CN205370161U - Direct action type electric control lock - Google Patents
Direct action type electric control lock Download PDFInfo
- Publication number
- CN205370161U CN205370161U CN201620166871.5U CN201620166871U CN205370161U CN 205370161 U CN205370161 U CN 205370161U CN 201620166871 U CN201620166871 U CN 201620166871U CN 205370161 U CN205370161 U CN 205370161U
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- CN
- China
- Prior art keywords
- electric control
- control lock
- iron core
- action type
- direct action
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- Expired - Fee Related
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Abstract
The utility model discloses a direct action type electric control lock, its characterized in that: including connecting gradually end cover (2), electro -magnet casing (3) and iron core (5), be equipped with between electro -magnet casing (3) and iron core (5) coil winding (4), iron core (5) middle part is equipped with the stroke cavity, and stroke cavity and end cover (2) inner wall is equipped with at a distance from magnetic ring (7), is equipped with armature (8) in magnetic ring (7), is equipped with small circle post inner chamber (12) and big cylindrical groove (13) of mutual intercommunication in armature (8), is equipped with reset spring (6) between the bottom in big cylindrical groove (13) and iron core (5), and small circle post inner chamber (12) is equipped with spring bolt (1), and stretch out outside end cover (2) spring bolt (1). The utility model has the characteristics of the electro -magnet reaction rapidly, the electromagnetic force is great, the electromagnetic force is steady and the armature stroke is big, can satisfy aircraft parachute -opening electric control lock stably unblanks rapidly under the environment of great impact force.
Description
Technical field
This utility model relates to the door lock driving mechanism in a kind of automatic control system, particularly a kind of protecting against shock Direct Action Type electric control lock for aircraft parachute opener.
Background technology
The actuator of aircraft parachute-opening is mostly completed by electric control lock.Cause the misoperation of electric control lock to prevent inertia impact acceleration in flight course, Direct Action Type lock core needs the spring adopting big pretightning force to keep locked position.Therefore, during parachute-opening, driving mechanism needs the pretightning force acting overcoming spring bigger, it is desirable to electric control lock keeps bigger electromagnetic force within the scope of LAP, it is achieved the aircraft parachute-opening function of electric control lock.But, the electromagnetic attraction that proportion electro-magnet energising in current most of electric control lock produces can change along with armature change in displacement, the factors such as electromagnetic attraction is little, stroke is shorter, spring stress is unstable, make the impact that electric control lock is easily subject to inertia impact cause drag parachute to open by mistake or malfunctioning situation, be unsuitable for being applied in that this impulsive force of aircraft parachute-opening is strong, electromagnetic force requires bigger occasion.
Utility model content
The purpose of this utility model is in that, it is provided that a kind of Direct Action Type electric control lock.This utility model has the advantages that electric magnet is swift in response, electromagnetic force is relatively big, electromagnetic force is steady and armature travel is big, can meet aircraft parachute-opening electric control lock and stably unblank rapidly under the environment of greater impact power.
The technical solution of the utility model: a kind of Direct Action Type electric control lock, including being sequentially connected with end cap, electromagnet housing and iron core, coil windings it is provided with between electromagnet housing and iron core, it is provided with stroke cavity, stroke cavity and end cap inwall in the middle part of described iron core and is provided with magnetism-isolating loop, in magnetism-isolating loop, be provided with armature, the small column inner chamber and big cylindrical groove that are interconnected it is provided with in armature, being provided with back-moving spring between big cylindrical groove and iron core inner bottom part, small column inner chamber is provided with dead bolt, and dead bolt extend out to outside end cap.
In aforesaid Direct Action Type electric control lock, the outer surface of described iron core is conical outer wall, and inner surface is cylindrical inner wall.
In aforesaid Direct Action Type electric control lock, the cone angle of described conical outer wall is 9-10 °.
In aforesaid Direct Action Type electric control lock, the big cylindrical groove of the bottom of described dead bolt and armature is fastened and connected.
In aforesaid Direct Action Type electric control lock, described back-moving spring one end and dead bolt ends contact, the other end contacts with the bottom surface cylindrical groove of iron core inner bottom part.
In aforesaid Direct Action Type electric control lock, described end cap is connected by fixing screw with electromagnet housing.
In aforesaid Direct Action Type electric control lock, described coil windings is connected to binding post.
Compared with prior art, the pretightning force of back-moving spring of the present utility model is relatively big, and after energising, the electromagnetic attraction that armature is subject to is relatively big, can effectively prevent electric control lock misoperation under inertia impact environment or malfunctioning situation of unblanking.Cone iron core of the present utility model improves the effective cross-sectional area of coil windings in certain space, makes the electromagnetic attraction that electric control lock produces in stroke range relatively big and steady.The magnetism-isolating loop that this utility model adopts both can reduce leakage field, the axiality in armature motion process can be improved again, weaken the frictional force being subject in armature motion process, compared with the mode with bearing and sealing ring, compact conformation, simple process, reduces leakage field effect better, improve the reliability that electric control lock works under inertia impact environment, meet the requirement of aircraft parachute-opening electric control lock steady operation in particular circumstances.And this utility model adopts simple Direct Action Type cylinder dead bolt, dead bolt is directly installed on armature, and moves with armature after coil electricity simultaneously, and this compares with the frame for movement of original complexity, reduces the difficulty of electric control lock assembling manufacturing.This utility model has the advantages that electric magnet is swift in response, electromagnetic force is relatively big, electromagnetic force is steady and armature travel is big, can meet aircraft parachute-opening electric control lock and stably unblank rapidly under the environment of greater impact power.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model；
Fig. 2 is external structure of the present utility model；
Fig. 3 is the axial symmetry face magnetic circuit figure of electric magnet in this utility model electric control lock.
Being labeled as in accompanying drawing: 1-dead bolt, 2-end cap, 3-electromagnet housing, 4-coil windings, 5-iron core, 6-back-moving spring, 7-magnetism-isolating loop, 8-armature, 9-fixes screw, 10-binding post, 11-reel, 12-small column inner chamber, the big cylindrical groove of 13-.
Detailed description of the invention
Below in conjunction with drawings and Examples, this utility model is further described, but is not intended as the foundation to this utility model restriction.
Embodiment.A kind of Direct Action Type electric control lock, constitute as illustrated in fig. 1 and 2, including being sequentially connected with end cap 2, electromagnet housing 3 and iron core 5, coil windings 4 it is provided with between electromagnet housing 3 and iron core 5, it is provided with stroke cavity in the middle part of described iron core 5, stroke cavity and end cap 2 inwall are provided with magnetism-isolating loop 7, armature 8 it is provided with in magnetism-isolating loop 7, the small column inner chamber 12 and big cylindrical groove 13 that are interconnected it is provided with in armature 8, it is provided with back-moving spring 6 between big cylindrical groove 13 and iron core 5 inner bottom part, small column inner chamber 12 is provided with dead bolt 1, and dead bolt 1 extend out to outside end cap 2.
The outer surface of described iron core 5 is conical outer wall, and inner surface is cylindrical inner wall.
The cone angle of described conical outer wall is 9-10 ° (being generally adopted by 9.5 °).
The bottom of described dead bolt 1 and the big cylindrical groove 13 of armature 8 are fastened and connected.
Described back-moving spring 6 one end and dead bolt 1 ends contact, the other end contacts with the bottom surface cylindrical groove of iron core 5 inner bottom part, and the pretightning force that back-moving spring 6 needs is approximately 30-35N.
Described end cap 2 is connected by fixing screw 9 with electromagnet housing 3.
Described coil windings 4 is connected to binding post 10.
Preferably, described coil windings 4 adopts uneven winding structure, that is: reel 11 is connected the bobbin of composition coil with iron core 5 conical outer wall, and the upper end coiling of coil windings 4 is on cylindrical reel 11, and the lower end coiling of coil windings 4 is on the outside conical surface of iron core 5.Coil windings 4 can fill up the space being made up of iron core 5, housing 3 and magnetism-isolating loop 7, and is connected with outside control circuit by binding post 10.
Described magnetism-isolating loop 7 can be made thin-walled ring by metallic copper material, and magnetism-isolating loop 7 is close to iron core 5, end cap 2 inwall, and iron core 5 and end cap 2 inwall are connected into a big cylindrical cavity.
When dead bolt 1 of the present utility model stretches out end cap 2, electric control lock is in locking state, and when the coil is energized, when electromagnetic attraction attracts armature 8 to drive dead bolt 1 indentation end cap 2, electric control lock is in unlocking condition.
The work magnetic circuit schematic diagram of the axially symmetric structure of the electric magnet of this utility model electric control lock is as shown in Figure 3, it is specific as follows: after binding post 10 is connected energising with outside control circuit, coil windings 4 is produced magnetic field by electric energy, armature 8 produces electromagnetic force and this electromagnetic force held stationary within the scope of stroke 10mm under the effect of magnetic circuit.Dead bolt 1 is under the drive of armature 8 in indentation end cap 2, it is achieved the function that aircraft parachute-opening electric control lock is opened.When outside control circuit power-off, make dead bolt 1 reset under the effect of back-moving spring 6 and stretch out outside end cap 2, it is achieved aircraft parachute-opening electric control lock closes.
Claims (7)
1. a Direct Action Type electric control lock, it is characterized in that: include being sequentially connected with end cap (2), electromagnet housing (3) and iron core (5), coil windings (4) it is provided with between electromagnet housing (3) and iron core (5), described iron core (5) middle part is provided with stroke cavity, stroke cavity and end cap (2) inwall are provided with magnetism-isolating loop (7), armature (8) it is provided with in magnetism-isolating loop (7), the small column inner chamber (12) and big cylindrical groove (13) that are interconnected it is provided with in armature (8), back-moving spring (6) it is provided with between big cylindrical groove (13) and iron core (5) inner bottom part, small column inner chamber (12) is provided with dead bolt (1), dead bolt (1) extend out to end cap (2) outward.
2. Direct Action Type electric control lock according to claim 1, it is characterised in that: the outer surface of described iron core (5) is conical outer wall, and inner surface is cylindrical inner wall.
3. Direct Action Type electric control lock according to claim 2, it is characterised in that: the cone angle of described conical outer wall is 9-10 °.
4. Direct Action Type electric control lock according to claim 1, it is characterised in that: the big cylindrical groove (13) of the bottom of described dead bolt (1) and armature (8) is fastened and connected.
5. Direct Action Type electric control lock according to claim 4, it is characterised in that: described back-moving spring (6) one end and dead bolt (1) ends contact, the other end contacts with the bottom surface cylindrical groove of iron core (5) inner bottom part.
6. Direct Action Type electric control lock according to claim 1, it is characterised in that: described end cap (2) is connected by fixing screw (9) with electromagnet housing (3).
7. Direct Action Type electric control lock according to claim 1, it is characterised in that: described coil windings (4) is connected to binding post (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620166871.5U CN205370161U (en) | 2016-03-04 | 2016-03-04 | Direct action type electric control lock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620166871.5U CN205370161U (en) | 2016-03-04 | 2016-03-04 | Direct action type electric control lock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205370161U true CN205370161U (en) | 2016-07-06 |
Family
ID=56265673
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620166871.5U Expired - Fee Related CN205370161U (en) | 2016-03-04 | 2016-03-04 | Direct action type electric control lock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205370161U (en) |
-
2016
- 2016-03-04 CN CN201620166871.5U patent/CN205370161U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160706 Termination date: 20170304 |