The Mission’s Design of a Solar Sail Spacecraft to the Nearest Circumsolar Space, Based on Local-optimal Control Laws

2018 ◽  
Vol 1 (1) ◽  
pp. 81-85 ◽  
Author(s):  
Olga L. Starinova ◽  
Irina V. Chernyakina
Keyword(s):  
Optimal Control ◽  
Solar Sail ◽  
Control Laws

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.

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

Optimal Control Laws for Axially Symmetric Solar Sails

2005 ◽  
Vol 42 (6) ◽  
pp. 1130-1133 ◽  
Author(s):  
Giovanni Mengali ◽  
Alessandro A. Quarta
Keyword(s):  
Optimal Control ◽  
Axially Symmetric ◽  
Solar Sails ◽  
Control Laws

Scheduling Strategy of Multiple Semi-Active Controllers With Information on the Disturbance and the Structural Response

2016 ◽  
Author(s):  
Kazuhiko Hiramoto ◽  
Taichi Matsuoka ◽  
Katsuaki Sunakoda
Keyword(s):  
Optimal Control ◽  
Control System ◽  
Active Control ◽  
Structural Response ◽  
Design Parameters ◽  
Control Law ◽  
Control Performance ◽  
Multiple Control ◽  
Control Laws ◽  
Scheduling Strategy

A scheduling strategy of multiple semi-active control laws for various earthquake disturbances is proposed to maximize the control performance. Generally, the semi-active controller for a given structural system is designed as a single control law and the single control law is used for all the forthcoming earthquake disturbances. It means that the general semi-active control should be designed to achieve a certain degree of the control performance for all the assumed disturbances with various time and/or frequency characteristics. Such requirement on the performance robustness becomes a constraint to obtain the optimal control performance. We propose a scheduling strategy of multiple semi-active control laws. Each semi-active control law is designed to achieve the optimal performance for a single earthquake disturbance. Such optimal control laws are scheduled with the available data in the control system. As the scheduling mechanism of the multiple control laws, a command signal generator (CSG) is defined in the control system. An artificial neural network (ANN) is adopted as the CSG. The ANN-based CSG works as an interpolator of the multiple control laws. Design parameters in the CSG are optimized with the genetic algorithm (GA). Simulation study shows the effectiveness of the approach.

Periodic Optimal Control of Dampers

1997 ◽  
Author(s):  
Prakash S. Kasturi ◽  
Pierre E. Dupont
Keyword(s):  
Optimal Control ◽  
Singular Control ◽  
Maximum Energy ◽  
Periodic Forcing ◽  
Control Effort ◽  
Control Laws ◽  
Single Degree Of Freedom ◽  
State Dependent ◽  
Alternate Control ◽  
Energy Dissipated

Abstract Optimal control of dampers has been proposed to mitigate vibration effects in mechanical systems. In many cases, systems are subject to periodic forcing and the goal is to maximize the energy dissipated by the damper. In contrast to prior work utilizing instantaneous or infinite-time-horizon optimization, this paper employs periodic optimal control to maximize the energy dissipated per cycle. For single degree of freedom systems in which the maximum allowable control effort is of the same order as the forcing magnitude, a state-dependent singular control law is shown to deliver maximum energy dissipation. Alternate control laws are proposed for situations when rattlespace requirements dictate damper displacements other than that of the singular solution.

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