CN111140641A - Backlash eliminating gear for coupling flight control shaft and angle sensor and using method thereof - Google Patents
Backlash eliminating gear for coupling flight control shaft and angle sensor and using method thereof Download PDFInfo
- Publication number
- CN111140641A CN111140641A CN201911265467.8A CN201911265467A CN111140641A CN 111140641 A CN111140641 A CN 111140641A CN 201911265467 A CN201911265467 A CN 201911265467A CN 111140641 A CN111140641 A CN 111140641A
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- Prior art keywords
- gear
- hole
- backlash
- annular tooth
- angle sensor
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- Pending
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 22
- 238000000034 method Methods 0.000 title claims abstract description 16
- 230000008878 coupling Effects 0.000 title claims description 9
- 238000010168 coupling process Methods 0.000 title claims description 9
- 238000005859 coupling reaction Methods 0.000 title claims description 9
- 230000005540 biological transmission Effects 0.000 claims abstract description 10
- 230000013011 mating Effects 0.000 claims description 5
- 238000009434 installation Methods 0.000 abstract description 5
- 230000007547 defect Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000008030 elimination Effects 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H55/00—Elements with teeth or friction surfaces for conveying motion; Worms, pulleys or sheaves for gearing mechanisms
- F16H55/02—Toothed members; Worms
- F16H55/17—Toothed wheels
- F16H55/18—Special devices for taking up backlash
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H55/00—Elements with teeth or friction surfaces for conveying motion; Worms, pulleys or sheaves for gearing mechanisms
- F16H55/02—Toothed members; Worms
- F16H55/12—Toothed members; Worms with body or rim assembled out of detachable parts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H55/00—Elements with teeth or friction surfaces for conveying motion; Worms, pulleys or sheaves for gearing mechanisms
- F16H55/02—Toothed members; Worms
- F16H55/14—Construction providing resilience or vibration-damping
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gear Transmission (AREA)
- Gears, Cams (AREA)
Abstract
The invention discloses an anti-backlash gear and a meshing installation method, belongs to the technical field of transmission design of sensors of flight control systems, and relates to RVDT anti-backlash gear transmission design, which comprises a gear A, a gear B, a tension spring, a limiting pin, a baffle plate and an installation pin; the gear is provided with the mounting hole, the phase of the mounting hole is aligned with the gear tooth phase of the gear, and the process hole positioning method is adopted, so that the multiple groups of anti-backlash gears are simply and conveniently meshed with the main gear, the gear is not damaged, and the mounting quality and the production efficiency are improved.
Description
Technical Field
The invention belongs to the field of RVDT transmission design, and particularly relates to an anti-backlash gear for coupling a flight control shaft and an angle sensor and a using method thereof.
Background
In the airplane control system, a rotary position sensor converts a control angular displacement signal of an airplane into an electric signal and sends the electric signal to a flight control system, the rotary position sensor is driven by a gear, and the meshing clearance of the gear drive directly influences the real-time performance of a flight control instruction. Therefore, anti-backlash gears are often used for transmission.
The existing anti-backlash gears are inconvenient to install and limited in precision, accurate meshing between each group of anti-backlash gears and a main gear is very critical in a redundant gear transmission system, the existing anti-backlash gears need to be meshed simply by using a tool during meshing, the surfaces of gear teeth are easily scratched or even damaged, and the defects of inconvenient installation and operation exist.
Disclosure of Invention
The purpose of the invention is: aiming at the defects of the transmission of the sensor gear of the existing flight control system, the clearance elimination gear coupling the flight control shaft and the angle sensor and the use method thereof are provided, the gear is provided with the mounting hole, the phase of the mounting hole is aligned with the gear tooth of the gear, and the positioning method of the process hole is adopted, so that the multiple groups of clearance elimination gears are simply and conveniently meshed with the main gear, the gear is not damaged, and the mounting quality and the production efficiency are improved.
The technical scheme of the invention is as follows: an anti-backlash gear for coupling a flight control operating shaft with an angle sensor comprises a gear, wherein one end of the gear is provided with a connecting structure with an input shaft of the angle sensor, the other end of the gear is sleeved with an annular tooth sheet, the annular tooth sheet is limited in the axial direction through a baffle, and gear teeth of the gear and gear teeth of the annular tooth sheet form a transmission end; the limiting pin is a stepped cylindrical pin, the small end of the limiting pin is in interference fit with a first limiting pin hole of the gear, the large end of the limiting pin is arranged in a second limiting pin hole on the annular tooth piece, and the annular tooth piece can move; a through waist-shaped through hole is further formed in the eccentric position of the gear and the annular tooth sheet, one end of a tension spring is installed at one end of the waist-shaped through hole of the gear, and the other end of the tension spring is installed at the other end of the waist-shaped through hole of the annular tooth sheet; the gear is also provided with a first positioning hole, the annular tooth sheet is also provided with a second positioning hole, the first positioning hole and the second positioning hole are superposed, and the circle center is positioned on the central line of any tooth of the gear.
Furthermore, the gear is provided with an axial bulge, the height of the axial bulge is slightly higher than the thickness of the annular tooth piece, and the annular tooth piece is sleeved on the axial bulge.
Further, the axial protrusion is beyond the annular tooth plate by 0.05-0.30 mm.
Further, the baffle is installed on the axial protrusion of the gear through a screw.
Furthermore, the end part of the gear, which is connected with the tension spring, in the waist-shaped through hole is provided with a first sinking groove, the first sinking groove is provided with a first through hole, and a first hook connected with the tension spring is installed in the first sinking groove; the annular tooth sheet is provided with a second sinking groove in the waist-shaped through hole and the end part of the tension spring, the second sinking groove is provided with a second through hole, and a second hook connected with the tension spring is installed in the second sinking groove.
Furthermore, the connecting structure with the input shaft of the angle sensor comprises a hollow shaft with an opening, the bottom of the hollow shaft is provided with a groove, the opening is provided with a via hole, and the hollow shaft is connected with the input shaft of the angle sensor in a holding mode.
Further, the positioning during the installation is carried out by inserting the installation pin into the first positioning hole and the second positioning hole.
The invention also provides a use method of the backlash eliminating gear for coupling the flight control operating shaft with the angle sensor, the method realizes the transmission of the flight control operating shaft and the angle sensor by using the backlash eliminating gear, and the method comprises the following steps:
a) sleeving the annular toothed sheet on the gear, adjusting the first positioning hole and the second positioning hole to be aligned and using the mounting pin for restraining;
b) installing and fixing a baffle plate;
c) installing a tension spring;
d) mounting and fixing the anti-backlash gear and a mating gear of the flight control operating shaft in a meshing manner;
e) removing the mounting pin;
f) the gear is connected with an angle sensor.
Furthermore, a plurality of anti-backlash gears are respectively arranged between a plurality of mating gears and a plurality of angle sensors of the flight control operating shaft.
The invention has the advantages that: the meshing of the anti-backlash gear and the main gear is simple and convenient, the gear is not damaged, and the mounting quality and the production efficiency are improved.
Drawings
FIG. 1 is a front view of a diagram of an anti-backlash gear of the present invention;
FIG. 2 is a cross-sectional view A-A of FIG. 1;
FIG. 3 is a schematic structural view of a gear;
FIG. 4 is a left side view of FIG. 3;
FIG. 5 is a schematic structural view of an annular tooth plate;
FIG. 6 is a schematic view of a spacing pin;
fig. 7 is a right side view of fig. 6.
Wherein: 1-gear, 2-annular gear piece, 3-limit pin, 4-baffle, 5-tension spring, 6-mounting pin, 7-screw, 1 a-first through hole, 1 b-first limit pin hole, 1 c-first locating hole, 1 d-axial bulge, 1 e-hollow shaft, 1 f-via hole, 1 g-groove, 1 h-opening, 2 a-second through hole, 2 b-second limit pin hole, 2 c-second locating hole, 3 a-cylindrical pin thick end and 3 b-cylindrical pin thin end
Detailed Description
Referring to fig. 1 through 7, specific embodiments are provided: an anti-backlash gear for coupling a flight control operating shaft and an angle sensor comprises a gear 1, an annular tooth sheet 2, a limiting pin 3, a baffle 4, a tension spring 5, a mounting pin 6 and a screw 7.
The gear is provided with a limiting pin hole 1b, the small end 2b of the limiting pin 3 is fixedly connected with the limiting pin hole 1b, the gear is provided with a positioning hole 1c, the phase of the positioning hole 1c is consistent with that of a tooth on the gear, the gear 1 is provided with at least one first through hole 1a, the left end of the first through hole 1a is provided with a sunk groove with a part of half surface not communicated, the sunk groove is provided with a through hole 1a, the center of the gear 1 is provided with a raised connecting structure 1e which is concentric and coaxial with the gear 1, the connecting structure 1e is radially provided with an opening, half of the connecting structure is a threaded hole and half of the connecting structure is a through hole, and the axial direction is separated from the gear.
The annular tooth piece 2 is provided with a second limit pin hole 2b, the thick end 3a of the limit pin moves with the limit pin hole 2b, the annular tooth piece 2 is provided with a positioning hole 2c, and the positioning hole 2c is consistent with the tooth phase of the annular tooth piece 2. The limit pin 3 is a stepped cylindrical pin and has a thick end 3a and a thin end 3 b.
The axial protrusion of the gear 1 beyond the annular tooth blade 2 is 0.1 mm; the baffle 4 is mounted on the axial projection 1d of the gear 1 by means of a screw 7.
The connecting structure of the input shaft of the angle sensor comprises a hollow shaft 1e with an opening 1h, wherein the bottom of the hollow shaft 1e is provided with a groove 1g, and a through hole 1f is formed in the opening and is connected with the input shaft of the angle sensor in a holding manner; and the mounting pin 6 is inserted into the first positioning hole 1c and the second positioning hole 2c for positioning during mounting.
When the flight control shaft is meshed with the backlash eliminating gear coupled with the angle sensor for use, the method comprises the following steps:
a) sleeving the annular toothed sheet 2 on the gear 2, adjusting the first positioning hole 1c and the second positioning hole 2c to be aligned and restricting by using the mounting pin 6;
b) installing and fixing a baffle 4;
c) installing a tension spring 5;
d) mounting and fixing the anti-backlash gear and a mating gear of the flight control operating shaft in a meshing manner;
e) removing the mounting pin 6;
f) the gear 1 is connected to an angle sensor.
When the flight control shaft couples the four angle sensors, four-redundancy connection is realized, and during use, four anti-backlash gears are adopted and are respectively installed between a plurality of pairing gears and the angle sensors of the flight control shaft.
Claims (9)
1. The utility model provides a fly to control backlash gear that control shaft and angle sensor coupling which characterized in that: the angle sensor comprises a gear (1), wherein one end of the gear is provided with a connecting structure with an input shaft of an angle sensor, the other end of the gear is sleeved with an annular tooth sheet (2), the annular tooth sheet (2) is limited in the axial direction through a baffle (4), and gear teeth of the gear (1) and gear teeth of the annular tooth sheet (2) jointly form a transmission end; the limiting pin (3) is a stepped cylindrical pin, the small end (3b) is in interference fit with the first limiting pin hole (1b) of the gear (1), the large end (3a) is arranged in the second limiting pin hole (2b) on the annular tooth piece (2), and the annular tooth piece (2) can move; a through waist-shaped through hole is further formed in the eccentric positions of the gear (1) and the annular tooth sheet (2), one end of a tension spring (5) is installed at one end of the waist-shaped through hole of the gear (1), and the other end of the tension spring (5) is installed at the other end of the waist-shaped through hole of the annular tooth sheet (2); the gear (1) is further provided with a first positioning hole (1c), the annular tooth piece (2) is further provided with a second positioning hole (2c), the first positioning hole (1c) and the second positioning hole (2c) are overlapped, and the circle center is located on the central line of any tooth of the gear (1).
2. The anti-backlash gear according to claim 1, wherein: the gear (1) is provided with an axial bulge (1d), the height of the axial bulge (1d) is slightly higher than the thickness of the annular tooth piece (2), and the annular tooth piece (2) is sleeved on the axial bulge.
3. The anti-backlash gear according to claim 2, wherein: the axial protrusion exceeds the annular tooth sheet (2) by 0.05-0.30 mm.
4. The anti-backlash gear according to claim 2, wherein: the baffle (4) is arranged on an axial bulge (1d) of the gear (1) through a screw (7).
5. The anti-backlash gear according to any one of claims 1 to 4, wherein: the end part of the gear (1) connected with the tension spring (5) in the waist-shaped through hole is provided with a first sinking groove, the first sinking groove is provided with a first through hole (1a), and a first hook connected with the tension spring (5) is installed in the first sinking groove; the annular tooth sheet (2) is provided with a second sinking groove in the waist-shaped through hole and the end part of the tension spring (5), the second sinking groove is provided with a second through hole (2a), and a second hook connected with the tension spring (5) is installed in the second sinking groove.
6. The anti-backlash gear according to any one of claims 1 to 4, wherein: the connecting structure with the input shaft of the angle sensor comprises a hollow shaft (1e) with an opening (1h), a groove (1g) is formed in the bottom of the hollow shaft (1e), a through hole (1f) is formed in the opening, and the connecting structure is connected with the input shaft of the angle sensor in a holding mode.
7. The anti-backlash gear according to claim 4, wherein: and positioning during mounting is performed by inserting the mounting pin (6) into the first positioning hole (1c) and the second positioning hole (2 c).
8. A method for using an anti-backlash gear for coupling a flight control steering shaft with an angle sensor, wherein the method utilizes the anti-backlash gear of any one of claims 1 to 7 to realize transmission of the flight control steering shaft with the angle sensor, and comprises the following steps:
a) sleeving the annular gear sheet (2) on the gear (1), adjusting the first positioning hole (1c) and the second positioning hole (2c) to be aligned and using the mounting pin (6) for constraint;
b) installing and fixing a baffle plate (4);
c) a tension spring (5) is arranged;
d) mounting and fixing the anti-backlash gear and a mating gear of the flight control operating shaft in a meshing manner;
e) removing the mounting pin (6);
f) the gear (1) is connected with an angle sensor.
9. The use method of an anti-backlash gear according to claim 8, wherein: a plurality of anti-backlash gears are respectively arranged between a plurality of mating gears and a plurality of angle sensors of the flight control operating shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911265467.8A CN111140641A (en) | 2019-12-11 | 2019-12-11 | Backlash eliminating gear for coupling flight control shaft and angle sensor and using method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911265467.8A CN111140641A (en) | 2019-12-11 | 2019-12-11 | Backlash eliminating gear for coupling flight control shaft and angle sensor and using method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111140641A true CN111140641A (en) | 2020-05-12 |
Family
ID=70517980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911265467.8A Pending CN111140641A (en) | 2019-12-11 | 2019-12-11 | Backlash eliminating gear for coupling flight control shaft and angle sensor and using method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111140641A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112762816A (en) * | 2020-12-25 | 2021-05-07 | 兰州飞行控制有限责任公司 | Redundancy angular displacement sensor with self-isolation blocking fault and use method |
| EP4036528A1 (en) * | 2021-01-29 | 2022-08-03 | Sensata Technologies, Inc. | Dual rotary variable differential transducer |
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| CN202441839U (en) * | 2012-03-01 | 2012-09-19 | 北京机械设备研究所 | Axially-limited anti-backlash gear |
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| CN103388669A (en) * | 2013-08-05 | 2013-11-13 | 潍柴动力股份有限公司 | Idler wheel and motor with the idler wheel |
| WO2013190458A1 (en) * | 2012-06-18 | 2013-12-27 | Adept Airmotive (Proprietary) Limited | Anti-backlash arrangement for use with a gear drive assembly |
| CN103775610A (en) * | 2012-10-25 | 2014-05-07 | 米巴烧结奥地利有限公司 | Gear system |
| CN204175921U (en) * | 2014-10-23 | 2015-02-25 | 贵州群建精密机械有限公司 | One disappears gap planetary pinion |
| CN205190676U (en) * | 2015-12-01 | 2016-04-27 | 上海宗力印刷包装机械有限公司 | Combined type gear |
| CN205278329U (en) * | 2015-11-20 | 2016-06-01 | 重庆市上泽机电有限公司 | Gear crack structure that disappears |
| CN205937707U (en) * | 2016-08-30 | 2017-02-08 | 长城汽车股份有限公司 | Anti -backlash gear subassembly and balanced axle assembly |
| CN205937708U (en) * | 2016-06-07 | 2017-02-08 | 上海锐拍智能科技有限公司 | Integral type drive gear |
| CN206072296U (en) * | 2016-09-14 | 2017-04-05 | 沈阳精力传动设备有限公司 | A kind of backlash gear mechanism |
| CN110206868A (en) * | 2019-06-29 | 2019-09-06 | 潍柴动力股份有限公司 | A kind of gear assembly and engine |
-
2019
- 2019-12-11 CN CN201911265467.8A patent/CN111140641A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202441839U (en) * | 2012-03-01 | 2012-09-19 | 北京机械设备研究所 | Axially-limited anti-backlash gear |
| WO2013190458A1 (en) * | 2012-06-18 | 2013-12-27 | Adept Airmotive (Proprietary) Limited | Anti-backlash arrangement for use with a gear drive assembly |
| CN202690961U (en) * | 2012-08-01 | 2013-01-23 | 贵州群建精密机械有限公司 | Gear without backlash |
| CN103775610A (en) * | 2012-10-25 | 2014-05-07 | 米巴烧结奥地利有限公司 | Gear system |
| CN102996757A (en) * | 2012-12-11 | 2013-03-27 | 北京遥测技术研究所 | Double gear backlash structure for staggered teeth regulation spring force |
| CN103388669A (en) * | 2013-08-05 | 2013-11-13 | 潍柴动力股份有限公司 | Idler wheel and motor with the idler wheel |
| CN204175921U (en) * | 2014-10-23 | 2015-02-25 | 贵州群建精密机械有限公司 | One disappears gap planetary pinion |
| CN205278329U (en) * | 2015-11-20 | 2016-06-01 | 重庆市上泽机电有限公司 | Gear crack structure that disappears |
| CN205190676U (en) * | 2015-12-01 | 2016-04-27 | 上海宗力印刷包装机械有限公司 | Combined type gear |
| CN205937708U (en) * | 2016-06-07 | 2017-02-08 | 上海锐拍智能科技有限公司 | Integral type drive gear |
| CN205937707U (en) * | 2016-08-30 | 2017-02-08 | 长城汽车股份有限公司 | Anti -backlash gear subassembly and balanced axle assembly |
| CN206072296U (en) * | 2016-09-14 | 2017-04-05 | 沈阳精力传动设备有限公司 | A kind of backlash gear mechanism |
| CN110206868A (en) * | 2019-06-29 | 2019-09-06 | 潍柴动力股份有限公司 | A kind of gear assembly and engine |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112762816A (en) * | 2020-12-25 | 2021-05-07 | 兰州飞行控制有限责任公司 | Redundancy angular displacement sensor with self-isolation blocking fault and use method |
| CN112762816B (en) * | 2020-12-25 | 2022-07-05 | 兰州飞行控制有限责任公司 | Redundancy angular displacement sensor with self-isolation blocking fault and use method |
| EP4036528A1 (en) * | 2021-01-29 | 2022-08-03 | Sensata Technologies, Inc. | Dual rotary variable differential transducer |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200512 |
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| RJ01 | Rejection of invention patent application after publication |