SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS

A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 20 - OCTOBER 07, 2006

15 LAUNCH VEHICLES AND LAUNCH OPERATIONS
Includes all classes of launch vehicles, launch/space vehicle systems, and boosters; and launch operations.

For related information see also 18 Spacecraft Design, Testing and Performance; and 20 Spacecraft Propulsion and Power.

20050214850 NASA Glenn Research Center, Cleveland, OH, USA

Air-Breathing Launch Vehicle Technology Being Developed

Trefny, Charles J.; Research and Technology 2002; March 2003; 3 pp.; In English; No Copyright; Avail.: CASI: A01, Hardcopy

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. Derived from text

Technology Assessment; Single Stage to Orbit Vehicles; Launch Vehicles; Air Breathing Engines

20050214862 NASA Glenn Research Center, Cleveland, OH, USA

Control Surface Seals Investigated for Re- Entry Vehicles

Dunlap, Patrick H.; Steinetz, Bruce M.; Research and Technology 2002; March 2003; 4 pp.; In English; No Copyright; Avail.: CASI: A01, Hardcopy

Re-entry vehicles generally use control surfaces (e.g., rudders, body flaps, and elevons) to steer or guide them as they pass into and through the Earth s atmosphere. High temperature seals are required around control surfaces both along hinge lines and in areas where control surface edges seal against the vehicle body to limit hot gas ingestion and the transfer of heat to underlying low-temperature structures. Working with the NASA Johnson Space Center, the Seals Team at the NASA Glenn Research Center completed a series of tests on the baseline seal design for the rudder/fin control surface interfaces of the X-38 vehicle. This seal application was chosen as a case study to evaluate a currently available control surface seal design for applications in future re-entry vehicles. The structures of the rudder/fin assembly and its associated seals are shown in the following illustration. Derived from text

Control Surfaces; Flapping; Heat Transfer; High Temperature Gases; Hinges; Reentry Vehicles

20050215283 NASA Glenn Research Center, Cleveland, OH, USA

Atlas V Launch Incorporated NASA Glenn Thermal Barrier

Dunlap, Patrick H., Jr.; Steinetz, Bruce M.; Research and Technology 2003; May 2004; 3 pp.; In English; No Copyright; Avail.: CASI: A01, Hardcopy

In the Spring of 2002, Aerojet experienced a major failure during a qualification test of the solid rocket motor that they were developing for the Atlas V Enhanced Expendable Launch Vehicle. In that test, hot combustion gas reached the O-rings in the nozzle-to-case joint and caused a structural failure that resulted in loss of the nozzle and aft dome sections of the motor.

To improve the design of this joint, Aerojet decided to incorporate three braided carbon-fiber thermal barriers developed at the NASA Glenn Research Center. The thermal barriers were used to block the searing-hot 5500 F pressurized gases from reaching the temperature-sensitive O-rings that seal the joint. Glenn originally developed the thermal barriers for the nozzle joints of the space shuttle solid rocket motors, and Aerojet decided to use them on the basis of the results of several successful ground tests of the thermal barriers in the shuttle rockets.

Aerojet undertook an aggressive schedule to redesign the rocket nozzle-to-case joint with the thermal barriers and to qualify it in time for a launch planned for the middle of 2003. They performed two successful qualification tests (Oct. and Dec. 2002) in which the Glenn thermal barriers effectively protected the O-rings. These qualification tests saved hundreds of thousands of dollars in development costs and put the Lockheed-Martin/Aerojet team back on schedule.

On July 17, 2003, the first flight of an Atlas V boosted with solid rocket motors successfully launched a commercial satellite into orbit from Cape Canaveral Air Force Station. Aero-jet's two 67-ft solid rocket boosters performed flawlessly, with each providing thrust in excess of 250,000 lbf. Both motors incorporated three Glenn-developed thermal barriers in their nozzle-to-case joints.

The Cablevision satellite launched on this mission will be used to provide direct-to-home satellite television programming for the U.S. market starting in late 2003. The Atlas V is a product of the military's Enhanced Expendable Launch Vehicle program designed to provide assured military access to space. It can lift payloads up to 19,100 lb to geosynchronous transfer orbit and was designed to meet Department of Defense, commercial, and NASA needs. The Atlas V and Delta IV are two launch systems being considered by NASA to launch the Orbital Space Plane/Crew Exploration Vehicle. The launch and rocket costs of this mission are valued at $250 million.

Successful application of the Glenn thermal barrier to the Atlas V program was an enormous breakthrough for the program's technical and schedule success. Author

Atlas Able 5 Launch Vehicle; Thermal Barriers (Plasma Control); Space Shuttle Boosters; NASA Space Programs

20050215335 Christian Brothers Univ., Memphis, TN, USA

Integration of Launch Vehicle Simulation/Analysis Tools and Lunar Cargo Lander Design, Part 1/2

Shiue, Yeu-Sheng Paul; The 2004 NASA Faculty Fellowship Program Research Reports; January 2005, pp. XL-1 - XL-6; In English; See also 20050215300; Original contains color illustrations; No Copyright; Avail.: CASI: A02, Hardcopy

Simulation and analysis of vehicle performance is essential for design of a new launch vehicle system. It is more and more demand to have an integrated, highly efficient, robust simulation tool with graphical user interface (GUI) for vehicle performance and simulations. The objectives of this project are to integrate and develop launch vehicle simulation and analysis tools in MATLAB/Simulink under PC Platform, to develop a vehicle capable of being launched on a Delta-IV Heavy Launch Vehicle which can land on the moon with the goal of pre-implanting cargo for a new lunar mission, also with the capability of selecting other launch vehicles that are capable of inserting a payload into Trans-Lunar Injection (TLI). The vehicle flight simulation software, MAVERIC-II (Marshall Aerospace VEhicle Representation In ‘C'), developed by Marshall Space Flight Center was selected as a starting point for integration of simulation/analysis tools. The goals are to convert MAVERIC-II from UNIX to PC platform and build input/output GUI s in the MATLAB environment, and then integrate them under MATLAB/Simulink with other modules. Currently, MAVERIC-II has been successfully converted from UNIX to PC using Microsoft Services for UNIX subsystem on PC. Input/Output GUI's have been done for some key input/output files. Calling MAVERIC-II from Simulink has been tested. Details regarding Lunar Cargo Lander Design are described in Part 2/2 of the paper on page X-1. Derived from text

Cargo; Flight SIMulation; Aerospace Vehicles; Systems Integration; Computerized SIMulation; Delta 4 Launch Vehicle; Lunar Landing; Launch Vehicle Configurations

20050216389 NASA Glenn Research Center, Cleveland, OH, USA

Intelligent Elements for the ISHM Testbed and Prototypes (ITP) Project

Maul, William A.; Park, Han; Schwabacher, Mark; Watson, Michael; Mackey, Ryan; Fijany, Amir; Trevino, Luis; Weir, John; September 2005; 14 pp.; In English; Sensors for Industry Conference (SIcon/05), 8-10 Feb. 2005, Houston, TX, USA; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 22-303-30-72 Report No.(s): NASA/TM-3005-213848; E-15219; No Copyright; Avail.: CASI: A03, Hardcopy

Deep-space manned missions will require advanced automated health assessment capabilities. Requirements such as in-space assembly, long dormant periods and limited accessibility during flight, present significant challenges that should be addressed through Integrated System Health Management (ISHM). The ISHM approach will provide safety and reliability coverage for a complete system over its entire life cycle by determining and integrating health status and performance information from the subsystem and component levels. This paper will focus on the potential advanced diagnostic elements that will provide intelligent assessment of the subsystem health and the planned implementation of these elements in the ISHM Testbed and Prototypes (ITP) Project under the NASA Exploration Systems Research and Technology program. Author

Systems Integration; Health; Fault Detection; Manned Space Flight; Deep Space

20050217094 NASA Langley Research Center, Hampton, VA, USA

Thermal Structures Technology Development for Reusable Launch Vehicle Cryogenic Propellant Tanks

Johnson, Theodore F.; Natividad, Roderick; Rivers, H. Kevin; Smith, Russell W.; September 2005; 28 pp.; In English Contract(s)/Grant(s): 23-064-20-32 Report No.(s): NASA/TM-2005-213913; L-19165; No Copyright; Avail.: CASI: A03, Hardcopy

Analytical and experimental studies conducted at the NASA, Langley Research Center (LaRC) for investigating integrated cryogenic propellant tank systems for a reusable launch vehicle (RLV) are described. The cryogenic tanks are investigated as an integrated tank system. An integrated tank system includes the tank wall, cryogenic insulation, thermal protection system (TPS) attachment sub-structure, and TPS. Analysis codes are used to size the thicknesses of cryogenic insulation and TPS insulation for thermal loads, and to predict tank buckling strengths at various ring frame spacings. The unique test facilities developed for the testing of cryogenic tank components are described. Testing at cryogenic and high-temperatures verifies the integrity of materials, design concepts, manufacturing processes, and thermal/structural analyses. Test specimens ranging from the element level to the subcomponent level are subjected to projected vehicle operational mechanical loads and temperatures. The analytical and experimental studies described in this paper provide a portion of the basic information required for the development of light-weight reusable cryogenic propellant tanks. Author

Cryogenics; Propellant Tanks; Reusable Launch Vehicles; Structural Analysis; Thermal Protection; Test Facilities; Technology Utilization

Source: NASA.