A- 26 Invader in Action by Jim Mesko

By Jim Mesko

A- 26 Invader in motion - Squadron/Signal 1134 КНИГИ ;ВОЕННАЯ ИСТОРИЯ Издательство: Squadron/Signal courses Серия: airplane 134 Название: A-26 Invader in motion Язык: English Год издания: 1993 Количество страниц: forty nine ISBN: 0-89747-296-9 Формат: pdf Размер: 10.8 mb eighty five

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3 we demonstrate the design of a space station attitude control system using CMGs. 3 LINEAR PERTURBATION EQUATIONS USED IN CONTROL ANALYSIS The following differential equations are linearized about an operating point or a trim condition. ” They are used for analyzing vehicle stability in the frequency domain, robustness to parameter uncertainties, and for designing control laws at fixed flight conditions. They are also used in linear simulations to appraise the vehicle performance by examining its response to commands and transient disturbances.

37) where ????o Jw Jv is the orbital rate, is the individual wheel moment of inertia about their spin axis, is the spacecraft inertia and it includes the weights of the reaction wheels. 8. It consists of a spinning rotor that is mounted on a structure that can be gimbaled perpendicular to the rotor axis. The rotor spin rate is maintained at a constant speed by a small motor that produces a constant angular momentum h. It is the precession of this vector that produces a useful output torque that is substantially greater than a reaction wheel torque, and for this reason it is very attractive in high torque and Ref .

It minimizes sideslip and undesirable aeroloading by rolling about the velocity vector V0 , and it maximizes aerodynamic efficiency. To perform coordinated stability axis rolls, both roll and yaw systems are used to provide roll control about the velocity vector and to maintain zero sideslip. At low angles of attack there is usually adequate rudder power to obtain the desired motion. However, as the angle of attack increases, the demand on rudder authority increases rapidly. 20. This loop allows the vehicle to achieve its commanded roll rate, otherwise, without the turn coordination feedback it would result in a nonzero steady-state roll rate error.

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