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与通常的氢氧发动机相比,采用原子氢推进剂可以使比冲提高几百秒。通过介绍运载火箭采用原子氢推进剂的发展前景、原子氢推进剂火箭的起飞质量和干重,以及原子氢推进剂火箭设计的最佳方案,在比较宽的混合比范围、固氢颗粒中原子态含量范围、液氦载体含量范围估算火箭发动机性能,可以得到混合比为0时,作为单元推进剂的火箭起飞质量最低。原子氢推进剂以其优良的比冲性能给航天运载器带来质的飞跃,但对低温技术提出挑战。
Compared with the usual oxy-hydrogen engine, the specific hydrogen impulse can be used to increase specific impulse by several hundred seconds. By introducing the development prospect of atomic hydrogen propellants, the take-off mass and dry weight of atomic hydrogen propellant rocket, and the best scheme of atomic hydrogen propellant rocket design, in a wide range of mixing ratio, State content range, liquid helium content range of the rocket engine performance estimates can be obtained when the mixing ratio is 0, the rocket take off as the lowest quality of the unit propellant. Atomic hydrogen propellants bring a qualitative leap to aerospace carriers with their excellent specific impulse performance, but they pose challenges to cryogenic technologies.