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Aircraft Constrained Optimization Method Based on Filter Technology and Subdivision Rectangle Algorithm

A constrained optimization and filter technology, applied in constraints-based CAD, instruments, calculations, etc., can solve problems such as the large impact of optimal design results, and achieve the effects of increasing design costs, enhancing robustness, and eliminating uncertainty.

Inactive Publication Date: 2018-12-25
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, in the actual application combined with the DIRECT or PSO algorithm, it is found that the penalty factor and its update strategy in this method have a greater impact on the optimal design results, and generally require multiple tests to obtain empirical values ​​for specific problems
At present, design simulation analysis in aircraft design often uses high-precision analysis models (such as finite element analysis in structural design, computational fluid dynamics in aerodynamic analysis, etc.), and the design time and cost caused by the repetition in this design are immeasurable of

Method used

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  • Aircraft Constrained Optimization Method Based on Filter Technology and Subdivision Rectangle Algorithm
  • Aircraft Constrained Optimization Method Based on Filter Technology and Subdivision Rectangle Algorithm
  • Aircraft Constrained Optimization Method Based on Filter Technology and Subdivision Rectangle Algorithm

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Embodiment 1

[0031] Optimal Design of Light Aircraft Landing Gear Shock Absorbing Spring

[0032] Light aircraft have light take-off weight and relatively simple structure, and tension / compression springs are often used as shock absorbers for their landing gear. In order to reduce the structural mass of light and small aircraft, it is hoped that the mass of the spring should be minimized under the constraints of minimum deflection, shear stress and vibration frequency.

[0033] The total mass (objective function) of the damping spring design can be expressed as:

[0034]

[0035] where x 1 is the spring coil diameter d; x 2 is the average coil diameter D; x 3 is the effective number of turns N.

[0036] Constraints to be met by the design include:

[0037]

[0038] At the same time, the value range of each design variable is: 0.05≤x 1 ≤0.20, 0.25≤x 2 ≤1.30, 2.0≤x 3 ≤15.0, the schematic diagram is as follows Figure 4 shown.

[0039] The filter DIRECT (filter-DIRECT) and the...

Embodiment 2

[0054] Embodiment 2: Solid Rocket Motor Shell Design

[0055] The solid rocket motor shell is an important part of the solid rocket motor, and it is an important guarantee to ensure the static strength of the engine structure and the pressure bearing capacity of the combustion chamber. Solid rocket motors are mostly disposable consumables. Under the premise of satisfying the constraints, it is hoped that its total cost will be the smallest, including the cost of materials, forming and welding. The total cost (objective function) of solid rocket motor shell design can be expressed as

[0056]

[0057] where x 1 is the shell thickness T s ; x 2 is the thickness of the cap T h ; x 3 is the inner diameter R; x 4 is the length L of the cylindrical part, the schematic diagram is as follows Figure 5 shown.

[0058] The material, forming and welding constraints that the design needs to satisfy are described as follows

[0059]

[0060] Using the optimization design met...

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Abstract

The invention relates to an aircraft constrained optimization method based on filter technology and a rectangle division algorithm and belongs to the optimization design field in aircraft design. The method comprises the steps of normalizing design space to n-dimensional hypercubes and putting the central points of the n-dimensional hypercubes in a filter; sub-dividing the design space continuously by using the segmentation strategy of the rectangle division algorithm in an iterative process, and obtaining target function values with the central point of each hypercube as a sample point; with the sample points obtained by segmenting the hypercubes as design points, updating elements in the filter according to the dominating thought; judging whether the optimization process is converged, ending the optimization if yes, and, if no, selecting to-be-segmented hypercubes from the filter according to certain conditions to obtain new sample points through segmentation and updating the filter further. The method can obtain the feasible optimal solutions through less tests, thereby saving the computing cost and increasing the design efficiency. The method is great in universality.

Description

technical field [0001] The invention relates to an aircraft constraint optimization method based on filter technology and subdivision rectangle algorithm, which belongs to the field of optimization design in aircraft design. Background technique [0002] Optimum design techniques are increasingly widely used in modern aircraft design to improve system performance and reduce design costs. In practical engineering problems, most of the problems have constraints, that is, optimization problems under constraints. Therefore, it is of great practical significance to study the solution method of the constrained optimization problem for carrying out related design work. In order to solve the constraint problem in the design, the methods of dealing with the constraint conditions commonly used at home and abroad include: penalty function method, sequential quadratic programming and feasible direction method. The latter two methods need to calculate the gradient value of the function...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17G06F2111/04
Inventor 龙腾寇家勋刘莉
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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