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Results for “MANNED 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.

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At least 73 records · Page 4

All sources NASA NTRS DOE OSTI

NASA NTRS1972

Comparison of the radiation flux profiles and spectral detail from three detailed nongray radiation models at conditions representative of hypervelocity earth entry

The radiation models were compared on the basis of the approaches used for the transport calculations and absorption coefficients and of results obtained for the radiation flux profiles and spectral distributions. The calculated results were for shock layer conditions representative of manned earth reentry from an interplanetary mission. The three models are RATRAP, RADICAL, and MDAC. The results show that significant differences exist in the radiation flux computed by the three models. The RADICAL model was found to depend on fewer approximations, to include more detail, and to require less computer time than the other models.

Suttles, J. T.↗

NASA NTRS1971

The kinetics of reaction of the by-products of ablative materials at high temperatures and the rate of heat transfer between hot surfaces and reactive gases

Research has been conducted by means of laboratory experiments to enhance understanding of the fundamental mechanisms of heterogeneous and homogeneous chemical reactions taking place during ablative processes that accompany the reentry or manned space vehicles into planetary atmospheres. Fundamental mechanisms of those chemical reactions believed to be important in the thermal degradation of ablative plastic heat shield materials, and the gases evolved, are described.

Spokes, G. N.↗

NASA NTRS1980

Analytic theory of orbit contraction and ballistic entry into planetary atmospheres

A space object traveling through an atmosphere is governed by two forces: aerodynamic and gravitational. On this premise, equations of motion are derived to provide a set of universal entry equations applicable to all regimes of atmospheric flight from orbital motion under the dissipate force of drag through the dynamic phase of reentry, and finally to the point of contact with the planetary surface. Rigorous mathematical techniques such as averaging, Poincare's method of small parameters, and Lagrange's expansion, applied to obtain a highly accurate, purely analytic theory for orbit contraction and ballistic entry into planetary atmospheres. The theory has a wide range of applications to modern problems including orbit decay of artificial satellites, atmospheric capture of planetary probes, atmospheric grazing, and ballistic reentry of manned and unmanned space vehicles.

Longuski, J. M.↗

NASA NTRS1959

Studies of Accelerations in Manned Vehicles During Exit and Reentry Flight

Several experiments with human centrifugation are shown with subjects wearing different flight suits.

Source record↗

NASA NTRS1965

A configuration for re-entry from mars missions using aerobraking.

Reentry vehicle configuration from manned Mars missions, using aerobraking

REENTRY VEHICLE↗

NASA NTRS1966

Optimum earth re-entry corridors

Steepest ascent optimization procedure for reentry trajectory of manned aerospace vehicles

REENTRY TRAJECTORY↗

NASA NTRS1961

SUBSONIC AERODYNAMIC CHARACTERISTICS OF DISK RE-ENTRY CONFIGURATIONS WITH ELLIPTIC CROSS SECTIONS AND THICKNESS-DIAMETER RATIOS OF 0.225 AND 0.325

Aerodynamics of disk reentry configurations, for manned space flight, with elliptic cross sections and thickness diameter ratios of 0.225 and 0.325

REENTRY VEHICLE↗

NASA NTRS1963

ATMOSPHERE ENTRY PROBLEMS OF MANNED INTERPLANETARY FLIGHT

Atmospheric entry problems of manned interplanetary flight, including force and stability effects, radiative and convective heating and minimum heat transfer configurations

REENTRY EFFECT↗

NASA NTRS1965

Low-density, autorotating wings for manned re-entry.

Aerodynamic and structural aspects of rotary atmospheric entry aids, including high temperature rotor material selection, rotor blade design, and lift and drag modulation problems

REENTRY VEHICLE↗

NASA NTRS1966

Progress report on the manned lifting body flight test program.

Manned lifting body flight test program, noting NASA M2-F2 and HL-10 and USAF SV-5P

FLIGHT TEST↗

NASA NTRS1963

A LOOK AT MANNED ENTRY AT CIRCULAR TO HYPERBOLIC VELOCITIES

Vehicles for circular and hyperbolic entry by manned spacecraft

CIRCULAR ORBIT↗

NASA NTRS1963

APPLICATIONS FOR PLASTICS IN AEROSPACE RE-ENTRY VEHICLES

Application of plastics as ablative materials in the design of ballistic and manned superorbital lifting reentry vehicles

HEAT SHIELD↗

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 NTRS1960

Structures for Reentry Heating

The basic structural approaches for dealing with reentry heating of manned vehicles are summarized. The weight and development status of both radiative and ablative shields are given and the application of these shields to various vehicles is indicated.

Anderson, Roger A.↗

NASA NTRS1966