Final results of the XLR129 program
Design, engineering mockup, and performance tests on XLR129 reusable rocket engine
Atherton, R. R.↗
SEARCH · Engineering Papers
Results for “Reusability”
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.
Scheduling technique improvement study for advanced programs. Volume 2: Stage 2 advanced space transport program
Scheduling techniques for manned, reusable orbiting transport vehicle stage of advanced space program
Crain, D. P.↗
Scheduling technique improvement study for advanced programs. Volume 3: Stage 1 advanced space transport program
Schedules and logic diagrams of manned reusable boost vehicle for advanced space transport program
Crain, D. P.↗
Current status of the Space Shuttle
Economical reusable space shuttle development for cargo and passenger transportation to and from orbit
Swigert, J. L.↗
Space shuttle
Two stage space shuttle, discussing NASA reusable spacecraft cost reduction and technological problems
Tischler, A. O.↗
NASA's space tug and hydrogen oxygen auxiliary propulsion
Space based reusable manned/unmanned tug, discussing potential missions, system requirements and auxiliary hydrogen oxygen propulsion system
Burke, J. R.↗
Supply and resupply of stations in synchronous orbit
Logistics system for synchronous orbit space stations supply, discussing parking to synchronous orbit transfer of reusable and disposable logistics vehicles
Dugan, D. W.↗
Pratt and Whitney Aircraft's space shuttle main engine
Space shuttle main engine based on high pressure, staged combustion, reusable, minimum risk and low cost concepts
Mulready, R. C.↗
The economics of a new space transportation system
NASA space transporation system economics, discussing cost analytic considerations in comparing reusable vs expendable launch systems
Lindley, R. N.↗
Space shuttle booster wing geometry trade studies
Canard space shuttle reusable launch vehicle wing geometry variations effect on flyback systems weight, noting influence of aspect ratio and wing area
Butsko, J. E.↗
Space transportation report
Two stage reusable space shuttle system for space transportation program, discussing budget, development and testing, international cooperation and information exchange
Myers, D. D.↗
Optimal round trip space tug trajectories for earth escape missions
Reusable space tug payload injection missions, determining optimal round trip trajectories at earth escape energy levels
Teren, F.↗
Quick release acoustic sensor holding fixture
Quick-release spring holder secures acoustic sensor to test material surface eliminating adhesive bonding to test material and achieving acoustic emission evaluation from tensile tests. Reusability of sensors reduces test cost.
Mcmahon, W.↗
Study of space shuttle environmental control and life support problems
Four problem areas were treated: (1) cargo module environmental control and life support systems; (2) space shuttle/space station interfaces; (3) thermal control considerations for payloads; and (4) feasibility of improving system reusability.
Dibble, K. P.↗
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.↗
Investigation of thermal protection systems effects on viscid and inviscid flow fields for manned entry systems
Procedures and methods for predicting aerothermodynamic heating to delta orbiter shuttle vehicles were reviewed. A number of approximate methods were found to be adequate for large scale parameter studies, but are considered inadequate for final design calculations. It is recommended that final design calculations be based on a computer code which accounts for nonequilibrium chemistry, streamline spreading, entropy swallowing, and turbulence. It is further recommended that this code be developed with the intent that it can be directly coupled with an exact inviscid flow field calculation when the latter becomes available. A nonsimilar, equilibrium chemistry computer code (BLIMP) was used to evaluate the effects of entropy swallowing, turbulence, and various three dimensional approximations. These solutions were compared with available wind tunnel data. It was found study that, for wind tunnel conditions, the effect of entropy swallowing and three dimensionality are small for laminar boundary layers but entropy swallowing causes a significant increase in turbulent heat transfer. However, it is noted that even small effects (say, 10-20%) may be important for the shuttle reusability concept.
Bartlett, E. P.↗
Spaceborne computer executive routine functional design specification. Volume 2: Computer executive design for space station/base
The computer executive functional system design concepts derived from study of the Space Station/Base are presented. Information Management System hardware configuration as directly influencing the executive design is reviewed. The hardware configuration and generic executive design requirements are considered in detail in a previous report (System Configuration and Executive Requirements Specifications for Reusable Shuttle and Space Station/Base, 9/25/70). This report defines basic system primitives and delineates processes and process control. Supervisor states are considered for describing basic multiprogramming and multiprocessing systems. A high-level computer executive including control of scheduling, allocation of resources, system interactions, and real-time supervisory functions is defined. The description is oriented to provide a baseline for a functional simulation of the computer executive system.
Kennedy, J. R.↗
Space shuttle phase B extension, volume 1
In order to define a system which would significantly reduce payload delivery costs, activities were extended to modifications of the reusable space shuttle design concept. Considered were systems using orbiters with external propellant tanks and an interim expendable booster which allowed phased development of the usable orbiter and booster. Analyzed were: Merits of internal and external propellant tanks and the impact of external LH2 compared to L02 and LH2; impact of cargo bay size; impact abort; merit of expendable booster options; and merit of a phased development program. Studies showed that external L02/LH2 and the continued use of the J-2S engine on the orbiter reduced program cost and risk.
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