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Air-to-air missile

About: Air-to-air missile is a(n) research topic. Over the lifetime, 445 publication(s) have been published within this topic receiving 3165 citation(s). The topic is also known as: AAM & air intercept missile.

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Journal ArticleDOI
Abstract: Current air-to-air missile guidance and control technology is assessed. Areas explored include target state estimation, advanced guidance laws, and bank-to-turn autopilots. The assumptions, benefits, and limitations of recent applications of nonlinear filtering, adaptive filtering, modern control, adaptive control, dual control, differential game theory, and modern control design techniques to the air-to-air missile problem are discussed. >

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145 citations


Journal ArticleDOI
Ernest Ohlmeyer1, Craig Phillips1Institutions (1)
Abstract: This paper proposes and evaluates a new guidance law termed generalized vector explicit guidance (GENEX). This guidance law can simultaneously achieve design specifications on miss distance and final missile-target relative orientation. The latter may be used to enhance the performance of warheads the effectiveness of which is influenced by the terminal encounter geometry. The GENEX guidance law is parameterized in terms of a design coefficient that determines the degree of curvature in the trajectory. Feasibility of GENEX guidance was demonstrated by its application to two weapon scenarios. The first was an air-to-air missile terminal homing scenario. Assuming ideal sensor information and a single-lag missile response model, the guidance was shown to perform well against an air target performing evasive maneuvers. A specified zero-aspect terminal encounter angle was achieved while simultaneously minimizing miss distance. The second application involved an air-to-surface munition released from an unmanned air vehicle. The GENEX guidance law was able to produce trajectories satisfying a terminal impact angle constraint. In addition, an engagement region of sufficient size was shown to be achievable using guidance gains scheduled with target location and weapon release altitude.

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140 citations


Journal ArticleDOI
Fred Austin, Giro Carbone, Hans Hinz, Michael S. Lewis1  +1 moreInstitutions (1)
TL;DR: A game-matrix approach has been developed to generate intelligent maneuvering decisions for low-flying aircraft during one-on-one air combat over hilly terrain and generates some of the tactics employed by experienced pilots in combat flight tests.

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Abstract: A game-matrix approach has been developed to generate intelligent maneuvering decisions for low-flying aircraft during one-on-one air combat over hilly terrain. The decisions are made by comparing scores based on the predicted orientation, range, velocity, and terrain clearance for various maneuver combinations of both aircraft. A computer program implements the decision process in real time and computes the state of the aircraft employing the selected maneuvers. Predicted states are obtained by numerically integrating the dynamic equations. The program has been installed and demonstrated at the NASA Ames vertical motion simulator to provide an automated adversary for manned helicopter combat simulations. A stand-alone version of the program, in which the decisions of both combatants are generated by the computer, has also been prepared for nonpiloted simulations. Sample trajectories show that this new automated maneuvering logic generates some of the tactics employed by experienced pilots in combat flight tests. Whereas the current application applies to helicopter combat, the program can be used for fixed-wing aircraft by replacing those subroutines that provide the aircraft capabilities.

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81 citations



Journal ArticleDOI
Abstract: Examines the closed-loop stability of a bank-to-turn, air-to-air missile with a dynamic inversion controller using a two time-scale separation assumption. A state-space formulation for the /spl alpha/, /spl beta/, and /spl phi/ dynamics of the missile, assuming the inner-loop dynamic inversion is performed exactly, is presented. It is then shown that, under certain assumptions, the exponential stability of the /spl alpha/, /spl beta/, and /spl phi/ dynamics about the commanded values can be guaranteed if the inner loop design frequency is large enough. An example calculation of the required inner-loop frequency to guarantee stability is done for a particular bank-to-turn missile. Finally, nonlinear six degree-of-freedom simulation results of a maneuver performed with the dynamic inversion controller are presented.

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77 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20212
20207
201911
20187
201714
201613

Top Attributes

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Topic's top 5 most impactful authors

Min-Jea Tahk

4 papers, 18 citations

Debasis Chakraborty

4 papers, 22 citations

K. Anandhanarayanan

3 papers, 17 citations

Takeshi Kuroda

3 papers, 66 citations

Konark Arora

3 papers, 16 citations