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A low-altitude flight-altitude control system for soft-wing unmanned aerial vehicles

A low-altitude flight, control system technology, applied in aircraft parts, aircraft power units, transportation and packaging, etc., can solve problems such as complex control system structure

Active Publication Date: 2018-02-09
XIANGYANG HONGWEI AIRCRAFT
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Its control system has a complex structure and is suitable for fixed-wing UAV altitude control, but not for soft-wing UAV low-altitude altitude control.

Method used

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  • A low-altitude flight-altitude control system for soft-wing unmanned aerial vehicles
  • A low-altitude flight-altitude control system for soft-wing unmanned aerial vehicles
  • A low-altitude flight-altitude control system for soft-wing unmanned aerial vehicles

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Embodiment Construction

[0028] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not constitute a conflict with each other.

[0029] figure 1 It is a structural schematic diagram of the altitude determination control system of the soft-wing unmanned aerial vehicle in the embodiment of the present invention. As can be seen from the figure, a kind of soft-wing unmanned aerial vehicle low-altitude flight altitude determination control system of the present invention includes a stamping parafoil 1, a power unit 9, Main co...

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Abstract

The invention discloses a low-altitude flight fixed-height control system for a soft-wing unmanned plane and belongs to the field of soft-wing unmanned plane flight. The system comprises a ram parafoil, a power unit, a master control processor, height measurement equipment and a throttle adjusting unit, the ram parafoil is arranged at the top of a cabin of the soft-wing unmanned plane, the height measurement equipment is used for measuring the actual altitude of the soft-wing unmanned plane, the power unit comprises an engine and a propeller connected with the engine, the propeller is arranged at the tail of the cabin, the throttle adjusting unit is connected with the engine of the power unit so that the amount of fuel oil input into the engine can be adjusted, and the master control processor is arranged in the cabin and electrically connected with the throttle adjusting unit and the height measurement equipment at the same time so that the throttle adjusting unit can be controlled, the amount of fuel oil input into the engine can be further adjusted and the actual altitude of the soft-wing unmanned plane can be acquired from the height measurement equipment. By means of the control system, fixed-height flight of the soft-wing unmanned plane can be controlled accurately.

Description

technical field [0001] The invention belongs to the field of altitude determination control for soft-wing unmanned aerial vehicles, and more particularly relates to a low-altitude flight altitude determination control system for soft-wing unmanned aerial vehicles. Background technique [0002] At present, drones are used in more and more fields, such as aerial photography, agricultural sowing, emergency communications and material airdrops. However, due to the single function of existing UAVs, many applications are greatly restricted, especially those with strict restrictions on flight height, ground condition perception and location requirements. [0003] In terms of the means of flight altitude measurement, the current commonly used method mainly uses GPS navigation or barometric altimeter to obtain the distance of the unmanned aerial vehicle by obtaining the absolute altitude and the altitude of the aircraft latitude and longitude position on the map. ground height. Alt...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D31/06
CPCB64D31/06
Inventor 薛富利郭海军徐杰龚松洁李晨晨
Owner XIANGYANG HONGWEI AIRCRAFT
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