CN103466088A - Nacelle gear tilting mechanism for tilt rotor aircraft - Google Patents
Nacelle gear tilting mechanism for tilt rotor aircraft Download PDFInfo
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- CN103466088A CN103466088A CN2013103735753A CN201310373575A CN103466088A CN 103466088 A CN103466088 A CN 103466088A CN 2013103735753 A CN2013103735753 A CN 2013103735753A CN 201310373575 A CN201310373575 A CN 201310373575A CN 103466088 A CN103466088 A CN 103466088A
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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; each unilateral mechanism comprises a nacelle, a wing, a rotating shaft, an internal gear, an external gear, a main driving gear, a main hydraulic motor, gears and an intermediate driving shaft; the connecting manner of each unilateral mechanism is as follows: the nacelles are connected with the wings through revolute pairs, the rotating shafts of the revolute pairs are fixed on the wings, the internal gears are fixedly connected with the nacelles, the external gears are connected onto the wings through the revolute pairs, the rotating shaft lines of the external gears are coaxial with the nacelles, each driving gear is positioned between each internal gear and each external gear, and meshed with the internal gears and the external gears simultaneously, the driving gears are fixedly connected with the output shafts of the hydraulic motors, the hydraulic motors are fixed on the wings, and the intermediate driving shaft is connected with tilting mechanisms on the two sides. The nacelle gear tilting mechanism for the tilt rotor aircraft provided by the invention has a redundancy driving mode, the motion transmission line is short, and the structure is compact.
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 nacelle inclining rotary mechanism that the invention provides a kind of tilt rotor aircraft, this mechanism kinematic all meshes and is transmitted by gear, there is 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 gear 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, inner gear 7, external gear 9, main driven wheel 11, main HM Hydraulic Motor 15, gear 19, gear 21, center drive shaft 23; Right side mechanism comprises nacelle 2, wing 4, rotating shaft 6, inner gear 8, external gear 10, main driven wheel 12, main HM Hydraulic Motor 16, gear 20, gear 22, center drive shaft 23.
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, inner gear 7 is connected with nacelle 1 and is coaxial with rotating shaft 5, external gear 9 is connected with wing 3 by revolute pair, its rotation axis is coaxial with rotating shaft 5, main driven wheel 11 is between inner gear 7 and external gear 9, and mesh with the two simultaneously, the output shaft fixed connection of main driven wheel 11 and main HM Hydraulic Motor 15, main HM Hydraulic Motor 15 is fixed on wing 3, gear 19 is connected with external gear 9 and meshes with gear 21, and gear 21 is connected with center drive shaft 23.
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, inner gear 8 is connected with nacelle 2 and is coaxial with rotating shaft 6, external gear 10 is connected with wing 4 by revolute pair, its rotation axis is coaxial with rotating shaft 6, main driven wheel 12 is between inner gear 8 and external gear 10, and mesh with the two simultaneously, the output shaft fixed connection of main driven wheel 12 and main HM Hydraulic Motor 16, main HM Hydraulic Motor 16 is fixed on wing 4, gear 20 is connected with external gear 10 and meshes with gear 22, gear 22 is connected with center drive shaft 23.
In described left side arrangement of mechanism, one or more redundant hydraulic motors 17 are arranged, its output shaft is by gear mechanism and inner gear 7 and external gear 9 engagements.
In described right side arrangement of mechanism, one or more redundant hydraulic motors 18 are arranged, its output shaft is by gear mechanism and inner gear 8 and external gear 10 engagements.
The invention has the beneficial effects as follows: the present invention, by center drive shaft and nacelle rotating shaft coaxle, makes structure more compact, has reduced the taking of wing wing box space, and is conducive to the design of wing and fuel tank; The present invention is gear drive, makes the motion transfer route short, is conducive to improve driving efficiency; 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
Fig. 4 is mechanism principle left side view 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 gear 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, inner gear 7, external gear 9, main driven wheel 11, main HM Hydraulic Motor 15, gear 19, gear 21, center drive shaft 23; Right side mechanism comprises nacelle 2, wing 4, rotating shaft 6, inner gear 8, external gear 10, main driven wheel 12, main HM Hydraulic Motor 16, gear 20, gear 22, center drive shaft 23.
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, inner gear 7 is connected with nacelle 1 and is coaxial with rotating shaft 5, external gear 9 is connected with wing 3 by revolute pair, its rotation axis is coaxial with rotating shaft 5, main driven wheel 11 is between inner gear 7 and external gear 9, and mesh with the two simultaneously, the output shaft fixed connection of main driven wheel 11 and main HM Hydraulic Motor 15, main HM Hydraulic Motor 15 is fixed on wing 3, gear 19 is connected with external gear 9 and meshes with gear 21, and gear 21 is connected with center drive shaft 23.
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, inner gear 8 is connected with nacelle 2 and is coaxial with rotating shaft 6, external gear 10 is connected with wing 4 by revolute pair, its rotation axis is coaxial with rotating shaft 6, main driven wheel 12 is between inner gear 8 and external gear 10, and mesh with the two simultaneously, the output shaft fixed connection of main driven wheel 12 and main HM Hydraulic Motor 16, main HM Hydraulic Motor 16 is fixed on wing 4, gear 20 is connected with external gear 10 and meshes with gear 22, gear 22 is connected with center drive shaft 23.
In described left side arrangement of mechanism, one or more redundant hydraulic motors 17 are arranged, its output shaft is by gear mechanism and inner gear 7 and external gear 9 engagements.
In described right side arrangement of mechanism, one or more redundant hydraulic motors 18 are arranged, its output shaft is by gear mechanism and inner gear 8 and external gear 10 engagements.
This mechanism principle of work is as follows: main HM Hydraulic Motor 15 drives the rotation of main driven wheel 11, main driven wheel 11 drives the rotation of inner gear 7 by the engagement with inner gear 7, and then drive nacelle 1 is done yaw motion around its rotating shaft 5, simultaneously, main driven wheel 11 drives the rotation of external gear 9 by the engagement with external gear 9, the rotation of external gear 9 is delivered to center drive shaft 23 by the engagement of gear 19 and gear 21 again; Equally, main HM Hydraulic Motor 16 drives the rotation of main driven wheel 12, main driven wheel 12 drives the rotation of inner gear 8 by the engagement with inner gear 8, and then drive nacelle 2 is done yaw motion around its rotating shaft 6, simultaneously, main driven wheel 12 drives the rotation of external gear 10 by the engagement with external gear 10, the rotation of external gear 10 is delivered to center drive shaft 23 by the engagement of gear 20 and gear 22 again.
If main HM Hydraulic Motor 15 or main driven wheel 11 et out of orders, redundant hydraulic motor 17 and standby driven wheel 13 enter mode of operation; Equally, if main HM Hydraulic Motor 16 or main driven wheel 12 et out of orders, redundant hydraulic motor 18 and standby driven wheel 14 enter mode of operation, and its driving process is the same.
This mechanism has multiple remaining drive pattern:
A) main HM Hydraulic Motor 15 and main HM Hydraulic Motor 16 drive the inclining rotary mechanism of both sides, and center drive shaft 23 couples together the motion of arranged on left and right sides simultaneously;
B) main HM Hydraulic Motor 15 and redundant hydraulic motor 18 drive the inclining rotary mechanism of both sides, and center drive shaft 23 couples together the motion of arranged on left and right sides simultaneously;
C) redundant hydraulic motor 17 and main HM Hydraulic Motor 16 drive the inclining rotary mechanism of both sides, and center drive shaft 23 couples together the motion of arranged on left and right sides simultaneously;
D) redundant hydraulic motor 17 and redundant hydraulic motor 18 drive the inclining rotary mechanism of both sides, and center drive shaft 23 couples together the motion of arranged on left and right sides simultaneously;
E) inclining rotary mechanisms motion on the left of main HM Hydraulic Motor 15 drives, initiatively HM Hydraulic Motor 16 drive right side inclining rotary mechanisms move, and center drive shaft 23 disconnections are connected with left and right inclining rotary mechanism;
F) main HM Hydraulic Motor 15 drive left side inclining rotary mechanism motions, redundant hydraulic motor 18 drives right side inclining rotary mechanisms motion, and center drive shaft 23 disconnections are connected with left and right inclining rotary mechanism;
G) inclining rotary mechanisms motion on the left of 17 drives of redundant hydraulic motor, initiatively HM Hydraulic Motor 16 drive right side inclining rotary mechanisms move, and center drive shaft 23 disconnections are connected with left and right inclining rotary mechanism;
H) redundant hydraulic motor 17 drive left side inclining rotary mechanism motions, redundant hydraulic motor 18 drives right side inclining rotary mechanisms motion, and center drive shaft 23 disconnections are connected with left and right inclining rotary mechanism.
Claims (3)
1. the nacelle gear 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), inner gear (7), external gear (9), main driven wheel (11), main HM Hydraulic Motor (15), gear (19), gear (21), center drive shaft (23); Right side mechanism comprises nacelle (2), wing (4), rotating shaft (6), inner gear (8), external gear (10), main driven wheel (12), main HM Hydraulic Motor (16), gear (20), gear (22), center drive shaft (23).
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), inner gear (7) is connected with nacelle (1) and is coaxial with rotating shaft (5), external gear (9) is connected with wing (3) by revolute pair, its rotation axis is coaxial with rotating shaft (5), main driven wheel (11) is positioned between inner gear (7) and external gear (9), and mesh with the two simultaneously, the output shaft fixed connection of main driven wheel (11) and main HM Hydraulic Motor (15), main HM Hydraulic Motor (15) is fixed on wing (3), gear (19) is connected and meshes with gear (21) with external gear (9), gear (21) is connected with center drive shaft (23).
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), inner gear (8) is connected with nacelle (2) and is coaxial with rotating shaft (6), external gear (10) is connected with wing (4) by revolute pair, its rotation axis is coaxial with rotating shaft (6), main driven wheel (12) is positioned between inner gear (8) and external gear (10), and mesh with the two simultaneously, the output shaft fixed connection of main driven wheel (12) and main HM Hydraulic Motor (16), main HM Hydraulic Motor (16) is fixed on wing (4), gear (20) is connected and meshes with gear (22) with external gear (10), gear (22) is connected with center drive shaft (23).
2. a kind of tilt rotor aircraft nacelle gear inclining rotary mechanism according to claim 1, it is characterized in that, in the left side arrangement of mechanism, one or more redundant hydraulic motors (17) are arranged, its output shaft is by gear mechanism and inner gear (7) and external gear (9) engagement.
3. a kind of tilt rotor aircraft nacelle gear inclining rotary mechanism according to claim 1, it is characterized in that, in the right side arrangement of mechanism, one or more redundant hydraulic motors (18) are arranged, its output shaft is by gear mechanism and inner gear (8) and external gear (10) engagement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310373575.3A CN103466088B (en) | 2013-08-23 | 2013-08-23 | The nacelle gear inclining rotary mechanism of a kind of rotocraft that verts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310373575.3A CN103466088B (en) | 2013-08-23 | 2013-08-23 | The nacelle gear inclining rotary mechanism of a kind of rotocraft that verts |
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| CN103466088A true CN103466088A (en) | 2013-12-25 |
| CN103466088B CN103466088B (en) | 2016-06-01 |
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| CN201310373575.3A Active CN103466088B (en) | 2013-08-23 | 2013-08-23 | The nacelle gear inclining rotary mechanism of a kind of rotocraft that verts |
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Cited By (4)
| 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 |
| CN106979317A (en) * | 2015-12-01 | 2017-07-25 | 波音公司 | Gear-box and its manufacture method for tilt rotor aircraft |
| CN107902084A (en) * | 2017-11-20 | 2018-04-13 | 李宁 | A kind of tilt rotor aircraft rotor wing rotation structure design |
| US10421540B1 (en) | 2017-03-02 | 2019-09-24 | Bell Textron Inc. | Tiltrotor aircraft having optimized hover capabilities |
Citations (4)
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| 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 |
| CN102431646A (en) * | 2011-11-29 | 2012-05-02 | 南京航空航天大学 | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft |
| EP2572984A1 (en) * | 2011-09-20 | 2013-03-27 | Bell Helicopter Textron Inc. | Tiltrotor vectored exhaust system |
-
2013
- 2013-08-23 CN CN201310373575.3A patent/CN103466088B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| EP2572984A1 (en) * | 2011-09-20 | 2013-03-27 | Bell Helicopter Textron Inc. | Tiltrotor vectored exhaust system |
| CN102431646A (en) * | 2011-11-29 | 2012-05-02 | 南京航空航天大学 | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft |
Non-Patent Citations (1)
| Title |
|---|
| 缪君, 田伟, 王三民: "某型倾转旋翼机传动系统固有特性分析", 《机械设计与制造》, 31 October 2008 (2008-10-31), pages 149 - 151 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106979317A (en) * | 2015-12-01 | 2017-07-25 | 波音公司 | Gear-box and its manufacture method for tilt rotor aircraft |
| CN106979317B (en) * | 2015-12-01 | 2021-05-28 | 波音公司 | Gearbox for tilt rotor aircraft and method of manufacturing the same |
| 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 |
| US10421540B1 (en) | 2017-03-02 | 2019-09-24 | Bell Textron Inc. | Tiltrotor aircraft having optimized hover capabilities |
| CN107902084A (en) * | 2017-11-20 | 2018-04-13 | 李宁 | A kind of tilt rotor aircraft rotor wing rotation structure design |
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| Publication number | Publication date |
|---|---|
| CN103466088B (en) | 2016-06-01 |
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