Thermostructural analysis of three structural concepts for reusable space vehicles

Taylor, Arthur C.; Jackson, L. R.

doi:10.2514/6.1979-874

Cited by 9 publications

(6 citation statements)

References 2 publications

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“…TPS system concepts (Fig. 9) that may be used for hypersonic transportation (both HST and TAV/ATAV) have been verified by rigorous tests at temperatures beyond 1500 K [22,23].…”

Section: Materials Structures and Thermal Protectionmentioning

confidence: 95%

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Advanced Hypersonic Transportation Perspectives

Gopalaswami

2023

joast

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High-speed transportation design concepts are examined for advanced civil aviation and space transportation applications. The design concept of transatmospheric vehicles, flying directly from earth to orbit, will enable launching and recovery of small telecommunication and remote sensing satellites, harvesting solar energy from space, and space tourism.Commonality of flight regimes in atmospheric flight, the similarity of fuels, propulsion technology, aerodynamic configuration design, and airframe structure materials used in these high-speed flight regimes for air and space transportation are discussed in detail.A single, Integrated Hypersonic Transport Programme, is recommended, based on small size, low risk, and low cost vehicles. A dual fuel, kerosene-hydrogen system meets the needs of such an Integrated Hypersonic Transportation Programme, with kerosene for take-off, powered landing and low speed ascent/descent flight. Hydrogen is used for high-speed cruise flight. India would greatly benefit by an Integrated Hypersonics Transportation Programme, with leading institutions like ISRO, NAL and ADA working together to jointly study, design and build a strong technology base for small, unmanned hypersonic flight demonstrators. This project could then lead on, safely and economically, to hypersonic Executive Jet aircraft, and small fully Reusable Trans-Atmospheric Vehicles for direct ascent of the hypersonic aerospacecraft to earth orbit.

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“…TPS system concepts (Fig. 9) that may be used for hypersonic transportation (both HST and TAV/ATAV) have been verified by rigorous tests at temperatures beyond 1500 K [22,23].…”

Section: Materials Structures and Thermal Protectionmentioning

confidence: 95%

“…Typical optimized thermostrucutural design solutions for the critcal Integral Hydrogen Fuel Tank of a HST/TAV are shown in Fig. 11 [22].…”

Section: Unit Mass Of Optimised Thermostructural Systemsmentioning

confidence: 99%

Advanced Hypersonic Transportation Perspectives

Gopalaswami

2023

joast

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“…was used to represent the heat sink capacity of the vehicle structure. 7 The back surface of the structure was in all cases assumed to be adiabatic (no active cooling was considered). The initial temperature throughout the surface was assumed to be 3UK (100°F), a value shown in previous studies to be consistent with typical vehicle attitude, orbital inclinations, and thermal control on orbit.…”

Section: Methods Of Analysismentioning

confidence: 99%

“…For use as a primary structure, L-605 was assumed to have a maximum temperature capability of 1089K (1500°F), corresponding to the temperature at which the material retains about 40% of its room-temperature mechanical properties. The Ren£ 41 honeycomb mass per unit area was determined from previous studies, 7 and the values for other metallic systems were again related to this value based upon their strength-to-density ratios at operating temperature. The sizing criteria for the Ren£ 41 hot structure and the aluminum cold structure should be consistent as they were derived from the same study.…”

Section: Materials Considerationsmentioning

confidence: 99%

Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design

Wurster

1983

Journal of Spacecraft and Rockets

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The study described in this paper examines the impact of thermostructural/trajectory design integration on advanced-winged entry vehicle mass. A variety of thermal protection system (TPS) concepts are considered, and entry trajectories tailored specifically to each concept in terms of peak heat rate and total heat load are used in conjunction with an aerodynamic heating/thermal analysis program to determine the TPS requirements. Results indicate that for an aluminum structure, either the reusable surface insulation (RSI) or the hybrid TPS (RSI forward, Ren£ 41 metallic standoff aft) has the potential to yield the lowest mass system. The metallic standoff system is, however, quite competitive and, with the 25% reduction in the panel mass anticipated, could surpass the RSI system. Results also indicate that significant improvements in hot-structure design are necessary before such a system can become competitive. An assessment is made of the potential impact of higher temperature structure materials on combined TPS/structure mass. Results indicate that the greatest reduction in mass is obtained with the first 200K increase in temperature capability over that of aluminum and, thus, the potential for the lowest mass system appears to lie with either a graphite/polyimide or a titanium structure.Nomenclature lift coefficient specific heat at constant pressure, J/kg • K acceleration due to gravity, m/s 2 altitude, km thermal conductivity, W/m-K vehicle length, m lift-to-drag ratio reference heat rate, kW/m 2 reference heat load, MJ/m 2 thickness, cm temperature, K Earth-relative velocity, m/s body centerline location, m angle of attack, deg density, kg/m 3 ultimate tensile strength, kN/m 2

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“…10, have been the subject of a recent analytical study. 50 All of the concepts have been sized for a horizontal takeoff, turbojet-boosted spacejet application. The concept, which uses closed-cell organic form to perform the allimportant function of eliminating cryopumping, is the heaviest of the three and represents the current state-of-theart.…”

Section: Tankage Structuresmentioning

confidence: 99%

Research in structures and materials for future space transportationsystems - An overview

Kelly

Rummler

Jackson

1983

Journal of Spacecraft and Rockets

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This paper provides a review of some of the advances of the past decade in structures and materials that have application to future space transportation systems. The paper concentrates on metallic thermal protection systems and structures that could provide the structural efficiency, reliability, and durability dictated by future space utilization requirements. The need for completely reusable, onboard cryogenic fuel tanks is cited as the most challenging technical opportunity, and potential thermostructural concepts for tanks are identified. Other critical areas needing technology advances are discussed. Finally, the unique research opportunities offered by the Shuttle Orbiter experiments program for testing structures and thermal protection systems are explored.

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Thermostructural analysis of three structural concepts for reusable space vehicles

Cited by 9 publications

References 2 publications

Advanced Hypersonic Transportation Perspectives

Advanced Hypersonic Transportation Perspectives

Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design

Research in structures and materials for future space transportationsystems - An overview

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