CN203047529U - Adjusting device - Google Patents
Adjusting device Download PDFInfo
- Publication number
- CN203047529U CN203047529U CN 201220620385 CN201220620385U CN203047529U CN 203047529 U CN203047529 U CN 203047529U CN 201220620385 CN201220620385 CN 201220620385 CN 201220620385 U CN201220620385 U CN 201220620385U CN 203047529 U CN203047529 U CN 203047529U
- Authority
- CN
- China
- Prior art keywords
- torque tube
- deformation
- torque
- adjusting device
- joint
- 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.)
- Expired - Lifetime
Links
- 230000000694 effects Effects 0.000 abstract description 2
- 230000000903 blocking Effects 0.000 abstract 1
- 230000001131 transforming Effects 0.000 abstract 1
- 230000001808 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001105 regulatory Effects 0.000 description 1
Abstract
The utility model relates to an adjusting device which is used for transformation adjustment of a torque tube of an actuation system on an airplane. One end of a universal joint of the adjusting device is connected with the torque tube; the torque tube is provided with a connecting hole; the other end of the universal joint is connected with a torque tube with an internal spline; and a long round hole is formed in the torque tube with the internal spline. The adjusting device has the advantages and the beneficial effects that the axial deformation and the angle deformation of the torque tubes can be adjusted according to needs, so that the seam slat actuation system can completely adapt to the deformation of a wing structure, the damage of the torque tubes due to deformation of wings can be avoided, the damage of structure caused by damage of the torque tubes can be avoided, the blocking of the actuation system caused by the deformation of the wings can be avoided, the operation efficiency of the seam slat actuation system can be ensured, and the safety of the airplane can be ensured.
Description
Technical field
The utility model relates to a kind of control apparatus for the deformation adjustment of actuating system Torque tube on the aircraft wing.
Background technology
Aircraft flap slat actuating system Torque tube is arranged in the fixedly front and rear edge of wing, and the trend of its Torque tube is fixed structurally along the wing front and rear beam, and distributed area is very long.When the wing stress deformation, be arranged in the Torque tube in the wing owing to be fixed on the wing structure, also can produce distortion along with the distortion of structure.The span of wing is long, be out of shape also bigger, if do not consider the compatible deformation of actuating system, actuating system may be because of wing distortion clamping stagnation, the structure stress distortion might damage Torque tube, if Torque tube damage meeting damages structure, influence the driving efficiency of flap slat actuating system, influence the safety of aircraft.
Summary of the invention
The purpose of this utility model provides the deformation adjustment device of actuating system torsion bar on a kind of aircraft wing.Technical solution of the present utility model is, an end of universal-joint connects a Torque tube, has two orthogonal connecting bores on the Torque tube, and the other end of universal-joint connects the Torque tube of a band female splines, has slotted hole on the Torque tube of band female splines.
The advantage that the utlity model has and beneficial effect, can regulate axial deformation and the angular distortion of Torque tube on demand by the utility model control apparatus, make the distortion of adaline wing structure fully of flap slat actuating system, avoid Torque tube to damage because of the wing distortion, avoid because of the Torque tube damage structure being damaged, avoid actuating system because of wing distortion clamping stagnation, guarantee the driving efficiency of flap slat actuating system, guarantee the safety of aircraft.
Description of drawings
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the cutaway view of Fig. 1;
Fig. 3 is application scheme drawing of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is elaborated.One end of universal-joint 1 connects a Torque tube 2, has connecting bore 5 on the Torque tube 2, and the other end of universal-joint 1 connects the Torque tube 6 of a band female splines, has slotted hole 7 on the Torque tube 6 of band female splines.
Be universal-joint 1 in the middle of the control apparatus, two termination one ends are hollow Torque tubes 2, the other end is the Torque tube 6 of band female splines, on the Torque tube 6 of Torque tube 2 and band female splines connecting bore 5 and 7 are arranged, the Torque tube 8 that the connecting bore 5 of Torque tube 2 one ends is used on the captive joint aircraft, the connecting bore 7 of Torque tube 6 one ends of band female splines is slotted hole, is used for the deflection of control aircraft Torque tube.Permanent joint 4 is male splines with Torque tube 6 coupling ends of band female splines, and with the spline fitted of the Torque tube 6 of being with female splines, permanent joint 4 has a hole to be connected with the slotted hole 7 usefulness bolts 3 of the Torque tube 6 of band female splines.As shown in Figure 3.In use, Torque tube 8 one ends are captiveed joint with the Torque tube 2 usefulness rivets of universal-joint 1 one ends, and are fastening in order to guarantee to connect, and can connect from mutually perpendicular direction with two rivets; Permanent joint 4 is fixedly connected on the wing structure; Torque tube 6 one ends and the permanent joint 4 of universal-joint 1 band female splines are engaged by spline, connect by bolt 3 again; When the Torque tube on the aircraft is compressed or is extended with the wing structure distortion, the spline of interlock shortens or elongation along with the Torque tube on the aircraft between universal-joint 1 and the permanent joint 4, be fixed in the slotted hole 7 of bolt 3 on universal-joint 1 on the permanent joint 4 mobile, in order to control to adjust the axial deflection of Torque tube on the aircraft, universal-joint 1 is used for regulating its angle to be changed.
Claims (2)
1. control apparatus, it is characterized in that, one end of the universal-joint of control apparatus (1) connects a Torque tube (2), have connecting bore (5) on the Torque tube (2), the other end of universal-joint (1) connects the Torque tube (6) of a band female splines, has slotted hole (7) on the Torque tube (6) of band female splines.
2. a kind of control apparatus according to claim 1 is characterized in that, has two orthogonal connecting bores (5) on the described Torque tube (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220620385 CN203047529U (en) | 2012-11-21 | 2012-11-21 | Adjusting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220620385 CN203047529U (en) | 2012-11-21 | 2012-11-21 | Adjusting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203047529U true CN203047529U (en) | 2013-07-10 |
Family
ID=48730512
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220620385 Expired - Lifetime CN203047529U (en) | 2012-11-21 | 2012-11-21 | Adjusting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203047529U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104973237A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Cardan universal joint type flap transmission mechanism |
-
2012
- 2012-11-21 CN CN 201220620385 patent/CN203047529U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104973237A (en) * | 2015-07-15 | 2015-10-14 | 江西洪都航空工业集团有限责任公司 | Cardan universal joint type flap transmission mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130710 |
|
| CX01 | Expiry of patent term |