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Hybrid power system for multi-rotor aircraft and multi-rotor aircraft

A technology of a hybrid power system and a multi-rotor aircraft, which is applied in the aerospace field, can solve the problems of low reliability, complex structure, and the weight of the engine accounts for a large proportion, and achieves the effect of light weight and flexible control

Inactive Publication Date: 2019-11-22
TSINGHUA UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, compared with the electric motor, the fuel engine cannot meet the requirements of quickly controlling the flight attitude of the multi-rotor aircraft due to the slow speed adjustment of the piston engine compared with the electric motor.
In addition, the oil-powered multi-rotor aircraft has a large weight, low mechanical transmission efficiency, complex structure, and low reliability.
[0005] Although the existing hybrid multi-rotor aircraft can solve some of the problems of the above-mentioned multi-rotor aircraft, the weight of the engine and the corresponding mechanical devices still account for a large proportion

Method used

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  • Hybrid power system for multi-rotor aircraft and multi-rotor aircraft

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Embodiment Construction

[0039] Embodiments of the invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0040] Such as figure 1 As shown, the aircraft 1000 includes a main rotor 300, an auxiliary rotor 200 and a hydrogen balloon 11, the main rotor 300 and the auxiliary rotor 200 are used to drive the aircraft 1000 to fly, and the hydrogen balloon 11 is mechanically connected to the aircraft 1000 above the central axis of gravity of the aircraft 1000, It is used to reduce the weight of the aircraft and increase the payload.

[0041] Refer below figure 1 A hybrid system 100 for an aircraft 1000 according to one embodiment of the invention is described. Such as figure 1 As shown, a hybrid power system 100 for an aircraft 1000 includes an engine 2 , a power battery...

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Abstract

Disclosed is a hybrid power system for a multi-rotor aircraft. The hybrid power system comprises: an engine (2); a power battery (5); a starting and power generation integrated motor (7) which is electrically connected with the power battery (5) and mechanically connected with the engine (2), wherein power output by at least one of the engine (2) and the starting and power generation integrated motor (7) is used for being provided for a main rotor (300) of the multi-rotor aircraft; an auxiliary rotor wing motor (10) which is electrically connected with the power battery (5), wherein the outputof the auxiliary rotor wing motor (10) is used for being mechanically connected with an auxiliary rotor wing (200) of the multi-rotor aircraft; and a hydrogen balloon (11) which is positioned above the central axis of the gravity center of the multi-rotor aircraft and is mechanically connected with the multi-rotor aircraft. The multi-rotor aircraft using the hybrid power system is flexible in control, high in safety performance, large in load, capable of saving oil and long in endurance time.

Description

technical field [0001] The invention relates to the field of aerospace and aviation, in particular to a hybrid power system for a multi-rotor aircraft and the multi-rotor aircraft with the hybrid power system. Background technique [0002] Multi-rotor aircraft is an aircraft with simple structure, flexible control, easy to carry, stable flight attitude, and low safety hazard. There are different types of multi-rotor aircraft such as four-axis, six-axis, and eight-axis multi-rotor aircraft. It not only plays an increasingly important role in the military field, but also has been widely used in many civilian fields such as disaster rescue, assessment, dangerous environment investigation, traffic inspection and aerial photography. [0003] However, due to the limitations of current battery technology, battery-powered multi-rotor aircraft generally have short battery life, limited load capacity, frequent battery replacement, low operating efficiency, and high cost, which greatl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/02B64C27/12B64C27/08
CPCB64D27/02B64C27/12B64C27/08B64U50/11B64U10/10B64U50/19B64D27/026
Inventor 张海涛周明兰旭东
Owner TSINGHUA UNIV
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