Engineering Papers⌕ Search

SEARCH · Engineering Papers

Results for “SPACE”

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 1,081 records · Page 60
All sourcesNASA NTRSDOE OSTI
NASA NTRS1971

Space shuttle: Static stability characteristics and control surface effectiveness of the Boeing .00435 scale model space shuttle booster H-32

Experimental aerodynamic investigations were made in the Grumman 36-inch hypersonic wind tunnel on a .00435 scale model of the H-32 reusable space shuttle booster. The objectives of the test were to determine the static stability characteristics and control surface effectiveness at hypersonic speeds. Data were taken at M = 8.12 over a range of angles of attack between -5 and 85 deg at beta = 0 deg and over a range of side slip angles between -10 and 10 deg at alpha = 0 and 70 deg. Six component balance data and base-cavity pressure data were recorded.

Houser, J. F.↗
NASA NTRS1972

Methods of space radiation dose analysis with applications to manned space systems

The full potential of state-of-the-art space radiation dose analysis for manned missions has not been exploited. Point doses have been overemphasized, and the critical dose to the bone marrow has been only crudely approximated, despite the existence of detailed man models and computer codes for dose integration in complex geometries. The method presented makes it practical to account for the geometrical detail of the astronaut as well as the vehicle. Discussed are the major assumptions involved and the concept of applying the results of detailed proton dose analysis to the real-time interpretation of on-board dosimetric measurements.

Langley, R. W.↗
NASA NTRS1972

Space shuttle: Experimental investigations for base drag reduction on a 0.015 scale model MSFS proposed space shuttle booster at Mach numbers from 0.40 to 1.10

A 0.015-scale model of a modified version of the MDAC space shuttle booster was tested to obtain force, static stability, and control effectiveness data. The objective of this test was the reduction of cruise (M = 0.4) base drag by the use of base flaps, base vents, elevon deflection and base flow from a plenum mounted forward of the base heat shield. Transonic data were also obtained to determine the aerodynamic characteristics of the new base shape. Six component aerodynamic force and moment data were recorded over an angle of attack range from 4 deg to 20 deg at 0 deg sideslip and over a sideslip range from -6 deg to 6 deg at 0 deg, 6 deg and 15 deg angle of attack. Mach number varied from 0.4 to 1.10 at a constant R of 2 million per unit length.

Bradley, D.↗
NASA NTRS1972

Space shuttle: Static aerodynamic characteristics of the MSC-040A the Msc-040A space shuttle orbiter with wedge centerline vertical and twin vertical tails at Mach numbers from 0.6 to 4.96

The results are presented from experimental aerodynamic investigations conducted on a 0.6-percent scale model of the MSC-040 space shuttle orbiter in a 14 inch trisonic wind tunnel. The purpose of the test program was to define the stability, control, and performance characteristics of the baseline MSC-040A orbiter configuration with proposed alternate wing pods, with several vertical tail configurations with and without flared rudders, and with upper wing surface flap deflections. Force and moment data and model base and balance cavity pressure data were obtained for a Mach range of 0.60 through 4.96 and dynamic pressure range of 465 through 1580 psf. Model attitude was varied from 0 to +34 degrees angle of attack at zero sideslip and -4 to +10 degrees angle of sideslip at 0, 10, 20, and 24 degrees angle of attack.

Glass, K. J.↗
NASA NTRS1972

Study of solid rocket motors for a space shuttle booster. Appendix E: Environmental impact statement, solid rocket motor, space shuttle booster

An analysis of the combustion products resulting from the solid propellant rocket engines of the space shuttle booster is presented. Calculation of the degree of pollution indicates that the only potentially harmful pollutants, carbon monoxide and hydrochloric acid, will be too diluted to constitute a hazard. The mass of products ejected during a launch within the troposphere is insignificant in terms of similar materials that enter the atmosphere from other sources. Noise pollution will not exceed that obtained from the Saturn 5 launch vehicle.

Source record↗
NASA NTRS1972

Space shuttle: Aerodynamic characteristics of a double delta wing space shuttle orbiter (M equals 0.6 - 5.0)

This test program was the first wind tunnel investigation of a double delta wing space shuttle orbiter. The 0.004 scale model used for this test was the first model constructed of this configuration and as such lacked certain refinements incorporated in later models, the principal differences being that the wing is located 0.1 inches model scale further forward than later models and that the nose contours are slightly different.

Ellis, R. R.↗
NASA NTRS1972

Space shuttle: A comparison of wind tunnel facility data on the 040A space shuttle orbiter configuration

A series of comparisons made on the longitudinal and lateral directional stability and control characteristics of the baseline 040A space shuttle orbiter configuration is documented. The data used for the comparisons were obtained from five wind tunnel tests conducted in four different wind tunnel facilities. The media for comparison were the aerodynamic slope values plotted as a function of Mach number for the different facilities. The slopes were computed using the SADSAC system and have been reduced relative to a common reference system. Data used for the comparison were selected based on a common baseline configuration. Identical configurations were available in all cases except MSFC 551 where an off-baseline vertical tail was tested. Some of the factors considered in comparing the various data were balance operating ranges and sensitivities, Reynolds number differences, scaling effects and control deflection accuracies.

Gyorfi, R. A.↗
NASA NTRS1972

Manned space flight nuclear system safety. Volume 6: Space base nuclear system safety plan

A qualitative identification of the steps required to assure the incorporation of radiological system safety principles and objectives into all phases of a manned space base program are presented. Specific areas of emphasis include: (1) radiological program management, (2) nuclear system safety plan implementation, (3) impact on program, and (4) summary of the key operation and design guidelines and requirements. The plan clearly indicates the necessity of considering and implementing radiological system safety recommendations as early as possible in the development cycle to assure maximum safety and minimize the impact on design and mission plans.

Source record↗