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Optimal low-thrust transfer using variable bounded thrust
Acta Astronautica, 1995Abstract The problem of minimum-fuel time-fixed transfer and rendezvous using variable bounded thrust is presented based on the use of a set of non-singular orbit elements. The consideration of maximum and minimum bounds on the thrust magnitude with constant power is equivalent to constraining the specific impulse of the propulsion system such that ...
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1998
The limitations of conventional chemical propulsion for missions to the outer planets, comets, and asteroids were illustrated in Table 5.2 of the previous chapter. An alternative approach to the use of swingby manoeuvres is to exploit the very high specific impulses that can be achieved through the use of electric propulsion, eg. exhaust velocities the
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The limitations of conventional chemical propulsion for missions to the outer planets, comets, and asteroids were illustrated in Table 5.2 of the previous chapter. An alternative approach to the use of swingby manoeuvres is to exploit the very high specific impulses that can be achieved through the use of electric propulsion, eg. exhaust velocities the
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Applications of combined high-thrust, low- thrust propulsion systems
3rd Propulsion Joint Specialist Conference, 1967Combined electric constant low thrust and chemical or nuclear high thrust space propulsion systems for interplanetary ...
D. DUGAN, A. MASCY, S. PITTS
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Low-thrust mission risk analysis
11th Aerospace Sciences Meeting, 1973A computerized multi-stage failure process simulation procedure is used to evaluate the risk in a solar electric space mission. The procedure uses currently available thrust-subsystem reliability data and performs approximate simulations of the thrust subsystem burn operation, the system failure processes, and the retargetting operations.
C. YEN, D. SMITH
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Flight Mechanics of Low-Thrust Spacecraft
Journal of the Aerospace Sciences, 1959Spacecraft starting from circular orbits and using a low thrust, tangentially directed, will follow a spiraled flight path as illustrated in Fig. 1. Whether or not the thrust is constant, if it remains less than one per cent of local vehicle weight the mean path of these trajectories will maintain the familiar circular velocityaltitude relationship for
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Low thrust cryogenic engine technology
23rd Joint Propulsion Conference, 1987The Air Force Rmket Pmmlsion Laborator, is sponsoring a program to devzop the techno14 for a 50O-lbF 0 /H rccket engine interded t o provide low d t 2pmpulsion for delivery of large space structures to geosynchronous orbit, following deployment and checkout i n low earth orbit.
BARBARA SCHNEIDER, ROY MICHEL, JOHN GIBB
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Low-Thrust Spacecraft Formation Keeping
Journal of Spacecraft and Rockets, 2006Replacing large and costly satellites with formations of smaller satellites, flying in close proximity, is a current subject of interest. One of the keys to successful formation flying is the control system that maintains the formation geometry and provides proper positioning of each member of the formation.
Pierre Vignal, Henry Pernicka
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Optimal low thrust geocentric transfer
10th Electric Propulsion Conference, 1973A computer code which will rapidly calculate time-optimal low thrust transfers is being developed as a mission analysis tool. The final program will apply to NEP or SEP missions and will include a variety of environmental effects. The current program assumes constant acceleration. The oblateness effect and shadowing may be included.
T. EDELBAUM, L. SACKETT, H. MALCHOW
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Low-Area Ratio, Thrust-Augmenting Ejectors
Journal of Aircraft, 1971The thrust augmentation, lift augmentation, and noise reduction characteristics of compact ejectors make them potentially attractive for propulsion lift systems; however, in the past, poor thrust augmentation results have negated the other benefits.
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Low-thrust propulsion for the MORL
5th Electric Propulsion Conference, 1966Advanced low thrust propulsion systems and propellants evaluation for stationkeeping and stability control of NASA Manned Orbital Research ...
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