CN208377055U - A kind of Fixed Wing AirVehicle - Google Patents
A kind of Fixed Wing AirVehicle Download PDFInfo
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- CN208377055U CN208377055U CN201820803644.8U CN201820803644U CN208377055U CN 208377055 U CN208377055 U CN 208377055U CN 201820803644 U CN201820803644 U CN 201820803644U CN 208377055 U CN208377055 U CN 208377055U
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- supporting rod
- tail supporting
- wing
- fixed wing
- fuselage
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Abstract
The utility model discloses a kind of Fixed Wing AirVehicles, comprising: fuselage；Main wing is installed on the fuselage；2 tail supporting rods, are installed on the middle part of the main wing；Empennage is installed on to the tail portion of the tail supporting rod；2 generate the preceding Power Component of upward pulling force or forward pulling force, are respectively arranged in the head of 2 tail supporting rods；N generates the rear Power Component of upward pulling force, is installed on the middle part of the tail supporting rod；Wherein n is positive even numbers, n >=2.The aircraft with VTOL, hovering, can enrich applicable place and the job content of aircraft；Tail supporting rod replaces fuselage connection empennage and main wing, reduces body volume, while Power Component being mounted on tail supporting rod reduces Power Component installation bring supernumerary structure.
Description
Technical field
The utility model relates to aircraft fields, can be with the Fixed Wing AirVehicle of VTOL more particularly to one kind.
Background technique
Fixed Wing AirVehicle has the characteristics that continuation of the journey is strong, load-carrying is big, flight is fast, but Fixed Wing AirVehicle needs runway to carry out
Landing, and turning radius is big in its flight course and can not hover, and seriously limits its use scope, user's flight experience is poor.
Multi-rotor aerocraft has the characteristics that flight operation is flexible, can limit with VTOL and control hovering place
It is smaller, more air taskings can be completed.But its flight efficiency is low, and load factor is small, and complicated feature of flying seriously constrains
Its load capacity and flight time.
The advantages of how making Flight Vehicle Design have both Fixed Wing AirVehicle and multi-rotor aerocraft is that current industry emphasis is ground
One of direction studied carefully.
Utility model content
To solve the above problems, the utility model discloses a kind of Fixed Wing AirVehicles, comprising: fuselage；Main wing is installed on
The fuselage；2 are parallel to the tail supporting rod of the fuselage axis, are installed on the middle part of the main wing；Empennage is installed on to the tail supporting rod
Tail portion；2 generate the preceding Power Component of upward pulling force or forward pulling force, are respectively arranged in the head of 2 tail supporting rods；N production
The rear Power Component of raw upward pulling force, is installed on the middle part of the tail supporting rod；Wherein n is positive even numbers, n >=2.The preceding Power Component packet
Include the preceding rotor, the preceding driving assembly for driving the preceding rotor, the component that verts for controlling direction of pull for generating pulling force, the wherein preceding rotation
The wing is connected to the preceding driving assembly, which is connected to the head of the tail supporting rod by the component that verts.The rear power
Component includes the rear rotor for generating upward pulling force, the rear driving assembly for driving the rear rotor, after wherein the rear rotor is connected to this
Driving assembly, the rear driving assembly are installed on the middle part of the tail supporting rod；Undercarriage is installed on bottom or the tail supporting rod of the fuselage
Bottom.
Further, further include winglet, be installed on the main wing wingtip.
Preferably, which is the empennage of falling V or twin vertical fin.
Preferably, which is the straight wing.
Preferably, aileron is installed on the outside of the wingtip rear of the main wing.
Preferably, which is equipped with movable rudder face
Preferably, which is streamlined.
The utility model combines the advantages of Fixed Wing AirVehicle and multi-rotor aerocraft, can be with VTOL, in the air
Hovering, enriches applicable place and the job content of aircraft；Autonomous optimization design aerofoil profile, fusion type winglet are streamlined
Fuselage is greatly improved pneumatic efficiency, increases the flight time；Tail supporting rod replaces fuselage connection empennage and main wing, reduces fuselage
Volume, while rotor assemblies being mounted on tail supporting rod reduce rotor assemblies installation bring supernumerary structure；The empennage of falling V has both
Vertical fin horizontal tail function, reduces construction weight, improves load capacity.
Detailed description of the invention
Structure chart when Fig. 1 is a kind of Fixed Wing AirVehicle VTOL state of the utility model embodiment.
Fig. 2 is a kind of Fixed Wing AirVehicle level flight condition schematic diagram of the utility model embodiment.
Wherein appended drawing reference are as follows:
1: fuselage 2: main wing 21: winglet
22: aileron 3: empennage 31: movable rudder face
4: undercarriage 5: tail supporting rod 6: preceding Power Component
61: preceding rotor 62: preceding driving assembly 63: vert component
7: rear Power Component 71: rear rotor 72: rear driving assembly
Specific embodiment
Specific embodiment of the present utility model is further described in detail with reference to the accompanying drawing, described reality
Applying example is only an embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention,
Those of ordinary skill in the art's all other embodiment obtained under that premise of not paying creative labor, belongs to this reality
With novel protection scope.
The utility model, which provides one kind, to have both Fixed Wing AirVehicle and more rotors with the Fixed Wing AirVehicle of VTOL
The advantage of aircraft has the ability of VTOL, low to landing site's requirement, is not necessarily to runway, and flight efficiency is high in the sky,
Load-carrying is big, can be in designated flying zone hovering operation, and has Fast Installation ability, is convenient for carrying transport.
Fig. 1 is a kind of Fixed Wing AirVehicle structural schematic diagram of the utility model embodiment.As shown in Figure 1, this is practical new
The aircraft of type embodiment includes body and the Power Component that is mounted on body, wherein body includes fuselage 1, main wing 2, tail
The wing 3, undercarriage 4, tail supporting rod 5.The aircraft of the utility model uses high mounted wing configuration, and main wing 2 is fixedly connected on 1 middle part of fuselage
And close to 1 top position of fuselage, main wing 2 is the straight wing, and aileron 22, the installation of 2 wingtip of main wing are equipped on the outside of 2 wingtip rear of main wing
There is fusion type winglet 21, winglet 21 increases effective aspect ratio of main wing 2, and weakens main wing 2 by dissipation effect
Wingtip vortex, reduce the induced drag of aircraft；Two tail supporting rods 5 are respectively arranged in the middle part of left and right main wing 2, and along fuselage 1
Axis direction extends back, and to support empennage 3, in the embodiments of the present invention, empennage 3 uses the empennage of falling V, the empennage of falling V
Be installed on the tail portion of tail supporting rod 5, the rear for the empennage of falling V is equipped with movable rudder face 31, the empennage of falling V have both common fixed-wing vertical fin with
The function of horizontal tail, construction weight is small, and control efficiency is high；Empennage 3 can also be using twin vertical fin or the empennage of other configurations, this is practical
It is novel to be not limited thereto；Undercarriage 4 is installed on fuselage 1 or tail supporting rod 5, and the Fixed Wing AirVehicle of the utility model embodiment is logical
Frequently with vertical mode landing, therefore undercarriage 4 can be using e.g. stent-type, Sledge type or other configurations, can also be uneasy
Undercarriage 4 is filled, and is landed in the form of ventral, parachute, air bag or arresting net etc., above-mentioned aircraft landing technology is common skill
Art, details are not described herein again.
The Power Component of the Fixed Wing AirVehicle of the utility model embodiment includes power after 2 preceding Power Components 6 and 2
Component 7, wherein preceding Power Component 6 includes preceding rotor 61, preceding driving assembly 62 and the component 63 that verts, preceding rotor 61 is installed on forerunner
Dynamic component 62, preceding driving assembly 62 are installed on the head of tail supporting rod 5 by the component 63 that verts；Preceding rotor 61 passes through preceding driving assembly
62 driving high speed rotation, rotor 61 accelerates backward before air-flow flows through, thus the generation of rotor 61 pulling force before making, and the component 63 that verts
Upward or forward pulling force is then generated to control preceding rotor 61 by the power output direction of driving assembly 62 before controlling；Power afterwards
Component 7 includes rear rotor 71 and rear driving assembly 72, and rear rotor 71 is installed on rear driving assembly 72, and rear driving assembly 72 is installed on
The middle and back of tail supporting rod 5, rear rotor 71 by the driving high speed rotation of rear driving assembly 72, air-flow flow through rear rotor 71 accelerate to
Under, so that rear rotor 71 be made to generate upward pulling force, and when current power component 6 generates upward pulling force, rear Power Component 7 is opened
Beginning work；When current power component 6 generates forward pulling force, rear Power Component 7 stops working.The utility model embodiment flies
The Power Component of row device can also use other power modes, e.g. jet engine or ducted fan；Or use electric power storage
The modes such as pond, solar battery or fuel oil provide the energy；For improve aircraft VTOL performance, can also install it is multiple after
Power Component 7, the utility model is not limited thereto.
The Fixed Wing AirVehicle of the utility model embodiment carries out flight operation in the following manner:
(1) take off: preceding rotor 61 generates pulling force vertically upward with preceding driving assembly 62 under the control for the component 63 that verts,
And rear rotor 71 also generates pulling force vertically upward with rear driving assembly 72, pulling force resultant force overcomes aircraft gravity, makes to fly
Device takes off vertically；The state of preceding Power Component 6 is as shown in Figure 1 at this time；
(2) put down and fly: aircraft is after reaching predetermined altitude, and the component 63 that verts of preceding Power Component 6 is by preceding rotor 61 with before
Driving assembly 62, which inclines, to be turn 90 degrees, and rotor 61 generates the forward pulling force parallel with fuselage axis direction before making, as shown in Figure 2.?
When flat winged, preceding rotor 61 is driven by preceding driving assembly 62, high speed rotation, makes to accelerate backward, to obtain by the air-flow of preceding rotor 61
Forward pulling force, so that aircraft bring resistance so that aircraft obtains level speed, put down by main wing 2 when overcoming flat fly
Lift is generated after degree at full speed to overcome aircraft gravity, rear Power Component 7 stops working in flat fly into after equalling winged state；
(3) land: preceding rotor 61 replys takeoff condition under the control for the component 63 that verts with preceding driving assembly 62 again, produces
Raw pulling force vertically upward；And rear rotor 71 also generates pulling force vertically upward with rear driving assembly 72, pulling force resultant force makes whole
Machine slowly vertically declines, until falling to the ground.
The Fixed Wing AirVehicle of the utility model embodiment, compared with existing Fixed Wing AirVehicle or rotor craft,
With VTOL, hovering, applicable place and the job content of aircraft can be enriched；Autonomous optimization design aerofoil profile, fusion
Formula winglet, streamline fuselage are greatly improved pneumatic efficiency, increase the flight time；Fuselage is replaced to connect tail with tail supporting rod
The wing and main wing reduce body volume, while Power Component being mounted on tail supporting rod reduce Power Component installation bring
Supernumerary structure；The empennage of falling V has both vertical fin horizontal tail function, reduces construction weight, improves load capacity.
The description of the utility model and application be it is illustrative, be not wishing to for the scope of the utility model to be limited in above-mentioned reality
It applies in example.The deformation and change of embodiments disclosed herein be it is possible, for those skilled in the art come
The replacement and equivalent various parts for saying embodiment are well known.It will be apparent to those skilled in the art that practical not departing from
In the case where novel spirit or essential characteristics, the utility model can in other forms, structure, arrangement, ratio, and use it
Its component, material and component are realized.In this way, if these modifications and variations of the present invention belong to the utility model right
It is required that and its within the scope of equivalent technologies, then the utility model is also intended to include these modifications and variations.
Claims (10)
1. a kind of Fixed Wing AirVehicle characterized by comprising fuselage；Main wing is installed on the fuselage；2 are parallel to the fuselage
The tail supporting rod of axis is installed on the middle part of the main wing；Empennage is installed on the tail portion of the tail supporting rod；2 generate upward pulling force or to
The preceding Power Component of preceding pulling force, is respectively arranged in the head of the tail supporting rod；N generates the rear Power Component of upward pulling force, installation
In the middle part of the tail supporting rod；Wherein n is positive even numbers, n >=2.
2. Fixed Wing AirVehicle as described in claim 1, which is characterized in that the preceding Power Component includes the preceding rotation for generating pulling force
The wing, the preceding driving assembly for driving the preceding rotor, the component that verts for controlling direction of pull, wherein the preceding rotor is connected to the preceding driving
Component, the preceding driving assembly are connected to the head of the tail supporting rod by the component that verts.
3. Fixed Wing AirVehicle as described in claim 1, which is characterized in that the rear Power Component includes generating upward pulling force
Afterwards rotor, drive the rear drive equipment of the rear rotor, wherein the rear rotor is connected to the rear driving assembly, rear driving assembly peace
Middle part loaded on the tail supporting rod.
4. Fixed Wing AirVehicle as described in claim 1, which is characterized in that further include undercarriage, be installed on the bottom of the fuselage
Portion or the bottom of the tail supporting rod.
5. Fixed Wing AirVehicle as described in claim 1, which is characterized in that further include winglet, be installed on the main wing wing
The tip.
6. Fixed Wing AirVehicle as described in claim 1, which is characterized in that the empennage is the empennage of falling V or twin vertical fin.
7. Fixed Wing AirVehicle as described in claim 1, which is characterized in that the main wing is the straight wing.
8. Fixed Wing AirVehicle as claimed in claim 7, which is characterized in that be equipped with pair on the outside of the wingtip rear of the main wing
The wing.
9. Fixed Wing AirVehicle as described in claim 1 or 6, which is characterized in that the empennage is equipped with movable rudder face.
10. Fixed Wing AirVehicle as described in claim 1, which is characterized in that the fuselage is streamlined.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820803644.8U CN208377055U (en) | 2018-05-28 | 2018-05-28 | A kind of Fixed Wing AirVehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820803644.8U CN208377055U (en) | 2018-05-28 | 2018-05-28 | A kind of Fixed Wing AirVehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208377055U true CN208377055U (en) | 2019-01-15 |
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ID=64969204
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820803644.8U Active CN208377055U (en) | 2018-05-28 | 2018-05-28 | A kind of Fixed Wing AirVehicle |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573013A (en) * | 2019-01-24 | 2019-04-05 | 猎鸢科技(厦门)有限公司 | A kind of unmanned plane and its flying method based on multi-composite type dynamical system |
| CN110109472A (en) * | 2019-04-25 | 2019-08-09 | 广州笨笨网络科技有限公司 | A kind of unmanned aerial vehicle (UAV) control method, system, terminal and unmanned plane |
| CN112896499A (en) * | 2021-03-08 | 2021-06-04 | 四川腾盾科技有限公司 | Vertical take-off and landing aircraft with combined layout of tilting duct and fixed propeller |
| CN112896500A (en) * | 2021-03-08 | 2021-06-04 | 四川腾盾科技有限公司 | Aircraft with four ducts in tilting layout |
| CN116968919A (en) * | 2023-09-19 | 2023-10-31 | 上海柘飞航空科技有限公司 | Vertical take-off and landing aircraft with tilting power system and control method thereof |
-
2018
- 2018-05-28 CN CN201820803644.8U patent/CN208377055U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573013A (en) * | 2019-01-24 | 2019-04-05 | 猎鸢科技(厦门)有限公司 | A kind of unmanned plane and its flying method based on multi-composite type dynamical system |
| CN110109472A (en) * | 2019-04-25 | 2019-08-09 | 广州笨笨网络科技有限公司 | A kind of unmanned aerial vehicle (UAV) control method, system, terminal and unmanned plane |
| CN112896499A (en) * | 2021-03-08 | 2021-06-04 | 四川腾盾科技有限公司 | Vertical take-off and landing aircraft with combined layout of tilting duct and fixed propeller |
| CN112896500A (en) * | 2021-03-08 | 2021-06-04 | 四川腾盾科技有限公司 | Aircraft with four ducts in tilting layout |
| CN116968919A (en) * | 2023-09-19 | 2023-10-31 | 上海柘飞航空科技有限公司 | Vertical take-off and landing aircraft with tilting power system and control method thereof |
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