CN109421921A - A kind of tilt rotor aircraft method that actively intervention controls center of gravity - Google Patents
A kind of tilt rotor aircraft method that actively intervention controls center of gravity Download PDFInfo
- Publication number
- CN109421921A CN109421921A CN201710732892.8A CN201710732892A CN109421921A CN 109421921 A CN109421921 A CN 109421921A CN 201710732892 A CN201710732892 A CN 201710732892A CN 109421921 A CN109421921 A CN 109421921A
- Authority
- CN
- China
- Prior art keywords
- tilt rotor
- rotor aircraft
- gravity
- aircraft
- flight
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
-
- 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
- B64C27/22—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
Abstract
A kind of tilt rotor aircraft method that actively intervention controls center of gravity, affiliated tilt rotor aircraft control technology field, when converting flight attitude the present invention relates to tilt rotor aircraft, control center of gravity is intervened using active, tilt rotor aircraft is made to automatically control the solution of balance.During mutually being converted between vertical lift state (dual-rotor helicopter mode) and state of flight of marching forward (fixed-wing mode), when adjusting aircraft pitch attitude using two propeller difference rotational angles in vertical lift state (dual-rotor helicopter mode), all there is engine (motor) rotation reaction force, easily causes air crash failure.The technical solution adopted by the present invention is that: counterweight (airborne equipment etc.) is moved back and forth in head and tail direction using controller, the heart is thought highly of in active change of flight, utilizes gravitation correction aircraft pitch attitude.
Description
Technical field
When invention is related to tilt rotor aircraft transformation flight attitude, control center of gravity is intervened using active, makes to incline
Inclined rotary-wing aircraft automatically controls the solution of balance.
Background technique
Tilt rotor aircraft is a kind of not only with pure helicopter VTOL and hovering ability, but also has spiral
The rotor craft of paddle aircraft high speed cruise flight ability.
The principle (Fig. 1) as helicopter is used when tilt rotor aircraft is taken off, and passes through two propellers
Air-flow reaction force mentions aircraft.Then the angle (Fig. 2) for gradually adjusting propeller, so that tilt rotor aircraft is by hanging down
Straight jacking condition becomes forward flight state.When having reached certain speed, wing can satisfy tilt rotor aircraft
When lift needs, propeller horizontality (Fig. 3) has been tuned into just.This principle is in fact very simple.But meet double helix
Paddle is extremely difficult from vertically becoming this horizontal process.
Because mutually being converted between vertical lift state (dual-rotor helicopter mode) and state of flight of marching forward (fixed-wing mode)
During, easily cause air crash failure.
Summary of the invention
In order to overcome the problems, such as that tilt rotor aircraft is unstable in flight course, invention will provide an arbitrage
Control center of gravity is intervened with active, makes the technical solution of tilt rotor aircraft smooth flight.
Invention solves the problems, such as that the used technical solution of its unbalance is: when tilt rotor aircraft flies
When being influenced to occur nosepiston by external force during row, using controller to counterweight (airborne equipment) head and tail direction come
Return is dynamic, changes tilt rotor aircraft center of gravity, and the tilt rotor aircraft head made and tail keep horizontality.
Case is embodied:
Such as (one)
1, when tilt rotor aircraft engine from vertical mode into horizontal pattern transition process, engine (motor) verts
Reaction force makes nose-high, then controls counterweight (airborne equipment) by sliding rail to heading movement, make to incline using gravity
Inclined rotary-wing aircraft head and tail keep horizontality.(Fig. 4)
2, for tilt rotor aircraft in flight, when head is out of control upwards, then control controls counterweight (airborne equipment) by sliding rail
It is mobile to heading by sliding rail, so that tilt rotor aircraft head and tail is kept horizontality using gravity.(Fig. 4)
1, when tilt rotor aircraft engine from horizontal pattern into vertical mode transition process, engine (motor) verts
Reaction force makes head downward, then controls counterweight (airborne equipment) by sliding rail to the movement of tail direction, make to incline using gravity
Inclined rotary-wing aircraft head and tail keep horizontality.(Fig. 5)
2, for tilt rotor aircraft in flight, when head is out of control downwards, then control controls counterweight (airborne equipment) by sliding rail
It is mobile to tail direction by sliding rail, so that tilt rotor aircraft head and tail is kept horizontality using gravity.(Fig. 5)
Detailed description of the invention:
This patent is further illustrated with reference to the accompanying drawings and examples
Fig. 1: tilt rotor aircraft hovers mode (dual-rotor helicopter mode)
Fig. 2: tilt rotor aircraft is in hovering mode, between fixed-wing mode in conversion process, and 45 degree of engine tilts.
Fig. 3: state of flight of marching forward (fixed-wing mode).
Fig. 4: from vertical mode into horizontal pattern transition process, engine (motor) inclines tilt rotor aircraft engine
The reaction force turned makes nose-high, then it is mobile to tail head direction by sliding rail to control counterweight (airborne equipment).
Fig. 5: when tilt rotor aircraft engine from horizontal pattern into vertical mode transition process, engine (motor)
The reaction force to vert makes head downward, then it is mobile to tail direction by sliding rail to control counterweight (airborne equipment).
Fig. 6: all parts brief description.
Claims (2)
1. the reaction torsion generated when tilt rotor aircraft engine (motor) verts makes tilt rotor aircraft machine
Head upward or downward, is then moved by center of gravity (counterweight, airborne equipment etc.) to tilt rotor aircraft heading or tail direction
It is dynamic, the reaction torsion generated when engine (motor) verts is offset using gravity, makes tilt rotor aircraft head and tail
Keep horizontality.
2. tilt rotor aircraft is in flight, when head is out of control upward or downward, then by center of gravity (counterweight, airborne equipment etc.)
It is mobile to tilt rotor aircraft heading or tail direction, tilt rotor aircraft head and tail are kept using gravity
Horizontality.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710732892.8A CN109421921A (en) | 2017-08-24 | 2017-08-24 | A kind of tilt rotor aircraft method that actively intervention controls center of gravity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710732892.8A CN109421921A (en) | 2017-08-24 | 2017-08-24 | A kind of tilt rotor aircraft method that actively intervention controls center of gravity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109421921A true CN109421921A (en) | 2019-03-05 |
Family
ID=65500303
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710732892.8A Pending CN109421921A (en) | 2017-08-24 | 2017-08-24 | A kind of tilt rotor aircraft method that actively intervention controls center of gravity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109421921A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010028018A1 (en) * | 2000-03-16 | 2001-10-11 | Darbyshire Ian T. | Flight control system for an aircraft |
| US20050051666A1 (en) * | 2003-09-04 | 2005-03-10 | Supersonic Aerospace International, Llc | Aircraft with active center of gravity control |
| KR20090101413A (en) * | 2009-08-21 | 2009-09-28 | 곽상호 | Vertical takedff and landingairplane |
| CN203767067U (en) * | 2014-01-28 | 2014-08-13 | 河海大学 | Centre-of-gravity shift yawing device for helicopters |
| CN105059535A (en) * | 2015-09-14 | 2015-11-18 | 江富余 | Gravity trimming vertical lift aircraft |
| CN106081086A (en) * | 2016-08-03 | 2016-11-09 | 安阳全丰航空植保科技股份有限公司 | The dynamic many rotors agricultural plant protection unmanned helicopter flight attitude regulation device of oil |
| CN106114822A (en) * | 2016-08-03 | 2016-11-16 | 安阳全丰航空植保科技股份有限公司 | The dynamic many rotors agricultural plant protection helicopter flight attitude regulator control system of oil |
| CN106143885A (en) * | 2015-03-24 | 2016-11-23 | 马世强 | Single rotor high-speed helicopter |
-
2017
- 2017-08-24 CN CN201710732892.8A patent/CN109421921A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010028018A1 (en) * | 2000-03-16 | 2001-10-11 | Darbyshire Ian T. | Flight control system for an aircraft |
| US20050051666A1 (en) * | 2003-09-04 | 2005-03-10 | Supersonic Aerospace International, Llc | Aircraft with active center of gravity control |
| KR20090101413A (en) * | 2009-08-21 | 2009-09-28 | 곽상호 | Vertical takedff and landingairplane |
| CN203767067U (en) * | 2014-01-28 | 2014-08-13 | 河海大学 | Centre-of-gravity shift yawing device for helicopters |
| CN106143885A (en) * | 2015-03-24 | 2016-11-23 | 马世强 | Single rotor high-speed helicopter |
| CN105059535A (en) * | 2015-09-14 | 2015-11-18 | 江富余 | Gravity trimming vertical lift aircraft |
| CN106081086A (en) * | 2016-08-03 | 2016-11-09 | 安阳全丰航空植保科技股份有限公司 | The dynamic many rotors agricultural plant protection unmanned helicopter flight attitude regulation device of oil |
| CN106114822A (en) * | 2016-08-03 | 2016-11-16 | 安阳全丰航空植保科技股份有限公司 | The dynamic many rotors agricultural plant protection helicopter flight attitude regulator control system of oil |
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