Integrated optimization method for specific thrust ballistic between stages of suborbital launch vehicle
A technology for launch vehicles and optimization methods, which is applied in design optimization/simulation, geometric CAD, special data processing applications, etc., can solve problems such as no launch vehicle optimization design, and achieve reduced speed loss, increased shift speed, and increased range. effect of ability
Active Publication Date: 2020-05-12
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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there is currently no method for optimizing the design of conventional launch vehicles for suborbital launch missions
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[0072] The performance indicators of launch vehicle optimization can usually be summarized into the following categories: 1. Maximum range or maximum shift speed; 2. Minimum take-off mass; 3. Maximum payload; 4. Minimum cost. For different types of launch vehicles, their importance is not the same. According to the nature of the problem and design experience, the parameters that have a significant impact on the objective function should be selected as design variables. The objective function selected by the present invention is the maximum shift speed under the condition that the total charge of the launch vehicle remains unchanged. There are many parameters that affect the performance index of the launch vehicle. In the present invention, the propellant thrust of engines at various levels and the flight trajectory of the carrier rocket are used as optimization variables.
[0073] The optimization problem involved in the present invention is an optimization problem combining ...
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The invention discloses an integrated optimization method for the interstage ratio thrust trajectory of a sub-orbital carrier rocket. The method comprises the following steps that: through a genetic algorithm, multiple groups of parameter combinations of interstage ratios, thrusts and sliding time are given to serve as the individual of an initial population; each group of parameter combination is independently taken as an input condition, a shift exchange speed is taken as a target function, and solving is carried out through an internal layer optimization algorithm to obtain an optimal flight trajectory and the corresponding shift exchange speed under each group of interstage ratios and thrust; and the shift exchange speed serves as the fitness of each group of parameters, and the genetic algorithm is used for obtaining an optimal vehicle interstage ratio and thrust combination and the corresponding flight trajectory. By use of the method, under a situation that dynamic pressure, overload and heat flow constraints in a flight process of the sub-orbital carrier rocket are met, when the total explosive payload of the vehicle is constant, the shift exchange speed of the sub-orbital carrier rocket can be improved as much as possible to enable an effective load to own higher shift exchange speed.
Description
technical field [0001] The invention relates to an integrated optimization method for interstage specific thrust ballistics applied to suborbital launch vehicles, and belongs to the field of overall parameter design of launch vehicles. Background technique [0002] As a brand-new aerial platform, the suborbital vehicle has opened up the vast vacuum zone that exists between the aircraft and the satellite, and has unique advantages that traditional aircraft cannot match. Compared with traditional launch vehicles, the ballistic form of suborbital launch vehicles has the following characteristics: [0003] 1) The handover altitude is relatively low, and the entire booster phase is flown in the atmosphere. [0004] 2) The inclination angle of the shift trajectory close to 0° requires the vehicle to turn quickly in the atmosphere. [0005] The use of traditional launch vehicles designed for space orbital missions to launch suborbital vehicles will inevitably bring about increase...
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IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20
Inventor 孙石杰张烨琛闵昌万于明星汪雷李加玉徐春铃袁江波张宁宁杨凌霄
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST