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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 361 records · Page 20
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NASA NTRS1975

Study of safety implications for shuttle launched spacecraft using fluorinated oxidizers. Volume 1: Complete text

The safety implications of space shuttle launched spacecraft using liquid flourine as the oxidizer for spacecraft propulsion were investigated. Feasibility of safe operation was investigated and the equipment and procedures necessary to maximize the chance of success determined. Hazards to the shuttle were found to be similar in kind if not degree to those encountered in use of nitrogen tetroxide (also toxic oxidizer). It was concluded that residual risks from spacecraft using fluorine and nitrogen tetroxide during ground and flight handling may be reduced by isolation of the oxidizer to only its tank. Operation of planetary spacecraft propulsion in the vicinity of the shuttle in earth orbit is not required. The primary hazard to personnel was identified as propellant loading operations, which should be accomplished in an area reasonably remote from personnel and facilities concentrations. Clearing the pad during spacecraft mating with the shuttle orbiter is recommended.

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NASA NTRS1976

The Space Shuttle's testing gauntlet

The Space Shuttle verification program is detailed, with verification network flowcharts. Performance qualification tests, life endurance tests, structural verification tests, and vibration/dynamic tests of components, subsystems, and major systems at various test levels are dealt with. Ground tests, static firings of the Shuttle main engine, external-tank separation tests, ground vibration tests of vehicle mated to external tank, and main propulsion tests and test scheduling are described. Functions of the Shuttle avionics integration laboratory and electronic systems test laboratory are discussed. Test preparations and procedures for orbital flight testing, launch pad tests, and Shuttle approach- and landing-tests are described.

Mcintosh, G. P.↗
NASA NTRS1976

Vibroacoustic testing of Space Shuttle thermal protection system panels

The modes and acoustic responses of two panels representing Space Shuttle thermal protection panels were investigated. The panels consisted of flat aluminum sheet stiffened longitudinally with hat-section stringers and corrugated supporting panels representing Shuttle ring frame bulkheads. In addition, one panel had 24 tiles of LI900 silica thermal insulation material and a strain isolator pad bonded to the face sheet. Both panels were found to have approximately eight modal frequencies in the 60 to 500 Hz range, where Shuttle acoustic loads are expected to be high. The strain response to a progressive acoustic wave representing a Shuttle spectrum was characterized by the occurrence of larger strains in the direction normal to the stringers than in the direction parallel to the stringers; three modes in the 100 to 400 Hz range contributed significantly to the strain response.

Rucker, C. E.↗
NASA NTRS1975

An earth and ocean SAR for Space Shuttle - User requirements and data handling implications

A brief summary is presented of user requirements for the Shuttle synthetic aperture radar (SAR) to be flown on a sortie mission of 7 to 10 days in duration, based on information collected from survey of the literature and direct user contacts. This information suggests selection of a dual frequency (L and X band) dual polarization SAR capable of meeting most user requirements. Particular attention is given to the SAR system specifications and the data handling capability expected to be available during the 1980s for the tracking and data relay satellite system (TDRSS). The data link requirements of the majority of Shuttle experiments will eventually determine whether the necessary high-capacity Shuttle-TDRSS return link will be part of the intrinsic Shuttle capability or will be part of the SAR payload.

Cohen, E. A.↗
NASA NTRS1976

Microbiology studies in the Space Shuttle

Past space microbiology studies have evaluated three general areas: microbe detection in extraterrestrial materials; monitoring of autoflora and medically important species on crewmembers, equipment, and cabin air; and in vitro evaluations of isolated terrestrial species carried on manned and unmanned spaceflights. These areas are briefly reviewed to establish a basis for presenting probable experiment subjects applicable to the Space Shuttle era. Most extraterrestrial life detection studies involve visitations to other heavenly bodies. Although this is not applicable to the first series of Shuttle flights, attempts to capture meteors and spores in space could be important. Human pathogen and autoflora monitoring will become more important with increased variety among crewmembers. Inclusion of contaminated animal and plant specimens in the space lab will necessitate inflight evaluation of cross-contamination and infection potentials. The majority of Shuttle microbiology studies will doubtless fall into the third study area. Presence of a space lab will permit a whole range of experimentation under conditions similar to these experienced in earth-based laboratories. The recommendations of various study groups are analyzed, and probable inflight microbiological experiment areas are identified for the Life Sciences Shuttle Laboratory.

Taylor, G. R.↗
NASA NTRS1976

The Tethered Balloon Current Generator - A space shuttle-tethered subsatellite for plasma studies and power generation

The objectives of the Tethered Balloon Current Generator experiment are to: (1) generate relatively large regions of thermalized, field-aligned currents, (2) produce controlled-amplitude Alfven waves, (3) study current-driven electrostatic plasma instabilities, and (4) generate substantial amounts of power or propulsion through the MHD interaction. A large balloon (a diameter of about 30 m) will be deployed with a conducting surface above the space shuttle at a distance of about 10 km. For a generally eastward directed orbit at an altitude near 400 km, the balloon, connected to the shuttle by a conducting wire, will be positive with respect to the shuttle, enabling it to collect electrons. At the same time, the shuttle will collect positive ions and, upon command, emit an electron beam to vary current flow in the system.

Williamson, P. R.↗
NASA NTRS1977

Direct delivery of automated spacecraft using the Shuttle - Thoughts for the designer

Following an outline of the main functions of the Tracking and Data Relay Satellite System (TDRSS) and the Astrophysics Transient Explorer (ATREX), the design options of the delivery into orbit of automated spacecraft, ATREX in particular, on board the Shuttle are discussed. The proportional counters used as detectors in ATREX need protection from humidity, so the spacecraft will be shipped in a sealed container filled with dry nitrogen and not opened until it is safely in the clean room at the launch site. The spacecraft and its booster will be loaded into a canister maintaining low humidity, to protect them all the way through the payload changeout room and into the Shuttle itself. After launching the Shuttle into orbit, the spacecraft will be tested on board the Shuttle just before releasing it. The future applications of this technique in Extravehicular Activity (EVA) and Gamma Ray Astronomy Observatories are discussed.

Townsend, M. R.↗
NASA NTRS1978

Mission Control Center (MCC) system specification for the shuttle Orbital Flight Test (OFT) timeframe

The Mission Control Center Shuttle (MCC) Shuttle Orbital Flight Test (OFT) Data System (OFTDS) provides facilities for flight control and data systems personnel to monitor and control the Shuttle flights from launch (tower clear) to rollout (wheels stopped on runway). It also supports the preparation for flight (flight planning, flight controller and crew training, and integrated vehicle and network testing activities). The MCC Shuttle OFTDS is described in detail. Three major support systems of the OFTDS and the data types and sources of data entering or exiting the MCC were illustrated. These systems are the communication interface system, the data computation complex, and the display and control system.

Source record↗
NASA NTRS1977

Shuttle Avionics Integration Laboratory

The SAIL (Shuttle Avionics Integration Laboratory) has been established to provide direct in-line support to the space shuttle program. The SAIL provides a central facility where the avionics and related flight hardware, flight software, and flight procedures will be brought together for integration and verification testing. The basic approach is to utilize qualifiable avionics flight hardware to the greatest extent possible. Where this is not feasible, flight hardware simulators are developed that provide the electrical/electronic termination, stimulation, and signal interface to the flight hardware that it would actually encounter in the shuttle vehicle. This paper discusses the existing laboratory configuration supporting the approach and landing test phase of the shuttle program, the operational experience gained to date, and the design of the laboratory elements to support the orbital flight test phase.

Chambers, T. V.↗
NASA NTRS1977

Space Shuttle Orbiter approach and landing program status

The approach and landing test (ALT) phase of the Space Shuttle program aims at assessing the Orbiter's subsonic aerodynamic flight and landing characteristics along with the support equipment, ground facilities, and the approximate hardware and software to be used in the terminal phase of orbital missions. The program also evaluates the performance of the Shuttle carrier aircraft (SCA) as related to the transport of the Orbiter to the launch sites during the stages of Space Shuttle operations. Results are presented for the SCA inert Orbiter flight testing and the program plans up to the completion of the ALT program. Emphasis is placed on testing the airworthiness of the mated B-747 Shuttle carrier aircraft and Orbiter, checkout of the Orbiter systems in captive flight, and launching the Orbiter with and without the tail cone installed. Major program milestones before the first manned orbital flight are summarized in graphic form.

Andrews, W. H.↗
NASA NTRS1979

Shuttle Global Positioning System (GPS) system design study

The various integration problems in the Shuttle GPS system were investigated. The analysis of the Shuttle GPS link was studied. A preamplifier was designed since the Shuttle GPS antennas must be located remotely from the receiver. Several GPS receiver architecture trade-offs were discussed. The Shuttle RF harmonics and intermode that fall within the GPS receiver bandwidth were analyzed. The GPS PN code acquisition was examined. Since the receiver clock strongly affects both GPS carrier and code acquisition performance, a clock model was developed.

Nilsen, P. W.↗
NASA NTRS1978

Food packages for Space Shuttle

The paper reviews food packaging techniques used in space flight missions and describes the system developed for the Space Shuttle. Attention is directed to bite-size food cubes used in Gemini, Gemini rehydratable food packages, Apollo spoon-bowl rehydratable packages, thermostabilized flex pouch for Apollo, tear-top commercial food cans used in Skylab, polyethylene beverage containers, Skylab rehydratable food package, Space Shuttle food package configuration, duck-bill septum rehydration device, and a drinking/dispensing nozzle for Space Shuttle liquids. Constraints and testing of packaging is considered, a comparison of food package materials is presented, and typical Shuttle foods and beverages are listed.

Fohey, M. F.↗
NASA NTRS1979

Adaptation of solar sounding rocket payloads for Shuttle

The advent of the Shuttle will permit small solar sounding rocket class payloads to be used for orbital applications as a sub satellite. Solutions to such problems as thermal protection, deployment and retrieval and Shuttle bay storage will be presented. Adapting sounding rocket hardware such as solar telescopes, solar attitude control systems and data acquisition modules along with extending power and control gas requirements is discussed. This resulting hardware may be used either in a sounding rocket or Shuttle payload. This paper will combine the solar sounding rocket quick reaction, low cost techniques with the Shuttle Transportation System.

Windsor, R. M.↗
NASA NTRS1978

Space Shuttle data acquisition and processing

The techniques of minimizing the amount of Space Shuttle data processed by using real-time ground data and on board computer to prescreen the data are presented. With the advent of long duration space flight and the large amounts of data generated, it became necessary to limit the amount of data to be processed and also to present data in a manner that highlights the most important data. The Shuttle operational data system with output of 128 kilobits/sec, the developmental flight instrumentation system, and screening of data by the analysts, flight crew, or onboard computers is described, noting that by using these monitoring methods the mission evaluation team can rapidly determine time periods for which postflight data processing is required. Postflight processing systems, batch system output products, data compression techniques, the interactive computer system, and the special telemetry conversion system are discussed, and it is concluded that the combination of Shuttle on board and ground data processing systems enhances the ability to perform a functional evaluation of the Space Shuttle vehicle.

Foster, G. B., Jr.↗
NASA NTRS1980

Space shuttles: A pyrotechnic overview

Pyrotechnic components specified in Shuttle system designs to accomplish varied tasks during all mission phases are described. The function of these pyrotechnics in the operation of the space shuttle vehicle is discussed. Designs are presented for pyrotechnics with innovative features of those meeting unique shuttle requirements for safety and reliability. A rationale for the qualification and certification of these devices is developed. Maintenance of this qualified system in production hardware is explained through a description of shuttle flight certification review process.

Graves, T. J.↗
NASA NTRS1980

Friction evaluation of unpaved, gypsum-surface runways at Northrup Strip, White Sands Missile Range, in support of Space Shuttle Orbiter landing and retrieval operations

Friction measurement results obtained on the gypsum surface runways at Northrup Strip, White Sands Missile Range, N. M., using an instrumented tire test vehicle and a diagonal braked vehicle, are presented. These runways were prepared to serve as backup landing and retrieval sites to the primary sites located at Dryden Flight Research Center for shuttle orbiter during initial test flights. Similar friction data obtained on paved and other unpaved surfaces was shown for comparison and to indicate that the friction capability measured on the dry gypsum surface runways is sufficient for operations with the shuttle orbiter and the Boeing 747 aircraft. Based on these ground vehicle friction measurements, estimates of shuttle orbiter and aircraft tire friction performance are presented and discussed. General observations concerning the gypsum surface characteristics are also included and several recommendations are made for improving and maintaining adequate surface friction capabilities prior to the first shuttle orbiter landing.

Yager, T. J.↗
NASA NTRS1980

Verification of the Space Shuttle ascent flight control

The unique avionics design features of the Space Shuttle ascent flight control are described, along with the test article, test equipment, and test techniques used to verify the ascent flight control prior to commitment to the first orbital flight test. The ascent mission profiles are described, noting that upon ignition of the solid rocket boosters the Shuttle vehicle will rise vertically until achieving tower clearance. The Space Shuttle vehicle uses an integrated avionics system with the Orbiter avionics providing the command, control, and monitoring for the total mated Shuttle vehicle. The sensors and the actuator systems are discussed; the method of ascent flight control system verification is described, and it is concluded that the need for an advanced avionics integration and verification laboratory was recognized early in the program to provide maximum support to all program requirements.

Chambers, T. V.↗
NASA NTRS1981

The Shuttle environment from a payload viewpoint

The paper describes the basis for current estimates of Shuttle environments. It considers available predictions of environments, uncertainties, worst-case conditions and discusses how this data base is used to derive the environmental design requirements. These requirements are assessed from a payload viewpoint, i.e., how they affect payload type, design, mission, location in Shuttle and payload classification. Finally, typical future Shuttle payloads (a pallet-mounted instrument and a spacecraft) are discussed relative to how the Shuttle environments influenced the payload design and test approach.

Divita, E. L.↗