CN109263941A - A kind of omnidirectional's flight wing structure of vertical translation aircraft - Google Patents
A kind of omnidirectional's flight wing structure of vertical translation aircraft Download PDFInfo
- Publication number
- CN109263941A CN109263941A CN201811274758.9A CN201811274758A CN109263941A CN 109263941 A CN109263941 A CN 109263941A CN 201811274758 A CN201811274758 A CN 201811274758A CN 109263941 A CN109263941 A CN 109263941A
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- Prior art keywords
- aircraft
- rotor
- aircraft body
- omnidirectional
- flight
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Classifications
-
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
-
- 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
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
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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 omnidirectional's flight wing structures of vertical translation aircraft, speed measuring device can be according to the flying speed of aircraft, rotor flies to be converted between state in jacking condition peace before automatically controlling, and it controls automatically whether rear rotor works, to realize the rapid vertical lifting of aircraft when preceding rotor is in jacking condition and rear rotor works, lift requirement is smaller and does not need other ancillary equipments, further mitigates aircraft weight；In addition, realize that aircraft is flat when preceding rotor is in flat winged state and rear rotor stops working and fly, thrust ratio requires low, and energy consumption is few.
Description
Technical field
The present invention relates to vehicle technology fields, more particularly to omnidirectional's flight wing of vertical translation aircraft
Structure.
Background technique
There are mainly two types of current practical aircraft: helicopter and fixed wing aircraft, and helicopter is generated using propeller
Upward lift, during flight, propeller high speed rotation, aircraft needs overcome very big resistance to realize itself
Balance, flight efficiency is lower, also, aircraft is easy to be influenced by external force during flight, when there is crosswind in the air,
Aircraft is easy to rock, or even rollover, stability are poor.Helicopter is restricted by self-condition, generally installs an engine, flight
During flight, engine once breaks down device, aircraft can not normal flight, there are some potential safety problemss, and
And the propeller of helicopter is all mounted on top, the lifesaving appliances such as installation parachute is not easy to, if helicopter is in the process of flight
In break down, the personnel in helicopter do not have survival equipment, and safety coefficient is low, in addition, current Flight Vehicle Structure is more multiple
Miscellaneous, manufacturing process is cumbersome, high to the intensity requirement of material, and cost of manufacture is high.
Therefore, how providing one kind can not only be vertically moved up or down, and can be realized the vertical lift flight of omnidirectional's flight
The problem of omnidirectional's flight wing structure of device is those skilled in the art's urgent need to resolve.
Summary of the invention
In view of this, the present invention provides a kind of omnidirectional's flight wing structure of vertical translation aircraft, speed measuring device energy
Enough flying speeds according to aircraft, rotor flies to be converted between state in jacking condition peace before automatically controlling, and from
It is dynamic to control whether rear rotor works, to realize aircraft when preceding rotor is in jacking condition and rear rotor works
Rapid vertical lifting, lift requirement is smaller and does not need other ancillary equipments, further mitigates aircraft weight；In addition, preceding
Rotor is in when equalling winged state and rear rotor stops working, realizing that aircraft is flat winged, and thrust ratio requirement is low, and energy consumption is few.
To achieve the goals above, the invention provides the following technical scheme:
A kind of omnidirectional's flight wing structure of vertical translation aircraft, including aircraft body, further includes: preceding rotor, vert machine
Structure, rear rotor and control system；The preceding rotor is at least provided with two, positioned at the front end of the aircraft body, and along institute
The central axis or so for stating aircraft body is symmetrical arranged two-by-two；The preceding rotor is arranged in the aircraft inclining rotary mechanism
The front end of ontology, and fly to be converted between state in jacking condition peace for controllably controlling the preceding rotor；Described
When jacking condition, the heading of the rotation axis of the preceding rotor perpendicular to the aircraft body；In the flat winged state
When, the rotation axis of the preceding rotor is parallel to the heading of the aircraft body；Rotor is at least provided with two after described
It is a, it is fixed at the two sides of tail of the aircraft body, and the central axis about the aircraft body is symmetrical, it is described
Heading of the rotation axis of rotor perpendicular to the aircraft body afterwards；The control system includes: speed measuring device and control
Device processed；The speed measuring device is arranged on the aircraft body, the flight speed for aircraft body described in real-time monitoring
Degree；The airspeed information control on the aircraft body, for transmitting according to the speed measuring device is arranged in the controller
The inclining rotary mechanism is made, the controller is also used to control the rear rotor work when the preceding rotor is in jacking condition,
And the rear rotor is controlled when the preceding rotor is in flat winged state and is stopped.
Preferably, in omnidirectional's flight wing structure of above-mentioned vertical translation aircraft, each preceding rotor passes through
The front end of the aircraft body is arranged in one inclining rotary mechanism.
Preferably, in omnidirectional's flight wing structure of above-mentioned vertical translation aircraft, the control system further includes
Including wind direction/air velocity transducer part；The signal input part of wind direction/air velocity transducer part signal output end connection controller；Control
The control signal input of the control signal output connecting steering mechanism of device processed.
Preferably, in omnidirectional's flight wing structure of above-mentioned vertical translation aircraft, the inclining rotary mechanism includes: to incline
Turn bracket, steering engine and first connecting rod；The steering engine is fixed at the axial midpoint position of the bracket that verts；Described
One connecting rod one end is connect with the steering engine, and the other end is fixedly connected with the front end of the aircraft body, and the steering engine is used for
Vert holder pivots described in driving under controller control, and the bracket that verts described in the axis conduct of the first connecting rod
Pivot center.
Preferably, in omnidirectional's flight wing structure of above-mentioned vertical translation aircraft, the preceding rotor includes: first
Driving motor and the first propeller；There are two first driving motor and first propeller are respectively provided with；Described first drives
Dynamic motor is symmetrically fixed at the axial ends of the bracket that verts；First propeller is driven by described first respectively
Motor driven, the rotation axis coincident of two first propellers, and it is vertical with the axis of the first connecting rod, in addition,
The direction of rotation of two first propellers is opposite.
Preferably, in omnidirectional's flight wing structure of above-mentioned vertical translation aircraft, the rear rotor includes: second
Driving motor, the second propeller and the second connecting rod；There are two second driving motor and second propeller are respectively provided with；
Second propeller is driven by second driving motor, the rotation axis coincident of two second propellers respectively, and
The direction of rotation of two second propellers is opposite；Second connecting rod one end is fixedly attached to two second drivings
At position between motor, the other end is fixedly attached to the tail portion of the aircraft body.
Preferably, in omnidirectional's flight wing structure of above-mentioned vertical translation aircraft, the aircraft body includes
The wing of the left and right sides is provided with aileron in the wing outer segment, vertical end is fixedly installed in the end of the wing
Plate.
Preferably, in omnidirectional's flight wing structure of above-mentioned vertical translation aircraft, the speed measuring device fixation is set
It sets in the front end of the aircraft body.
Preferably, in omnidirectional's flight wing structure of above-mentioned vertical translation aircraft, omnidirectional's flight wing knot
Structure further include: empennage；The tail portion of the aircraft body is arranged in the empennage；The empennage includes the wing for being located at empennage middle section
Knife and vertical winglet.
It can be seen via above technical scheme that compared with prior art, the present disclosure provides a kind of vertical lifts to fly
Omnidirectional's flight wing structure of row device, speed measuring device can be according to the flying speeds of aircraft, and rotor is being gone up and down before automatically controlling
State peace flies to be converted between state, and controls automatically whether rear rotor works, to be in preceding rotor
Realize the rapid vertical lifting of aircraft when jacking condition and rear rotor work, lift requirement is smaller and does not need other auxiliary and sets
It is standby, further mitigate aircraft weight；In addition, realizing flight when preceding rotor is in flat winged state and rear rotor stops working
Device is flat to fly, and thrust ratio requirement is low, and energy consumption is few.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 attached drawing is structural schematic diagram of the invention；
Fig. 2 attached drawing is the structural schematic diagram of inclining rotary mechanism of the invention.
In figure: rotor, 21 first driving motors, 22 first before 1 aircraft body, 11 wings, 12 ailerons, 13 end plates, 2
Propeller, 3 inclining rotary mechanisms, 31 are verted rotor, 41 second driving motors, 42 second behind 32 steering engine of bracket, 33 first connecting rods, 4
Propeller, 43 second connecting rods, 5 speed measuring devices, 6 empennages.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The embodiment of the invention discloses a kind of omnidirectional's flight wing structures of vertical translation aircraft, and speed measuring device being capable of root
According to the flying speed of aircraft, rotor flies to be converted between state in jacking condition peace before automatically controlling, and automatic right
Whether rotor works and is controlled afterwards, to realize the quick of aircraft when preceding rotor is in jacking condition and rear rotor works
Vertical lift, lift requirement is smaller and does not need other ancillary equipments, further mitigates aircraft weight；In addition, in preceding rotor
Fly in when equalling winged state and rear rotor stops working, realizing that aircraft is flat, thrust ratio requirement is low, and energy consumption is few.
A kind of omnidirectional's flight wing structure of vertical translation aircraft, including aircraft body 1, further includes: preceding rotor 2,
Inclining rotary mechanism 3, rear rotor 4 and control system；
Preceding rotor 2 is at least provided with two, positioned at the front end of aircraft body 1, and along the central axis or so of aircraft body 1
It is symmetrical arranged two-by-two；The front end of aircraft body 1 is arranged in preceding rotor 2 by inclining rotary mechanism 3, and for rotation before controllably control
The wing 2 flies to be converted between state in jacking condition peace；In jacking condition, the rotation axis of preceding rotor 2 is perpendicular to flight
The heading of device ontology 1；In flat winged state, the rotation axis of preceding rotor 2 is parallel to the heading of aircraft body 1；
Rotor 4 is fixed at the two sides of tail of aircraft body 1, and the center about aircraft body 1 at least provided with two afterwards
Axisymmetrical, the heading of the rotation axis of rear rotor 4 perpendicular to aircraft body 1；Control system includes: speed measuring device 5
And controller；The flying speed on aircraft body 1, for real-time monitoring aircraft body 1 is arranged in speed measuring device 5；Control
Device is arranged on aircraft body 1, and the airspeed information for being transmitted according to speed measuring device 5 controls inclining rotary mechanism 3, control
Device is also used to control the back spin wing 4 when preceding rotor 2 is in jacking condition and work, and is in flat winged state time control in preceding rotor 2
Rotor 4 stops after system.
In order to further optimize the above technical scheme, each preceding rotor 2 is arranged by an inclining rotary mechanism 3 in aircraft sheet
The front end of body 1.
In order to further optimize the above technical scheme, control system further include include wind direction/air velocity transducer part；Wind direction/
The signal input part of the signal output end connection controller of air velocity transducer part；The control signal output of controller connects rotation
The control signal input of mechanism.
In order to further optimize the above technical scheme, inclining rotary mechanism 3 includes: vert bracket 31, steering engine 32 and the first connection
Bar 33；Steering engine 32 is fixed at the axial midpoint position for the bracket 31 that verts；33 one end of first connecting rod is connect with steering engine 32,
The other end is fixedly connected with the front end of aircraft body 1, and steering engine 32 is used to drive the rotation of bracket 31 of verting under control of the controller,
And pivot center of the axis of first connecting rod 33 as the bracket 31 that verts.
In order to further optimize the above technical scheme, preceding rotor 2 includes: the first driving motor 21 and the first propeller 22；
There are two first driving motor 21 and the first propeller 22 are respectively provided with；First driving motor 21, is symmetrically fixed at branch of verting
The axial ends of frame 31；First propeller 22 is driven by the first driving motor 21 respectively, the rotary shaft of two the first propellers 22
Line is overlapped, and vertical with the axis of first connecting rod 33, in addition, the direction of rotation of two the first propellers 22 is opposite.
In order to further optimize the above technical scheme, rear rotor 4 includes: the second driving motor 41,42 and of the second propeller
Second connecting rod 43；There are two second driving motor 41 and the second propeller 42 are respectively provided with；Second propeller 42, respectively by second
Driving motor 41 drives, the rotation axis coincident of two the second propellers 42, and the direction of rotation phase of two the second propellers 42
Instead；Second connecting rod, 43 one end is fixedly attached at the position between two the second driving motors 41, and the other end is fixedly attached to
The tail portion of aircraft body 1.
In order to further optimize the above technical scheme, aircraft body 1 includes the wing 11 of the left and right sides, outside wing 11
It is provided with aileron 12 in section, vertical end plate 13 is fixedly installed in the end of wing 11.
In order to further optimize the above technical scheme, speed measuring device 5 is fixed at the front end of aircraft body 1.
In order to further optimize the above technical scheme, omnidirectional's flight wing structure further include: empennage；Empennage setting is being flown
The tail portion of device ontology 1；Empennage includes wing fence and vertical winglet.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.For device disclosed in embodiment
For, since it is corresponded to the methods disclosed in the examples, so being described relatively simple, related place is said referring to method part
It is bright.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (9)
1. a kind of omnidirectional's flight wing structure of vertical translation aircraft, including aircraft body (1), which is characterized in that also wrap
It includes: preceding rotor (2), inclining rotary mechanism (3), rear rotor (4) and control system；The preceding rotor (2) is located at least provided with two
The front end of the aircraft body (1), and be symmetrical arranged two-by-two along the central axis or so of the aircraft body (1)；It verts
The preceding rotor (2) is arranged in the front end of the aircraft body (1) for mechanism (3), and for controllably controlling the preceding rotation
The wing (2) flies to be converted between state in jacking condition peace；In the jacking condition, the rotary shaft of the preceding rotor (2)
Heading of the line perpendicular to the aircraft body (1)；In the flat winged state, the rotation axis of the preceding rotor (2)
It is parallel to the heading of the aircraft body (1)；Rotor (4) is fixed at described at least provided with two after described
The two sides of tail of aircraft body (1), and the central axis about the aircraft body (1) is symmetrical, the rear rotor (4)
Heading of the rotation axis perpendicular to the aircraft body (1)；The control system includes: speed measuring device (5) and control
Device；The speed measuring device (5) is arranged on the aircraft body (1), for aircraft body (1) described in real-time monitoring
Flying speed；The controller is arranged on the aircraft body (1), flies for what is transmitted according to the speed measuring device (5)
Row velocity information controls the inclining rotary mechanism (3), and the controller is also used to be in jacking condition time control in the preceding rotor (2)
Rear rotor (4) work is made, and controls the rear rotor (4) when the preceding rotor (2) is in flat winged state and stops.
2. omnidirectional's flight wing structure of vertical translation aircraft according to claim 1, which is characterized in that each described
Preceding rotor (2) is arranged by an inclining rotary mechanism (3) in the front end of the aircraft body (1).
3. omnidirectional's flight wing structure of vertical translation aircraft according to claim 1, which is characterized in that the control
System further include include wind direction/air velocity transducer part；The signal of wind direction/air velocity transducer part signal output end connection controller
Input terminal；The control signal input of the control signal output connecting steering mechanism of controller.
4. omnidirectional's flight wing structure of vertical translation aircraft according to claim 2, which is characterized in that described to vert
Mechanism (3) includes: vert bracket (31), steering engine (32) and first connecting rod (33)；The steering engine (32) is fixed at described
It verts at the axial midpoint position of bracket (31)；Described first connecting rod (33) one end is connect with the steering engine (32), the other end
It is fixedly connected with the front end of the aircraft body (1), the steering engine (32) is used under controller control described in drive
It verts bracket (31) rotation, and the axis of the first connecting rod (33) verts the pivot center of bracket (31) as described in.
5. omnidirectional's flight wing structure of vertical translation aircraft according to claim 4, which is characterized in that rotation before described
The wing (2) includes: the first driving motor (21) and the first propeller (22)；First driving motor (21) and first spiral
There are two paddle (22) is respectively provided with；First driving motor (21) is symmetrically fixed at the axial direction of bracket (31) of verting
Both ends；First propeller (22) is driven by first driving motor (21), two first propellers (22) respectively
Rotation axis coincident, and it is vertical with the axis of the first connecting rod (33), in addition, two first propellers (22)
Direction of rotation is opposite.
6. omnidirectional's flight wing structure of vertical translation aircraft according to claim 1-5, which is characterized in that
Rotor (4) includes: the second driving motor (41), the second propeller (42) and the second connecting rod (43) after described；Described second drives
There are two dynamic motor (41) and second propeller (42) are respectively provided with；Second propeller (42), respectively by described second
Driving motor (41) driving, the rotation axis coincident of two second propellers (42), and two second propellers
(42) direction of rotation is opposite；Described second connecting rod (43) one end be fixedly attached to two second driving motors (41) it
Between position at, the other end is fixedly attached to the tail portion of the aircraft body (1).
7. omnidirectional's flight wing structure of vertical translation aircraft according to claim 6, which is characterized in that the flight
Device ontology (1) includes the wing (11) of the left and right sides, aileron (12) is provided in the wing (11) outer segment, in the wing
(11) end is fixedly installed vertical end plate (13).
8. omnidirectional's flight wing structure of vertical translation aircraft according to claim 6, which is characterized in that described to test the speed
Device (5) is fixed at the front end of the aircraft body (1).
9. omnidirectional's flight wing structure of vertical translation aircraft according to claim 6, which is characterized in that the omnidirectional
Flight wing structure further include: empennage；Tail portion of the empennage setting in the aircraft body (1)；The empennage includes the wing
Knife and vertical winglet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274758.9A CN109263941A (en) | 2018-10-30 | 2018-10-30 | A kind of omnidirectional's flight wing structure of vertical translation aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274758.9A CN109263941A (en) | 2018-10-30 | 2018-10-30 | A kind of omnidirectional's flight wing structure of vertical translation aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263941A true CN109263941A (en) | 2019-01-25 |
Family
ID=65195246
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274758.9A Withdrawn CN109263941A (en) | 2018-10-30 | 2018-10-30 | A kind of omnidirectional's flight wing structure of vertical translation aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263941A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112238939A (en) * | 2020-09-21 | 2021-01-19 | 南京航空航天大学 | Novel-configuration tilt rotor aircraft and flight control method thereof |
| RU208853U1 (en) * | 2021-06-14 | 2022-01-18 | Илья Алексеевич Галкин | VTOL unmanned aerial vehicle designed for aerial surveying |
-
2018
- 2018-10-30 CN CN201811274758.9A patent/CN109263941A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112238939A (en) * | 2020-09-21 | 2021-01-19 | 南京航空航天大学 | Novel-configuration tilt rotor aircraft and flight control method thereof |
| CN112238939B (en) * | 2020-09-21 | 2022-04-22 | 南京航空航天大学 | Novel-configuration tilt rotor aircraft and flight control method thereof |
| RU208853U1 (en) * | 2021-06-14 | 2022-01-18 | Илья Алексеевич Галкин | VTOL unmanned aerial vehicle designed for aerial surveying |
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Application publication date: 20190125 |