scholarly journals Generalized Guidance Scheme for Low-Thrust Orbit Transfer

2014 ◽  
Vol 2014 ◽  
pp. 1-9
Author(s):  
Henzeh Leeghim ◽  
Dong-Hyun Cho ◽  
Su-Jang Jo ◽  
Donghoon Kim
Keyword(s):  
Energy Term ◽  
Low Thrust ◽  
Orbital Elements ◽  
Orbit Transfer ◽  
Suggested Approach ◽  
Shadow Area ◽  
Electrical Propulsion ◽  
Additional Improvement ◽  
Lyapunov Feedback Control ◽  
Low Thrust Orbit Transfer

The authors present an orbital guidance scheme for the satellite with an electrical propulsion system using a Lyapunov feedback control. The construction of a Lyapunov candidate is based on orbital elements, which consist of angular momentum and eccentricity vectors. This approach performs orbit transfers between any two arbitrary elliptic or circular orbits without any singularity issues. These orbital elements uniquely describe a non degenerate Keplerian orbit. The authors improve the reliability of the existing Lyapunov orbital guidance scheme by considering the energy term. Additional improvement is achieved by adding the penalty function. Furthermore, it is shown that the final suggested approach is suitable for the satellite passing the earth’s shadow area.

The Dynamics of Low-Thrust Spacecraft Manoeuvres

1968 ◽  
Vol 72 (695) ◽  
pp. 925-940 ◽  
Author(s):  
E. G. C. Burt
Keyword(s):  
Power Supplies ◽  
Relativity Theory ◽  
Time Varying ◽  
Low Thrust ◽  
Orbital Elements ◽  
Propulsion Systems ◽  
Optimum Time ◽  
Orbital Transfers ◽  
Electrical Propulsion ◽  
Increasing Function

Summary Orbital manoeuvres by means of impulsive thrusts, such as those available with chemical rockets, are well known, but a different treatment is needed for the small, continuous thrusts that are typical of electrical propulsion systems. It is shown that with the aid of these small forces it is possible to change independently all the orbital elements of a spacecraft, and thus to proceed slowly from a given orbit to any other. For each manoeuvre there exists an equivalent velocity which depends only on the initial and final orbital states, and which can be related directly to the spacecraft propulsion parameters. For any form of propulsion where the propellent acquires some or all of its energy from a separate energy source, as in electrical propulsion, it is found that optimum time-varying relations exist between the flow of mass and of energy, which may also be expressed in terms of the exhaust velocity and the thrust. In particular, the optimum exhaust velocity is shown to be an increasing function of time, related to the way in which the energy is released. The practical realisation of electrical propulsion depends on the development of efficient propulsion units and of lightweight power supplies; these and other spacecraft components are discussed, and a number of examples of orbital manoeuvres are given, including close-Earth, far-Earth and lunar orbits. The paper concludes with a discussion of these orbital transfers in relation to their possible uses, including communication satellites and a test of relativity theory

Time-critical low-thrust orbit transfer optimization

1992 ◽  
Vol 29 (2) ◽  
pp. 286-288 ◽  
Author(s):  
Rodney L. Burton ◽  
Carl Wassgren
Keyword(s):  
Low Thrust ◽  
Orbit Transfer ◽  
Low Thrust Orbit Transfer ◽  
Time Critical
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