某航空活塞发动机进、排气正时优化

利用基于仿真的遗传算法优化方法,对某型点燃式航空活塞发动机气门正时优化进行了研究。通过耦合发动机性能模型与modeFrontier专业优化软件,以提高发动机巡航工况下有效功率和降低燃油消耗率为目标对发动机的进、排气正时和进、排气持续期进行了优化。分析结果表明:相比于原机,通过优化进、排气门正时和进、排气持续期,发动机在巡航工况下燃油消耗率降低2.5%,功率提升7.3%;优化后的进、排气参数也可以提升发动机节气门全开时发动机的性能,减少飞行器的起飞滑跑距离。      

空中加油变质量建模与干扰补偿控制

为抑制空中加油给飞机带来的变质量影响,将质量的变化等效为对飞机的干扰力和干扰力矩,建立了变质量飞机的一般动力学模型,并经过小扰动线性化得到飞机带干扰的纵向状态方程.采用比例积分观测器(PIO)对干扰进行观测,基于观测值设计了补偿控制器以实现对变质量干扰的抑制.以受油机为例进行计算机仿真,结果表明,该模型有效地反映了变质量受油机的动力学特性,干扰补偿控制器能够实现对变质量受油机的精确控制.     

Flow control of double bypass variable cycle engine in modal transition

To study the change mechanism and the control of the variable cycle engine in the process of modal transition, a variable cycle engine model based on component level characteristics is established. The two-dimensional CFD technology is used to simulate the influence of mode selection valve rotation on the engine flow field, which improves the accuracy of the model. Furthermore, the constant flow control plan is proposed in the modal transition process to reduce the engine installed drag. The con...     

精密球体零件加工工艺的研究与应用

球体零件是某国家重点型号发动机某一球阀的核心零件,它具有高形位公差要求、形状不规则、表面质量要求高等特点,给实际的加工生产带来极大难度,该零件被列入某国家重点型号发动机研制中的关键工艺技术之一.通过反复试加工与参数摸索,在充分了解铝材质球体零件结构特点及加工难点的基础上,总结出一套粗加工、半精加工、精加工的加工工艺流程方法,并依据金属材料热处理原理在粗加工后、精加工前分别穿插进行不同热处理以达到消除粗加工去除大余量过程中产生的机械加工应力与稳定零件尺寸的目的,最后采用自制辅助工装夹具、刀具选择以及优化切削参数等措施,成功生产出一批完全满足设计要求的精密球体零件,装配该球体零件的球阀顺利通过热试车考核.     

双泵电静液作动器控制研究

功率电传技术是未来全电飞机发展须攻克的难点,其中具有集成化优势的小型高效电静液作动器是功率电传技术领域的一项重要内容。智能材料驱动的电静液作动器由于具备集成度高、能量密度大、响应快、精度高等优势,已逐步成为电静液作动器的主流发展方向之一。本文针对一种双压电泵驱动、电机配流的封闭式电液作动器,从驱动幅值、频率、相位3个控制维度出发,提出幅相控制、频相控制与纯相控制3种控制方法。试验证明,幅相控制与纯相控制误差低于频相控制,当该作动器在跟踪 0.5 Hz 频率、7.5 mm 峰峰值的正弦目标位移时,幅相控制和纯相控制的均方根误差分别为0,09 mm 与1.101 mm,相对低于频相控制时的0.169 mm。文中所提出的3种控制方法均可实现双泵电静液作动器的伺服控制,但幅相控制和纯相控制方法的控制精度优于频相控制。     

浮子式双油面控制器开启及燃油流动特性

飞机燃油系统具有储存燃油、将燃油输送到发动机以及调节飞机重心等功能,从储油箱供给发动机的燃油需经过消耗油箱,其中双油面控制器是消耗油箱中的 1种前导式阀门,能够控制输油的开启关闭,保证油箱基本满油。在使用过程中,发现双油面控制器会出现无法开启或提前关闭现象,给供输油安全带来极大影响。为了了解油面控制器工作异常的原因,并获取阀门内部燃油流动特性,文章采用动力学建模仿真的方法,获得大小活门不同工况下的运动轨迹,发现活门油压方向对开启过程具有明显影响;采用 CFD仿真方法,获取阀门燃油流动特性,发现随阀门开度和入口压力增大,出口燃油由“涌出”变为“喷出”,越过挡油板进入浮子腔的燃油占比增多,可能导致输油的提前关闭。     

Mathematical modeling of an armature assembly in pilot stage of a hydraulic servo valve based on distributed parameters

The dynamic performance of a nozzle-flapper servo valve can be affected by several factors such as the disturbance of the input signal, the motion of the armature assembly and the oscillation of the jet force. As the part of vibrating at high frequency, the armature assembly plays a vital role during the operation of the servo valve. In order to accurately predict the transient response of the armature assembly during the vibration, a mathematical model of armature assembly is established based on the distributed parameters method (DPM) and Hamilton principle. The new mathematical model is composed of three main parts, the modal eigenfunction, modal mechanical response expressions of the spring tube and the motion equation of the other armature assembly. After programing, the purpose of using the DPM to predict the dynamic response of different positions located on the armature assembly is achieved. For verifying the validity of the mathematical model, the finite element method (FEM) and classic model (CM) of armature assembly are applicated by commercial software under the same condition. The comparison results prove that the DPM can effectively predict the axial and tangential deflection of the armature assembly different positions which the CM can’t duing to its over-simplification. A certain error is generated when predicting the axial deformation at different heights by DPM, which is caused by an approximate method to simulate the torsion of the spring tube. The comparison results of the spring tube deflection at different vibration frequencies shows that the adaptability of DPM is significantly higher than the classic model, which verify the model is more adaptable for predicting the dynamic response of the armature assembly.     

Experimental and numerical study on pressure oscillation in a combustor with rotary valve

A rotary valve coupled in a combustor assembly can generate periodic pressure oscillations inside the combustor and can be used to study the combustion instability in the combustion chamber of a rocket engine. This paper proposes a cold gas flow experimental system based on a rotary valve and a corresponding rotation model. A 3D numerical model is proposed to obtain the transient flow inside the rotary valve, and the dynamic mesh technique and User-Defined Functions (UDFs) are adopted to implement a swing motion instead of a rotary motion. Several cold gas flow experiments are carried out at rotating speeds of 75 225, and 375 rpm to verify the validity of the numerical model. The effects of rotating speed, stroke length ratio and radius of the RED (Rotor Exhaust Duct) on the pressure oscillations are studied using this numerical model. The results show that the maximum and peak-to-peak values of the pressure oscillations gradually decrease with increasing rotating speed. The ratio of the corresponding peak-to-peak value to the maximum pressure (pressure amplitude ratio) is reduced from 1.81 to 0.6%. The stroke length ratio affects the pressure waveform because it leads to a change in the time spent in the non-exhaust stage. When the stroke length ratio is 0, the waveform closely resembles a sine wave. With the increase in the stroke length ratio, the pressure waveform exhibits a more square or a triangular wave shape. Finally, a high-frequency and high-amplitude pressure oscillation can be obtained by appropriately increasing the radius of the RED.     

一起发动机软轴断裂引发直升机双发停车的故障分析

通过对一起米-171直升机空中双发停车故障原因的探究,分析了造成双发停车的原因,剖析了发生问题的主要根源,为今后防止发生此类问题提供了借鉴.     

基于旋转阀的脉冲爆震火箭发动机实验

针对现有条件下电磁阀高频与大流量不可兼得的矛盾,设计了一种凸轮式旋转阀,以此来控制脉冲爆震火箭发动机氧化剂、燃料和隔离气体的间歇式供给.基于该旋转阀,以汽油和富氧空气为推进剂,进行了不同频率下的实验.实验结果表明,推进剂和隔离气供给压力与点火相位直接影响到能否稳定起爆.随着频率的增加,在1～ 10 Hz范围内,降低隔离氮气压力、调整点火相位可实现发动机的稳定工作;10Hz以上时,仅需要提高油气的供给压力.基于该旋转阀控制技术,脉冲爆震火箭发动机实现了工作频率30 Hz的稳定工作.