运载火箭助推器伞控回收方案及安全性分析

近年来民营航天公司在火箭回收技术上取得了巨大的突破和成功,受到了广泛关注,各国各种先进回收技术和方案也在验证中,我国也已加速开展回收方案论证和试验验证。提出了一种简单可靠、子系统成熟、成本低廉且具备快速搭载飞行试验演示验证条件的回收方案,该方案采取伞降减速、翼伞落点控制及支腿着陆防护的方式回收助推器,可以作为我国火箭回收工程实践的第一步,为后续回收技术研究和实践积累经验和数据。通过助推器分离仿真分析、再入过程气动计算及姿态仿真计算表明助推器回收方案不影响主飞行任务安全性,再入回收过程可控,具备工程实施的可行性。

Recovering Scheme of Launch Vehicle Boosters Using Steerable Parachutes and the Safety Study

In recent years privately-funded aerospace companies have achieved great success in reusable launch vehicle design and manufacturing, which have drawn extensive public attention and driven us to speed up the recovering schematic design and experimental verification. A scheme for recovering of boosters is proposed, which uses parachutes to reduce the descending velocity and then uses steerable parachutes to control the drop point, and finally, uses support legs to protect the boosters while landing. The scheme is simple, reliable and cost-efficient, the subsystems of which are mature. Further, it can be soon carried for demonstration and testing in a launch mission. The scheme is proper to be a first step for engineering practice of our launch vehicle recovering. It will provide experience and data for the following recovering study and practice. After performing booster separation simulation, aerodynamic calculation and attitude simulation, it is proven that the scheme has no effect to the safety of the launch mission, and, the reentry process is controllable and the scheme is qualified for implementation.