Flight Matching Method of Piston Engine and Unmanned Helicopter

Abstract

The invention discloses a flight matching method of a piston engine and an unmanned helicopter, wherein the control method includes the following steps of judging the current flight state of the unmanned helicopter; The required power N under T XU and the collective distance relationship, and finally get the corresponding relationship between the throttle OIL and the collective distance; 0 Under the required power N XU Finally, the corresponding relationship between the throttle OIL and the collective distance in the forward flight state is obtained. The above-mentioned flight control method not only ensures the balance of force but also the balance of power, thus avoiding the flight accident of the unmanned piston helicopter due to improper coordination with the engine.

Description

technical field [0001] The invention relates to the field of unmanned helicopters, in particular to a flight matching method of a piston engine and an unmanned helicopter. Background technique [0002] In the past ten years, with the rapid development of composite materials, power systems, sensors, and electronic technologies, especially the development of flight control technology, unmanned helicopters have developed rapidly. At present, unmanned helicopters are mostly small helicopters, most of which are equipped with piston engines. Since small piston engines have simple structures and no fuel adjustment system, how to ensure the matching of the two under any flight conditions has become the focus of research. [0003] Through the analysis of the flight principle of the unmanned helicopter, it is shown that the unmanned helicopter must ensure the tension balance and power balance at the same time in order to make a stable flight at a fixed height in the air: [0004] (1)...

AI Technical Summary

Problems solved by technology

Although the flight weight of the unmanned helicopter does not change much during flight, due to the unique aerodynamic characteristics of the rotor, its collective distance value is different under the same weight and different flight speeds;

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