| Citation: | CHAO Lide, GUO Hongjie, ZHANG Yuan, et al. Performance and structural scheme design of the diffuser for attitude and orbit control engines with high chamber pressure and large flow rate in mid-high-altitude simulation test[J]. Journal of Aerospace Power, 2024, 39（8）：20220956 doi: 10.13224/j.cnki.jasp.20220956
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The thermodynamic calculation method, normal shock wave theory, heat transfer theory, and strength theory were adopted to carry out the matching design and theoretical analysis of the performance and structural scheme of liquid attitude and orbit control engines and cylindrical diffusers. A design calculation method and procedure for determining the performance and structural scheme of diffusers was presented from the aspects of its performance, main dimensions, heat transfer mode, strength and stability verification. Influence curves of the area ratio of cylindrical diffusers, combustion chamber pressure ratio, vacuum chamber pressure ratio, and gas isentropic index on the main dimensions and operating characteristics of diffusers were obtained. A cylindrical diffuser with an inner diameter of 1.1 m, a length of 8 m, and an inner wall thickness and cooling jacket width of 10 mm was designed for the testing requirements of a certain NTO/MMH liquid attitude and orbit control engine with a thrust of
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