Abstract: In order to demonstrate that the turbocharged solid propellant ramjet (TSPR) has the ability to accelerate and climb to cruise state independently， and get the suitable ballistic flight plan， the research on the climbing flight plan of TSPR has been carried out. Firstly， the off-design performance of TSPR with two different design points-high altitude cruise condition design point and maximum power design point， has been analyzed by drawing on the parameters of the existing projectiles in the range of ballistic flight. Then compared with the engine thrust and the aircraft drag， it can be concluded that， with the high altitude cruise condition as design point， the thrust provided by the TSPR during climbing was less than the drag of the vehicle， which makes it difficult for TSPR to climb independently. Nevertheless， when the engine was designed at the maximum power sate and the relative conversion speed was constant， the climb performance of TSPR is excellent， and it is able to accelerate from (3km， Ma0.9) to (10km， Ma2.2). Besides， the range of the missile driven by TSPR is three times as long as that of solid rocket， which proves that TSPR has the ability to independently accelerate and climb to cruise state， and has good impulse performance as well.

Key words: Turbocharged solid propellant ramjet；Climbing?control?plan；Maximum power rating；Relative corrected speed unchanged

摘要： 为了证明涡轮增压固冲发动机(TSPR)具有自主加速飞行的能力，进而得到合适的弹道飞行方案，开展了TSPR爬升飞行方案研究。首先通过借鉴已有弹体参数，分析了以高空巡航状态为设计点和以最大功率状态为设计点时，飞行器在弹道飞行范围内的非设计点性能。随后对比了发动机推力和飞行器阻力大小，得出:当TSPR以高空巡航点为设计点时，TSPR在爬升段(非设计点)所提供的推力小于飞行器阻力，难以实现自主爬升；当TSPR以最大功率状态为设计点，且采用等相对换算转速的调节规律时，TSPR具有优良的爬升加速性能，能够从(3km，Ma0.9)加速爬升至(10km，Ma2.2)状态巡航，其射程是固体火箭发动机的三倍，这证明TSPR在具有自主加速飞行能力的同时还具有良好的比冲性能。

关键词: 涡轮增压固冲发动机；爬升方案；最大功率状态；等相对换算转速