CN109263930A - A kind of Fixed Wing AirVehicle being vertically moved up or down - Google Patents
A kind of Fixed Wing AirVehicle being vertically moved up or down Download PDFInfo
- Publication number
- CN109263930A CN109263930A CN201811274487.7A CN201811274487A CN109263930A CN 109263930 A CN109263930 A CN 109263930A CN 201811274487 A CN201811274487 A CN 201811274487A CN 109263930 A CN109263930 A CN 109263930A
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- Prior art keywords
- machine
- right flank
- vertically moved
- left wing
- rack gear
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- 238000009434 installation Methods 0.000 claims abstract description 5
- 238000006073 displacement reaction Methods 0.000 claims description 8
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 230000008901 benefit Effects 0.000 abstract description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000001035 drying Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses the Fixed Wing AirVehicles that one kind can be vertically moved up or down, including body and the machine left wing being set on body and machine right flank, integral installation has a rotary shaft in the machine left wing and machine right flank and the rotary shaft extends transversely through entire body, a circle gear is fixedly installed on the rotary shaft outer surface for being located at body area, the gear passes through pneumatic rotary device control rotation；The junction of the machine left wing, machine right flank and the body is equipped with inclining rotary mechanism；The rear end of the machine left wing and machine right flank is respectively symmetrically equipped with several propeller power devices；The front and back both sides of the machine left wing and machine right flank upper surface are symmetrically installed with several jet power units.The present invention not only can as helicopter VTOL and spot hover, but also the high-performance cruise ability with jet-propelled fixed wing aircraft, while the aircraft has the advantages that structure is simple, maintainability is good, cheap, possesses boundless application prospect.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of fixed-wing flight that can be vertically moved up or down
Device.
Background technique
Due to fixed wing aircraft need certain time and distance it is sliding run can takeoff and landing, to landing site
There is certain requirement.However it is expensive, time-consuming to build landing site, and wartime is easily destroyed.Therefore, people wish always for a long time
Prestige has one kind can be in the aviation aircraft of small space landing.The birth of helicopter meets this demand of people.Helicopter
Rotor be both lifting surface and control surface, it enables helicopter VTOL, spot hover.But as fixed-wing flies
The structure type of machine determines that its existing defects in landing is the same, and the structure type of helicopter also determines it in some aspects
Shortcomings, such as: bare weight coefficient is big, and load factor is small, and cruise power to weight ratio is big, and pneumatic efficiency is low, therefore less economical；Structure
It is complicated, fragile expensive；Vibration is big, and stability is bad；Due to the airflow asymmetry situation of rotor under preceding winged working environment, go straight up to
Machine maximum forward flight speed is limited by advancing blade comperssibility influence and the separation of retreating blade air-flow, the maximum of pure helicopter
Cruising speed is usually at 300 kilometers/hour or so.In many occasions, speed is also at the key factor for restricting helicopter application.
Therefore, the characteristics of helicopter and fixed wing aircraft can be had both by developing a kind of aircraft, allow it civilian
It can play an important role in military affairs, be the problem that current those skilled in the art need to solve.
Summary of the invention
In view of this, the present invention provides a kind of fixations being vertically moved up or down for having both helicopter and fixed wing aircraft advantage
Rotor aircraft.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of Fixed Wing AirVehicle being vertically moved up or down, including body and the machine left wing being set on body and machine right flank, institute
Integral installation has a rotary shaft in Shu Ji left wing and machine right flank and the rotary shaft extends transversely through entire body, is being located at body portion
A circle gear is fixedly installed on the rotary shaft outer surface of position, the gear passes through pneumatic rotary device control rotation；
The junction of the machine left wing, machine right flank and the body is equipped with inclining rotary mechanism；
The rear end of the machine left wing and machine right flank is respectively symmetrically equipped with several propeller power devices；
The front and back both sides of the machine left wing and machine right flank upper surface are symmetrically installed with several jet power units.
By using above-mentioned technical proposal, the invention has the benefit that the present invention is by designing machine left wing, machine right flank
For can tilting type structure, while propeller power device being installed in machine left wing, machine right flank, make the aircraft had one it is secondary both
It can be used as rotor rotate at high speed, and the host wing as fixed-wing can be locked.Simultaneously the present invention by setting rotary shaft with
And jet power unit is installed in machine left wing, machine right flank, the driving method for rotating host wing had both included that traditional axis drives,
Again include wing tip reaction driving, substantially increases the rotation efficiency of host wing.
Preferably, the pneumatic rotary device includes cylinder, gear drive and angle demodulator, outside the cylinder
Shape is integrally in rectangle, and the gear drive is installed in cylinder comprising be fixed on described cylinder one end rack gear row one,
The rack gear row two being connected with the cylinder piston medial surface, rack gear row one and rack gear row two in being oppositely arranged up and down, and
The rack gear row one, rack gear row two and the gear of the rotary shaft outer surface are intermeshed, and the angle demodulator includes connection
Piston rod on the cylinder piston lateral surface, the motor of displacement sensor, promotion piston rod movement on piston rod
And the controller being connected with motor and displacement sensor.In the present invention, pneumatic rotary device is controlled by angle demodulator
The movement of gear transmission structure, then gear transmission structure drives the gear rotation in rotary shaft, final to realize turning for rotary shaft
Dynamic adjustable angle.
Preferably, the rack shapes that the rack gear row one and rack gear arrange two outboard ends are all larger than other rack gears.In this way when
Gear in rotary shaft can also allow rotation by the self-locking of end rack gear after turning to the end of rack gear row one and rack gear row two
Axis stops operating, and the angle demodulator on pneumatic rotary device is assisted to realize being precisely controlled to the rotational angle of rotary shaft.
Preferably, the propeller power device in the machine left wing and machine right flank is two or three.
Preferably, the propeller power device is connected with the intracorporal engine device of the machine.
Preferably, the jet power unit include air compressor, dried-air drier, air accumulator, filter, it is normally opened/often
Close solenoid valve, electric control valve and safety valve, be sequentially connected with rubber hose between each device by steel pipe together with, the electricity
It is also connected with nozzle outside dynamic regulating valve, the nozzle is symmetrically arranged on the front and back both sides of the machine left wing and machine right flank upper surface.
Since the high pressure gas humidity come out from air compressor machine is very big, its corrosion to pipeline and valve and instrument in order to prevent, the present invention
Drying machine and filter have been concatenated in jet flow pipeline.It is furthermore preferred that two filters are sequentially there are two the filter settings
Connection.
Preferably, small pressure, temperature and velocity sensor are installed, the sensor and aircraft are total at the nozzle
Console is connected.Specifically: sensor signal is transmitted to by rotating part by non-rotating portion by collecting ring, by survey
Pressure, temperature and the velocity amplitude of air-flow are analyzed at the jet hole obtained, realize the reasonable control to spray air flow.
Preferably, the electric control valve is connected with aircraft supervisory control desk, by aircraft supervisory control desk according to acquisition
Data analysis result adjust its opening and closing degree.
Beneficial effects of the present invention: the present invention is the combination of rotor craft and Fixed Wing AirVehicle, maximum feature
It is to have a pair that can not only be used as rotor rotate at high speed, but also the rotor blade as fixed-wing can be locked, makes it both can be as straight
The such VTOL of the machine of liter and spot hover, and the high-performance cruise ability with jet-propelled fixed wing aircraft.The aircraft has
The advantage that structure is simple, maintainability is good, cheap, boundless application prospect is possessed in military-civil field.
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 the overall structure diagram for the Fixed Wing AirVehicle that one kind provided by the invention can be vertically moved up or down.
Fig. 2 attached drawing is the structural schematic diagram of pneumatic rotary device of the present invention.
Fig. 3 attached drawing is the scheme of installation of jet power unit of the present invention.
Wherein, in figure,
1- body；2- machine left wing；3- machine right flank；4- rotary shaft；5- gear；6- pneumatic rotary device, 61- cylinder, 62- gear pass
Motivation structure, 621- rack gear arrange one, 622- rack gear and arrange two, 63- angle demodulator；7- propeller power device；8- nozzle.
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.
Embodiment
As shown in Figure 1, the embodiment of the invention discloses the Fixed Wing AirVehicle that can be vertically moved up or down of one kind, including body 1 with
And it is set to the machine left wing 2 on body 1 and machine right flank 3, aircraft integral installation in machine left wing 2 and machine right flank 3 has one
The rotary shaft 4 and rotary shaft 4 extends transversely through entire body is also fixedly mounted on 4 outer surface of rotary shaft for being located at 1 position of body
There is a circle gear 5, which passes through a pneumatic rotary device 6 control rotation.
As shown in Fig. 2, above-mentioned pneumatic rotary device 6 specifically includes in the embodiment of the present invention: cylinder 61, gear drive
62 and angle demodulator 63.Wherein 61 shape of cylinder is integrally in rectangle, and piston is located at the right end in cylinder cylinder；Gear drive machine
Structure 62 is installed on cylinder piston and cylinder block is formed by space comprising the rack gear row one being fixed on the inside of cylinder left end
621 and the rack gear row 2 622 that is connected with cylinder piston medial surface, rack gear row 1 and rack gear row 2 622 are in opposite up and down
Setting, and rack gear row 1, rack gear row 2 622 and the gear 5 of 4 outer surface of rotary shaft are intermeshed, that is to say, that rack gear row
1 and rack gear row 2 622 relative in rotary shaft 4 gear 5 be symmetrical arranged.When cylinder piston is mobile, rack gear row will push
2 622 is mobile, since rack gear row 1, rack gear row 2 622 and the gear 5 of 4 outer surface of rotary shaft are intermeshed, therefore can band
Moving gear 5 and rotary shaft 4 rotate, the final wing rotation for driving aircraft.
Further, angle demodulator 63 includes: the piston rod being connected on cylinder piston lateral surface, is located on piston rod
Displacement sensor, the motor for pushing piston rod mobile and the controller being connected with motor and displacement sensor.Angle tune
Section device 63 connect setting with piston rod, for limiting the shift position of piston, specifically: power is provided by motor, passes through position
Displacement sensor incudes moving distance, and the information that controller feed back by displacement sensor controls the start and stop of motor, the controller and
Aircraft supervisory control desk is connected.
The rack shapes that rack gear row 1 and rack gear arrange 622 2 outboard ends are also designed as by the embodiment of the present invention simultaneously
Greater than other rack gears, when piston is pushed to the end of rack gear row, which can also withstand piston, and it is further forward to limit it
Movement, and then assist angle demodulator 63 realize to rotary shaft 4 rotate angle accurate control.
In the embodiment of the present invention, the junction of machine left wing 2, machine right flank 3 and body 1 is equipped with inclining rotary mechanism, the inclining rotary mechanism
Be able to achieve 90 ° of rotations of machine left wing 2 and machine right flank 3, Ji Ji left wing 2, machine right flank 3 rear end from the upward 90 ° of rotations of horizontality
To vertical state.
In the embodiment of the present invention, the rear end of machine left wing 2 and machine right flank 3 is respectively symmetrically equipped with several propeller power dress
Set 7, it is preferred that the propeller power device 7 is provided with two or three on each wing, all propeller power devices
7 are connected with the engine device in body 1.When aircraft needs VTOL or hovering, propeller power dress
It sets 7 and is rotated into 1 top of body, while wing state in a vertical shape, provide the lift to fly upwards for the aircraft；Work as aircraft
When needing to accelerate flight forward, propeller power device 7 is rotated into 1 rear of body, while wing is in a horizontal state, and flies for this
The thrust of row device offer flight forward.
In order to advanced optimize technical solution of the present invention, the engine device of control propeller power device 7 in body
Two should be at least arranged, general 4-8 platform is advisable, and as needed, which can choose whirlpool paddle, also can choose
Turbofan is either arranged in pairs or groups simultaneously using two kinds or three kinds of different engine devices, so that propeller power device 7 has enough
Big lift and thrust.
If as shown in figure 3, the front and back both sides of 3 upper surface of Zhong Ji of embodiment of the present invention left wing 2 and machine right flank are symmetrically installed with
Dry gas power device.This is because the wing of aircraft is generally all very heavy, the machines such as rotary shaft 5, pneumatic rotary device 6 are relied solely on
Tool transmission mechanism is likely difficult to that wing is made to obtain effect of preferably verting, and rotates the mill to mechanical transmission mechanism for a long time
Damage consumption is also very big, therefore is based on this, and the present invention is additionally arranged several jet power units again, which is mainly rotation
The nozzle 8 of wing provides compressed air, while controlling the flow of compressed air, realizes wing by jet reaction
Vert comprising air compressor, dried-air drier, air accumulator, filter, normally opened/normally closed solenoid valve, electric control valve with
And safety valve, be sequentially connected with rubber hose by steel pipe between each device together with, nozzle 8 is also connected with outside electric control valve.
As shown in Figure 1, nozzle 8 is symmetrically arranged on the front and back both sides of 3 upper surface of machine left wing 2 and machine right flank, small-sized pressure is installed at nozzle 8
Power, temperature and velocity sensor, these sensors are connected with aircraft supervisory control desk.Specific workflow are as follows: pass through collection
It flows ring and sensor signal is transmitted to non-rotating portion by rotating part, then transmit it to aircraft supervisory control desk, master control
Platform is analyzed by pressure, temperature and the velocity amplitude to air-flow at the jet hole measured, final to control on jet power unit
Electric control valve realizes the reasonable control to spray air flow, and then control the tilt angle of wing by adjusting its opening and closing degree
Degree.
Since the high pressure gas humidity come out from air compressor machine is very big, its corruption to pipeline and valve and instrument in order to prevent
Erosion, the present invention have concatenated drying machine and filter in jet flow pipeline.It is furthermore preferred that there are two filter settings, two filterings
Device is sequentially connected with, to ensure that high pressure gas is constantly in reasonable humidity range.
The present invention has two kinds of offline mode of gyroplane and fixed wing aircraft simultaneously, by supervisory control desk to both of which
Mutually conversion, make the aircraft can VTOL, hovering but high speed, efficiently cruise, compared to existing flight
Device, practicability with higher.
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. the Fixed Wing AirVehicle that one kind can be vertically moved up or down, including body and the machine left wing being set on body and machine right flank,
It is characterized in that, integral installation has a rotary shaft in the machine left wing and machine right flank and the rotary shaft extends transversely through entire machine
Body, is fixedly installed with a circle gear on the rotary shaft outer surface for being located at body area, and the gear passes through a pneumatic rotation
Rotary device control rotation；
The junction of the machine left wing, machine right flank and the body is equipped with inclining rotary mechanism；
The rear end of the machine left wing and machine right flank is respectively symmetrically equipped with several propeller power devices；
The front and back both sides of the machine left wing and machine right flank upper surface are symmetrically installed with several jet power units.
2. the Fixed Wing AirVehicle that one kind according to claim 1 can be vertically moved up or down, which is characterized in that the pneumatic rotation
Rotary device includes cylinder, gear drive and angle demodulator, and the cylinder shape is integrally in rectangle, the gear drive
Mechanism is installed in cylinder comprising the rack gear for being fixed on described cylinder one end arranges one, is connected with the cylinder piston medial surface
The rack gear row two connect, the rack gear row one and rack gear row two are in be oppositely arranged up and down, and the rack gear arranges one, rack gear row two and institute
The gear intermeshing of rotary shaft outer surface is stated, the angle demodulator includes the work being connected on the cylinder piston lateral surface
Stopper rod, the motor and be connected with motor and displacement sensor that displacement sensor, promotion piston rod on piston rod move
The controller connect.
3. the Fixed Wing AirVehicle that one kind according to claim 2 can be vertically moved up or down, which is characterized in that the rack gear row
One and rack gear arrange two outboard ends rack shapes be all larger than other rack gears.
4. the Fixed Wing AirVehicle that one kind according to claim 1 can be vertically moved up or down, which is characterized in that the machine left wing
It is two or three with the propeller power device in machine right flank.
5. according to claim 1 or the Fixed Wing AirVehicle that can be vertically moved up or down of one kind described in 4, which is characterized in that the spiral shell
Rotation paddle power device is connected with the intracorporal engine device of the machine.
6. the Fixed Wing AirVehicle that one kind according to claim 1 can be vertically moved up or down, which is characterized in that the aerodynamic force
Device includes air compressor, dried-air drier, air accumulator, filter, normally opened/normally closed solenoid valve, electric control valve and peace
Full valve, be sequentially connected with rubber hose by steel pipe between each device together with, be also connected with nozzle outside the electric control valve, institute
State the front and back both sides that nozzle is symmetrically arranged on the machine left wing and machine right flank upper surface.
7. the Fixed Wing AirVehicle that one kind according to claim 6 can be vertically moved up or down, which is characterized in that the filter
There are two settings, and two filters are sequentially connected with.
8. the Fixed Wing AirVehicle that one kind according to claim 6 can be vertically moved up or down, which is characterized in that at the nozzle
Small pressure, temperature and velocity sensor are installed, the sensor is connected with aircraft supervisory control desk.
9. the Fixed Wing AirVehicle that one kind according to claim 6 can be vertically moved up or down, which is characterized in that the electric adjustable
Section valve is connected with aircraft supervisory control desk.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274487.7A CN109263930A (en) | 2018-10-30 | 2018-10-30 | A kind of Fixed Wing AirVehicle being vertically moved up or down |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274487.7A CN109263930A (en) | 2018-10-30 | 2018-10-30 | A kind of Fixed Wing AirVehicle being vertically moved up or down |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263930A true CN109263930A (en) | 2019-01-25 |
Family
ID=65195116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274487.7A Withdrawn CN109263930A (en) | 2018-10-30 | 2018-10-30 | A kind of Fixed Wing AirVehicle being vertically moved up or down |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263930A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110450938A (en) * | 2019-08-16 | 2019-11-15 | 刘忠革 | A kind of whole rotatable aircraft of wing |
| CN111268120A (en) * | 2020-03-11 | 2020-06-12 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN113581460A (en) * | 2021-08-11 | 2021-11-02 | 西南交通大学 | Intelligent hoisting and transporting aircraft with symmetric wings for vertical take-off and landing |
-
2018
- 2018-10-30 CN CN201811274487.7A patent/CN109263930A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110450938A (en) * | 2019-08-16 | 2019-11-15 | 刘忠革 | A kind of whole rotatable aircraft of wing |
| CN111268120A (en) * | 2020-03-11 | 2020-06-12 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN111268120B (en) * | 2020-03-11 | 2022-03-22 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN113581460A (en) * | 2021-08-11 | 2021-11-02 | 西南交通大学 | Intelligent hoisting and transporting aircraft with symmetric wings for vertical take-off and landing |
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| PB01 | Publication | ||
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Application publication date: 20190125 |