基于制导策略的多目标拦截器动力系统设计方法

李文韬; 李文博; 何允钦; 张艺仪; 郑涵匀; 梁国柱

doi:10.13224/j.cnki.jasp.20240219

基于制导策略的多目标拦截器动力系统设计方法

doi: 10.13224/j.cnki.jasp.20240219

1.
北京航空航天大学宇航学院，北京 102206
2.
清华大学航天航空学院，北京 100084

详细信息

作者简介:
李文韬（1999-），男，博士生，主要从事固体姿轨控发动机设计等方面的研究。E-mail：lwt_2017@buaa.edu.cn

通讯作者:
梁国柱（1966-），男，教授，博士，主要从事火箭动力系统原理、设计与试验等方面的研究。E-mail：lgz@buaa.edu.cn

中图分类号: V435.1
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出版历程
- 收稿日期: 2024-04-12
- 网络出版日期: 2024-11-05

Propulsion system design method for multi-object kill vehicles based on guidance strategy

1.
School of Astronautics，Beihang University，Beijing 102206，China
2.
School of Aerospace Engineering，Tsinghua University，Beijing 100084，China

摘要

摘要:
为了进一步提升多目标拦截器（MOKV）固体姿轨控系统的能量管理的效能，获得其质量最小的总体方案，提出一种基于制导策略的MOKV动力系统设计方法。首先，提出一套基于线性协方差分析的多脉冲制导策略评估方法，可快速解析地确定每次机动所需的最大速度增量；然后，确定了对称双燃烧室三脉冲固体姿轨控动力系统的布局方案，具有结构简单、易于控制的特点；随后，给出了动力系统的性能参数模型和质量模型，建立了基于制导策略的动力系统优化设计流程。经过相图法迭代优化，可得到满足尺寸约束条件下的质量最优解，并进一步给出了子拦截器的设计指标。最后，针对典型应用场景开展案例设计并通过蒙特卡洛随机测试评估脱靶量。结果表明，案例MOKV可携带12枚子拦截器，总质量为49.43 kg，轴向尺寸为540.7 mm，径向尺寸为231.9 mm。三次脉冲点火后，MOKV最大脱靶量从千米级缩小至百米级直至十米级，可实现子拦截器精准拦截目标。所提出的理论与方法可为MOKV的高效能量管理和轻质化设计提供有力支撑。
- 多目标拦截器 /
- 固体姿轨控系统 /
- 多脉冲制导策略 /
- 优化设计 /
- 蒙特卡罗随机测试
Abstract:
To further improve the energy management efficiency of the solid divert and attitude control system of the multi-objective kill vehicle (MOKV), and obtain the minimum overall mass scheme, a propulsion system design method for MOKV based on the guidance strategy was proposed. Firstly, a rapid evaluation method for the multi-pulse guidance strategy based on linear covariance analysis was proposed to determine the maximum velocity increment required for each maneuver. Then, the layout scheme of the three-pulse solid divert and attitude control propulsion system with a symmetrical dual-combustion chamber was determined, which featured a simple structure and high controllability. Subsequently, performance parameter and mass models for the propulsion system were established, and an optimal design process of the propulsion system based on the guidance strategy was developed. Through iterative optimization using phase diagram analysis, the mass-optimized solution satisfying size constraints can be obtained, and the design criteria for the sub-interceptors were further provided. Finally, a case design was carried out for typical application scenarios, and the miss distance was evaluated through Monte Carlo random test. The case results showed that the MOKV can carry 12 sub-interceptors, with a total mass of 49.43 kg, an axial dimension of 540.7 mm, and a radial dimension of 231.9 mm. After three pulse ignitions, the maximum miss distance of the MOKV was reduced from the kilometer level to the hundred-meter level and even the ten-meter level, which can achieve precise interception of the target by the sub-interceptors. The theory and method proposed can provide a strong support for the high-efficiency energy management and lightweight design of MOKV.
- multi-object kill vehicle /
- solid divert and attitude control system /
- multi-pulse guidance strategy /
- optimal design /
- Monte Carlo random test

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图 1 多脉冲拦截示意图

Figure 1. Illustration of the multi-pulse interception

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图 2 CV-SDACS的总体布局

Figure 2. General layout of the designed CV-SDACS

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图 3 固体姿轨控系统的控制策略

Figure 3. Control strategy of the designed SDACS

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图 4 基于制导策略的动力系统设计流程

Figure 4. Design workflow of propulsion system based on guidance strategy

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图 5 拦截器与目标飞行器的弹道示意图

Figure 5. Illustration of the trajectory of the interceptor and the target vehicle

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图 6 轨道机动段速度增量等值线图

Figure 6. Contour map of velocity increment in orbital maneuvering phase

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图 7 轨道修正段速度增量等值线图

Figure 7. Contour map of velocity increment in orbital correction phase

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图 8 燃烧室质量随燃烧室压力和参考燃速的变化

Figure 8. Mass of the combustion chamber varies with the chamber pressure and the reference burning rate

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图 9 蒙特卡洛随机测试结果

Figure 9. Monte Carlo random test results

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表 1 速度增量解析评估的给定条件

Table 1. Given condition for velocity increment analytic evaluation method

参数	数值
轨道机动段控制量噪声方差（相对值）$p_{w_1} $	0.01×0.01
轨道修正段控制量噪声方差p_w/（m/s）²	1×1
初始位置方差p_r/m²	1000×1000
初始速度方差 p_v/（m/s）²	50×50
最大允许拦截时长 t_f,max/s	500
最大允许拦截位置方差 $p_{{\mathrm{f}},{\boldsymbol{r}}_{\mathrm{max}}} $/m²	15×15
置信概率β/%	99
初始时拦截器与目标状态量之差$ {{\boldsymbol {\bar x}}_1} - {{\boldsymbol {x}}_{{\text{t,1}}}} $	上限	[−400 km, −250 km, 0 km, 3（km/s）, 2（km/s）, 0（km/s）]
	下限	[−500 km, −350 km, 0 km, 3（km/s）, 2（km/s）, 0（km/s）]

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表 2 动力系统总体指标

Table 2. Overall target of the propulsion system

参数	数值
第1次脉冲速度增量Δv₁/（m/s）	641.02
第2次脉冲速度增量Δv₂/（m/s）	23.24
第3次脉冲速度增量Δv₃/（m/s）	23.24
环境压力p_a/Pa	0
允许的发动机轴向最大尺寸L_max/mm	600
允许的发动机径向最大尺寸D_max/mm	250
阀门、导引头和子拦截器质量m₀/kg*	25
注：*为携带12枚子拦截器，每枚1 kg。

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表 3 CV-SDACS的最优设计结果

Table 3. Optimal design result of CV-SDACS

类别	参数	数值
性能	轨控喷管推力F_A/N	1586
	姿控喷管推力F_B/N	79.25
	第1级装药燃烧时间t₁/s	16.28
	第2级装药燃烧时间t₂/s	4.738
	第3级装药燃烧时间t₃/s	4.738
	轨控喷管比冲I_sp,A/（m/s）	1794
	姿控喷管比冲I_sp,B/（m/s）	1 897
燃烧	参考燃速（7 MPa下）r_ref/（mm/s）	8.5
燃烧	燃烧室压力p_c/MPa	5.5
尺寸	装药外半径R/mm	112.7
	第1级装药长度L₁/mm	127.2
	第2级（第3级）装药长度L₂/mm	37.01
	燃烧室壳体厚度δ_c/mm	1.500
	绝热层厚度δ_i/mm	1.821
	轨控喷管喉部半径R_tA/mm	7.150
	姿控喷管喉部半径R_tB/mm	1.555
	轨控喷管面积比ε_A	15.64
	姿控喷管面积比ε_B	46.55
	发动机轴向尺寸L/mm	540.7
	发动机的径向尺寸D/mm	231.9
质量	燃烧室质量（不包括阀门）m/kg	24.43
	第1级装药质量m_p1/kg	17.10
	第2级（第3级）装药质量m_p2/kg	0.7919
	阀门、导引头和子拦截器质量m₀/kg	25
	MOKV总质量m_total/kg	49.43

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