A hybrid rockoon, which is a hybrid rocket launched from a high-altitude balloon, is proposed. The rocket system configuration was studied for single-stage or multiple-stage rockets, and the performance and range safety requirements were considered. The propellants of the hybrid-rocket motor are a low-melting-point thermoplastic fuel and nitrous oxide, which are beneficial, owing to their mechanical properties at cold temperatures experienced in high-altitude environments. Three-dimensional launch trajectory analyses were performed for science missions aimed at sampling cosmic dust levitating in the upper stratosphere. The apogee altitude can be significantly increased by elevating the altitude of the launch point because the problem of low thrust level of the hybrid rocket is solved by increasing the nozzle expansion ratio. Suborbital trajectories with multiple apogee points and orbital missions to extremely low Earth orbits are presented, which provide a long flight path in the upper atmosphere. The sequence of events and flight characteristics of the proposed hybrid rockoon system are discussed, and necessary technological improvements in the structure and propulsion systems are presented.

提出了一种混合火箭，它是一种从高空气球发射的混合火箭。研究了单级或多级火箭的火箭系统配置，并考虑了性能和射程安全要求。混合火箭发动机的推进剂是一种低熔点热塑性燃料和一氧化二氮，由于它们在高海拔环境中的低温下具有机械性能，因此它们是有益的。对旨在对漂浮在平流层上层的宇宙尘埃进行采样的科学任务进行了三维发射轨迹分析。由于提高喷管膨胀比解决了混合火箭推力水平低的问题，提高发射点的高度可以显着提高远地点高度。介绍了具有多个远地点的亚轨道轨迹和极低地球轨道的轨道任务，提供了在高层大气中的长飞行路径。讨论了所提出的混合火箭系统的事件序列和飞行特性，并介绍了结构和推进系统的必要技术改进。