A spin-recovery parachute system for light general aviation airplanes
A spin-recovery parachute system for light general aviation airplanes
复制标题
一种轻型通用航空飞机自旋恢复降落伞系统
DOI：
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发表时间：
1980
期刊：
影响因子：
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通讯作者：
C. F. Bradshaw
中科院分区：
文献类型：
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作者：
C. F. Bradshaw
NASA兰利研究中心（NASA Langley Research Center）在轻型通用航空飞机上使用了尾部安装的自旋恢复降落伞系统。该系统设计用于典型的飞机配置，包括低翼，高翼，单引擎和双引擎设计。机械触发的烟火sl枪用于强行部署飞行员降落伞，该降落伞提取了一个部署环形插槽的旋转式降落伞的袋子。总系统重8.2千克（18磅）。系统设计因素包括飞机唤醒对降落伞部署的影响，预防过早降落伞部署，积极的降落伞抛弃，紧凑尺寸，低重量，系统可靠性以及飞行员和地面机组人员安全。进行了广泛的地面测试以验证该系统。恢复降落伞已在17次飞行中成功使用。
A tail-mounted spin-recovery parachute system has been designed and developed by the NASA Langley Research Center for use on light general aviation airplanes. The system was designed for use on typical airplane configurations, including low-wing, high-wing, single- and twin-engine designs. A mechanically triggered pyrotechnic slug gun is used to forcibly deploy a pilot parachute which extracts a bag that deploys a ring-slot spin-recovery parachute. The total system weighs 8.2 kg (18 lb). System design factors included airplane wake effects on parachute deployment, prevention of premature parachute deployment, positive parachute jettison, compact size, low weight, system reliability, and pilot and ground crew safety. Extensive ground tests were conducted to qualify the system. The recovery parachute has been used successfully in flight 17 times.