CN108953312B - Mechanical locking structure of actuator sensor - Google Patents
Mechanical locking structure of actuator sensor Download PDFInfo
- Publication number
- CN108953312B CN108953312B CN201810826956.5A CN201810826956A CN108953312B CN 108953312 B CN108953312 B CN 108953312B CN 201810826956 A CN201810826956 A CN 201810826956A CN 108953312 B CN108953312 B CN 108953312B
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- locking
- nut
- piston
- displacement sensor
- hole
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- 238000006073 displacement reaction Methods 0.000 claims abstract description 33
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 25
- 239000000463 material Substances 0.000 claims abstract description 5
- 238000007789 sealing Methods 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 241000256259 Noctuidae Species 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012795 verification Methods 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B1/00—Devices for securing together, or preventing relative movement between, constructional elements or machine parts
- F16B1/02—Means for securing elements of mechanisms after operation
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Actuator (AREA)
Abstract
The invention belongs to the design technology of airplane hydraulic actuators, and particularly relates to a mechanical locking structure of an actuator sensor. By piston (1), displacement sensor iron core (2), locking washer (3), nut (4), spring washer (5) and self-locking nut (6) are constituteed, blind hole (1a) bottom surface at piston (1) has increased a locking hole (1d), twist displacement sensor iron core (2) soon to assigned position and accomplish the zeroing back, make some materials of locking washer (3) take place plastic deformation through external force, imbed in locking hole (1d), and compress tightly through nut (4), accomplish the mechanical locking of displacement sensor iron core (2) and piston (1) and be connected. The mechanical zero setting and mechanical locking structure of the actuator displacement sensor can be achieved in a narrow space, normal work of the actuator is guaranteed, and reliability is improved.
Description
Technical Field
The invention belongs to the design technology of airplane hydraulic actuators, and particularly relates to a mechanical locking structure of an actuator sensor.
Background
The flight control hydraulic actuator is generally installed in narrow spaces such as under wings of an airplane, receives an electric instruction of a flight control computer, and controls a piston of the actuator to do linear reciprocating motion through a hydraulic power amplifying device so as to drive the opening and closing of a flight control surface. The actuator feeds back the position of the piston of the actuator through a displacement sensor to realize closed-loop control. The electric zero position of the displacement sensor passes through an electric or mechanical zero position adjusting device, and the mechanical zero position adjusting device adjusts the relative position of an iron core of the displacement sensor and a piston of the actuator through a gasket or a thread to achieve the aim of coinciding with the mechanical zero position of the actuator.
Wherein, the structure of zeroing is realized through the screw thread, needs to carry out mechanical locking to the screw thread. The common thread zero setting locking mode is to notch the outer thread of the displacement sensor, embed the tongue piece of the locking washer in the notch, screw down the nut matched with the outer thread of the displacement sensor after zero setting, and finally bend the locking washer to a wrench plane of the nut.
Because the installation space of the airplane is limited, the piston adopts a structure that the external thread is connected with the earring, and the zero setting locking mode can not be realized because the space for operating the bending gasket is unavailable. One solution is to add an elastic washer between the nut and the piston, and to use double nuts to screw down the lock, and the external nut is a self-locking nut. The locking device can effectively prevent the external thread of the displacement sensor from loosening to the left end, but cannot effectively prevent a large moment for screwing to the right end, so that the locking reliability depends on the assembly process, and the requirement on assembly and adjustment operation is high. Due to the large removal friction torque of the self-locking nut, the displacement sensor may be unintentionally screwed out of the threaded bore of the piston during maintenance removal.
Disclosure of Invention
The purpose of the invention is: the utility model provides an actuator sensor mechanical locking structure for locking and actuator's threaded connection after the sensor zero set.
The technical scheme of the invention is as follows: a mechanical locking structure of an actuator sensor comprises a piston 1, a displacement sensor iron core 2, a locking gasket 3, a nut 4, a spring washer 5 and a self-locking nut 6, wherein the piston 1 is a cylinder, one end close to the self-locking nut 6 is a right end, the right end of the piston is provided with a blind hole 1a, the bottom of the blind hole 1a is a plane, the center of the hole bottom is provided with a threaded hole 1b and a concentric unthreaded hole 1c, a locking hole 1d is arranged near the threaded hole 1b, the displacement sensor iron core 2 is a stepped shaft, one end close to the self-locking nut 6 is a right end, the right end is provided with a through rectangular groove 2a, the right end stepped shaft is provided with an external thread 2b and an axial key groove 2c, the external thread 2b is connected with the threaded hole 1b of the piston 1, the locking gasket 3 is a circular ring piece, is sleeved on the external thread 2b of the displacement sensor iron, have a tongue piece 3a on the inner circle, in embedding displacement sensor iron core 2's the keyway 2C, locking washer 3 has certain plastic deformation ability, partly material is in the locking hole 1d of plastic deformation embedding piston 1, locking washer 3's one end and nut 4 contact, the other end and the contact of 1 bottom outlet plane of piston, nut 4 is a drum, be connected with displacement sensor iron core 2's external screw thread 2b, spring washer 5 is one and is close confined C shape ring, the open-ended both ends are not in same plane, press on the terminal surface of nut 4 through self-locking nut 6, self-locking nut 6 is connected with displacement sensor iron core 2's external screw thread 2b, be a screw thread standard component that has screw thread auto-lock function.
The invention has the advantages that: the mechanical zero setting and mechanical locking structure of the actuator displacement sensor can be achieved in a narrow space, normal work of the actuator is guaranteed, and reliability is improved.
Drawings
Fig. 1 is a schematic view of a thread locking structure for an aircraft hydraulic actuator at present.
Fig. 2 is a schematic structural diagram of the present invention.
Wherein, 1-piston, 2-displacement sensor iron core, 3-locking washer, 4-nut, 5-spring washer, 6-self-locking nut, 1 a-blind hole, 1 b-threaded hole, 1 c-unthreaded hole, 1 d-locking hole, 2 a-rectangular groove, 2 b-external thread, 2 c-key groove and 3 a-tongue piece
Detailed Description
The present invention is described in further detail below. Referring to fig. 2, a mechanical locking structure of an actuator sensor comprises a piston 1, a displacement sensor iron core 2, a locking gasket 3, a nut 4, a spring washer 5 and a self-locking nut 6, wherein the piston 1 is a cylinder, one end close to the self-locking nut 6 is a right end, the right end of the piston is provided with a blind hole 1a, the bottom of the blind hole 1a is a plane, the center of the bottom of the hole is provided with a threaded hole 1b and a concentric unthreaded hole 1c, a locking hole 1d is arranged near the threaded hole 1b, the displacement sensor iron core 2 is a stepped shaft, one end close to the self-locking nut 6 is a right end, the right end is provided with a through rectangular groove 2a, the right end stepped shaft is provided with an external thread 2b and an axial key groove 2c, the external thread 2b is connected with the threaded hole 1b of the piston 1, the locking gasket 3 is a circular ring piece, is sleeved on the external thread 2b of, have a tongue piece 3a on the inner circle, in embedding displacement sensor iron core 2's the keyway 2C, locking washer 3 has certain plastic deformation ability, partly material is in the locking hole 1d of plastic deformation embedding piston 1, locking washer 3's one end and nut 4 contact, the other end and the contact of 1 bottom outlet plane of piston, nut 4 is a drum, be connected with displacement sensor iron core 2's external screw thread 2b, spring washer 5 is one and is close confined C shape ring, the open-ended both ends are not in same plane, press on the terminal surface of nut 4 through self-locking nut 6, self-locking nut 6 is connected with displacement sensor iron core 2's external screw thread 2b, be a screw thread standard component that has screw thread auto-lock function.
The working principle of the invention is as follows: the bottom surface of the blind hole 1a of the piston 1 is additionally provided with a locking hole 1d, after the displacement sensor iron core 2 is screwed to a specified position to complete zero setting, part of materials of the locking gasket 3 are subjected to plastic deformation through external force and are embedded into the locking hole 1d, and the locking hole is pressed through the nut 4, so that the mechanical locking connection of the displacement sensor iron core 2 and the piston 1 is completed.
According to the embodiment of the invention, experimental verification is carried out on a certain type of actuator, mechanical locking is realized after the displacement sensor is mechanically zeroed, the normal work of the actuator is ensured, and the flight safety is ensured.
Claims (2)
1. The utility model provides an actuator sensor mechanical locking structure, comprises piston (1), displacement sensor iron core (2), lock washer (3), nut (4), spring washer (5) and auto-lock nut (6), its characterized in that: the piston (1) is a cylinder, one end close to the self-locking nut (6) is a right end, the right end of the piston is provided with a blind hole (1a), the bottom of the blind hole (1a) is a plane, the center of the bottom of the hole is provided with a threaded hole (1b) and a concentric unthreaded hole (1c), a locking hole (1d) is arranged near the threaded hole (1b), the displacement sensor iron core (2) is a stepped shaft, one end close to the self-locking nut (6) is a right end, the right end is provided with a through rectangular groove (2a), the right end stepped shaft is provided with an external thread (2b) and an axial keyway (2c), the external thread (2b) is connected with the threaded hole (1b) of the piston (1), the locking gasket (3) is a circular ring piece and is sleeved on the external thread (2b) of the displacement sensor iron core (2) and is contacted with the bottom surface of the blind hole (1a) of the piston (1, the locking washer (3) is embedded into a key groove (2c) of the displacement sensor iron core (2) and has certain plastic deformation capacity; the nut (4) is a cylinder and is connected with the external thread (2b) of the displacement sensor iron core (2), the spring washer (5) is a C-shaped ring close to the sealing, the two ends of the opening are not on the same plane and are pressed on the end surface of the nut (4) through the self-locking nut (6), and the self-locking nut (6) is connected with the external thread (2b) of the displacement sensor iron core (2).
2. The actuator sensor mechanical locking structure of claim 1, wherein: and a part of material of the locking gasket (3) is embedded into the locking hole (1d) of the piston (1) through plastic deformation, one end of the locking gasket (3) is contacted with the nut (4), and the other end of the locking gasket is contacted with the bottom hole plane of the piston (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810826956.5A CN108953312B (en) | 2018-07-25 | 2018-07-25 | Mechanical locking structure of actuator sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810826956.5A CN108953312B (en) | 2018-07-25 | 2018-07-25 | Mechanical locking structure of actuator sensor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108953312A CN108953312A (en) | 2018-12-07 |
| CN108953312B true CN108953312B (en) | 2020-04-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810826956.5A Active CN108953312B (en) | 2018-07-25 | 2018-07-25 | Mechanical locking structure of actuator sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108953312B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2076621U (en) * | 1990-10-24 | 1991-05-08 | 郜蕴厚 | Anti-loose self-locking threaded fastener |
| CN202188000U (en) * | 2011-08-04 | 2012-04-11 | 德阳电业局 | Double-nut connecting bolt |
| CN103042661A (en) * | 2011-10-17 | 2013-04-17 | 博创机械股份有限公司 | Special piston rod fastening mechanism for injection molding machines |
| CN203018614U (en) * | 2012-11-29 | 2013-06-26 | 舒丽琴 | Self-locking nut convergent jig |
| CN103496615A (en) * | 2013-10-14 | 2014-01-08 | 东台立文色织有限公司 | Novel disk type tension device |
-
2018
- 2018-07-25 CN CN201810826956.5A patent/CN108953312B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2076621U (en) * | 1990-10-24 | 1991-05-08 | 郜蕴厚 | Anti-loose self-locking threaded fastener |
| CN202188000U (en) * | 2011-08-04 | 2012-04-11 | 德阳电业局 | Double-nut connecting bolt |
| CN103042661A (en) * | 2011-10-17 | 2013-04-17 | 博创机械股份有限公司 | Special piston rod fastening mechanism for injection molding machines |
| CN203018614U (en) * | 2012-11-29 | 2013-06-26 | 舒丽琴 | Self-locking nut convergent jig |
| CN103496615A (en) * | 2013-10-14 | 2014-01-08 | 东台立文色织有限公司 | Novel disk type tension device |
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| Publication number | Publication date |
|---|---|
| CN108953312A (en) | 2018-12-07 |
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