CN109263910A - A kind of aircraft of new vertical landing - Google Patents
A kind of aircraft of new vertical landing Download PDFInfo
- Publication number
- CN109263910A CN109263910A CN201811274331.9A CN201811274331A CN109263910A CN 109263910 A CN109263910 A CN 109263910A CN 201811274331 A CN201811274331 A CN 201811274331A CN 109263910 A CN109263910 A CN 109263910A
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- CN
- China
- Prior art keywords
- power device
- motor
- wing
- aircraft
- fuselage
- 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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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 2
- 230000005611 electricity Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
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
- B64C27/26—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
- 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
A kind of new vertical takeoff and landing vehicle belongs to vehicle technology field, including fuselage, control system, the first power device, the second power device, third power device, steering engine, wing, horizontal tail, vertical fin, undercarriage.Fuselage includes head and cabin, and head includes engine and battery, and cabin includes operating stick, control system, seat and instrument board；First power device is located in front of head, and wing is located at the left and right sides of fuselage, and wing has two altogether, there is an arc groove on each wing；Second power device and third power device are located in the arc groove of wing；Steering engine is connected with the second power device；Horizontal tail and vertical fin are located at afterbody；Undercarriage is located at below fuselage, is laid out using rear bikini.The present invention takes full advantage of lift caused by the second power device and drives aircraft vertical landing, and saving required place when taking off and landing improves efficiency when flight.
Description
Technical field
A kind of aircraft of new vertical landing belongs to vehicle technology field more particularly to a kind of new vertical landing
Aircraft.
Background technique
Traditional Fixed Wing AirVehicle flight course safety, the feature that flying speed is fast, voyage is remote and carrying capacity is big, but
Landing process is required to use runway and can not be hovered in the sky；And fixed wing aircraft becomes the first choice of people's trip, but by field
The limitation on ground, most of clients are unable to satisfy the flight desire of oneself, greatly limit the development of aircraft in this way and popularize.
Summary of the invention
The purpose of the present invention is overcoming the shortcomings of above-mentioned traditional aircraft, a kind of aircraft of new vertical landing is invented.
A kind of aircraft of new vertical landing, including fuselage, control system, the first power device, the second power device,
Third power device, steering engine, wing, horizontal tail, vertical fin, undercarriage.
The fuselage includes head and cabin, and head includes engine and battery, and cabin includes operating stick, control system
System, seat and instrument board；First power device is located in front of head, and the wing is located at the left and right sides of fuselage,
Wing has two altogether, there is an arc groove on each wing；Second power device and third power device is located at wing
Arc groove in；The steering engine is connected with the second power device；The horizontal tail and vertical fin is located at afterbody；Described rises
It falls frame to be located at below fuselage, be laid out using rear bikini.
The engine provides power for the first power device；The battery is capable of providing electric energy and fills to the second power
It sets；The control system is capable of the operation of feedback operation bar progress, and the revolving speed of control first motor, and described first is dynamic
Power device uses two blade propeller, is connected with engine, provides the power of flight for aircraft；The wing be divided into left wing and
Right flank mainly provides lift in flight course, enables the flight of aircraft held stationary in the sky；Second power
Device includes first crossbeam and the first motor with propeller, and the first crossbeam is connected using bearing with arc groove, the
First motor is installed on one crossbeam, as the support of first motor, the first motor is upward；The third power dress
The second motor including second cross beam and with propeller is set, the second cross beam is connected using bearing with arc groove, and second
Second motor is installed, as the support of first motor on crossbeam；Second motor is downward；The steering engine is located at arc
It in slot, is rotated for controlling first crossbeam, first motor rotation is driven by the rotation of first crossbeam, to mention for aircraft
For auxiliary power.
The first crossbeam and second cross beam is made of Carbon fibe material.
A kind of aircraft of new vertical landing also has GPS, radar and infrared camera.
A kind of working principle of the aircraft of the new vertical landing are as follows: when taking off, the first electricity of control system control
Machine and the second electric motor starting, the lift of the second power device and third power device just can drive aircraft to take off vertically；Fly
When machine rises to safe airspace, the first power device starts to start, and just drives aircraft flight forward；Then control system control flaps
Machine drives first crossbeam to rotate 15 degree along normal, thus to provide auxiliary power when aircraft flight；When aircraft need to the left or
When person bends to right, operating stick implements the operation turned to the left, and controller just controls first motor and the second motor in left wing
Revolving speed is reduced, the first motor and the second motor in right flank increase revolving speed, then control vertical fin carry out auxiliary turning, are just able to achieve
The left-hand rotation of aircraft；When operating stick implements right-handed operation, controller just controls first motor in right flank and the second motor subtracts
Few revolving speed, first motor and the second motor in left wing increase revolving speed, then control vertical fin carry out auxiliary turning, are just able to achieve winged
The right-hand rotation of machine；When aircraft needs to land, aircraft flies to the top airspace in landing place, starts the first motor on wing and the
Two motors just reduce hair when hovering in the sky until being able to maintain aircraft with lift caused by the second motor in first motor
The revolving speed of motivation, so that aircraft slowly land is then shut off engine, first motor and the second motor to ground.
The present invention takes full advantage of lift caused by the good third power device of the second power device and aircraft vertical is driven to rise
Drop, saving required place when taking off and landing, improves the utilization rate of the efficiency and the energy when flight.
Detailed description of the invention
Fig. 1 is a kind of axis side schematic diagram of the aircraft of new vertical landing, and Fig. 2 is a kind of flight of new vertical landing
The half-section diagram of device, Fig. 3 are the postrotational axis side schematic diagrames of first crossbeam.
In figure, 1- fuselage, 2- engine, 3- battery, 4- operating stick, 5- control system, the first power device of 6-, the left side 7-
The wing, 8- right flank, 9- arc groove, 10- first crossbeam, 11- first motor, 12- second cross beam, the second motor of 13-, 14- steering engine,
15- horizontal tail, 16- vertical fin, 17- undercarriage.
Specific embodiment
The present invention is illustrated now in conjunction with attached drawing: a kind of aircraft of new vertical landing, including fuselage 1, control
System 5 processed, the second power device, third power device, steering engine 14, wing, horizontal tail 15, vertical fin 16, rises first power device 6
Fall frame 17.
The fuselage 1 includes head and cabin, and head includes engine 2 and battery 3, and cabin includes operating stick 4, control
System 5, seat and instrument board；First power device 6 is located in front of head, and the wing is located at the left and right of fuselage 1
Two sides, wing have two altogether, there is an arc groove 9 on each wing；Second power device and third power device position
In the arc groove 9 of wing；The steering engine 14 is connected with the second power device；The horizontal tail 15 and vertical fin 16 is located at fuselage
1 tail portion；The undercarriage 17 is located at 1 lower section of fuselage, is laid out using rear bikini.
The engine 2 is that the first power device 6 provides power；It is dynamic to second that the battery 3 is capable of providing electric energy
Power device；The control system 5 is capable of the operation of the progress of feedback operation bar 4, and the revolving speed of control first motor, described
First power device 6 uses two blade propeller, is connected with engine 2, provides the power of flight for aircraft；The wing point
For left wing 7 and right flank 8, lift is mainly provided in flight course, enables the flight of aircraft held stationary in the sky；It is described
The second power device include first crossbeam 10 and the first motor 11 with propeller, the first crossbeam 10 using bearing with
Arc groove 9 is connected, and first motor 11 is equipped on first crossbeam 10, as the support of first motor 11, first electricity
Machine 11 is upward；The third power device includes second cross beam 12 and the second motor 13 with propeller, and described second is horizontal
Beam 12 is connected using bearing with arc groove 9, and the second motor 13, the branch as first motor 11 are equipped on second cross beam 12
Support；Second motor 13 is downward；The steering engine 14 is located in arc groove 9, is rotated for controlling first crossbeam 10,
First motor 11 is driven to rotate by the rotation of first crossbeam 10, to provide auxiliary power for aircraft.
The first crossbeam 10 and second cross beam 12 are made of Carbon fibe material.
A kind of aircraft of new vertical landing also has GPS, radar and infrared camera.
A kind of working principle of the aircraft of the new vertical landing are as follows: when taking off, first electricity of the control of control system 5
Machine 11 and the starting of the second motor 13, the lift of the second power device and third power device just can drive aircraft vertically to be risen
Fly；When aircraft rises to safe airspace, the first power device 6 starts to start, and just drives aircraft flight forward；Then control system
5 control steering engines 14 drive first crossbeam 10 to rotate 15 degree along normal, thus to provide auxiliary power when aircraft flight；Work as aircraft
When needing to the left or bending to right, operating stick 4 implements the operation turned to the left, and controller just controls the first electricity in left wing 7
Machine 11 and the second motor 13 reduce revolving speed, and the first motor 11 and the second motor 13 in right flank 8 increase revolving speed, then control vertical fin 16
Carry out auxiliary turning, be just able to achieve the left-hand rotation of aircraft；When operating stick 4 implements right-handed operation, controller just controls right flank 8
On first motor 11 and the second motor 13 reduce revolving speed, the first motor 11 and the second motor 13 in left wing 7 increase revolving speed, then
Control vertical fin 16 carries out auxiliary turning, is just able to achieve the right-hand rotation of aircraft；When aircraft needs to land, aircraft flies to landing place
Top airspace, start the first motor 11 and the second motor 13 on wing, in the first motor 11 and 13 institute of the second motor
When the lift of generation is able to maintain aircraft and hovers in the sky, just reduce the revolving speed of engine 2 so that aircraft slowly land to
Face is then shut off engine 2, first motor 11 and the second motor 13.
Claims (3)
1. a kind of aircraft of new vertical landing, it is characterised in that: including fuselage (1), control system (5), the first power dress
Set (6), the second power device, third power device, steering engine (14), wing, horizontal tail (15), vertical fin (16), undercarriage (17)；Institute
The fuselage (1) stated includes head and cabin, and head includes engine (2) and battery (3), and cabin includes operating stick (4), control system
System (5), seat and instrument board；First power device (6) is located in front of head, and the wing is located at fuselage (1)
The left and right sides is divided into left wing (7) and right flank (8), there is an arc groove (9) on each wing；Second power device and
Third power device is located in the arc groove (9) of wing；The steering engine (14) is connected with the second power device；The horizontal tail
(15) and vertical fin (16) is located at fuselage (1) tail portion；The undercarriage (17) is located at below fuselage (1), using rear bikini cloth
Office；First power device (6) uses two blade propeller, is connected with engine (2)；The second power device packet
First crossbeam (10) and the first motor (11) with propeller are included, the first crossbeam (10) is using bearing and arc groove (9)
It is connected, first motor (11), as the support of first motor (11), the first motor is installed on first crossbeam (10)
(11) upward；The third power device includes second cross beam (12) and the second motor (13) with propeller, and described
Using bearing, (9 are connected two crossbeams (12), the second motor (13) are equipped on second cross beam (12), as first with arc groove
The support of motor (11)；Second motor (13) is downward；The steering engine (14) is located in arc groove (9), for controlling
First crossbeam (10) is rotated, and first motor (11) rotation is driven by the rotation of first crossbeam (10), to mention for aircraft
For auxiliary power.
2. a kind of aircraft of new vertical landing according to claim 1, it is characterised in that: the first crossbeam
(10) it is made with second cross beam (12) of Carbon fibe material.
3. a kind of aircraft of new vertical landing according to claim 1 or 2, it is characterised in that: also have GPS, thunder
It reaches and infrared camera.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274331.9A CN109263910A (en) | 2018-10-30 | 2018-10-30 | A kind of aircraft of new vertical landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274331.9A CN109263910A (en) | 2018-10-30 | 2018-10-30 | A kind of aircraft of new vertical landing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263910A true CN109263910A (en) | 2019-01-25 |
Family
ID=65195111
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274331.9A Withdrawn CN109263910A (en) | 2018-10-30 | 2018-10-30 | A kind of aircraft of new vertical landing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263910A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110155317A (en) * | 2019-05-13 | 2019-08-23 | 中国人民解放军国防科技大学 | Oil-electricity hybrid vertical take-off and landing fixed-wing aircraft |
| CN110406684A (en) * | 2019-08-05 | 2019-11-05 | 江苏心源航空科技有限公司 | A kind of tailstock formula vertical take-off and landing drone power device |
-
2018
- 2018-10-30 CN CN201811274331.9A patent/CN109263910A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110155317A (en) * | 2019-05-13 | 2019-08-23 | 中国人民解放军国防科技大学 | Oil-electricity hybrid vertical take-off and landing fixed-wing aircraft |
| CN110406684A (en) * | 2019-08-05 | 2019-11-05 | 江苏心源航空科技有限公司 | A kind of tailstock formula vertical take-off and landing drone power device |
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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 |
Application publication date: 20190125 |
|
| WW01 | Invention patent application withdrawn after publication |