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Long March 6A and Its Technical Characteristics

ZHANG Weidong, YANG Fan, WU Jialin, ZHOU Chenghong, SHEN Zili, CHANG Dongfang

AEROSPACE CHINA 2022, 23 (2): 3-8. DOI: 10.3969/j.issn.1671-0940.2022.02.001

Abstract （229）

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China’s first solid-liquid bundled launch vehicle, the Long March 6A (LM-6A) successfully adopted a number of key new technologies, launching the Pujiang 2 and Tiankun 2 satellites precisely into their predetermined orbits, thus demonstrating that China has mastered solid-liquid bundled launch vehicle technology and has a new member in the new generation launch vehicle family. For the first time in China, a booster adopted a 2 m-diameter solid motor and a 270 V, 20 kW high-voltage and high-power electric servo system was used to control the swing of the solid motor nozzles. A health diagnosis system for the core first stage engine and unattended automation technology were also adopted for the first time.

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Research on Modal Test Technology of LM-6A Solid-Liquid Strap-On Launch Vehicle

ZHU Chunyan, YANG Bing, DI Wenbin, CHANG Dongfang, MAO Yuming

AEROSPACE CHINA 2022, 23 (2): 25-33. DOI: 10.3969/j.issn.1671-0940.2022.02.004

Abstract （138）

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The LM-6A new generation solid-liquid strap-on launch vehicle has the structural dynamic characteristics of lower frequencies, denser modes and coupling modes in longitudinal, bending and torsion modal space. During the development phase of LM-6A, modal tests of partial stacks and the full vehicle were designed to obtain the structural dynamic properties. The structural dynamic models using the finite element method (FEM) have been verified and calibrated based on the modal test data. This paper describes the pre-test predictions and test execution, and details the comparison between the pre-test predictions and the test data. The successful maiden flight of LM-6A further confirmed the effectiveness of structural dynamic modeling and modal test for LM-6A.

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Space Elastic Modal Modeling and Control of A New Generation Solid Bundled Rocket

Hong Gang, XIN Gaobo, LIU Yuxi, XUE Yu, SONG Pan, YANG Xinru

AEROSPACE CHINA 2022, 23 (2): 9-15. DOI: 10.3969/j.issn.1671-0940.2022.02.002

Abstract （135）

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In this paper, based upon the characteristics of elastic modal combination of large solid bundled launch vehicles, the finite element theory is used to describe the complex elastic vibration of a solid bundled launch vehicle, and a new three-channel unified elastic vibration equation was established. The elastic vibration equation can reflect the coupling between channels and between boosters and core stage. Some issues need consideration in the theoretical derivation, an engineering application was proposed, and the elastic vibration model was verified. The results of the theoretical derivation and simulation show that the elastic vibration equation of a solid bundled launch vehicle established in the paper is correct and can meet the needs for the engineering application.

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Research on Unattended Loading Technologies of the New Generation Launch Vehicles

LI Miao, SUN Lijie, WANG Bin, ZHENG Zhen, QI Yemin

AEROSPACE CHINA 2022, 23 (2): 69-75. DOI: 10.3969/j.issn.1671-0940.2022.02.009

Abstract （129）

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According to the unattended loading requirements of the new generation launch vehicles, auto-docking technology for the first stage fill-drain connector and zero-second quick detachment technology for the second stage fill-drain connector were proposed based on the analysis and summary of unattended loading connector technology at home and abroad. These technical solutions were verified to be reasonable and feasible by tests, and they had been successfully applied to the Long March 6A (LM-6A), laying a foundation for the unattended test and launch of the new generation launch vehicles.

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Research on Key Technologies of Segmented Solid Rocket Booster

LU Hejian, CHEN Hong, ZHAO Yujing, MIAO Zhiwen, LI Siheng

AEROSPACE CHINA 2022, 23 (2): 34-45. DOI: 10.3969/j.issn.1671-0940.2022.02.005

Abstract （129）

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The research status on the development of large segmented solid boosters is introduced, showing that the key technologies of the motor have now been acquired and meet the operational requirements of the rocket, which may provide a reference for subsequent development of large segmented solid booster motors and their application in space launchers with solid strap-on boosters.

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Adaptive Reconfiguration for Launch Vehicle Under Servo Mechanism Fault

HU Cunming, ZHANG Weidong, ZHOU Jing, ZHANG Yifeng, LI Guifang, XU Xice

AEROSPACE CHINA 2022, 23 (2): 62-68. DOI: 10.3969/j.issn.1671-0940.2022.02.008

Abstract （114）

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This paper investigates the servo mechanism reconfiguration and fault tolerance control issue for a launch vehicle. Firstly, the servo reconfiguration algorithm is considered as an optimization model, and commonly used optimization algorithms are analyzed and compared. An improved method based on Singular Value Decomposition (SVD) for solving the suboptimal solution of the direct assignment problem is proposed, being suitable for engineering application, while maintaining the advantages of existing algorithms. Theoretical analysis and simulation results confirm that the proposed method is able to provide the optimal reconfiguration strategy with higher computational efficiency. Finally, the numerical simulation of launch vehicle fault tolerance control fully verifies the feasibility and effectiveness of the improved method, which indicates that the method met the engineering application conditions.

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Research and Application of High-Voltage Power Supply and Distribution on Launch Vehicle

WANG Meng, GAO Li, YANG Xinru, XIN Gaobo, YAN Feng, WANG Shudan

AEROSPACE CHINA 2022, 23 (2): 46-54. DOI: 10.3969/j.issn.1671-0940.2022.02.006

Abstract （113）

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High-power electric actuators are generally used on solid propellant motors, which further enhances the requirement on onboard supply voltage and output power of a launch vehicle. In this paper, combined with the electrical demand of China’s new generation solid-liquid bundled launch vehicle (LM-6A), high-voltage battery technology, high-power switch control technology, insulation protection technology under low pressure are studied, and the key technologies and schemes are presented. The flight test of LM-6A shows that the high-voltage power supply and distribution technology adopted is reasonable and feasible, and can be used as a reference for the designs of other launch vehicles or spacecrafts.

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Application and Research of High-Power Electric Servo System on Launch Vehicle

FENG Wei, CUI Yebing, WANG Yaoyao, YU Ge, SONG Shuwei, CHEN Shuheng, GU Dawei,

AEROSPACE CHINA 2022, 23 (2): 55-61. DOI: 10.3969/j.issn.1671-0940.2022.02.007

Abstract （113）

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The 30 kW high-power electric servo system used in the solid booster of the Long March 6A (LM-6A) launch vehicle is introduced, and the function, composition of the system as well as its constituent equipments are detailed. To solve the problem of out-of-tolerance in the system dynamic characteristics, an advanced correction network algorithm architecture and double notch filter were designed. Experimental verification was conducted to prove that the dynamic characteristics requirement under multiple operating conditions could be met.

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Study on the Effect of Solid Particles on Jet Flow and Base Thermal Environment for Solid-Liquid Bundled Rocket

ZHANG Liang, YAN Li, SUN Peijie, YANG Fan, WANG Heping, REN Jie

AEROSPACE CHINA 2022, 23 (2): 16-24. DOI: 10.3969/j.issn.1671-0940.2022.02.003

Abstract （112）

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Compared with using liquid rocket engines, there are a lot of high-temperature solid particles in the solid-liquid bundled rocket, which make the rocket base thermal environment worse. In order to study the influence of high-temperature solid particles on the base thermal environment, firstly, the effect of particle diameter on the jet distribution and the thermal environment in a single solid motor jet was analyzed using a numerical simulation method, and the results were compared with those of a ground test. Further, the effects of high-temperature solid particles on the jet and the thermal environment of the solid-liquid bundled rocket were analyzed and compared with flight data. The results show that high-temperature solid particles can increase the jet temperature and reduce the jet velocity. The larger the particle diameter, the greater the impact on the jet core temperature. The role of high-temperature solid particles cannot be ignored in the study of the base thermal environment.

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ISSN 1671-0940

CN 11-4673/V

Content of SPECIAL ISSUE in our journal