A Design Method of General Parameters of Solid Rocket Motor

A technology of overall parameters and solid rockets, which is applied in the field of aerospace, can solve problems such as difficulty in obtaining optimal design results, poor program performance, and increased design cycle and time, so as to improve overall design efficiency and comprehensive performance, efficient optimization methods, The effect of reducing the number of times

Active Publication Date: 2021-12-03
NAT UNIV OF DEFENSE TECH
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  • Claims
  • 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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  • A Design Method of General Parameters of Solid Rocket Motor
  • A Design Method of General Parameters of Solid Rocket Motor
  • A Design Method of General Parameters of Solid Rocket Motor

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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 method for designing overall parameters of a solid rocket motor, which includes obtaining the task target, adopting the optimized Latin hypercube experiment design method to generate initial sample points in the design space; inputting the initial sample points into the engine performance simulation model to obtain the initial sample points Constraints and objective functions corresponding to the points; according to the initial training samples formed by the initial sample points and the constraints corresponding to the initial sample points and the objective function, construct the proxy model of the objective function and constraints; use the differential evolution algorithm to optimize the proxy model process and output the optimal sampling point; input the optimal sampling point as a new sampling point into the engine performance simulation model, and output the optimal engine structural design parameters according to the convergence conditions. By adopting the method of the invention, the structural parameter design with optimal comprehensive performance can be obtained, and the overall design efficiency and comprehensive performance of the solid rocket motor can be significantly 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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Patent Type & Authority Patents(China)
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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