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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 307 records · Page 17
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NASA NTRS1998

Solar Powered Propulsion for Space. (Latest citations from the Aerospace Database)

The bibliography contains citations concerning the design, development, and performance of solar propulsion systems. Solar electric propulsion and solar thermal propulsion are reviewed. Topics include solar power satellites, nuclear electric propulsion, solar-powered orbit transfer vehicles, and solar dynamic and bimodal power systems. References also discuss atmospheric pollution control, telephone services, space commercialization, interplanetary missions, and lunar and Mars exploration. (Contains 50-250 citations and includes a subject term index and title list.)

BIBLIOGRAPHIES↗
NASA NTRS1999

Solar Power System Analyses for Electric Propulsion Missions

Solar electric propulsion (SEP) mission architectures are applicable to a wide range of NASA missions including human Mars exploration and robotic exploration of the outer planets. In this paper, we discuss the conceptual design and detailed performance analysis of an SEP stage electric power system (EPS). EPS performance, mass and area predictions are compared for several PV array technologies. Based on these studies, an EPS design for a 1-MW class, Human Mars Mission SEP stage was developed with a reasonable mass, 9.4 metric tons, and feasible deployed array area, 5800 sq m. An EPS was also designed for the Europa Mapper spacecraft and had a mass of 151 kg and a deployed array area of 106 sq m.

Kerslake, Thomas W.↗
NASA NTRS2003

Exploring the Solar System

This viewgraph presentation reviews a number of advanced propulsion technologies for interplanetary spacecraft. The objective of the In Space Propulsion Technology Projects Office is to develop in-space propulsion technologies that can enable and/or benefit near and mid-term NASA science missions by significantly reducing cost, mass, and/or travel times. The technologies profiled are divided into several categories: High Priority (aerocapture, next generation ion propulsion, solar sails); Medium Priority (advanced chemical propulsion, solar electric propulsion, Hall thrusters); Low Priority (solar thermal propulsion); and High Payoff/High Risk (1 g/sq m solar sails, momentum exchange tethers, and plasma sails).

Les Johnson↗
NASA NTRS2006

In-Space Propulsion Technologies for Robotic Exploration of the Solar System

Supporting NASA's Science Mission Directorate, the In-Space Propulsion Technology Program is developing the next generation of space propulsion technologies for robotic, deep-space exploration. Recent technological advancements and demonstrations of key, high-payoff propulsion technologies have been achieved and will be described. Technologies under development and test include aerocapture, solar electric propulsion, solar sail propulsion, and advanced chemical propulsion.

Johnson, Les↗
NASA NTRS1977

Report of the Terrestrial Bodies Science Working Group. Volume 2: Mercury

The objectives and rationale for scientific investigation of Mercury are explored. Knowledge already obtained by astronomical observations and Mariner 10 spacecraft is reviewed and measurements required for the principal scientific goals are described. The use of low thrust propulsion systems is recommended so that maximum scientific return may be achieved and the reconnaissance phase of Mercury exploration may be completed in a single mission. Accelerated development is recommended on solar electric propulsion, solar sails, passive and active cooling mechanisms, and single rough landers.

Albee, A. L.↗
NASA NTRS1981

Zero gravity testing of flexible solar arrays

Zero gravity testing in the KC-135 aircraft of flat fold flexible solar array test specimens sufficiently demonstrated the adequacy of the panel design. The aircraft flight crew provided invaluable assistance and significantly contributed to the design and development of the flexible solar array, and ultimately to the potential success of the solar electric propulsion solar array shuttle flight experiment program.

Chung, D. T.↗
NASA NTRS1987

A comet nucleus sample return mission

A joint ESA/NASA proposal for the acquisition and delivery of samples of the cometary nucleus is considered, and the importance of such samples in providing input as to the origin of the solar system is underlined. Mission options employing all-chemical propulsion, solar electric propulsion, and a combination of the two are explored in detail. Conceptual spacecraft designs have been developed and mass performance estimates made for a wide range of possible targets. The importance of the use of some form of aerobraking during return to earth is noted. Methods for acquiring the nuclear samples are discussed, and characteristics of the mission operations are reviewed.

Kerridge, Stuart J.↗
NASA NTRS2001

Deep Space 1: Testing New Technologies for Future Small Bodies Missions

Launched on October 24, 1998, Deep Space 1 (DS1) was the first mission of NASA's New Millennium Program, chartered to validate in space high-risk, new technologies important for future space science programs. The advanced technology payload that was tested on DS1 comprises solar electric propulsion, solar concentrator arrays, autonomous on-board navigation and other autonomous systems, several telecommunications and microelectronics devices, and two low-mass integrated science instrument packages. The mission met or exceeded all of its success criteria. The 12 technologies were rigorously exercised so that subsequent flight projects would not have to incur the cost and risk of being the fist users of these new capabilities. Examples of the benefits to future small body missions from DS1's technologies will be described.

Deep Space 1 (DS1)↗
NASA NTRS2017

Interplanetary Trajectories for Ice Giant Mission Concepts

Interplanetary Trajectory options for missions to Uranus and Neptune, launching between 2025 and 2037, are presented. Trajectories using Chemical Propulsion, Solar Electric Propulsion and Radioisotope Thermoelectric Generator Electric Propulsion, with up to four planetary flybys are investigated. The effect of different launch vehicles with or without an optimal kick stage, on flight time, inserted mass and propellant throughput, is quantified. To enable simultaneous exploration of both planets, dual-spacecraft trajectories that deliver one spacecraft to each planet from a single launch, are presented. Attractive trajectories and mission opportunities for different multi-element mission architectures are presented.

Arora, Nitin↗
NASA NTRS1974

Thermal and structural integration problems associated with primary electric propulsion

A typical solar electric propulsion (SEP) spacecraft design which meets challenges posed by the physical characteristics of SEP and by the operational and environmental requirements associated with missions for which SEP is advantageous is used to develop structural and thermal integration requirements which are important to the successful design of electric propulsion elements. Included are discussions on thruster and power processor thermal and structural integration requirements and the definition of representative environmental requirements. Next, an improved power processor packaging concept, referred to as dual shear plate packaging, is described and shown to meet these requirements. Continued development of a two-axis-gimbal thruster array is also described. This concept demonstrates the successful thermal and structural integration of thrusters, propellant feed system, and thrust-vector-control actuators into a modular thrust assembly which meets the needs of a broad range of missions and possible vehicle configurations. Details of this design concept are presented.

Ross, R. G., Jr.↗
NASA NTRS1990

Advanced propulsion options for the Mars cargo mission

Several advanced propulsion options for a split-mission piloted Mars exploration scenario are presented. The primary study focus is on identifying concepts that can reduce total initial mass in low earth orbit (IMLEO) for the cargo delivery portion of the mission; in addition, concepts that can reduce the trip time of the piloted option are assessed. The propulsion options considered are nuclear thermal propulsion, solar sails, multimegawatt-class nuclear electric propulsion, solar electric propulsion, magnetic sails, mass drivers, rail guns, solar thermal rockets, beamed-energy propulsion systems, and tethers. For the cargo mission, solar sails are found to provide the greatest mass savings over the baseline chemical system, although they suffer from having very long trip times; a good performance compromise between a low IMLEO and a short trip time can be obtained using multimegawatt-class nuclear electric propulsion systems.

Frisbee, Robert H.↗
NASA NTRS2006

Implementation of a Low-Thrust Trajectory Optimization Algorithm for Preliminary Design

A tool developed for the preliminary design of low-thrust trajectories is described. The trajectory is discretized into segments and a nonlinear programming method is used for optimization. The tool is easy to use, has robust convergence, and can handle many intermediate encounters. In addition, the tool has a wide variety of features, including several options for objective function and different low-thrust propulsion models (e.g., solar electric propulsion, nuclear electric propulsion, and solar sail). High-thrust, impulsive trajectories can also be optimized.

optimization↗
NASA NTRS2018

Integrated Optimization of Mars Hybrid Solar-Electric/Chemical Propulsion Trajectories

NASA’s Human Exploration and Operation Mission Directorate is developing a reusable hybrid transportation architecture in which both chemical and solar-electric propulsion systems are used to deliver crew and cargo to the Martian sphere of influence. By combining chemical and solar-electric propulsions into a single spacecraft and applying each where it is the most effective, the hybrid architecture enables a series of Mars trajectories that are more fuel efficient than an all chemical propulsion architecture without significant increase to trip time. Solving the complex problem of low-thrust trajectory optimization coupled with the vehicle sizing requires development of an integrated trajectory analysis frame- work. Previous studies have utilized a more segmented optimization framework due to the limitation of the tools available. A new integrated optimization framework was recently developed to address the deficiencies of the previous methods that enables higher fidelity analysis to be performed and increases the efficiency of large design space explorations.

Chai, Patrick R.↗