Analytical control laws of the heliocentric motion of the solar sail spacecraft

2014 ◽  
Author(s):  
Irina Gorbunova ◽  
Olga Starinova
Keyword(s):  
Solar Sail ◽  
Analytical Control ◽  
Control Laws

scholarly journals Some New Locally Optimal Control Laws for Sailcraft Dynamics in Heliocentric Orbits

2013 ◽  
Vol 2013 ◽  
pp. 1-16 ◽  
Author(s):  
F. A. Abd El-Salam
Keyword(s):  
Cone Angle ◽  
Analytical Control ◽  
Input Constraints ◽  
Force Vector ◽  
Control Laws ◽  
Solar Sailing ◽  
Special Cases ◽  
Heliocentric Orbits ◽  
Solar Radiation Forces ◽  
Heliocentric Orbit

The concept of solar sailing and its developing spacecraft is presented. The gravitational and solar radiation forces are considered. The effect of source of radiation pressure and the force due to coronal mass ejections and solar wind on the sailcraft configurations is modeled. Some analytical control laws with some mentioned input constraints for optimizing sailcraft dynamics in heliocentric orbit using lagrange’s planetary equations are obtained. Optimum force vector in a required direction is maximized by deriving optimal sail cone angle. Ignoring the absorbed and diffusely reflected parts of the radiation, some special cases are obtained. New control laws that maximize thrust to obtain certain required maximization in some particular orbital element are obtained.

scholarly journals Procedure for forming nominal control program of solar sail spacecraft heliocentric movement using locally optimal control laws

2020 ◽  
Vol 4 (1) ◽  
pp. 5-13
Author(s):  
R. M. Khabibullin
Keyword(s):  
Optimal Control ◽  
Control Program ◽  
Solar Sail ◽  
Flight Trajectory ◽  
Control Laws ◽  
Phase Coordinates ◽  
Control Scheme ◽  
Control Schemes ◽  
Efficient Control ◽  
Interplanetary Flight

The paper is devoted to the non-coplanar interplanetary flight Earth-Venus of the spacecraft equipped with a solar sail. The goal of the heliocentric movement is to transfer a spacecraft with a non-perfectly reflecting solar sail into the Hill’s sphere of the Venus with zero hyperbolic excess speed. The magnitude and direction of acceleration is calculated taking into account specular and diffuse reflections, absorption and transmission of photons by the surface of the solar sail. One of the main tasks in the field of navigation and motion control of a spacecraft is the search for a simple energy-efficient control scheme for performing maneuvers during flight. These control schemes are locally optimal control laws, various combinations of which allow you to perform the necessary maneuvers during an interplanetary flight. The procedure for the formation of a control program for a non-coplanar interplanetary flight of the Earth-Venus type of a spacecraft with a non-perfectly reflecting solar sail is described. The results include the flight trajectory, the change in phase coordinates in time, graphs of changes in control angles, and the nominal control program. The obtained results satisfy all the boundary conditions described in the statement of the problem.

scholarly journals Control program for noncoplanar heliocentric flight to Venus of non-perfectly reflecting solar sail spacecraft

2020 ◽  
Vol 18 (4) ◽  
pp. 117-128 ◽  
Author(s):  
R. M. Khabibullin
Keyword(s):  
Thin Film ◽  
Optimal Control ◽  
Control Program ◽  
Solar Sail ◽  
Motion Simulation ◽  
Flight Trajectory ◽  
Control Laws ◽  
Osculating Elements

A noncoplanar controlled heliocentric flight to Venus of a spacecraft with a non-perfectly reflecting solar sail is considered. The aim of the heliocentric flight is to get a spacecraft into Hill sphere of Venus with zero hyperbolic excess velocity. An algorithm has been developed for applying the locally optimal control laws for the fastest change of the osculating elements. Solar sail orientation is controlled by thin-film control elements arranged along the solar sail surface perimeter. The flight trajectory, the control program and the required width and area of thin-film control elements are obtained as a result of motion simulation.

An Analysis of Guided Motion of a Research Spacecraft with a Solar Sail

2019 ◽  
pp. 94-103
Author(s):  
R.M. Khabibullin ◽  
O.L. Starinova
Keyword(s):  
Mathematical Model ◽  
Optimal Control ◽  
Finite Element ◽  
Finite Element Model ◽  
Coordinate System ◽  
Element Model ◽  
Solar Sail ◽  
Motion Simulation ◽  
Control Laws ◽  
Controlled Motion

The paper considers guided motion of a research spacecraft with a frame-type solar sail. When scheduled turns of the solar sail are performed, disturbing forces appear, the characteristics of which depend on the solar sail design. It is necessary to take into account the design features of the solar sail to analyze the controlled motion of the spacecraft. A finite element model of a frame-type solar sail spacecraft construction is developed. A mathematical model of motion in the combined helio-centric coordinate system is described. Local-optimal control laws of orbit elements maintenance and correction are formulated. The software developed for simulating the motion of a spacecraft with a solar sail in the heliocentric coordinate system is used in this study. The analysis of the data obtained during motion simulation demonstrates the feasibility of using the solar sail technology for interplanetary flights.

Analytical Control Laws for Planet-Centered Solar Sailing

2005 ◽  
Vol 28 (5) ◽  
pp. 1038-1048 ◽  
Author(s):  
Malcolm Macdonald ◽  
Colin R. McInnes
Keyword(s):  
Analytical Control ◽  
Control Laws ◽  
Solar Sailing

scholarly journals Heliocentric Solar Sail Orbit Transfers with Locally Optimal Control Laws

2007 ◽  
Vol 44 (1) ◽  
pp. 273-276 ◽  
Author(s):  
Malcolm Macdonald ◽  
Colin R. McInnes ◽  
Bernd Dachwald
Keyword(s):  
Optimal Control ◽  
Solar Sail ◽  
Control Laws
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