Multiple-input describing function technique applied to design a single channel ON-OFF controller for a spinning flight vehicle

Abstract

In this study, the guidance and control problem of a single-channel spinning missile is investigated. The missile utilizes a single ON-OFF actuator to drive a pair of control surfaces (e.g. elevators) and consequently to perform all required lateral maneouvers. An approximated linear response of the so-called non-rotating frame to ON-OFF input, applied to the rotating frame, is derived using the multiple-input describing function technique. It is shown that there is a relationship between the response of the non-rotating frame and that of the equivalent non-rotating body. It is also shown that the two-channel flight controller, designed for the equivalent non-rotating body, can be reduced to a single-channel controller, the output of which is applied to the rotating body. A necessary condition is introduced for this purpose. A proportional navigation guidance law for such a spinning missile is also introduced that generates an angular rate command instead of the acceleration command. Finally, the performance of the proposed controller in the presence of noise and uncertainties is validated through flight simulations.

Retrofiring control method via combination of a 1DoF gimbaled thrust vector control and spin-stabilization

“…In addition to the control gain K , two major decision parameters should be studied in the spacecraft design: (1) spin rate ωs and (2) spin-axis moment of inertia I 1 . Some reasons that confirm this majority are listed: To reduce the fuel consumption, the value of E s should be as small as possible 4 where Es=I1ωs 2 is the total energy needed for spin and despin. A high spin rate may damage the spacecraft structure, saturate the sensors and excite the flexibility and unmodeled dynamics; thus, it is better to design a spacecraft with a smaller ωs. Generally, I1=Imin results in a cylinder shape spacecraft and I1=Imax gives a disc shape one. Shape of a spacecraft may be important for a launcher; therefore, it is better to investigate the effects of some moment of inertia in the range of Imin≤I1≤Imax. …”

“…To reduce the fuel consumption, the value of E s should be as small as possible 4 where Es=I1ωs 2 is the total energy needed for spin and despin.…”

New Heuristic Algorithms for Rolling Air Frame Aerodynamic Parameters Estimation

“…The aerodynamic forces and moments calculated in first step are smoothed using Savitzky-Golay filter (Nirmal et al, 2016). In this filter a set of integers (A -n , A -(n-1) , …, A n-1 , A n ) are weighting coefficients to carry out the smoothing operation.…”

Retuning the actuator proportional–integral–derivative controller of spinning missiles

“…5 More sophisticated analyses usually regard the actuator as a second-order delayed system, and the required bandwidth is three or four times greater than the desired autopilot bandwidth to ensure a small phase lag. 6,7 However, for spinning missiles, there are no specific requirements for the actuators, although some papers have noted that the phase lag of the actuator should be sufficiently small to ensure the stability of the autopilot, [8][9][10][11] and its dynamic stiffness should be sufficiently large to resist the hinge moment. 12 Because the induced out-of-plane moment is a destabilizing factor for spinning missiles, another design criterion for the actuator is that it must guarantee the stability of the missile.…”