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Solid rocket engine overall parameter design method

An overall parameter, solid rocket technology, applied in the aerospace field, can solve problems such as poor performance, difficult to obtain optimal design results, increase design cycle and time, etc., to achieve comprehensive performance, improve overall design efficiency and comprehensive performance, The effect of reducing the number of times

Active Publication Date: 2020-10-16
NAT UNIV OF DEFENSE TECH
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  • Description
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  • Application Information

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Problems solved by technology

The traditional design optimization method decomposes the design optimization of solid engines into two independent processes of overall design optimization and subsystem parameter optimization. Although the design optimization problem is simplified, it is difficult to obtain design results that meet the engine index requirements in one design optimization. The above two The multiple iterations and coordination of the design optimization process mainly rely on the experience of engineers for coordination, which increases the design cycle and time. At the same time, due to the limitations of manual search, it is difficult to obtain the real optimal design results, resulting in poorer performance of the final solution. Difference

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Embodiment 1

[0152] Structural parametric design of two-dimensional star hole grain engine:

[0153] Index requirements: engine outer diameter: 260mm; total weight: ≤63kg; skirt spacing: 600mm; nozzle length: 200mm; working temperature: -40℃~50℃; normal temperature (20℃) average thrust: ≥23kN; Total flushing: ≥103kN·s, working time: 4.5s.

[0154] Charge configuration: star hole type, the number of star angles is 6, and the front and rear end faces are not covered.

[0155] Design variables: selected as throat diameter Dt, expansion ratio ε, reference burning rate r0 (6MPa), star hole charge configuration parameters (circumscribed circle diameter D, angle fraction λ, star tip arc radius r, star edge half angle θ , inscribed diameter d), and its variation range is shown in Table 1 below.

[0156] Table 1 Variation range of design variables

[0157]

[0158]

[0159] Propellant parameters: density 1770, pressure index 0.3, burning rate temperature sensitivity coefficient 0.002, gas ...

Embodiment 2

[0175] Wing post engine design:

[0176] Design requirements: The outer diameter of the engine is 915mm, the total length of the engine is less than or equal to 5400, the working temperature is -40°C to 50°C; .

[0177] Charge configuration: rear wing column type, the number of rear wings is 9, and the diameter of the inner hole is 250mm.

[0178] Propellant parameters: density 1770, pressure index 0.35, burning rate temperature sensitivity coefficient 0.002, gas specific heat ratio 1.17, characteristic velocity changes with pressure as shown in Table 4 below.

[0179] Table 4

[0180] Pressure (MPa) Characteristic speed (m / s) 5 1560 6 1570 7 1580 8 1590 9 1600

[0181] Shell material: the tensile strength is 1715MPa, and the yield stress is 1370MPa.

[0182] Heat insulation layer material: the density is 1200, the ablation rate is 0.2mm / s, and the thickness allowance is 0.5mm.

[0183] Design variables: selected as throat diameter...

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Abstract

The invention provides a solid rocket engine overall parameter design method. The method comprises the steps of obtaining a task target, and generating an initial sample point in a design space by adopting an optimized Latin hypercube experiment design method; inputting the initial sample point into an engine performance simulation model to obtain a constraint condition and an objective function corresponding to the initial sample point; constructing an agent model of the target function and the constraint condition according to the initial sample point, the constraint condition correspondingto the initial sample point and an initial training sample formed by the target function; carrying out optimization processing on the agent model by adopting a differential evolution algorithm, and outputting an optimal sampling point; and taking the optimal sampling point as a new sampling point to be input into the engine performance simulation model, and outputting the optimal engine structuredesign parameter according to the convergence condition. By the adoption of the method, structural parameter design with the optimal comprehensive performance can be obtained, and the overall design efficiency and the comprehensive performance of the solid rocket engine are remarkably improved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method for designing overall parameters of a solid rocket motor. Background technique [0002] Solid rocket motor is one of the important power systems of space vehicles such as missiles and rockets. The overall design has a decisive influence on the performance and quality indicators of the engine. The design of the engine components can only be carried out after the overall design has been completed. The task of the overall design is to determine the main structural parameters of the engine according to the overall index requirements of the projectile for the engine, including the charge configuration of the engine, nozzle throat diameter, expansion ratio, shell thickness, and heat insulation layer thickness, etc. [0003] Currently commonly used overall design methods are: [0004] (1) Based on existing cases and experience, the main design parameters of the engine are...

Claims

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Application Information

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IPC IPC(8): G06F30/17G06F30/20G06F111/04G06F119/12G06F119/14
CPCG06F30/17G06F30/20G06F2111/04G06F2119/12G06F2119/14
Inventor 武泽平彭博王东辉王文杰张为华
Owner NAT UNIV OF DEFENSE TECH
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