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

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.

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

Spacecrafts & Technologies ◽

10.26732/j.st.2020.1.01 ◽

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.

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An algorithm for controlling the spatial motion of a spacecraft with an imperfectly reflecting solar sail based on the laws of locally optimal control for Earth — Mars heliocentric flight

Engineering Journal Science and Innovation ◽

10.18698/2308-6033-2020-8-2006 ◽

2020 ◽

Author(s):

R.M. Khabibullin ◽

O.L. Starinova

Keyword(s):

Optimal Control ◽

Control Algorithm ◽

Center Of Mass ◽

Control Program ◽

Solar Sail ◽

Design Parameters ◽

Motion Simulation ◽

Light Pressure ◽

Spacecraft Control ◽

Osculating Elements

The article considers a spatial controlled heliocentric Earth-Mars flight of a spacecraft with an imperfectly reflecting solar sail. A new mathematical model of motion is described taking into account the dynamics of motion relative to the center of mass under the forces and moments from light pressure. A spacecraft control algorithm for implementing the flight is formed on the basis of the laws of locally optimal control for the fastest change of osculating elements. The orientation of the solar sail is controlled using thin-film control elements located around the perimeter of the solar sail surface. As a result of motion simulation, the duration and trajectory of the flight, the control program and the necessary design parameters of a spacecraft with a solar sail are determined.

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

Proceedings of Higher Educational Institutions Маchine Building ◽

10.18698/0536-1044-2019-12-94-103 ◽

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.

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Non-coplanar interplanetary flight simulation considering motion relative to the center of mass peculiarities of solar sail spacecraft

Spacecrafts & Technologies ◽

10.26732/j.st.2020.3.02 ◽

2020 ◽

Vol 4 (3) ◽

pp. 141-150

Author(s):

R. M. Khabibullin ◽

O. L. Starinova

Keyword(s):

Thin Film ◽

Center Of Mass ◽

Control Program ◽

Solar Sail ◽

Flight Simulation ◽

Light Pressure ◽

Second Stage ◽

Third Stage ◽

Angular Velocities ◽

The Hill

The paper is devoted to the non-coplanar interplanetary Earth–Venus flight of a spacecraft equipped with a non-perfectly reflecting solar sail, the magnitude and direction of acceleration from which is calculated taking into account specular and diffuse reflections, absorption and transmission of photons by the surface of the solar sail. The goal of the heliocentric motion is to transfer the solar sail spacecraft into the Hill sphere of Venus with zero hyperbolic excess of speed. A feature of the paper is the study of the motion of a non-perfectly reflecting solar sail spacecraft taking into account the motion relative to the center of mass. The problem is divided into three stages. At the first stage, a nominal program for controlling the motion of the spacecraft center of mass is formed. At the second stage, sufficient angular velocities are determined to ensure the obtained nominal control program and the parameters of the spacecraft controls – thin-film controls located along the perimeter of the solar sail – are calculated. The operating principle of the thin-film controls is quite simple. When the voltage applied to the thin-film controls changes, they become transparent or opaque, there is a difference in the normal components of the light pressure forces, which provides a control torque for changing the orientation of the spacecraft in space. At the third stage, the joint motion of the center of mass and relative to the center of mass of the spacecraft is simulated to demonstrate the feasibility of the obtained control program. As a result, a comparison is made of non-coplanar interplanetary Earth–Venus flights with and without thin-film control elements.

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