Development Of Attitude Control System Research Articles

Attitude Control of a Low L/D Re-entry Module with Multiple Equilibrium Points

The paper describes the development of attitude control system of a low L/D atmospheric entry capsule with multiple equilibrium points. The critical phase of flight occurs during the atmospheric aborts where the capsule gets separated from the abort vehicle at an unfavorable angle of attack and traverses multiple equilibrium points to reach the desired trim angle of attack. The nonlinear nature of aerodynamics and control law makes the problem challenging. The objective of this paper is to describe the challenges encountered and solution proposed in the development of control law for the crew capsule during re-entry. Phase plane analysis is extensively used as a tool to develop the control strategy. Performance of the proposed RCS control law is established using 6- DoF simulations for different flight conditions.

Development of attitude control system for hybrid airship vehicle

This paper documents and presents the development of attitude control system of Hybrid Airship Unmanned Aerial Vehicle (HAU) that should be able to change its attitude condition based on the response processed from the provided input. This is accomplished by data acquisition method that retrieves data from a flight controller and processes it into the control system without looking in deep on the mathematical model of the airship. Besides that, PID controller is used in order to create a good stable response for the hybrid airship. A working hybrid airship prototype was successfully developed and built, which is five meters in length and has four propellers that is symmetrically distanced to each other. A quadcopter attitude control mechanism is adopted into the hybrid airship to allow for good hovering capability and direct pure attitude control. Outdoor flight tests have been conducted to prove its stability in responding to attitude input given to the hybrid airship attitude controller. A data monitoring software is also written to make the data observation on the behaviour of the hybrid airship response to be easier and understandable. Result demonstrates that the hybrid airship does response to pitch, roll and yaw input from the operator, albeit the lack response stability and speed which can be improved in conservative continuation of research on the airship attitude control system.

Stability Analysis of the Microsatellite Attitude Control System

The problem of development of the microsatellite attitude control system on the base of reaction wheels positioned along its principal central axes of inertia is considered in this article. As difference from the classical mathematical models describing the microsatellite motion, this article includes the mathematical model of reaction wheel which is controlled by the input voltage of the electric motor. PD-controller is used as the basis for the development of the control law for microsatellite attitude. The stability analysis of the microsatellite attitude control process was carried out with the help of Lyapunov function method. This analysis allowed to prove that obtained attitude control law provides the asymptotic stability of the microsatellite rotational motion. Further, the function of control voltage for the reaction wheel’s electric motor with account of its technical specifications was obtained based on the derived mathematical model of the reaction wheel’s dynamics. The results of performed simulation showed the effectiveness of developed control. Obtained results of the study provide a base for the use of presented approach to the development of attitude control system for microsatellites with various missions.

G1500-2-4 航空機の姿勢制御実験装置(ロボティクス・メカトロニクス部門一般講演(2):機構と制御,社会変革を技術で廻す機械工学)

This paper describes the development of experimental attitude control apparatus which enables the research and development of attitude control system for many kinds of VTOL aircraft. In this equipment experimental VTOL model is set to the central base column through the supporting ball joint. The ball joint admits about ±sixty degrees roll and pitch motion and ±180 degrees yaw motion. Easy and safety experimental research and development can be conducted by this teststand. A design of attitude control system is tried for an experimental VTOL model. A strap-down inertial measurement sensor which includes gyros, accelerometers and magneto-meters is used as a attitude sensor for this test-stand.

Development of Attitude Control System of Micro LabSat

Micro LabSat is a 50(kg) class micro satellite that was launched on December 14, 2002. Micro LabSat switches attitude control modes according to the operation mode. In the nominal operation mode, spin-stabilized control is used. In the mission mode, three axis control is used. Micro LabSat carries only simple low cost sensors for attitude determination. This paper describes design and development of the Micro LabSat attitude control system.

DEVELOPMENT OF ATTITUDE CONTROL SYSTEM OF THE MICROLABSAT

DEVELOPMENT OF ATTITUDE CONTROL SYSTEM OF THE MICROLABSAT