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基于太陽能熱推進(jìn)的應(yīng)急飛行器系統(tǒng)優(yōu)化設(shè)計(jì)

System optimization of responsive vehicle with solar thermal propulsion

  • 摘要: 基于太陽能熱推進(jìn)的航天器推進(jìn)系統(tǒng)具備高比沖、高效率等諸多性能優(yōu)勢。文章基于太陽能熱推進(jìn)原理實(shí)現(xiàn)應(yīng)急軌道航天器的軌道補(bǔ)償控制，并對系統(tǒng)關(guān)鍵參數(shù)進(jìn)行了優(yōu)化設(shè)計(jì)。首先建立軌道控制系統(tǒng)的數(shù)學(xué)模型，然后根據(jù)太陽能熱推進(jìn)原理與軌道特性實(shí)現(xiàn)吸熱劑質(zhì)量與聚光器吸熱面積的優(yōu)化計(jì)算，最后仿真驗(yàn)證該方案的可行性。仿真結(jié)果表明：該方案適用于210～300 km高度的應(yīng)急軌道，且吸熱劑質(zhì)量與聚光器面積需求均在合理范圍內(nèi)。

     

    Abstract: The spacecraft control system with the solar thermal propulsion (STP) has some advantages, including the great specific impulse and a high efficiency. In this paper, the STP is applied to the orbit compensation control of a responsive vehicle, and is optimized for the mission with as less absorber mass and as smaller reflector area as possible. Firstly, the model of the orbit compensation control system is built. Then, the mass of the absorber and the area of the reflector are successively optimized according to the principle of the STP and the characteristics of the responsive orbit. Finally, a numerical simulation is performed to testify the feasibility of the STP-based orbit compensation control, and the results show that the scheme is applicable for the responsive orbit in the height of 210 km to 300 km, where the mass of the absorber and the area of the reflector are both practicable for applications.

     

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