CN108545182A - A kind of VTOL fixed-wing unmanned plane - Google Patents
A kind of VTOL fixed-wing unmanned plane Download PDFInfo
- Publication number
- CN108545182A CN108545182A CN201810194748.8A CN201810194748A CN108545182A CN 108545182 A CN108545182 A CN 108545182A CN 201810194748 A CN201810194748 A CN 201810194748A CN 108545182 A CN108545182 A CN 108545182A
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- unmanned plane
- fuselage
- wing
- rotor
- wing unmanned
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of VTOL fixed-wing unmanned plane, the unmanned plane includes fuselage, wing, the first dynamical system, the second dynamical system, support device and avionics cabin.The unmanned plane verts to rotor by regulating mechanism completion of verting during VTOL, unmanned plane is allow more flexibly to complete landing, simultaneously, support device plays good supporting role to the fuselage after landing, fuselage is allow to complete descending operation perpendicular to ground, floor space is small, and landing is convenient.It when unmanned plane is in state of flight, is mainly flown using wing, and pose adjustment is completed by the elevon of trailing edge position, to ensure that the speed of a ship or plane of flight course.Compared to existing fixed-wing unmanned plane and rotary wind type unmanned plane, the advantages of unmanned plane of the invention both combines well, there is the problems such as facilitating landing, the speed of a ship or plane fast, easy to use, meet increasingly complicated task needs, have a vast market foreground.
Description
Technical field
The present invention relates to unmanned plane field more particularly to a kind of VTOL fixed-wing unmanned planes.
Background technology
Unmanned plane (UAV) has many advantages, such as inexpensive, high efficiency-cost ratio, easy to use, thus in military, civil field
It is obtained for and is widely applied.According to unmanned plane during flying principle, unmanned plane can be divided into fixed-wing unmanned plane and rotor wing unmanned aerial vehicle (packet
Include helicopter and more rotors).
The advantages of fixed-wing unmanned plane, is that speed is fast, endurance is long, with the obvious advantage in a wide range of field of operation, but fixed-wing without
Man-machine landing is relatively difficult, for using the sliding unmanned plane for running landing mode, needs to match runway, for using ejection and
For the unmanned plane of parachuting mode, more ancillary equipment is needed, and is difficult to accomplish recycle without damage, therefore fixed-wing unmanned plane
Application range is by more limitation.
Rotor wing unmanned aerial vehicle have the function of VTOL, it is easy to use, can be with spot hover and good low-speed maneuver etc.
Feature, thus be widely used in executing many particular tasks, for example power-line patrolling or take photo by plane.But rotor wing unmanned aerial vehicle there is also
Following disadvantage：Flying speed and flight efficiency are low, and voyage is short, are not suitable for large area operation task.
To sum up, in order to adapt to increasingly complicated task, there is an urgent need to a kind of vertical take-off and landing drone, take into account above two without
Man-machine advantage so that this unmanned plane can as fixed-wing unmanned plane high speed level cruise and with the image rotation wing nobody
The same VTOL of machine, spot hover and low-speed stable flight.
Invention content
For this reason, it may be necessary to a kind of VTOL fixed-wing unmanned plane be provided, to solve existing fixed-wing unmanned plane landing
Difficult, the mobility difference and rotary wind type unmanned plane speed of a ship or plane is slow, voyage is short cannot be satisfied asking for the increasingly complex task demand of executing
Topic.
To achieve the above object, a kind of VTOL fixed-wing unmanned plane is inventor provided, there is fuselage, feature to exist
In, including：
Wing, the wing are set to the opposite sides of the fuselage；
First dynamical system, including the first driving unit, rotor and the regulating mechanism that verts；First driving unit and rotation
The wing is sequentially connected, for driving rotor rotational；The regulating mechanism that verts is connect with rotor, for adjusting rotor compared to level
The angle of inclination of line；The rotor and fuselage are coaxial, and are set to the front end of fuselage, including the first oppositely arranged rotor and
Second rotor；
Second dynamical system, including the second driving unit and at least a pair of of elevon, second driving unit and liter
It drops aileron to be sequentially connected, each pair of elevon is symmetrically disposed on the posterior border position of the wing；
Support device is connected to the rear end of the fuselage, is used to support the fuselage of the state of taking off vertically or state of landing；
Avionics cabin, is set to the fuselage interior, including control system, and the control system is single with the first driving respectively
Member, the connection of adjustment structure of verting, the second driving unit.
Further, further include：
Load cabin is set to the fuselage interior, and between avionics cabin and front end, light is provided in the load cabin
Electric load interface；It is additionally provided with window in the load cabin, radical occlusion device is provided at window, the radical occlusion device can be opposite
It is moved in the window, for closing or opening the window.
Further, further include：
Empennage, the empennage are vertically installed in the tail portion of fuselage, and the tail portion of the fuselage is located at wing position and rear end
Between.
Further, further include：
Rudder, the rudder is set to the posterior border position of empennage, and can be swung relative to the empennage.
Further, the mode of the rear end of the support device and fuselage connection is to be detachably connected.
Further, the fuselage is additionally provided with locating interface, and the locating interface is set to fuselage back.
Further, the fuselage is additionally provided with number and passes or scheme to pass interface, and the number passes or figure biography interface is set to fuselage
Abdomen.
Further, the wing is aft swept wings, and the aspect ratio of wing is not less than default value.
Further, first driving unit is piston engine or turboaxle motor.
Further, second driving unit is electric steering engine.
The present invention provides a kind of VTOL fixed-wing unmanned plane, the unmanned plane includes fuselage, wing, the first power
System, the second dynamical system, support device and avionics cabin.The unmanned plane is complete by the regulating mechanism that verts during VTOL
Pairs of rotor verts so that and unmanned plane more can flexibly complete landing, meanwhile, support device plays the fuselage after landing
To good supporting role so that fuselage can complete descending operation perpendicular to ground, and floor space is small, and landing is convenient.Work as nothing
It is man-machine when being in state of flight, it mainly flies using wing, and the elevon completion posture of dependence trailing edge position
Adjustment, to ensure that the speed of a ship or plane of flight course.It is of the invention compared to existing fixed-wing unmanned plane and rotary wind type unmanned plane
Unmanned plane combines the advantages of the two well, has the problems such as facilitating landing, the speed of a ship or plane fast, easy to use, meets increasingly multiple
Miscellaneous task needs, and has a vast market foreground.
Description of the drawings
Fig. 1 is the structural schematic diagram for the VTOL fixed-wing unmanned plane that one embodiment of the invention is related to；
Fig. 2 is the attitudes vibration figure for the VTOL fixed-wing unmanned plane lifting process that one embodiment of the invention is related to；
Reference numeral：
1, rotor；2, fuselage；3, wing；4, empennage；5, elevon；6, rudder；7, load cabin；8, avionics cabin；9、
Fuel tank；10, support device.
Specific implementation mode
It, below will be according to invention to keep the practical purpose, implementer's case, scheme advantage of patent of the present invention clearer
Patent accompanying drawing refines this patent specific embodiment.In the accompanying drawings, described embodiment is a part of the invention
Embodiment, instead of all the embodiments.The embodiment of attached drawing description is exemplary, it is intended to for explaining the present invention, without
It can be interpreted as limitation of the present invention.Based on the embodiment, those of ordinary skill in the art are not before making creative work
The every other embodiment obtained is put, shall fall within the protection scope of the present invention.The present embodiment is carried out below in conjunction with the accompanying drawings
It is described in detail.
In the description of the present invention, it is to be understood that, term "front", "rear", "left", "right", "vertical", "horizontal",
The orientation or positional relationship of the instructions such as "top", "bottom" "inner", "outside" be based on the orientation or positional relationship shown in the drawings, be only for
Convenient for the description present invention and simplify description, specific side must be had by not indicating or implying the indicated device or element
Position, with specific azimuth configuration and operation, therefore should not be understood as limiting the scope of the invention.
Referring to Fig. 1, the structural schematic diagram for the VTOL fixed-wing unmanned plane being related to for one embodiment of the invention.It is described
Unmanned plane includes：
Fuselage 2 mainly loads body for unmanned plane, and engine is installed in front end, and interlude is avionics cabin 8, interlude both sides
For fuel tank 9 and both sides wing 3, tail portion is vertical tail 4 and support device 10.Underbelly trepanning is the window of load cabin 7.
In the present embodiment, the fuselage is additionally provided with locating interface, and the locating interface is set to fuselage back.The fuselage is also
It is provided with number and passes or scheme to pass interface, the number passes or figure biography interface is set to belly.The locating interface is used for and positioning
Device connects, and positioning device can be GPS positioning device, Big Dipper positioning device etc..
Wing 3, the wing 3 are set to the opposite sides of the fuselage 2.Wing is that unmanned plane fixed-wing pattern (flies
Row pattern) under prevailing lift component.In the present embodiment, the wing 3 is aft swept wings, and the aspect ratio of wing is not low
In default value.Wing 3 is laid out using high aspect ratio swept-back, be can effectively improve unmanned plane lift resistance ratio, is allowed to have higher
Cruising speed and longer endurance.
First dynamical system, including the first driving unit, rotor 1 and the regulating mechanism that verts；First driving unit with
Rotary-wing transmission connects, for driving rotor rotational；The regulating mechanism that verts is connect with rotor, for adjusting rotor compared to water
The angle of inclination of horizontal line；The rotor and fuselage are coaxial, and are set to the front end of fuselage, including the first oppositely arranged rotor
With the second rotor, the first rotor and the second rotor are two leaves or upper leaf.In the present embodiment, first driving unit is to live
Piston engine or turboaxle motor.
Second dynamical system, including the second driving unit and at least a pair of of elevon 5, second driving unit and liter
It drops aileron 5 to be sequentially connected, each pair of elevon includes two elevons, is symmetrically arranged in the rear position of the wing
It sets.In the present embodiment, second driving unit is electric steering engine.In the present embodiment, the elevon is more
Right, the elevon positioned at the same side wing is driven by an electric steering engine.
Support device 10 is connected to the rear end of the fuselage 2, is used to support the machine of the state of taking off vertically or state of landing
Body.As shown in Figure 1, in the present embodiment, the support device includes that two connecting rods being mutually parallel and two are mutual
The parallel bar that contacts to earth, connecting rod is connected in the rear end of fuselage, including head rod and the second connecting rod；The bar that contacts to earth includes the
One bar and second that contacts to earth contacts to earth bar.Head rod and the end of the second connecting rod are bent downwardly, and first contacts to earth bar respectively with
The first end connection of the first end of one connecting rod, the second connecting rod；Second contact to earth bar respectively with the second connecting rod second
The second end connection of end, the second connecting rod.First contact to earth bar and second contact to earth bar edge be upturned.In this embodiment party
In formula, the mode of the rear end connection of the support device and fuselage is to be detachably connected, and is damaged to work as support device
When, it can be carried out to be individually replaced repair, reduce maintenance cost.
Avionics cabin 8 is set to the fuselage interior, including control system, and the control system is single with the first driving respectively
Member, the connection of adjustment structure of verting, the second driving unit.The control system includes the automatic pilot of unmanned plane, airborne power supply
System is commander's maincenter of entire UAV system, has the acquisition of UAV Attitude location information, unmanned aerial vehicle (UAV) control instruction solution
The functions such as calculation, Ground Control Information obtain, flight information passes down, airborne equipment control.
In certain embodiments, the unmanned plane further includes：
Load cabin 7 is set to the fuselage interior, between avionics cabin and front end, is provided in the load cabin
O-E Payload interface；It is additionally provided with window in the load cabin, radical occlusion device is provided at window, the radical occlusion device being capable of phase
The window is moved, for closing or opening the window.Preferably, the shape of radical occlusion device and the shape of window are mutually fitted
Match, radical occlusion device can be moved to described the window's position under control of the control system, to seal window, in unmanned plane landing
Or it is not required to during load operation, effective protection load can be played the role of and improves aerodynamic characteristic for fuselage.
Empennage 4, the empennage are vertically installed in the tail portion of fuselage, and the tail portion of the fuselage is located at wing position and rear end
Between.Empennage can be used for increasing the horizontal shipping-direction stability under unmanned plane fixed-wing pattern, to ensure unmanned plane smooth flight.
Rudder 6, the rudder is set to the posterior border position of empennage, and can be swung relative to the empennage.Direction
Rudder is controlled by control system, can be used to that elevon is coordinated to carry out coordinate turn.
As shown in Fig. 2, the posture change for the VTOL fixed-wing unmanned plane lifting process being related to for one embodiment of the invention
Change figure.
Unmanned plane is located at two rotors in front fuselage portion under the effect of the first driving unit in take-off process, and one positive one
Reverse rotation provides lift, while control system controls UAV Attitude, it is made to keep plumbness；In transfer process (i.e. from vertical
Go straight up to drop and be converted into horizontal flight) in, control system by vert adjustment structure control rotor vert so that direction of pull by
It gradually turns forward upwards, to pulling force before generating, and then unmanned plane is made to obtain horizontal acceleration, in the process, the appearance of rotor
State control action gradually weakens, and the gesture stability effect of fixed-wing (i.e. wing) gradually increases；After revert to level flight, dynamical system is only
It is responsible for no longer providing gesture stability torque to pulling force before providing；Descent executes above-mentioned reversed handoff procedure, realizes vertical drop
It falls.
It takes off vertically in unmanned plane in the handoff procedure that turns to put down and fly, with the increase of unmanned plane speed, elevon is to nothing
Man-machine pitching and roll attitude control action gradually increases.During unmanned plane is flat winged, unmanned plane pitching and roll attitude
Only controlled by elevon；Flat to fly during turning vertical landing, the gesture stability effect of elevon reduces with flying speed
And it gradually reduces.The instruction for the pitch channel and roll channel that elevon instruction is sent out by autopilot is formed by stacking, and pitching is logical
Road instruction makes the equidirectional deflection of both sides elevon, roll channel instruction that both sides elevon negative direction be made to deflect, two channels
Instruction is superposed to last deflection angle.
The present invention provides a kind of VTOL fixed-wing unmanned plane, the unmanned plane includes fuselage, wing, the first power
System, the second dynamical system, support device and avionics cabin.The unmanned plane is complete by the regulating mechanism that verts during VTOL
Pairs of rotor verts so that and unmanned plane more can flexibly complete landing, meanwhile, support device plays the fuselage after landing
To good supporting role so that fuselage can complete descending operation perpendicular to ground, and floor space is small, and landing is convenient.Work as nothing
It is man-machine when being in state of flight, it mainly flies using wing, and the elevon completion posture of dependence trailing edge position
Adjustment, to ensure that the speed of a ship or plane of flight course.It is of the invention compared to existing fixed-wing unmanned plane and rotary wind type unmanned plane
Unmanned plane combines the advantages of the two well, has the problems such as facilitating landing, the speed of a ship or plane fast, easy to use, meets increasingly multiple
Miscellaneous task needs, and has a vast market foreground.
It should be noted that although the various embodiments described above have been described herein, it is not intended to limit
The scope of patent protection of the present invention.Therefore, based on the present invention innovative idea, to embodiment described herein carry out change and repair
Change, or using equivalent structure or equivalent flow shift made by description of the invention and accompanying drawing content, it directly or indirectly will be with
Upper technical solution is used in other related technical areas, is included within the scope of patent protection of the present invention.
Claims (10)
1. a kind of VTOL fixed-wing unmanned plane has fuselage, which is characterized in that including：
Wing, the wing are set to the opposite sides of the fuselage；
First dynamical system, including the first driving unit, rotor and the regulating mechanism that verts；First driving unit is passed with rotor
Dynamic connection, for driving rotor rotational；The regulating mechanism that verts is connect with rotor, for adjusting rotor compared to horizontal
Angle of inclination；The rotor and fuselage are coaxial, and are set to the front end of fuselage, including oppositely arranged the first rotor and second
Rotor；
Second dynamical system, including the second driving unit and at least a pair of of elevon, second driving unit and lifting pair
The wing is sequentially connected, and each pair of elevon is symmetrically disposed on the posterior border position of the wing；
Support device is connected to the rear end of the fuselage, is used to support the fuselage of the state of taking off vertically or state of landing；
Avionics cabin, is set to the fuselage interior, including control system, the control system respectively with the first driving unit, incline
Modulation section structure, the connection of the second driving unit.
2. VTOL fixed-wing unmanned plane as described in claim 1, which is characterized in that further include：
Load cabin is set to the fuselage interior, and between avionics cabin and front end, photoelectricity load is provided in the load cabin
Lotus interface；It is additionally provided with window in the load cabin, radical occlusion device is provided at window, the radical occlusion device can be relative to institute
Window movement is stated, for closing or opening the window.
3. VTOL fixed-wing unmanned plane as described in claim 1, which is characterized in that further include：
Empennage, the empennage are vertically installed in the tail portion of fuselage, and the tail portion of the fuselage is between wing position and rear end.
4. VTOL fixed-wing unmanned plane as claimed in claim 3, which is characterized in that further include：
Rudder, the rudder is set to the posterior border position of empennage, and can be swung relative to the empennage.
5. VTOL fixed-wing unmanned plane as described in claim 1, which is characterized in that after the support device and fuselage
The mode of end connection is to be detachably connected.
6. VTOL fixed-wing unmanned plane as described in claim 1, which is characterized in that the fuselage is additionally provided with positioning and connects
Mouthful, the locating interface is set to fuselage back.
7. VTOL fixed-wing unmanned plane as described in claim 1, which is characterized in that the fuselage be additionally provided with number pass or
Figure passes interface, and the number passes or figure passes interface and is set to belly.
8. VTOL fixed-wing unmanned plane as described in claim 1, which is characterized in that the wing is aft swept wings,
The aspect ratio of wing is not less than default value.
9. VTOL fixed-wing unmanned plane as described in claim 1, which is characterized in that first driving unit is piston
Engine or turboaxle motor.
10. VTOL fixed-wing unmanned plane as described in claim 1, which is characterized in that second driving unit is electricity
Dynamic steering engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810194748.8A CN108545182A (en) | 2018-03-09 | 2018-03-09 | A kind of VTOL fixed-wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810194748.8A CN108545182A (en) | 2018-03-09 | 2018-03-09 | A kind of VTOL fixed-wing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108545182A true CN108545182A (en) | 2018-09-18 |
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ID=63515985
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810194748.8A Pending CN108545182A (en) | 2018-03-09 | 2018-03-09 | A kind of VTOL fixed-wing unmanned plane |
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| Country | Link |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112158325A (en) * | 2020-09-30 | 2021-01-01 | 浙江大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle and control method thereof |
| CN117075527A (en) * | 2023-10-17 | 2023-11-17 | 成都天域航通科技有限公司 | Flight control system of large fixed wing freight unmanned aerial vehicle |
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| US6382556B1 (en) * | 1999-12-20 | 2002-05-07 | Roger N. C. Pham | VTOL airplane with only one tiltable prop-rotor |
| CN106892102A (en) * | 2017-02-28 | 2017-06-27 | 王文正 | A kind of VUAV and its control method |
| CN107187595A (en) * | 2017-05-27 | 2017-09-22 | 沈阳航空航天大学 | A kind of VTOL fixed-wing unmanned plane with bending moment propeller |
| CN206664932U (en) * | 2017-04-25 | 2017-11-24 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN206856977U (en) * | 2017-05-18 | 2018-01-09 | 成都时代星光科技有限公司 | The undercarriage and aircraft of a kind of aircraft |
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2018
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6382556B1 (en) * | 1999-12-20 | 2002-05-07 | Roger N. C. Pham | VTOL airplane with only one tiltable prop-rotor |
| CN106892102A (en) * | 2017-02-28 | 2017-06-27 | 王文正 | A kind of VUAV and its control method |
| CN206664932U (en) * | 2017-04-25 | 2017-11-24 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN206856977U (en) * | 2017-05-18 | 2018-01-09 | 成都时代星光科技有限公司 | The undercarriage and aircraft of a kind of aircraft |
| CN107187595A (en) * | 2017-05-27 | 2017-09-22 | 沈阳航空航天大学 | A kind of VTOL fixed-wing unmanned plane with bending moment propeller |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112158325A (en) * | 2020-09-30 | 2021-01-01 | 浙江大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle and control method thereof |
| CN117075527A (en) * | 2023-10-17 | 2023-11-17 | 成都天域航通科技有限公司 | Flight control system of large fixed wing freight unmanned aerial vehicle |
| CN117075527B (en) * | 2023-10-17 | 2023-12-26 | 成都天域航通科技有限公司 | Flight control system of large fixed wing freight unmanned aerial vehicle |
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Application publication date: 20180918 |