Inverse Optimal Control Via Diagonal Stabilization Applied to Attitude Tracking of a Reusable Launch Vehicle

2021 ◽  
Author(s):  
Prasanna Parvathy ◽  
Jeevamma Jacob
Keyword(s):  
Optimal Control ◽  
Launch Vehicle ◽  
Inverse Optimal Control ◽  
Reusable Launch Vehicle ◽  
Attitude Tracking

Predefined-time control for a horizontal takeoff and horizontal landing reusable launch vehicle

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Liang Zhang ◽  
Liang Jing ◽  
Liheng Ye ◽  
Xing Gao
Keyword(s):  
Disturbance Observer ◽  
Control Parameter ◽  
Sliding Mode ◽  
Fixed Time ◽  
Launch Vehicle ◽  
Convergence Time ◽  
Content Type ◽  
Reusable Launch Vehicle ◽  
Attitude Tracking ◽  
Tracking Controller

Purpose This paper aims to investigate the problem of attitude control for a horizontal takeoff and horizontal landing reusable launch vehicle. Design/methodology/approach In this paper, a predefined-time attitude tracking controller is presented for a horizontal takeoff and horizontal landing reusable launch vehicle (HTHLRLV). Firstly, the attitude tracking error dynamics model of the HTHLRLV is developed. Subsequently, a novel sliding mode surface is designed with predefined-time stability. Furthermore, by using the proposed sliding mode surface, a predefined-time controller is derived. To compensate the external disturbances or model uncertainties, a fixed-time disturbance observer is developed, and its convergence time can be defined as a prior control parameter. Finally, the stability of the proposed sliding mode surface and the controller can be proved by the Lyapunov theory. Findings In contrast to other fixed-time methods, this controller only requires three control parameters, and the convergence time can be predefined instead of being estimated. The simulation results also demonstrate the effectiveness of the proposed controller. Originality/value A novel predefined-time attitude tracking controller is developed based on the predefined-time sliding mode surface (SMS) and fixed-time disturbance observer (FxTDO). The convergence time of the system can be selected as a prior control parameter for SMS and FxTDO.

scholarly journals Finite-Time Anti-Disturbance Inverse Optimal Attitude Tracking Control of Flexible Spacecraft

2013 ◽  
Vol 2013 ◽  
pp. 1-13 ◽  
Author(s):  
Chutiphon Pukdeboon ◽  
Anuchit Jitpattanakul
Keyword(s):  
Optimal Control ◽  
Lyapunov Function ◽  
Finite Time ◽  
Estimation Error ◽  
State Observer ◽  
Flexible Spacecraft ◽  
Extended State Observer ◽  
Inverse Optimal Control ◽  
Extended State ◽  
Attitude Tracking

We propose a new robust optimal control strategy for flexible spacecraft attitude tracking maneuvers in the presence of external disturbances. An inverse optimal control law is designed based on a Sontag-type formula and a control Lyapunov function. An adapted extended state observer is used to compensate for the total disturbances. The proposed controller can be expressed as the sum of an inverse optimal control and an adapted extended state observer. It is shown that the developed controller can minimize a cost functional and ensure the finite-time stability of a closed-loop system without solving the associated Hamilton-Jacobi-Bellman equation directly. For an adapted extended state observer, the finite-time convergence of estimation error dynamics is proven using a strict Lyapunov function. An example of multiaxial attitude tracking maneuvers is presented and simulation results are included to show the performance of the developed controller.

scholarly journals A Hybrid Parallel Harris Hawks Optimization Algorithm for Reusable Launch Vehicle Reentry Trajectory Optimization With No-fly Zones

2021 ◽  
Author(s):  
Ya Su ◽  
Ying Dai ◽  
Yi Liu
Keyword(s):  
Optimal Control ◽  
Trajectory Optimization ◽  
Launch Vehicle ◽  
Parallel Optimization ◽  
Initial Population ◽  
Smoothing Technique ◽  
Reusable Launch Vehicle ◽  
Reentry Trajectory ◽  
Reentry Trajectory Optimization ◽  
Optimization Mechanism

Abstract Reentry trajectory optimization is a critical optimal control problem for reusable launch vehicle (RLV) with highly nonlinear dynamic characteristics and complex constraints. In this paper, a hybrid parallel harris hawks optimization (HPHHO) algorithm is proposed to address the problem. HPHHO aims to enhance the performance of existing harris hawks optimization (HHO) algorithm by three strategies including oppositional learning, smoothing technique and parallel optimization mechanism. At the beginning of each iteration, the opposite population is calculated from the current population by the oppositional learning strategy. Following that, the individuals in the two populations are arranged in ascending order on the basis of the fitness function values, and the top half of the resulting population is selected as the initial population. The selected initial population is divided into two equal subpopulations which are assigned to the differential evolution and the HHO algorithm, respectively. The both algorithms operate in parallel to search and update the solutions of each subpopulation simultaneously. Then the solutions are smoothed for each iteration by the smoothing technique to reduce fluctuations. As a result, the optimal solution obtained by the parallel optimization mechanism avoids falling into local optima. The performance of HPHHO is evaluated by 4 CEC 2005 benchmark functions and 3 constrained continuous optimal control problems, showing better efficiency and robustness in terms of performance metrics, convergence rate and stability. Finally, the simulation results show that the proposed algorithm is very effective, practical and feasible in solving the RLV reentry trajectory optimization problem.

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