Parameter Analysis and Transient-Feature Study of a Long-Time Working Hybrid Rocket Motor-Reference-Cited by-同舟云学术

Parameter Analysis and Transient-Feature Study of a Long-Time Working Hybrid Rocket Motor

Published:2019-11 Issue:6 Volume:32 Page:04019086
ISSN:0893-1321
Container-title:Journal of Aerospace Engineering
language:en
Short-container-title:J. Aerosp. Eng.

Author:

Hao Zhu¹,Xingliang Sun²^ORCID,Chengen Li³,Hui Tian⁴,Guobiao Cai⁵^ORCID

Affiliation:

1. Lecturer, School of Astronautics, Beihang Univ., No. 37, Xueyuan Rd., Haidian District, Beijing 100191, China.

2. Engineer, Institute of Manned Space System Engineering, China Academy of Space Technology, No. 104, Youyi Rd., Haidian District, Beijing 100094, China (corresponding author). ORCID: .

3. Ph.D. Student, School of Astronautics, Beihang Univ., No. 37, Xueyuan Rd., Haidian District, Beijing 100191, China.

4. Professor, School of Astronautics, Beihang Univ., No. 37, Xueyuan Rd., Haidian District, Beijing 100191, China.

5. Professor, School of Astronautics, Beihang Univ., No. 37, Xueyuan Rd., Haidian District, Beijing 100191, China. ORCID: .

Publisher

American Society of Civil Engineers (ASCE)

Subject

Mechanical Engineering,Aerospace Engineering,General Materials Science,Civil and Structural Engineering

Link

http://ascelibrary.org/doi/pdf/10.1061/%28ASCE%29AS.1943-5525.0001071

Reference28 articles.

1. Arves J. P. H. S. Jones K. Kline K. Smith T. Slack and T. Bales. 1997. “Development of a N2O—HTPB hybrid rocket motor.” In Proc. 33rd Joint Propulsion Conf. and Exhibit 2803–2811. Reston VA: American Institute of Aeronautics and Astronautics.

2. Scale effect of fuel regression rate in hybrid rocket motor

3. Optimal design of hybrid rocket motor powered vehicle for suborbital flight

4. Pyrolysis Behavior of Hybrid-Rocket Solid Fuels Under Rapid Heating Conditions

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