舰载飞机的进场动力补偿和自动油门控制系统设计

【作者】 李应涛；

【导师】 徐利梅；

【作者基本信息】 电子科技大学 ， 机械电子工程， 2007， 硕士

【摘要】 舰上起降是常规起降固定翼舰载飞机所面临的核心技术问题。为确保舰载飞机安全着舰,自动着舰系统(Automatic Carrier Landing System,ACLS)被用于进场着舰引导和精确航迹控制。作为ACLS的一个重要子系统,进场动力补偿系统(Approach Power Compensator System,APCS)按进场动力补偿控制律对发动机油门(推力)进行自动控制,以克服舰载飞机低速进场时的速度不稳问题,提高航迹控制精度,并减轻飞行员在进场着舰段的工作负荷。要对发动机油门进行自动控制,就需要有自动油门控制系统(Automatic Throttle Control System,ATCS)。针对实际工程应用,本文对舰载飞机的进场动力补偿系统APCS和自动油门控制系统ATCS进行了研究。本文首先分析了不同的APCS补偿结构及其效果。基于飞机纵向小扰动动力学方程,忽略风扰因素、舵面变化和短周期力矩平衡过程,对含有APCS的航迹γ对姿态θ的响应环节的控制结构进行了简化,并推导了其传递函数,以简化分析APCS对航迹响应的影响。然后仿真分析了①无APCS补偿、②采用速度恒定的APCS|u补偿、③采用迎角恒定APCS|α补偿、④采用同时引入迎角α和法向加速度nz的APCS|α+nz补偿对航迹响应的影响。验证了APCS|α+nz对加速航迹响应过程、抑制长周期振荡,进而改善航迹响应特性的效果。针对某工程应用,确定了APCS的补偿结构、设计了控制律和自动油门指令算法。设计中采用APCS|α+nz+δe补偿结构,即在迎角恒定的APCS中同时引入迎角α、法向加速度nz和舵面变化信息δe。针对这种补偿结构,进行了系统参数设计,得到了APCS控制律和自动油门指令算法,并对航迹响应特性的进行了仿真分析,以验证APCS系统设计结果。介绍了一种改进设计的机/电双操纵模式的自动油门控制系统ATCS。在自动模式下,ATCS按照APCS控制律对发动机油门进行自动控制。本文对该系统的基本原理、控制逻辑及主要组成进行了简要介绍,特别是对自动油门伺服装置进行了介绍。介绍了自动油门控制系统的试验测试与验证。试验内容包括单元件特性测试和系统综合性能测试。在单元件特性测试中,测试了力矩开关、油门台、自动油门伺服装置和轮盘传动组件等单元件性能。在系统综合测试中,测试了系统对阶跃指令、正弦指令、随机指令等指令信号的响应特性,测试并验证了系统在模式切换时的响应特性。试验结果表明,该系统设计是可行的,能满足APCS进行自动油门控制的需要。更多还原

【Abstract】 Taking off and landing are the most important and difficult issues considered for fixed-wing carrier aircraft. Aimed at the strong need for improving carrier landing, the Automatic Carrier Landing System (ACLS) has been applied to approach guidance and path control for decades. As an important component of the ACLS, the Approach Power Compensator System (APCS) has a purpose of relieving the pilot of the throttle management task during all phases of carrier approach. By imposing the compensation control laws on the Automatic Throttle Control System (ATCS), the APCS is normally required to manage the engine power so as to keep flight stable and improve the flight path control. Aiming at an engineering application, some studies on the APCS and the ATCS are presented, and briefly listed below.Different APCS structures and the effects on flight path response are presented. Basing on small disturbance dynamic equations of aircraft moving within a vertical plane, without consideration of the air-wake, the elevator deflection and the short term process of moment balancing, a simplified control model of the flight path angleγresponse to pitch angleθwith APCS is presented. A normal transfer function of the simplified model is deduced, with which the effects of the APCS on flight path response can be easily analyzed. Simulations and validations of theγresponses toθwith four different compensation modes are presented. The four compensation modes are (a) without APCS, (b) with the speed regulator APCS|u, (c) with the angle of attack regulator APCS|αand (d) with APCS|α+nz fed back with both the angle of attackαand the normal acceleration nz respectively. The results indicate that the flight path response can be improved to be stable, rapid and accurate with the APCS|α+nz compensation structure.An engineering APCS, including its compensation structure, control laws and the throttle command algorithm are presented. Aimming at the actual requirements of the engineering application, a compensation structure of APCS|α+nz+δe is defined, where the angle of attackαand the normal acceleration nz and the elevator variationδe are all fed back. Basing on the structure, the system parameters are calculated, and the flight path response is simulated for system validation. The results support a conclusion that the APCS presented matchs the actual requirements well.An improved mechanical and electrical bi-operating ATCS is also presented in this paper. In auto mode of the ATCS, the APCS manages the throttle automatically according to the flight conditions and the control laws.The system principle, control logic, main components are presented briefly. In particularly, the automatic throttle servo device is further introduced.System validating tests for the improved ATCS, including separate component performances and integrated system performances, are presented. The performances of the moment switch, the throttle handling device, the throttle servo device, and the wire-wheel assembly are concerned separately. For integrated system performances, the throttle responses to step signal, sine wave singnal and random signal, and the performances of modes switching are tested and validated. The results indicate that the ATCS is feasible for the APCS applications.更多还原