Hot-firing Tests on 3-cell Linear Aerospike Nozzle
Employing GH2/GO2 as propellants, hot -firing tests were carried out on a 3-cell aerospike nozzle engine. Test apparatus, structures and design parameters of the main components of the experimental engines are described. Data measured in the tests,test photographs and data analyses are presented. Altitude characteristics of the aerospike nozzle engines were predicted by numerical simulation. The primary nozzle and inner layer of the combustion chamber were made of ablation-resistant W-Cu alloy and the plug ramps were made of steel. Detonation wave igniter was adopted in the tests and the engines without generation cooling executed several short-duration hot-firing tests successfully. The aerospike nozzle performance was obtained under several nozzle pressure ratio (CNPR). It is shown that good altitude compensation of thrust and high efficiencies were yielded in the tests. Near CNPR =50, efficiency varies from 92％ to 93. 5％ and efficiency varies from 95％ to 96％ near CNPR =350. The promising efficiency of more than 98％ at design point can be expected.
Rocket Engine Aerospike Nozzle Hot-firing Test Performance Numerical Simulation
Liao Yunfei Liu Yu Wang Changhui Wang Yibai
School of Astronautics Beijing University of Aeronautics and Astronautics,Beijing 100083,China
国际会议
The 11th International Space Conference of Pacific-basin Societies(第11届环太平洋国际航天会议)
北京
英文
570-577
2007-05-16（万方平台首次上网日期，不代表论文的发表时间）