CN109263918A - A kind of tilting rotor fixed wing aircraft - Google Patents
A kind of tilting rotor fixed wing aircraft Download PDFInfo
- Publication number
- CN109263918A CN109263918A CN201811274971.XA CN201811274971A CN109263918A CN 109263918 A CN109263918 A CN 109263918A CN 201811274971 A CN201811274971 A CN 201811274971A CN 109263918 A CN109263918 A CN 109263918A
- Authority
- CN
- China
- Prior art keywords
- wing
- fuselage
- tilting rotor
- tail
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
-
- 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
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of tilting rotor fixed wing aircrafts, it include: fuselage, host wing, the slave wing, empennage and tilting rotor component, host wing is symmetrically disposed on fuselage two sides, the slave wing is connected to the tail end of host wing, empennage is set to the tail end of fuselage, and tilting rotor component is symmetrically mounted on host wing；Tilting rotor component includes hydraulic stem, the first engine, the first propeller, shaft and two fixed blocks, and hydraulic stem one end is mounted on host wing top, and the other end and the first engine are hinged；Two fixed blocks are mounted on host wing top, and shaft is installed between two fixed blocks, and are rotatablely connected with two fixed blocks；First engine is connected by connector with shaft, the output shaft rotation connection of the first propeller and the first engine.The present invention can not only realize vertical lift and the hovering of aircraft, and improve the stationarity of aircraft flight.
Description
Technical field
The present invention relates to unmanned plane equipment technical field, more particularly to a kind of tilting rotor fixed wing aircraft.
Background technique
It is well known that fixed wing aircraft, which generates lift using the movement of wing relative wind, resists gravity, the inclined of rudder face is utilized
Rotate into row control, have many advantages, such as that flying speed is fast, voyage is remote, load-carrying is big, energy efficiency is high, disadvantage be exactly landing need it is long away from
From runway, hovering cannot achieve；Gyroplane generates pulling force using one or more rotors and resists gravity, is controlled using passing through
The Plane of rotation of rotor processed provides the power of aircraft horizontal movement with horizontal plane inclination angle, has structure simple, can be vertical
The advantages of landing and hovering, disadvantage are exactly that speed is slow, voyage is short, load-carrying is small, energy efficiency is low；Therefore, many people are always
All want that the high flight efficiency and gyroplane in conjunction with fixed wing aircraft being capable of hovering and the advantages of VTOL.
Therefore, the Convertiplane for how providing a kind of more rotors becomes asking for those skilled in the art's urgent need to resolve
Topic.
Summary of the invention
In view of this, can not only realize the vertical liter of aircraft the present invention provides a kind of tilting rotor fixed wing aircraft
Drop and hovering, and improve the stationarity of aircraft flight.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of tilting rotor fixed wing aircraft, comprising: fuselage, host wing, the slave wing, empennage and tilting rotor component, wherein institute
It states host wing and is symmetrically disposed on the fuselage two sides, the slave wing is connected to the tail end of the host wing, the empennage setting
In the tail end of the fuselage, the tilting rotor component is symmetrically mounted on the host wing；The tilting rotor component includes
Hydraulic stem, the first motor, the first propeller, shaft and two fixed blocks, one end of described hydraulic stem are mounted on the host wing
Top, the other end and first motor are hinged；Two fixed blocks are mounted on the host wing top, the shaft peace
It is rotatablely connected loaded between two fixed blocks, and with two fixed blocks；First motor by connector with
The shaft is connected, and the output shaft of first propeller and first motor is rotatablely connected.
Through the above technical solutions, technical effect of the invention: the slave wing is arranged in host wing tail end in the present invention, improves
The stability of aircraft flight；By installing tilting rotor component on host wing, the vertical lift of aircraft and aerial can be realized
Hovering；The lifting of hydraulic stem can push the first motor to go up and down, since the first motor is connected with shaft, to realize first
The adjustment of spiral propeller angle.
Preferably, the empennage includes horizontal tail, vertical fin and dorsal fin, and the vertical fin and the dorsal fin splice to be carried on the back in the fuselage
The tail portion in portion, the horizontal tail are symmetrically disposed on the two sides of the fuselage tail end.
Through the above technical solutions, technical effect of the invention: when flight, horizontal tail mainly controls the longitudinal stability of aircraft
And operability, vertical fin mainly control the lateral stability and operability of aircraft, dorsal fin is used to improve the lateral stable sea of aircraft
Property.
Preferably, the vertical fin top is provided with the second motor, and the output shaft of second motor is rotatably connected to
Second propeller.
Through the above technical solutions, technical effect of the invention: the setting of the second propeller had both been convenient to the vertical of aircraft
Lifting and hovering, and can be improved the stability of aircraft flight.
Preferably, the tail end of the horizontal tail is provided with elevator.
Through the above technical solutions, technical effect of the invention: by controlling the deflection of elevator, it can be achieved that aircraft pitch
The control of posture.
Preferably, the tail end of the vertical fin is provided with rudder.
Through the above technical solutions, technical effect of the invention: rudder can be used to change vector and realize aircraft
Low-angle turn to.
Preferably, the fuselage bottom end is provided with nose-gear and rear undercarriage, and the nose-gear is located at the fuselage
Head end, it is described after undercarriage be located at the tail end of the fuselage.
Preferably, spring element is inlaid with inside the nose-gear and the rear undercarriage.
Through the above technical solutions, technical effect of the invention: the setting of spring element can protect equipment in landing
Buffer the impact force to nose-gear and rear undercarriage.
Preferably, the fuselage interior is provided with control system, and the control system is electronic by circuit and described first
Machine, second motor are connected with the hydraulic stem, realize the control to the first motor, the second motor and hydraulic stem.
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.
Wherein, in figure,
1- fuselage；2- host wing；The 3- slave wing；4- empennage；41- horizontal tail；411- elevator；42- vertical fin；421- rudder；43-
Dorsal fin；The second motor of 44-；The second propeller of 45-；5- hydraulic stem；The first motor of 6-；The first propeller of 7-；8- shaft；9-
Fixed block；10- nose-gear；Undercarriage after 11-.
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.
Attached drawing 1 is please referred to, the present invention provides a kind of tilting rotor fixed wing aircrafts, comprising: fuselage 1, host wing 2, pair
Wing 3, empennage 4 and tilting rotor component, wherein host wing 2 is symmetrically disposed on 1 two sides of fuselage, and the slave wing 3 is connected to host wing
2 tail end, empennage 4 are set to the tail end of fuselage 1, and tilting rotor component is symmetrically mounted on host wing 2；Tilting rotor component packet
Hydraulic stem 5, the first motor 6, the first propeller 7, shaft 8 and two fixed blocks 9 are included, 5 one end of hydraulic stem is mounted on host wing 2
Top, the other end and the first motor 6 are hinged；Two fixed blocks 9 are mounted on 2 top of host wing, and shaft 8 is installed on two fixations
Between block 9, and it is rotatablely connected with two fixed blocks 9；First motor 6 is connected by connector with shaft 8, the first propeller 7
It is rotatablely connected with the output shaft of the first motor 6.
The slave wing 3 is arranged in 2 tail end of host wing in the present invention, improves the stability of aircraft flight；By on host wing 2
Tilting rotor component is installed, can be realized vertical lift and the hovering of aircraft；The lifting of hydraulic stem 5 can push first electronic
Machine 6 is gone up and down, since the first motor 6 is connected with shaft 8, so that the adjustment of 7 angle of the first propeller is realized, in aircraft vertical
It when lifting and hovering, is adjusted by hydraulic stem 5, makes the first motor 6 and 2 keeping parallelism of host wing, in aircraft traveling process,
The lifting height of hydraulic stem 5 can be adjusted according to real flight conditions to adjust the deflection angle of the first motor 6, not only improved winged
Capable stability, and the flight efficiency of aircraft can be improved.
In order to further optimize the above technical scheme, empennage 4 includes horizontal tail 41, vertical fin 42 and dorsal fin 43, vertical fin 42 and back
Fin 43 splices in the tail portion at 1 back of fuselage, and horizontal tail 41 is symmetrically disposed on the two sides of 1 tail end of fuselage.When flight, horizontal tail 41 is mainly controlled
The longitudinal stability and operability of aircraft processed are left a blank among horizontal tail 41, transversely and horizontally arrange one spiral of installation in position of leaving a blank
Paddle is so that it is convenient to aircraft steadily hovering or wide-angle pitching；Vertical fin 42 mainly controls the lateral stability and operability of aircraft, hangs down
Leave a blank among tail 42, longitudinal vertical arrangement one propeller of installation in position of leaving a blank so that it is convenient to when hang or low speed it is big
Angle turns to；Dorsal fin 43 is used to improve the lateral navigation stability of aircraft.
In order to further optimize the above technical scheme, 42 top of vertical fin is provided with the second motor 44, the second motor 44
Output shaft be rotatably connected to the second propeller 45.
In order to further optimize the above technical scheme, the tail end of horizontal tail 41 is provided with elevator 411.By controlling elevator
411 deflection, it can be achieved that aircraft pitch posture control.
In order to further optimize the above technical scheme, the tail end of vertical fin 42 is provided with rudder 421.Rudder 421 can be used
To change vector and realize that the low-angle of aircraft turns to.
In order to further optimize the above technical scheme, 1 bottom end of fuselage is provided with nose-gear 10 and rear undercarriage 11, and preceding
Fall the head end that frame 10 is located at fuselage 1, after 11 framves that rise and fall be located at the tail end of fuselage 1.
In order to further optimize the above technical scheme, spring element is inlaid with inside nose-gear 10 and rear undercarriage 11
Part.The setting of spring element can protect the equipment impact force of buffering to nose-gear 10 and rear undercarriage 11 in landing.
In order to further optimize the above technical scheme, fuselage 1 is internally provided with control system, control system by circuit with
First motor 6, the second motor 44 are connected with hydraulic stem 5, realize to the first motor 6, the second motor 44 and hydraulic stem 5
Control.
The working principle of the invention:
Hydraulic stem 5 and 6 bottom end of the first motor are hinged, and the lifting of hydraulic stem 5 can push the first motor 6 to go up and down, due to first
Motor 6 is connected with shaft 8, to realize the adjustment of 7 angle of the first propeller, when aircraft vertical is gone up and down and is hovered, leads to
The adjustment of hydraulic stem 5 is crossed, the first motor 6 and 2 keeping parallelism of host wing are made, to ensure that the first propeller 7 is in horizontal
State；In aircraft traveling process, the lifting height of hydraulic stem 5 can be adjusted according to real flight conditions to adjust the first motor 6
Deflection angle, the stability of aircraft flight is not only improved, and the power of aircraft can be utilized to greatest extent, to improve aircraft
Flight efficiency.
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 (7)
1. a kind of tilting rotor fixed wing aircraft characterized by comprising fuselage, host wing, the slave wing, empennage and rotation of verting
Wing component, wherein the host wing is symmetrically disposed on the fuselage two sides, and the slave wing is connected to the tail of the host wing
End, the empennage are set to the tail end of the fuselage, and the tilting rotor component is symmetrically mounted on the host wing；It is described to incline
Switch rotor component includes hydraulic stem, the first engine, the first propeller, shaft and two fixed blocks, one end of described hydraulic stem peace
Mounted in the host wing top, the other end and first engine are hinged；Two fixed blocks are mounted on the host wing
Top, the shaft are installed between two fixed blocks, and are rotatablely connected with two fixed blocks；Described first starts
Machine is connected by connector with the shaft, and the output shaft of first propeller and first engine is rotatablely connected.
2. a kind of tilting rotor fixed wing aircraft according to claim 1, which is characterized in that the empennage include horizontal tail,
Vertical fin and dorsal fin, the vertical fin and the dorsal fin splice in the tail portion of the fuselage back, and the horizontal tail is symmetrically disposed on described
The two sides of fuselage tail end.
3. a kind of tilting rotor fixed wing aircraft according to claim 2, which is characterized in that the vertical fin top is provided with
The output shaft of second engine, second engine is rotatably connected to the second propeller.
4. a kind of tilting rotor fixed wing aircraft according to claim 2, which is characterized in that the tail end of the horizontal tail is arranged
There is elevator.
5. a kind of tilting rotor fixed wing aircraft according to claim 3 or 4, which is characterized in that the tail end of the vertical fin
It is provided with rudder.
6. a kind of tilting rotor fixed wing aircraft according to claim 1, which is characterized in that the fuselage bottom end is provided with
Nose-gear and rear undercarriage, the nose-gear are located at the head end of the fuselage, and the rear undercarriage is located at the fuselage
Tail end.
7. a kind of tilting rotor fixed wing aircraft according to claim 6, which is characterized in that the nose-gear and described
Spring element is inlaid with inside undercarriage afterwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274971.XA CN109263918A (en) | 2018-10-30 | 2018-10-30 | A kind of tilting rotor fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274971.XA CN109263918A (en) | 2018-10-30 | 2018-10-30 | A kind of tilting rotor fixed wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263918A true CN109263918A (en) | 2019-01-25 |
Family
ID=65194536
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274971.XA Withdrawn CN109263918A (en) | 2018-10-30 | 2018-10-30 | A kind of tilting rotor fixed wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263918A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111619785A (en) * | 2019-02-27 | 2020-09-04 | 空客直升机德国有限公司 | Multi-rotor aircraft suitable for vertical take-off and landing |
-
2018
- 2018-10-30 CN CN201811274971.XA patent/CN109263918A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111619785A (en) * | 2019-02-27 | 2020-09-04 | 空客直升机德国有限公司 | Multi-rotor aircraft suitable for vertical take-off and landing |
| CN111619785B (en) * | 2019-02-27 | 2023-10-10 | 空客城市移动有限公司 | Multi-rotor aircraft suitable for vertical take-off and landing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190125 |