Analytical Solution of the Minimum Time Slew Maneuver Problem for an Axially Symmetric Spacecraft in the Class of Conical Motions

Молоденков, А. В.; Sapunkov, Ya. G.

doi:10.1134/s1064230718020120

Cited by 14 publications

(7 citation statements)

References 7 publications

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“…Notice, recent solutions [19][20][21][22] are not applicable for general case of three-dimensional turn of arbitrary spacecraft; the work [25] describes synthesis of terminal reorientation control only for spacecraft which moves along circular orbit. But method designed in present article is universal control, it does not depend on a ratio (proportion) of moments of inertia or final position of a spacecraft.…”

Section: Discussionmentioning

confidence: 99%

“…Diverse methods are used for constructing control program of spacecraft orientation, in particular, algorithm of fuzzy logic [7] or concept of inverse problem of dynamics [8,9] . Finding the optimal solution of spacecraft's motion control is known also [10][11][12][13][14][15][16][17][18][19][20][21][22][23][24] . Time-optimal maneuvers are more popular [11][12][13][14][15][16][17][18][19][20] .…”

Section: Introductionmentioning

confidence: 99%

“…Finding the optimal solution of spacecraft's motion control is known also [10][11][12][13][14][15][16][17][18][19][20][21][22][23][24] . Time-optimal maneuvers are more popular [11][12][13][14][15][16][17][18][19][20] . Some solutions are obtained for axially symmetric spacecraft [19][20][21][22] .…”

Section: Introductionmentioning

confidence: 99%

“…Time-optimal maneuvers are more popular [11][12][13][14][15][16][17][18][19][20] . Some solutions are obtained for axially symmetric spacecraft [19][20][21][22] . Terminal control for orbital orientation of a spacecraft was considered also [25] ; controlling the spacecrafts with control moment gyroscopes has features [26][27][28] .…”

Section: Introductionmentioning

confidence: 99%

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Use of the Method of Guidance by a Required Velocity in Control of Spacecraft Attitude

Левский¹

2021

j. of mech. eng. res.

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We apply the method of guidance by a required velocity for solving theoptimal control problem over spacecraft’s reorientation from known initialattitude into a required final attitude. We suppose that attitude control iscarried out by impulse jet engines. For optimization of fuel consumption,the controlling moments are calculated and formed according to themethod of free trajectories together with principle of iterative controlusing the quaternions for generating commands to actuators. Optimalsolution corresponds to the principle “acceleration - free rotation - separatecorrections - free rotation - braking”. Rotation along a hitting trajectory issupported by insignificant correction of the uncontrolled motion at discreteinstants between segments of acceleration and braking. Various strategies在自由运动阶段形成校正脉冲的方法是建议。提高实现航天器最终位置的准确性通过终端控制使用有关当前姿态的信息和用于确定开始时刻的角速度测量制动（根据实际运动参数开始制动的条件以分析形式制定）。所描述的方法是通用的并且相对于转动惯量不变。发展的态度法则控制涉及具有预测模型的算法，综合控制模式对于外部扰动和参数错误。数学建模的结果表明证明设计算法的实际可行性和高效率。

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Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Use of the Method of Guidance by a Required Velocity in Control of Spacecraft Attitude

Левский¹

2021

j. of mech. eng. res.

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“…Various methods and algorithms are used to construct an SC's attitude control program (including those based on fuzzy logic [4], the concept of inverse problems of dynamics [5,6], etc.). The problems of the optimal control of an SC's motion are also well known [1,2,[7][8][9][10][11][12][13][14][15][16][17][18][19], including those with unlimited control [8,9] (both with a fixed [8] and with nonfixed time of the end of the maneuver [9]). The tasks of the optimal turning time are the most popular tasks [1,[10][11][12][13][14][15][16]18].…”

Section: Introductionmentioning

confidence: 99%

Optimal Orientation Control of a Space Vehicle with Restrictions on the Control and Phase Variables

Левский¹

2021

J. Comput. Syst. Sci. Int.

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The problem of the optimal control of the reorientation of a spacecraft (SC) from an arbitrary initial angular position to the given final angular position is solved analytically in the presence of ellipsoidal constraints on the phase variables and control functions (the angular velocity and force moment are limited). The turning time is minimized. The case when the maximal allowable kinetic energy of rotation is a significant limitation is considered. The construction of the optimal control of a turn is based on quaternion variables and models. It is shown that during the optimal turn, the moment of forces is parallel to a straight line that is stationary in inertial space, and when the SC rotates, the direction of the kinetic momentum is constant relative to the inertial coordinate system. Analytical equations and relations for finding the optimal control program are written out. The calculation formulas are given for determining the time characteristics of the maneuver and calculating the duration of acceleration and deceleration. For an axisymmetric SC, the posed problem of the optimal control is solved completely: the dependences are obtained as explicit functions of time for the control variables and relations for calculating the key parameters of the control law. A numerical example and the results of mathematical modeling of the motion of an SC under the optimal control are given, demonstrating the practical feasibility of the developed method for controlling the orientation of an SC.

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An attitude control by the functional series in the problem of nanosatellite reorientation

Elisov

Крамлих

Ломака

et al. 2023

Aerospace Science and Technology

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Analytical Solution of the Minimum Time Slew Maneuver Problem for an Axially Symmetric Spacecraft in the Class of Conical Motions

Cited by 14 publications

References 7 publications

Use of the Method of Guidance by a Required Velocity in Control of Spacecraft Attitude

Use of the Method of Guidance by a Required Velocity in Control of Spacecraft Attitude

Optimal Orientation Control of a Space Vehicle with Restrictions on the Control and Phase Variables

An attitude control by the functional series in the problem of nanosatellite reorientation

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