CN204433036U - Without bulge aircraft aileron structure - Google Patents
Without bulge aircraft aileron structure Download PDFInfo
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- CN204433036U CN204433036U CN201420815373.XU CN201420815373U CN204433036U CN 204433036 U CN204433036 U CN 204433036U CN 201420815373 U CN201420815373 U CN 201420815373U CN 204433036 U CN204433036 U CN 204433036U
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- servo
- aileron
- torsion bar
- unit
- line angle
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Abstract
The utility model belongs to field of airplane structure, relates to the improvement of the rudder face structures such as aircraft aileron.Describedly comprise rudder face without bulge aircraft aileron structure, drive mechanism and servo-unit joint, wherein, drive mechanism comprises torsion bar and drive line angle box, described drive line angle box section is by " [" type and circular arc type two parts form, wherein, " [" type structure is connected with aileron front-axle beam phase fit, the center of circle of circular arc type part is concentric with aileron rotating shaft, torsion bar is connected on drive line angle box, servo-unit joint one end is coaxially connected with torsion bar, its other end is by bearing and be fixed on fuselage, form two fulcrum beam, servo-unit joint rocking arm is connected with the servo-unit being arranged on fuselage interior, and it is vertical with torsion bar.Servo-unit can be placed in fuselage by the utility model, thus servo-unit bulge huge under eliminating wing, wing main plane does not need the lid safeguarding servo-unit, decreases the destruction of main force support structure, improve structure efficiency.
Description
Technical field
The utility model belongs to field of airplane structure, relates to the improvement of the movable rudder face structures such as aircraft aileron.
Background technology
The lift of aircraft is provided by wing, force and moment required when the movable rudder face of aircraft is responsible for providing aircraft to do various maneuvering flight.The Main Function of aileron is the moment being provided aircraft rolling by the different deflection angles of left and right aileron.Traditional aileron structure adopts beam rib structure to form aileron rudder face, and aileron spar arranges multiple intersection point according to the length of aileron, and aileron rudder face is connected with main plane by intersection point.Below aileron rudder face, arrange servo-unit joint, this joint is connected with servo-unit pressurized strut, is reached the object of rudderon rudder face by the driving of pressurized strut.Drive the servo-unit joint of rudder face inevitably to need certain rocking arm length, therefore form servo-unit bulge below so also inevitable side and aileron rudder face under the wings of an airplane.Bulge is very large on the impact of aircraft aerodynamic performance, thus causes the loss of aircraft on fuel oil consumption and economy.Along with aircraft is to the requirement of Stealth Fighter, profile bulge also more and more becomes one of its Main Bottleneck.Adopt servo-unit door cylinder isolation technics to reduce bulge to a certain extent for present generation aircraft, but bulge can not be eliminated completely.In addition, in conventional structure layout, aileron servo-unit is generally placed in main plane, therefore needs to open on main plane to safeguard lid, so just inevitably destroys main force transferring structure, reduces structure efficiency.
Summary of the invention
The purpose of this utility model is: proposing one and can eliminate the bulge of aileron rudder face servo-unit, safeguarding the novel aileron structure of lid without the need to opening servo-unit on main plane.
Technical solution of the present utility model is: a kind of without bulge aircraft aileron structure, it comprises rudder face, drive mechanism and servo-unit joint, wherein, drive mechanism comprises torsion bar and drive line angle box, described drive line angle box section is by " [" type and circular arc type two parts form, wherein, " [" type structure is connected with aileron front-axle beam phase fit, the center of circle of circular arc type part is concentric with aileron rotating shaft, torsion bar is connected on drive line angle box, require that torsion bar is coaxial with aileron rotating shaft simultaneously, servo-unit joint one end is coaxially connected with torsion bar, its other end is by bearing and be fixed on fuselage, form two fulcrum beam, servo-unit joint rocking arm is connected with the servo-unit being arranged on fuselage interior, and it is vertical with torsion bar.
Servo-unit joint with between torsion bar for fit is connected.
Rudder face drive line angle box connecting portion is provided with some strengthening ribs for improving the rigidity of structure.
Torsion bar is by being connected with drive line angle box wearing bolt.
The utility model beneficial effect is: the utility model without bulge aircraft aileron structure by servo-unit is arranged in fuselage, and realize the deflecting operation to aileron rudder face by torsion bar and drive line angle box, eliminate servo-unit bulge, improve pneumatic and stealthy benefit, the servo-unit simultaneously eliminating main plane safeguards lid, decrease the destruction of main force transferring structure, improve structure efficiency, thus bring pneumatic, the huge income of stealthy, fuel oil, economy.And some strengthening ribs are set at rudder face drive line angle box connecting portion, ensure that the driving efficiency of the rigidity of structure and aileron.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the partial enlarged drawing of Fig. 1;
Wherein, 1-rudder face, 2-drive mechanism, 3-servo-unit joint.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is elaborated.
Refer to Fig. 1, it is the schematic diagram of the utility model without bulge aircraft aileron structure.Describedly comprise rudder face 1, drive mechanism 2 and servo-unit joint 3 without bulge aircraft aileron structure.Rudder face 1 integral structure profile similar and conventional aileron rudder situation, rudder face drive line angle box connecting portion is provided with some strengthening ribs, to improve aileron rudder face rigidity.
Refer to Fig. 2, it is the partial enlarged drawing of Fig. 1, and drive mechanism comprises torsion bar and drive line angle box.Wherein, described drive line angle box is irregular structure, and its section is by " [" type and circular arc type two parts form.Wherein, " [" type structure is straight mount structure, and it is connected with aileron front-axle beam fit, and the two mates mutually, has higher power transmission efficiency.The center of circle of described circular arc type part is concentric with aileron rotating shaft, thus can reduce interference, improves drive line angle box torsional stiffness.Torsion bar, by being connected on drive line angle box to wearing bolt, requires that torsion bar is coaxial with aileron rotating shaft simultaneously.
Servo-unit joint one end is connected with the coaxial fit of torsion bar, and its other end is by bearing and be fixed on fuselage, forms two fulcrum beam, to increase torsion efficiency.Servo-unit joint rocking arm is connected with the servo-unit being arranged on fuselage interior, and vertical with torsion bar, provides a moment of rotation.
During practical set, first drive line angle box is installed in aileron rudder face, again aileron rudder face is installed on main plane, then from fuselage, torsion bar is inserted drive line angle box, and by fixing wearing bolt, again by servo-unit adaptor cup jointing on torsion bar, servo-unit rocking arm be arranged on servo-unit in fuselage and be connected, complete aileron and install.
During real work, servo-unit drives torsion bar to rotate by servo-unit joint, and moves the rotation of aileron rudder face by drive line angle tape.
Claims (4)
1. one kind without bulge aircraft aileron structure, it is characterized in that: comprise rudder face, drive mechanism, servo-unit and servo-unit joint, wherein, drive mechanism comprises torsion bar and drive line angle box, described drive line angle box section is by " [" type and circular arc type two parts form, wherein, " [" type structure is connected with aileron front-axle beam phase fit, the center of circle of circular arc type part is concentric with aileron rotating shaft, torsion bar is connected on drive line angle box, require that torsion bar is coaxial with aileron rotating shaft simultaneously, servo-unit joint one end is coaxially connected with torsion bar, its other end is fixed on fuselage by bearing, form two fulcrum beam, servo-unit joint rocking arm is connected with the servo-unit being arranged on fuselage interior, and it is vertical with torsion bar.
2. according to claim 1 without bulge aircraft aileron structure, it is characterized in that: servo-unit joint with between torsion bar for fit is connected.
3. according to claim 2 without bulge aircraft aileron structure, it is characterized in that: rudder face drive line angle box connecting portion is provided with some strengthening ribs for improving the rigidity of structure.
4. according to any one of claims 1 to 3 without bulge aircraft aileron structure, it is characterized in that: torsion bar is by being connected with drive line angle box wearing bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420815373.XU CN204433036U (en) | 2014-12-19 | 2014-12-19 | Without bulge aircraft aileron structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420815373.XU CN204433036U (en) | 2014-12-19 | 2014-12-19 | Without bulge aircraft aileron structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204433036U true CN204433036U (en) | 2015-07-01 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420815373.XU Active CN204433036U (en) | 2014-12-19 | 2014-12-19 | Without bulge aircraft aileron structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204433036U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017196A (en) * | 2019-11-21 | 2020-04-17 | 成都飞机工业（集团）有限责任公司 | Coaxial type bending and twisting same-transmission control surface transmission mechanism |
| CN112339986A (en) * | 2020-09-22 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Skin skeleton integrated intermediate-temperature rapid molding composite material structure and method |
-
2014
- 2014-12-19 CN CN201420815373.XU patent/CN204433036U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017196A (en) * | 2019-11-21 | 2020-04-17 | 成都飞机工业（集团）有限责任公司 | Coaxial type bending and twisting same-transmission control surface transmission mechanism |
| CN112339986A (en) * | 2020-09-22 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Skin skeleton integrated intermediate-temperature rapid molding composite material structure and method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |