Abstract
Non-strapdown seeker disturbances which involve counter-electromotive force, spring restoring torque, and friction torque can corrupt the seeker tracking accuracy and degrade the missile guidance performance. In this article, the effects of guidance parameters and disturbances on the guidance stability and the miss distance are analyzed. It is shown that these disturbances have a pronounced deterioration in the guidance performance for the anti-air missile under high altitude and head-on interception. A new approach for disturbance rejection using disturbance observer–based control is presented. Disturbances in seeker stabilizing loop are estimated by the observer which has synthetic inputs based on the available seeker measurement signals. The estimates are fed back into the seeker inner loop to compensate the disturbances, and an additional loop is applied to improve the effect of disturbance compensation. The performance of the approach under non-nominal condition is analyzed. Simulation studies are performed to examine the effect of this control scheme. The result shows that this approach can effectively reduce the influences of corrupting disturbances and significantly improve the miss distance performance.
Highlights
In the missile homing guidance, the line-of-sight (LOS) rate is required to achieve proportional navigation
The results show that the missile guidance system may even become unstable in the cases of high altitude, head-on interception, and large guidance gain
The effect of seeker disturbances, which involve counter-electromotive force (CEMF), spring restoring torque (SRT), and friction torque (FT), on missile guidance stability and miss distance has been studied in this article, and the relationship between guidance performance and main guidance parameters is provided
Summary
In the missile homing guidance, the line-of-sight (LOS) rate is required to achieve proportional navigation. Smita Sadhu[10] extended this method for LOS rate estimation by treating the input signal of the seeker as a disturbance This extension simplified the DOBC structure and did not require any additional sensor, the estimated output is degraded by mismatch dynamics of the mathematic model with the physical system, which is evaluated in simulation. This article focuses on the effect of seeker disturbances (i.e. CEMF, SRT and FT) on missile guidance performance and demonstrates a new control architecture that employs DOBC compensation to eliminate these disturbances. The transfer function Gc = q_ s=q_ t of the LOS rate q_ t input to seeker output q_ s with AL is compensation approach can guarantee the control system working within the stability region at a far target distance.
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