CAJ | 학술논문

理想速度公式的级间比解析分析忽略了重力损失和阻力损失的影响。为了更加贴近实际、更加全面的分析，利用直接积分弹道法研究了临近空间运载火箭关机点高度对运载器级间配置的影响。建立飞行器运动模型、控制模型、质量模型和优化模型，利用遗传算法在不同关机点高度下进行级间比/弹道一体化优化。分析得出结论：关机点高度较低时，一、二级燃料量要相对充足，这样可以保证足够的转弯时间；关机点高度越高，第三级燃料量越大，这样可以减少阻力损失。最大的运载能力需要由级间比、飞行程序和关机点高度的最佳组合来实现。
이상속도공식적급간비해석분석홀략료중력손실화조력손실적영향。위료경가첩근실제、경가전면적분석，이용직접적분탄도법연구료림근공간운재화전관궤점고도대운재기급간배치적영향。건립비행기운동모형、공제모형、질량모형화우화모형，이용유전산법재불동관궤점고도하진행급간비/탄도일체화우화。분석득출결론：관궤점고도교저시，일、이급연료량요상대충족，저양가이보증족구적전만시간；관궤점고도월고，제삼급연료량월대，저양가이감소조력손실。최대적운재능력수요유급간비、비행정서화관궤점고도적최가조합래실현。
The analytic solutions of mass distribution based on ideal velocity formula ignore the loss of resistance and gravity. In order to achieve a practical and comprehensive analysis, the direct integral ballistic trajectory method is adopted to do the research of the impact of different burnout heights on the mass distribution of launch vehicle. The aircraft movement model, control model, quality model and optimization model for launch vehicle are established. Best mass distribution of the vehicle is implemented based on Genetic algorithm in different burnout height. The analysis shows that: The fuel quality of the first stage must be sufficient when the height of burnout point is low. The fuel quality of the third stage increases with the height of burnout point so that the resistant loss is reduced. The maximum launch capacity is carried out by the best combination of mass distribution, flight program and the burnout point.