辅助动力装置系统空中起动设计和验证

辅助动力装置(Auxiliary Power Unit,简称APU)系统空中起动设计和验证共涉及APU 本体研制、APU 系统进排气冲压恢复计算分析、APU 系统进排气和APU 本体性能匹配计算分析、APU 系统进气风门设计、进气风门气动载荷计算分析、进气风门作动机构设计、进气风门控制逻辑设计、本体起动控制逻辑设计、冲压恢复测量试飞、适航验证试验试飞等内容,这对飞机主制造商的系统集成能力和适航验证能力提出了很高要求。APU 系统空中起动设计直接影响系统起动性能和起动包线,对某型飞机的辅助动力装置系统空中起动设计和验证进行了介绍,在型号研制经验的基础上,对APU 系统空中起动设计和验证流程和方法进行总结,对后续型号研制具有较强的指导性。

Design and Certification of Auxiliary Power Unit System In-flight Starting

Auxiliary Power Unit (APU) system in-flight starting design and certification involve APU development, APU system inlet and exhaust ram recovery analysis, APU inlet/ exhaust impact on APU performance analysis, APU inlet door design, inlet door aerodynamic load analysis, inlet door actuation mechanism design, inlet door control logic design, APU starting control logic design, ram recovery flight test, certification flight test. APU system in-flight starting design has an impact on APU performance and in-flight starting envelope. This paper presents a design of Auxiliary Power Unit system in-flight starting. Based on the development and research experience,it summarizes the APU system design and certification process and method. It is a good reference to other aircraft model development.