Aircraft winglet expansion amount optimization method based on Gaussian pseudo-spectrum method

A Gaussian pseudospectral method and optimization method technology, applied in the field of aerospace propulsion control, can solve the problems of lack of co-state, low precision, and inability to test optimality

Inactive Publication Date: 2019-06-07
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Description
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  • Application Information

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Problems solved by technology

The direct method overcomes the shortcomings of the indirect method, because it does not need to calculate the information of the co-state

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  • Aircraft winglet expansion amount optimization method based on Gaussian pseudo-spectrum method
  • Aircraft winglet expansion amount optimization method based on Gaussian pseudo-spectrum method
  • Aircraft winglet expansion amount optimization method based on Gaussian pseudo-spectrum method

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Embodiment Construction

[0073] The technical solutions of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0074] The idea of ​​the present invention is aimed at the characteristics of the near-space variable-wing aircraft, which consumes a large amount of fuel during the climbing process, and the reduction in mass during the climbing process is similar to the consumption of fuel. Since the fuel carried by the aircraft itself is limited, in order to have more fuel for the flight in the cruising section, the aircraft is required to climb with the most fuel-saving, that is, the mass of the aircraft at the end of the climb is kept at the maximum, and the winglets need to be retracted during the climb section. The trajectory is optimized.

[0075] The essence of Gaussian pseudospectral method (GPM) is to convert the continuous time problem into a discrete point first, and use the unknown variables such as state quantity and control quantity to expre...

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Abstract

The invention discloses an aircraft winglet expansion amount optimization method based on a Gaussian pseudo-spectrum method, which comprises the following steps of: establishing constraint conditionsof a winglet expansion track of a climbing section of a near-space variable-wing aircraft, including boundary constraint, path constraint, state variable and control variable constraint; establishinga performance index function of the small wing telescopic track of the climbing section of the near-space variable-wing aircraft, wherein the performance index function is established according to a target with the most fuel-saving effect; discretizing the established continuous optimization control problem by adopting a Gaussian pseudo-spectrum method so as to convert the discretized continuous optimization control problem into a nonlinear programming problem, and solving the nonlinear programming problem to obtain an optimal near-space variable-wing aircraft climbing section winglet telescopic track. According to the method, the expansion amount of the winglet of the climbing section of the near-space variable-wing aircraft can be optimized within a short time, and the control target ofthe minimum fuel consumption is achieved.

Description

technical field [0001] The invention belongs to the technical field of aerospace propulsion control, and in particular relates to a method for optimizing the stretching amount of an aircraft winglet based on a Gaussian pseudospectral method. Background technique [0002] Near-space variable-wing aircraft, also known as hypersonic variable-wing aircraft, refers to an aircraft that flies in a near-space region and whose wing shape and structure can be changed. The near-space variable-wing aircraft adopts wing-body fusion, and its shape structure is triangular. The trajectory research of its climbing section is a complex, highly nonlinear, multi-variable and multi-constrained optimal control problem. Due to the sensitivity of the system to aerodynamic parameters at hypersonic speeds, the leaping nature of the state parameter changes in the climb section, and the disturbance caused by the expansion and contraction of the winglets of the variable wing in the climb section, all o...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 万月丰徐文萤文成馀江驹
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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