CN-122009550-A - Coaxial double-rotor-wing configuration water unmanned aerial vehicle and application method thereof

CN122009550ACN 122009550 ACN122009550 ACN 122009550ACN-122009550-A

Abstract

The invention belongs to the technical field of aircraft design and control, and relates to a coaxial double-rotor-wing configuration water unmanned aerial vehicle and a use method thereof. The floating assisting air bag comprises a power component and a mounting component, wherein the mounting component is structurally connected with the power component through bolts, electrification is achieved through an aviation connector, the outer side of the lower part of the power component is wrapped with an assisting floating air bag, and the assisting floating air bag is wrapped with a transverse ring layer and used for achieving stable water surface floating.

Inventors

Zhang Chuzhe
LIU CONG
CUI YUE
JIN TAO
LI HUI
PENG MIAO
WANG MINGZHEN

Assignees

中国特种飞行器研究所

Dates

Publication Date: 20260512
Application Date: 20260320

Claims (10)

1. The coaxial double-rotor-wing-shaped water unmanned aerial vehicle is characterized by comprising a power component and a mounting component, wherein the mounting component is connected with the power component through bolts, the power component is electrified through an aviation connector, the outer side of the lower part of the power component is wrapped with an auxiliary floating air bag, and the auxiliary floating air bag is wrapped by a transverse ring layer.
2. The coaxial dual rotor configuration unmanned aerial vehicle of claim 1, wherein the power components comprise an upper rotor, an upper rotary disk power motor, a lower rotor, a lower rotary disk power motor, a first steering engine, a power battery, a flight control system and a floating assisting system, The upper rotary disc type power motor output disc faces downwards, the lower rotary disc type power motor output disc faces upwards and respectively drives an upper rotary wing and a lower rotary wing to rotate in a coaxial reverse mode, the upper rotary wing and the lower rotary wing are fixed on a rotary wing clamping head, the rotary wing clamping head can be folded by 90 degrees, the rotary wing can be unfolded through centrifugal force during rotation, the first steering engine controls the upper rotary wing and the lower rotary wing to change torque through a ball head bolt and a ball head connecting rod, a power battery, a flight control system and a floating assisting system are located in a cabin, an aircraft joint is reserved at the watertight bottom end of the cabin and is electrified with a mounting part, the power battery is powered, the flight control system is used for flight control, and the floating assisting system controls automatic inflation of a floating assisting air bag.
3. The coaxial double-rotor configuration unmanned aerial vehicle of claim 1, wherein the floating assisting system comprises a second steering engine, a gas cylinder and an automatic deflation device, wherein the automatic deflation device is communicated with the air bag through an air tap, the automatic deflation device is connected with the second steering engine through a coupling, a port of the gas cylinder is in threaded connection with the side wall of the automatic deflation device, and the gas cylinder is controlled through the second steering engine.
4. The coaxial double-rotor configuration water unmanned aerial vehicle according to claim 1, wherein the automatic deflation device comprises a shell, an airtight outer cavity and an airtight inner cavity which are sequentially arranged from outside to inside, one end of the airtight inner cavity is connected with the second steering engine through a coupling, an airtight inner cavity air inlet hole is formed in the side wall of the airtight inner cavity, an airtight outer cavity air inlet is formed in the side wall of the airtight outer cavity, and the airtight outer cavity air inlet is a needle-shaped air inlet.
5. The coaxial dual rotor configuration unmanned aerial vehicle of claim 1, wherein the center of gravity is maintained below the center of buoyancy by the flotation air bag and cabin internal structure.
6. The coaxial dual rotor configuration water craft of claim 1, wherein the center of gravity position is adjusted by symmetrically arranging cabin interior components, filling buoyancy blocks, custom battery packs.
7. The coaxial dual rotor configuration unmanned aerial vehicle of claim 1, wherein the mounting form comprises an electro-optic pod, an underwater sensor.
8. The coaxial twin-rotor configuration unmanned aerial vehicle of claim 1, wherein the tasks of water quality detection, resource detection, underwater photography are performed by changing the task mount carried.
9. The coaxial dual rotor configuration water craft according to claim 1, wherein the coaxial dual rotor configuration water craft is stored or mounted in a barrel in the rotor folded condition supporting a hand-held jettisoning or barrel jettisoning.
10. A method of using a coaxial twin-rotor configuration water craft as claimed in any one of claims 1 to 9, comprising: When the air inlet of the airtight inner cavity is overlapped with the air inlet of the airtight outer cavity, CO 2 gas in the air bottle enters the airtight inner cavity and is released in a large quantity instantly through the air tap to inflate the floating assisting air bag; When the flying control end needs to do yaw flying, the flying control end sends out an instruction to enable the steering engine to generate a certain deflection angle at the same time, the steering engine drives the upper rotor wing and the lower rotor wing to change the total distance of the rotor wings through the ball stud and the ball connecting rod, and the tilting disc is tilted to realize periodic torque conversion, so that the course of the machine body is changed.

Description

Coaxial double-rotor-wing configuration water unmanned aerial vehicle and application method thereof Technical Field The invention belongs to the technical field of aircraft design and control, and relates to a coaxial double-rotor-wing configuration water unmanned aerial vehicle and a use method thereof. Background The unmanned aerial vehicle on water is an aircraft with amphibious capability and capable of executing tasks such as exploration and monitoring, tour and sightseeing, cargo transportation and the like. At present, domestic unmanned aerial vehicles on water are designed aiming at tasks on water, the development degree of the unmanned aerial vehicles on water is insufficient, and the unmanned aerial vehicles on water have the defects of low moving speed, large weight and difficult carrying and recycling. The traditional unmanned aerial vehicle on water makes the complete machine float in the surface of water through hull or flotation pontoon more, and the unrestrained ability is not enough, is difficult to accomplish the take-off and land on the wave sea, realizes the perpendicular take-off and land of surface of water through coaxial double rotor system and then can be fine solution this problem. The coaxial double-rotor-wing configuration unmanned aerial vehicle adopts a coaxial counter-rotor design, is compact in structure, is convenient to store and transport, is smaller than a multi-rotor-wing layout unmanned aerial vehicle with the radial size being smaller than the same level, is convenient to guarantee self-balance of a machine body due to the fact that the gravity center is located near a gravity center axis, is high in design, can provide a shielded working space for lower hanging equipment, and is suitable for being applied to finishing high-density accurate position maintenance tasks (such as inspection and fine detection) of an underwater environment. The blank of unmanned plane products applied underwater can be effectively filled. Disclosure of Invention The invention aims to: the coaxial double-rotor-wing configuration water unmanned aerial vehicle and the application method thereof are provided, and the water vertical take-off and landing, stable floating on the water surface and air flight are realized. The technical scheme is as follows: The coaxial double-rotor-wing-configuration water unmanned aerial vehicle comprises a power component and a mounting component, wherein the mounting component is structurally connected with the power component through bolts, electrification is realized through an aviation connector, the outer side of the lower part of the power component is wrapped with an auxiliary floating air bag, and the auxiliary floating air bag is wrapped with a transverse ring layer and used for realizing stable water surface floating. The power component comprises an upper rotor, an upper rotary disc type power motor, a lower rotor, a lower rotary disc type power motor, a first steering engine, a power battery, a flight control system and a floating assisting system, wherein the upper rotary disc type power motor and the lower rotary disc type power motor are arranged in an up-down mode, an output disc of the upper rotary disc type power motor faces downwards, an output disc of the lower rotary disc type power motor drives the upper rotor and the lower rotor to rotate in a coaxial counter-paddle mode, blades of the upper rotor and blades of the lower rotor are fixed on a rotor clamping head, the rotor clamping head can realize 90-degree turnover, rotor unfolding is realized through centrifugal force during rotation, the first steering engine controls the torque conversion of the upper rotor and the lower rotor through a ball stud and a ball connecting rod, the power battery, the flight control system and the floating assisting system are located in a cabin, an aviation connector is reserved at the bottom end of the cabin and is electrified with a mounting component, the power battery is used for supplying power to the power consumption component of the whole unmanned aerial vehicle, the flight control system is used for controlling the flight of the unmanned aerial vehicle, and the floating assisting system is used for controlling automatic inflation of a floating assisting air bag. The floating assisting system further comprises a second steering engine, a gas cylinder and an automatic air discharging device, wherein the automatic air discharging device is communicated with the air bag through an air tap, the automatic air discharging device is connected with the second steering engine through a coupler, a port of the gas cylinder is in threaded connection with the side wall of the automatic air discharging device, and the gas cylinder is controlled by the second steering engine to realize inflation of the air bag. The automatic deflation device comprises a shell, an air tap, an airtight inner cavity and an airtight outer cavity, wherein the shell, the airtight outer