CN104973237A - Cardan universal joint type flap transmission mechanism - Google Patents
Cardan universal joint type flap transmission mechanism Download PDFInfo
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- CN104973237A CN104973237A CN201510412655.4A CN201510412655A CN104973237A CN 104973237 A CN104973237 A CN 104973237A CN 201510412655 A CN201510412655 A CN 201510412655A CN 104973237 A CN104973237 A CN 104973237A
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- universal joint
- drive shaft
- transmission
- joint cross
- transmission device
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Abstract
The invention discloses a cardan universal joint type flap transmission mechanism. The cardan universal joint type flap transmission mechanism comprises a rotary block, connecting rods, swing arms, transmission rotary shafts, cardan universal joint assemblies and rolling bearings. The two ends of the rotary block are hinged to the connecting rods respectively. The connecting rods are hinged to one ends of the swing arms. The other ends of the swing arms are connected with the transmission rotary shafts. The rolling bearings are installed at the two ends of the transmission rotary shafts in an interference fit mode. The transmission rotary shafts are split into two sections for connection according to requirements through the cardan universal joint assemblies. The mechanism can effectively solve the problem that transmission accuracy is affected by small wing space, the long transmission path and wing bending deformation, can be widely applied to occasions with limited installation space and long-distance transmission, and is driven by a single power source, motion synchronism of a left flap and a right flap is good, the deflection symmetry of the flaps in the forward direction and the reverse direction is good, and response is reliable. Through refitting, the mechanism can be universal in design according to different types and different airload conditions.
Description
Technical field
The present invention relates to a kind of aileron transmission device, particularly relate to a kind of universal joint cross formula aileron transmission device.
Background technology
Along with the progress of science and technology, increasing target drone adopts high aspect ratio wing, to increase cruise duration and voyage, improves target drone performance.For the wing of high aspect ratio, require more and more higher to the operating torque of body rolling, tradition aileron is arranged in wing root and cannot meets operating needs, in order to meet the operating torque of body rolling necessity, farthest reduce steering wheel working load, target drone aileron need be in the layout of wing end, though this total arrangement reduces the control difficulty of body simultaneously, but cause the drive path of aileron long, transmission accuracy declines.What current aircraft aileron extensively adopted is electric transmission, hydraulic control circuit or many cover connecting rod mechanism connection in series-parallel forms, but the general wing of target drone is thinner, and therefore the application of aircraft aileron type of belt drive on target drone aileron has certain limitation.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
Summary of the invention
Be in the layout of wing end for aileron and Airfoil thinner, mechanism kinematic and the limited situation of installing space, the technical issues that need to address of the present invention are to provide a kind of universal joint cross formula aileron transmission device, thus realize from steering wheel to aileron rotating shaft transmission, effectively and reliably pass to aileron by the horsepower output (displacement) of steering wheel and load, make it to do corresponding deflection on request.
For solving technical matters of the present invention, the technical solution used in the present invention is:
A kind of universal joint cross formula aileron transmission device, this cover aileron transmission device comprises turning block, connecting rod, rocking arm, drive shaft, universal joint cross assembly and antifriction-bearing box, described turning block two ends are articulated linkage respectively, described connecting rod and one end hinged, the described rocking arm other end is connected with drive shaft, described antifriction-bearing box interference fit is installed on drive shaft two ends, and described drive shaft splits into two sections of connections as required by universal joint cross assembly.
As a further improvement on the present invention, described universal joint cross assembly comprises hexagonal grooved jam nut, spring cotter, ball-headed bolt, cushion block, lining and rotating shaft, cushion block is pressed into the corresponding centre hole of drive shaft, lining, the corresponding centre hole of rotating shaft press-in drive shaft, pass cushion block, lining and rotating shaft successively with ball-headed bolt afterwards, tighten hexagonal grooved jam nut and insertion opening pin.
Wherein, in the middle part of described turning block, there is power entrance point.
Wherein, described drive shaft end has movement output point.
This mechanism carries out comformability modification on the basis of traditional four-bar linkage, and mechanism adopts a set of universal joint cross assembly that drive shaft is split connection as required, realizes propulsion source to the reliable transmission of aileron.Making full use of in the narrow and small aerofoil profile space basis of wing, drive shaft is arranged in parallel in airfoil chord plane along aileron shaft axis direction, universal joint cross assembly allows two between centers to have larger angle simultaneously, the relative displacement of diaxon can be compensated, the rotating shaft clamping stagnation problem effectively avoiding wing flexural deformation to cause.By universal joint cross number of components and layout in changing mechanism, the present invention can be applied to the different aerodynamic loading situation of different type of machines, realizes General design.
Beneficial effect of the present invention: this mechanism structure is simple, institutional adjustment is flexible, transmitting ratio is constant, and output torque variation range is large, and it is little effectively can to solve wing space, drive path length and wing flexural deformation affect the problems such as transmission accuracy, can be widely used in the aileron transmission device that installing space is limited and grow apart from transmission, mechanism is driven by single power source, and left and right aileron motion synchronicity is good, aileron both forward and reverse directions deflection symmetry is good, and response is reliable; By repacking, can according to the different aerodynamic loading situation of different type of machines, mechanism can realize designing universalization.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 a is the structural representation of four-bar linkage of the present invention.
Fig. 2 b is the structural representation of universal joint cross assembly of the present invention.
Fig. 2 c is the structural representation of rocking arm of the present invention.
1, power entrance point, 2, turning block, 3, connecting rod, 4, rocking arm, 5, drive shaft, 6, universal joint cross assembly, 7, antifriction-bearing box, 8, movement output point, 9, drive shaft, 10, cushion block, 11, hexagonal grooved jam nut, 12, spring cotter, 13, ball-headed bolt, 14, lining, 15, rotating shaft, 16, drive shaft, 17, connecting bore, 18, connecting bore.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the invention will be further described.Following examples, only for illustration of the present invention, are not used for limiting the scope of the invention.
Shown in Fig. 1, a kind of universal joint cross formula aileron transmission device of the present invention, this cover aileron transmission device comprises turning block 2, connecting rod 3, Rocker arm 4, drive shaft 5, universal joint cross assembly 6 and antifriction-bearing box 7, turning block 2 two ends are hinged with connecting rod 3 respectively, connecting rod 3 is hinged with Rocker arm 4 one end; the Rocker arm 4 other end is connected with drive shaft 5, and antifriction-bearing box 7 interference fit is installed on drive shaft 5 two ends, and drive shaft 5 splits into two sections of connections as required by universal joint cross assembly 6.
When wherein turning block 2 rotates to a certain set direction under single power source effect, connect the motion of left linkages 3 reversing sense, then the differential deflection of left and right aileron is realized, produce the operating torque that target drone is rolled around fuselage axis, realize the motor performance or stable around fuselage axis, meet again mechanism's synchronism requirement simultaneously.In order to ensure that mechanism has good Linear transmission relation, should make between connecting rod 3 and Rocker arm 4 vertical as far as possible when steering wheel is in center position, but wing have employed large sweepback angle, Rocker arm 4 two ends have connecting bore, in one connecting bore 18, stud connection has connecting rod 3, another connecting bore 17 has assigned drive shaft 5, Rocker arm 4 two connecting bore 17 in the present invention, 18 axis and be designed with certain angle (Fig. 2 a respectively between connecting rod 3 axis and drive shaft 5 axis, Fig. 2 c), it is 0 ° between connecting bore 17 axis and drive shaft 5 axis, it is 90 ° between connecting bore 18 axis and connecting rod 3 axis, the strong rigidity of Rocker arm 4 is improved under the prerequisite meeting drive path, ensure that mechanism has constant ratio.In addition, for alleviating in target drone flight course, wing produces the rotating shaft clamping stagnation being out of shape and causing by Aerodynamic force action, aileron drive shaft 5 cuts point as required, adopt universal joint cross transmission component 6 to carry out connecting (as shown in Figure 2 b) between segmentation rotating shaft, this kind of coupler structure is compact, easy to maintenance, allow two between centers to have larger angle, the relative displacement of diaxon can be compensated.
Fig. 2 b, above-mentioned universal joint cross assembly 6 comprises hexagonal grooved jam nut 11, spring cotter 12, ball-headed bolt 13, cushion block 10, lining 14 and rotating shaft 15, cushion block 10 is pressed into the corresponding centre hole of drive shaft 5, lining 14, rotating shaft 15 are pressed into the corresponding centre hole of drive shaft 5, pass cushion block 10, lining 14 and rotating shaft 15 successively with ball-headed bolt 13 afterwards, tighten hexagonal grooved jam nut 11 and insertion opening pin 12.
When driving device is installed, first antifriction-bearing box 7 interference fit is installed on drive shaft 5, then universal joint cross assembly 6 is installed, cushion block 10 is pressed into the corresponding centre hole of drive shaft 9, lining 14, rotating shaft 15 are pressed into the corresponding centre hole of drive shaft 16, pass cushion block 10, lining 14 and rotating shaft 15 successively with ball-headed bolt 13 afterwards, tighten hexagonal grooved jam nut 11 and insertion opening pin 12; Then by connecting bore 17 connection for transmission rotating shaft 5 and Rocker arm 4, then by connecting bore 18 connecting rocker arm 4 and connecting rod 3, finally by connecting rod 3 connecting rocker arm 4 and turning block 2, so far installation process is completed.
As can be seen from Figure 1, turning block 2 central shaft that rotates under propulsion source (power entrance point 1 place) effect rotates by action command rule, and drive Rocker arm 4 to do corresponding actions by connecting rod 3, then drive shaft 5 is driven to rotate around its line of centers, so far propulsion source displacement and load effectively and are reliably passed to the aileron at power takeoff point 8 place, complete aileron control function.
Claims (4)
1. a universal joint cross formula aileron transmission device, it is characterized in that: this cover aileron transmission device comprises turning block, connecting rod, rocking arm, drive shaft, universal joint cross assembly and antifriction-bearing box, described turning block two ends are articulated linkage respectively, described connecting rod and one end hinged, the described rocking arm other end is connected with drive shaft, described antifriction-bearing box interference fit is installed on drive shaft two ends, and described drive shaft splits into two sections of connections as required by universal joint cross assembly.
2. a kind of universal joint cross formula aileron transmission device according to claim 1, it is characterized in that: described universal joint cross assembly comprises hexagonal grooved jam nut, spring cotter, ball-headed bolt, cushion block, lining and rotating shaft, cushion block is pressed into the corresponding centre hole of drive shaft, lining, the corresponding centre hole of rotating shaft press-in drive shaft, pass cushion block, lining and rotating shaft successively with ball-headed bolt afterwards, tighten hexagonal grooved jam nut and insertion opening pin.
3. a kind of universal joint cross formula aileron transmission device according to claim 1, is characterized in that: have power entrance point in the middle part of described turning block.
4. a kind of universal joint cross formula aileron transmission device according to claim 1, is characterized in that: described drive shaft end has movement output point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510412655.4A CN104973237A (en) | 2015-07-15 | 2015-07-15 | Cardan universal joint type flap transmission mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510412655.4A CN104973237A (en) | 2015-07-15 | 2015-07-15 | Cardan universal joint type flap transmission mechanism |
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| Publication Number | Publication Date |
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| CN104973237A true CN104973237A (en) | 2015-10-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510412655.4A Pending CN104973237A (en) | 2015-07-15 | 2015-07-15 | Cardan universal joint type flap transmission mechanism |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107215279A (en) * | 2017-07-14 | 2017-09-29 | 余忠勇 | Electric turnover pedal assembly |
| CN110027700A (en) * | 2019-04-09 | 2019-07-19 | 沈阳无距科技有限公司 | Steering engine connecting rod and unmanned plane |
| CN108987168B (en) * | 2018-09-29 | 2023-10-13 | 长高电新科技股份公司 | Rotating shaft connecting rod connecting structure of high-voltage isolating switch and assembling method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB467539A (en) * | 1935-09-17 | 1937-06-18 | Fritz Faudi | Joint for control rods, in particular for aircraft, motor vehicles and the like |
| CN103174763A (en) * | 2013-04-11 | 2013-06-26 | 钟婕 | Rotating torsion conveyer |
| CN203047529U (en) * | 2012-11-21 | 2013-07-10 | 中国航空工业集团公司西安飞机设计研究所 | Adjusting device |
| CN103318404A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Guided missile aileron control mechanism |
| CN103423326A (en) * | 2012-05-15 | 2013-12-04 | 哈米尔顿森德斯特兰德公司 | Articulable rotational coupling for an aircraft |
| CN203796781U (en) * | 2014-03-27 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Aligning cross universal shaft component for mounting horizontal-tail steering engine |
| CN204871588U (en) * | 2015-07-15 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Cross universal joint formula aileron drive mechanism |
-
2015
- 2015-07-15 CN CN201510412655.4A patent/CN104973237A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB467539A (en) * | 1935-09-17 | 1937-06-18 | Fritz Faudi | Joint for control rods, in particular for aircraft, motor vehicles and the like |
| CN103423326A (en) * | 2012-05-15 | 2013-12-04 | 哈米尔顿森德斯特兰德公司 | Articulable rotational coupling for an aircraft |
| CN203047529U (en) * | 2012-11-21 | 2013-07-10 | 中国航空工业集团公司西安飞机设计研究所 | Adjusting device |
| CN103174763A (en) * | 2013-04-11 | 2013-06-26 | 钟婕 | Rotating torsion conveyer |
| CN103318404A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Guided missile aileron control mechanism |
| CN203796781U (en) * | 2014-03-27 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Aligning cross universal shaft component for mounting horizontal-tail steering engine |
| CN204871588U (en) * | 2015-07-15 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Cross universal joint formula aileron drive mechanism |
Non-Patent Citations (1)
| Title |
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| 潘科第、童仲良: "《装载机的构造、使用与维修》", 31 July 1993 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107215279A (en) * | 2017-07-14 | 2017-09-29 | 余忠勇 | Electric turnover pedal assembly |
| CN108987168B (en) * | 2018-09-29 | 2023-10-13 | 长高电新科技股份公司 | Rotating shaft connecting rod connecting structure of high-voltage isolating switch and assembling method thereof |
| CN110027700A (en) * | 2019-04-09 | 2019-07-19 | 沈阳无距科技有限公司 | Steering engine connecting rod and unmanned plane |
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Application publication date: 20151014 |
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