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摘要:
平流层飞艇放飞方式是其安全起飞的先决条件。本文对平流层飞艇放飞过程动力学响应建立了力学模型，提出了解析求解方法，开展了定量分析研究。依据影响平流层飞艇放飞过程的关键因素，对单氦气囊结构以及多氦气囊结构的平流层飞艇放飞过程进行了动力学分析，将单氦气囊结构飞艇动力学响应的定量分析结果与飞行试验过程中获得的数据进行对比，验证了分析方法的准确性，为进一步优化放飞过程的操作提供了依据。
Abstract:Launch mode of the stratospheric airship is the prerequisite factor to safely reach the target altitude. In this paper, a dynamics model for the launch process of stratospheric airship is firstly established, and the analytical solution method is put forward, and the quantitative analysis is carried out. Secondly, according to the typical issues that influence the launch process, the dynamic analysis of both the single-helium and multi-helium envelope structure are carried out, including dynamics response and force status. Furthermore, the numerical results of a single helium envelope structure are obtained and then compared with experimental data. The result verified the accuracy of the analytical method, which can also provide the basis for launch process of the airship and the design of the launch equipment.
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图 1 平流层飞艇氦气囊结构示意图
Figure 1. Schematic of helium-envelope structure of stratospheric airship
图 4 一种单氦气囊结构飞艇的放飞过程
Figure 4. Launch process of airship with single helium envelope structure
图 6 飞艇放飞过程中受力与角度示意图
Figure 6. Schematic of force status and angle during airship launch process
图 7 多氦气囊结构飞艇的飞行过程
Figure 7. Flight process of airship with multi-helium envelope structure
图 8 多氦气囊结构飞艇放飞前后受力
Figure 8. Force status for multi-helium envelope structure before and after airship launch
图 9 参数xb, yb和Izb随飞艇仰角变化示意图
Figure 9. Fluctuation of parameter xb, yb and Izb with airship elevation angle
图 11 飞艇放飞过程中质心速度变化
Figure 11. Fluctuation of center-of-mass velocity during airship launch process
图 12 飞艇仰角计算结果与实测数据对比
Figure 12. Comparison of elevation angle of airship between calculation results and flight test data
图 13 飞艇角速度计算结果与实测数据对比
Figure 13. Comparison of angular velocity of airship between calculation results and flight test data
图 15 放飞后飞艇仰角与升速变化
Figure 15. Fluctuation of pitch angle and rising velocity of airship after launch
图 16 3种典型浮重比下飞艇升速变化
Figure 16. Fluctuation of rising velocity of airship for three typical buoyancy-weight ratios
图 17 两种氦气囊结构升速与浮重比关系
Figure 17. Comparison of rising velocity and buoyancy-weight ratio between two kinds of helium envelope structure
表 1 不同浮重比飞艇稳定仰角和升速
Table 1. Stable pitch angle and rising velocity of airship for different buoyancy-weight ratios
浮重比 仰角/(°) 升速/(m·s-1) 1.1 11.13 1.56 1.2 11.41 2.20 1.3 11.56 2.69 1.4 11.66 3.11 1.5 11.72 3.47 1.6 11.77 3.81 1.7 11.81 4.11 1.8 11.84 4.39 1.9 11.86 4.66 2.0 11.88 4.91 
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表 2 两种氦气囊结构对比
Table 2. Comparison between two kinds of helium envelope structure
比较项目 单氦气囊结构 多氦气囊结构 氦气分布 同一容腔 多个容腔 飞艇浮心变化 很大，不可控 很小，受控 升空姿态 大仰角 小仰角，可选择 放飞时飞艇姿态 加速抬头，尾部下顿 仰角不变 排气方式 尾部集中排气 分段排气 升速/(m·s-1) 5~10 2~5 浮重比 小 大 副气囊结构 简单 复杂 加工工艺 简单 复杂 压控 简单 复杂 放飞形式 复杂 简单 典型案例 日本SPF-1 美国HALE-D
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