CN107902084A - A kind of tilt rotor aircraft rotor wing rotation structure design - Google Patents
A kind of tilt rotor aircraft rotor wing rotation structure design Download PDFInfo
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- CN107902084A CN107902084A CN201711156035.4A CN201711156035A CN107902084A CN 107902084 A CN107902084 A CN 107902084A CN 201711156035 A CN201711156035 A CN 201711156035A CN 107902084 A CN107902084 A CN 107902084A
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- rotor
- wing
- gear
- aircraft
- tilt
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of tilt rotor aircraft rotor wing rotation structure design.Tilt rotor aircraft feature performance benefit：Speed is fast；Noise is small；Voyage is remote；Loading capacity is big；Oil consumption rate is low；Cost of transportation is low；It is with small vibration.The present invention changes rotor and airframe angle, realizes that rotor verts from upright position to horizontal level or horizontal level to upright position by a kind of gear assembled structure.
Description
Technical field
The present invention relates to a kind of tilt rotor aircraft rotor wing rotation structure design.
Background technology
Tilt rotor aircraft, using the osprey tilt rotor aircraft in the U.S. as representative, V-22, i.e. osprey tilt rotor aircraft generation
Number, start to research and develop in the last century 80's, first-fly success on March 19th, 1989, undergoes prolonged test, modification, verification
After work.Enter United States Air Force on November 16th, 2006 to be on active service, be on active service in U. S. Marine Corps within 2007, the same year leaves for A Fu
Sweat carries out actual combat deployment.
But two rotatable driven by engine two of wing tip have rotor, and under fixed-wing state, V-22 seems a frame
In both sides, wing tip has the aircraft of the propeller of two super larges；Under helicopter state, V-22 seem again a frame have two it is less than normal
Rotor helicopter, it is possessed the vertical lift ability of helicopter, but possess fixed rotor and propeller aircraft at a high speed,
Voyage is remote and the advantages of oil consumption is relatively low, and maximum flying speed is to fly most fast helicopter at present in the world up to 509 kilometers.
Heligyro feature performance benefit：Speed is fast；Noise is small；Voyage is remote；Loading capacity is big；Oil consumption rate is low；Cost of transportation is low；
It is with small vibration.
Although tiltrotor has many advantages compared with general helicopter, also there is many shortcomings, be mainly manifested in as
Under several aspects.Development cost is high, unit is of high cost：Since tiltrotor is a new high-tech product, its technical sophistication,
Difficulty is high, therefore to verify that every technology needs very high expense, causes development cost and unit cost all prohibitively high.As beautiful
The development cost of " osprey " tiltrotor of state is up to 38,000,000,000 dollars, the unit price of its maritime version MV-22 is up to 44,000,000 dollars.Skill
Art difficulty is high：Tiltrotor will realize rotor from upright position to horizontal level or water because existing rotor has wing again
Prosposition, which is put to upright position, to vert, thus during rotor verts aerodynamic characteristic determine；Rotor/wing, rotor/rotor,
Aerodynamic interference problem between rotor/body；Structure design；Dynamic analysis of the rotor during verting, rotor/wing coupling
Close dynamic loading and stability problem；Manipulate control technology and steerable system dynamics Design etc. and all encounter many technologies hardly possiblies
Topic.
The content of the invention
（1）Purpose：It is an object of the present invention to by a kind of gear assembled structure, change rotor and airframe angle,
Realize that rotor verts from upright position to horizontal level or horizontal level to upright position.
（2）Technical solution：
Rotation by the gear for being connected to engine, drives aircraft rotary wing rotation, realizes aircraft rotary wing and turn of fuselage angle
Become, by the cooperation of the morphologic changes such as wing, change the state of flight of aircraft, i.e. aircraft flight angle vertical in fuselage, or
That is aircraft flight angle parallel is in fuselage.Finally realize aircraft vertical rise and fall as helicopter, fly similar to conventional propeller
The same high-speed flight of machine.
Since general propeller aircrafts are to flow to the leading edge of a wing using air, it is divided into upper and lower two strands of air-flows, respectively along wing
When upper and lower surface is flowed through, upper surface of the airfoil compares protrusion, and pressure reduces.And wing lower surface, pressure increase.Because on wing,
There is pressure differential in lower surface, aircraft is overcome self gravitation fly on blue sky by the lift obtained on wing.Vert rotation
Smooth when wing aircraft wing is in order to ensure vertical flight, wing is fairly simple, therefore unless design it is new can in flight according to
According to the wing for needing change form, otherwise it is necessary to do larger improvement in fuselage design aspect, such as U.S. V-22（Osprey is verted rotation
Wing aircraft）Roomy with regard to design adult form, organism bottom is more straight, and the external engine body form that top is rounder and more smooth.Gyroplane exists
Air hydrodynamics test should be carried out during change of flight state, to find the state of flight requirement of special period.
The present invention is simply related to the part of rotor wing rotation, respective design and automatic control for wing and airframe
The problems such as processed, is not related to.
Tilt rotor aircraft rotor wing rotation structure is made of gear, the band rotating motor of moving gear, and rotor.
The motor rotated with moving gear is fixed on aircraft wing, can realize that gear rotates by motor rotation, rotation
Direct geared or drive the gear being connected with rotor indirectly, and then drive aircraft wing on rotor, realize rotor turn
It is dynamic.The angle for changing rotor and fuselage is rotated by gear, realizes that rotor is vertical with airframe, or and standard of fuselage.
（3）Beneficial effect：Tilt rotor aircraft flying speed is fast, and landing is flexible, and loading capacity is big, can extensively using with army
In thing and social construction activity, huge economic benefit and military value are achieved in the U.S..And China's correlative study, exploitation are just
In the starting stage.
The present invention have the advantages that following features and：Principle is simple, simple in structure.Gear can produce larger torque, full
The overall mechanical requirements of sufficient gyroplane rotor part.Pass through the structure, it is possible to achieve the flexible rotating movement of rotor structure,
Realize that a crucial step is carried out in the flight of rotor multi-angle for gyroplane.
（4）Brief description of the drawings：
Fig. 1 is a normal cross-section schematic diagram after the present invention is connected with rotor.
Fig. 2 is Fig. 1 parts A-A diagrammatic cross-sections of the present invention.
（5）Embodiment：
Whole device structure is included with lower part：1 crust of the device, 2 master gears, 3 connecting shafts, 4 master gear lightening holes, 5 master gears
With rotor coupling part, 6 auxiliary gears, 7 auxiliary gear rotation axis, 8 auxiliary gear lightening holes, 9 motors, 10 device fixed structures, are machines
A part for the wing, 11 rotor structures.
Inventive structure passes through 10 device fixed structures, i.e. aircraft wing end connection aircraft.Total gear parts are all
It is tightly fitted to inside 1 crust of the device, 1 crust of the device is fixed on 10 device fixed structures.2 master gears and 6 auxiliary gears respectively have 4
Master gear lightening hole and 8 auxiliary gear lightening holes mitigate gear parts weight.Device passes through 5 master gears and rotor coupling part, weldering
Connect or connected using bolt etc., 2 master gears are fixed with 11 rotor structures.11 rotor structures are crossed in 3 connecting shafts, by 3 connections
Axis supports, and can rotate by a certain angle around 3 connecting shafts.3 connecting shafts are the epitaxial parts of wing.
6 auxiliary gears rotate under the drive of 9 motors, and control 2 master gears rotation, passes through 5 master gears and rotation after the rotation of 2 master gears
Wing coupling part drives 11 rotor structures to be rotated around 3 connecting shafts, realizes rotor within the specific limits.As 11 rotors can be 0
In the range of ~ 90 degree of degree, freely change the angle of 11 rotor structures and airframe.
Claims (3)
- A kind of 1. tilt rotor aircraft rotor wing rotation structure design, by the motor, rotatable gear and rotation that are fixed on wing The wing forms.
- 2. tilt rotor aircraft rotor wing rotation structure design according to claim 1, gear is divided into the main tooth of connection rotor Wheel, rotates the auxiliary gear of master gear, auxiliary gear can be single gear or gear set.
- 3. tilt rotor aircraft rotor wing rotation structure design according to claim 1, drives the master gear of rotor to pass through weldering Connect, or bolt etc. is fixed on the appropriate location of rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711156035.4A CN107902084A (en) | 2017-11-20 | 2017-11-20 | A kind of tilt rotor aircraft rotor wing rotation structure design |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711156035.4A CN107902084A (en) | 2017-11-20 | 2017-11-20 | A kind of tilt rotor aircraft rotor wing rotation structure design |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107902084A true CN107902084A (en) | 2018-04-13 |
Family
ID=61846283
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711156035.4A Pending CN107902084A (en) | 2017-11-20 | 2017-11-20 | A kind of tilt rotor aircraft rotor wing rotation structure design |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107902084A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3236027A1 (en) * | 1982-07-07 | 1984-01-12 | Bernd 6352 Ober-Mörlen Jung | Drive for a helicopter |
| CN101973398A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Tilt rotation driving mechanism for tilt rotation nacelle of tilt rotor craft |
| CN103434642A (en) * | 2013-08-20 | 2013-12-11 | 朱幕松 | Linked double-wing and double-rotor-wing vertical lifting aircraft |
| CN103466088A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Nacelle gear tilting mechanism for tilt rotor aircraft |
-
2017
- 2017-11-20 CN CN201711156035.4A patent/CN107902084A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3236027A1 (en) * | 1982-07-07 | 1984-01-12 | Bernd 6352 Ober-Mörlen Jung | Drive for a helicopter |
| CN101973398A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Tilt rotation driving mechanism for tilt rotation nacelle of tilt rotor craft |
| CN103434642A (en) * | 2013-08-20 | 2013-12-11 | 朱幕松 | Linked double-wing and double-rotor-wing vertical lifting aircraft |
| CN103466088A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Nacelle gear tilting mechanism for tilt rotor aircraft |
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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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180413 |