CN205469821U - Perpendicular or short take off and landing fixed wing aircraft - Google Patents
Perpendicular or short take off and landing fixed wing aircraft Download PDFInfo
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- CN205469821U CN205469821U CN201620027802.6U CN201620027802U CN205469821U CN 205469821 U CN205469821 U CN 205469821U CN 201620027802 U CN201620027802 U CN 201620027802U CN 205469821 U CN205469821 U CN 205469821U
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Abstract
The utility model discloses a perpendicular or short take off and landing fixed wing aircraft, including fuselage and wing, the wing includes the host computer wing, fin or the duck wing, the fin includes horizontal tail and vertical fin, its characterized in that be provided with the screw that a plurality of can vert on the host computer wing, fin and the duck wing respectively, each screw passes through steering mechanism and wing and links to each other, steering mechanism can with the aircraft plane of symmetry in - 10~110 vert in the parallel plane, the utility model discloses the pneumatic efficiency of aircraft main wing, also be exactly lift -to -drag than higher, structure burden is less, small -size screw adds the motor drive mode for the load of every oar is less, therefore can use comparatively simply, and cantilever beam type that the structure the is lighter mechanism of verting has reduced mechanism's weight, the security is higher, and after partial oar became invalid, safety influence was little to the complete machine.
Description
Technical field
The present invention relates to aircraft field, especially relate to a kind of V/STOL Fixed Wing AirVehicle.
Background technology
Helicopter compared by vertically/STOL fixed wing airplane, has flight speed fast, and the flight time is long, fuel-efficient
Advantage, compares fixed wing airplane, has landing convenient, shell hovering, it is not necessary to big airport and the advantage of long plane track.Cause
And this technology is constantly subjected to pay close attention to greatly, from the forties in last century, aeronautical chart carries out this technical research the most always,
But up to this point, the aircraft of volume production only osprey, Harrier, refined gram 141, F35 etc. is capable of vertical/short distance and rises
Fall, horizontal flight.When these aircrafts use VTOL mode, the lift of needs and power are big especially, so that dynamical system
System has the biggest weight, thus when significantly reducing flight, payload and boat.Technical identification machine aspect, aviation
This kind of aircraft studying 43 kinds of different models such as XV-3, X-22A, XC-124A, CL-84, " volt Bristol " 76 is sent out on boundary, but greatly
All ending in failure, only Bell Helicopter Company of the U.S. successfully have developed XV-3, XV-15, and on the basis of XV-15
Successfully develop military version " osprey " and civil version BA609 tiltrotor.After very long exploratory development, rotation of verting
Wing machine has put into actual application the most veritably.Harrier, refined gram 141, the turbojet power of the employing such as F35 turns
To and high-lift ducted fan scheme, its energy efficiency is the lowest, and the payload causing aircraft is the least, and oil consumption is too big, and uncomfortable
Share and make transporter use, be also not suitable for civil aircraft and use.
Can vert DCB Specimen technology side by side in the left and right that existing v22 osprey uses, v22 slightly installs two by the wing at main wing
The individual rotor turning 90 degrees that can incline provides lift when taking off and control moment, when flat flying, gradually by oar dish upward to
Before vert, produce pulling force forward so that aircraft accelerates, and after reaching certain speed, main wing can produce enough
Lift, this be lift oar dish forward, it is provided that pull strength, promote aircraft advance, empennage provide control moment, keep aircraft balanced and
Manipulation.
This technology has a following shortcoming:
When taking off vertically, wing remains in that level, and some area of oar dish is overlapping with wing so that oar dish lift quilt
Offset a part, reduce the efficiency of oar, increase power consumption；
Electromotor and dynamical system are arranged on the wing wing slightly, define a taper load and weight the biggest cantilever beam knot
Structure so that structure is very easy to shake, this is also the main cause that the technical identification machine of v22 early stage is failed, shake to be reduced
Dynamic, it is necessary for strengthening structure, thus can be greatly increased construction weight, with the aspect ratio of limit main wing；
Main wing pneumatic efficiency, namely lift-drag ratio is relatively low.Due to the restriction of layout type, the main wing aspect ratio of this scheme
Smaller, also allow for complete machine lift-drag ratio less, so can increase oil consumption, reduce voyage, though so this kind of flight
Bigger than helicopter, but much smaller than the conventional airplane of same level
This kind of aircraft is when employing is slided and taken off mode, and owing to blade is oversize, propeller cannot be fully seated to horizontal level,
So can limit the maximum take-off weight under its sliding race mode；
This aircraft, when using short distance rolling start, if takeoff speed is the lowest, then may cannot provide enough rudders because of empennage
Effect and cannot take off, so constraining it uses under short takeoff pattern, and minimum is taken off distance and flying speed.
Existing Canadair CL-84 Dynavert tiltrotor, the scheme that this aircraft uses is: two are started
Machine is contained in the middle part of wing, fixes with wing and is connected, and rotating mechanism is contained in fuselage and wing junction, and wing is together with electromotor one
Rise and rotate 0-90 °, install a lifting rotor upward additional at afterbody, in order to when taking off vertically or land simultaneously, it is provided that control
Moment processed.When taking off vertically, the direct half-twist of wing, the startup of main lift fan draws high aircraft, and the lift fan of afterbody carries simultaneously
For control moment, keep aircraft balanced.After lift-off, host wing is together with propeller steering horizontal direction, and aircraft proceeds to level
Offline mode.
This technology has a following shortcoming:
Whole wing rotates together with dynamical system, Stability Analysis of Structures to be kept, and this can make the weight of steering mechanism
It is significantly increased, thus can be greatly increased aero-structure weight；
Main wing verts together with dynamical system so that the flight force and moment suffered by aircraft changes non-in this process
The most complicated, the center of gravity of aircraft is also significantly changing simultaneously, and the control causing aircraft is extremely difficult；
This kind of aircraft is when employing is slided and taken off mode, and owing to blade is oversize, propeller cannot be fully seated to horizontal level,
So can limit the maximum take-off weight under its sliding race mode；
This aircraft, when using short distance rolling start, if takeoff speed is the lowest, then may cannot provide enough rudders because of empennage
Effect and cannot take off, so constraining it uses under short takeoff pattern, and minimum is taken off distance and flying speed.
The propeller of afterbody vertical direction, only has an effect during landing, after revert to level flight, causes complete machine pneumatic
Efficiency reduces, when affecting flight and boat.
Existing BELL X-22A tiltrotor, uses tandem double-vane layout, at front wing and the wingtip of rear wing
It is equipped with a ducted fan, total of four ducted fan.The afterbody of each ducted fan is also equipped with a rudder face, is used for providing
Control moment and once rising.Lift when taking off and control moment is provided by the wing 4 rotors turning 90 degrees that can incline slightly,
Flat when flying, gradually oar dish upward is tilted forward, produce pulling force forward so that aircraft accelerates, reaching certain speed
After, wing can produce enough lift, this be lift oar dish forward, it is provided that pull strength, promote aircraft advance, empennage carries
For control moment, keep aircraft balanced and manipulation.
This technology has a following shortcoming:
Electromotor and dynamical system are arranged on the wing wing slightly, define a taper load and weight the biggest cantilever beam knot
Structure so that structure is very easy to shake, this is also the main cause that the technical identification machine of X-22A early stage is failed, reduce
Vibrations, are necessary for strengthening structure, thus can be greatly increased construction weight, with the aspect ratio of limit main wing；
Main wing pneumatic efficiency, namely lift-drag ratio is relatively low.Due to the restriction of layout type, the main wing aspect ratio of this scheme
Smaller, also allow for complete machine lift-drag ratio less, so can increase oil consumption, reduce voyage, though so this kind of flight
Bigger than helicopter, but much smaller than the conventional airplane of same level
This kind of aircraft is when employing is slided and taken off mode, and owing to blade is oversize, propeller cannot be fully seated to horizontal level,
So can limit the maximum take-off weight under its sliding race mode；
This aircraft, when using short distance rolling start, if takeoff speed is the lowest, then may cannot provide enough rudders because of empennage
Effect and cannot take off, so constraining it uses under short takeoff pattern, and minimum is taken off distance and flying speed.
Summary of the invention
It is an object of the invention to provide a kind of V/STOL Fixed Wing AirVehicle, this aircraft can vertically or
STOL, when having again voyage farther out and longer boat.
To achieve these goals, the present invention adopts the following technical scheme that
A kind of V/STOL Fixed Wing AirVehicle, including fuselage, wing, propeller and electromotor, described wing
Including host wing, empennage and canard, described empennage includes horizontal tail and vertical fin；It is characterized in that described host wing, horizontal tail or canard,
Being respectively arranged with several propellers that can vert on vertical fin, each propeller is connected with wing by steering mechanism, turns to
Mechanism can vert in the range of-10 °～110 ° with propeller.Each propeller passes through one with corresponding steering mechanism
Independent motor drives.
In technique scheme, host wing is provided with the propeller being not less than four, horizontal tail, canard is provided with the lowest
In the propeller of two, vertical fin is provided with the propeller being not less than.
In technique scheme, the propeller on host wing, empennage and canard is symmetrical arranged along fuselage axis.
In technique scheme, vertical fin and the forward position of horizontal tail on described empennage arrange propeller.
In technique scheme, described propeller is arranged on the forward position of host wing or is arranged on the trailing edge of host wing.
In technique scheme, the tilt angle of each propeller described independently controls, non-interference.
In technique scheme, described propeller distance wing position be wing vert 90 ° time, described propeller
Oar dish is the most overlapping with wing.
In technique scheme, the slip-stream that propeller on host wing, empennage, canard produces each cover host wing,
Empennage, canard.
In technique scheme, the described mutually opposing rotation of adjacent propeller.
In technique scheme, described host wing uses super large aspect ratio layout, and described empennage uses high aspect ratio cloth
Office.
In sum, owing to have employed technique scheme, the invention has the beneficial effects as follows:
The pneumatic efficiency of aircraft main wing, namely lift-drag ratio is higher.Owing to this programme uses a fairly large number of small size spiral shell
Rotation oar replaces the large scale propeller of traditional scheme, and propeller is distributed on main wing front.Thus the aspect ratio of main wing is permissible
That does is bigger, and this lift-drag ratio that can directly result in main wing has a raising by a relatively large margin；
Structural burden is less.Multiple sizes are less, motor-driven propeller, are evenly distributed on main wing, bring
Vibrations and stress are all much smaller than double oars so that main wing can accomplish high aspect ratio, and without significantly reinforcing；
Small propeller adds motor drive mode so that the load of each oar is less, thus can use relatively simple, knot
The beam type inclining rotary mechanism that structure is lighter, reduces mechanism's weight；
When usual manner landing, owing to the high speed slip-stream of main oar substantially completely covers host wing, the high ski-running of auxiliary oar
Stream substantially completely covers empennage so that landing distance significantly can shorten than conventional airplane, and landing speed can be greatly reduced,
The most controllable；
When using short distance mode landing, owing to the high speed slip-stream of auxiliary oar substantially completely covers empennage, compare osprey mode,
There is higher driving efficiency, it is thus possible to take off with shorter distance；
By adjusting the rotating speed of main oar, direction etc. so that the slip-stream flowing through main wing provides more energy for main wing boundary-layer
Amount, postpones trailing edge and separates, and suppress wing-tip vortex induced drag so that the aeroperformance of main wing improves, and improves maximum lift and
Big lift-drag ratio, thus improve airplane synthetic performance.
Safety is higher, after part oar lost efficacy, little to complete machine security implication.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is the structural representation of the present invention；
Fig. 2 is VTOL pattern diagram；
Fig. 3 is STOL pattern diagram；
Wherein: 1 is horizontal tail, 2 is vertical fin, and 3 is steering mechanism, and 4 is tail-rotor, and 5 is main oar, and 6 is fuselage, and 7 is host wing, 8
It it is head.
Detailed description of the invention
The agent structure of the present invention is as shown in Fig. 1, and the host wing at aircraft is provided with 7, amounts to 14 spirals
Oar, horizontal tail is provided with 2, amounts to 4 propellers, vertical fin is provided with 2 propellers, by the rotational band of propeller
The lifting of dynamic aircraft and flight.
On host wing, the diameter of propeller, more than the propeller on empennage, is referred to as main oar.Main oar can be arranged on
The forward position of host wing, it is also possible to be arranged on the trailing edge of main frame, main oar is connected to the outfan of motor by a rotary shaft, by electricity
Machine output power drives main oar to rotate.
Same setting, empennage includes horizontal tail and vertical fin, the forward position of horizontal tail and vertical fin is provided with diameter less
Propeller, is referred to as tail-rotor.
Either on empennage or on host wing, the initial position of propeller is equal, and its axis is parallel with the axis of fuselage to be set
Put, each propeller with fuselage junction point for initial point in the parallel surface at the aircraft plane of symmetry ,-10～110 ° of scope introversions
Turn, when propeller distance wing position just make propeller incline turn 90 degrees time, its oar dish is the most overlapping with wing；In the present invention
Power mainly use turbogenerator to carry out generating electricity and then supply each motor, propeller uses pure electronic mode to be driven
Dynamic, thus realize the hybrid mode of whole aircraft, when improving voyage boat.
In the present invention, each motor and propeller are controlled by flight control, and control system can
With all of propeller of Synchronization Control, it is also possible to the single propeller of independent control, the control of propeller makes between propeller
Mutually non-interference, the most independently controlled.
This aircraft has three kinds of modes of taking off
1) using VTOL mode, when taking off, all propellers incline and turn 90 degrees so that propeller is positioned at above wing, electricity
Machine drives propeller rotational, produces enough lift and aircraft is gone up to the air, as shown in Figure 2.After entering certain altitude, propeller turning direction
Horizontal level, aircraft enters to put down and flies pattern；The process of landing is the most contrary.In take-off process, it is also possible to keep vertical fin and horizontal tail
On propeller remain as horizontal level, the air-flow that propeller produces flows through horizontal tail and vertical fin, and this is to use rudder
Control aircraft balanced, as shown in Figure 2.
2) very short takeoff and landing, main oar verts a specific angle, i.e. produces lift and produces again pulling force so that aircraft is quick
Slide.Tail-rotor also vert an angle or holding level constant, produce thrust, promote aircraft taxi.Tail-rotor produces simultaneously
High speed slip-stream, can be greatly improved the rudder effectiveness of horizontal tail and vertical fin, it is ensured that aircraft handling during short takeoff, such as Fig. 3
Shown in, as shown in Figure 3.
3) CTOL mode have maximum take-off weight, owing to the paddle size of this programme is less, oar dish completely to
Before be also not result in that blade gets to the situation on ground, it is possible to landing in a conventional manner, this landing mode is due to wing
Being covered by propellerslip with empennage almost all, therefore its landing distance still can be significantly smaller than conventional transport.
The invention is not limited in aforesaid detailed description of the invention.The present invention expands to any disclose in this manual
New feature or any new combination, and the arbitrary new method that discloses or the step of process or any new combination.
Claims (10)
1. a V/STOL Fixed Wing AirVehicle, including head (8), fuselage (6), wing, propeller (4,5) and send out
Motivation, described wing includes host wing (7), empennage and canard, and described empennage includes horizontal tail (1) and vertical fin (2)；It is characterized in that
Being respectively arranged with several propellers that can vert on described host wing, empennage and canard, each propeller is by turning to machine
Structure (3) is connected with wing, and steering mechanism can vert in the range of-10 °～110 ° with propeller.
A kind of V/STOL Fixed Wing AirVehicle the most according to claim 1, it is characterised in that host wing, flat
It is respectively arranged with the propeller being not less than two on tail, canard, vertical fin is provided with the propeller being not less than.
A kind of V/STOL Fixed Wing AirVehicle the most according to claim 2, it is characterised in that host wing, empennage
It is symmetrical arranged along fuselage axis with the propeller on canard.
A kind of V/STOL Fixed Wing AirVehicle the most according to claim 3, it is characterised in that on described empennage
Vertical fin and the forward position of horizontal tail propeller is set.
A kind of V/STOL Fixed Wing AirVehicle the most according to claim 3, it is characterised in that described propeller
It is arranged on the forward position of host wing or is arranged on the trailing edge of host wing.
6. according to the arbitrary described a kind of V/STOL Fixed Wing AirVehicle of Claims 1 to 5, it is characterised in that described
The tilt angle of each propeller can independently control, non-interference.
A kind of V/STOL Fixed Wing AirVehicle the most according to claim 6, it is characterised in that described propeller
Distance wing position be wing vert 90 ° time, the oar dish of described propeller is the most overlapping with wing.
A kind of V/STOL Fixed Wing AirVehicle the most according to claim 6, it is characterised in that host wing, tail
The slip-stream that propeller on the wing, canard produces each covers host wing, empennage, canard.
A kind of V/STOL Fixed Wing AirVehicle the most according to claim 6, it is characterised in that adjacent is described
The mutually opposing rotation of propeller.
A kind of V/STOL Fixed Wing AirVehicle the most according to claim 1, it is characterised in that described host wing
Using super large aspect ratio layout, described empennage uses high aspect ratio layout.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620027802.6U CN205469821U (en) | 2016-01-13 | 2016-01-13 | Perpendicular or short take off and landing fixed wing aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620027802.6U CN205469821U (en) | 2016-01-13 | 2016-01-13 | Perpendicular or short take off and landing fixed wing aircraft |
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| CN205469821U true CN205469821U (en) | 2016-08-17 |
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| CN201620027802.6U Active CN205469821U (en) | 2016-01-13 | 2016-01-13 | Perpendicular or short take off and landing fixed wing aircraft |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105460215A (en) * | 2016-01-13 | 2016-04-06 | 绵阳空天科技有限公司 | Fixed-wing air vehicle achieving vertical or short-distance take-off and landing |
| CN107585281A (en) * | 2016-07-07 | 2018-01-16 | 龙全洪 | Water surface aircraft |
| CN108058812A (en) * | 2018-01-02 | 2018-05-22 | 晨龙飞机（荆门）有限公司 | A kind of unmanned plane for possessing folded wing |
| CN112262075A (en) * | 2018-05-10 | 2021-01-22 | 杰欧比飞行有限公司 | Electric tilting rotor aircraft |
| 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 |
| CN112262075B (en) * | 2018-05-10 | 2024-04-12 | 杰欧比飞行有限公司 | Electric tilting rotor aircraft |
-
2016
- 2016-01-13 CN CN201620027802.6U patent/CN205469821U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105460215A (en) * | 2016-01-13 | 2016-04-06 | 绵阳空天科技有限公司 | Fixed-wing air vehicle achieving vertical or short-distance take-off and landing |
| CN107585281A (en) * | 2016-07-07 | 2018-01-16 | 龙全洪 | Water surface aircraft |
| CN108058812A (en) * | 2018-01-02 | 2018-05-22 | 晨龙飞机（荆门）有限公司 | A kind of unmanned plane for possessing folded wing |
| CN112262075A (en) * | 2018-05-10 | 2021-01-22 | 杰欧比飞行有限公司 | Electric tilting rotor aircraft |
| CN112262075B (en) * | 2018-05-10 | 2024-04-12 | 杰欧比飞行有限公司 | Electric tilting rotor aircraft |
| 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 |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190109 Address after: 710000 No. 2 Fu067, Chang'an South Road, Yanta District, Xi'an City, Shaanxi Province Patentee after: Li Haigang Address before: Room 324, Incubator D, Incubator Service Center, Kechuang Park, Mianyang City, Sichuan Province, 621000 Patentee before: MIANYANG KONGTIAN TECHNOLOGY CO., LTD. |