A framework for analysis of aircraft maneuverability

Beck, Jeff; Cord, Thomas

doi:10.2514/6.1995-3448

Cited by 7 publications

(7 citation statements)

References 1 publication

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“…10. Here the point of view was to characterize agility within the context of an extended maneuver envelope obtained by increased control power and admissible angles of attack.…”

Section: Figures 3d Trajectorymentioning

confidence: 99%

“…In practice, a succession of open loop controls must be found so that the system can reach the desired final state with the minimum associated cost. Since the cost is expressed by (15), we can also write (10) The simplest numerical approach to solve the optimization stated by (9) and (10) is an iterative first order gradient-based descent of the cost functional yielding, at each step (11) …”

Section: Missile Modelmentioning

confidence: 99%

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Missile trajectory optimization with agility issues

Nasuti

Innocenti

1996

Guidance, Navigation, and Control Conference

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The synthesis of an optimal trajectory envelope for a missile capable of controllable post-stall maneuvering is considered. The model is representative of a generic high performance system with control capability enhanced by reaction jet thrust. Trajectory synthesis is carried out first by using classical nonlinear costrained optimization methods on a point mass model with relaxed constraints on angles of attack and sideslip. A second approach includes maneuverability and agility considerations in the optimization process, with a kinematic model and constraints obtained from dynamic limits. Results are presented for both methods, with reference to a minimum time heading reversal maneuver. (Author) AbstractThe synthesis of an optimal trajectory envelope for a missile capable of controllable post-stall maneuvering is considered.The model is representative of a generic high performance system with control capability enhanced by reaction jet thrust. Trajectory synthesis is carried out first by using classical nonlinear costrained optimization methods on a point mass model with relaxed constraints on angles of attack and sideslip. A second approach, includes maneuverability and agility considerations in the optimization process, with a kinematic model and constraints obtained from dynamic limits. Results are presented for both methods, with reference to a minimum time heading reversal maneuver. Notation T = main thrustF w = -pV 2 S(C D ;Cy;C L } aerodynamic force £ m = mass of vehicle p= air density a = speed of sound g = gravity acceleration F= speed (m Y> %) = Euler angles of the wind axis frame (a, P) = aerodynamic angles T mg 2mg (adimensional time) (Thrust/Weight ratio) (Reference area) (Mach number) fPhD Student Associate Professor, Associate Fellow AIAA "

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“…10. Here the point of view was to characterize agility within the context of an extended maneuver envelope obtained by increased control power and admissible angles of attack.…”

Section: Figures 3d Trajectorymentioning

confidence: 99%

Section: Missile Modelmentioning

confidence: 99%

Missile trajectory optimization with agility issues

Nasuti

Innocenti

1996

Guidance, Navigation, and Control Conference

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“…5 Later work by Beck and Cord 6 followed a strictly mathematical approach to the de nitions of maneuverabilityand agility of Ref. 5. In their work, Beck and Cord 6 have the following de nitions:…”

Section: Agility Metricsmentioning

confidence: 99%

“…It is oriented in a right-handed coordinate system, with the quantities t, n, and b representing unit vectors along the X F ; Y F , and Z F axes, respectively. 6 The maneuver performance parameters are characterized by the translationalrate and rotationalrates, and the agility componentsare speci ed by the maneuver performance parameters and their derivatives. The velocity of the aircraft expressed in the Frenet system is given by…”

Section: Agility Metricsmentioning

confidence: 99%

Comparison of Agility Metrics to Beck Agility Metrics Using Linear Error Theory

Valasek

Smith

2003

Journal of Guidance, Control, and Dynamics

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“…In particular, we choose to subscribe to the definitions used by Beck and Cord (1995), where maneuver performance is defined as a measure of steady maneuver capability and agility is defined as a measure of the ability to transition between steady maneuvers. Consequently, the relevant maneuver states of a surface vehicle include the surge speed , the sway speed , and the yaw rate .…”

Section: Maneuverability and Agilitymentioning

confidence: 99%

Straight-Line Target Tracking for Unmanned Surface Vehicles

Breivik¹,

Hovstein²,

Fossen³

2008

MIC

169

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This paper considers the subject of straight-line target tracking for unmanned surface vehicles (USVs). Target-tracking represents motion control scenarios where no information about the target behavior is known in advance, i.e., the path that the target traverses is not defined apriori. Specifically, this work presents the design of a motion control system which enables an underactuated USV to track a target that moves in a straight line at high speed. The motion control system employs a guidance principle originally developed for interceptor missiles, as well as a novel velocity controller inspired by maneuverability and agility concepts found in fighter aircraft literature. The performance of the suggested design is illustrated through full-scale USV experiments in the Trondheimsfjord.

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A framework for analysis of aircraft maneuverability

Cited by 7 publications

References 1 publication

Missile trajectory optimization with agility issues

Missile trajectory optimization with agility issues

Comparison of Agility Metrics to Beck Agility Metrics Using Linear Error Theory

Straight-Line Target Tracking for Unmanned Surface Vehicles

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