H ∞ Design of the F/A-18A Automatic Carrier Landing System

Subrahmanyam, M. B.

doi:10.1007/978-1-4612-4272-7_6

Cited by 11 publications

(15 citation statements)

References 2 publications

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“…As discussed in [14], the Navy Automatic Carrier Landing System (ACLS) consists of a shipboard radar, computer system, and a data link to the aircraft autopilot. The role of the computer system is to calculate pitch and bank commands based on the current aircraft position and ship motion; these commands are transmitted to the aircraft via a radio frequency data link.…”

Section: Descriptionmentioning

confidence: 99%

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Stable adaptive fault-tolerant control of overactuated aircraft using multiple models, switching and tuning

Boskovic

Mehra

1998

Guidance, Navigation, and Control Conference and Exhibit

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In this paper we considered the existing stable adaptive fault-tolerant control system design from references [3,4] for achieving acceptable flight performance in the presence of control effector failures. This controller is developed for the overactuated case, i.e. the case when the number of control effectors exceeds the number of controlled outputs. We have shown that, in some cases, single or multiple effector failures introduce disturbances that are too large to be effectively handled by a single adaptive controller. To address this problem, in this paper we developed an adaptive fault-tolerant flight control system based on the concept of multiple models, switching and tuning from reference [11]. We have shown that such a controller yields a stable overall system, is sufficiently robust in the presence of severe control effector failures, and achieves excellent overall performance as illustrated through simulations of F/A-18A carrier landing maneuver.

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Section: Descriptionmentioning

confidence: 99%

“…The performance' achieved using the switching scheme suggested in this paper was illustrated using the F/A-18A carrier landing maneuver described in detail in [14].…”

Section: Introductionmentioning

confidence: 99%

Stable adaptive fault-tolerant control of overactuated aircraft using multiple models, switching and tuning

Boskovic

Mehra

1998

Guidance, Navigation, and Control Conference and Exhibit

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“…It was noted that those gains were designed without considering the wind shear turbulence in a classical technique (e.g., root-locus and optimal control [7]). Also, the gains in (9) satisfied the constraint in (10). for j=P,I,D.…”

Section: Design Of Gain-scheduled Controllermentioning

confidence: 82%

“…Substantial research has been carried out on the design of an auto-landing controller. Examples include a linear quadratic Gaussian with a Loop Transfer Recovery technique for commercial aircrafts encountering wind shear [7,8], an H ∞ − output feedback synthesis technique for an F-14 aircraft [9], and finite horizon H ∞ − techniques for the F/A-18A [10]. Other examples include a mixed 2 / H H ∞ − technique with gain scheduling [11], an H ∞ − control problem in which the wind shear effect is minimized [12], and an H ∞ − control technique for robust gain-scheduled controller design to handle the longitudinal auto-landing maneuvers of aircraft encountering dangerous wind shear [13].…”

Section: Introductionmentioning

confidence: 99%

Gain-scheduled directional guidance controller design using a genetic algorithm for automatic precision landing

2010

Int. J. Control Autom. Syst.

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This paper discusses the guidance controller design problem of an aircraft in automatic landing and touchdown flight, subject to dangerous and unpredictable gusts known as wind-shear and to directional crosswind. The associated airplane in the landing flight was statically unstable in this paper. The wind-shear, based on the Dryden gust model, was included in the nonlinear airplane model. A directional guidance control system with gain-scheduling fuzzy logic was proposed in this paper. In fuzzy logic, an even number of exponential membership functions in the output are considered and their shape, decay rate, and scaling factors are optimized using a genetic algorithm. In this control system, the glide slope capture logic and the flare logic were also included for longitudinal and lateral control, respectively. The nonlinear aircraft model simulation illustrated that the proposed guidance control system shows satisfactory performances in accurate touchdowns and is adequately robust to the strong crosswind and wind-shear turbulences.

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“…The following equation is obtained as follows: At this datum state [13][14] , the characteristic of longitudinal motion of aircraft is presented as follows:…”

Section: Systemmentioning

confidence: 99%

Approach power compensator system with variable structure control based on sliding mode

Dong

Zhang

2014

2014 IEEE International Conference on Mechatronics and Automation

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Approach power compensator system for carrierbased aircraft was studied. A variable structure control based on sliding mode for discrete-time system was used to design approach power compensator system with the constant angle of attack on ground velocity. The integrated simulation model of automatic carrier landing for aircraft was constructed. The simulation results show that: a carrier-based aircraft can fly along the expected flight path and touchdown the angle deck with approach power compensator system. It can effectively resist the terminal approach carrier disturbance, and the aircraft flying qualities in landing on carrier are improved.Index Terms -approach power compensator; variable structure control; aircraft; constant angle of attack; flying quality

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H ∞ Design of the F/A-18A Automatic Carrier Landing System

Cited by 11 publications

References 2 publications

Stable adaptive fault-tolerant control of overactuated aircraft using multiple models, switching and tuning

Stable adaptive fault-tolerant control of overactuated aircraft using multiple models, switching and tuning

Gain-scheduled directional guidance controller design using a genetic algorithm for automatic precision landing

Approach power compensator system with variable structure control based on sliding mode

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