Advanced propulsion for the XXIst century
This paper presents an overview of advanced space propulsion concepts and their research activities at the beginning of the 21st Century.
advanced propulsion↗
Engineering topics
Frisbee, R. H.
Publications and source records attributed to Frisbee, R. H..
Solar sails for Mars cargo missions
This paper presents an analysis of solar sails for the Mars cargo mission.
solar↗
Interstellar travel : challenging propulsion and power technologies for the next 50 years
This paper will propose one vision for an interstellar program. It will include a discussion of mission concepts as well as technological requirements for accomplishing those missions.
interstellar↗
Oxygen-Propellant Plasma Thrusters for Cis-Lunar Electric Propulsion Missions
This paper presents an analysis of the mission benefits and technology requirements of electric propulsion thrusters designed to use oxygen (O2) as propellant, and an overview of the status of current research in this area.
plasma↗
Evaluation of Propulsion Options for Interstellar Missions
This paper describes an evaluation of various propulsion options for robotic interstellar rendezvous missions to stars ranging from 4.5 Light Years (L.Y.) with a 10-Year trip time, to 40 L.Y. with a 100-Year trip time.
Propulsion↗
The NASA Advanced Propulsion Concepts at the Jet Propulsion Laboratory
Research activities in advanced propulsion concepts at the Jet Propulsion Laboratory are reviewed. The concepts were selected for study because each offers the potential for either significantly enhancing space transportation capability or enabling bold, ambitious new missions.
plasma thrusters advanced propulsion↗
Inflatable Solar Sails for Low-Cost Robotic Mars Missions
This paper presents an evaluation of the use of solar sails based on inflatable-structures technologies to perform low-cost robotic planetary missions.
low-cost↗
Power Processing Units for High Powered Solar Electric Propulsion Using MPD Thrusters
The power of various multimegawatt (MMW) vehicles required for deep space missions such asthe Mars Missions in the stipulated time frame of years 2000-2015 ranges from 5 to 100 MWe. Thispaper summarizes an evaluation of high-power processing units (PPUs) for MMW solar electricpropulsion (SEP) vehicles using advanced magnetoplasma- dynamic (MPD) thrusters. Each PPUprovides DC-DC conversion and voltage matching between the phovoltaic power system and the MPDthrusters. The power system consists of DC-DC converter using MCTs. The PPUs are thencombined with contractors to provide PPU input and output isolation, and to allow switching betweenoperating and spare (redundant) PPUs and thrusters as needed. Based on analyses, it is found thatsignificant economies of scale are possible for PPUs that supply power to MPD thrusters operating at0.1 to 5 MWe per thruster.
Frisbee, R. H.↗
Mass and power estimates for Mars in-situ propellant production systems
An in-situ propellant production (ISPP) concept, a method for producing oxygen from carbon dioxide in the Martian atmosphere, is evaluated. The concept considered here employs zirconia membrane technology to separate O2 from CO2. Several options which can improve the reliability of the CO2/O2 ISPP system and also reduce the mass and power requirements are examined, and it is noted that the use of absorption pumps and advanced zirconia membranes significantly improves system reliability by eliminating the rotating turbomachinery of mechanical pumps. Mass and power requirements of ISPP systems designed to produce O2 only from CO2 (for an unmanned Mars mission) and to produce both CO and O2 from CO2 (for a manned Mars mission) are evaluated.
Frisbee, R. H.↗
Analysis of flow decay potential on Galileo
The risks posed to the NASA's Galileo spacecraft by the oxidizer flow decay during its extended mission to Jupiter is discussed. The Galileo spacecraft will use nitrogen tetroxide (NTO)/monomethyl hydrazine bipropellant system with one large engine thrust-rated at a nominal 400 N, and 12 smaller engines each thrust-rated at a nominal 10 N. These smaller thrusters, because of their small valve inlet filters and small injector ports, are especially vulnerable to clogging by iron nitrate precipitates formed by NTO-wetted stainless steel components. To quantify the corrosion rates and solubility levels which will be seen during the Galileo mission, corrosion and solubility testing experiments were performed with simulated Galileo materials, propellants, and environments. The results show the potential benefits of propellant sieving in terms of iron and water impurity reduction.
Cole, T. W.↗
Recent concepts in missions to Mars - Extraterrestrial processes
This paper presents some recent concepts in Mars Sample Return (MSR) missions that utilize extraterrestrial resources. The concepts examined include the power and energy needs of this mission. It is shown that solar energy is not especially attractive. Radioisotopic power generator and a Rankine cycle use are seen to be viable options. Quantitative estimates, taking into consideration state-of-the-art and projected technologies indicate that the power/energy per se is not critical to the mission - but reliability is. Hence, various modern options for the components of the power generation and utilization are discussed. The dramatic savings in Shuttle (or other) vehicle launches are quantitatively plotted. The basic system that is discussed here is the production of hydrocarbon (methane) fuel and oxygen from Martian atmosphere. For the simplest mission, it is seen that earth-carried methane burned with oxygen produced on site provides the best system.
Ramohalli, K. N.↗
Augmenting Thrust With Waste Heat
According to NASA report, energy rejected by nuclear reactor adds to rocket thrust. With augmentation, specific impulse increased by as much as 23 percent over that of conventional engine.
Frisbee, R. H.↗
Laser propulsion for orbit transfer - Laser technology issues
Using reasonable near-term mission traffic models (1991-2000 being the assumed operational time of the system) and the most current unclassified laser and laser thruster information available, it was found that space-based laser propulsion orbit transfer vehicles (OTVs) can outperform the aerobraked chemical OTV over a 10-year life-cycle. The conservative traffic models used resulted in an optimum laser power of about 1 MW per laser. This is significantly lower than the power levels considered in other studies. Trip time was taken into account only to the extent that the system was sized to accomplish the mission schedule.
Horvath, J. C.↗
Laser propulsion for the orbital transfer mission
America's space activities in the 1990s and beyond will partly consist of missions involving the transportation of cargo from low earth orbit (LEO) to higher orbits or to an escape trajectory. Such missions are to be performed with the aid of an orbit transfer vehicle (OTV). The operation of the OTV can be based on different propulsion concepts. A chemical OTV is characterized by a high thrust and low specific impulse. The result is a short trip time at the cost of large quantities of propellant. On the other hand, low-thrust systems such as electric propulsion units, consume very little propellant, but would have a long trip time. The present paper is concerned with a compromise between these two extremes. The employed propulsion system utilizes laser thermal propulsion, in which a ground or space-based laser is used to beam energy to a thruster on the OTV. The laser light is absorbed by a propellant. The resulting heating of the propellant causes an expansion of the propellant through a nozzle to produce thrust. Details regarding this propulsion concept are discussed, taking into account operational questions and missions.
Frisbee, R. H.↗
Should we make products on the moon?
It is pointed out that products from extraterrestrial materials can play a major role in future space operations within the useful lifetime of the first major space station, now in the planning stage. Possible economic advantages regarding the use of such products could be related to the recognition that it takes seven times more energy to get one kilogram from the earth's surface to low earth orbit (LEO) than it does to move one kilogram from the moon's surface to LEO. An analysis regarding the margin of advantage of extraterrestrial materials as been conducted, taking into account equipment and supplies which ust be launched from earth to make the acquisition of extraterrestrial products feasible. The present investigation is concerned with a study of engineering practicality. Attention is given to the transport of processing equipment from LEO to the lunar surface and of lunar products to LEO and the geosynchronous orbit. It is found that lunar oxygen and radiation shielding could possibly be utilized by the turn of the century.
Carroll, W. F.↗
A parametric study of thermally augmented O2/H2 rocket enines
An analysis is presented of the performance of a conceptual propulsion system in which liquid hydrogen and liquid oxygen are first vaporized and heated by thermal power from a spacecraft nuclear electric power supply prior to combustion in a rocket engine. Calculations of the specific impulse (I-sp) are presented for a series of O2/H2 oxidizer-to-fuel mixture ratios and reactant pre-heat temperatures (T-aug). It is found that the ratio of the augmentation power to the total engine jet power (P-aug/P-tot) determines the engine thrust for a given P-aug, T-aug, and I-sp. In addition, the performance of an unaugmented O2/H2 and a heated-hydrogen rocket engine were also calculated for the same conditions. Results show that an augmented O2/H2 engine has three to eight times the thrust of a heated H2 engine for a given P-aug. It is concluded that it should be possible to design a high/low thrust propulsion system using a common propellant, with the option of using thermal power from the nuclear electric power supply to augment the low-thrust propulsion system during cruise periods when the reactor's full electric power is not needed.
Frisbee, R. H.↗
An analysis of propulsion options for transport of lunar materials to earth orbit
This paper describes the results of analyses of space-based transportation systems for the transport of extraterrestrial materials from their point of origin on the lunar surface to final delivery point in earth orbit and transport of equipment and supplies for extraterrestrial processing to the operational site. The emphasis has been on the use of near-term (pre-year 2000) propulsion systems, such as advanced chemical (H2, O2) and nuclear-electric systems. More exotic systems (mass drivers, nuclear-thermal rockets, etc.) were also considered to evaluate the potential to be gained by use of post-year 2000 technologies. Finally, the effects of using extraterrestrial propellants (e.g., H2 from lunar polar water-ice for chemical systems) were compared to those of propulsion systems deriving all or part of their propellants from the earth.
Frisbee, R. H.↗
An improved technique for measuring the thermal conductivity of cast elastomeric materials
A technique for measuring the thermal conductivity of cast elastomeric materials, including solid propellants, is described. The technique is modified to take into account end losses.
Frisbee, R. H.↗