scholarly journals Low-Thrust Control of a Lunar Mapping Orbit

2009 ◽  
Vol 32 (3) ◽  
pp. 939-948 ◽  
Author(s):  
Nathan Harl ◽  
Henry J. Pernicka
Keyword(s):  
Low Thrust ◽  
Thrust Control ◽  
Lunar Mapping

scholarly journals Low-Thrust Control Strategies for Earth-to-Mars Trajectories

Space Flight ◽  
2018 ◽  
Author(s):  
Marco Gómez Jenkins ◽  
Jose Antonio Castro Nieto
Keyword(s):  
Control Strategies ◽  
Low Thrust ◽  
Thrust Control

Artificial Martian frozen orbits and Sun-Synchronous orbits using continuous low-thrust control

2014 ◽  
Vol 352 (2) ◽  
pp. 503-514 ◽  
Author(s):  
Zhigang Wu ◽  
Fanghua Jiang ◽  
Junfeng Li
Keyword(s):  
Low Thrust ◽  
Frozen Orbits ◽  
Thrust Control

Fourier Coefficient Selection for Low-Thrust Control Shaping

2013 ◽  
Vol 36 (6) ◽  
pp. 1783-1786
Author(s):  
Jennifer S. Hudson ◽  
Daniel J. Scheeres
Keyword(s):  
Fourier Coefficient ◽  
Low Thrust ◽  
Thrust Control ◽  
Selection For

COMPARATIVE ANALYSIS OF THE EFFICIENCY OF CONSTANT POWER THROTTLED ROCKET ENGINES FOR INTERORBITAL FLIGHTS TO GEOSTATIONAR

2021 ◽  
Vol 6 ◽  
pp. 66-77
Author(s):  
Igor Vasiliev ◽  
◽  
Boris Kiforenko ◽  
Yaroslav Tkachenko ◽  
◽  
...  
Keyword(s):  
Mathematical Models ◽  
Electric Propulsion ◽  
Rocket Engine ◽  
Power Level ◽  
Specific Impulse ◽  
Rocket Engines ◽  
Low Thrust ◽  
Constant Power ◽  
Control Functions ◽  
Thrust Control

Carrying out low-thrust transfers of spacecrafts in the near-earth space from intermediate elliptic to the geostationary orbit using electric rocket engines seems to be one of the most important tasks of modern cosmonautics. Electric rocket engines, whose specific impulse of the reactive jet is an order of magnitude more than in chemical RD, are preferable for interorbit flights with a maximum payload in the case when a significant increase in the duration of the maneuver is permissible. Ability to throttling the rocket engine thrust is traditionally considered as one of the ways to reduce both the engine mass and the required fuel assumptions for performing the specified maneuver. Using the concept of an ideal-rocket engine provides the upper estimates of the payload mass of interborbital flights for the given power level. Accounting for the properties of real engines leads to the need of considering the mathematical models with more strict limits on control functions. A study of the efficiency of three modes of thrust control of an electric propulsion rocket engine was carried out when performing practically interesting spacecraft flights from highly elliptical intermediate near-earth orbits to geostationary orbits. A mathematical model of constant power relay rocket engine has been built. The formulation of the variational problem of the Maer type is given about the execution of a given dynamic maneuver for the throttled and unregulated electric rocket engines of constant power. Using the Pontryagin maximum principle, an analysis of the optimal control functions was carried out, for which the final relations were written out, which allowed to write down the system of differential equations of the optimal movement of the spacecraft, equipped with relay electric rocket engine. The obtained numerical and quality results of the study of the effectiveness of various modes of thrust control of an electric propulsion engine to increase the payload of a given orbital maneuver confirmed the correctness of mathematical models of throttled and relay engines and, in general, the efficiency of using solutions of the averaged equations of optimal motion of a spacecraft for numerical solution of the corresponding boundary value problems in an exact formulation.

scholarly journals Design of Artificial Sun-Synchronous Orbits with Main Zonal Harmonics and Solar Radiation Pressure Using Continuous Low-Thrust Control Strategies

2019 ◽  
Vol 28 (1) ◽  
pp. 124-130
Author(s):  
Akram Masoud ◽  
Walid Ali Rahoma ◽  
Elamira Hend Khattab ◽  
Fawzy Ahmed Abd El-Salam
Keyword(s):  
Solar Radiation ◽  
Radiation Pressure ◽  
Control Strategies ◽  
Solar Radiation Pressure ◽  
Continuous Variable ◽  
Low Thrust ◽  
Surface Mapping ◽  
Orbital Parameters ◽  
Zonal Harmonics ◽  
Thrust Control

AbstractArtificial sun-synchronous orbits are suitable for remote sensing satellites and useful in giving accurate surface mapping. To design such orbits accurately with arbitrary orbital elements, three control strategies are provided with the consideration of main zonal harmonics up to J4 and solar radiation pressure (SRP). In this paper, the continuous variable low-thrust control is used as a way to achieve these artificial orbits and given by electric propulsions rather than chemical engines to enlarge lifespan of the spacecraft. The normal continuous low-thrust control is used to illustrate the control strategies. Furthermore, formulas for refinement of normal control thrusts are applied to overcome errors due to approximations. The results of the simulation show that the control strategies explained in this paper can realize sun-synchronous orbits with arbitrary orbital parameters without side effects and the effect of solar radiation pressure is very small relative to main zonal harmonics. A new technique is suggested, ASSOT-3, to minimize fuel consumption within one orbital period more than others. This technique is based on computing the root mean square of the rate of ascending node longitude instead of the average.

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