Results 181 to 190 of about 599 (223)

A self adaptive automatic carrier landing system (ACLS)

1970 IEEE Symposium on Adaptive Processes (9th) Decision and Control, 1970
This paper describes the results of a simulation study carried out to demonstrate the feasibility of a Self Adaptive ACLS. Results indicate that such a system can successfully reduce system errors due to nonlinearities and noise effects.
W. T. Ruxton-davies, F. Powell
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Improved noise rejection in automatic carrier landing systems

Journal of Guidance, Control, and Dynamics, 1992
A technique for reducing the effect of sensor noise in a closed-loop control system is developed. The effect of radar noise on an automatic carrier landing system is studied using digital computer simulation techniques. A noise rejection filter, which blends model estimates of the plane’s vertical velocity and acceleration with altitude information ...
D. Joseph Mook, Douglas A. Swanson, Michael J. Roemer, Roger Noury   +3 more
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Automatic carrier landing systems

1974 IEEE Conference on Decision and Control including the 13th Symposium on Adaptive Processes, 1974
One of the more difficult control problems of the aerospace world is that of successfully landing a flying vehicle. This problem is obviously more severe in some branches of the industry than in others, the U. S. Navy being plagued with probably the most difficult landing situation.
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H-Dot Automatic Carrier Landing System for Approach Control in Turbulence

Journal of Guidance and Control, 1981
The Automatic Carrier Landing System (ACLS) provides a fully automatic approach and landing capability for high-performance carrier-based fighter aircraft. Approach path air turbulence produces significant touchdown error. Using power spectral density definitions of turbulence, a method to determine flight-path deviation due to turbulence and effects ...
R.K. Hess J.M. Urnes, R.F. Moomaw, R.W. Huff   +2 more
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Variable structure approach power compensation system design of an automatic carrier landing system

2009 Chinese Control and Decision Conference, 2009
The design problem of approach power compensation system via variable structure control theory is considered. The function of approach power compensation system in automatic carrier landing system is introduced, and its working principle is analyzed.
null Zhu Qi-dan, null Wang Tong, null Zhang Wen, null Zhou Fang   +3 more
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Adaptive variable structure guidance system design of a longitudinal automatic carrier landing system

2009 Chinese Control and Decision Conference, 2009
The design problem of guidance system of a longitudinal automatic carrier landing system is considered. The mathematic model of the landing guidance problem is created based on the analysis of the main architecture of a longitudinal automatic carrier landing system.
null Zhu Qi-dan, null Wang Tong, null Zhong Xun-yu, null Zhou Fang   +3 more
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On Automatic Landing System for carrier plane based on integration of INS, GPS and vision

2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC), 2016
How to land safely on an aircraft carrier is an important problem for carrier plane. This paper proposes that the relative navigation information of GPS and vision based navigation are integrated with airborne INS and shipboard INS to get accuracy plane-ship relative position which will be used to guide carrier plane to land. CDGPS is used to calculate
null Daquan Tang, null Yongkang Jiao, null Jie Chen   +2 more
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Design of Automatic Carrier Landing Control System using Block Diagonal Controller

2006 6th World Congress on Intelligent Control and Automation, 2006
The block diagonal controller (BDC) was introduced and the properties of aircraft were analyzed simply. Then, the longitudinal motion equations of aircraft were transformed in block diagonal form. And the inverse-analytic solution of longitudinal motion equations was given.
null Guorong Zhao, null Jixin Li, null Muqing Chen   +2 more
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H ∞ Design of the F/A-18A Automatic Carrier Landing System

1995
In this chapter a design of the F/A-18A Automatic Carrier Landing System is accomplished using finite horizon H ∞ techniques. If the final time is sufficiently large, the dynamic Riccati equations involved in the design of the suboptimal output feedback controller give rise to constant solutions.
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Adjustment method of automatic carrier landing system design criterion for scaled model aircraft

2017 36th Chinese Control Conference (CCC), 2017
Based on the dimension theory, this paper deduces the similarity relationships of prototype aircraft and scaled-model aircraft. American army standard AR-40A is an automatic carrier landing system design criterion generally used but not applicable for scaled-model aircraft any more.
Wangqiang Xu, Rong Zhao, Lixin Wang
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