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- W1532966001 abstract "This paper demonstrates a guidance and control scheme for a spinning, aerodynamically asymmetrical vehicle. Attitude manoeuvres of such a vehicle are complicated primarily by the fact that the dynamics cannot be linearised in a mathematically well-posed way. In the proposed scheme, a non-linear guidance law acts as an outer loop to issue commands to an autopilot system. The guidance law accepts sensor inputs and desired attitude information and calculates pitch and yaw-rate commands for autopilot input, based on error in attitude and additional compensation terms derived from Euler's rotational equations. The autopilot control system consists of two self-adaptive single-input, single-output (SISO) proportional plus integral controllers, derived using the pole placement technique. A numerical 6 degree-of-freedom simulation shows that a 4.24 kg, unpowered supersonic payload, called the HyShot Stability Demonstrator, that starts at Mach 3.5 would be capable of attitude manoeuvres at a spin-rate of 2.0 Hz." @default.
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- W1532966001 date "2011-01-01" @default.
- W1532966001 modified "2023-09-26" @default.
- W1532966001 title "Attitude guidance and control for a spinning, asymmetrical rocket payload" @default.
- W1532966001 hasPublicationYear "2011" @default.
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