CN207759015U - A kind of tear-away captive VTOL fixed-wing unmanned plane - Google Patents
A kind of tear-away captive VTOL fixed-wing unmanned plane Download PDFInfo
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- CN207759015U CN207759015U CN201721835572.7U CN201721835572U CN207759015U CN 207759015 U CN207759015 U CN 207759015U CN 201721835572 U CN201721835572 U CN 201721835572U CN 207759015 U CN207759015 U CN 207759015U
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Abstract
The utility model discloses a kind of tear-away captive VTOL fixed-wing unmanned planes, include fixed-wing structural system, fixed-wing dynamical system, rotor power system, power source system, flight control system and airborne avionics system；Power source system includes power management module, lithium battery group, fuel tank and tear-away separable electric connector；The power supply output end of tear-away separable electric connector, lithium battery group are connect with power management module, and ground power supply system is connect with the energization input of tear-away separable electric connector.The utility model is connected by being tethered at cable with ground power supply system using tear-away separable electric connector during taking off, directly feed the electric energy needed for rotor power system, power is sufficient, ensure the power requirement of lift-off flight, payload is increased, stability and wind loading rating in more rotor work process are enhanced.
Description
Technical field
The utility model is related to unmanned plane field, specifically a kind of tear-away captive VTOL fixed-wing unmanned plane.
Background technology
Relative to traditional Fixed Wing AirVehicle and rotor craft, can VTOL Fixed Wing AirVehicle due to using
The composite construction forms of fixed-wing+more rotors, it may be unnecessary to runway and landing spatial domain, it can be in complexity such as mountain area, hills, jungles
Landform and the intensive smooth operation in region of building, and avoid slow multi-rotor aerocraft flying speed, air mileage and endurance
Short problem.But also unavoidably there is more rotors defect of itself simultaneously, maximum load is limited to the ability of more rotors.
Utility model content
The technical problem to be solved by the present invention is to provide a kind of tear-away captive VTOL fixed-wing unmanned plane,
Power is not when solving the power that general VTOL fixed-wing unmanned plane uses lithium battery group as more rotors, in uphill process
Foot, lithium battery group energy density is low, and wind resistance is poor, the limited problem of payload weight.
The technical solution of the utility model is：
A kind of tear-away captive VTOL fixed-wing unmanned plane, includes fixed-wing structural system, fixed-wing power
System, rotor power system, power source system, flight control system and airborne avionics system；
The fixed-wing structural system include fuselage, two be connected to side-of-body along the symmetrical machine of fuselage axis
The wing, the tailplane and vertical tail for being connected to afterbody, the tailplane and vertical tail are mutually perpendicular to；Described
Flight control system and airborne avionics system may be contained in fuselage；
The fixed-wing dynamical system includes to be set to the twin-tub two-cycle engine of front fuselage and be connected to double
Vertical propeller on cylinder two-cycle engine power output end；
The rotor power system includes there are two horizontally disposed flight support frame, is fixed on each flight support frame
On propeller driving motor and electricity adjust, with corresponding propeller driving motor output end connect horizontal propeller, the rotation
Wing supporting rack be connected on corresponding wing and and wing vertical, the propeller driving motor be four, any two
It is connected to the top at corresponding flight support frame both ends, the electricity is adjusted to be connect with the input terminal of propeller driving motor；
The power source system includes the power management module for being set to fuselage interior, lithium battery group and fuel tank,
And it is connected to the tear-away separable electric connector on fuselage bottom；The power supply of the tear-away separable electric connector is defeated
Outlet, lithium battery group are connect with power management module, and the power supply of ground power supply system and tear-away separable electric connector is defeated
Enter end connection, the described electric tune, the electricity generation module of twin-tub two-cycle engine, flight control system and airborne avionics system with
Power management module connects, and the power source input terminal of the twin-tub two-cycle engine is connect with fuel tank；Described takes off
Fall the fixing end and free end that separable electric connector includes connection, the fixing end be fixed on fuselage bottom and with electricity
Source control module connects, and the free end is connect by being tethered at cable with ground power supply system；
The twin-tub two-cycle engine, electric tune, power management module, airborne avionics system are and flight control system
Connection.
The fixing end of the tear-away separable electric connector is socket, free end is plug, and the socket includes
There are the insulation fixed pedestal being fixedly connected on fuselage bottom and contact pin and spring, plug is provided on the fixed pedestal that insulate
The bottom of nested troughs, plug nested troughs is provided with the interior convex block of protrusion, is provided with multiple jacks on interior convex block, in multiple jacks
It is provided with the contact pin being connect with power management module, the interior and periphery positioned at interior convex block of plug nested troughs is set with the bullet
Spring, the plug include the free pedestal of insulation, electromagnetism inserted sheet and electromagnetic coil, and it is embedding to be provided with socket on the free pedestal that insulate
Grooving, the bottoms of socket nested troughs are provided with the U-shaped slot of protrusion, electromagnetism inserted sheet be set to that the free pedestal of insulation is interior and outer end from
The bottom of U-shaped slot is stretched out, and electromagnetic coil is set to the periphery insulated in free pedestal and positioned at electromagnetism inserted sheet, the electromagnetism
Coil, electromagnetism inserted sheet be tethered at cable connection；When the plug and socket connects, electromagnetic coil is powered, electromagnetism inserted sheet tool
It is magnetic, the plug nested troughs of the U-shaped slot insertion socket of plug are located at the periphery of interior convex block and resist the spring, socket
Insulation fixed pedestal is located in the socket nested troughs of periphery insertion plug of plug nested troughs, and the electromagnetism inserted sheet of plug extend into slotting
It is connect in the jack of seat and with contact pin electromagnetic adsorption.
The bottom of the fuselage is equipped with undercarriage.
The pitot parallel with fuselage is provided on the wing, and Pitot-static tube is connected by tracheae and flight control system
It connects, the trailing edge is rotatably connected to aileron, and the tailplane rear is rotatably connected to lifting rudder face, described
Aileron and lifting rudder face are connect with flight control system.
The flight control system includes controller, the aviation attitude system that is connect respectively with controller, barometertic altimeter,
Pitot meter and GNSS locating modules, the pitot are connect with pitot meter by tracheae.
The airborne avionics system includes on-board data link radio station, the on-board data link radio station and ground
Data path radio station communication connection, ground data link radio station are connect with earth station system, ground data link radio station, earth station
System connect power supply with ground power supply system.
The front end of the vertical propeller is equipped with radome fairing.
The advantages of the utility model：
The utility model is using tear-away separable electric connector by being tethered at cable and ground during taking off
Power supply system is connected, and directly feeds the electric energy needed for rotor power system, and power is sufficient, ensures the power requirement of lift-off flight,
Payload is increased, stability and wind loading rating in more rotor work process are enhanced, it can be in ground power supply connection
Lower long-time floating reduces the maximum discharge-rate requirement of lithium battery group, enhances multi-rotor aerocraft and take off vertically and hang
The ability stopped（Surface power supply can hover for a long time）；The utility model stops surface power supply, tear-away Split type electric after lift-off
Connector can be automatically separated, and be powered using lithium battery group, since lift-off is not powered using lithium battery group, and it is vertical
Landing fixed-wing maximum take-off weight is limited to more rotor load abilities, also just increases the payload capability of complete machine, lithium electricity
Pond group need to only ensure more rotors and fixed-wing handoff procedure and descent electricity, reduce the weight of lithium battery group, in addition lithium
Battery weight and service life are restricted by maximum discharge-rate, and uphill process is powered using ground power supply, reduces lithium battery
Maximum discharge current needed for group further reduces the weight for carrying battery
In conclusion the utility model is more battery-powered than pure（Battery weight is calculated with 10 kilograms）VTOL it is solid
Determine wing unmanned plane, on-board batteries weight reduces 7 kilograms or so, and payload can be improved 9 kilograms or so, pure lithium electricity in take-off process
Group the power maximum wind loading rating of more rotors in pond can be increased to 15m/s from 12m/s.
The utility model combines rotor craft and the respective advantage of Fixed Wing AirVehicle, that is, utilizes surface power supply rotor
Dynamical system is taken off vertically, hovered and is landed, and cruise operation, tool are carried out using lithium battery group power supply fixed-wing dynamical system
There is the features such as landing space is small, cruising speed is big, voyage is remote, and endurance is long.
Description of the drawings
Fig. 1 is the vertical view of the utility model.
Fig. 2 is the side view of the utility model.
Fig. 3 is the structural schematic diagram of the tear-away separable electric connector socket of the utility model.
Fig. 4 is the structural schematic diagram of the tear-away separable electric connector plug of the utility model.
Fig. 5 is the principles of the present invention block diagram.
Specific implementation mode
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
See Fig. 1-Fig. 5, a kind of tear-away captive VTOL fixed-wing unmanned plane, includes fixed-wing structural system,
Fixed-wing dynamical system, rotor power system, power source system, flight control system and airborne avionics system；
Fixed-wing structural system includes that 1, two, fuselage is connected to 1 side of fuselage along the symmetrical wing of 1 axis of fuselage
2, it is connected to the tailplane 3 and vertical tail 4 of 1 tail portion of fuselage, tailplane 3 and vertical tail 4 are mutually perpendicular to, on wing 2
It is provided with the pitot 5 parallel with fuselage 1,2 rear of wing is rotatably connected to aileron 6, and 3 rear of tailplane is rotatably connected to
Rudder face 7 is lifted, the bottom of fuselage 1 is equipped with undercarriage 8；Flight control system 22 and airborne avionics system 23 may be contained within fuselage
In 1；
Fixed-wing dynamical system includes to be set to the twin-tub two-cycle engine 9 of 1 front end of fuselage and be connected to twin-tub two
The front end of vertical propeller 10 on 9 power output end of Stroke Engine, vertical propeller 10 is equipped with radome fairing 11；
Rotor power system includes there are two horizontally disposed flight support frame 12, is fixed on each flight support frame 12
Propeller driving motor 13 and electricity adjust 14, with corresponding 13 output end of propeller driving motor connect horizontal propeller 15, revolve
Wing supporting rack 12 be connected to it is on corresponding wing 2 and vertical with wing 2, propeller driving motor 13 be four, any two
It is connected to the top at corresponding 12 both ends of flight support frame, electricity adjusts 14 to be connect with the input terminal of propeller driving motor 13；
Power source system includes power management module 16, lithium battery group 18 and the fuel tank 19 being set to inside fuselage 1,
And it is connected to the tear-away separable electric connector 17 on 1 bottom of fuselage；The power supply of tear-away separable electric connector 17 is defeated
Outlet, lithium battery group 18 are connect with power management module 16, ground power supply system 20 and tear-away separable electric connector 17
Energization input connection, electricity adjusts the 14, electricity generation module 21 of twin-tub two-cycle engine 9, flight control system 22 and airborne boat
Electric system 23 is connect with power management module 16, and the power source input terminal of twin-tub two-cycle engine 9 is connect with fuel tank 19；
Wherein, tear-away separable electric connector 17 includes socket and plug, and socket includes to be fixedly connected on fuselage 1
Insulation fixed pedestal 701 and contact pin 702 on bottom and spring 703, insulate fixed pedestal 701 on be provided with plug nesting
The bottom of slot 704, plug nested troughs 704 is provided with the interior convex block 705 of protrusion, and multiple jacks 706 are provided on interior convex block 705,
The contact pin 702 being connect with power management module 16 is both provided in multiple jacks 706, plug nested troughs 704 are interior and are located at convex
The periphery of block 705 is set with spring 703, and plug includes the free pedestal 707 of insulation, electromagnetism inserted sheet 708 and electromagnetic coil 709,
Socket nested troughs 710 are provided on the free pedestal of insulation 707, the bottom of socket nested troughs 710 is provided with the U-shaped slot of protrusion
711, electromagnetism inserted sheet 708 is set in the free pedestal of insulation 707 and outer end is from the stretching of the bottom of U-shaped slot 711, electromagnetic coil
709 are set to the periphery for insulating in free pedestal 707 and being located at electromagnetism inserted sheet 708, electromagnetic coil 709, electromagnetism inserted sheet 708 with
It is tethered at the connection of cable 24；Plug and socket connect when, electromagnetic coil 709 be powered, electromagnetism inserted sheet 708 have magnetism, plug it is U-shaped
The plug nested troughs 704 that slot 711 is inserted into socket are located at the periphery of interior convex block 705 and resist spring 703, the fixed base of socket insulation
The periphery that seat 701 is located at plug nested troughs 704 is inserted into the socket nested troughs 710 of plug, and the electromagnetism inserted sheet 708 of plug is extend into
It is connect in the jack 706 of socket and with 702 electromagnetic adsorption of contact pin；When electromagnetic coil 709 powers off, electromagnetism inserted sheet 708 loses magnetism,
Spring 703 ejects the U-shaped slot 711 of plug, to which plug and socket detaches, plug and is tethered at cable 24 under the effect of gravity
It falls down, lithium battery group 18 continues through power management module 16 and is powered.
Aileron 6, lifting rudder face 7, twin-tub two-cycle engine 9, electricity adjust 14, power management module 16, airborne avionics system
23 connect realization with flight control system 22 is uniformly controlled.
Wherein, flight control system 22 includes controller 221, the aviation attitude system 222 that is connect respectively with controller 221,
Barometertic altimeter 223, pitot meter 224 and GNSS locating modules 225, pitot 5 are connect with pitot meter 224 by tracheae；It is airborne
Avionics system 23 includes on-board data link radio station 231, and on-board data link radio station 231 is logical with ground data link radio station 25
News connection, ground data link radio station 25 are connect with earth station system, and cooperation control unmanned plane executes task, ground number as required
According to link radio station 25, earth station system power supply is connect with ground power supply system 20.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is appreciated that can these embodiments be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaiied
Change, replace and modification, the scope of the utility model are defined by the appended claims and the equivalents thereof.
Claims (7)
1. a kind of tear-away captive VTOL fixed-wing unmanned plane, it is characterised in that：Include fixed-wing structural system, Gu
Determine wing dynamical system, rotor power system, power source system, flight control system and airborne avionics system；
The fixed-wing structural system include fuselage, two be connected to side-of-body along the symmetrical wing of fuselage axis,
It is connected to the tailplane and vertical tail of afterbody, the tailplane and vertical tail are mutually perpendicular to；Described flies
Row control system and airborne avionics system may be contained in fuselage；
The fixed-wing dynamical system includes to be set to the twin-tub two-cycle engine of front fuselage and be connected to twin-tub two
Vertical propeller on Stroke Engine power output end；
The rotor power system includes there are two horizontally disposed flight support frame, is fixed on each flight support frame
The horizontal propeller that propeller driving motor and electricity are adjusted, connected with corresponding propeller driving motor output end, the rotor branch
Support be connected on corresponding wing and and wing vertical, the propeller driving motor be four, any two difference
It is connected to the top at corresponding flight support frame both ends, the electricity is adjusted to be connect with the input terminal of propeller driving motor；
The power source system includes the power management module for being set to fuselage interior, lithium battery group and fuel tank, and
The tear-away separable electric connector being connected on fuselage bottom；The tear-away separable electric connector for electricity output
End, lithium battery group are connect with power management module, the supply input of ground power supply system and tear-away separable electric connector
End connection, the described electric tune, the electricity generation module of twin-tub two-cycle engine, flight control system and airborne avionics system with electricity
Source control module connects, and the power source input terminal of the twin-tub two-cycle engine is connect with fuel tank；Described is tear-away
Separable electric connector includes fixing end and the free end of connection, and the fixing end is fixed on fuselage bottom and and power supply
Management module connects, and the free end is connect by being tethered at cable with ground power supply system；
The twin-tub two-cycle engine, electric tunes, power management module, airborne avionics system with flight control system company
It connects.
2. a kind of tear-away captive VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：It is described
Tear-away separable electric connector fixing end be socket, free end is plug, the socket includes to be fixedly connected on
Insulation fixed pedestal and contact pin on fuselage bottom and spring, insulate fixed pedestal on be provided with plug nested troughs, plug is embedding
The bottom of grooving is provided with the interior convex block of protrusion, and multiple jacks are provided on interior convex block, is both provided in multiple jacks and power supply
The contact pin of management module connection, the interior and periphery positioned at interior convex block of plug nested troughs are set with the spring, the plug
Include the free pedestal of insulation, electromagnetism inserted sheet and electromagnetic coil, socket nested troughs are provided on the free pedestal that insulate, socket is nested
The bottom of slot is provided with the U-shaped slot of protrusion, and electromagnetism inserted sheet is set to that the free pedestal of insulation is interior and outer end is from the bottom of U-shaped slot
It stretches out, electromagnetic coil is set to the periphery insulated in free pedestal and positioned at electromagnetism inserted sheet, the electromagnetic coil, electromagnetism inserted sheet
Be tethered at cable connection；When the plug and socket connects, electromagnetic coil is powered, and electromagnetism inserted sheet has magnetism, the U of plug
The plug nested troughs that type slot is inserted into socket are located at the periphery of interior convex block and resist the spring, socket insulation fixed pedestal position
Be inserted into the socket nested troughs of plug in the periphery of plug nested troughs, the electromagnetism inserted sheet of plug extend into the jack of socket and with
Contact pin electromagnetic adsorption connects.
3. a kind of tear-away captive VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：It is described
The bottom of fuselage undercarriage is installed.
4. a kind of tear-away captive VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：It is described
Wing on be provided with the pitot parallel with fuselage, and Pitot-static tube is connect by tracheae with flight control system, the machine
Wing rear is rotatably connected to aileron, and the tailplane rear is rotatably connected to lifting rudder face, the aileron and lifting
Rudder face is connect with flight control system.
5. a kind of tear-away captive VTOL fixed-wing unmanned plane according to claim 4, it is characterised in that：It is described
Flight control system include controller, aviation attitude system, barometertic altimeter, pitot meter and the GNSS being connect respectively with controller
Locating module, the pitot are connect with pitot meter by tracheae.
6. a kind of tear-away captive VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：It is described
Airborne avionics system include on-board data link radio station, the on-board data link radio station and ground data link radio station
Communication connection, ground data link radio station connect with earth station system, and ground data link radio station, earth station system are and ground
Power supply system connection power supply.
7. a kind of tear-away captive VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：It is described
The front end of vertical propeller radome fairing is installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721835572.7U CN207759015U (en) | 2017-12-25 | 2017-12-25 | A kind of tear-away captive VTOL fixed-wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721835572.7U CN207759015U (en) | 2017-12-25 | 2017-12-25 | A kind of tear-away captive VTOL fixed-wing unmanned plane |
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| CN207759015U true CN207759015U (en) | 2018-08-24 |
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| CN201721835572.7U Active CN207759015U (en) | 2017-12-25 | 2017-12-25 | A kind of tear-away captive VTOL fixed-wing unmanned plane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111422351A (en) * | 2020-04-14 | 2020-07-17 | 中国人民解放军32180部队 | High-wind-resistance tail-cone type mooring unmanned aerial vehicle and flight control method thereof |
-
2017
- 2017-12-25 CN CN201721835572.7U patent/CN207759015U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111422351A (en) * | 2020-04-14 | 2020-07-17 | 中国人民解放军32180部队 | High-wind-resistance tail-cone type mooring unmanned aerial vehicle and flight control method thereof |
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