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Results for “SPACECRAFT PERFORMANCE”

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 307 records · Page 17
All sourcesNASA NTRSDOE OSTI
NASA NTRS1974

The development and demonstration of hybrid programmable attitude control electronics

HYPACE provides an adaptable, analog/digital design approach that permits preflight and in-flight accommodation of mission changes, component performance variations, spacecraft changes, etc., through programing. This enabled broad multimission flexibility of application in a cost-effective manner. The HYPACE design, which was demonstrated in breadboard form on a single-axis gas-bearing spacecraft simulation, uses a single control channel to perform the attitude control functions sequentially, thus significantly reducing the number of component parts over hard-wired designs. The success of this effort resulted in the concept being selected for the Mariner/Jupiter/Saturn 1977 spacecraft application.

Smith, L. S.↗
NASA NTRS1998

A Model-Based Thruster Leakage Monitor for the Cassini Spacecraft

The Cassini spacecraft was launched on October 15, 1997. It uses thrusters to perform many spacecraft control functions: to detumble the spacecraft, to maintain three-axis attitude control, to perform small trajectory correction burns, to desaturate the reaction wheels, and others.

Cassini↗
NASA NTRS1987

Performance analysis of advanced spacecraft TPS

For the Space Shuttle several types of ceramic heat shield materials were developed, both flexible and rigid. Improvements on the materials are continuously evolving. Material properties that have been studied and improved are high temperature limits, material strength, surface ruggedness, and surface catalycity. The results are presented of preliminary analyses concerning the thermal protection systems of future spacecraft and their sensitivity to the above material properties.

Pitts, William C.↗
NASA NTRS1987

Performance analysis of advanced spacecraft TPS

The analysis on the feasibility for using metal hydrides in the thermal protection system of cryogenic tanks in space was based on the heat capacity of ice as the phase change material (PCM). It was found that with ice the thermal protection system weight could be reduced by, at most, about 20 percent over an all LI-900 insulation. For this concept to be viable, a metal hydride with considerably more capacity than water would be required. None were found. Special metal hydrides were developed for hydrogen fuel storage applications and it may be possible to do so for the current application. Until this appears promising further effort on this feasibility study does not seem warranted.

Pitts, William C.↗
NASA NTRS1988

High performance arrays for lightweight spacecraft

JPL is developing the solar arrays for NASA's ultralightweight spacecraft, the Lunar Get-Away Special (L-GAS), which requires 1 kWe after its slow passage through the Van Allen Belts. The solar array design developed for the mission extended recent NASA-developed photovoltain array technology to power levels well below those conventionally considered practical for deployable lightweight array technology. It has become feasible by these means to consider the design of lightweight spacecraft which require up to 3 kWe at the begining of their service life.

Stella, Paul M.↗
NASA NTRS1992

Measurement of the passive attitude control performance of a recovered spacecraft

A novel silver detector incorporated in the Long Duration Exposure Facility (LDEF) has been used to measure the attitude stability of the vehicle. It is thereby established that the LDEF spacecraft maintained a very stable attitude during its nearly 6-year-long flight, notwithstanding a small offset yaw of 8.0 +/- 0.4 deg clockwise from nominal attitude (as viewed from space) and a +/- 0.2-deg oscillation about this offset yaw. LDEF experiments which depend on orientation relative to the forward direction may need to be corrected for the angular offset.

Gregory, J. C.↗
NASA NTRS2007

Automated Rendezvous and Docking Sensor Testing at the Flight Robotics Laboratory

The Exploration Systems Architecture defines missions that require rendezvous, proximity operations, and docking (RPOD) of two spacecraft both in Low Earth Orbit (LEO) and in Low Lunar Orbit (LLO). Uncrewed spacecraft must perform automated and/or autonomous rendezvous, proximity operations and docking operations (commonly known as Automated Rendezvous and Docking, (AR&D).) The crewed versions of the spacecraft may also perform AR&D, possibly with a different level of automation and/or autonomy, and must also provide the crew with relative navigation information for manual piloting. The capabilities of the RPOD sensors are critical to the success of the Exploration Program. NASA has the responsibility to determine whether the Crew Exploration Vehicle (CEV) contractor-proposed relative navigation sensor suite will meet the CEV requirements. The relatively low technology readiness of relative navigation sensors for AR&D has been carried as one of the CEV Projects top risks. The AR&D Sensor Technology Project seeks to reduce this risk by increasing technology maturation of selected relative navigation sensor technologies through testing and simulation, and to allow the CEV Project to assess the relative navigation sensors.

Howard, Richard T.↗
NASA NTRS2008

Three year orbital trim maneuver performance of the Cassini spacecraft attitude control subsystem.

Cassini is a sophisticated interplanetary spacecraft providing scientific findings that continue to offer insight into our solar system. After arriving at Saturn on June 30, 2004 it has completed three years of a four year prime mission. To date, Cassini has completed 49 orbits about Saturn and over 40 targeted flybys of Saturn’s moons. This has been achieved with a nominal design using three delta-V maneuvers per targeted encounter.

Smith, Brett A.↗
NASA NTRS2006

Analytical Assessment of the Reciprocating Feed System

A preliminary analysis tool has been created in Microsoft Excel to determine deliverable payload mass, total system mass, and performance of spacecraft systems using various types of propellant feed systems. These mass estimates are conducted by inserting into the user interface the basic mission parameters (e.g., thrust, burn time, specific impulse, mixture ratio, etc.), system architecture (e.g., propulsion system type and characteristics, propellants, pressurization system type, etc.), and design properties (e.g., material properties, safety factors, etc.). Different propellant feed and pressurization systems are available for comparison in the program. This gives the user the ability to compare conventional pressure fed, reciprocating feed system (RFS), autogenous pressurization thrust augmentation (APTA RFS), and turbopump systems with the deliverable payload, inert mass, and total system mass being the primary comparison metrics. Analyses of several types of missions and spacecraft were conducted and it was found that the RFS offers a performance improvement, especially in terms of delivered payload, over conventional pressure fed systems. Furthermore, it is competitive with a turbopump system at low to moderate chamber pressures, up to approximately 1,500 psi. Various example cases estimating the system mass and deliverable payload of several types of spacecraft are presented that illustrate the potential system performance advantages of the RFS. In addition, a reliability assessment of the RFS was conducted, comparing it to simplified conventional pressure fed and turbopump systems, based on MIL-STD 756B; these results showed that the RFS offers higher reliability, and thus substantially longer periods between system refurbishment, than turbopump systems, and is competitive with conventional pressure fed systems. This is primarily the result of the intrinsic RFS fail-operational capability with three run tanks, since the system can operate with just two run tanks.

Eddleman, David E.↗
NASA NTRS1979

Interactions between spacecraft and the charged-particle environment

Spacecraft-environment interactions are defined as the responses of a spacecraft surface to a charged-particle environment. This response can influence spacecraft system performance. Interactions can be divided into two broad categories: spacecraft passive, in which the environment acts on the spacecraft; and spacecraft active, in which the spacecraft causes the interaction. Passive interactions include the spacecraft-charging phenomenon. Active interactions include the relatively new interactions arising from the use of very large spacecraft and space power systems in future missions. To illustrate active interactions, a large power system operating at elevated voltages is considered. Possible interactions are described, available experimental data are reviewed, and the effect on power system performance is estimated.

Stevens, N. J.↗