CN103466087A - Nacelle tilting mechanism for tilt rotor aircraft - Google Patents
Nacelle tilting mechanism for tilt rotor aircraft Download PDFInfo
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- CN103466087A CN103466087A CN2013103734159A CN201310373415A CN103466087A CN 103466087 A CN103466087 A CN 103466087A CN 2013103734159 A CN2013103734159 A CN 2013103734159A CN 201310373415 A CN201310373415 A CN 201310373415A CN 103466087 A CN103466087 A CN 103466087A
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Abstract
The invention belongs to the technical field of aircraft design and particularly relates to a nacelle tilting mechanism for a tilt rotor aircraft. The nacelle tilting mechanism is characterized in that the mechanism is arranged in bilateral symmetry about the symmetry plane of an aircraft; the components of the mechanism mainly comprise nacelles (1 and 2), wings (3 and 4), spiral screw rods (7 and 8), gears, main hydraulic motors, an output gear, base frames, driving shafts, universal joints, bevel gears and an intermediate driving shaft (37). The principle of the nacelle tilting mechanism for the tilt rotor aircraft is that the distance between the each connecting point of the spiral screw rods and the nacelles and each connecting point of the spiral screw rods and the wings is changed through the helical motion of the spiral screw rods, thereby pulling the nacelles to perform deflection movement surrounding the rotating shafts of the nacelles; meanwhile, the tilting movements of the nacelles on two sides are connected through the intermediate driving shaft (37). According to the nacelle tilting mechanism for the tilt rotor aircraft provided by the invention, the spiral screw rods (7 and 8) are connected with the nacelles (1 and 2) and the wings (3 and 4), the motion transmission is performed between each of the spiral screw rods (7 and 8) and the intermediate driving shaft (37), and the nacelle tilting mechanism has a redundancy running mode.
Description
Technical field
The invention belongs to the airplane design technical field, be specifically related to a kind of nacelle inclining rotary mechanism of tilt rotor aircraft.
Background technology
Tilt rotor aircraft combines the advantage of heligyro and fixed wing aircraft, the motion of verting by nacelle, realize the conversion between heligyro and fixed wing aircraft, the vertical takeoff and landing of existing helicopter, vertical flight ability, the advantage such as the flying speed that has again fixed wing aircraft concurrently is fast, flying height is large, voyage is far away, flying power is strong.In the tilt rotor aircraft designing technique, the nacelle inclining rotary mechanism is core wherein, and the prior art shorter mention in this respect.Patents through retrieving has two, is respectively US5054716 and US6247667B1.For patent US5054716, it has highlighted the screw propeller rotary drive system of tilt rotor aircraft, the scheme of verting for nacelle has only been done simply and has been mentioned---by screw, drives, one end of screw is connected with wing, one end is connected with nacelle, and how screw is connected with other drive member and transmission component is not introduced.For patent US6247667B1, its nacelle of mainly from the system control angle, having introduced tilt rotor aircraft system of verting, connect to do in detail to mechanism yet and illustrate, as how screw is connected with wing.Therefore, inventing a kind of failure-free nacelle inclining rotary mechanism is the inevitable requirement of grasping tilt rotor aircraft core design technology.
Summary of the invention
The objective of the invention is: the invention provides a kind of nacelle inclining rotary mechanism of tilt rotor aircraft, have the redundance drive pattern, the verting of left and right nacelle moves through center drive shaft and is connected, and this axle drive shaft and nacelle rotating shaft coaxle.
Technical scheme of the present invention is: a kind of nacelle inclining rotary mechanism of tilt rotor aircraft, it is characterized in that, arrangement of mechanism is about aircraft symmetrical plane left-right symmetric, and left side mechanism comprises nacelle 1, wing 3, rotating shaft 5, screw 7, leading screw end 9, nut end 11, gear 13, main HM Hydraulic Motor 15, gear 17, pedestal 23, gear 25, axle drive shaft 27, Hooke's coupling 29, axle drive shaft 31, finishing bevel gear cuter 33, finishing bevel gear cuter 35, center drive shaft 37; Right side mechanism comprises nacelle 2, wing 4, rotating shaft 6, screw 8, leading screw end 10, nut end 12, gear 14, main HM Hydraulic Motor 16, gear 18, pedestal 24, gear 26, axle drive shaft 28, Hooke's coupling 30, axle drive shaft 32, finishing bevel gear cuter 34, finishing bevel gear cuter 36, center drive shaft 37.
Left side mechanism type of attachment is: nacelle 1 is connected by revolute pair with wing 3, the rotating shaft 5 of this revolute pair is fixed on wing 3, the leading screw end 9 of screw 7 is hinged with nacelle 1, nut end 11 is connected with gear 13, gear 13 and gear 17 engagements, the output shaft fixed connection of gear 17 and main HM Hydraulic Motor 15, main HM Hydraulic Motor 15 is connected on pedestal 23, pedestal 23 is connected by revolute pair with 3, wing, its rotation axis is parallel with rotating shaft 5, gear 13 meshes with gear 25 simultaneously, gear 25 is connected with axle drive shaft 27 by cylindrical pair, axle drive shaft 27 1 ends are connected with pedestal 23 by cylindrical pair, the other end is connected with axle drive shaft 31 by crosspin type joint 29, axle drive shaft 31 is connected with finishing bevel gear cuter 33, finishing bevel gear cuter 33 and finishing bevel gear cuter 35 engagements, finishing bevel gear cuter 35 is fixed on center drive shaft 37, center drive shaft 37 is coaxial with rotating shaft 5 and be connected by revolute pair with 3, wing.
Right side mechanism type of attachment is: nacelle 2 is connected by revolute pair with wing 4, the rotating shaft 6 of this revolute pair is fixed on wing 4, the leading screw end 10 of screw 8 is hinged with nacelle 2, nut end 12 is connected with gear 14, gear 14 and gear 18 engagements, the output shaft fixed connection of gear 18 and main HM Hydraulic Motor 16, main HM Hydraulic Motor 16 is connected on pedestal 24, pedestal 24 is connected by revolute pair with 4, wing, its rotation axis is parallel with rotating shaft 6, gear 14 meshes with gear 26 simultaneously, gear 26 is connected with axle drive shaft 28 by cylindrical pair, axle drive shaft 28 1 ends are connected with pedestal 24 by cylindrical pair, the other end is connected with axle drive shaft 32 by crosspin type joint 30, axle drive shaft 32 is connected with finishing bevel gear cuter 34, finishing bevel gear cuter 34 and finishing bevel gear cuter 36 engagements, finishing bevel gear cuter 36 is fixed on center drive shaft 37, center drive shaft 37 is coaxial with rotating shaft 6 and be connected by revolute pair with 4, wing.
In the left side arrangement of mechanism, redundant hydraulic motor 19 is arranged, its output shaft and gear 21 are connected, gear 21 and gear 13 engagements.
In the right side arrangement of mechanism, redundant hydraulic motor 20 is arranged, its output shaft and gear 22 are connected, gear 22 and gear 14 engagements.
The invention has the beneficial effects as follows: the present invention drives nacelle to realize its motion of verting by screw, and the nacelle of both sides verts and moves through center drive shaft and be connected, the present invention is by center drive shaft and nacelle rotating shaft coaxle, make structure more compact, reduced the taking of wing wing box space, be conducive to the design of wing and fuel tank; The invention provides screw and be connected with the mechanism of nacelle and wing, and the motion transmission between screw and center drive shaft, domestic prior art blank filled up; The present invention has the redundance drive pattern, has improved mechanism's fiduciary level.
The accompanying drawing explanation
Fig. 1 is tilt rotor aircraft helicopter mode schematic diagram
Fig. 2 is tilt rotor aircraft fixed wing aircraft pattern diagram
Fig. 3 is mechanism principle schematic diagram of the present invention
The specific embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
A kind of nacelle inclining rotary mechanism of tilt rotor aircraft, it is characterized in that, arrangement of mechanism is about aircraft symmetrical plane left-right symmetric, and left side mechanism comprises nacelle 1, wing 3, rotating shaft 5, screw 7, leading screw end 9, nut end 11, gear 13, main HM Hydraulic Motor 15, gear 17, pedestal 23, gear 25, axle drive shaft 27, Hooke's coupling 29, axle drive shaft 31, finishing bevel gear cuter 33, finishing bevel gear cuter 35, center drive shaft 37; Right side mechanism comprises nacelle 2, wing 4, rotating shaft 6, screw 8, leading screw end 10, nut end 12, gear 14, main HM Hydraulic Motor 16, gear 18, pedestal 24, gear 26, axle drive shaft 28, Hooke's coupling 30, axle drive shaft 32, finishing bevel gear cuter 34, finishing bevel gear cuter 36, center drive shaft 37.
Left side mechanism type of attachment is: nacelle 1 is connected by revolute pair with wing 3, the rotating shaft 5 of this revolute pair is fixed on wing 3, the leading screw end 9 of screw 7 is hinged with nacelle 1, nut end 11 is connected with gear 13, gear 13 and gear 17 engagements, the output shaft fixed connection of gear 17 and main HM Hydraulic Motor 15, main HM Hydraulic Motor 15 is connected on pedestal 23, pedestal 23 is connected by revolute pair with 3, wing, its rotation axis is parallel with rotating shaft 5, gear 13 meshes with gear 25 simultaneously, gear 25 is connected with axle drive shaft 27 by cylindrical pair, axle drive shaft 27 1 ends are connected with pedestal 23 by cylindrical pair, the other end is connected with axle drive shaft 31 by crosspin type joint 29, axle drive shaft 31 is connected with finishing bevel gear cuter 33, finishing bevel gear cuter 33 and finishing bevel gear cuter 35 engagements, finishing bevel gear cuter 35 is fixed on center drive shaft 37, center drive shaft 37 is coaxial with rotating shaft 5 and be connected by revolute pair with 3, wing.
Right side mechanism type of attachment is: nacelle 2 is connected by revolute pair with wing 4, the rotating shaft 6 of this revolute pair is fixed on wing 4, the leading screw end 10 of screw 8 is hinged with nacelle 2, nut end 12 is connected with gear 14, gear 14 and gear 18 engagements, the output shaft fixed connection of gear 18 and main HM Hydraulic Motor 16, main HM Hydraulic Motor 16 is connected on pedestal 24, pedestal 24 is connected by revolute pair with 4, wing, its rotation axis is parallel with rotating shaft 6, gear 14 meshes with gear 26 simultaneously, gear 26 is connected with axle drive shaft 28 by cylindrical pair, axle drive shaft 28 1 ends are connected with pedestal 24 by cylindrical pair, the other end is connected with axle drive shaft 32 by crosspin type joint 30, axle drive shaft 32 is connected with finishing bevel gear cuter 34, finishing bevel gear cuter 34 and finishing bevel gear cuter 36 engagements, finishing bevel gear cuter 36 is fixed on center drive shaft 37, center drive shaft 37 is coaxial with rotating shaft 6 and be connected by revolute pair with 4, wing.
In the left side arrangement of mechanism, redundant hydraulic motor 19 is arranged, its output shaft and gear 21 are connected, gear 21 and gear 13 engagements.
In the right side arrangement of mechanism, redundant hydraulic motor 20 is arranged, its output shaft and gear 22 are connected, gear 22 and gear 14 engagements.
The principle of work of this mechanism is as follows: the nut end 11 that the engagement of the engagement by gear 17 and gear 13 of main HM Hydraulic Motor 15 or redundant hydraulic motor 19 or gear 21 and gear 13 rotatablely moves it to be delivered to screw 7, drive the screw motion between nut and leading screw, change screw 7 and the distance of nacelle 1 point of connection to screw 7 and wing 3 point of connection, thereby pull nacelle 1 to rotate around its rotating shaft 5, simultaneously, the output of main HM Hydraulic Motor 15 or redundant hydraulic motor 19 rotatablely moves and also by gear 17 or gear 21, with the engagement of gear 13, is delivered to gear 13, be delivered to gear 25 by gear 13 and the engagement of gear 25 again, be delivered to again axle drive shaft 27, axle drive shaft 27 rotatablely moves it to be delivered to axle drive shaft 31 by Hooke's coupling 29, axle drive shaft 31 rotatablely moves it to be delivered to center drive shaft 37 by the engagement of finishing bevel gear cuter 33 and finishing bevel gear cuter 35 again, equally, the nut end 12 that the engagement of the engagement by gear 18 and gear 14 of main HM Hydraulic Motor 16 or redundant hydraulic motor 20 or gear 22 and gear 14 rotatablely moves it to be delivered to screw 8, drive the screw motion between nut and leading screw, change screw 8 and the distance of nacelle 2 point of connection to screw 8 and wing 4 point of connection, thereby pull nacelle 2 to rotate around its rotating shaft 6, simultaneously, the output of main HM Hydraulic Motor 16 or redundant hydraulic motor 20 rotatablely moves and also by gear 18 or gear 22, with the engagement of gear 14, is delivered to gear 14, be delivered to gear 26 by gear 14 and the engagement of gear 26 again, be delivered to again axle drive shaft 28, axle drive shaft 28 rotatablely moves it to be delivered to axle drive shaft 32 by Hooke's coupling 30, axle drive shaft 32 rotatablely moves it to be delivered to center drive shaft 37 by the engagement of finishing bevel gear cuter 34 and finishing bevel gear cuter 36 again.Center drive shaft 37 links together the motion of verting of both sides nacelle, and center drive shaft 37 also can disconnect with the both sides nacelle and vert contacting of motion and allow the both sides nacelle to do the motion of independently verting in addition.
This mechanism has following multiple drive modes:
A) main HM Hydraulic Motor 15 and main HM Hydraulic Motor 16 drive the inclining rotary mechanism motion of both sides, and center drive shaft 37 couples together the motion of arranged on left and right sides simultaneously;
B) main HM Hydraulic Motor 15 and redundant hydraulic motor 20 drive the inclining rotary mechanism motion of both sides, and center drive shaft 37 couples together the motion of arranged on left and right sides simultaneously;
C) redundant hydraulic motor 19 and main HM Hydraulic Motor 16 drive the inclining rotary mechanism motion of both sides, and center drive shaft 37 couples together the motion of arranged on left and right sides simultaneously;
D) redundant hydraulic motor 19 and redundant hydraulic motor 20 drive the inclining rotary mechanism motion of both sides, and center drive shaft 37 couples together the motion of arranged on left and right sides simultaneously;
E) main HM Hydraulic Motor 15 driving left side inclining rotary mechanism motions, main HM Hydraulic Motor 16 drives right side inclining rotary mechanisms motion, and center drive shaft 37 disconnections are connected with left and right inclining rotary mechanism;
F) main HM Hydraulic Motor 15 driving left side inclining rotary mechanism motions, redundant hydraulic motor 20 drives right side inclining rotary mechanisms motion, and center drive shaft 37 disconnections are connected with left and right inclining rotary mechanism;
G) redundant hydraulic motor 19 driving left side inclining rotary mechanism motions, main HM Hydraulic Motor 16 drives right side inclining rotary mechanisms motion, and center drive shaft 37 disconnections are connected with left and right inclining rotary mechanism;
H) redundant hydraulic motor 19 driving left side inclining rotary mechanism motions, redundant hydraulic motor 20 drives right side inclining rotary mechanisms motion, and center drive shaft 37 disconnections are connected with left and right inclining rotary mechanism.
Claims (3)
1. the nacelle inclining rotary mechanism of a tilt rotor aircraft, it is characterized in that, arrangement of mechanism is about aircraft symmetrical plane left-right symmetric, and left side mechanism comprises nacelle (1), wing (3), rotating shaft (5), screw (7), leading screw end (9), nut end (11), gear (13), main HM Hydraulic Motor (15), gear (17), pedestal (23), gear (25), axle drive shaft (27), Hooke's coupling (29), axle drive shaft (31), finishing bevel gear cuter (33), finishing bevel gear cuter (35), center drive shaft (37); Right side mechanism comprises nacelle (2), wing (4), rotating shaft (6), screw (8), leading screw end (10), nut end (12), gear (14), main HM Hydraulic Motor (16), gear (18), pedestal (24), gear (26), axle drive shaft (28), Hooke's coupling (30), axle drive shaft (32), finishing bevel gear cuter (34), finishing bevel gear cuter (36), center drive shaft (37).
Left side mechanism type of attachment is: nacelle (1) is connected by revolute pair with wing (3), the rotating shaft of this revolute pair (5) is fixed on wing (3), the leading screw end (9) of screw (7) is hinged with nacelle (1), nut end (11) is connected with gear (13), gear (13) and gear (17) engagement, the output shaft fixed connection of gear (17) and main HM Hydraulic Motor (15), main HM Hydraulic Motor (15) is connected on pedestal (23), between pedestal (23) and wing (3), by revolute pair, be connected, its rotation axis is parallel with rotating shaft (5), gear (13) meshes with gear (25) simultaneously, gear (25) is connected with axle drive shaft (27) by cylindrical pair, axle drive shaft (27) one ends are connected with pedestal (23) by cylindrical pair, the other end is connected with axle drive shaft (31) by crosspin type joint (29), axle drive shaft (31) is connected with finishing bevel gear cuter (33), finishing bevel gear cuter (33) and finishing bevel gear cuter (35) engagement, finishing bevel gear cuter (35) is fixed on center drive shaft (37), center drive shaft (37) coaxial with rotating shaft (5) and with wing (3) between by revolute pair, be connected.
Right side mechanism type of attachment is: nacelle (2) is connected by revolute pair with wing (4), the rotating shaft of this revolute pair (6) is fixed on wing (4), the leading screw end (10) of screw (8) is hinged with nacelle (2), nut end (12) is connected with gear (14), gear (14) and gear (18) engagement, the output shaft fixed connection of gear (18) and main HM Hydraulic Motor (16), main HM Hydraulic Motor (16) is connected on pedestal (24), between pedestal (24) and wing (4), by revolute pair, be connected, its rotation axis is parallel with rotating shaft (6), gear (14) meshes with gear (26) simultaneously, gear (26) is connected with axle drive shaft (28) by cylindrical pair, axle drive shaft (28) one ends are connected with pedestal (24) by cylindrical pair, the other end is connected with axle drive shaft (32) by crosspin type joint (30), axle drive shaft (32) is connected with finishing bevel gear cuter (34), finishing bevel gear cuter (34) and finishing bevel gear cuter (36) engagement, finishing bevel gear cuter (36) is fixed on center drive shaft (37), center drive shaft (37) coaxial with rotating shaft (6) and with wing (4) between by revolute pair, be connected.
2. a kind of tilt rotor aircraft nacelle inclining rotary mechanism according to claim 1, is characterized in that, in the left side arrangement of mechanism, redundant hydraulic motor (19) is arranged, and its output shaft and gear (21) are connected, gear (21) and gear (13) engagement.
3. a kind of tilt rotor aircraft nacelle inclining rotary mechanism according to claim 1, is characterized in that, in the right side arrangement of mechanism, redundant hydraulic motor (20) is arranged, and its output shaft and gear (22) are connected, gear (22) and gear (14) engagement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013103734159A CN103466087A (en) | 2013-08-23 | 2013-08-23 | Nacelle tilting mechanism for tilt rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013103734159A CN103466087A (en) | 2013-08-23 | 2013-08-23 | Nacelle tilting mechanism for tilt rotor aircraft |
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| CN103466087A true CN103466087A (en) | 2013-12-25 |
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| CN2013103734159A Pending CN103466087A (en) | 2013-08-23 | 2013-08-23 | Nacelle tilting mechanism for tilt rotor aircraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106585976A (en) * | 2016-11-30 | 2017-04-26 | 北京航空航天大学 | Aircraft layout of tilt rotors/lift fan during high-speed long endurance |
| CN106672204A (en) * | 2017-03-09 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Tilting mechanism for tilting rotor wing airplane |
| CN106697282A (en) * | 2015-11-18 | 2017-05-24 | 陈佳伟 | Duct type tilting aircraft with vertical take-off and landing functions |
| CN108033004A (en) * | 2017-12-20 | 2018-05-15 | 长安大学 | One kind rotary wings machine that inclines verts system |
| CN109649649A (en) * | 2019-01-21 | 2019-04-19 | 合肥工业大学 | Tiltrotor aircraft |
| CN113232852A (en) * | 2021-05-11 | 2021-08-10 | 重庆大学 | Transmission mechanism for wings of tilt rotor aircraft |
| CN113320694A (en) * | 2021-07-13 | 2021-08-31 | 广东汇天航空航天科技有限公司 | Tilt rotor mechanism and aircraft with same |
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| US5054716A (en) * | 1989-10-16 | 1991-10-08 | Bell Helicopter Textron Inc. | Drive system for tiltrotor aircraft |
| US5092539A (en) * | 1989-10-13 | 1992-03-03 | Bell Helicopter Textron Inc. | Jam resistant ball screw actuator |
| EP0754620A1 (en) * | 1995-07-21 | 1997-01-22 | Freiherr von Wilmowsky, Kaspar | Tilt rotor helicopter |
| US6227481B1 (en) * | 1999-08-06 | 2001-05-08 | Bell Helicopter Textron, Inc. | Method and apparatus for controlling force fights in a rotating shaft |
| US6247667B1 (en) * | 1999-08-06 | 2001-06-19 | Bell Helicopter Textron Inc. | Tiltrotor aircraft pylon conversion system |
| US20090266941A1 (en) * | 2008-04-25 | 2009-10-29 | Abe Karem | Combination Spar and Trunnion Structure for a Tilt Rotor Aircraft |
| US20100276549A1 (en) * | 2005-09-02 | 2010-11-04 | Abe Karem | Fail-operational multiple lifting-rotor aircraft |
| 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 |
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2013
- 2013-08-23 CN CN2013103734159A patent/CN103466087A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5092539A (en) * | 1989-10-13 | 1992-03-03 | Bell Helicopter Textron Inc. | Jam resistant ball screw actuator |
| US5054716A (en) * | 1989-10-16 | 1991-10-08 | Bell Helicopter Textron Inc. | Drive system for tiltrotor aircraft |
| EP0754620A1 (en) * | 1995-07-21 | 1997-01-22 | Freiherr von Wilmowsky, Kaspar | Tilt rotor helicopter |
| US6227481B1 (en) * | 1999-08-06 | 2001-05-08 | Bell Helicopter Textron, Inc. | Method and apparatus for controlling force fights in a rotating shaft |
| US6247667B1 (en) * | 1999-08-06 | 2001-06-19 | Bell Helicopter Textron Inc. | Tiltrotor aircraft pylon conversion system |
| US20100276549A1 (en) * | 2005-09-02 | 2010-11-04 | Abe Karem | Fail-operational multiple lifting-rotor aircraft |
| US20090266941A1 (en) * | 2008-04-25 | 2009-10-29 | Abe Karem | Combination Spar and Trunnion Structure for a Tilt Rotor Aircraft |
| 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 |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697282A (en) * | 2015-11-18 | 2017-05-24 | 陈佳伟 | Duct type tilting aircraft with vertical take-off and landing functions |
| CN106585976A (en) * | 2016-11-30 | 2017-04-26 | 北京航空航天大学 | Aircraft layout of tilt rotors/lift fan during high-speed long endurance |
| CN106585976B (en) * | 2016-11-30 | 2019-05-24 | 北京航空航天大学 | A kind of long endurance aircraft layout of tilting rotor/lift fan high speed |
| CN106672204A (en) * | 2017-03-09 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Tilting mechanism for tilting rotor wing airplane |
| CN108033004A (en) * | 2017-12-20 | 2018-05-15 | 长安大学 | One kind rotary wings machine that inclines verts system |
| CN108033004B (en) * | 2017-12-20 | 2023-11-07 | 长安大学 | Tilting system of tilting wing machine |
| CN109649649A (en) * | 2019-01-21 | 2019-04-19 | 合肥工业大学 | Tiltrotor aircraft |
| CN109649649B (en) * | 2019-01-21 | 2021-08-20 | 合肥工业大学 | Tilt rotor aircraft |
| CN113232852A (en) * | 2021-05-11 | 2021-08-10 | 重庆大学 | Transmission mechanism for wings of tilt rotor aircraft |
| CN113232852B (en) * | 2021-05-11 | 2023-05-09 | 重庆大学 | Transmission mechanism for tilting rotorcraft wing |
| CN113320694A (en) * | 2021-07-13 | 2021-08-31 | 广东汇天航空航天科技有限公司 | Tilt rotor mechanism and aircraft with same |
| CN113320694B (en) * | 2021-07-13 | 2023-08-18 | 广东汇天航空航天科技有限公司 | Tilt rotor mechanism and aircraft with same |
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Application publication date: 20131225 |