微孔注氦型固-气混合火箭发动机比冲增益机制

doi:10.7527/S1000-6893.2025.31693

Abstract

Abstract:

Limited by the energy level of solid propellant， the specific impulse of solid rocket motor is relatively low. The helium-injected solid-gas hybrid rocket motor can effectively improve the specific impulse of solid rocket motor by injecting helium with low molecular weight and strong expansion capacity into the rocket motor. To improve the performance of the helium-injected solid-gas hybrid rocket motor， the effect of micro-hole arrays on the performance of the helium-injected solid-gas hybrid rocket motor is investigated. Results show that the specific impulse of the motor presents a parabolic trend with the variation of helium injection ratio （mass flow ratio of helium to combustion gas）， and the peak value is reached when the helium injection ratio is 1∶4. The motor can obtain a maximum specific impulse gain of 5.77% with the micro-hole diameter of 2 mm. The mixed gas with low helium mass fraction provides positive gain to the specific impulse of the motor， while the mixed gas with high helium mass fraction causes negative gain due to the low total temperature and weak expansion capacity. Therefore， the specific impulse of the motor depends on the combination of the mixed gas with high and low helium mass fraction. Furthermore， motor thrust increases with the increase of helium injection ratio. By changing the helium injection ratio from 0 to 2∶1， a motor can achieve a maximum thrust regulation range of 100%–313%. The injection of helium greatly reduces the nozzle outlet temperature by up to 1 600 K. Therefore， the helium-injected solid-gas hybrid motor can effectively reduce the plume temperature of the rocket motor， suppress the infrared radiation characteristics， and achieve a better infrared stealth effect.

Key words: solid-gas hybrid rocket motor, Helium, specific impulse gain, thrust regulation, infrared stealth

CLC Number:

V435

Chengke LI, Ge WANG, Zenan YANG, Yi LI. Specific impulse gain mechanism of micro-holes helium injected solid-gas hybrid rocket motor[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(16): 131693.

Figures/Tables 17

Fig.1

Table 1

Table 2

Physical parameters of combustion gas and helium

参数	燃气	氦气
质量流量 $m ˙ /$ （kg·s^-1）	10.54	1.054，2.635，5.27，10.54，21.08
总温T₀/K	3 709	281.13
分子量M/（g·mol^-1）	29	4
定压比热容c_p /（J·kg^-1·K^-1）	1 327.926 1+0.350 3T-9.126 5×10^-5T²+8.798 6×10^-9T³	5 193

Table 2

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

References 21

[1]	PENDLETON R. Rapidly deployable space capabilities based assessment-approach and status［C］∥7th Responsive Space Conference. Reston： AIAA， 2009.
[2]	NOWAKOWSKI P， OKNINSKI A， PAKOSZ M， et al. Development of small solid rocket boosters for the ILR-33 sounding rocket‍［J］. Acta Astronautica， 2017， 138： 374-383.
[3]	CAVENY L H， GEISLER R L， ELLIS R A， et al. Solid rocket enabling technologies and milestones in the United States‍［J］. Journal of Propulsion and Power， 2003， 19（6）： 1038-1066.
[4]	GUERY J F， CHANG I S， SHIMADA T， et al. Solid propulsion for space applications： an updated roadmap［J］. Acta Astronautica， 2010， 66（1-2）： 201-219.
[5]	JAFFE P， CLIFFORD G， SUMMERS J. SpaceWire for operationally responsive space［C］∥2008 IEEE Aerospace Conference. Piscataway： IEEE Press， 2008： 1-5.
[6]	中国成功发射首型商业运载火箭引力一号［EB/OL］. （2024-01-12）［2024-12-09］. .
	China launches commercial Gravity-1 rocket from sea［EB/OL］. （2024-01-12）［2024-12-09］. （in Chinese）.
[7]	ERICKSON A S. China’‍s space development history： a comparison of the rocket and satellite sectors［J］. Acta Astronautica， 2014， 103： 142-167.
[8]	DAVIS A. Solid propellants： the combustion of particles of metal ingredients‍［J］. Combust Flame， 1963，7： 359-367.
[9]	CHEUNG H， COHEN N S. Performance of solid propellants containing metal additives‍［J］. AIAA Journal， 1965， 3（2）： 250-257.
[10]	D’‍ANDREA B， LILLO F， FAURE A， et al. A new generation of solid propellants for space launchers‍［J］. Acta Astronautica， 2000， 47（2-9）： 103-112.
[11]	BABUK V A， VASSILIEV V A， SVIRIDOV V V. Propellant formulation factors and metal agglomeration in combustion of aluminized solid rocket propellant‍［J］. Combustion Science and Technology， 2001， 163（1）： 261-289.
[12]	DAVENAS A. Development of modern solid propellants［J］. Journal of Propulsion and Power， 2003， 19（6）： 1108-1128.
[13]	LEMPERT D B， NECHIPORENKO H N， SOGLASNOVA S I. Energetic possibilities of compositions basing on polynitrogene high-enthalpy compounds［J］. Phys Comb Explos， 2009， 45（2）： 58-67.
[14]	DOSSI S， REINA A， MAGGI F， et al. Innovative metal fuels for solid rocket propulsion［J］. Int J Energ Mater Ch， 2012， 11（4）： 299-322.
[15]	NAPIOR J， GARMY V. Controllable solid propulsion for launch vehicle and spacecraft application［C］∥57th International Astronautical Congress. Reston： AIAA， 2006.
[16]	BURROUGHS S. Status of army pintle technology for controllable thrust propulsion［C］∥37th Joint Propulsion Conference and Exhibit. Reston： AIAA， 2001.
[17]	YUE S C， SHAO S Y， HE W J， et al. Pioneer exploration on the energy recovery technology for waste heat in solid rocket motors by utilizing thermoelectric materials［J］. Energy Conversion and Management， 2024， 302： 118151.
[18]	LI C K， WANG G， WANG H， et al. Numerical investigation on thrust gain mechanism of helium injected solid-gas hybrid rocket motor［J］. 2024， 36（9）： 096121.
[19]	MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications［J］. AIAA Journal， 1994， 32（8）： 1598-1605.
[20]	TRAINEAU J C， HERVAT P， KUENTZMANN P. Cold-flow simulation of a two-dimensional nozzleless solid rocket motor‍［C］‍∥22nd Joint Propulsion Conference. Reston： AIAA， 1986.
[21]	BAI N J， FAN W J， ZHANG R C. A mixing enhancement mechanism for a hydrogen transverse jet coupled with a shear layer for gas turbine combustion［J］. 2023， 35（4）： 045111.

参数	数值
燃烧室直径d_c/mm	300
燃烧室内径d_f/mm	190
推进剂长度L_f/mm	800
喷管喉部直径d_t/mm	56
喷管出口直径d_e/mm	178
喷管收敛角度θ_c/（°）	45
喷管扩张角度θ_e/（°）	15

Specific impulse gain mechanism of micro-holes helium injected solid-gas hybrid rocket motor

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 17

References 21

Related Articles 6

Recommended Articles

Metrics

Comments

[1]	Ge WANG, Zhibang WANG, Fuqi WANG, Ben GUAN, Limin WANG, Haoran NING. Numerical study on quasi⁃one⁃dimensional internal ballistics of throttling segregated fuel⁃oxidizer systems [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 129111-129111.
[2]	Zhiguang SHI, Yujie YANG, Zongyu ZUO. Multi-element coupled modeling and simulation for multi-capsule near-space airships [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(16): 228451-228451.
[3]	LI Shu, WANG Li, WU Shuo, SHEN Dong, HUANG Rui, WANG Qiang. Analysis of high temperature nozzle exhaust flow towards aircraft-engine integrated design [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(1): 364-370.
[4]	Zhao Zhenlu;Wang Xiaoqun;Du Shanyi. Review of Research on Gas Retention Layer Material for Stratospheric Airship Envelope and Helium Permeation in Polymers [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(9): 1761-1768.
[5]	Wang Youfu;Chang Dayong . SELECTION OF THE OPTIMAL LIGHTER-THAN-AIR GAS FOR AIRSHIP AND A SCHEME OF DOUBLE-LAYER STRUCTURAL DESIGN [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1988, 9(8): 381-382.
[6]	Yang Yihe;Bai Changcheng. THE PROBLEMS OF THE INFRARED STEALTH OF THE FLYING VEHICLES [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1988, 10(12): 549-554.