CN106904280A - The landing mode and the combination unit of use of a kind of aircraft - Google Patents
The landing mode and the combination unit of use of a kind of aircraft Download PDFInfo
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- CN106904280A CN106904280A CN201710139339.3A CN201710139339A CN106904280A CN 106904280 A CN106904280 A CN 106904280A CN 201710139339 A CN201710139339 A CN 201710139339A CN 106904280 A CN106904280 A CN 106904280A
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- 238000003860 storage Methods 0.000 claims abstract description 37
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 26
- 238000004891 communication Methods 0.000 claims abstract description 24
- 230000009187 flying Effects 0.000 claims description 9
- 238000005183 dynamical system Methods 0.000 claims description 4
- 238000003032 molecular docking Methods 0.000 claims description 4
- 238000004364 calculation method Methods 0.000 claims description 3
- 230000004992 fission Effects 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 230000007423 decrease Effects 0.000 claims 1
- 230000001133 acceleration Effects 0.000 description 4
- 238000005259 measurement Methods 0.000 description 4
- 238000012545 processing Methods 0.000 description 4
- 238000001931 thermography Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
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- 238000010276 construction Methods 0.000 description 1
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- 238000010586 diagram Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/12—Target-seeking control
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- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The landing mode and the combination unit of use of a kind of aircraft, belong to technical field of aerospace, more particularly to aircraft landing mode and the combination unit of use.Combination unit includes fixed wing aircraft and multi-rotor aerocraft, and fixed wing aircraft includes fuselage, undercarriage, GPS navigation device, inertial sensor, infrared illuminator, communication module and connection end；Multi-rotor aerocraft includes flight-control computer, many rotor inertial sensors, thermal infrared imager, many rotor GPS navigation devices, many rotor communication modules, storage device, connecting rope, connecting rod, connecting-rod cap and connecting rod vertical means；Multi-rotor aerocraft is separated after hanging drawing fixed wing aircraft lift-off, realizes taking off for fixed wing aircraft；Multi-rotor aerocraft flies to and is combined with fixed wing aircraft in the air, hangs the landing for drawing fixed wing aircraft.The present invention can utilize multi-rotor aerocraft advantage, be combined with fixed wing aircraft using multi-rotor aerocraft, for the landing mode of fixed wing aircraft provides new departure.
Description
Technical field
The landing mode and the combination unit of use of a kind of aircraft, belong to technical field of aerospace, more particularly to aircraft rises
Drop mode and the device of use.
Background technology
With the opening of low altitude airspace, Aircraft Market scale will be skyrocketed through, and fixed wing aircraft and multi-rotor aerocraft are all
There are respective advantage and disadvantage；Fixed wing aircraft flight course safety, flying speed are fast, remote voyage and the characteristics of big carrying capacity,
But landing process is required for using runway and cannot hovering in the air；The VTOL of multi-rotor aerocraft energy, technology are simple, motor-driven
Flexibly, simple to operate and flight vibrations are small, but cruising time is short and security is low；Examined for security and endurance
Consider, fixed wing aircraft turns into the first-selection of people's trip, but limited by the field, most of clients cannot meet the flight of oneself and be intended to
Hope, so greatly limit the development and popularization of fixed wing aircraft.
The content of the invention
The purpose of the present invention is the above-mentioned deficiency for overcoming traditional aircraft, using multi-rotor aerocraft advantage, using many
Rotor craft is combined with fixed wing aircraft, for the landing of aircraft provides a kind of new paragon.
A kind of landing mode of aircraft, is to realize that the combination unit includes fixed wing aircraft by following combination unit
And multi-rotor aerocraft；The fixed wing aircraft includes fuselage, undercarriage, GPS navigation device, inertial sensor, infraluminescence
Device, communication module and connection end；The connection end is the device that fixed wing aircraft is docked with multi-rotor aerocraft, is located across solid
Determine the fuselage roof of wing aircraft center of gravity plumb line, many rotor flyings can be made when multi-rotor aerocraft pull-up fixed wing aircraft hovers
Device and fixed wing aircraft relative equilibrium；The connection end includes bayonet unit；The undercarriage can be when fixed wing aircraft lands
Use；The GPS navigation device is the alignment system of fixed wing aircraft；The inertial sensor has measurement fixed wing aircraft
The function of the information such as acceleration, gradient, vibration and switch, positioned at fuselage interior；The infrared illuminator is located at connection end
Side, for sending infrared signal；The communication module is the device that fixed wing aircraft is connected with external information；The buckle
Device is located at the inside of connection end.The multi-rotor aerocraft includes flight-control computer, many rotor inertial sensors, infrared
Thermal imaging system, many rotor GPS navigation devices, many rotor communication modules, storage device, connecting rope, connecting rod, connecting-rod cap and connection
Bar vertical means；The connecting rope includes left connecting rope and right connecting rope；The connecting rod includes left connecting rod and right connecting rod；
The connecting rod vertical means include left connecting rod vertical means and right connecting rod vertical means.The flight-control computer is
The control centre of multi-rotor aerocraft, including image recognition processing system and temperature identification processing system, flight-control computer
Temperature data that thermal infrared imager collects can be processed and temperature reading and image is converted into, thermal infrared imager, many is connected respectively
Rotor inertial sensor, many rotor GPS navigation devices and many rotor communication modules；The thermal infrared imager is located under connecting rod
Half part, the horizontal range of thermal infrared imager to connecting rod is equal to infrared illuminator to the horizontal range of connection end, can receive with
Converge testee transmitting infra-red radiation and be converted into electric signal and be sent to flight-control computer formed temperature information and
Image information, the position of infrared illuminator is caught for recognizing；Many rotor inertial sensors have many rotor flyings of measurement
The function of the information such as the acceleration of device, gradient, vibration and switch, positioned at multi-rotor aerocraft fuselage interior；Many rotors
GPS navigation device is the alignment system of multi-rotor aerocraft；Many rotor communication modules are that multi-rotor aerocraft is believed with extraneous
Cease the device of connection；The storage device is located at the both sides of multi-rotor aerocraft, respectively left storage device and right storage device,
For the left connecting rod of folding and unfolding and right connecting rod, left storage device is connected with left connecting rope, and right storage device is connected with right connecting rope,
The folding and unfolding of connecting rope is rotarily driven by the motor received on device；The connecting rope includes left connecting rope and right connecting rope, left
Left storage device and the left connecting rod of connecting rope connection, right right storage device and the right connecting rod of connecting rope connection；The connecting rod is
The device that multi-rotor aerocraft is connected with fixed wing aircraft, it is vertical with multi-rotor aerocraft positioned at the center of multi-rotor aerocraft,
Connecting rod is symmetrical fissions structure into two, is respectively the top of left connecting rod and right connecting rod, left connecting rod and right connecting rod
It is arc structure to hold, and facilitates the merging and division of left connecting rod and right connecting rod, is used to be docked with fixed wing aircraft during merging, point
Can bonding parallel with multi-rotor aerocraft when splitting；The connecting-rod cap is the portion that multi-rotor aerocraft is connected with fixed wing aircraft
, positioned at the lower end of connecting rod, there are two grooves position；The connecting rod vertical means are located at the top of connecting rod and fly with many rotors
Row device is connected, and left connecting rod vertical means and right connecting rod vertical means are each passed through left connecting rod and right connecting rod.
The connection end is in funnel shaped.
Two grooves of the connecting-rod cap, in funnel shaped.
The connecting rod vertical means are cylindrical structure.
A kind of mode of taking off of aircraft：When fixed wing aircraft needs to take off, many rotations are signaled to by communication module
Rotor aircraft, multi-rotor aerocraft receives signal by many rotor communication modules, while the GPS for receiving fixed wing aircraft leads
Boat positional information, at ground, connecting rod is collapsed state to multi-rotor aerocraft, and connecting rod is put down with the fuselage of multi-rotor aerocraft
Row bonding.Multi-rotor aerocraft takes off, and during taking off, putting for drive connecting rope is rotated by receiving the motor on device
Pine, is combined left connecting rod and right connecting rod, and then multi-rotor aerocraft flies to fixed wing aircraft top, inertial sensor
With the information Real-Time Sharing of many rotor inertial sensors, while thermal infrared imager catches the position of infrared illuminator, flight is controlled
Computer determines the position relationship between fixed wing aircraft and multi-rotor aerocraft, occurs in the picture just in infrared illuminator
During lower position, connecting-rod cap and connection end are alignd, flight-control computer control multi-rotor aerocraft calibrating position, slowly under
Drop, makes connecting-rod cap enter connection end, and then bayonet unit enters the groove location of connection end, multi-rotor aerocraft and fixed-wing
Multi-rotor aerocraft drives fixed wing aircraft to take off after connection between aircraft is pinned, and when flying to setting height, many rotors fly
Row device is accelerated forwardly, and during to setting speed, the dynamical system of fixed wing aircraft starts, and multi-rotor aerocraft is protected with fixed wing aircraft
Geo-stationary is held, fixed wing aircraft and multi-rotor aerocraft are accelerated to when can allow fixed wing aircraft flight, bayonet unit unclamps, even
Extension bar head and connection end depart from, and multi-rotor aerocraft flies upwards, and fixed wing aircraft independently flies, and multi-rotor aerocraft is by many rotations
The origin information of wing GPS navigation device positioning returns to alone takeoff point, during multi-rotor aerocraft lands, receives device
Tightening up for connecting rope is driven, connecting rope drives connecting rod, left connecting rod and right connecting rod is put down with the fuselage of multi-rotor aerocraft
Row bonding, then drops to ground.
A kind of landing modes of aircraft：When fixed wing aircraft needs landing, many rotations are signaled to by communication module
Rotor aircraft, multi-rotor aerocraft takes off, while receiving GPS navigation positional information, route information and the speed of fixed wing aircraft
Degree information, flight-control computer calculates the course line of fixed wing aircraft, is drawn close to fixed wing aircraft.With fixed wing aircraft also
When having setpoint distance, multi-rotor aerocraft direction of advance is made a U-turn, and course is gone to fixed wing aircraft heading, Gu
It is horizontal flight to determine wing aircraft.When multi-rotor aerocraft and relatively close fixed wing aircraft position, multi-rotor aerocraft leads to
The shared information of the GPS navigation device for receiving is crossed to determine the positional information of fixed wing aircraft and fly on the front of fixed wing aircraft
Sky, and carry out docking preparation in front.When fixed wing aircraft and multi-rotor aerocraft are relativelyed close to, by GPS navigation device
Gps signal with multi-rotor aerocraft GPS navigation device carries out height coarse alignment, then inertial sensor and many rotor inertia
The information Real-Time Sharing of sensor, while thermal infrared imager catches the position of infrared illuminator, flight-control computer is according to GPS
Information and infrared thermal imagery that guider, many rotor GPS navigation devices, inertial sensor, many rotor inertial sensors are provided
Close the locus that the positional information calculation to infrared illuminator that instrument catches goes out between fixed wing aircraft and multi-rotor aerocraft
After system, the flight attitude and speed of flight-control computer control multi-rotor aerocraft, when infrared illuminator appears in image
In position directly below when, connecting-rod cap and connection end are alignd, fixed wing aircraft and multi-rotor aerocraft geo-stationary flight one
After the section time, flight-control computer control multi-rotor aerocraft slowly declines, and connecting-rod cap is entered connection end.Connecting-rod cap
After insertion connection end, the groove location that bayonet unit enters connecting-rod cap pins connecting-rod cap, and then fixed wing aircraft is dynamic
Force system is flame-out to open undercarriage simultaneously, and multi-rotor aerocraft slowly slows down the landing place flown to and specify with fixed wing aircraft
Afterwards, bayonet unit is unclamped, and connection end and connecting-rod cap are separated, and multi-rotor aerocraft returns to alone ground.
It is of the invention to utilize the VTOL of multi-rotor aerocraft energy and flexible advantage, using multi-rotor aerocraft and
Fixed wing aircraft combine, for the landing of fixed wing aircraft provides a kind of scheme, allow fixed wing aircraft also can the landing on platform, subtract
Lack the construction of runway needed for fixed wing aircraft, be conducive 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 structural representation of the multi-rotor aerocraft at ground；Fig. 5 is
The structural representation of storage device, connecting rope and connecting rod.
In figure, 1- flight-control computers, 200- connecting rod vertical means, many rotor communication modules of 3-, 4- connecting rods, 5-
Many rotor GPS navigation devices, many rotor inertial sensors of 6-, 7- multi-rotor aerocrafts, 9- connecting-rod caps, 10- grooves, 11- is red
Outer thermal imaging system, 13- bayonet units, 14- connection ends, 15- infrared illuminators, 16- fuselages, 17- undercarriages, 18- inertial sensors,
19-GPS guiders, 20- communication modules, 21- fixed wing aircrafts, 80- storage devices, the left storage devices of 801-, 802 right storages
Device, 90- connecting ropes, the left connecting ropes of 901-, the right connecting ropes of 902-, the left connecting rods of 41-, the right connecting rods of 42-, the left connections of 2001-
Bar vertical means, the right connecting rod vertical means of 2002-.
Specific embodiment
The present invention is illustrated below in conjunction with the accompanying drawings；A kind of landing mode of aircraft, is by following combination unit
Realize, the combination unit include fixed wing aircraft 21 and multi-rotor aerocraft 7, the fixed wing aircraft 21 include fuselage 16,
Undercarriage 17, GPS navigation device 19, inertial sensor 18, infrared illuminator 15, communication module 20 and connection end 14；The company
Connecing end 14 includes bayonet unit 13；Undercarriage 17 can take in fuselage 16 below the belly of fuselage 16, can be in fixed wing aircraft 21
Used during landing；The GPS navigation device 19 is the alignment system of fixed wing aircraft 21；The inertial sensor 18 has measurement
The function of the information such as the acceleration of fixed wing aircraft, gradient, vibration and switch, inside fuselage 16；The infraluminescence
Device 15 is located at the side of connection end 14, for sending infrared signal；The communication module 20 is fixed wing aircraft 21 and the external world
The device of information connection；The connection end 14 is the device that fixed wing aircraft 21 is connected with multi-rotor aerocraft 7, in infundibulate
Shape, is located across the top of fuselage 16 of the center of gravity plumb line of fixed wing aircraft 7, can be in the pull-up fixed wing aircraft of multi-rotor aerocraft 7
Make multi-rotor aerocraft 7 and the relative equilibrium of fixed wing aircraft 21 during 21 hovering；Inside of the bayonet unit 13 in connection end 14.
The multi-rotor aerocraft 7 includes flight-control computer 1, many rotor inertial sensors 6, thermal infrared imager 11, many rotor GPS
Guider 5, many rotor communication modules 3, storage device 80, connecting rope 90, connecting rod 4, connecting-rod cap 9 and connecting rod are vertically filled
Put 200；The storage device 80 includes left storage device 801 and right storage device 802；The connecting rope 90 includes left connecting rope
901 and right connecting rope 902；The connecting rod 4 includes left connecting rod 41 and right connecting rod 42；The connecting rod vertical means 200
Including left connecting rod vertical means 2001 and right connecting rod vertical means 2002；There are receipts in the fuselage of the multi-rotor aerocraft 7
Receive the space for placing left connecting rod 41 and right connecting rod 42；During the flight-control computer 1 is the control of multi-rotor aerocraft 7
The heart, including image recognition processing system and temperature identification processing system, flight-control computer 1 can process thermal infrared imager collection
To temperature data and be converted into temperature reading and image, thermal infrared imager 11, many rotor inertial sensors 6, many is connected respectively
Rotor 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 imaging system 11 is equal to infrared illuminator 15 to the horizontal range of connection end 14 to the horizontal range of connecting rod 4, can receive and converge
Testee transmitting infra-red radiation and be converted into telecommunications be sent to flight-control computer 1 formed temperature information and image letter
Breath, positioned at the latter half of connecting rod 4, the position of infrared illuminator 15 is caught for recognizing；Many rotor inertial sensors 6
The function of the information such as acceleration, gradient, vibration and switch with measurement multi-rotor aerocraft 7, positioned at multi-rotor aerocraft 7
Fuselage interior；Many rotor GPS navigation devices 5 are the alignment systems of multi-rotor aerocraft 7；Many rotor communication modules 3
It is device that multi-rotor aerocraft 7 is connected with external information；The storage device 80 is located at the both sides of multi-rotor aerocraft, respectively
Be it is left storage device 801 and it is right storage device 802, it is left storage device 801 be connected with left connecting rope 901, it is right storage device 802 with
Right connecting rope 902 is connected, and the folding and unfolding of connecting rope 90 is rotarily driven by receiving the motor on device 80；The connecting rope 90 includes
Left connecting rope 901 and right connecting rope 902, left connecting rope 901 connect left storage device 801 and left connecting rod 41, right connecting rope 902
Right storage device 802 and the right connecting rod 42 of connection；The connecting rod 4 is that multi-rotor aerocraft 7 is connected with fixed wing aircraft 21
Device, vertical with multi-rotor aerocraft 7 positioned at the center of multi-rotor aerocraft 7, connecting rod 4 is symmetrical fissions knot into two
The top of structure, respectively left connecting rod 41 and right connecting rod 42, left connecting rod 41 and right connecting rod 42 is arc structure, convenient left
The merging and division of connecting rod 41 and right connecting rod 42, during merging be used for docked with fixed wing aircraft 21, during division can with it is many
The parallel bonding of rotor craft 7；The connecting-rod cap 9 is the position that multi-rotor aerocraft 7 is connected with fixed wing aircraft 21, is located at
, there are two grooves 10 lower end of connecting rod 4, in funnel shaped；The connecting rod vertical means 200 are cylindrical structure, are located at
The top of connecting rod 4 is simultaneously connected with multi-rotor aerocraft 7, left connecting rod vertical means 2001 and right connecting rod vertical means 2002
It is each passed through left connecting rod 41 and right connecting rod 42.
A kind of mode of taking off of aircraft：When fixed wing aircraft 21 needs to take off, it is signaled to by communication module 20
Multi-rotor aerocraft 7, multi-rotor aerocraft 7 receives signal by many rotor communication modules 3, while receiving fixed wing aircraft
21 GPS navigation positional information, at ground, connecting rod 4 is collapsed state to multi-rotor aerocraft 7, and connecting rod 4 flies with many rotors
The parallel bonding of fuselage of row device 7.Multi-rotor aerocraft 7 takes off, and during taking off, is turned by receiving the motor on device 80
It is dynamic to drive loosening for connecting rope 90, left connecting rod 41 and right connecting rod 42 are combined, then multi-rotor aerocraft 7 flies to solid
The information Real-Time Sharing of the top of wing aircraft 21, inertial sensor 18 and many rotor inertial sensors 6 is determined, while thermal infrared imager 11
The position of infrared illuminator 15 is caught, flight-control computer 1 determines the position between fixed wing aircraft 21 and multi-rotor aerocraft 7
Relation is put, when position directly below in the picture occurs in infrared illuminator 15, connecting-rod cap 9 and connection end 14 are alignd, flown
Control computer 1 controls the calibrating position of multi-rotor aerocraft 7, slowly declines, and connecting-rod cap 9 is entered connection end 14, then blocks
Buckle device 13 enters the position of groove 10 of connection end, after the connection between multi-rotor aerocraft 7 and fixed wing aircraft 21 is pinned
Multi-rotor aerocraft 7 drives fixed wing aircraft 21 to take off, and when flying to setting height, multi-rotor aerocraft 7 is accelerated forwardly, to setting
During speed, the dynamical system of fixed wing aircraft 21 starts, and multi-rotor aerocraft 7 keeps geo-stationary with fixed wing aircraft 21, Gu
Determine wing aircraft 21 and multi-rotor aerocraft 7 is accelerated to when can allow 21 flight of fixed wing aircraft, bayonet unit 13 unclamps, many rotors fly
Row device 7 flies upwards, and connecting-rod cap 9 and connection end 14 depart from, the independent flight of fixed wing aircraft 21, and multi-rotor aerocraft 7 is by more
The origin information of the positioning of rotor GPS navigation device 5 returns to alone takeoff point, and during landing, storage device 80 drives and connects
Splicing 90 is tightened up, and connecting rope 90 drives connecting rod 4, makes the machine of left connecting rod 41 and right connecting rod 42 and multi-rotor aerocraft 7
The parallel bonding of body, then drops to ground.
A kind of landing modes of aircraft：When fixed wing aircraft 21 needs landing, it is signaled to by communication module 20
Multi-rotor aerocraft 7, multi-rotor aerocraft 7 takes off, while receiving GPS navigation positional information, the course line of fixed wing aircraft 21
Information and velocity information, flight-control computer 1 calculate the course line of fixed wing aircraft 21, are drawn close to fixed wing aircraft 21.
When also having setpoint distance with fixed wing aircraft 21, the direction of advance of multi-rotor aerocraft 7 is made a U-turn, and course is gone to fixation
The heading of wing aircraft 21, fixed wing aircraft 21 is horizontal flight.When multi-rotor aerocraft 7 and the position phase of fixed wing aircraft 21
During to being close to, the GPS navigation device 19 that multi-rotor aerocraft 7 passes through to receive shares the position that information determines fixed wing aircraft 21
Information simultaneously flies to the front overhead of fixed wing aircraft 21, and carries out docking preparation in front.In fixed wing aircraft 21 and many rotors
When aircraft 7 is relativelyed close to, height is carried out by the gps signal of GPS navigation device 19 and many rotor GPS navigation devices 5 thick right
Standard, the then information Real-Time Sharing of inertial sensor 18 and many rotor inertial sensors 6, while thermal infrared imager 11 catches red
The position of outer photophore 15, flight-control computer 1 is according to GPS navigation device 19, multi-rotor aerocraft GPS navigation device 5, used
Property the position to infrared illuminator 15 that catches of sensor 18, multi-rotor aerocraft inertial sensor 6 and thermal infrared imager 11 believe
Breath is calculated after the spatial relation between fixed wing aircraft 21 and multi-rotor aerocraft 7, and flight-control computer 1 is controlled
The flight attitude and speed of multi-rotor aerocraft 7, when there is position directly below in the picture in infrared illuminator 15, connection
Head 9 and connection end 14 are alignd, after fixed wing aircraft 21 and the geo-stationary flight setting time of multi-rotor aerocraft 7, flight control
The control multi-rotor aerocraft 7 of computer processed 1 slowly declines, and connecting-rod cap 9 is entered connection end 14.Connecting-rod cap 9 enters connection
Behind the 14 of end, connecting-rod cap 9 is pinned in the position of groove 10 that bayonet unit 13 enters connecting-rod cap, and then fixed wing aircraft 21 is dynamic
Force system is flame-out to open undercarriage 17 simultaneously, and multi-rotor aerocraft 7 slowly slows down the drop flown to and specify with fixed wing aircraft 21
Pick-up point, after fixed wing aircraft 21 lands, bayonet unit 13 is unclamped, and connection end 14 and connecting-rod cap 9 are separated, multi-rotor aerocraft
7 return to alone ground.
Claims (6)
1. a kind of combination unit of aircraft, it is characterised in that including fixed wing aircraft（21）And multi-rotor aerocraft（7）, it is described
Fixed wing aircraft（21）Including GPS navigation device（19）, inertial sensor（18）, infrared illuminator（15）, communication module（20）
And connection end（14）；The connection end（14）Including bayonet unit（13）；The multi-rotor aerocraft（7）Including flight control meter
Calculation machine（1）, many rotor inertial sensors（6）, thermal infrared imager（11）, many rotor GPS navigation devices（5）, many rotors communication moulds
Block（3）, storage device（80）, connecting rope（90）, connecting rod（4）, connecting-rod cap（9）With connecting rod vertical means（200）；It is described
Storage device（80）Including left storage device（801）With right storage device（802）；The connecting rope（90）Including left connecting rope
（901）With right connecting rope（902）；The connecting rod（4）Including left connecting rod（41）With right connecting rod（42）；The connecting rod is hung down
Straight device（200）Including left connecting rod vertical means（2001）With right connecting rod vertical means（2002）.
2. the combination unit of a kind of aircraft according to claim 1, it is characterised in that：The multi-rotor aerocraft（7）'s
There is storage to place left connecting rod in fuselage（41）With right connecting rod（42）Space；The storage device（80）Fly positioned at many rotors
The both sides of row device, are respectively left storage devices（801）With right storage device（802）, left storage device（801）With left connecting rope
（901）Connection, right storage device（802）With right connecting rope（902）Connection, by receiving device（80）On motor rotarily drive
Connecting rope（90）Folding and unfolding；The connecting rope（90）Including left connecting rope（901）With right connecting rope（902）, left connecting rope（901）
Connect left storage device（801）With left connecting rod（41）, right connecting rope（902）Connect right storage device（802）With right connecting rod
（42）；The connecting rod（4）It is multi-rotor aerocraft（7）With fixed wing aircraft（21）The device of connection, positioned at many rotor flyings
Device（7）Center, with multi-rotor aerocraft（7）Vertically, connecting rod（4）It is symmetrical fissions structure into two, respectively left company
Extension bar（41）With right connecting rod（42）, left connecting rod（41）With right connecting rod（42）Top be arc structure；The connecting rod
Head（9）It is multi-rotor aerocraft（7）With fixed wing aircraft（21）The position of connection, positioned at connecting rod（4）Lower end, the connection
Bar vertical means（200）It is cylindrical structure, positioned at connecting rod（4）Top and and multi-rotor aerocraft（7）Connection, left connection
Bar vertical means（2001）With right connecting rod vertical means（2002）It is each passed through left connecting rod（41）With right connecting rod（42）.
3. the combination unit of a kind of aircraft according to claim 1 and 2, it is characterised in that：The connection end（14）It is solid
Determine wing aircraft（21）With multi-rotor aerocraft（7）The device of connection, in funnel shaped, positioned at fixed wing aircraft（7）Center of gravity extends
The fuselage of line（16）Top, can be in multi-rotor aerocraft（7）Pull-up fixed wing aircraft（21）Make multi-rotor aerocraft during hovering（7）
And fixed wing aircraft（21）Relative equilibrium.
4. the landing mode of a kind of aircraft according to claim 1 and 2, it is characterised in that：The bayonet unit（13）
Connection end（14）Inside.
5. the mode of taking off of a kind of aircraft, it is characterised in that：Work as fixed wing aircraft（21）When needing to take off, by communication module
（20）It is signaled to multi-rotor aerocraft（7）, multi-rotor aerocraft（7）The signal that takes off is received, while receiving fixed-wing
Aircraft（21）GPS navigation positional information；Multi-rotor aerocraft（7）Take off, during taking off, by receiving device（80）
On motor rotate drive connecting rope（90）Loosen, make left connecting rod（41）With right connecting rod（42）It is combined, Ran Houduo
Rotor craft（7）Fly to fixed wing aircraft（21）Top, inertial sensor（18）With many rotor inertial sensors（6）Information
Real-Time Sharing, while thermal infrared imager（11）Catch infrared illuminator（15）Position, flight-control computer（1）It is determined that fixed
Wing aircraft（21）With multi-rotor aerocraft（7）Between position relationship, work as infrared illuminator（15）Occur in the picture just under
When orientation is put, connecting-rod cap（9）And connection end（14）Alignment, flight-control computer（1）Control multi-rotor aerocraft（7）Calibration
Position, slowly declines, and makes connecting-rod cap（9）Into connection end（14）, then bayonet unit（13）Into the groove of connection end
（10）Position, multi-rotor aerocraft（7）With fixed wing aircraft（21）Between connection pin after multi-rotor aerocraft（7）Drive
Fixed wing aircraft（21）Take off, when flying to setting height, multi-rotor aerocraft（7）It is accelerated forwardly, during to setting speed, fixed-wing
Aircraft（21）Dynamical system start, multi-rotor aerocraft（7）With fixed wing aircraft（21）Keep geo-stationary, fixed wing aircraft
（21）And multi-rotor aerocraft（7）Accelerating to can allow fixed wing aircraft（21）During oneself flight, bayonet unit（13）Unclamp, revolve more
Rotor aircraft（7）Fly upwards, connecting-rod cap（9）And connection end（14）Depart from, fixed wing aircraft（21）Independent flight, many rotors fly
Row device（7）By many rotor GPS navigation devices（5）The origin information of positioning returns to alone takeoff point, during landing, receives
Receive device（80）Drive connecting rope（90）Tighten up, connecting rope（90）Drive connecting rod（4）, make left connecting rod（41）With right connection
Bar（42）With multi-rotor aerocraft（7）The parallel bonding of fuselage, then drop to ground.
6. a kind of landing modes of aircraft, it is characterised in that：Work as fixed wing aircraft（21）When needing landing, by communication module
（20）It is signaled to multi-rotor aerocraft（7）, multi-rotor aerocraft（7）Take off, while receiving fixed wing aircraft（21）'s
GPS navigation positional information, route information and velocity information, flight-control computer（1）Calculate fixed wing aircraft（21）Boat
Line, to fixed wing aircraft（21）Draw close；Work as multi-rotor aerocraft（7）And fixed wing aircraft（21）When position is relatively close, revolve more
Rotor aircraft（7）By the GPS navigation device for receiving（19）Shared information determines fixed wing aircraft（21）Positional information simultaneously
Fly to fixed wing aircraft（21）Front overhead, and front carry out docking prepare；In fixed wing aircraft（21）Fly with many rotors
Row device（7）When relativelying close to, by GPS navigation device（19）With many rotor GPS navigation devices（5）Gps signal carry out height
Coarse alignment, then inertial sensor（18）With many rotor inertial sensors（6）Information Real-Time Sharing, while thermal infrared imager
（11）Catch infrared illuminator（15）Position, flight-control computer（1）According to GPS navigation device（19）, many rotor flyings
Device GPS navigation device（5）, inertial sensor（18）, multi-rotor aerocraft inertial sensor（6）And thermal infrared imager（11）Catch
To infrared illuminator（15）Positional information calculation go out fixed wing aircraft（21）With multi-rotor aerocraft（7）Between space bit
After putting relation, flight-control computer（1）Control multi-rotor aerocraft（7）Flight attitude and speed, work as infraluminescence
Device（15）When there is position directly below in the picture, connecting-rod cap（9）And connection end（14）Alignment, fixed wing aircraft（21）With
Multi-rotor aerocraft（7）After geo-stationary flight setting time, flight-control computer（1）Control multi-rotor aerocraft（7）Slowly
It is slow to decline, make connecting-rod cap（9）Into connection end（14）；Connecting-rod cap（9）Into connection end it（14）Afterwards, bayonet unit（13）
Into the groove of connecting-rod cap（10）Pin connecting-rod cap in position（9）, then fixed wing aircraft（21）Dynamical system it is flame-out same
When open undercarriage（17）, multi-rotor aerocraft（7）With fixed wing aircraft（21）The landing place specified is flown in slowly deceleration,
Fixed wing aircraft（21）After landing, bayonet unit（13）Unclamp, connection end（14）And connecting-rod cap（9）Separate, many rotor flyings
Device（7）Ground is returned to alone.
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| CN201710139339.3A CN106904280A (en) | 2017-03-10 | 2017-03-10 | The landing mode and the combination unit of use of a kind of aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651177A (en) * | 2017-09-18 | 2018-02-02 | 佛山市神风航空科技有限公司 | A kind of device for increasing multi-rotor unmanned aerial vehicle flying distance |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110049288A1 (en) * | 2008-08-21 | 2011-03-03 | Satoshi Suzuki | Unmanned aircraft system and operation method thereof |
| US20170036762A1 (en) * | 2015-08-03 | 2017-02-09 | Dustin Gamble | Release and Capture of a Fixed-Wing Aircraft |
| CN206704540U (en) * | 2017-03-10 | 2017-12-05 | 佛山市神风航空科技有限公司 | A kind of combination unit of aircraft |
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2017
- 2017-03-10 CN CN201710139339.3A patent/CN106904280A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110049288A1 (en) * | 2008-08-21 | 2011-03-03 | Satoshi Suzuki | Unmanned aircraft system and operation method thereof |
| US20170036762A1 (en) * | 2015-08-03 | 2017-02-09 | Dustin Gamble | Release and Capture of a Fixed-Wing Aircraft |
| CN206704540U (en) * | 2017-03-10 | 2017-12-05 | 佛山市神风航空科技有限公司 | A kind of combination unit of aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651177A (en) * | 2017-09-18 | 2018-02-02 | 佛山市神风航空科技有限公司 | A kind of device for increasing multi-rotor unmanned aerial vehicle flying distance |
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Application publication date: 20170630 |