Purpose

In this paper, with the goal of reducing the fuel consumption of UAV, the engine performance optimization is studied and on the basis of aircraft/engine integrated control, the minimum fuel consumption optimization method of engine given thrust is proposed. In the case of keeping the given thrust of the engine unchanged, the main fuel flow of the engine without being connected to the afterburner is optimally controlled so as to minimize the fuel consumption.

Design/methodology/approach

In this study, the reference model real-time optimization control method is adopted. The engine reference model uses a nonlinear real-time mathematical model of a certain engine component method. The quasi-Newton method is adopted in the optimization algorithm. According to the optimization variable nozzle area, the turbine drop-pressure ratio corresponding to the optimized nozzle area is calculated, which is superimposed with the difference of the drop-pressure ratio of the conventional control plan and output to the conventional nozzle controller of the engine. The nozzle area is controlled by the conventional nozzle controller.

Findings

The engine real-time minimum fuel consumption optimization control method studied in this study can significantly reduce the engine fuel consumption rate under a given thrust. At the work point, this is a low-altitude large Mach work point, which is relatively close to the edge of the flight envelope. Before turning on the optimization controller, the fuel consumption is 0.8124 kg/s. After turning on the optimization controller, you can see that the fuel supply has decreased by about 4%. At this time, the speed of the high-pressure rotor is about 94% and the temperature after the turbine can remain stable all the time.

Practical implications

The optimal control method of minimum fuel consumption for the given thrust of UAV is proposed in this paper and the optimal control is carried out for the nozzle area of the engine. At the same time, a method is proposed to indirectly control the nozzle area by changing the turbine pressure ratio. The relevant UAV and its power plant designers and developers may consider the results of this study to reach a feasible solution to reduce the fuel consumption of UAV.

Originality/value

Fuel consumption optimization can save fuel consumption during aircraft cruising, increase the economy of commercial aircraft and improve the combat radius of military aircraft. With the increasingly wide application of UAVs in military and civilian fields, the demand for energy-saving and emission reduction will promote the UAV industry to improve the awareness of environmental protection and reduce the cost of UAV use and operation.

中文翻译：

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基于最小油耗模式的固定翼无人机飞行推进系统综合优化控制

目的

本文以降低无人机油耗为目标，对发动机性能优化进行了研究，提出了基于飞机/发动机综合控制的发动机给定推力最小油耗优化方法。在保持发动机给定推力不变的情况下，对未连接加力燃烧室的发动机主燃油流进行优化控制，以最大限度地减少燃油消耗。

设计/方法/方法

本研究采用参考模型实时优化控制方法。发动机参考模型采用某种发动机部件方法的非线性实时数学模型。优化算法采用拟牛顿法。根据优化变量喷管面积，计算出优化喷管面积对应的涡轮降压比，与常规控制方案的压降比之差叠加，输出给发动机常规喷管控制器. 喷嘴面积由传统的喷嘴控制器控制。

发现

本研究所研究的发动机实时最小油耗优化控制方法可以在给定推力下显着降低发动机油耗率。在工作点，这是一个低空大马赫工作点，比较靠近飞行包线的边缘。开启优化控制器前，油耗为0.8124 kg/s。开启优化控制器后，可以看到燃油供应减少了4%左右。此时高压转子的转速约为94%，涡轮后的温度可以一直保持稳定。

实际影响

提出了无人机给定推力下油耗最小的优化控制方法，并对发动机的喷管面积进行了优化控制。同时提出了一种通过改变涡轮压比间接控制喷嘴面积的方法。相关无人机及其动力装置的设计者和开发者可以考虑本研究的结果，以达成降低无人机油耗的可行方案。

原创性/价值

油耗优化可以节省飞机巡航时的油耗，提高商用飞机的经济性，提高军用飞机的作战半径。随着无人机在军用和民用领域的应用越来越广泛，节能减排的需求将推动无人机行业提高环保意识，降低无人机使用和运营成本。