激波风洞两级入轨飞行器纵向级间分离试验技术

doi:10.7527/S1000-6893.2022.28126

Abstract

Abstract:

The multi-body separation problem in hypersonic flow is a key technical issue in the research and development of aerospace multibody vehicles. Due to the complexity of high-speed flow during separation， the wind tunnel test study is extremely challenging， particularly the shock tunnel separation test. The test flow of the shock tunnel has the characteristics of high flow speed and high enthalpy， which can simulate the flow characteristics with gas effect at high temperature and duplicate the reliable aerodynamic and thermal characteristics of hypersonic multibody separation. However， its effective test time is short in order of milliseconds； therefore it is difficult to conduct dynamic tests of separation. In this study， a High-speed Pneumatic Ejection to Launch vehicle model System （HPELS） applied to the shock tunnel is proposed， which enables the model to actively complete the separation within the short test time. The precise time calibration and timing control methods of HPELS delay time and separation time are introduced in detail. For the high-performance evaluation of the separation trajectory and aerodynamic parameters during separation， a non-contact separation motion trajectory capture and aerodynamic parameter measurement technology based on schlieren images is developed. The safety stage separation of Two Stages to Orbit （TSTO） vehicle is a typical high-speed separation problem. In view of the longitudinal separation scheme and parallel-staged TSTO vehicle proposed by the author， the effectiveness of the application of the high-speed dynamic multi-body separation test technology is verified in the JF-12 duplicated flight conditions shock tunnel. Meanwhile， the principle of the parallel-staged TSTO safety longitudinal stage separation scheme is verified in the shock tunnel for the first time. Comparison of the experimental results with the numerical results shows good agreement.

Key words: two stages to orbit (TSTO), multi-body separation, hypersonic, stage separation, trajectory capture, shock tunnel

CLC Number:

V411.7

Yue WANG, Yunpeng WANG, Zonglin JIANG. Test technology of longitudinal stage separation for two-stage-to-orbit vehicle in shock tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 128126.

Figures/Tables 20

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Table 1

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Table 3

Characteristics and complementary analysis of JF-12 duplicated flight condition shock tunnel and routine hypersonic wind tunnel for multi-body separation test

分类

JF-12复现风洞

常规高超声速风洞

特点

1. 大功率反向爆轰驱动技术激波风洞，复现高超声速飞行条件：飞行马赫数5~9，飞行高度25~50 km

2. 试验气流总温高

3. 激波风洞有效试验时间短（百毫秒量级）

4. 喷管出口直径2.5 m，试验段直径3.5 m，试验段尺寸大

5. 航天飞行器气动力/热、气动布局、级间分离特性、喷流控制，以及吸气式发动机特性试验研究

1. 分为连续式和间歇式两种，且以吹-吸式较为多见，试验来流马赫数5~10

2. 试验气流总温较低

3. 有效试验时间长（可达分钟量级）

4. 容易集成多项多体分离试验技术，比如网格测力、CTS

5. 航天飞行器气动力/热、气动布局、级间分离特性、喷流控制，以及吸气式发动机特性试验研究

优势

1. 在模拟参数相似性方面优于常规高超声速风洞，复现气流总温和总压，产生纯净试验气体，实现从“模拟”到“复现”飞行条件的跨越，更加有利于多体分离试验

2. 试验气流总温高，能够模拟更高马赫数范围的试验气流焓值，包含多体分离过程中复杂气动干扰中的高温真实气体效应

3. 大试验段尺度，有利于进行大尺寸/全尺寸飞行器部件（多体）分离试验

1. 有效试验时间长：可以在一次吹风试验车次中，进行网格测力试验获得飞行器多个相对位置下的气动力/热数据与流场图像；或者采用CTS系统获得多体分离过程中的实时轨迹、气动力解算信息

2. 采用CTS系统进行分离试验，可以对模型进行反复使用，无模型损坏成本问题，且不需要像投放分离试验要求动力相似

3. 在较长的有效试验时间范围内，完成操作比较复杂的自由飞多体动态分离试验较为容易，且适用于重模型进行投放/弹射分离试验

互补

1．JF-12复现风洞有效试验时间尽管长达130 ms，但是开展主动式多体动态分离试验难度很大，多体分离特征可以与在常规高超风洞开展的长试验时间的试验结果进行对比互补

2．JF-12复现风洞，冲击大，多种振动信号与气动信号耦合，惯性振动信号与试验时间同量级。尤其是在多体动态分离过程中，测得非定常气动力信号可以与在常规高超风洞中CTS测得的气动力进行对比，助力攻关激波风洞非定常气动力测量与处理技术难题

3．JF-12复现风洞试验气流总温高，可以揭示高超声速多体分离过程中的高温真实气体效应，试验结果与常规高超风洞试验结果对比，可以获得真实气体效应对多体分离气动载荷的具体影响，有利于揭示关键技术设计缺陷，提出改进依据和数据，规避飞行试验事故

4．常规高超风洞CTS多体分离试验本质上属于准定常静态试验，无法复现复杂气动干扰与多体运动耦合效应，并且试验存在模型支撑干扰影响。JF-12复现风洞动态分离试验与CTS分离试验对比，可以体现多体运动耦合效应的影响，并对模型支撑干扰影响进行校正

5．常规高超风洞有效试验时间长，可以进行轻/重模型的多体自由飞分离试验；而激波风洞有效试验时间短，在进行多体自由飞分离试验时，一般要求模型质量较轻，轻/重模型在两种风洞中的分离结果可以进行融合对比

Table 3

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序号	难点与挑战	应对策略
1	短试验时间（ms量级）内完成主动式纵向分离	应用于激波风洞的飞行器模型高速气动发射系统
2	轨道级气动力反问题	轨道级模型标识点图像识别轨迹捕捉
3	轨道级模型损坏成本	轨道级模型落点预测和防护

车次	T_d/ms	T_s/ms	T_f/ms
平均值	76	79	177
1	80	77	176
2	72	80	177
3	78	80	176
4	67	79	178
5	83	80	178

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Test technology of longitudinal stage separation for two-stage-to-orbit vehicle in shock tunnel

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