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Power system and start control method and system of heavy rotor aircraft

A rotorcraft and power system technology, applied in the field of aircraft, can solve the problems of slow start-up process, poor stability, low efficiency, etc., and achieve the effect of increasing the start-up speed, reducing the impact of take-off, and simplifying the power transmission structure

Pending Publication Date: 2018-12-07
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Although the above method can realize the safe startup of heavy-duty aircraft, the startup process is slow, poor in stability and low in efficiency.

Method used

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  • Power system and start control method and system of heavy rotor aircraft
  • Power system and start control method and system of heavy rotor aircraft
  • Power system and start control method and system of heavy rotor aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] figure 1 It is a schematic structural diagram of a power system of a heavy-duty rotorcraft provided by an embodiment of the present invention. see figure 1 As shown, the power system of the heavy-duty rotorcraft includes: the first engine 1, the first one-way bearing 2, the first bevel gear set 4, the first motor 5, the transmission shaft 6, and the rotor 8 for connecting the heavy-duty rotorcraft The second bevel gear set 7; wherein, the output shaft of the first motor 1 is connected to the first bevel gear set 4 through the first one-way bearing 2, and the output shaft of the first motor 5 is connected to the first cone gear set 4 , the first bevel gear set 4 is connected to the second bevel gear set 7 through the transmission shaft 6 .

[0031] The output shaft of the first engine 1 is connected with the first one-way bearing 2. Its effect is that when the first motor 5 drives the propeller to pre-rotate, the rotation of the driven shaft cannot be transmitted to th...

Embodiment 2

[0040] figure 2 It is a flowchart of a first start-up control method for a heavy-duty rotorcraft provided by an embodiment of the present invention. Such as figure 2 Shown, a kind of start control method 200 of heavy-duty rotorcraft, wherein, described heavy-duty rotorcraft is provided with the power system of described heavy-duty rotorcraft, described start-up control method 200 comprises:

[0041] First, in step 201, when the start trigger signal is received, the first motor is controlled to start;

[0042] Secondly, in step 202, receiving the sensed speed signal of the rotor;

[0043] Again, in step 203, when it is determined according to the speed signal of the rotor that the difference between the speed value of the rotor and the preset critical take-off speed is less than a preset threshold, the first engine is controlled to start without load;

[0044] Then, in step 204, when the first engine reaches idle speed and it is determined according to the speed signal of ...

Embodiment 3

[0048] image 3 It is a flow chart of a second start-up control method for a heavy-duty rotorcraft provided by an embodiment of the present invention. Such as image 3 Shown, a kind of start control method 300 of heavy-duty rotorcraft, wherein, described heavy-duty rotorcraft is provided with the power system of described heavy-duty rotorcraft, described start-up control method 300 comprises:

[0049] First, in step 301, when a start trigger signal is received, the first motor and the second motor are controlled to start;

[0050] Secondly, in step 302, receiving the sensed speed signal of the rotor;

[0051] Again, in step 303, when it is determined according to the speed signal of the rotor that the difference between the speed value of the rotor and the preset critical take-off speed is less than a preset threshold, the first engine and the second engine are controlled to start;

[0052] Then, in step 304, when the first engine and the second engine reach idle speed and ...

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Abstract

The invention discloses a power system and start control method and system of a heavy rotor aircraft. The power system of the heavy rotor aircraft comprises a first engine, a first one-way bearing, afirst bevel gear set, a first motor, a transmission shaft and a second bevel gear set used for being connected with rotors of the heavy rotor aircraft. An output shaft of the first engine is connectedwith the first bevel gear set through the first one-way bearing, an output shaft of the first motor is connected with the first bevel gear set, and the first bevel gear set is connected with the second bevel gear set through the transmission shaft. The start speed of the heavy rotor aircraft can be increased, start impact is reduced, start efficiency is improved, and the service life of the engine is prolonged.

Description

technical field [0001] The invention relates to the field of aircraft, in particular to a power system, start control method and system of a heavy-duty rotorcraft. Background technique [0002] In order to meet the heavy-duty power requirements of traditional double-duct heavy-duty aircraft, multiple engines usually drive each rotor separately. For example, the Chinese invention patent CN201510120914.6, which is called a double-duct flying motorcycle, discloses a double-duct coaxial multi-rotor flying motorcycle, which belongs to the field of special aircraft. It includes a body, two main rotors, four auxiliary rotors and a control system installed in the body, the two main rotors are respectively arranged in front and rear of the body, and two auxiliary rotors are respectively installed under each main rotor. The auxiliary rotor can rotate around its connection point with the main rotor; the four auxiliary rotors are located on the same horizontal plane, and the four auxil...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/10B64C27/12B64D31/00
CPCB64C27/10B64C27/12B64D31/00
Inventor 项昌乐徐彬张一博樊伟
Owner BEIJING INSTITUTE OF TECHNOLOGYGY