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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
03 May 1978
TL;DR: In this article, a floor track system is used to guide the movement of the missile racks within a cargo compartment of the fuselage for a continuous carousel movement for continuous missile launching sequence.
Abstract: An air launched cruise missile carrier airplane having a floor mounted track system for moving missile racks into a launch position adjacent to a side opening in the fuselage and ejecting missiles therethrough, then moving the empty missile racks from the launch location and repositioning a full rack of missiles thereat. A continuous missile launching sequence is provided by the floor track system which guides the movement of the missile racks within a cargo compartment of the fuselage for a continuous carousel movement.

34 citations

Journal ArticleDOI
TL;DR: In this paper, the authors proposed a nonlinear H∞-guided missile guidance law for pursuit-evasion trajectories, which is expressed in a simple form by solving the associated Hamilton-Jacobi partial differential inequality analytically.
Abstract: This paper proposes a novel three-dimensional missile guidance law design based on nonlinear H∞ control. The complete nonlinear kinematics of pursuit–evasion motion is considered in the three-dimensional spherical co-ordinates system; neither linearization nor small angle assumption is made here. The nonlinear H∞ guidance law is expressed in a simple form by solving the associated Hamilton–Jacobi partial differential inequality analytically. Unlike adaptive guidance laws, the implement of the proposed robust H∞ guidance law does not require the information of target acceleration, while ensuring acceptable interceptive performance for arbitrary target with finite acceleration. The resulting pursuit–evasion trajectories for both the H∞-guided missile and the worst-case target are determined in closed form, and the performance robustness against variations in target acceleration, in engagement condition, and in control loop gain, is verified by numerical simulations. Copyright © 2001 John Wiley & Sons, Ltd.

34 citations

Patent
03 Feb 1975
TL;DR: In this article, a single objective lens for receiving both visible and infrared energy and directing those energies on a first prism is presented, where the first prism separates the visible energy from the infrared energy, and the second prism directs the visible information to an eyepiece for a viewer, followed by a second image of infrared energy at a second sensor by a rotating prism.
Abstract: A missile guidance system is disclosed which utilizes one optical system for visually tracking a target and directing a missile thereto by means of infrared (IR) energy emitted from the missile. The optical system includes a single objective lens for receiving both visible and infrared energy and directing those energies on a first prism. The first prism separates the visible energy from the infrared energy and directs the visible energy to an eyepiece for a viewer. A first image of infrared energy is directed to a first infrared sensor by a retrodirective reflector. A second image of infrared energy is directed at a second sensor by a rotating prism. The output signals from the first and second sensors are provided to missile control circuitry which compares these signals with reference signals and thereby generates command signals for steering the missile to the target.

34 citations

Journal ArticleDOI
TL;DR: In this article, pitch-and roll-damping test mechanisms were developed for obtaining stability characteristics of high fineness ratio missiles at angles of attack up to 90 degrees, and wind-tunnel tests were conducted on two missile configurations at Mach numbers 0.22 through 2.5.
Abstract: Pitch- and roll-damping test mechanisms were developed for obtaining stability characteristics of high fineness ratio missiles at angles of attack up to 90 deg. Wind-tunnel tests were conducted on two missile configurations at Mach numbers 0.22 through 2.5. Mechanism evaluation tests showed that strut interference was not appreciable. The pitch-damping derivatives were found to be highly nonlinear functions of angle of attack, and the roll-damping and Magnus characteristics were very nonlinear with spin rate'at high angles of attack and low Mach numbers. Large and erratic variations in side force and yawing moment with angle of attack and high autorotation characteristics also were found at the low Mach numbers.

34 citations

Journal ArticleDOI
TL;DR: It is shown that on top of enforcing a different flight geometry for the interceptor, the use of the new guidance to collision sliding mode guidance law can enhance the capture zone of the intercepted missile.
Abstract: An exo-atmospheric interception scenario between an accelerating missile and its target is investigated. It is assumed that the maneuvering acceleration is obtained by instantaneous rotation of the missile's body to the required attitude. Two different guidance laws are derived for such an interceptor using the sliding mode control methodology. The difference is in the definition of the sliding surface enforcing different trajectories for the interceptor. It is shown that if this surface is chosen as the zero-effort-miss of the well-known proportional navigation guidance law, then the missile is commanded to point its acceleration vector along the line-of-sight and consequently fly along a curved trajectory. For the second guidance law, a unique sliding surface is chosen enforcing the missile to fly on a straight line towards collision, after the initial heading error is nulled. The performance of the guidance laws is analyzed and compared using a nonlinear two dimensional simulation. It is shown that on top of enforcing a different flight geometry for the interceptor, the use of the new guidance to collision sliding mode guidance law can enhance the capture zone of the interceptor.

34 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20241
2023270
2022639
2021202
2020352
2019451