CN111003159B - Circumferential adjusting device of aircraft steering angular displacement release mechanism - Google Patents
Circumferential adjusting device of aircraft steering angular displacement release mechanism Download PDFInfo
- Publication number
- CN111003159B CN111003159B CN201911265450.2A CN201911265450A CN111003159B CN 111003159 B CN111003159 B CN 111003159B CN 201911265450 A CN201911265450 A CN 201911265450A CN 111003159 B CN111003159 B CN 111003159B
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- base
- waist
- adjusting
- release mechanism
- hole
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Mechanical Control Devices (AREA)
- Toys (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
Abstract
The invention belongs to the field of design of aircraft control systems, and particularly relates to a circumferential adjusting device of an aircraft control angular displacement release mechanism, which is used for adjusting phase deviation when the aircraft control angular displacement release mechanism is installed. The existing aircraft steering angular displacement release mechanism is characterized in that a bellows coupling is utilized to adjust the circumferential angle generated during installation, and the circumferential angle is mainly compensated by utilizing the elasticity of a bellows. Poor transmission rigidity; the transmitted rated load is smaller; the structure is relatively complex. The invention comprises a left adjusting block and a right adjusting block, wherein the left adjusting block is provided with a plurality of waist-shaped holes in the left base, and the edge of the left base is also provided with opposite stop blocks; the right adjusting block is provided with a plurality of threaded holes which are opposite to the waist-shaped holes around the right base. The adjusting device can solve all errors generated by the spline of the front and back steering rod system during processing and assembly, the adjusting process is simple, the transmission rigidity of the adjusted device is high, no gap exists during movement, and larger load can be transmitted.
Description
Technical Field
The invention belongs to the field of design of aircraft control systems, and particularly relates to a circumferential adjusting device of an aircraft control angular displacement release mechanism, which is used for adjusting phase deviation when the aircraft control angular displacement release mechanism is installed.
Background
The existing aircraft steering angular displacement release mechanism is characterized in that a bellows coupling is utilized to adjust the circumferential angle generated during installation, and the circumferential angle is mainly compensated by utilizing the elasticity of a bellows. The bellows coupling consists of two hubs and a thin-walled metal tube that are joined together by welding or bonding. The input end of the coupler is of a clamping clamp structure, pretightening force is generated through a clamping screw, the power input shaft and the clamping clamp are fixedly connected into a whole, the output end of the coupler is of an expansion structure, and the expansion sleeve is expanded through the pretightening cone of the expansion screw and is matched with the inner hole of the power output shaft to be connected into a whole. The middle is a corrugated pipe structure, and two ends of the corrugated pipe are fixedly connected with the input end and the output end in a cementing way.
The defects are that: firstly, the bellows has poor transmission rigidity because of good elasticity; secondly, the corrugated pipe wall is thinner, so that the rated load which can be transmitted is smaller; finally, the structure which has been deformed for compensating the bellows at the time of installation has play in the movement and is relatively complex in structure.
Disclosure of Invention
The purpose of the invention is that: a circumferential adjustment device of an airplane steering angle displacement release mechanism is provided, and is used for adjusting the phase deviation of a spline of a positive and negative steering rod system when the angle displacement release mechanism is connected with the positive and negative steering rod system. The adjusting device can solve all errors generated by the spline of the front and back steering rod system during processing and assembly, the adjusting process is simple, the transmission rigidity of the adjusted device is high, no gap exists during movement, and larger load can be transmitted.
The technical scheme of the invention is as follows: a circumferential adjusting device of an aircraft steering angle displacement release mechanism comprises a left adjusting block and a right adjusting block, wherein
The left adjusting block is provided with a left base, the left side of the left base is in spline connection with a positive driving rod, a plurality of waist-shaped holes are formed in the left base, opposite stop blocks are further arranged at the edge of the left base, the stop blocks (1 c) are provided with threaded holes, and shafts are arranged on the right side of the left base;
the right adjusting block is provided with a right base, the right side of the right base is connected with a rod body in the release mechanism, the middle of the right base is provided with a hole, and a plurality of threaded holes opposite to the waist-shaped holes are formed in the periphery of the right base;
the screw passes through the waist-shaped hole and is connected with the threaded hole of the right base, the screw rod is respectively connected with the threaded hole of the stop block and tightly pushes against the convex block, and the screw rod is locked by the double-lug stop washer and the nut.
Further, the left base is of a partial disc-shaped structure, the right base is of a disc-shaped structure, the stop blocks are arranged in the non-circular arc area of the left base, and a certain movable angle is formed between the two stop blocks by the protruding blocks.
Further, the left side of the right base is provided with a plurality of bosses which are opposite to the waist-shaped holes, and the bosses are provided with threaded holes.
Further, the left base is provided with a holding structure on the left end face, the holding structure is provided with a spline and an open end, and an end hole is formed in a clamping arm at the open end and is clamped after being connected through a bolt.
Furthermore, the device can be adjusted in a stepless manner in the circumferential direction, and the adjusting angle is restrained by the length of the kidney-shaped hole and the size of the notch.
Further, the adjustment angle is in the range of 0 ° -30 °.
Further, during installation, the shaft is matched with the hole for radial positioning, and the right end face of the left base is matched with the boss of the right base for axial positioning.
Further, the size and position of the kidney-shaped aperture is determined by the angle and position of the aperture that need circumferential adjustment.
The number of kidney-shaped holes is 3.
The invention has the advantages that: the circumferential adjusting device of the airplane steering angle displacement release mechanism is used for compensating the phase deviation of the spline of the positive and negative steering column system when the angle displacement release mechanism is connected with the positive and negative steering column system, so that the problem of difficult installation of the rigid release mechanism is solved; the adjusting device can compensate all errors generated by the spline of the front and back steering rod system during processing and assembly, the adjusting process is simple, the transmission rigidity of the adjusted device is high, no gap exists during movement, and larger rated load can be transmitted.
Drawings
FIG. 1 is an exploded schematic view of a circumferential adjustment device of an aircraft steering angular displacement release mechanism of the present invention;
FIG. 2 is a front view of a circumferential adjustment device of the aircraft steering angular displacement release mechanism of the present invention;
FIG. 3 is a left side view of the circumferential adjustment device of the aircraft steering angular displacement release mechanism of the present invention;
fig. 4 is a top cross-sectional view of a circumferential adjustment device of the aircraft steering angular displacement release mechanism of the present invention.
1-a left regulating block; 1 a-spline; 1 b-a waist-shaped hole; 1 c-bump; 1 d-notch; 1 f-axis; 1 h-end hole; 2-right adjusting block; 2 a-bumps; 2 b-a threaded hole; 2 c-boss; 2 d-linker; 2 e-well; 3-screws; 3 a-a safety vent; 4-a screw; 4 a-sphere; 5-binaural stop washers; 6-nut
Detailed Description
The present invention will be described in further detail below. The circumferential adjusting device of the aircraft steering angle displacement release mechanism comprises a left adjusting block 1, a right adjusting block 2, three screws 3, two screws 4, two double-lug stop washers 5 and two nuts 6.
The spline 1a on the left adjusting block 1 is connected with the spline of the positive driving rod system, and the end hole 1h is used for installing a bolt so as to prevent the relative movement of the spline of the positive driving rod system after being connected with the spline 1 a; when the left adjusting block 1 and the right adjusting block 2 are installed, the shaft 1f is matched with the hole 2e for radial positioning, and the right end face 1g of the left adjusting block 1 is matched with the three bosses 2c of the left end face of the right adjusting block 2 for axial positioning; the right joint 2d of the right regulating block 2 is connected with the inner rod body of the release mechanism and is used for transmitting the movement of the positive steering rod system to the release mechanism until reaching the auxiliary steering rod system; when the phase is adjusted to meet the requirement, three screws 3 pass through waist-shaped holes 1b on the left adjusting block 1 and then are connected with threaded holes on three bosses 2c of the right adjusting block 2, then the screw 4 is rotated to enable a screw sphere 4a to prop against a boss 2a of the right adjusting block 2, a double-lug stop washer 5 is installed, and a nut 6 is fastened; finally, the fuse is threaded into the head safety holes 3a of the three screws 3 for locking. The binaural stop washer 5 is used for preventing the loosening of the nut 6, and the screw 3 is selected to have a head with a safety hole 3a specification, so as to prevent the loosening of the screw 3.
The working principle of the invention is as follows: the relative rotation between the left adjusting block 1 and the right adjusting block 2 is utilized to adjust the phase of the internal spline 1a to be consistent with that of the spline of the positive driving rod system, the pretightening force generated by the screw 3 on the matching surface of the end face 1g and the three bosses 2c is utilized to transmit torque after adjustment, the load which can be transmitted is larger, the adjusting process is simple, the transmission rigidity of the device after adjustment is high, and no gap exists during movement.
One embodiment of the invention: the circumferential adjusting device of the aircraft steering angle displacement release mechanism comprises two left adjusting blocks 12, three screws 3, two screw rods 4, two double-lug stop washers 5 and two nuts 6 which are matched with each other; the left adjusting block 1 is provided with an inner spline 1a connected with the positive steering column spline, and the upper end hole is used for installing a fastening screw so as to prevent the relative movement of the positive steering column spline and the inner spline 1a after being connected; when the left regulating block 12 is installed, the shaft 1f is matched with the hole 2e for radial positioning, and the end face 1g is matched with the three bosses 2c for axial positioning; the upper joint 2d of the right regulating block 2 is connected with a rod body inside the release mechanism and is used for transmitting the motion of the positive steering rod system to the release mechanism until reaching the auxiliary steering rod system; the screw and the screw are in a unscrewed state before the adjustment, the left adjusting block 1 or the right adjusting block 2 is rotated, after the phase is adjusted to meet the requirement, the three screws 3 are fastened, then the screw 4 is rotated to enable the screw sphere 4a to prop against the convex block 2a, the double-lug stop washer 5 is installed, and the nut 6 is fastened; finally, the fuse is threaded into the head safety holes 3a of the three screws 3 for locking.
In this embodiment, the maximum load transmitted by the circumferential adjustment device of the aircraft steering angular displacement release mechanism is 87n.m, so that the specification of the screw 3 is m8x22, the diameter of the center of the kidney-shaped hole 1b is phi 59mm, the maximum outer diameter of the left adjustment block 1 is phi 72mm, the rotatable angle of the screw 3 in the kidney-shaped hole 1b is 24 degrees, the rotatable angle of the lug 2a and the groove 1d is +/-11.6 degrees, and the adjustment angle range of the device is +/-11.6 degrees.
Claims (5)
1. The utility model provides a circumferential direction adjusting device of aircraft manipulation angular displacement tripping device which characterized in that: the device comprises a left regulating block (1) and a right regulating block (2), wherein
The left adjusting block (1) is provided with a left base, the left side of the left base is in spline connection with a positive driving rod system, a plurality of waist-shaped holes (1 b) are formed in the left base, opposite stop blocks (1 c) are further arranged at the edge of the left base, the stop blocks (1 c) are provided with first threaded holes (1 e), and a shaft (1 f) is arranged on the right side of the left base;
the right adjusting block (2) is provided with a right base, the right side of the right base is connected with a rod body in the release mechanism, the middle part of the right base is provided with a hole (2 e), the left side of the right base is provided with a plurality of bosses (2 c) opposite to the waist-shaped hole (1 b) and a lug (2 a) positioned between a pair of stop blocks (1 c) after being combined, and the bosses (2 c) are provided with second threaded holes (2 b);
during installation, the shaft (1 f) is matched with the hole (2 e) for radial positioning, and the right end face (1 g) of the left base is matched with the boss (2 c) of the right base for axial positioning;
the screw (3) passes through the waist-shaped hole (1 b) to be connected with the second threaded hole (2 b) of the right base, the screw rod (4) is respectively connected with the first threaded hole (1 e) of the stop block (1 c) and tightly props against the convex block (2 a), and the screw rod is locked by the double-lug stop washer (5) and the nut (6); the left base is of a partial disc-shaped structure, the right base is of a disc-shaped structure, the stop blocks (1 c) are arranged in the non-circular arc area of the left base, and the convex blocks (2 a) have a certain movable angle between the two stop blocks (1 c); the device can be adjusted steplessly in the circumferential direction, and the adjusting angle is restrained by the length of the waist-shaped hole (1 b) and the size of the notch (1 d).
2. The circumferential adjustment apparatus of claim 1, wherein: the left base is provided with a holding structure on the left end face, the holding structure is provided with a spline (1 a) and an open end, and an end hole (1 h) is formed in a clamping arm of the open end and is clamped after being connected through a bolt.
3. The circumferential adjustment apparatus of claim 1, wherein: the adjusting angle is in the range of 0-30 degrees.
4. The circumferential adjustment apparatus of claim 1, wherein: the size and position of the waist-shaped hole (1 b) are determined by the angle required to be circumferentially adjusted and the position of the second threaded hole (2 b).
5. The circumferential adjustment apparatus of claim 1, wherein: the number of the waist-shaped holes (1 b) is 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911265450.2A CN111003159B (en) | 2019-12-11 | 2019-12-11 | Circumferential adjusting device of aircraft steering angular displacement release mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911265450.2A CN111003159B (en) | 2019-12-11 | 2019-12-11 | Circumferential adjusting device of aircraft steering angular displacement release mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111003159A CN111003159A (en) | 2020-04-14 |
| CN111003159B true CN111003159B (en) | 2023-09-22 |
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ID=70115255
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911265450.2A Active CN111003159B (en) | 2019-12-11 | 2019-12-11 | Circumferential adjusting device of aircraft steering angular displacement release mechanism |
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| Country | Link |
|---|---|
| CN (1) | CN111003159B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4881922A (en) * | 1987-08-31 | 1989-11-21 | Texas Instruments Incorporated | Separable drive coupling using metal bellows |
| CN203335657U (en) * | 2013-07-19 | 2013-12-11 | 皇明太阳能股份有限公司 | Coupler |
-
2019
- 2019-12-11 CN CN201911265450.2A patent/CN111003159B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4881922A (en) * | 1987-08-31 | 1989-11-21 | Texas Instruments Incorporated | Separable drive coupling using metal bellows |
| CN203335657U (en) * | 2013-07-19 | 2013-12-11 | 皇明太阳能股份有限公司 | Coupler |
Non-Patent Citations (1)
| Title |
|---|
| 王亚芹.《联轴器》.《全国机械行业职业教育优质规划教材》.2019, * |
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| Publication number | Publication date |
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| CN111003159A (en) | 2020-04-14 |
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