Topic
Missile
About: Missile is a research topic. Over the lifetime, 12829 publications have been published within this topic receiving 94307 citations. The topic is also known as: guided missile & missiles.
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Patent•
28 Jan 1982
TL;DR: In this paper, a missile container for storing a missile and having an extraction mechanism for extracting the missile from the container and placing the missile in the proper launch attitude is described, but the mechanism is not described.
Abstract: A missile container for storing a missile therein and having an extraction mechanism for extracting the missile from the container and placing the missile in the proper launch attitude.
21 citations
TL;DR: In this paper, the authors developed an optimal guidance law that takes into account both the missile acceleration limit and a maximum value allowed for the guidance gain, which is dictated mainly by the possible coupling between the missile body motions and the measurement of the inertial target line-of-sight angle rate.
Abstract: The purpose of this paper is to develop an optimal guidance law that takes into account both the missile acceleration limit and a maximum value allowed for the guidance gain. The maximum value of the guidance gain is dictated mainly by the possible coupling between the missile body motions and the measurement of the inertial target line-of-sight angle rate. The tools for this work are the linear quadratic stochastic Gaussian optimal control theory coupled with the use of random-input describing functions. Although the use of the random-input describing function introduces an approximation in the work, it has been shown in the past that the use of random-input describing functions in miss distance calculations results in good approximations for the predicted miss distance. The paper includes the derivation of the optimal guidance law that accounts for both the missile acceleration limit and the constraint on the guidance gain and a simple one-dimensional Monte Carlo simulation to examine the performance of the guidance law.
21 citations
TL;DR: The results of this study show that identification of aerodynamic coefficients from time-accurate simulation of the forced motions requires significantly less computational time, and could reduce the computational cost of estimating stability derivatives up to 90%.
21 citations
TL;DR: A new EM brake is designed which is more energy efficient and reliable compared to a conventional solenoid operated brake and can be adapted for aerospace and other critical applications.
Abstract: Electromagnetic (EM) brakes are gaining importance in aerospace vehicles for various critical applications In guided missiles, they are primarily used for locking the actuator when the missile is in carriage either by road or by air such that the position of the actuator is not changed when servo is in the off condition In this paper, a new EM brake is designed which is more energy efficient and reliable compared to a conventional solenoid operated brake The nonlinear magnetic analysis is carried out on the brake, and the hardware is realized and tested The test results are promising and this topology can be adapted for aerospace and other critical applications
21 citations
Patent•
17 Sep 1974TL;DR: In this paper, a guidance system for automatically boresighting a small field-of-view, lresolution image, sensed by an infrared missile imaging sensor, to a large field of view, high-resolution image was proposed.
Abstract: A guidance system for automatically boresighting a small field-of-view, lresolution image, sensed by an infrared missile imaging sensor, to a large field-of-view, high-resolution image, sensed by an imaging sensor located within an airplane. The image sensed by each sensor is applied to a digital correlator which makes a bit-by-bit digital correlation of the images. The image sensed by the large field-of-view aircraft sensor is monitored on a CRT. Cross-hairs are placed at the centerpoint of the area in the monitored aircraft sensor image which has the highest correlation with the missile sensor image. Thus the boresight of the missile sensor is ostensibly located in the monitored, aircraft, sensor image. This system may be used to slave automatically one sensor boresight to another. Where a plurality of missiles are carried by one plane, the boresight of each missile may be located in the large field-of-view aircraft monitor.
21 citations