Purpose

This paper aims to present assessment of models and simulation results used in the development process of flight stabilisation system that uses trim tabs for PZL-130 Orlik turboprop military trainer aircraft. Flight test of the system allowed to compare software and hardware simulation results with real flight recordings.

Design/methodology/approach

Proposed flight stabilisation system was developed using modern techniques of model-based design, automatic code generation, software and hardware in the loop testing. The project reached flight testing stage which allowed to gather data to verify models and simulation results and asses their quality.

Findings

Results of the comparison showed that the trim tab actuator model used in simulation can be improved by adding play. This reduced the difference between simulation and real flight system output – actuator angle. The influence of airloads on the flying actuator angle compared to hardware in the loop simulation in lab is less than ± 0.6°.

Originality/value

Proposed flight stabilisation system that uses trim tabs has several benefits over classic automatic flight system in terms of weight, energy consumption and structure simplicity and does not need aircraft primary control modification. It was developed using modern techniques of model-based design, automatic code generation and hardware in the loop simulations.

中文翻译：

---

飞行稳定系统软硬件在环仿真的初始飞行试验验证

目的

本文旨在对 PZL-130 Orlik 涡轮螺旋桨军用教练机使用配平片的飞行稳定系统开发过程中使用的模型和仿真结果进行评估。系统的飞行测试可以将软件和硬件模拟结果与真实飞行记录进行比较。

设计/方法论/途径

拟议的飞行稳定系统是利用基于模型的设计、自动代码生成、软件和硬件在环测试等现代技术开发的。该项目进入了飞行测试阶段，可以收集数据来验证模型和模拟结果并评估其质量。

发现

比较结果表明，可以通过增加游隙来改进仿真中使用的配平片致动器模型。这减少了模拟和真实飞行系统输出——执行器角度之间的差异。与实验室硬件在环仿真相比，空气载荷对飞行执行器角度的影响小于±0.6°。

原创性/价值

所提出的使用配平片的飞行稳定系统在重量、能耗和结构简单性方面比传统的自动飞行系统具有多个优点，并且不需要飞机主要控制修改。它是使用基于模型的设计、自动代码生成和硬件在环仿真的现代技术开发的。