Optimal guidance from hyperbolic to circular orbits.
Minimum fuel guidance from hyperbolic into specified circular orbit
Edelbaum, T. N.↗
Engineering topics
Edelbaum, T. N.
Publications and source records attributed to Edelbaum, T. N..
Minimum impulse guidance Interim scientific report
Minimum fuel guidance for time-open rendezvous, orbit transfer, and orbit transfer with tangential nominal impulses
Edelbaum, T. N.↗
Optimal guidance from hyperbolic to circular orbits
Solution for minimum fuel guidance from hyperbolic to circular orbit
Edelbaum, T. N.↗
Minimum impulse transfers in the near vicinity of a circular orbit.
Analytic solution obtained for minimum impulse transfer between two neighboring low eccentricity orbits
THRUST CONTROL↗
A general solution for minimum impulse transfers in the near vicinity of a circular orbit
Analytic solution for minumum impulse transfer between two neighboring low eccentricity orbits
CIRCULAR ORBIT↗
Minimum-impulse time-free transfer between elliptic orbits
Minimum impulse time free transfer between elliptic orbits
ORBITAL TRANSFER↗
How many impulses/ques/
Minimum fuel transfer solution of Lawden problem involving finite number of impulse thrusts separated by coasting arcs
OPTIMUM THRUST PROGRAMMING↗
Application of a finite-difference Newton- Raphson algorithm to problems of low-thrust trajectory optimization.
Low thrust trajectory optimization, using Newton- Raphson method to solve nonlinear two-point boundary value problem
TRAJECTORY OPTIMIZATION↗
Optimization problems in powered space flight.
Minimum fuel transfer between circular or elliptic orbits in central gravitational field
OPTIMUM THRUST PROGRAMMING↗
Applications of snap-50 class powerplants to selected unmanned electric propulsion missions.
SNAP-50 power plants applied to selected unmanned electric propulsion space missions
NUCLEAR POWER PLANT↗
Application of a finite-difference newton- raphson algorithm to problems of low-thrust trajectory optimization.
Low thrust trajectory optimization, using Newton- Raphson method to solve nonlinear two-point boundary value problem
BOUNDARY VALUE↗
Applications of snap-50 class powerplants to selected unmanned electric propulsion missions
Snap-50 powerplants for unmanned spacecraft propulsion
UNMANNED SPACECRAFT↗
Mission Capabilities of Ion Engines. Phase II
Payloads and mission times were calculated for space vehicles propelled by ion rockets using nuclear power supplies having specific weights from 10 t o 50 lb/kw. Included in the study were five missions: low-altitude lunar satellite, low-altitude Venus satellite, solar probe, Saturn probe, and a Jupiter satellite with a circular orbit at the altitude of Jupiter's fourth moon. The variation of payload with the ration of power supply weight to gross weight was studied and the optimum power levels thereby determined. The ion rocket payload capabilities were compared with those of high-thrust vehicles using hydrogen-oxygen rockets and tungsten-core nuclear rockets; in addition the performance of high- and low-thrust systems staged in combination has been investigated. Launch vehicles considered in this study were the Atlas-Centaur, the Saturn C-1, and the Saturn C-5.
IONIC PROPULSION↗
Mission Capabilities of Ion Engines Using SNAP-8 Power Supplies
Mission performance capabilities of ion engines powered by the 30 kw and 60 kw SNAP-8 power supplies are compared for the following missions: a 24-hr equatorial satellite, a 100 n mi lunar satellite, a 500 n mi Mars satellite, a Mercury probe, and an out-of-the-ecliptic probe. The capabilities of arc- jet engines and chemical engines for the same missions are compared with those of the ion engines. The majority of the comparisons are for 8500-lb spacecraft which are boosted into a 300 n mi orbit by the Atlas-Centaur. Variations in initial orbit altitude, the use of actual launch dates rather than dates based on simplifying assumptions, and the combined use of chemical and electrical propulsion systems were also evaluated in terms of their effect on mission performance.
IONIC PROPULSION↗