A Fast and Efficient Attitude Control Algorithm of a Tilt-Rotor Aerial Platform Using Inputs Redundancies

2021 ◽  
pp. 1-1
Author(s):  
Yao Su ◽  
Lecheng Ruan ◽  
Pengkang Yu ◽  
Chen-Huan Pi ◽  
Matthew Gerber ◽  
...  
Keyword(s):  
Attitude Control ◽  
Control Algorithm ◽  
Tilt Rotor ◽  
Aerial Platform

scholarly journals Design of Satellite Attitude Control Algorithm Based on the SDRE Method Using Gas Jets and Reaction Wheels

2013 ◽  
Vol 2013 ◽  
pp. 1-8 ◽  
Author(s):  
Luiz C. G. de Souza ◽  
Victor M. R. Arena
Keyword(s):  
Attitude Control ◽  
Control Algorithm ◽  
Controller Design ◽  
Algorithm Design ◽  
Large Angle ◽  
Space Mission ◽  
Control Technique ◽  
Gas Jets ◽  
State Dependent ◽  
Highly Nonlinear

An experimental attitude control algorithm design using prototypes can minimize space mission costs by reducing the number of errors transmitted to the next phase of the project. The Space Mechanics and Control Division (DMC) of INPE is constructing a 3D simulator to supply the conditions for implementing and testing satellite control hardware and software. Satellite large angle maneuver makes the plant highly nonlinear and if the parameters of the system are not well determined, the plant can also present some level of uncertainty. As a result, controller designed by a linear control technique can have its performance and robustness degraded. In this paper the standard LQR linear controller and the SDRE controller associated with an SDRE filter are applied to design a controller for a nonlinear plant. The plant is similar to the DMC 3D satellite simulator where the unstructured uncertainties of the system are represented by process and measurements noise. In the sequel the State-Dependent Riccati Equation (SDRE) method is used to design and test an attitude control algorithm based on gas jets and reaction wheel torques to perform large angle maneuver in three axes. The SDRE controller design takes into account the effects of the plant nonlinearities and system noise which represents uncertainty. The SDRE controller performance and robustness are tested during the transition phase from angular velocity reductions to normal mode of operation with stringent pointing accuracy using a switching control algorithm based on minimum system energy. This work serves to validate the numerical simulator model and to verify the functionality of the control algorithm designed by the SDRE method.

Robust Nonlinear Combined Attitude Control Algorithm Using Control Moment Gyro for Agile Satellites

2016 ◽  
Author(s):  
Mohamed A. Elkhayat ◽  
Yehia Elhalwagy ◽  
Ahmed Yehia ElRaffie ◽  
Gamal Ahmed Elnashar
Keyword(s):  
Attitude Control ◽  
Control Algorithm ◽  
Control Moment ◽  
Control Moment Gyro

scholarly journals An Underwater Vector Propulsion Device Based on the RS+2PRS Parallel Mechanism and Its Attitude Control Algorithm

2019 ◽  
Vol 9 (23) ◽  
pp. 5210 ◽  
Author(s):  
Wang ◽  
Guo ◽  
Zhong
Keyword(s):  
Attitude Control ◽  
Parallel Mechanism ◽  
Control Algorithm ◽  
Simulation Analysis ◽  
Autonomous Underwater Vehicles ◽  
Propulsion System ◽  
Precession Angle ◽  
Nutation Angle ◽  
Prismatic Joints ◽  
Spherical Parallel Mechanism

In order to overcome the disadvantages of some existing autonomous underwater vehicles (AUVs), such as actuator extraposition and degree-of-freedom (DOF) redundancy, a 2-DOF vector propeller propulsion system with built-in actuator based on the deficient DOF parallel mechanism is proposed. The RS+2PRS (Revolute-Spherical+ Prismatic-Revolute-Spherical) parallel mechanism is used as the main structure, and the driving parts are placed in the interior of the AUV cabin, which is beneficial to the sealing and protection of the propulsion system. In addition, the motion parameters decoupling shows that the two independent parameters are the precession angle and the nutation angle of the propeller installation platform. Therefore, the attitude control algorithm uses two prismatic joints as driving units to establish the nonlinear mapping model with the two Euler attitude angles. In the end, the simulation analysis and the real device are used to verify the feasibility of the attitude control algorithm and the in situ adjustment function of the propeller, which lays the theoretical foundation for engineering applications in the future.

Model predictive attitude control of an unmanned Tilt-Rotor aircraft

2011 ◽  
Author(s):  
Christos Papachristos ◽  
Kostas Alexis ◽  
George Nikolakopoulos ◽  
Anthony Tzes
Keyword(s):  
Attitude Control ◽  
Tilt Rotor
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