Aerial Refueling Implications for Commercial Aviation

Bennington, Matthew A.; Visser, Kenneth D.

doi:10.2514/1.4770

Cited by 31 publications

(10 citation statements)

References 4 publications

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“…where a and b are representations of a and b, respectively, in the frame having vectrix [1]. Note that S(a) is a skew-symmetric matrix constructed with representation a such that…”

Section: Factmentioning

confidence: 99%

“…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%

“…In the case of aerial refueling, fuel transferred to the receiver aircraft brings in momentum and changes its inertia properties. Previous works [45,7,46,47,48,49,50,51,1,52] in aerial refueling either ignore the effect of mass transfer or treat it as disturbance causing parametric uncertainty [7]. In this work, the equations of motion for the receiver are derived considering the system of the receiver aircraft and the fuel before and after being transferred into the receiver.…”

Section: Introductionmentioning

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.…”

Section: Introductionmentioning

confidence: 99%

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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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“…where a and b are representations of a and b, respectively, in the frame having vectrix [1]. Note that S(a) is a skew-symmetric matrix constructed with representation a such that…”

Section: Factmentioning

confidence: 99%

“…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%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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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“…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%

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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Adaptive Backstepping Fast Terminal Sliding Mode Controller for Refueling Boom with Elastic

Zhao

et al. 2021

Lecture Notes in Electrical Engineering

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Aerial Refueling Implications for Commercial Aviation

Cited by 31 publications

References 4 publications

Derivation of the Dynamics Equations of Receiver Aircraft in Aerial Refueling

Derivation of the Dynamics Equations of Receiver Aircraft in Aerial Refueling

Flight Control and Simulation for Aerial Refueling

Adaptive Backstepping Fast Terminal Sliding Mode Controller for Refueling Boom with Elastic

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