Configuration system design and longitudinal flight simulation verification of variable stability helicopter

变稳直升机构型系统设计及纵向飞行仿真验证

Key Laboratory of Flight Simulation Aeronautical Technology of AVIC, Xi'an 710089, China

Received: 29 May 2021

Abstract

For in-flight simulation of variable stability helicopter, how to have the ability to change a wide range of response characteristics and ensure flight safety is an important design problem. This paper proposes configuration design technology of the variable stability helicopter, which purpose is to safely change steady-state and dynamic response characteristics of the variable stability helicopter, and make the pilot feel good or poor helicopter response characteristics. The configuration control system of the variable stability helicopter is designed theoretically, and the configuration switch logic is studied from the perspective of flight safety. The numerical simulation test of the longitudinal configuration control law was carried out, and the configuration control law and configuration switch logic were added to the ground closed-loop test to verify. The results show that the expected response characteristics of the helicopter are obtained by applying the configuration system design technology.

摘要

针对在空中飞行模拟中, 变稳直升机需具有响应特性的大范围变化能力以及飞行安全性设计等问题, 提出变稳直升机构型设计技术, 目的是安全地实现变稳直升机稳态和动态响应特性的变化, 使驾驶员能感受到较好或较差的直升机响应特性。从理论上设计变稳直升机构型控制系统, 并从飞行安全角度研究构型切换逻辑; 对纵向构型控制律进行数值仿真试验, 并在地面台架试验中验证构型控制律和构型切换逻辑。试验结果表明, 通过应用构型系统设计技术, 获得了期望的直升机响应特性。