Directional stability of a large receiver aircraft in air-to-air refueling

Bloy, A. W.; Lea, K. A.

doi:10.2514/3.46741

Cited by 14 publications

(8 citation statements)

References 2 publications

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“…Air Force Research Laboratory,Air Vehicles Directorate,Wright Patterson AFB,OH,45433 8. PERFORMING ORGANIZATION REPORT NUMBER…”

Section: Performing Organization Name(s) and Address(es)mentioning

confidence: 99%

“…While the effect of the leader's vortices on the follower in a formation flight is beneficial in reducing drag/fuel consumed, 1 the influence of a tanker's vortices on a receiver aircraft during aerial refueling 2,3 can be detrimental to the stability of the receiver aircraft. There has been some recent work [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18] dealing with demonstration of the benefit of and issues with the control system development for aerial refueling. However, they do not study the effect of the tanker's trailing wake vortex on the receiver aircraft.…”

Section: Introductionmentioning

confidence: 99%

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Flight Control and Simulation for Aerial Refueling

Dogan¹,

Sato

2005

AIAA Guidance, Navigation, and Control Conference and Exhibit

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This paper addresses the problem of controlling the receiver aircraft to achieve a successful aerial refueling. For the performance verification of the controller, a new set of nonlinear, 6-DOF, rigid body equations of motion for the receiver aircraft has been derived. The equations are developed using the reference frame as one that is attached to, translates and rotates with the tanker aircraft. Furthermore, the nonlinear equations contain the wind effect terms and their time derivatives to represent the aerodynamic coupling involved between the two aircraft. These wind terms are obtained using an averaging technique that computes the effective induced wind components and wind gradients in the receiver aircraft's body frame. Dynamics of the engine and the actuators are also included in the study. A linear position-tracking controller has been designed using a combination of integral control and optimal LQR design. The controller does not use the information of the tanker's vortex induced wind effects acting on the receiver aircraft as well as the mass change that occurs during refueling. The performance of the controller is evaluated in the high fidelity simulation environment employing the new sets of equations of motion. The simulation and control design are applied to a tailless fighter aircraft with innovative control effectors and thrust vectoring capability. Various allocation schemes for redundant control variables are analyzed in a realistic approach maneuver to the refueling contact position behind the tanker aircraft. In this paper, the performance evaluation is presented only during the initial phase of aerial refueling maneuver when the receiver aircraft maneuvers to reach the refueling contact position.

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“…Air Force Research Laboratory,Air Vehicles Directorate,Wright Patterson AFB,OH,45433 8. PERFORMING ORGANIZATION REPORT NUMBER…”

Section: Performing Organization Name(s) and Address(es)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Flight Control and Simulation for Aerial Refueling

Dogan¹,

Sato

2005

AIAA Guidance, Navigation, and Control Conference and Exhibit

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“…There are two reference frames with vectrices [1] and [2]. The rotation matrix from the first frame to the second is defined to be R 21 .…”

Section: Matrix and Vector Propertiesmentioning

confidence: 99%

“…This operation might be needed to sustain/complete some critical flight missions that require an endurance or range beyond what the aircraft, either military or commercial [1], was designed for. The important modeling and control problems studied in the context of aerial refueling [2,3,4,5,6,7] include models of the tanker-receiver interference, stability of the receiver aircraft and design of an autonomous refueling controller. There has been a great interest in the research community [7] to develop an autonomous and efficient control algorithm that would enable a successful aerial refueling, with least disturbance effect on the receiver aircraft during the whole operation.…”

Section: Introductionmentioning

confidence: 99%

Derivation of the Dynamics Equations of Receiver Aircraft in Aerial Refueling

Waishek

Dogan

Blake

2009

Journal of Guidance, Control, and Dynamics

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“…Recent work [3][4][5][6][7][8][9][10][11][12][13][14][15][16] has dealt with demonstration of the benefit of and issues with the control system development for aerial refueling. Most of this work treats the vortex as an unknown disturbance or stochastic turbulence in the control law development and validation procedure.…”

mentioning

confidence: 99%

Flight Data Analysis and Simulation of Wind Effects During Aerial Refueling

Lewis

2008

Journal of Aircraft

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To my brothers Ben and John, from whom I have learned much. ACKNOWLEDGEMENTSI am continually grateful to my supervising professor, Dr. Atilla Dogan, for his support of my graduate work at UTA. I have greatly benefited from the opportunities for research and publishing he has provided over the last two years, and I thank him for involving me early in research during my first semester in the master's program.His knowledge and guidance have proven invaluable to my academic career.

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Directional stability of a large receiver aircraft in air-to-air refueling

Cited by 14 publications

References 2 publications

Flight Control and Simulation for Aerial Refueling

Flight Control and Simulation for Aerial Refueling

Derivation of the Dynamics Equations of Receiver Aircraft in Aerial Refueling

Flight Data Analysis and Simulation of Wind Effects During Aerial Refueling

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