Experimental Results on Dynamic Attitude Control Allocation for a Hexarotor Platform with Faulty Motors

2022 ◽  
Author(s):  
Jesse Jaramillo ◽  
Emre Yildirim ◽  
Ahmet T. Koru ◽  
Tansel Yucelen ◽  
Medrdad Pakmehr ◽  
...  
Keyword(s):  
Attitude Control ◽  
Experimental Results ◽  
Control Allocation

Extended validation of a ground-based three-axis spacecraft simulator model

2020 ◽  
pp. 095441002093896
Author(s):  
H Sh Ousaloo ◽  
Gh Sharifi ◽  
B Akbarinia
Keyword(s):  
Mathematical Model ◽  
Attitude Control ◽  
Aerodynamic Drag ◽  
Center Of Mass ◽  
Model Development ◽  
Optimization Method ◽  
Experimental Results ◽  
Spacecraft Dynamics ◽  
Detailed Model ◽  
Mass Properties

The ground-based spacecraft dynamics simulator plays an important role in the implementation and validation of attitude control scenarios before a mission. The development of a comprehensive mathematical model of the platform is one of the indispensable and challenging steps during the control design process. A precise mathematical model should include mass properties, disturbances forces, mathematical models of actuators and uncertainties. This paper presents an approach for synthesizing a set of trajectories scenarios to estimate the platform inertia tensor, center of mass and aerodynamic drag coefficients. Reaction wheel drag torque is also estimated for having better performance. In order to verify the estimation techniques, a dynamics model of the satellite simulator using MATLAB software was developed, and the problem reduces to a parameter estimation problem to match the experimental results obtained from the simulator using a classical Lenevnberg-Marquardt optimization method. The process of parameter identification and mathematical model development has implemented on a three-axis spherical satellite simulator using air bearing, and several experiments are performed to validate the results. For validation of the simulator model, the model and experimental results must be carefully matched. The experimental results demonstrate that step-by-step implementation of this scenario leads to a detailed model of the platform which can be employed to design and develop control algorithms.

scholarly journals Microplasma thruster for ultra-small satellites: Plasma chemical and aerodynamical aspects

2008 ◽  
Vol 80 (9) ◽  
pp. 2013-2023 ◽  
Author(s):  
Yoshinori Takao ◽  
Takeshi Takahashi ◽  
Koji Eriguchi ◽  
Kouichi Ono
Keyword(s):  
Microwave Power ◽  
Attitude Control ◽  
Specific Impulse ◽  
Experimental Results ◽  
Station Keeping ◽  
Plasma Chemical ◽  
Small Satellites ◽  
Thrust Efficiency

A microplasma thruster has been developed of electrothermal type using azimuthally symmetric microwave-excited microplasmas. The microplasma source was ~2 mm in diameter and ~10 mm long, being operated at around atmospheric pressures; the micronozzle was a converging-diverging type, having a throat ~0.2 mm in diameter and ~1 mm long. Numerical and experimental results with Ar as a working gas demonstrated that this miniature electrothermal thruster gives a thrust of >1 mN, a specific impulse of ~100 s, and a thrust efficiency of ~10 % at a microwave power of <10 W, making it applicable to attitude-control and station-keeping maneuver for a microspacecraft of <10 kg.

scholarly journals Attitude Blended Control for Aerospace Vehicle with Lateral Thrusters and Aerodynamic Fins

2019 ◽  
Vol 37 (3) ◽  
pp. 532-540
Author(s):  
Aijun Li ◽  
Yu Wang ◽  
Yong Guo ◽  
Changqing Wang
Keyword(s):  
Control Strategy ◽  
Finite Time ◽  
Attitude Control ◽  
Sliding Mode ◽  
Control Allocation ◽  
Sliding Mode Controller ◽  
Attitude Error ◽  
The Neural Network ◽  
And Control ◽  
Attitude Model

A finite-time blended control strategy is proposed for the reentry phase attitude control of the aerospace vehicle (ASV) based on the neural network, sliding mode control theory and control allocation. Firstly, a finite-time neural networks sliding mode controller is designed based on the attitude model of the ASV in the reentry phase to obtain the virtual control moments which can make the attitude error converge to the equilibrium point in finite time. Secondly, the desired control moments are mapped into the control commands on the aerodynamic deflectors and the reaction control system (RCS) by using the control allocation. Finally, simulation results are provided to demonstrate the effectiveness of the attitude blended control strategy proposed.

scholarly journals Control Allocation for Double-ended Ferries with Full-scale Experimental Results

2020 ◽  
Vol 18 (3) ◽  
pp. 556-563
Author(s):  
Tobias R. Torben ◽  
Astrid H. Brodtkorb ◽  
Asgeir J. Sørensen
Keyword(s):  
Full Scale ◽  
Experimental Results ◽  
Control Allocation

scholarly journals Control Allocation Design of Reaction Control System for Reusable Launch Vehicle

2014 ◽  
Vol 2014 ◽  
pp. 1-13 ◽  
Author(s):  
Rongjun Mu ◽  
Xin Zhang
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Control Method ◽  
Early Stage ◽  
Launch Vehicle ◽  
Programming Algorithm ◽  
Control Allocation ◽  
Control Effect ◽  
Reusable Launch Vehicle ◽  
Reaction Control System

During the early stage of reusable launch vehicle (RLV) reentry flight, reaction control system (RCS) is the major attitude control device. RCS, which is much different from the atmospheric steer’s control, requires a well designed control allocation system to fit the attitude control in high altitude. In this paper, an indexed control method was proposed for RCS preallocation, a 0-1 integer programming algorithm was designed for RCS allocation controller, and then this RCS scheme’s effect was analyzed. Based on the specified flight mission simulation, the results show that the control system is satisfied. Moreover, several comparisons between the attitude control effect and RCS relevant parameters were studied.

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