Ducted vertical lifting aircraft and liquid container device thereof

A liquid container and vertical lifting technology, which is applied in launching devices, aircraft parts, transportation and packaging, etc. It can solve the problems of aircraft control and maneuverability, impact on aircraft flight stability, and asymmetric overall weight distribution of aircraft.

Active Publication Date: 2017-05-24
千叶智能科技(深圳)有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the fluidity of the liquid will change the weight distribution of the aircraft and may affect the flight stability of the aircraft
[0006] During the flight, the concentration of the liquid weight distribution in the tilt direction will lead to asymmetrical weight distribution of the aircraft, and changes in the tilt angle and steering of the aircraft will also cause oscillations in the liquid, and these problems will lead to aircraft handling and maneuvering Performance suffers

Method used

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  • Ducted vertical lifting aircraft and liquid container device thereof
  • Ducted vertical lifting aircraft and liquid container device thereof
  • Ducted vertical lifting aircraft and liquid container device thereof

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Embodiment Construction

[0033] Figure 1 to Figure 3A perspective view of one embodiment of a ducted convertiplane according to the invention is shown. In this embodiment, the ducted vertical lift aircraft mainly includes: a driving device, a rotor 1 capable of rotating under the driving of the driving device, a smooth ring-shaped inner wall surrounded by several liquid container units 4 And coaxially surround the duct 2 of the rotor and the liquid weight distribution control device 10 . The number of these liquid container units 4 is eight here, and they together form the liquid container device 3 of the ducted convertiplane, and are in fluid communication with each other through the communication port (and the corresponding communication pipe). In addition to two communication ports connecting adjacent liquid container units 4 , each liquid container unit 4 also has a liquid inlet 5 , a liquid outlet 6 , and an air inlet 7 . The liquid inlet 5 of each liquid container unit 4 is merged into the si...

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Abstract

The invention relates to a ducted vertical lifting aircraft comprising a drive device, rotors which are capable of rotating under the drive of the drive device, a duct with a smooth-annular-structure inside wall and coaxially surrounding the rotors, a liquid container device coaxially surrounding the rotors and a liquid weight distribution control device. The liquid container device consists of a plurality of directly or indirectly connected liquid container units, wherein each of the liquid container unit is provided with a liquid inlet, a liquid outlet, an air inlet, communicating holes respectively used for communicating the adjacent liquid container units and control valves respectively arranged for the air inlet and the communicating holes. The liquid weight distribution control device is designed to be adapted to determine a real-time liquid weight distribution of the ducted vertical lifting aircraft based on sensor data, thereby generating a control signal for causing each of the control valves to operate so that the liquid can flow among the liquid container units, so as to adjust the liquid weight distribution of the ducted vertical lifting aircraft in real time.

Description

technical field [0001] The invention relates to a ducted vertical lift aircraft, in particular to a ducted vertical lift aircraft with a liquid container device. The invention also relates to a liquid container arrangement for said ducted convertiplane. Background technique [0002] Under the existing technology, ducted vertical lift aircraft has been available for many years, and it can achieve higher thrust output efficiency than open propellers through the circular barrier arranged around the propeller. Especially, because internal combustion engine power is not suitable for driving multi-blade aircraft, thus single-blade power is also the preferred aircraft form when internal combustion engine power is adopted, because the rapid start, stop and reverse rotation of each rotor of multi-blade aircraft can be performed within the motor's under control, but not with internal combustion engine power. [0003] Although it has been proved in theory and practice that the single...

Claims

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Application Information

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Patent Type & AuthorityApplications(China)
IPC IPC(8): B64D1/18B64D47/00
CPCB64D1/18B64D47/00
Inventor张凯帆
Owner千叶智能科技(深圳)有限公司