空射火箭可重复使用技术

doi:10.7527/S1000-6893.2022.28083

Abstract

Abstract:

The application of vertical recovery technology to air-launched launch vehicles causes insufficient carrying capacity， and the current launch schemes are not conducive to full utilization of the launch platforms’ performance as a zero-stage reusable power. Given these two problems， the application of reusable technology to and its effect on air-launched launch vehicles are studied from the aspects of the recovery method of the first-stage booster and launch schemes of the launch platforms. Firstly， combined with the force characteristics analysis of the approximate horizontal launch of the air-launched launch vehicles， the design method of the orbital flight program angle and the trajectory optimization methods are derived， the recovery method of the first-stage booster for the reuse of the air rudders is proposed， and the aerodynamic characteristics analysis and guidance control method of the recovery flight section are analyzed. Then， two launch schemes are proposed. One is a combined power high-altitude unmanned aerial vehicle and the other is a reusable unmanned platform propelled by a subsonic aircraft. Finally， the orbit design parameters and the mathematical simulation results of the first-stage booster’s reusable section are presented with a typical air-launched launch vehicle configuration to quantitatively analyze the contribution of the first-stage booster recovery and the two new launch schemes in terms of carrying efficiency into the orbit and economic cost.

Key words: air-launched vehicle, reusable launch vehicle, combined power, UAV, booster recovery

CLC Number:

Yan LYU, Lin LIU, Guangyong ZHANG, Lei LIANG, Xuesheng ZHENG. Reusable technology of air⁃launched launch vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 628083-628083.

Figures/Tables 30

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Table 1

Fig.6

Table 2

Fig.7

Fig.8

Table 3

Fig.9

Table 4

Table 5

Table 6

Orbit optimization results

项目	优化值
一级小攻角段 $α 2$ /（°）	6.93
二级攻角 $α 3$ /（°）	-2.64
二三级滑行时间 $t f$ /s	378.82
有效载荷 $m l o a d$ /kg	282.04

Table 6

Fig.10

Fig.11

Table 7

Fig.12

Table 8

Deviations of simulation

参数	偏差量（3 $σ$ ）
气动力预示偏差/%	$±$ 30
空气舵零位安装偏差/（°）	$±$ 0.1
回收部分质量特性偏差/%	$±$ 5
初始姿态角偏差/（°）	$±$ 3
初始姿态角速度偏差/（（°）·s^-1）	$±$ 3
风干扰	设计风场

Table 8

Table 9

Guidance & control design parameters

参数	设计值
$K θ$	4
$K ψ$	4
$K ω z$	0.9
$K φ$	3.2

Table 9

Fig.13

Table 10

Table 11

Table 12

Fig.14

Table 13

Fig.15

Table 14

Table 15

References 26

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时序	动作
火箭一二级分离	空气舵控制下向回收点飞行
减速至亚声速（高度降至10 km备保）	空气舵归零，打开牵引伞，助推器俯仰角调整至约90°
高度降至8 km	打开主减速伞
高度降至2 km	陆上回收：缓冲气囊充气，海上回收：直升机抓取

参数	设计值
最大起飞重量/t	100
空机重量/t	35
最大挂载火箭/t	20
机翼展长/m	50
机翼面积/m²	250
机身长度/m	26
液体发动机数量/台	2

参数	设计值
最大起飞质量/t	48
空机质量/t	22
最大挂载火箭/t	20
机翼展长/m	12
机翼面积/m²	167
机身长度/m	22
液体发动机数量/台	2

参数	构型
参数	一级	二级	三级
直径/m	1.4	1.4	1.0
长度/m	16	8.8	5.7
推进剂质量/t	11.8	4.8	0.8
推进剂类型	液氧煤油	固体	固体
平均推力/kN	583	300	56
比冲/s	330	286	286

速度倾角/（°）	攻角/（°）	500 kmSSO运载能力/kg
0	0	282
0	15	285
15	0	296

Reusable technology of air⁃launched launch vehicle

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项目	设计值
发射高度/km	12
发射马赫数	0.75
速度倾角/（°）	0
攻角/（°）	0

型号	起飞质量/t	500 km SSO运载能力/kg
捷龙一号（SD-1）^［25］	23	200
快舟一号甲（KZ-1A）^［26］	30	260
空射火箭	20	282

H/km	500 kmSSO运载能力/kg
H/km	Ma=0.75	Ma=0.95	Ma=2.0	Ma=3.0
12	296	310
20	316	333	432	540
30	327	345	454	572

运载平台	投送质量/t	500 km SSO运载能力/kg
亚声速飞机	火箭20	296
亚声速飞机	火箭25	446
高空无人机	液氧煤油5+火箭20	344
组合平台	液氧煤油4.4+火箭20	571

运载平台	复用	500 km SSO运载能力/kg	火箭成本
亚声速飞机	0次	296	C
亚声速飞机	10次	295×11	C+32%C×10
高空无人机	10次	343×11	C+32.5%C×10
组合平台	10次	570×11	C+32.5%C×10

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