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

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...

AI Technical Summary

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, but the accuracy of the solution is low, the co-state is missing, and the first-order necessary condition for optimality cannot be tested

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