CN206537510U - A kind of lifting gear of aircraft - Google Patents
A kind of lifting gear of aircraft Download PDFInfo
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- CN206537510U CN206537510U CN201720227398.1U CN201720227398U CN206537510U CN 206537510 U CN206537510 U CN 206537510U CN 201720227398 U CN201720227398 U CN 201720227398U CN 206537510 U CN206537510 U CN 206537510U
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- fixed wing
- wing aircraft
- rotor
- connecting rod
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Abstract
The landing mode and its device of a kind of aircraft, belong to technical field of aerospace, more particularly to a kind of fixed wing aircraft landing mode and its device.Lifting gear includes fixed wing aircraft, many gyroplanes and many gyroplane parking platforms；There are GPS navigation device, inertial sensor, infrarede emitting diode, communication module and connection end on fixed wing aircraft；Connection end includes bayonet unit；Many gyroplanes include flight-control computer, many rotor inertial sensors, thermal infrared imager, many rotor GPS navigation devices, many rotor communication modules, connecting rod and connecting rod vertical means；Connecting rod includes connecting-rod cap.Multi-rotor aerocraft is separated after hanging drawing fixed wing aircraft lift-off, realizes taking off for fixed wing aircraft；Multi-rotor aerocraft is flown to be combined with fixed wing aircraft in the air, hangs the landing for drawing fixed wing aircraft.The utility model can allow multi-rotor aerocraft and fixed wing aircraft to realize that aerial and ground is docked, and solving traditional fixed wing aircraft can not take off vertically and the problem of vertical landing.
Description
Technical field
A kind of lifting gear of aircraft, belongs to technical field of aerospace.Specifically related to takeoff and landing device.
Background technology
Fixed Wing AirVehicle and multi-rotor aerocraft suffer from respective advantage and disadvantage；Fixed Wing AirVehicle flight course is pacified
Entirely, flying speed is fast, remote voyage and the characteristics of big carrying capacity, but landing process is required for using runway and can not hanged in the air
Stop；The VTOL of multi-rotor aerocraft energy, simple technology, maneuverability, simple to operate and flight vibrations are small, but cruising time is short
It is low with security；Although also there is the aircraft that some combine fixed-wing and many rotors at present, such as CW-20 rocs,
It is simply strong that two combine using respective advantage, many rotor modes are used during landing, using solid during high-performance cruise
Determine wing pattern, but this also increases the burden of aircraft, reduce flying quality.
The content of the invention
The purpose of the present invention is the above-mentioned deficiency for overcoming traditional fixed wing aircraft, and the present invention is excellent using multi-rotor aerocraft
Point, allows multi-rotor aerocraft and fixed wing aircraft to realize the docking of aerial and ground, solving traditional fixed wing aircraft can not be vertical
The problem of takeoff and landing.
A kind of lifting gear of aircraft, including fixed wing aircraft, multi-rotor aerocraft and multi-rotor aerocraft parking platform；Institute
Stating fixed wing aircraft includes fuselage, undercarriage, GPS navigation device, inertial sensor, infrared illuminator, communication module and connection
End；The undercarriage can take in fuselage below belly, can be used when fixed wing aircraft lands；The GPS navigation
Device is the alignment system of fixed wing aircraft；The inertial sensor has the acceleration for measuring fixed wing aircraft, gradient, shaken
The function of the information such as dynamic and switch, positioned at fuselage interior；The infrared illuminator is located at the side of connection end, infrared for sending
Optical signal；The communication module is the device that fixed wing aircraft is connected with external information；The connection end be fixed wing aircraft with
The device of multi-rotor aerocraft connection, the plumb line for being located across fixed wing aircraft center of gravity is placed in fuselage roof, can be in many rotors
Aircraft pull-up fixed wing aircraft makes multi-rotor aerocraft and fixed wing aircraft relative equilibrium when hovering；The connection end includes card
Buckle device, the bayonet unit is located at the inside of connection end, for locking connecting-rod cap.The multi-rotor aerocraft includes flight
Control computer, many rotor inertial sensors, thermal infrared imager, many rotor GPS navigation devices, many rotor communication modules, connection
Bar and connecting rod vertical means；The flight-control computer is the control centre of multi-rotor aerocraft, including at image recognition
Reason system and temperature identification processing system, flight-control computer can handle temperature data and the conversion that thermal infrared imager is collected
Into temperature reading and image, thermal infrared imager, many rotor inertial sensors, many rotor GPS navigation devices and many rotations are connected respectively
Wing communication module；The thermal infrared imager is located at the latter half of connecting rod, horizontal range of thermal infrared imager to connecting rod etc.
In the horizontal range of infrared illuminator to connection end, it can receive and converge the infra-red radiation of testee transmitting and be converted into telecommunications
Flight-control computer formation temperature information and image information number are sent to, the position of infrared illuminator is caught for recognizing；Institute
Stating many rotor inertial sensors has the function of the information such as acceleration, gradient, vibration and the switch of measurement multi-rotor aerocraft,
Positioned at multi-rotor aerocraft fuselage interior；Many rotor GPS navigation devices are the alignment systems of multi-rotor aerocraft；It is described many
Rotor communication module is the device that multi-rotor aerocraft is connected with external information；The connecting rod is multi-rotor aerocraft and fixation
It is vertical with multi-rotor aerocraft on the device of wing aircraft connection, the vertical curve for being located at the center of multi-rotor aerocraft；The company
Extension bar includes connecting-rod cap, and connecting-rod cap is the position that multi-rotor aerocraft is connected with fixed wing aircraft, under connecting rod
End；It is vertical state that the connecting rod vertical means, which can allow connecting rod to remain, the both sides positioned at the top of connecting rod, and many
Rotor craft is connected, and the position being connected with multi-rotor aerocraft, which has, block baffle plate in the middle of 20 degree to 30 degree of breach, breach, make
Connecting rod vertical means energy switch angle is no more than 10 degree.The multi-rotor aerocraft parking platform is that multi-rotor aerocraft is parked
Platform.
The connection end is in funnel shaped.
The connecting-rod cap is tapered, there is two grooves.
When fixed wing aircraft needs to take off, multi-rotor aerocraft, many rotor flyings are signaled to by communication module
Device receives signal by many rotor communication modules, while receiving the GPS navigation positional information of fixed wing aircraft, many rotors fly
Row device, which takes off, to be flown to above fixed wing aircraft, the information Real-Time Sharing of inertial sensor and many rotor inertial sensors, while red
Outer thermal imaging system catches the position of infrared illuminator, and flight-control computer is determined between fixed wing aircraft and multi-rotor aerocraft
Position relationship, when there is position directly below in the picture in infrared illuminator, connecting-rod cap and connection end alignment, flight control
Computer controls multi-rotor aerocraft calibrating position, slowly declines, connecting-rod cap is entered connection end, and then bayonet unit enters
The groove location of connection end, multi-rotor aerocraft, which is hung, after the connection between multi-rotor aerocraft and fixed wing aircraft is pinned hauls
Fixed wing aircraft takes off, when flying to certain altitude, when flying to certain altitude, and the dynamical system of fixed wing aircraft starts, many rotors
Aircraft is accelerated forwardly, when fixed wing aircraft speed reaches takeoff speed, and bayonet unit unclamps, and connecting-rod cap and connection end are de-
From multi-rotor aerocraft flies upwards, and fixed wing aircraft independently flies, and multi-rotor aerocraft is fixed by many rotor GPS navigation devices
The origin information of position returns to alone multi-rotor aerocraft parking platform.
When fixed wing aircraft needs landing, multi-rotor aerocraft, many rotor flyings are signaled to by communication module
Device is taken off, while receiving GPS navigation positional information, route information and the velocity information of fixed wing aircraft, flight control is calculated
Machine calculates the course line of fixed wing aircraft, is drawn close to fixed wing aircraft.When also having certain distance with fixed wing aircraft, many rotors
Aircraft direction of advance is made a U-turn, and course is gone to fixed wing aircraft heading, and fixed wing aircraft is horizontal flight
's.When multi-rotor aerocraft and relatively close fixed wing aircraft position, multi-rotor aerocraft is filled by the GPS navigation received
Put shared information to determine the positional information of fixed wing aircraft and fly to the front overhead of fixed wing aircraft, and carry out in front docking
Prepare.When fixed wing aircraft and multi-rotor aerocraft are relativelyed close to, pass through GPS navigation device and many rotor GPS navigation devices
Gps signal carry out height coarse alignment, then inertial sensor and many rotor inertial sensors information Real-Time Sharing, simultaneously
Thermal infrared imager catches the position of infrared illuminator, and flight-control computer is filled according to GPS navigation device, many rotor GPS navigations
Put, inertial sensor, many rotor inertial sensors provide information and thermal infrared imager catch the position to infrared illuminator
Confidence breath is calculated after the spatial relation between fixed wing aircraft and multi-rotor aerocraft, and flight-control computer control is more
The flight attitude and speed of rotor craft, when there is position directly below in the picture in infrared illuminator pipe, connecting rod
Head and connection end alignment, fixed wing aircraft and multi-rotor aerocraft geo-stationary flew after a period of time, flight-control computer
Control multi-rotor aerocraft slowly declines, and connecting-rod cap is entered connection end.After connecting-rod cap insertion connection end, bayonet unit
Groove location into connecting-rod cap pins connecting-rod cap, and then flame-out open simultaneously of the dynamical system of fixed wing aircraft is risen and fallen
Frame, multi-rotor aerocraft slowly slows down with fixed wing aircraft behind the landing place flown to and specified, and bayonet unit unclamps, connection end
Separated with connecting-rod cap, multi-rotor aerocraft returns to alone multi-rotor aerocraft parking platform.
The present invention can utilize the VTOL of multi-rotor aerocraft energy and flexible advantage, allow fixed wing aircraft to be revolved with more
Rotor aircraft realizes that aerial and ground is docked, and solving traditional fixed wing aircraft can not take off vertically and the problem of vertical landing,
And the process accelerated can be completed in the air, and the construction of runway, has greatly saved resource needed for reducing fixed wing aircraft, has
Beneficial to the popularization of fixed wing aircraft.
Brief description of the drawings
Fig. 1 is multi-rotor aerocraft structural representation；Fig. 2 is the structural representation of connection end and connecting rod；Fig. 3 is fixed
The docking schematic diagram of wing aircraft and multi-rotor aerocraft；Fig. 4 is the structural representation of multi-rotor aerocraft parking platform；Fig. 5 is to connect
The cross section structure schematic diagram of extension bar vertical means and multi-rotor aerocraft connecting portion.
In figure, 1- flight-control computers, 2- connecting rod vertical means, many rotor communication modules of 3-, 4- connecting rods, 5- is more
Rotor GPS navigation device, many rotor inertial sensors of 6-, 7- multi-rotor aerocrafts, 9- connecting-rod caps, 10- grooves, 11- is infrared
Thermal imaging system, 12- multi-rotor aerocraft parking platforms, 13- bayonet units, 14- connection ends, 15- infrared illuminators, 16- fuselages, 17-
Undercarriage, 18- inertial sensors, 19-GPS guiders, 20- communication modules, 21- fixed wing aircrafts, 60- breach, 70- gears
Plate.
Embodiment
The present invention is illustrated below in conjunction with the accompanying drawings：A kind of lifting gear of fixed wing aircraft, including fixed-wing fly
Machine 21, multi-rotor aerocraft 7 and multi-rotor aerocraft parking platform 12；Fixed wing aircraft 21 includes fuselage 16, undercarriage 17, GPS
Guider 19, inertial sensor 18, infrared illuminator 15, communication module 20 and connection end 14；Undercarriage 17 is in the abdomen of fuselage 16
Below portion, fuselage 16 can be taken in, can be used when fixed wing aircraft 21 lands；GPS navigation device 19 is fixed wing aircraft 21
Alignment system；Inertial sensor 18 has the information such as acceleration, gradient, vibration and the switch of measurement fixed wing aircraft 21
Function, inside fuselage 16；Infrared illuminator 15 is located at the side of connection end 14, for sending infrared signal；Communicate mould
Block 20 is the device that fixed wing aircraft 21 is connected with external information；Connection end 14 is fixed wing aircraft 21 and multi-rotor aerocraft 7
The device of connection, in funnel shaped, is located across on the center of gravity plumb line of fixed wing aircraft 21 and is placed in the top of fuselage 16, can be many
It is multi-rotor aerocraft 7 and the relative equilibrium of fixed wing aircraft 21 that rotor craft 7, which is hauled when fixed wing aircraft 21 hovers,；Connection end
14 include bayonet unit 13, and bayonet unit 13 is in the inside of connection end 14, for locking connecting-rod cap 9.Multi-rotor aerocraft 7 is wrapped
Flight-control computer 1, many rotor inertial sensors 6, thermal infrared imager 11, many rotor GPS navigation devices 5, many rotors is included to lead to
Believe module 3, connecting rod 4 and connecting rod vertical means 2；Flight-control computer 1 is the control centre of multi-rotor aerocraft 7, bag
Image recognition processing system and temperature identification processing system are included, flight-control computer 1 can handle what thermal infrared imager was collected
Temperature data is simultaneously converted into temperature reading and image, and thermal infrared imager 11, many rotor inertial sensors 6, many rotors are connected respectively
GPS navigation device 5 and many rotor communication modules 3；The thermal infrared imager 11 is located at the latter half of connecting rod 4, infrared thermal imagery
Instrument 11 is equal to the horizontal range that infrared illuminator 15 arrives connection end 14 to the horizontal range of connecting rod 4, can receive and converge and be tested
The infra-red radiation of object emission is simultaneously converted into electric signal and is sent to the formation temperature information and image information of flight-control computer 1,
Positioned at the latter half of connecting rod 4, the position of infrared illuminator 15 is caught for recognizing；Many rotor inertial sensors 6 have
There is the function of the information such as acceleration, gradient, vibration and the switch of measurement multi-rotor aerocraft 7, positioned at the machine of multi-rotor aerocraft 7
Inside body；Many rotor GPS navigation devices 5 are the alignment systems of multi-rotor aerocraft 7；Many rotor communication modules 3 are
The device that multi-rotor aerocraft 7 is connected with external information；The connecting rod 4 is that multi-rotor aerocraft 7 connects with fixed wing aircraft 21
The device connect, it is vertical with multi-rotor aerocraft 7 positioned at the center of multi-rotor aerocraft 7；Connecting rod 4 includes connecting-rod cap 9, even
Extension bar first 9 is the position that multi-rotor aerocraft 7 is connected with fixed wing aircraft 21, positioned at the lower end of connecting rod 4, there is two grooves
10, it is tapered；The connecting rod vertical means 2 can allow connecting rod 4 to remain perpendicular to the ground, positioned at the top of connecting rod 4
Both sides, are connected with multi-rotor aerocraft 7, and there are 20 degree to 30 degree of breach 60, breach 60 in the position being connected with multi-rotor aerocraft 7
There is block baffle plate 70 centre, the switch angle of connecting rod vertical means 2 is no more than 10 degree；The multi-rotor aerocraft parking platform 12
It is the platform that multi-rotor aerocraft 7 is parked.
When fixed wing aircraft 21 needs to take off, multi-rotor aerocraft 7, many rotors are signaled to by communication module 20
Aircraft 7 receives signal by many rotor communication modules 3, while the GPS navigation positional information of fixed wing aircraft 21 is received,
Multi-rotor aerocraft 7, which takes off, flies to the top of fixed wing aircraft 21, and the information of inertial sensor 18 and many rotor inertial sensors 6 is real
When it is shared, while thermal infrared imager 11 catches the position of infrared illuminator 15, flight-control computer 1 determines fixed wing aircraft 21
With the position relationship between multi-rotor aerocraft 7, when position directly below in the picture occurs in infrared illuminator 15, connecting rod
First 9 and connection end 14 align, flight-control computer 1 control the calibrating position of multi-rotor aerocraft 7, slowly decline, make connecting rod
First 9 enter connection end 14, and then bayonet unit 13 enters the position of groove 10 of connection end, and multi-rotor aerocraft 7 flies with fixed-wing
Multi-rotor aerocraft 7 drives fixed wing aircraft 21 to take off after connection between machine 21 is pinned, when flying to certain altitude, fixed-wing
The dynamical system of aircraft 21 starts, and multi-rotor aerocraft 7 is accelerated forwardly, when the speed of fixed wing aircraft 21 reaches takeoff speed,
Bayonet unit 13 unclamps, and multi-rotor aerocraft 7 flies upwards, and connecting-rod cap 9 and connection end 14 depart from, and fixed wing aircraft 21 is independent to fly
OK, the origin information that multi-rotor aerocraft 7 is positioned by many rotor GPS navigation devices 5 returns to alone many rotor parking platforms 12.
When fixed wing aircraft 21 needs landing, multi-rotor aerocraft 7, many rotors are signaled to by communication module 20
Aircraft 7 takes off, while GPS navigation positional information, route information and the velocity information of fixed wing aircraft 21 are received, flight control
Computer 1 processed calculates the course line of fixed wing aircraft 21, is drawn close to fixed wing aircraft 21.It is certain also having with fixed wing aircraft 21
Apart from when, the direction of advance of multi-rotor aerocraft 7 is made a U-turn, and course is gone to the heading of fixed wing aircraft 21, fixed-wing
Aircraft 21 is horizontal flight.When multi-rotor aerocraft 7 and the relatively close position of fixed wing aircraft 21, multi-rotor aerocraft 7
Information is shared by the GPS navigation device 19 received to determine the positional information of fixed wing aircraft 21 and fly to fixed wing aircraft 21
Front overhead, and carry out in front docking and prepare.When fixed wing aircraft 21 and multi-rotor aerocraft 7 are relativelyed close to, pass through
The gps signal of GPS navigation device 19 and many rotor GPS navigation devices 5 carries out height coarse alignment, then inertial sensor 18 and many
The information Real-Time Sharing of rotor inertial sensor 6, while thermal infrared imager 11 catches the position of infrared illuminator 15, flight control
Computer 1 is according to GPS navigation device 19, many rotor GPS navigation devices 5, inertial sensor 18, many and of rotor inertial sensor 6
The positional information calculation to infrared illuminator 15 that thermal infrared imager 11 is caught go out fixed wing aircraft 21 and multi-rotor aerocraft 7 it
Between spatial relation after, flight-control computer 1 control multi-rotor aerocraft 7 flight attitude and speed, when outer
When position directly below in the picture occurs in light emitting diode 15, connecting-rod cap 9 and connection end 14 are alignd, the He of fixed wing aircraft 21
After the geo-stationary flight setting time of multi-rotor aerocraft 7, the control multi-rotor aerocraft 7 of flight-control computer 1 slowly declines,
Connecting-rod cap 9 is set to enter connection end 14.Connecting-rod cap 9 enters behind the 14 of connection end, and bayonet unit 13 enters the recessed of connecting-rod cap
Connecting-rod cap 9 is pinned in the position of groove 10, and then the dynamical system of fixed wing aircraft 21 is flame-out opens undercarriage 17 simultaneously, and many rotors fly
Row device 7 slowly slows down the landing place flown to and specified with fixed wing aircraft 21, after fixed wing aircraft 21 lands, bayonet unit 13
Unclamp, connection end 14 and connecting-rod cap 9 are separated, and multi-rotor aerocraft 7 returns to alone multi-rotor aerocraft parking platform 12.
Claims (3)
1. a kind of lifting gear of aircraft, it is characterised in that：Including fixed wing aircraft（21）, multi-rotor aerocraft（7）With many rotations
Rotor aircraft parking platform（12）；Fixed wing aircraft（21）Including fuselage (16）, undercarriage (17), GPS navigation device (19), inertia
Sensor (18), infrared illuminator (15), communication module (20) and connection end (14)；Undercarriage (17) is in fuselage (16）Belly
Below, fuselage (16 can be taken in）；Inertial sensor (18) is located at fuselage (16）It is internal；Infrared illuminator (15) is located at connection end
(14) side；Connection end (14) is located across fixed wing aircraft（21）The fuselage (16 of center of gravity plumb line）Top；Connection end
(14) bayonet unit (13), inside of the bayonet unit (13) in connection end (14) are included；Multi-rotor aerocraft（7）Including flight control
Computer (1) processed, many rotor inertial sensors (6), thermal infrared imager (11), many rotor GPS navigation devices (5), many rotors lead to
Believe module (3), connecting rod (4) and connecting rod vertical means (2)；Flight-control computer (1) includes image recognition processing system
With temperature identification processing system, they connect thermal infrared imager (11), many rotor inertial sensors (6), many rotor GPS navigations dress
Put (5) and many rotor communication modules (3)；The thermal infrared imager (11) is located at the latter half of connecting rod (4), thermal infrared imager
(11) horizontal range to connecting rod (4) is equal to the horizontal range that infrared illuminator (15) arrives connection end (14), positioned at connecting rod
(4) the latter half；Many rotor inertial sensors (6) are located at multi-rotor aerocraft（7）Fuselage interior；The connecting rod
(4) multi-rotor aerocraft is passed through（7）Center, with multi-rotor aerocraft（7）Vertically；Connecting rod (4) includes connecting-rod cap (9),
Connecting-rod cap (9) is located at the lower end of connecting rod (4), there is two grooves (10)；The connecting rod vertical means (2) are located at connecting rod
(4) top both sides, with multi-rotor aerocraft（7）Connection.
2. a kind of lifting gear of aircraft according to claim 1, it is characterised in that：The connection end (14) is in infundibulate
Shape.
3. a kind of lifting gear of aircraft according to claim 1 or 2, it is characterised in that：The connecting-rod cap (9) is in cone
Shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720227398.1U CN206537510U (en) | 2017-03-10 | 2017-03-10 | A kind of lifting gear of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720227398.1U CN206537510U (en) | 2017-03-10 | 2017-03-10 | A kind of lifting gear of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206537510U true CN206537510U (en) | 2017-10-03 |
Family
ID=59941632
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720227398.1U Expired - Fee Related CN206537510U (en) | 2017-03-10 | 2017-03-10 | A kind of lifting gear of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206537510U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112262357A (en) * | 2018-06-11 | 2021-01-22 | 瑞典爱立信有限公司 | Determining control parameters for formation of multiple UAVs |
-
2017
- 2017-03-10 CN CN201720227398.1U patent/CN206537510U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112262357A (en) * | 2018-06-11 | 2021-01-22 | 瑞典爱立信有限公司 | Determining control parameters for formation of multiple UAVs |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171003 Termination date: 20200310 |