pathfinder team members outside JPL.

  11. Vehicle Dynamics due to Magnetic Launch Propulsion

    NASA Technical Reports Server (NTRS)

    Galaboff, Zachary J.; Jacobs, William; West, Mark E.; Montenegro, Justino (Technical Monitor)

    2000-01-01

    The field of Magnetic Levitation Lind Propulsion (MagLev) has been around for over 30 years, primarily in high-speed rail service. In recent years, however, NASA has been looking closely at MagLev as a possible first stage propulsion system for spacecraft. This approach creates a variety of new problems that don't currently exist with the present MagLev trains around the world. NASA requires that a spacecraft of approximately 120,000 lbs be accelerated at two times the acceleration of gravity (2g's). This produces a greater demand on power over the normal MagLev trains that accelerate at around 0.1g. To be able to store and distribute up to 3,000 Mega Joules of energy in less than 10 seconds is a technical challenge. Another problem never addressed by the train industry and, peculiar only to NASA, is the control of a lifting body through the acceleration of and separation from the MagLev track. Very little is understood about how a lifting body will react with external forces, Such as wind gusts and ground effects, while being propelled along on soft springs such as magnetic levitators. Much study needs to be done to determine spacecraft control requirements as well as what control mechanisms and aero-surfaces should be placed on the carrier. Once the spacecraft has been propelled down the track another significant event takes place, the separation of the spacecraft from the carrier. The dynamics involved for both the carrier and the spacecraft are complex and coupled. Analysis of the reaction of the carrier after losing, a majority of its mass must be performed to insure control of the carrier is maintained and a safe separation of the spacecraft is achieved. The spacecraft angle of attack required for lift and how it will affect the carriage just prior to separation, along with the impacts of around effect and aerodynamic forces at ground level must be modeled and analyzed to define requirements on the launch vehicle design. Mechanisms, which can withstand the

  12. The Application of the NASA Advanced Concepts Office, Launch Vehicle Team Design Process and Tools for Modeling Small Responsive Launch Vehicles

    NASA Technical Reports Server (NTRS)

    Threet, Grady E.; Waters, Eric D.; Creech, Dennis M.

    2012-01-01

    The Advanced Concepts Office (ACO) Launch Vehicle Team at the NASA Marshall Space Flight Center (MSFC) is recognized throughout NASA for launch vehicle conceptual definition and pre-phase A concept design evaluation. The Launch Vehicle Team has been instrumental in defining the vehicle trade space for many of NASA s high level launch system studies from the Exploration Systems Architecture Study (ESAS) through the Augustine Report, Constellation, and now Space Launch System (SLS). The Launch Vehicle Team s approach to rapid turn-around and comparative analysis of multiple launch vehicle architectures has played a large role in narrowing the design options for future vehicle development. Recently the Launch Vehicle Team has been developing versions of their vetted tools used on large launch vehicles and repackaged the process and capability to apply to smaller more responsive launch vehicles. Along this development path the LV Team has evaluated trajectory tools and assumptions against sounding rocket trajectories and air launch systems, begun altering subsystem mass estimating relationships to handle smaller vehicle components, and as an additional development driver, have begun an in-house small launch vehicle study. With the recent interest in small responsive launch systems and the known capability and response time of the ACO LV Team, ACO s launch vehicle assessment capability can be utilized to rapidly evaluate the vast and opportune trade space that small launch vehicles currently encompass. This would provide a great benefit to the customer in order to reduce that large trade space to a select few alternatives that should best fit the customer s payload needs.

  13. 4. "LAUNCH SILOS, EQUIPMENT ROOMS SECTIONS AND DETAILS." Specifications ...

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

    4. "LAUNCH SILOS, EQUIPMENT ROOMS - SECTIONS AND DETAILS." Specifications No. ENG-04-353-59-73; Drawing No. 5841S-5; D.O. SERIES AW-1525/28; Stamped: RECORD DRAWING AS CONSTRUCTED. Below Stamp: Contract No. 6601, Date 18 Sep 59. - Edwards Air Force Base, Air Force Rocket Propulsion Laboratory, Missile Silo Type, Test Area 1-100, northeast end of Test Area 1-100 Road, Boron, Kern County, CA

  14. 3. "LAUNCH SILOS; AREA PAVING AND GRADING PLAN." Specifications No. ...

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

    3. "LAUNCH SILOS; AREA PAVING AND GRADING PLAN." Specifications No. ENG-04-353-59-73; Drawing No. 5841C-11; D.O. SERIES AW-1525/17; Stamped: RECORD DRAWING AS CONSTRUCTED. Below stamp: Contract No. 6601, Date 18 Sep 59. - Edwards Air Force Base, Air Force Rocket Propulsion Laboratory, Missile Silo Type, Test Area 1-100, northeast end of Test Area 1-100 Road, Boron, Kern County, CA

  15. 5. "LAUNCH SILOS; EQUIP. ROOM; SECTIONS AND DETAILS." Specifications No. ...

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

    5. "LAUNCH SILOS; EQUIP. ROOM; SECTIONS AND DETAILS." Specifications No. ENG-04-353-59-73; Drawing No. 5841S-6; D.O. SERIES AW-1525/29; Stamped: RECORD DRAWING AS CONSTRUCTED. Below stamp: Contract No. 6601, Date 18 Sep 59. - Edwards Air Force Base, Air Force Rocket Propulsion Laboratory, Missile Silo Type, Test Area 1-100, northeast end of Test Area 1-100 Road, Boron, Kern County, CA

  16. 34. Launch Control Center, bottom of drawer of commander's console, ...

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

    34. Launch Control Center, bottom of drawer of commander's console, signed by alert crew members on their last alerts. Lyon - Whiteman Air Force Base, Oscar O-1 Minuteman Missile Alert Facility, Southeast corner of Twelfth & Vendenberg Avenues, Knob Noster, Johnson County, MO

  17. 13. WALKWAY FROM LAUNCHING PAD TO CABLE TUNNEL STAIRWELL, ALSO ...

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

    13. WALKWAY FROM LAUNCHING PAD TO CABLE TUNNEL STAIRWELL, ALSO SHOWING A PROTECTIVE BERM AT TOP LEFT, AND FIRING CONTROL BLOCKHOUSE 0545 AT TOP RIGHT. - Edwards Air Force Base, South Base Sled Track, Firing Control Blockhouse, South of Sled Track at east end, Lancaster, Los Angeles County, CA

  18. 14 CFR 101.27 - ATC notification for all launches.

    Code of Federal Regulations, 2010 CFR

    2010-01-01

    ... 14 Aeronautics and Space 2 2010-01-01 2010-01-01 false ATC notification for all launches. 101.27... (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES MOORED BALLOONS, KITES, AMATEUR ROCKETS AND UNMANNED FREE... three days before beginning the operation: (a) The name and address of the operator; except when...

  19. 14 CFR 101.27 - ATC notification for all launches.

    Code of Federal Regulations, 2014 CFR

    2014-01-01

    ... (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES MOORED BALLOONS, KITES, AMATEUR ROCKETS AND UNMANNED FREE BALLOONS Amateur Rockets § 101.27 ATC notification for all launches. No person may operate an unmanned rocket other than a Class 1—Model Rocket unless that person gives the following information to the...

  20. 14 CFR 101.27 - ATC notification for all launches.

    Code of Federal Regulations, 2013 CFR

    2013-01-01

    ... (CONTINUED) AIR TRAFFIC AND GENERAL OPERATING RULES MOORED BALLOONS, KITES, AMATEUR ROCKETS AND UNMANNED FREE BALLOONS Amateur Rockets § 101.27 ATC notification for all launches. No person may operate an unmanned rocket other than a Class 1—Model Rocket unless that person gives the following information to the...