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NASA NTRS1975

Tracking techniques for space shuttle rendezvous

The space shuttle rendezvous radar has a requirement to track cooperative and non-cooperative targets. For this reason the Lunar Module (LM) Rendezvous Radar was modified to incorporate the capability of tracking a non-cooperative target. The modifications are discussed. All modifications except those relating to frequency diversity were completed, and system tests were performed to confirm proper performance in the non-cooperative mode. Frequency diversity was added to the radar and to the special test equipment, and then system tests were performed. This last set of tests included re-running the tests of the non-cooperative mode without frequency diversity, followed by tests with frequency diversity and tests of operation in the original cooperative mode.

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NASA NTRS1982

Science on the Space Shuttle

On the Space Shuttle's third flight, scientific instruments will study the electromagnetic environment with charging and electron beams. Beam plasma discharge will be studied. The plasma diagnostics package contains electromagnetic and particle sensors to study the ionosphere. An attempt will be made to establish a more accurate base of solar UV irradiance measurements with an absolute error of 10 percent or less over the wavelength region 120-400 nm. The solar flare X-ray polarimeter will observe flare X-rays emitted between 5 and 30 keV and measure their polarization as a function of time and photon energy. A photopolarimeter will help study zodiacal light, and interplanetary dust will be sampled by a section of thick aluminum foil. Plant seedlings will be grown to research the effect of near-zero gravity on lignification. A thermal canister experiment will help determine whether instruments can be maintained at a fixed temperature under varying thermal loads.

Neupert, W. M.↗

NASA NTRS1985

An improved APU for the Space Shuttle Orbiter

The Space Shuttle Orbiter Auxiliary Power Unit has operated successfully on all four orbiter vehicles and all missions. The current Auxiliary Power Unit (APU) operational life is limited to 12 missions, and the APU turnaround time between flights is longer than originally anticipated. The objective of the Improved APU program is to increase life to 50 missions, reduce installed vehicle weight by 134 lb., and reduce turnaround time. This paper describes the design changes incorporated into the improved APU and the associated development testing.

Mckenna, R.↗

NASA NTRS1984

The US re-usable launch system - The Space Shuttle

The NASA Space Shuttle furnishes a range of readily available, and either already planned or yet-to-be-defined services, which already encompass satellite on-orbit servicing, refueling and repair, and satellite retrieval services. A gradual expansion will be made of services that capitalize on the presence of a large crew during commercial and scientific operations, while pursuing the development of automated, standardized procedures for the handling of experiments in order to reduce research costs.

Lee, C. M.↗

NASA NTRS1992

An Aerodynamic Preliminary Analysis System (APAS) calibration report - Space Shuttle Orbiter

The Space Shuttle Orbiter is modelled and analyzed using the Aerodynamic Preliminary Analysis System (APAS). APAS predictions of Orbiter longitudinal and lateral-directional aerodynamics are compared to Shuttle Orbiter Aerodynamic Design Data Book (ADDB) values from Mach numbers of 0.3 to 20. Agreement between APAS results and the ADDB was good, especially in the case of the longitudinal aerodynamic coefficients. The results of this study establish a sense of confidence in the use of the APAS for conceptual and preliminary studies.

Cruz, Christopher I.↗

NASA NTRS2013

Environmentally-driven Materials Obsolescence: Material Replacements and Lessons Learned from NASA's Space Shuttle Program

The Space Shuttle Program was terminated in 2011 with the last flight of the Shuttle Endeavour. During the 30 years of its operating history, the number of domestic and international environmental regulations increased rapidly and resulted in materials obsolescence risks to the program. Initial replacement efforts focused on ozone depleting substances. As pressure from environmental regulations increased, Shuttle worked on the replacement of heavy metals. volatile organic compounds and hazardous air pollutants. Near the end of the program. Shuttle identified potential material obsolescence driven by international regulations and the potential for suppliers to reformulate materials. During the Shuttle Program a team focused on environmentally-driven materials obsolescence worked to identify and mitigate these risks. Lessons learned from the Shuttle experience can be applied to new NASA Programs as well as other high reliability applications.

Meinhold, Anne↗

NASA NTRS1995

STS-63 Space Shuttle report

The STS-63 Space Shuttle Program Mission Report summarizes the Payload activities and provides detailed data on the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle Main Engine (SSME) systems performance during this sixty-seventh flight of the Space Shuttle Program, the forty-second since the return to flight, and twentieth flight of the Orbiter vehicle Discovery (OV-103). In addition to the OV-103 Orbiter vehicle, the flight vehicle consisted of an ET that was designated ET-68; three SSME's that were designated 2035, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-070. The RSRM's that were an integral part of the SRB's were designated 360Q042A for the left SRB and 360L042B for the right SRB. The STS-63 mission was planned as an 8-day duration mission with two contingency days available for weather avoidance or Orbiter contingency operations. The primary objectives of the STS-63 mission were to perform the Mir rendezvous operations, accomplish the Spacehab-3 experiments, and deploy and retrieve the Shuttle Pointed Autonomous Research Tool for Astronomy-204 (SPARTAN-204) payload. The secondary objectives were to perform the Cryogenic Systems Experiment (CSE)/Shuttle Glo-2 Experiment (GLO-2) Payload (CGP)/Orbital Debris Radar Calibration Spheres (ODERACS-2) (CGP/ODERACS-2) payload objectives, the Solid Surface Combustion Experiment (SSCE), and the Air Force Maui Optical Site Calibration Tests (AMOS). The objectives of the Mir rendezvous/flyby were to verify flight techniques, communication and navigation-aid sensor interfaces, and engineering analyses associated with Shuttle/Mir proximity operations in preparation for the STS-71 docking mission.

Fricke, Robert W., Jr.↗

NASA NTRS1982

Mission definition study for a VLBI station utilizing the Space Shuttle

The uses of the Space Shuttle transportation system for orbiting VeryLong-Baseline Interferometry (OVLBI) were examined, both with respect to technical feasibility and its scientific possibilities. The study consisted of a critical look at the adaptability of current technology to an orbiting environment, the suitability of current data reduction facilities for the new technique, and a review of the new science that is made possible by using the Space Shuttle as a moving platform for a VLBI terminal in space. The conclusions are positive in all respects: no technological deficiencies exist that would need remedy, the data processing problem can be handled easily by straightforward adaptations of existing systems, and there is a significant new research frontier to be explored, with the Space Shuttle providing the first step. The VLBI technique utilizes the great frequency stability of modern atomic time standards, the power of integrated circuitry to perform real-time signal conditioning, and the ability of magnetic tape recorders to provide essentially error-free data recording, all of which combine to permit the realization of radio interferometry at arbitrarily large baselines.

Burke, B. F.↗

NASA NTRS2008

The 2006 Kennedy Space Center Range Reference Atmosphere Model Validation Study and Sensitivity Analysis to the Performance of the National Aeronautics and Space Administration's Space Shuttle Vehicle

The Kennedy Space Center (KSC) Range Reference Atmosphere (RRA) is a statistical model that summarizes wind and thermodynamic atmospheric variability from surface to 70 km. The National Aeronautics and Space Administration's (NASA) Space Shuttle program, which launches from KSC, utilizes the KSC RRA data to evaluate environmental constraints on various aspects of the vehicle during ascent. An update to the KSC RRA was recently completed. As part of the update, the Natural Environments Branch at NASA's Marshall Space Flight Center (MSFC) conducted a validation study and a comparison analysis to the existing KSC RRA database version 1983. Assessments to the Space Shuttle vehicle ascent profile characteristics were performed by JSC/Ascent Flight Design Division to determine impacts of the updated model to the vehicle performance. Details on the model updates and the vehicle sensitivity analyses with the update model are presented.

Burns, Lee↗

NASA NTRS2011

Aerospace News: Space Shuttle Commemoration. Volume 2, No. 7

The complex space shuttle design was comprised of four components: the external tank, two solid rocket boosters (SRB), and the orbiter vehicle. Six orbiters were used during the life of the program. In order of introduction into the fleet, they were: Enterprise (a test vehicle), Columbia, Challenger, Discovery, Atlantis and Endeavour. The space shuttle had the unique ability to launch into orbit, perform on-orbit tasks, return to earth and land on a runway. It was an orbiting laboratory, International Space Station crew delivery and supply replenisher, satellite launcher and payload delivery vehicle, all in one. Except for the external tank, all components of the space shuttle were designed to be reusable for many flights. ATK s reusable solid rocket motors (RSRM) were designed to be flown, recovered, and the metal components reused 20 times. Following each space shuttle launch, the SRBs would parachute into the ocean and be recovered by the Liberty Star and Freedom Star recovery ships. The recovered boosters would then be received at the Cape Canaveral Air Force Station Hangar AF facility for disassembly and engineering post-flight evaluation. At Hangar AF, the RSRM field joints were demated and the segments prepared to be returned to Utah by railcar. The segments were then shipped to ATK s facilities in Clearfield for additional evaluation prior to washout, disassembly and refurbishment. Later the refurbished metal components would be transported to ATK s Promontory facilities to begin a new cycle. ATK s RSRMs were manufactured in Promontory, Utah. During the Space Shuttle Program, ATK supported NASA s Marshall Space Flight Center whose responsibility was for all propulsion elements on the program, including the main engines and solid rocket motors. On launch day for the space shuttle, ATK s Launch Site Operations employees at Kennedy Space Center (KSC) provided lead engineering support for ground operations and NASA s chief engineer. It was ATK s responsibility to have a representative in Firing Room 2 at KSC in case of potential motor problems. However, the last time ATK was responsible for a space shuttle launch slip was 1989. During launch, engineers were also stationed in Promontory on teleconference with counterparts at KSC in the event their support was required.

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NASA NTRS1990

Potential orbital use of the Space Shuttle External Tanks

The Space Shuttle was designed so that major components would be reusable; however, it has been shown that it would not be cost-effective to reuse the external tanks in the same manner as the solid rocket boosters. Studies have been conducted to investigate using the external tanks on orbit. Utilizing an external tank on-orbit appears simple enough, since the tank obtains 98 percent of orbital velocity during the Space Shuttle's ascent phase. However, there are many requirements, issues, and difficulties that users must be aware of and satisfy. Studies for converting an external tank into a gamma-ray imaging telescope (GRIT), conducted at NASA Marshall, have identified many of these specific issues. Results of the GRIT studies and other considerations for the potential conversion of external tanks into useful space resources are summarized.

Nein, Max E.↗

NASA NTRS1973

Space Shuttle Program overview.

The Space Shuttle Program is described in terms of the master planning schedule, design details of the Orbiter vehicle and solid rocket boosters, and payload capabilities of the vehicle for various types of missions. Initial flight tests are described along with subsequent envisioned operational missions. Additional topics include individual phases comprising a complete Space Shuttle mission, typical payload curves for various circular and elliptical orbit missions, details of the payload bay and the remote payload manipulator system, and a general listing of avionics provisions in the vehicle.

Everline, R. T.↗

NASA NTRS1985

Space shuttle revitalization system

The Space Shuttle air revitalization system is discussed. The sequential steps in loop closure are examined and a schematic outline of the regenerative air revitalization system is presented. Carbon dioxide reduction subsystem concepts are compared. Schemes are drawn for: static feedwater electrolysis cell, solid polymer electrolyte water electrolysis cell, air revitalization system, nitrogen generation reactions, nitrogen subsystem staging, vapor compression distillation subsystem, thermoelectric integrated membrane evaporation subsystem, catalytic distillation water reclamation subsystem, and space shuttle solid waste management system.

Quattrone, P. D.↗

NASA NTRS1974

The Space Shuttle - Key considerations

Typical Space Shuttle flight operations, including launch/insertion, on-orbit operations, de-orbit, and ground turnaround, are summarized. The orbiter, main engine, and solid rocket boosters will be reusable. The Shuttle will be able to abort ascent and return the orbiter plus payload to the launch site if necessary. Mission capabilities include a 7-30 day duration, crew of 4-7 (with 1-4 payload specialists), and 14,500-29,500 kg payloads. Payload accommodations, including cabin, crew provisions, pointing and position stability, thermal constraints, electric power, communications, payload deployment and retrieval, contamination control, and kits for extended missions, are considered. The Thermal Protection System, utilizing pyrolized carbon and silica tiles, is described. The Space Shuttle Main Engine design and performance are considered and compared to those of the J-2 engine used on Saturn/Apollo missions.

Malkin, M. S.↗

NASA NTRS1992

A summary of observations performed and the preliminary findings in the Space Shuttle Polarization Experiment

The Space Shuttle Polarization experiment began in 1984. The first data was collected by the crew of STS-51A during October of that year. Since that time polarization data has been acquired from six additional flights. The objective of the experiment was to test the feasibility of concept and the utility of polarized imagery of solar radiation reflected from Earth as acquired from low earth orbit. While this objective has been met, the preliminary results have been well documented in the open literature, and two Space Shuttle payload bay experiments, based in part on these findings are in the design phase, the data acquired have not been used to their full potential. The users of these data have been limited in number even though the images are inexpensive to acquire and are readily available in the public domain. To broaden their use, this paper summarizes the data available, scene content of the images, procedures used to acquire the experimental data, the attributes and shortcomings of the data and a description of uses to which they appear applicable. A catalog of images is now in preparation that should facilitate the application of these data.

Whitehead, Victor S.↗

NASA NTRS1998

Development of Lead Free Energy Absorber for Space Shuttle Blast Container

The Space Shuttle vehicle (SSV) is connected to the mobile launch platform (MLP) by four aft skirt hold down studs on each solid rocket booster (SRB). Prior to lift-off, the frangible nuts inside the aft skirt blast containers (BC) are severed into two nut halves by two pyrotechnic booster cartridges. This action releases the SSV and allows the hold down studs to eject through the aft skirt bore and then down into the MLP. USBI has been tasked to upgrade the BC for two specific reasons; 1. to eliminate lead for environmental concerns, and 2. to reduce the chance of nut recontact with the holddown stud. Nut recontact with the stud has been identified as a likely contributor to stud hangups. This upgrade will replace the lead liner with an aluminum foam material. The aluminum foam used as a energy absorber is a proven design in many other aerospace/defense applications. Additional benefits of using the open cell, energy absorbent aluminum foam in place of the solid lead liner are: A. Lead handling/ exposure, and possible contamination, along with hazardous waste disposal will be eliminated; B. Approximately 200 lbs. weight savings will be contributed to each Space Shuttle flight by using aluminum foam over lead; C. The new aluminum liner is designed to catch all shrapnel from frangible nuts thus virtually eliminating chance of foreign object debris (FOD) exiting the HDP, and causing potential damage to the vehicle; D. Potential of using the lighter aluminum liner over lead, allows for easier assembly and disassembly of blast container elements, also allowing for improvements in safety, operator handling, and efficiency of operations. Six BC firing tests will be required to determine if the new liner material will perform in a way to decrease the chance of stud hangups and enhance the ability of the BC to retain blast debris. Testing will be performed at the Kennedy Space Center (KSC) facility known as the Launch Equipment Test Facility (LETF), and will simulate the SRB hold- down post, with actual BC hardware and pyrotechnics assembled, and then test fired. Initial testing was performed in 1997 using a frangible nut in a static drop test over lead and aluminum foam sheet materials. The aluminum foam showed a dramatic improvement of energy absorption over the lead liner material. Proof-of-Principle testing at the KSC-LETF commenced in May, 1998, and is expected to be completed by June, 1998.

Ingram, T.↗

NASA NTRS1994

Spectral representation of high-frequency Space Shuttle data

High frequency Space Shuttle liftoff data are treated by autoregressive (AR) and autoregressive-moving-average (ARMA) digital algorithms. These algorithms provide useful information on the spectral densities of the data. Further, they yield spectral models, which lend themeselves to incorporation into the concept of the random response spectrum. This concept yields a reasonably smooth power spectrum for the design of structural and mechanical systems when the available data bank is limited. Due to the nonstationary of the liftoff event, the pertinent data are split into three slices. Each of the slices is associated with a rather distinguished phase of the liftoff event, in which stationarity can be expected. The presented results are preliminary in nature; they aim to call attention to the availability of the discussed concepts and to the need to augment the Space Shuttle data bank as more flights are completed.

Spanos, P. D.↗

NASA NTRS1975

Launch Processing System - A system to support the Space Shuttle

Kennedy Space Center (KSC) is designing and acquiring a Launch Processing System (LPS), an important part of Ground Support Equipment (GSE), to Support launch site operations in a more efficient way than was done on previous programs. LPS will provide (1) automatic control of GSE and Shuttle systems for test and operations, (2) real time data analysis and information display, and (3) efficient recall of test data and engineering files to support Shuttle ground operations. Modern automation techniques, off-the-shelf components, and modular design are being employed to the maximum to achieve these goals. The cost of acquisition, operations, and maintenance of LPS is of great importance and is considered with each engineering trade.

Paul, H. C.↗