Application of modern control and nonlinear estimation techniques
Control and nonlinear estimation techniques applied to optimal guidance of low thrust spacecraft, planetary soft landings, and feedback systems design
Ash, G. R.↗
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Results for “Low Thrust”
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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Experimental investigation of reaction control, storable bipropellant thrustors
Performance of low thrust storable bipropellant thrustors in spacecraft reaction control system
Rollbuhler, R. J.↗
Design and performance of a thermal storage resistojet.
Single nozzle thermal storage resistojet thrustor for low thrust satellite attitude and orbit control applications, noting design and performance
Cygnarowicz, T. A.↗
Trajectory optimization using regularized variables
Regularized equations for a particular optimal trajectory are compared with unregularized equations with respect to computational characteristics, using perturbation type numerical optimization. In the case of the three dimensional, low thrust, Earth-Jupiter rendezvous, the regularized equations yield a significant reduction in computer time.
Lewallen, J. M.↗
Mission analysis model requirements for electric propulsion.
Spacecraft electric propulsion parameters and launching vehicle characteristics in low thrust mission simulation, discussing spacecraft path
Barber, T. A.↗
Canonical transformation applications to optimal trajectory analysis.
Canonical transformation and Hamilton-Jacobi theories applied to space vehicle trajectory analysis, discussing elliptical coast arc and optimal low thrust problems
Powers, W. F.↗
MEPSIS - Minimal electric propulsion systems for interplanetary spacecraft.
Minimal electric propulsion systems for interplanetary spacecraft, discussing payload, reduced trip time and low thrust systems for Jupiter flyby
Duck, K. I.↗
Solar electric grand tour missions to the outer planets Final report
Optimized solar electric low thrust propulsion and intermediate planetary swingby technique for grand tour missions to outer planets
Flandro, G. A.↗
Ion accelerator designs for Kaufman thrusters
Automated parameter search techniques applied to low thrust mission design, stressing trajectories and mission optimization
Lathem, W. C.↗
Some three-body numerical solutions to outer planet orbiter missions using nuclear-electric propulsion
Three body numerical solutions to low thrust guidance and navigation for outer planet orbiter with nuclear-electric propulsion
Mackay, J. S.↗
Resistojet waste methane utilization in manned space application
Environmental control-life support systems /ECLSS/ waste methane gas utilization in low thrust resistojet for manned space applications
Duncan, L. F.↗
Advanced propulsion techniques
High and low thrust hybrid rocket propulsion systems involving combinations of chemical, nuclear, thermal and electric propellants for interplanetary flights
Evvard, J. C.↗
Numerical implementation of a second-order variational endpoint condition
Second order variational endpoint condition numerical application used for low thrust minimum fuel orbital transfer problems
Brusch, R. G.↗
Solid-propellant motors for high-incremental velocity low-acceleration maneuvers in space
Low thrust long burning solid rocket propellant motor for orbit insertion maneuvers, discussing design, static tests, nozzle composition, igniter and performance
Shafer, J. I.↗
Spectral factorization in time-varying systems having periodic coefficients and its application to navigation of solar electric interplanetary missions
Low thrust interplanetary spacecraft tracking, using spectral factorization for Kalman filtering equations steady state solution
Nishimura, T.↗
Rapid analysis of electric propulsion missions
Computer program has been designed to handle computations for low thrust missions rapidly and with acceptable accuracy. Program defines performance and system requirements of electrically-propelled unmanned planet-orbiter and flyby missions. The program is written in FORTRAN 4 for use on an IBM 360 or CDC 6600 computer.
Mascy, A. C.↗
Mars surface sample return missions via solar electric propulsion
The characteristics and capabilities are described of solar electric propulsion (SEP) for performing Mars Surface Sample Return (MSSR) missions. The scope of the study emphasizes trajectory/payload analysis and the comparison of mission/system tradeoff options. The MSSR mission is examined only for the 1981-82 launch opportunity. Several other study constraints which bear directly on the results obtained are: (1) return samples in the range 5-25 kg, (2) use of lifting (offset C.G.) atmospheric entry at Mars which allows a low ratio (1.25) of entry weight to landed weight, and (3) rendezvous and docking in Mars orbit. Major results of the study are presented as performance curves of earth departure mass versus sample size for a number of different mission/system options. These options represent a spectrum of trip time, launch vehicle capability, combinations of low-thrust and ballistic maneuvers, chemical retro type, and earth recovery mode.
Spadoni, D. J.↗
An analysis and comparison of several trajectory optimization methods
The sensitivities of the convergence characteristics of the methods to initially assumed parameters and trial solution, convergence times, computer logic, and storage requirements are discussed. Numerical comparison of the convergence characteristics is made by considering a minimum time, low thrust, Earth-Mars transfer trajectory. A modified quasi-linearization method reduces convergence time by approximately 70% when compared with the generalized Newton-Raphson method and allows the terminal boundary to be specified by a general function of the problem variables. A uniquely specified and easily determined, time dependent weighting matrix for the gradient techniques accelerates the shaping of the optimal control program and improves the convergence characteristics during the terminal iterations. Convergence envelopes, indicating how sensitive the convergence characteristics are to initially assumed parameters, are plotted for the perturbation and quasi-linearization methods. Several iteration schemes are proposed which increase the size of the convergence envelopes and decrease the sensitivity of the method to initially assumed parameters.
Lewallen, J. M.↗