Tests on GH₂/GO₂ model engine with aerospike nozzle

Hot-firing tests were carried out on a 1-cell GH₂/G0₂ linear. aerospike nozzle engine with round-to-rectangle primary nozzle. Test apparatus, structures and design parameters of the main parts of the experimental engine are described. The primary nozzle and inner layer of the combustion chamber were made of ablation resistant W-Cu alloy and the aerospike ramp was made of steel. Five short duration hot firing tests on the aerospike engine without generation cooling were executed successfully. The aerospike nozzle performance was obtained under different C_NPR(C_NPR is the the ratio of combustion chamber pressure p_c to ambient pressure p_a). It is shown that good altitude compensation of thrust and high efficiencies were yielded in the tests. If C_NPR = 110, efficiency is from 93% to 95%. If C_NPR =450, efficiency is from 96% to 98% and efficiency is from 93% to 96% if C_NPR = 1000. The promising efficiency of more than 98% at design point can be expected.