The fundamental objective of autopilot design for missile systems is to provide stability with satisfactory performance and robustness over the whole range of flight conditions throughout the entire flight envelope that missiles are required to operate in, during all probable engagements. Depending on the control mode (skid-to-turn or bank-to-turn), intercept scenario (such as surface to surfac...

The position and velocity errors are divergent of traditional navigation algorithms used in ballistic missile for it cannot estimate the bias of accelerometer precisely. To solve this problem, a novel SINS/CNS integrated navigation algorithm is proposed in this paper, which adds high angle error, azimuth angle error and height error on the basis of the traditional navigation method. As these th...

n semi-active missile guidance, a high-power transmitter not collocated with the missile generates continuous wave or interrupted continuous wave illumination that is reflected from the target to the homing missile. Noise introduced into this illumination, which is reflected from rain, chaff, land, or sea clutter or is carried on spillover, can compete with the target return. The Navy has taske...

We report results from a field demonstration of a nonscanning high-speed imaging spectrometer [computed-tomography imaging spectrometer (CTIS)] capable of simultaneously recording spatial and spectral information about a rapidly changing scene. High-speed spectral imaging was demonstrated by collection of spectral and spatial snapshots of a missile in flight. This instrument is based on compute...

A missile during air carriage is subjected to high vibratory forces. These forces consequently impose high levels of stress on the attachment points to the aircraft. A repetitive application of stress causes fatigue. However, since the vibratory forces cannot be measured directly at the interface, an inverse method utilising missile accelerometer data has been used to determine the forces. This...

This paper investigates the application of velocity-based gain-scheduling techniques to a demanding, highly nonlinear, missile control design task. Scheduling on instantaneous incidence (a rapidly varying quantity) is well known to lead to considerable difficulties with conventional gain-scheduling methods. Moreover, the missile dynamics do not have well-defined relative degree at operating poi...

This paper addresses the problem of bearings only and bearings and extent tracking for closed loop missile guidance systems using particle methods compared with derivative free methods. Lack of observability is a typical phenomenon for the bearings only tracking problem. We demonstrate that exploiting angular extent information does help mitigating the lack of observability issues. The simulati...

Traditionally, missile autopilots have been designed using linear control approaches with gain scheduling. Autopilot design is typically carried out in the frequency domain and the plant is linearized around various operating points on the trajectory. Moreover, three single axis autopilots are usually designed without considering the interaction among the motion axes, i.e., the autopilots in ea...