Search NASA⌕ Search

SEARCH · Search NASA

Results for “Reentry”

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.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 361 records · Page 20
All sourcesNASA NTRSDOE OSTI
NASA NTRS1986

Numerical simulations of rarefied reentry flows

A review of recent calculations obtained with Bird's direct simulation Monte Carlo (DSMC) method is presented for the transitional flowfield encountered at reentry conditions. Consequently, the emphasis is the real-gas effects resulting from a highly energetic nonequilibrium flow. The DSMC calculations for both wide-angle and slender bodies are compared with continuum calculations. The wide-angle body calculations simulate the windward nose of the Shuttle Orbiter and projected aeroassisted orbital transfer vehicles. For the slender, blunted configurations, both two-dimensional and axisymmetric results are presented. Comparisons between the DSMC and continuum calculations show the altitude range where differences in flowfield structure and surface quantities become significant.

Moss, James N.↗
NASA NTRS1987

Effects of forced and free convections on structural temperatures of Space Shuttle Orbiter during reentry flight

Structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat transfer analysis of the Space Shuttle Orbiter wing subjected to reentry aerodynamic heating. With sufficient external forced convective cooling near the end of the heating cycle, the calculated surface temperatures of the thermal protection system (TPS) agree favorably with the flight data for the entire flight profile. However, the effects of this external forced convective cooling on the structural temperatures were found to be negligible. Both free convection and forced convection elements were introduced to model the internal convection effect of the cool air entering the Shuttle interior. The introduction of the internal free convection effect decreased the calculated wing lower skin temperatures by 20 F at most, 1200 sec after touchdown. If the internal convection is treated as forced convection, the calculated wing lower skin temperatures after touchdown can be reduced to match the flight-measured data very closely. By reducing the TPS thicknesses to certain effective thickness to account for the TPs gap heating, the calculated wing lower skin temperatures prior to touchdown can be raised to agree with the flight data perfectly.

Ko, William L.↗
NASA NTRS1988

A theoretical prediction of the attitude dynamics due to aerodynamic effects on the reusable reentry satellite

As part of the preliminary mission analysis of the Reusable Reentry Satellite (RRS) (planned for launching in the early to mid-1990s), the on-orbit attitude dynamics of the RRS were analyzed to quantify various parameters that would affect the attitude dynamics of the vehicle. The analysis simulated the attitude dynamics of the RRS due to aerodynamic forces coupled with the motion of the satellite moving around the orbit, estimated the levels of induced angular rates due to external disturbance torques while in orbit, and established the limits of operational orbit altitudes. The results show that, for a typical 60-day mission, orbit altitudes above 350 km are necessary to prevent undesirable orbit decay, with about 200 km as the lower limit. It was also found that, in order to maintain a pointing attitude toward the sun within an acceptable angular deviation for periods exceeding 8 hrs, it is necessary to orbit at an altitude above 600 km.

Wercinski, P. F.↗
NASA NTRS1988

A conceptual design study of the reusable reentry satellite

Experimentation leading to an understanding of life processes under reduced and extremely low gravitational forces will profoundly contribute to the success of future space missions involving humans. In addition to research on gravitational biology, research on the effects of cosmic radiation and the interruption and change of circadian rhythms on life systems is also of prime importance. Research in space, however, is currently viewed by biological scientists as an arena that is essential, yet largely inaccessible to them for their experimentation. To fulfill this need, a project and spacecraft system described as the Reusuable Reentry Satellite or Lifesat has been proposed by NASA.

Swenson, Byron L.↗
NASA NTRS1989

The reusable reentry satellite - A mission and system description and operational concept

A significant need exists for a system which will provide the life science experimenter with relatively frequent and inexpensive access to the space environment. To fulfill this need, a project and spacecraft system described as the Reusable Reentry Satellite (RRS) or LifeSat has been proposed by NASA. The RRS provides a relatively inexpensive method of access to space for extended periods of time and eventual intact recovery of the experiments on the earth's surface. The payload support requirements, flight operations concept are reviewed and the mission and system of the RRS are described in detail.

Swenson, Byron L.↗
NASA NTRS1989

Monte Carlo simulation of reentry plasmas

Attention is given to the treatment of ionization and plasma effects in the direct simulation Monte Carlo method. The requirements for accurate modeling of reentry plasmas are discussed along with the difficulties these requirements present. The current method for modeling such plasmas is reviewed and an alternative method is presented. Both methods are applied to the flow of a 10 km/s shock wave in air at 0.1 torr; a flowfield directly relevant to the projected aeroassisted orbital transfer vehicle. The results are compared and the differences between the methods are discussed.

Carlson, Ann B.↗
NASA NTRS1989

Gravity wave structure between 60 and 90 km inferred from Space Shuttle reentry data

Density fluctuations obtained along seven Space Shuttle reentry tracks are used to examine the horizontal structure and the vertical distribution of density variance in the mesosphere and lower thermosphere. The tracks lie primarily over open ocean at middle and low latitudes and represent the only measurements of horizontal atmospheric structure at these heights available to date. The density fluctuations are interpreted in terms of gravity-wave motions and reveal significant density (and velocity) variance at horizontal scales ranging from about 10 to 1000 km. Fluctuation amplitudes are used to infer corresponding velocity perturbations and characteristic vertical scales and frequencies of the wave spectrum. Results suggest that the mean velocity variance is smaller over the Pacific ocean than over major land masses, and that the variance increases with height in a manner consistent with that expected in the present of wave saturation processes.

Fritts, David C.↗
NASA NTRS1989

Monte Carlo turbulence simulation for Shuttle reentry studies

A realistic model for the Space Shuttle reentry which will permit more rational selection of the reaction control fuel redlines than did the current turbulence model, is described, with special attention given to the turbulence simulation difference equations, which are revised in this paper. The difference equations for the third-order approximation are presented for both the longitudinal turbulence and the transverse turbulence equations. Each set of equations can be used to generate a probability distribution of fuel remaining at landing.

Campbell, Warren C.↗
NASA NTRS1990

Direct simulation of reentry flows with ionization

The Direct Simulation Monte Carlo (DSMC) method is applied in this paper to the study of rarefied hypersonic reentry flows. The assumptions and simplifications involved with the treatment of ionization, free electrons and the electric field are investigated. A new method is presented for the calculation of the electric field and handling of charged particles with DSMC. In addition, a two-step model for electron impact ionization is implemented. The flowfield representing a 10 km/sec shock at an altitude of 65 km is calculated. The effects of the new modeling techniques on the calculation results are presented and discussed.

Carlson, Ann B.↗
NASA NTRS1990

Thermochemical nonequilibrium issues for earth reentry of Mars mission vehicles

The thermochemical environment about an axisymmetric 60-deg sphere-cone with a circular aft skirt is computed using the Langley Aerothermodynamic Upwind Relaxation Algorithm. Earth entry at 12 km/sec is examined at 70-km and 80-km altitude for two vehicle base radii of 2 m and 6 m. These four test cases bracket some proposed scenarios for earth reentry of a manned Mars mission aerobrake at this velocity. Thermochemical nonequilibrium results are examined for each case and compared with thermal equilibrium results produced by artificially accelerating vibrational relaxation rates and with equilibrium results produced by a viscous shock layer method.

Mitcheltree, R. A.↗
NASA NTRS1991

Reusable surface insulations for reentry spacecraft

A family of ceramic, reusable surface insulations developed for the thermal protection of reentry vehicles is discussed. Their thermal properties are summarized and their thermal capabilities are compared. The insulation requirements for the Personnel Launch System are evaluated.

Chiu, S. Amanda↗
NASA NTRS1992

Characteristics of the Shuttle Orbiter leeside flow during a reentry condition

A study of the leeside flow characteristics of the Shuttle Orbiter is presented for a reentry flight condition. The flow is computed using a point-implicit, finite-volume scheme known as the Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA). LAURA is a second-order accurate, laminar Navier-Stokes solver, incorporating finite-rate chemistry with a radiative equilibrium wall temperature distribution and finite-rate wall catalysis. The resulting computational solution is analyzed in terms of salient flow features and the surface quantities are compared with flight data.

Kleb, William L.↗
NASA NTRS1991

Reusable Reentry Satellite (RRS) system design study

The Reusable Reentry Satellite (RRS) is intended to provide investigators in several biological disciplines with a relatively inexpensive method to access space for up to 60 days with eventual recovery on Earth. The RRS will permit totally intact, relatively soft, recovery of the vehicle, system refurbishment, and reflight with new and varied payloads. The RRS is to be capable of three reflights per year over a 10-year program lifetime. The RRS vehicle will have a large and readily accessible volume near the vehicle center of gravity for the Payload Module (PM) containing the experiment hardware. The vehicle is configured to permit the experimenter late access to the PM prior to launch and rapid access following recovery. The RRS will operate in one of two modes: (1) as a free-flying spacecraft in orbit, and will be allowed to drift in attitude to provide an acceleration environment of less than 10(exp -5) g. the acceleration environment during orbital trim maneuvers will be less than 10(exp -3) g; and (2) as an artificial gravity system which spins at controlled rates to provide an artificial gravity of up to 1.5 Earth g. The RRS system will be designed to be rugged, easily maintained, and economically refurbishable for the next flight. Some systems may be designed to be replaced rather than refurbished, if cost effective and capable of meeting the specified turnaround time. The minimum time between recovery and reflight will be approximately 60 days. The PMs will be designed to be relatively autonomous, with experiments that require few commands and limited telemetry. Mass data storage will be accommodated in the PM. The hardware development and implementation phase is currently expected to start in 1991 with a first launch in late 1993.

Source record↗
NASA NTRS1991

System specification for the reusable reentry satellite

The RRS design shall provide a relatively inexpensive method of access to micro and fractional gravity space environments for an extended period of time, with eventual intact recovery on the surface of the Earth. This specification establishes the performance, design, development, and test requirements for the Reusable Reentry Satellite (RRS) system.

Source record↗
NASA NTRS1990

Reusable Reentry Satellite (RRS): Launch tradeoff study

A goal of the Phase B study is to define the launch system interfaces for the reusable reentry satellite (RRS) program. The focus of the launch tradeoff study, documented in this report, is to determine which expendable launch vehicles (ELV's) are best suited for the RRS application by understanding the impact of all viable launch systems on RRS design and operation.

Source record↗
NASA NTRS1991

Experiment module/support module interface specification for the reusable reentry satellite

This Interface Specification (IFS) identifies, defines, and controls the interface between the Reusable Reentry Satellite (RRS) Vehicle (RRV) Experiment Module (EM) and the Support Module (SM) equipment. Contained in this specification are the physical, functional, and environmental interface requirements for the SM and EM. This specification is tailored to the unique requirements of the EM associated with the Rodent Module. The addenda to this specification contain the requirements for alternate EM's.

Source record↗
NASA NTRS1990

Reusable Reentry Satellite (RRS): Thermal control trade study

The design and assessment work performed in defining the on-orbit Thermal Control Subsystem (TCS) requirements for the Reusable Reentry Satellite (RRS) is discussed. Specifically, it describes the hardware and design measures necessary for maintaining the Payload Module (PM) Environmental Control Life Support System (ECLSS) heat exchanger, the hydrazine propellant, and PM water supply within their required temperature limits.

Wallace, Clark↗