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Results for “Earth-to-Orbit Transportation”

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
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NASA NTRS1979

Use of a duct-burning turbofan for an earth-to-orbit vehicle booster

The Space Shuttle will soon reduce the cost of transportation to orbit. The resulting traffic growth will lead to economic pressure for a new vehicle. Several vehicles have been studied. A supersonically staged system with twin turbojet boosters may be attractive but the development of a large supersonic turbojet engine would be required. Subsonic staging with a reasonable number of turbojet engines does not provide the desired payload capability with existing engines. The addition of a duct burner to an existing large turbofan engine provides sufficient thrust to allow the design of an attractive system with twin boosters staged subsonically.

Martin, J. A.↗
NASA NTRS1986

Advanced manned earth-to-orbit vehicle

Advanced manned launch vehicle concepts which are designed to meet the space transportation architecture and mission needs for the early 21st century are described. Concepts are described which are based both on modest (evolutionary) and revolutionary advancements in performance technologies but with emphasis on defining operations cost. Design options feature fully reusable, vertical-takeoff, horizontal-landing, rocket-powered concepts and include a variety of possible staging arrangements depending on the desired mission emphasis and the available technologies.

Eldred, Charles H.↗
NASA NTRS1990

Space Station requirements and transportation options for lunar outpost

Preliminary design studies conducted by NASA are summarized which determined the requirements of the Space Station Freedom and transportation options for the establishment of a lunar outpost. Three phases are defined - emplacement, consolidation, and utilization - to describe the gradual development of the outpost. The lunar transportation system is based on the use of an earth-to-orbit and an LEO-lunar surface system for moving vehicles, propellant, crew, and cargo to the outpost. The vehicle-design and size requirements are defined for the reusable lunar-transfer vehicle and the lunar-excursion vehicle. Space Station Freedom is established as the LEO transportation node which transfers the required payloads to the excursion spacecraft following a 300-km low lunar orbit. The proposed lunar excursion vehicle is theorized to be capable of delivering 33 tons of cargo to the surface of the moon in the cargo-expendable mode.

Young, Archie C.↗
NASA NTRS1990

Technologies for aerobraking

Aerobraking is one of the largest contributors to making both lunar and Mars missions affordable. The use of aerobraking/aeroassist over all-propulsive approaches saves as much as 60 percent of the initial mass required in LEO, thus reducing the number and size of earth-to-orbit launch vehicles. Lunar transfer vehicles, which will be used to transport personnel and materials from LEO to lunar outposts, will aerobrake into earth's atmosphere at aproximately 11 km/sec on return from the lunar surface. Current plans for both manned and robotic missions to Mars use aerocapture during arrival at Mars and at earth return. At Mars, the entry velocities will range from about 6 to 9.5 km/sec, and at earth the return velocity will be about 12.5 to 14 km/sec. In order to successfully design aerobrakes to withstand the aerodynamic forces and heating associated with these entry velocities, as well as to make them efficient, several critical technologies must be developed. These are vehicle concepts and configurations, aerothermodynamics, thermal protection system materials, and guidance, navigation, and control systems. This paper describes the status of each of these technologies and outlines what must be accomplished in each area to meet the requirements of the Space Exploration Initiative.

Cooper, David M.↗
NASA NTRS1979

Economic and programmatic considerations for advanced transportation propulsion technology

Requirements for space transportation will increase after the Space Shuttle becomes operational. Shuttle derivatives and new earth-to-orbit vehicles are compared economically. The addition of both one and two new vehicle types are considered. Programmatic considerations are included in deriving a scenario which appears reasonable and includes the Space Shuttle, a heavy-lift cargo derivative of the Shuttle, a unique dual-fuel orbit transfer vehicle, and a small new earth-to-orbit vehicle in the foreseeable future. Large new orbital transfer and earth-to-orbit vehicles would be added when needed.

Martin, J. A.↗
NASA NTRS1978

Propulsion options for space-based orbital transfer vehicles

A concept for a lightweight space-based orbital transfer vehicle (OTV) featuring thin, spherical, pressure-designed aluminum liquid-oxygen and liquid-hydrogen tanks and a truss structure of composite materials is used as a baseline design for a large-cargo OTV. Vehicle sizing, fleet analysis, and parametric cost analysis are used to evaluate the effects of engine technology, vehicle staging, and high-thrust versus low-thrust transfer. Results indicate that Earth-to-orbit launch costs and OTV engine performance are strong drivers in orbital transportation cost and that there is no significant benefit in staging vehicles. At the low values of Earth-to-orbit cost representative of advanced launch vehicles, low-thrust and high-thrust OTV's are competitive.

Rehder, J. J.↗
NASA NTRS1988

Earth transportation node requirements and design

The objective of this paper is to establish the requirements for an inhabited earth orbiting transportation node and to develop design concepts for such a facility. The use of an earth orbiting transportation node is required to support many of the space flight projects proposed for the beginning of the 21st century. The requirements for such an orbiting facility are derived from the missions which they support. Future missions investigated include automated and human exploration of the solar system, support of a lunar base, and missions to planet earth. Design concepts are presented for transportation nodes based on a variation of the current Space Station Freedom design. Designs accommodate a variety of earth-to-orbit, orbit-to-orbit, and deep-space probe transportation systems. Finally, the technology needed to develop such a transportation node is summarized.

Hook, W. Ray↗
NASA NTRS1988

Space shuttle main engine monitoring experience and advanced monitoring systems development

Advanced space transportation systems must provide improved availability, reliability, safety, and reduced cost in order to make a new, more vigorous level of space activity economically feasible. Earth-to-Orbit (ETO) propulsion monitoring systems are a major factor in progress toward these improvements, and in the success of current systems. Operational experience with the Space Shuttle Main Engine (SSME), the first reusable ETO rocket engine, is valuable for examining current rocket engine monitoring capability and technology developments. Here, Space Shuttle Main Engine (SSME) monitoring practice and experience are surveyed. Unique aspects of rocket engine mission requirements are highlighted to provide improved understanding of engine monitoring practices and technology needs. Current ETO engine transportation systems mission needs are outlined. With this foundation, the techniques and components addressed within current technology programs are discussed to complete a picture of ETO propulsion monitoring status and development.

Cikanek, Harry A.↗
NASA NTRS1989

Earth-to-orbit propulsion for the 21st century

This paper presents an overview of NASA's liquid and solid rocket and air-breathing propulsion research programs along with some recent accomplishments. Attention is focused on two contrasting, but complementary, space transportation system elements. One is directed toward the unmanned delivery of massive and/or bulky 'space cargo' to low earth orbit. The other is tailored to the transportation of humans and light priority cargo in smaller manned piloted vehicles.

Rosen, Robert↗
NASA NTRS1988

Advanced Earth-to-orbit propulsion technology program overview: Impact of civil space technology initiative

The NASA Earth-to-Orbit (ETO) Propulsion Technology Program is dedicated to advancing rocket engine technologies for the development of fully reusable engine systems that will enable space transportation systems to achieve low cost, routine access to space. The program addresses technology advancements in the areas of engine life extension/prediction, performance enhancements, reduced ground operations costs, and in-flight fault tolerant engine operations. The primary objective is to acquire increased knowledge and understanding of rocket engine chemical and physical processes in order to evolve more realistic analytical simulations of engine internal environments, to derive more accurate predictions of steady and unsteady loads, and using improved structural analyses, to more accurately predict component life and performance, and finally to identify and verify more durable advanced design concepts. In addition, efforts were focused on engine diagnostic needs and advances that would allow integrated health monitoring systems to be developed for enhanced maintainability, automated servicing, inspection, and checkout, and ultimately, in-flight fault tolerant engine operations.

Stephenson, Frank W., Jr.↗
NASA NTRS1990

An infrastructure assessment of alternative Mars Transfer Vehicles

Development and evolutionary paths for many space transportation elements must be considered as the United States space program embarks on the Space Exploration Initiative (SEI). A central element of the space transportation infrastructure necessary to support the SEI is Mars Transportation System (MTS). This system consists of the Mars Transfer Vehicle (MTV) and Mars Excursion Vehicle. This paper describes the process and results in evaluating the alternate MTV propulsion concepts. Primary discriminators in evaluating different options for the MTV alternatives are: requirements for earth-to-orbit delivery, on-orbit facility and assembly requirements, and mission performance. Propulsion candidates assessed in this paper include nuclear thermal propulsion, nuclear electric propulsion, solar electric propulsion, and cryogenic chemical propulsion (LO2/LH2). The primary discriminators as well as additional selection criteria will be discussed for each MTS alternative.

Holdridge, Jeffrey D.↗
NASA NTRS1990

Fiber-reinforced ceramic composites for Earth-to-orbit rocket engine turbines

Fiber reinforced ceramic matrix composites (FRCMC) are emerging materials systems that offer potential for use in liquid rocket engines. Advantages of these materials in rocket engine turbomachinery include performance gain due to higher turbine inlet temperature, reduced launch costs, reduced maintenance with associated cost benefits, and reduced weight. This program was initiated to assess the state of FRCMC development and to propose a plan for their implementation into liquid rocket engine turbomachinery. A complete range of FRCMC materials was investigated relative to their development status and feasibility for use in the hot gas path of earth-to-orbit rocket engine turbomachinery. Of the candidate systems, carbon fiber-reinforced silicon carbide (C/SiC) offers the greatest near-term potential. Critical hot gas path components were identified, and the first stage inlet nozzle and turbine rotor of the fuel turbopump for the liquid oxygen/hydrogen Space Transportation Main Engine (STME) were selected for conceptual design and analysis. The critical issues associated with the use of FRCMC were identified. Turbine blades were designed, analyzed and fabricated. The Technology Development Plan, completed as Task 5 of this program, provides a course of action for resolution of these issues.

Brockmeyer, Jerry W.↗
NASA NTRS1974

Development of large earth orbital space station

This paper outlines the major aspects of the development of large earth orbital space stations. At the outset, the uses of the space station are surveyed and the major systems and configurational drivers enumerated. A representative 12-man space station, studied by the Space Division of North American Rockwell Corporation under NASA contract is described. The subsequent discussion centers around earth-to-orbit logistics and possible future missions with emphasis on the establishment of a branch station geosynchronous orbit. In dealing with the associated transportation between low and high orbits, the concept of a geospace shuttle station oscillating between near-earth and synchronous orbit is compared with conventional shuttle vehicles with chemical and nuclear propulsion. In the final part, the evolution of the 12-man space station to a larger space base is described.

Ehricke, K. A.↗
NASA NTRS1981

Advanced oxygen-hydrocarbon Earth-to-orbit propulsion

Liquid oxygen/hydrocarbon (LO2/HC) rocket engine cycles for a surface to orbit transportation system were evaluated. A consistent engine system data base is established for defining advantages and disadvantages, system performance and operating limits, engine parametric data, and technology requirements for candidate engine systems. Preliminary comparisons of the engine cycles utilizing delivered specific impulse values are presented. Methane and propane staged combustion cycles are the highest LO2/HC performers. The hydrogen cooled LO2/methane dual throat engine was found to be the highest performing. Technology needs identified in the study include: high temperature turbines; oxidizer-rich preburners; LO2, methane, and propane cooling; methane and propane fuel-rich preburners; the HC fuel turbopump; and application of advanced composite materials to the engine system. Parametric sensitivity analysis data are displayed which show the effect of variations in engine thrust, mixture ratio, chamber pressure, area ratio, cycle life, and turbine inlet temperature on specific impulse and engine weight.

Obrien, C. J.↗
NASA NTRS1982

System design concepts and requirements for aeroassisted orbital transfer vehicles

The Orbital Transfer Vehicle (OTV) is an advanced upper stage concept which will deliver spacecraft from operating systems at Low Earth Orbit (LEO) such as Space Shuttle, Earth-To-Orbit (ETO) vehicles, and Space Operations Center (SOC), to High Earth Orbit (HEO) and planetary excursions. The OTV will be driven by the need to achieve significant reductions in the operational costs for delivering payloads to Geostationary Equatorial Orbit (GEO). Aeroassist is a technological capability that has a potential for OTV's ranging from mission enhancing (reusable OTV for payload delivery) to mission enabling (manned GEO and some DOD). It is shown that the use of aeroassist for OTV's is a high leverage technology which can potentially reduce space transportation costs and enable a number of highly desirable missions.

Austin, R. E.↗
NASA NTRS1986

Status of advanced propulsion for space based orbital transfer vehicle

A new Orbital Transfer Vehicle (OTV) propulsion system will be required to meet the needs of space missions beyond the mid-1990's. As envisioned, the advanced OTV will be used in conjunction with Earth-to-orbit vehicles, Space Station, and Orbit Maneuvering Vehicle. The OTV will transfer men, large space structures, and conventional payloads between low Earth and higher energy orbits. Space probes carried by the OTV will continue the exploration of the solar system. When lunar bases are established, the OTV will be their transportation link to Earth. NASA is currently funding the development of technology for advanced propulsion concepts for future Orbital Transfer Vehicles. Progress in key areas during 1986 is presented.

Cooper, L. P.↗
NASA NTRS1986

Status of advanced propulsion for space based orbital transfer vehicle

A new Orbital Transfer Vehicle (OTV) propulsion system will be required to meet the needs of space missions beyond the mid-1990's. As envisioned, the advanced OTV will be used in conjunction with earth-to-orbit vehicles, Space Station, and Orbit Maneuvering Vehicle. The OTV will transfer men, large space structures, and conventional payloads between low earth and higher energy orbits. Space probes carried by the OTV will continue the exploration of the solar system. When lunar bases are established, the OTV will be their transportation link to earth. NASA is currently funding the development of technology for advanced propulsion concepts for future Orbital Transfer Vehicles. Progress in key areas during 1986 is presented.

Cooper, Larry P.↗