Systems Engineering Technology for Launch Coefficient Improvement

doi:10.3873/j.issn.1000-1328.2023.03.002

Abstract

Abstract:

In order to improve the launch coefficient as the goal, a systems engineering technology is proposed. Combined with the design object, the overall multi-level design process and optimization object are sorted out from the four aspects of design concept, constraint boundary, design method, and identification return, to build the overall system of technologies. Taking the system as the traction, combined with the development practice of the new generation of launch vehicles, the research process and application effects of some of the technologies such as safety margin shooting, active environmental control, multi-disciplinary joint optimization, and propellant residue identification are summarized. At the same time, the direction of follow-up and continuous research is pointed out, which is of great significance to support the improvement of the launch coefficient.

Key words: Launch vehicle, Launch coefficient, Probability design, Optimal control, Identification and regression

CLC Number:

V416

WANG Xiaojun. Systems Engineering Technology for Launch Coefficient Improvement[J]. Journal of Astronautics, 2023, 44(3): 322-333.

Figures/Tables 22

Fig.1 Statistics of launch vehicle take-off mass and launch coefficient

Fig.2 Hierarchical process for the overall design

Fig.3 System of the overall technologies

Fig.4 Relationship between the exhaustion probability of the first stage and the safety margin of the second stage

Fig.5 Relationship between the exhaustion probability of the first stage and carrying capacity

Table 1 The proportion of safety margin of the total fuel

型号	助推器	一子级	二子级
火箭1	1.74%	0.54%	1.45%
火箭2	1.19%	0.67%	1.27%
火箭3(新一代)	0.96%	0.83%	0.80%

Fig.6 Comparison of the qα results

Fig.7 Probability density function of the load and strength

Fig.8 Random vibration environment of the equal bandwidth and 1/6 octave variable bandwidth

Fig.9 Damping effect of the particle damper

Fig.10 Comparison of noise environmental conditions of launch vehicles

Fig.11 Comparison of flight effects with sound-absorbing structures

Fig.12 Heat flow simulation of 7 engines

Fig.13 Grid fins during a rocket launch

Fig.14 Comparison of real samples and simulation samples under deviation method considering correlation

Fig.15 Development of the wind compensation technology

Fig.16 Performance of the load relief in a typical case

Fig.17 Comparison of time history of dynamic pressure before and after throttling adjustment

Fig.18 Simulation of gas-liquid two-phase temperature in the sliding phase of a liquid hydrogen tank

Fig.19 The identification results of Y-direction overload at the satellite-rocket interface

Table 2 Generalized displacement calculation and recognition results

方向	星箭界面过载识别结果		计算值
方向	Q₁/m	Q₂/m	Q₁/m	Q₂/m
Y向	0.0110	0.0127	—	—
Z向	0.0265	0.0112	—	—
合成	0.0287	0.0169	0.1330	0.000

Fig.20 Statistics on propellant residue of a type of rocket boosters

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