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Driving device, driving method and low-to-medium altitude aircraft

A low-altitude aircraft and drive device technology, applied in the field of aircraft, can solve problems such as the inability to meet the market application requirements of agricultural plant protection drones, the difficulty of rapid popularization of drones, and the heavy weight of energy storage batteries. It achieves high flight control efficiency, Lightweight and compact effect

Active Publication Date: 2019-11-08
王子墨
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] 1) Energy storage batteries are generally heavy, which greatly increases the weight of the aircraft, which is not conducive to flight;
[0004] 2) The service life is short, the battery life is limited, and it is only used in short-distance occasions, and the battery life is short, which cannot meet the broad market application requirements of agricultural plant protection drones
[0005] 3) The price is high. The research found that for an agricultural plant protection drone worth about 100,000 yuan, the charging time needs about 1 hour, and the working time is only about 10 minutes. Frequent battery replacement or charging brings a lot of inconvenience to use and promotion. , making it difficult for UAVs to spread rapidly

Method used

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  • Driving device, driving method and low-to-medium altitude aircraft
  • Driving device, driving method and low-to-medium altitude aircraft
  • Driving device, driving method and low-to-medium altitude aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] Embodiment 1: as figure 1 Shown, a kind of low-altitude aircraft driving device, comprises high-pressure air source 1, air supply pipeline 5 and at least one thruster 4;

[0034] The propeller 4 includes a casing 11, a guide cylinder 12 arranged in the casing 11, and an annular slit 8. An annular cavity 13 is formed between the flow guide cylinder 12 and the casing 11, and the annular slit 8 connects the annular cavity 13 with the outside world. Communication; the gas coming out through the annular slit 13 is adsorbed on the inner wall of the draft tube 12 and becomes the Coanda airflow 9 . The high-pressure gas source communicates with the annular cavity through the gas supply pipeline.

[0035] The annular slit can be arranged anywhere in the annular cavity, and the thruster throat is the best. It can also be arranged at two places: one is located above the annular cavity, and the other is located below the annular cavity, of course, the driving effect is not very g...

Embodiment 2

[0036] Embodiment 2: In order to maximize the utilization of the induced airflow 6 , the annular slit 8 is arranged between the housing 11 and the guide tube 12 and above the annular cavity 13 . Such setting can increase the air pressure difference between the wall of the draft tube 12 and the center.

Embodiment 3

[0037] Example 3: The ratio of the width of the annular slit 8 to the center diameter of the guide cylinder 12 is 1:200. According to the diameter of the guide cylinder 12, the width of the annular slit 8 is generally set to 0.05-5.0mm, and the gas in the annular slit 8 The flow velocity is more than 15 times of the gas flow velocity at the inlet of the propeller. In this case, the pressure difference between the wall of the guide cylinder 12 and the center of the guide cylinder 12 is relatively large, and the driving effect is good.

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Abstract

The invention relates to a low-to-medium-altitude aircraft driving device, a driving method, and a low-to-medium-altitude aircraft, wherein the driving device includes a high-pressure air source, an air supply pipeline, and at least one propeller; A cylinder and an annular slit, an annular cavity is formed between the guide cylinder and the housing, and the annular slit communicates the annular cavity with the outside; the high-pressure gas source communicates with the annular cavity through an air supply pipeline. Most of the existing small aircraft use the energy storage battery as the power source. The energy storage battery has the technical problems of heavy weight, short service life and limited cruising distance. The invention uses compressed air to drive, and under the action of the Coanda effect, forms The high-speed downward jet stream forms relative negative pressure areas and positive pressure areas above and below the aircraft, providing lift and propulsion for the aircraft.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a driving device and a driving method for low-to-medium altitude aircraft. Background technique [0002] At present, in the mainstream propulsion technology of commercial aircraft, larger aircraft are powered by fuel oil; only micro aircraft such as small unmanned aerial vehicles can use energy storage batteries to provide power for propellers, which can reduce the consumption of fossil fuels to a certain extent. Direct dependence, reducing exhaust emissions. Although energy storage batteries can provide power for propellers, energy storage batteries still have the following problems, which restrict the popularization of small UAVs: [0003] 1) Energy storage batteries are generally heavy, which greatly increases the weight of the aircraft, which is not conducive to flight; [0004] 2) The service life is short, the battery life is limited, and it is only used in short-distanc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D27/20B64C15/02
CPCB64C15/02B64D27/20B64U50/00
Inventor 王子墨
Owner 王子墨
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