CN110341950A - A kind of multi-rotor unmanned aerial vehicle having gliding function - Google Patents
A kind of multi-rotor unmanned aerial vehicle having gliding function Download PDFInfo
- Publication number
- CN110341950A CN110341950A CN201910520228.6A CN201910520228A CN110341950A CN 110341950 A CN110341950 A CN 110341950A CN 201910520228 A CN201910520228 A CN 201910520228A CN 110341950 A CN110341950 A CN 110341950A
- Authority
- CN
- China
- Prior art keywords
- control system
- flight control
- unmanned plane
- motor
- aerial vehicle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The invention discloses a kind of multi-rotor unmanned aerial vehicles for having gliding function.The present invention includes multi-rotor unmanned aerial vehicle batswing tab body and power plant module, and multi-rotor unmanned aerial vehicle batswing tab body includes flight control system, gyroscope, power supply, batswing tab shell；Main control chip and various kinds of sensors needed for flight control system carries unmanned plane during flying, for controlling the flight of entire unmanned plane；Gyroscope is connect with flight control system, and flight control system obtains the real-time flight posture of unmanned plane by gyroscope；Power supply is powered to entire unmanned plane, is connected to flight control system, and Real-time Feedback electricity is to flight control system；Batswing tab shell be on the rack increased one removably with the shell of batswing tab；Power plant module includes holder, motor, propeller；Propeller is connected to motor, and motor is mounted on holder, and holder is fixed on rack bar and is connected to flight control system；The holder is used for rotary electric machine, controls the angle between motor and unmanned rack.The present invention enhances the flexibility ratio of multi-rotor unmanned aerial vehicle flight.
Description
Technical field
The present invention relates to unmanned planes, particularly with the addition of the multi-rotor unmanned aerial vehicle of auxiliary wing and adjustable motor
Background technique
Multi-rotor unmanned aerial vehicle is a kind of new concept weapon equipment being in rapid development, with maneuverability, reaction
Quickly, unmanned flight, operation require low advantage.Unmanned plane by carry multiclass sensor, may be implemented image real-time Transmission,
High-risk areas detecting function, be satellite remote sensing and traditional air remote sensing strong supplement.Currently, the use scope of unmanned plane is
Military affairs, scientific research, civilian three big field are widened, specifically in fields such as electric power, communication, meteorology, agricultural, ocean, explorations using very
Extensively.The rotor structure of multiaxis unmanned plane is fairly simple, does not need the trimming movement structure of system helicopter complexity, it is only necessary to controller
The revolving speed of rotor can achieve the purpose that control posture.
Multi-rotor unmanned aerial vehicle can not utilize air fluid lift force in cruise, but completely by by the spiral shell on fixed motor
It revolves paddle and lift and forward thrust is provided, this kind of single power mode makes multi-rotor unmanned aerial vehicle energy consumption mistake in cruise
Greatly, lead to that the type unmanned plane cruise time is all very short and mobility is not strong, flexibility is low.The type unmanned plane belongs to low latitude and flies
Row, the flight noise that propeller generates will lead to when certain quiet scenic spots carry out unmanned plane shooting, can meet with periphery trip
The intervention of visitor and administrative staff, significantly impact the use scope and the frequency of unmanned plane.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of multi-rotor unmanned aerial vehicles for having gliding function, solve existing
The problem that the multi-rotor unmanned aerial vehicle cruise time is short, flexibility is low and flight noise is big, batswing tab airframe systems and adjustable motor
It is versatile, it is suitble to all multi-rotor unmanned aerial vehicles to install and use.
In order to solve the above technical problems, the technical scheme is that
A kind of multi-rotor unmanned aerial vehicle having gliding function, including multi-rotor unmanned aerial vehicle batswing tab body and power plant module；
The multi-rotor unmanned aerial vehicle batswing tab body includes flight control system, gyroscope, power supply, batswing tab shell；Described
Main control chip and various kinds of sensors needed for flight control system carries unmanned plane during flying, for controlling the flight of entire unmanned plane；Institute
The gyroscope stated is connect with flight control system, and flight control system obtains the real-time flight posture of unmanned plane by gyroscope；The electricity
Source powers to entire unmanned plane, is connected to flight control system, and Real-time Feedback electricity is to flight control system；The batswing tab shell is
Increased one removably with the shell of batswing tab on the rack；
The power plant module includes holder, motor, propeller；Propeller is connected to motor, and motor is mounted on holder,
Holder is fixed on rack bar and is connected to flight control system；The holder is used for rotary electric machine, and control motor rotation is adjusted.
Under the control of flight control system, holder can adjust the angle between motor and rack, and propeller is mentioned
For the power of unmanned plane multi-angle, unmanned plane more flexible can be flown.
Each unmanned plane includes four power plant modules, specifically includes four holders and four motors.
When flight control system sends control signals to corresponding holder, the rotation of the holder drives corresponding motor adjustment
With the angle between unmanned aerial vehicle rack bar；Motor can not rotate or slowly run according to the control of flight control system, so that nothing
It is man-machine that gliding state is under the control of flight control system.
The beneficial effect of the invention compared with the existing technology is:
The motor unmanned plane shell with batswing tab and be adjusted by rotation, in cruise, to machine when air passes through wing
The lift that the wing generates, can undertake the most weight of unmanned plane itself, so that unmanned aerial vehicle body itself will be held up by reducing propeller
The consumption of weight makes unmanned plane unpowered gliding or low-power gliding in the gas flow, reduces the noise that propeller generates, extend continuous
ETS estimated time of sailing.The angle of the change motor being adjusted by rotation and rack, the flexibility ratio of enhancing multi-rotor unmanned aerial vehicle flight can be passed through.
Detailed description of the invention
Fig. 1 unmanned plane overall profile top view
Fig. 2 unmanned plane gliding side view
Fig. 3 unmanned plane modules connection schematic diagram
Fig. 4 unmanned plane modules block diagram
Specific embodiment
The invention is further explained in the following combination with the attached drawings of the specification.
A kind of multi-rotor unmanned aerial vehicle having gliding function, including multi-rotor unmanned aerial vehicle batswing tab body and power plant module
As shown in Figure 1, the multi-rotor unmanned aerial vehicle batswing tab body can make unmanned plane in cruise, air passes through wing
When to wing generate lift, the most weight of unmanned plane itself can be undertaken, so that unmanned plane machine will be held up by reducing propeller
The consumption of body own wt extends cruise duration.Unmanned plane can also rely on the lift unpowered gliding or low-power in the gas flow
Gliding reduces the noise that propeller generates.
The power plant module includes propeller, motor and holder as shown in Figure 2, and propeller is connected to motor, with electricity
The rotation of machine and rotate, motor is mounted on holder, and holder is connected to flight control system, and under the control of flight control system, holder can
To adjust the angle between motor and rack, so that propeller is capable of providing the power of unmanned plane multi-angle, allow unmanned plane can
More flexible flight.
Flight control system as shown in Figure 2 sends control signals to holder, makes the holder back rotation 45 of motor 3 and motor 4
The holder of degree, motor 1 and motor 2 does not rotate, and 45 degree of motors 3 of back rotation and motor 4 can provide unmanned plane horizontal direction and hang down
Histogram to power, motor 1 and motor 2 can not rotate or slowly run according to the control of flight control system, and unmanned plane is in flight control system
Control under be in gliding state；
As shown in figure 3, a kind of multi-rotor unmanned aerial vehicle for having gliding function, including multi-rotor unmanned aerial vehicle batswing tab body and
Power plant module, the multi-rotor unmanned aerial vehicle batswing tab body include flight control system, gyroscope, power supply, batswing tab shell.Described
Main control chip and various kinds of sensors needed for flight control system carries unmanned plane during flying for controlling the flight of entire unmanned plane be
The Central Control Center of entire unmanned plane, in the shell of the flight control system batswing tab, the gyroscope is connect with flight control system,
Flight control system obtains the real-time flight posture of unmanned plane by gyroscope, and the power supply is powered to entire unmanned plane, is connected to
Flight control system, and Real-time Feedback electricity, to flight control system, the batswing tab shell is to increase one on the rack detachably
The shell with batswing tab；
The holder and motor of four power plant modules as shown in Figure 4 are connected to flight control system, the transmittable control letter of flight control system
Number control holder and motor, holder adjust the angle between motor and rack according to the instruction of flight control system, and motor is according to flying to control
The instruction of system adjusts revolving speed.Gyroscope is connected to flight control system, and flight control system obtains the real-time of unmanned plane by gyroscope and flies
Row posture, to control entire unmanned plane during flying.Power module connects flight control system, is the power supply source of entire unmanned plane, and real
It applies and sends electricity to the flight control system of unmanned plane, flight control system makes corresponding decision according to electricity.
Claims (4)
1. a kind of multi-rotor unmanned aerial vehicle for having gliding function, it is characterised in that including multi-rotor unmanned aerial vehicle batswing tab body and move
Power module；
The multi-rotor unmanned aerial vehicle batswing tab body includes flight control system, gyroscope, power supply, batswing tab shell；The winged control
Main control chip and various kinds of sensors needed for system carries unmanned plane during flying, for controlling the flight of entire unmanned plane；Described
Gyroscope is connect with flight control system, and flight control system obtains the real-time flight posture of unmanned plane by gyroscope；The power supply is given
Entire unmanned plane power supply, is connected to flight control system, and Real-time Feedback electricity is to flight control system；The batswing tab shell is in machine
On frame increased one removably with the shell of batswing tab；
The power plant module includes holder, motor, propeller；Propeller is connected to motor, and motor is mounted on holder, holder
It is fixed on rack bar and is connected to flight control system；The holder is used for rotary electric machine, and control motor rotation is adjusted.
2. a kind of multi-rotor unmanned aerial vehicle for having gliding function according to claim 1, it is characterised in that in flight control system
Control under, holder can adjust the angle between motor and rack, so that propeller is capable of providing the dynamic of unmanned plane multi-angle
Unmanned plane more flexible can be flown for power.
3. a kind of multi-rotor unmanned aerial vehicle for having gliding function according to claim 2, it is characterised in that each unmanned plane
It specifically include four holders and four motors including four power plant modules.
4. a kind of multi-rotor unmanned aerial vehicle for having gliding function according to claim 2 or 3, it is characterised in that be when flying control
When system sends control signals to corresponding holder, the rotation of the holder is driven between corresponding motor adjustment and unmanned aerial vehicle rack
Angle；Motor can not rotate or slowly run according to the control of flight control system, so that control of the unmanned plane in flight control system
System is lower to be in gliding state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910520228.6A CN110341950A (en) | 2019-06-17 | 2019-06-17 | A kind of multi-rotor unmanned aerial vehicle having gliding function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910520228.6A CN110341950A (en) | 2019-06-17 | 2019-06-17 | A kind of multi-rotor unmanned aerial vehicle having gliding function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110341950A true CN110341950A (en) | 2019-10-18 |
Family
ID=68182122
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910520228.6A Pending CN110341950A (en) | 2019-06-17 | 2019-06-17 | A kind of multi-rotor unmanned aerial vehicle having gliding function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110341950A (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101830283A (en) * | 2010-05-28 | 2010-09-15 | 东北大学 | Raised wing for flapping wing air vehicle |
| US20180072414A1 (en) * | 2016-09-09 | 2018-03-15 | Wal-Mart Stores, Inc. | Apparatus and method for unmanned flight |
-
2019
- 2019-06-17 CN CN201910520228.6A patent/CN110341950A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101830283A (en) * | 2010-05-28 | 2010-09-15 | 东北大学 | Raised wing for flapping wing air vehicle |
| US20180072414A1 (en) * | 2016-09-09 | 2018-03-15 | Wal-Mart Stores, Inc. | Apparatus and method for unmanned flight |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109896008B (en) | Self-adaptive water-air amphibious unmanned aerial vehicle adopting rotor wing tilting mechanism | |
| CN106004287B (en) | Amphibious multifunctional vertical landing aircraft | |
| CN202080435U (en) | Ranked dual-rotor vertically-lifted unmanned aerial vehicle (UAV) | |
| CN104859851A (en) | Multi-rotor aircraft driven by duct lift fans with diversion helms | |
| CN105204514A (en) | Novel tilt-rotor unmanned aerial vehicle attitude control system | |
| CN110001953A (en) | A kind of aerofoil profile unmanned plane and its flight control method | |
| US20120298789A1 (en) | Aircraft | |
| CN204223181U (en) | A kind of combined type vertically taking off and landing flyer | |
| CN112722273B (en) | Gravity center adjustable composite propulsion unmanned aerial vehicle and control method thereof | |
| CN109606674A (en) | Tail sitting posture vertical take-off and landing drone and its control system and control method | |
| CN104477381A (en) | Double-variable-pitch-propeller aircraft | |
| WO2016058502A1 (en) | Tail-sitter aircraft | |
| WO2021201927A2 (en) | High-speed, vertical take-off and landing aircraft | |
| WO2019109215A1 (en) | Power device, unmanned aerial vehicle, and flight control method | |
| CN108583867B (en) | Torque self-balancing three-duct fan bionic aircraft | |
| CN214824104U (en) | Unmanned aerial vehicle | |
| CN210526849U (en) | Fixed wing unmanned aerial vehicle of tilting-rotating force | |
| CN110341950A (en) | A kind of multi-rotor unmanned aerial vehicle having gliding function | |
| CN114379777B (en) | Tilting rotor unmanned aerial vehicle structure and working method thereof | |
| CN115771364A (en) | Water-air amphibious vector multi-rotor aircraft based on synchronous belt transmission structure and control method | |
| CN216269839U (en) | Novel underwater glider | |
| CN210822753U (en) | Single-oar plant protection unmanned aerial vehicle with flight attitude controlled by control surface | |
| CN214930610U (en) | Unmanned aerial vehicle capable of sailing on water | |
| CN104229130A (en) | Four-rotor wing unmanned aerial vehicle with pneumatic structure | |
| CN211336424U (en) | Six rotors spray unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191018 |
|
| RJ01 | Rejection of invention patent application after publication |