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Unmanned aerial vehicle power device

A technology of motor power and power generation device, applied in the field of aviation power, can solve the problems of reducing the overall reliability of the power system, severe vibration of the piston engine, and increasing the weight of the power system structure, and achieves the effect of simple structure, small weight and reduced interference.

Active Publication Date: 2017-03-29
重庆星环航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The piston engine runs with severe vibration, loud noise, complex mechanical structure, and inconvenient maintenance. It needs to install an enhanced cooling device and carry working fluid for long-term operation, which greatly increases the structural weight of the power system.
When a generator is used to supply power to airborne equipment, an additional transmission and speed change mechanism needs to be installed, which not only increases the weight, but also reduces the overall reliability of the power system

Method used

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  • Unmanned aerial vehicle power device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] Such as figure 1 As shown, the unmanned aerial vehicle power plant of the present invention includes a turboshaft engine 1, and the axis of the output shaft output direction of the turboshaft engine 1 is sequentially provided with a power generating device and a reduction box 8; it also includes a transmission shaft, and the The reduction box 8 is provided with a transmission shaft bearing seat 7, the left end of the transmission shaft is internally driven with the reduction box 8 and is matched with the transmission shaft bearing seat 7 through a bearing, and the right end is in transmission cooperation with the output shaft; the power generation device includes a stator 6 And the rotor 5, the stator 6 is fixed on the right end face of the transmission shaft bearing housing 7, and the transmission shaft freely passes through the stator 6; the rotor 5 is sleeved on the transmission shaft and fitted to the right end of the stator 6. The UAV power device of the present in...

Embodiment 2

[0024] Preferably, on the basis of the above-mentioned embodiments, this embodiment is further optimized, and the transmission shaft is driven and matched with the output shaft through a coupling. Since the transmission shaft is matched with the output shaft through the coupling, the installation and disassembly are convenient, and the maintenance is convenient. If the transmission shaft and the output shaft are integrally formed, the installation and disassembly of other parts will be relatively inconvenient.

Embodiment 3

[0026] As a preference, on the basis of the above-mentioned embodiments, this embodiment is further optimized, the coupling includes a coupling input disk 2 and a coupling output disk 4, and the right end of the coupling input disk 2 It is fixedly connected with the output shaft, the left end is connected with the right end of the coupling output disk 4, and the left end of the coupling output disk 4 is connected with the transmission shaft. Since the coupling includes a coupling input disc 2 and a coupling output disc 4, the right end of the coupling input disc 2 is fixedly connected to the output shaft, and the left end is connected to the right end of the coupling output disc 4, The left end of the coupling output disc 4 is connected to the transmission shaft, and the power transmission is realized through the cooperation of the coupling input disc 2 and the coupling output disc 4. Concave-convex structures are provided on the opposite side of the disc 4 to realize stable t...

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Abstract

The invention relates to the field of aviation power systems, in particular to an unmanned aerial vehicle power device which is mainly applied to the field of unmanned aerial vehicles, and is small in size, light in weight and high in work reliability. A generating set and a reduction gearbox are successively arranged in the axis of an output direction of an output shaft of a turboshaft engine; a transmission shaft bearing block is arranged on the reduction gearbox; the left end of a transmission shaft and the inside of the reduction gear box are in transmission; the left end of the transmission shaft is matched with the transmission shaft bearing block through a bearing; the right end of the transmission shaft is in transmission fit with the output shaft; the generating set comprises a stator and a rotor; the stator is fixed on the right end surface of the transmission shaft bearing block; the transmission shaft freely penetrates through the stator; and the rotor sleeves the transmission shaft. According to the unmanned aerial vehicle power device, the turboshaft engine, the transmission shaft, the reduction gearbox, the stator, the rotor and the like are matched with one another, and electric power is output while power is provided for an unmanned aerial vehicle. The unmanned aerial vehicle power device has the characteristics of simple structure, light weight and small occupation space in a cabin, can simultaneously generate to drive an unmanned aerial vehicle rotor wing and onboard electrical equipment, and therefore is convenient to use.

Description

technical field [0001] The invention relates to the field of aviation power, in particular to an unmanned aerial vehicle power device with small volume, light weight and high working reliability, which is mainly used in the field of unmanned aerial vehicles. Background technique [0002] The commonly used power systems of unmanned helicopters can be divided into two categories: electric drive and fuel drive. [0003] The electric drive system is driven by batteries, with low output power and short battery life. The battery contained in the electric drive system occupies a large volume of the cabin and has a large structural weight. The heat is high, which brings safety risks to other equipment in the unmanned helicopter cabin. In addition, it needs to be pre-charged when using it, which is quite inconvenient. [0004] The fuel power system is mainly based on a piston-type aero-engine. The fuel burns and expands in the cylinder, drives the piston to reciprocate, and outputs...

Claims

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Application Information

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IPC IPC(8): B64D27/16B64D35/02
CPCB64D27/16B64D35/02
Inventor 田松
Owner 重庆星环航空科技有限公司