Orbit Transfer via Tube Jumping in Planar Restricted Problems of Four Bodies

2005 ◽  
Vol 42 (2) ◽  
pp. 321-328 ◽  
Author(s):  
Hideaki Yamato ◽  
David B. Spencer
Keyword(s):  
Orbit Transfer ◽  
Restricted Problems

Orbit transfer vehicle propulsion system

1981 ◽  
Author(s):  
W. KETCHUM
Keyword(s):  
Propulsion System ◽  
Orbit Transfer ◽  
Vehicle Propulsion

A modular, ion propelled, orbit transfer vehicle

1986 ◽  
Author(s):  
J. HERMEL ◽  
R. MEESE ◽  
W. ROGERS ◽  
R. KUSHIDA ◽  
J. BEATTIE
Keyword(s):  
Orbit Transfer

Hubble Space Telescope On-orbit Transfer Function Test

1992 ◽  
Author(s):  
N. VADLAMUDI ◽  
M. BLAIR ◽  
B. CLAPP
Keyword(s):  
Transfer Function ◽  
Hubble Space Telescope ◽  
Orbit Transfer ◽  
Space Telescope ◽  
Function Test

Optimal Control of Orbit Transfer of Space Probe w...

2005 ◽  
Author(s):  
He Xingsuo ◽  
Wang Ping ◽  
Yuan Jianping ◽  
Lin Shengyong
Keyword(s):  
Optimal Control ◽  
Space Probe ◽  
Orbit Transfer

Transfers with a rendezvous lasting no more than one orbit between close near-circular coplanar orbits

2020 ◽  
pp. 82-93
Author(s):  
Aleksandr F. BRAGAZIN ◽  
Alexey V. USKOV
Keyword(s):  
Key Words ◽  
Relative Velocity ◽  
Free Parameter ◽  
Space Station ◽  
Characteristic Velocity ◽  
Orbital Station ◽  
Orbit Transfer ◽  
Simulation Results ◽  
The Moment ◽  
Phase Differences

Consideration has been given to orbit transfers involving spacecraft rendezvous which belong to a class of coplanar non-intersecting near-circular orbits of a spacecraft and a space station. The duration of the transfer is assumed to be limited by one orbit. The feasibility of a rendezvous using an optimal two-burn orbit-to-orbit transfer is studied. To determine a single free parameter of the transfer, i.e. the time of its start, ensuring a rendezvous at a given time or at a given velocity at the end of transfer, appropriate equations have been obtained To implement in the guidance algorithms optimal three-burn correction programs are proposed to achieve a rendezvous at a given time with a specified relative velocity at the moment of spacecraft contact. A range of phase differences at the start of maneuvering is determined, within which the characteristic velocity of the rendezvous is equal to the minimum characteristic velocity of the orbit-to-orbit transfer. The paper presents simulation results for “quick" rendezvous profiles that use the proposed programs. Key words: spacecraft, orbital station, “quick” rendezvous, orbit transfer, rendezvous program.

scholarly journals Solving non-Convex and Restricted Problems Using Swarms – Economic Dispatch Case

2014 ◽  
Vol 17 ◽  
pp. 502-509
Author(s):  
João Pontes ◽  
P.M. Fonte ◽  
Rui Pestana
Keyword(s):  
Economic Dispatch ◽  
Restricted Problems
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