CN211252297U - Safe type angle modulation ware core spare - Google Patents
Safe type angle modulation ware core spare Download PDFInfo
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- CN211252297U CN211252297U CN201921896089.9U CN201921896089U CN211252297U CN 211252297 U CN211252297 U CN 211252297U CN 201921896089 U CN201921896089 U CN 201921896089U CN 211252297 U CN211252297 U CN 211252297U
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Abstract
The utility model discloses a safety angle adjuster core piece, which comprises a tooth cover, a toothless cover, a lower plate spring, an upper spring and a middle rotating shaft, and also comprises a shifting piece, an airplane head, a left tooth piece and a right tooth piece; a rotating shaft hole is formed in the center of the shifting piece, and the shifting piece is sleeved on the middle rotating shaft through the rotating shaft hole; the outer side edge of the shifting sheet is provided with a convex part; a slotted hole is formed in the center of the airplane head in a manner of being matched with the shifting piece, locking convex parts are further respectively arranged on two side edges of the airplane head, and a locking groove is formed between the tail end of each locking convex part and the side edge of the airplane head; the left and right tooth plates are two tooth plates which are arranged on two sides of the aircraft head in an axisymmetric manner, outer teeth are respectively arranged on the outer sides of the left and right tooth plates, the outer side edges of the left and right tooth plates are meshed and connected with the inner side of the toothed cover, and hook-shaped convex parts are respectively arranged on the inner sides of the left and right tooth plates; the utility model aims at providing an effectual safe type angle modulation ware core spare of locking.
Description
Technical Field
The utility model belongs to angle modulation ware core field, concretely relates to safe type angle modulation ware core.
Background
The automobile seat is an important component of an automobile, in the using process of the seat, in order to meet different requirements, the angle of a backrest needs to be properly adjusted, and an important part for adjusting the angle of the seat is a seat angle adjuster. The locking effect of the core part of the existing angle adjuster is poor, and the sliding pool phenomenon can occur due to the fact that the force transmitted to the core part by the external force of the seat is too large.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an effectual safe type angle modulation ware core piece of locking to solve the problem among the background art.
The utility model provides a technical scheme is: a safe angle adjuster core piece comprises a tooth cover, a toothless cover, a lower plate spring, an upper spring, a middle rotating shaft, a shifting piece, an airplane head, a left tooth piece and a right tooth piece;
a rotating shaft hole is formed in the center of the shifting piece, and the shifting piece is sleeved on the middle rotating shaft through the rotating shaft hole; the outer side edge of the shifting sheet is provided with a convex part;
the center of the airplane head is provided with a slotted hole matched with the shifting sheet, the shifting sheet is driven to rotate when the middle rotating shaft rotates, and the slotted hole is pushed by the convex part of the shifting sheet to enable the airplane head to move when the convex part of the shifting sheet rotates; locking convex parts are respectively arranged on two side edges of the airplane head, and a locking groove is formed between the tail ends of the locking convex parts and the side edges of the airplane head;
the aircraft is characterized in that the left and right tooth plates are arranged on two tooth plates on two sides of the aircraft head in an axisymmetric manner, outer teeth are arranged on the outer sides of the left and right tooth plates respectively, the outer side edges of the left and right tooth plates are connected with the inner side of the toothed cover in a meshed manner, hook-shaped convex parts are arranged on the inner sides of the left and right tooth plates respectively, and when the aircraft head moves up and down, the hook-shaped convex parts can be inserted into or separated from the locking grooves.
Preferably, the outer side edge of the locking convex part of the aircraft head is a bevel edge, and the inner side edges of the left and right tooth plates are matched with the outer side edge of the locking convex part.
Preferably, still include static spacing dish, static spacing dish middle part is equipped with and passes the through-hole of countershaft, static spacing dish passes through the bolt fastening be used for compressing tightly in the top of aircraft head, plectrum and left and right teeth piece.
Preferably, the underside of the aircraft head is provided with lightening holes for reducing gravity.
Preferably, an edge wrapping ring is further sleeved between the outer sides of the toothed cover and the non-toothed cover.
Has the advantages that:
1. the utility model discloses a when the cooperation motion of aircraft head, tooth piece and plectrum makes seat external force transmit core spare locking position through the jackshaft, stirs aircraft head through the plectrum, aircraft the hypotenuse on first only locking convex part both sides and control the effect that produces the lever between the tooth piece, the unlocking force does not increase to the security that has improved the seat only lock has improved the safety and the stability of seat greatly.
2. The aircraft head and the left and right tooth sheets are in linear surface contact, so that the locking strength of the core piece is greatly improved.
3. The setting of static spacing dish can be spacing about tooth piece, plectrum and aircraft head move in a confined space for the core spare is more stable.
Drawings
Fig. 1 is a schematic view of the internal structure of the present invention;
FIG. 2 is an exploded view of the present invention;
FIG. 3 is a schematic view of the structure of the pick of the present invention;
fig. 4 is a schematic view of the structure of the aircraft head of the present invention;
fig. 5 is a schematic structural view of the left and right tooth plates of the present invention.
In the figure: 1-a toothed cover, 2-a toothless cover, 3-a lower plate spring, 4-an upper spring, 5-a central rotating shaft, 6-a plectrum, 7-an airplane head, 71-a locking convex part, 8-a left tooth piece and a right tooth piece, 81-a hook-shaped convex part, 9-a static limiting disc and 10-a binding ring.
Detailed Description
The embodiments of the present invention will be further explained with reference to the drawings.
As shown in fig. 1 and 2, the safety recliner core in the embodiment includes a toothed cover 1, a toothless cover 2, a lower plate spring 3, an upper spring 4 and a middle rotating shaft 5, and further includes a pick 6, an aircraft head 7 and left and right toothed sheets 8;
a rotating shaft hole is formed in the center of the shifting piece 6, and the shifting piece 6 is sleeved on the middle rotating shaft 5 through the rotating shaft hole; the outer side edge of the shifting sheet 6 is provided with a convex part;
a slotted hole is formed in the center of the airplane head 7 and matched with the shifting sheet 6, the shifting sheet 6 is driven to rotate when the middle rotating shaft 5 rotates, and the slotted hole is pushed by the convex part of the shifting sheet 6 to enable the airplane head 7 to move when the convex part of the shifting sheet 6 rotates; locking convex parts 71 are respectively arranged on two side edges of the airplane head 7, and a locking groove is formed between the tail ends of the locking convex parts and the side edge of the airplane head 7;
the aircraft head 7 is characterized in that the left tooth piece 8 and the right tooth piece 8 are arranged symmetrically to form two tooth pieces on two sides of the aircraft head 7, outer teeth are arranged on the outer sides of the left tooth piece 8 and the right tooth piece 8 respectively, the outer side edges of the left tooth piece 8 and the right tooth piece 8 are connected with the inner side of the toothed cover 1 in a meshed mode, hook-shaped convex portions 81 are arranged on the inner sides of the left tooth piece 8 and the right tooth piece 8 respectively, and when the aircraft head 7 moves up and down, the hook-shaped convex portions 81 can.
In this embodiment, the outside limit of the locking convex part of aircraft head 7 is the hypotenuse, the inboard side cooperation of controlling tooth piece 8 the outside limit of locking convex part 81 also is the hypotenuse, and the hypotenuse cooperation of locking convex part 71 is controlled the hypotenuse of tooth piece 8, and two straight line faces contact each other effectually has improved the atress ability to the locking intensity of core spare has been improved.
The aircraft is characterized by further comprising a static limiting disc 9, a through hole capable of penetrating through the middle rotating shaft 5 is formed in the middle of the static limiting disc 9, and the static limiting disc 9 is fixed above the aircraft head 7, the shifting piece 6 and the left and right tooth pieces 8 through bolts and used for pressing; the arrangement of the static limiting disc 9 can limit the left and right tooth sheets 8, the shifting sheet 6 and the airplane head 7 to move in a closed space, so that the core component is more stable.
The lower side of the aircraft head 7 is provided with lightening holes 72 for reducing gravity, and a surrounding ring 10 is further sleeved between the outer sides of the toothed cover 1 and the non-toothed cover 2.
In this embodiment, when the utility model is used, the protruding portion drives the inner side of the aircraft head 7 by the rotation of the dial piece 6, so as to control the aircraft head 7 to move up and down, so that the slot hole of the aircraft head 7 is far away from the hook-shaped protruding portion 81 or is spliced with the hook-shaped protruding portion 81, thereby achieving the locking effect; when a passenger sits on the seat, force is transmitted to the interior of the core part through the middle rotating shaft 5, the aircraft head 7 is shifted through the shifting piece 6, a lever effect is generated between the inclined edges of two sides of the locking convex part 71 of the aircraft head 7 and the left and right tooth pieces 8, unlocking force is not increased, and therefore the safety of seat locking is improved, and the safety and the stability of the seat are greatly improved; the aircraft head 7 and the left and right tooth sheets 8 are in linear surface contact, so that the locking strength of the core piece is greatly improved; the arrangement of the static limiting disc 9 can limit the left and right tooth sheets 8, the shifting sheet 6 and the airplane head 7 to move in a closed space, so that the core component is more stable.
For convenience of description, the descriptions of directions such as "up", "down", "left", "right", "front", "back", etc. referred to herein are consistent with the left-right direction of the drawings, but do not limit the structure of the present invention; the above detailed description of the embodiments of the present invention is only for exemplary purposes, and the present invention is not limited to the above detailed description. Any equivalent modifications and substitutions to those skilled in the art are also within the scope of the present invention. Accordingly, variations and modifications in equivalents may be made without departing from the spirit and scope of the invention, which is intended to be covered by the following claims.
Claims (5)
1. The utility model provides a safe type angle modulation ware core spare, is including tooth lid (1), no tooth lid (2), lower leaf spring (3), upper spring (4) and pivot (5), its characterized in that:
the aircraft also comprises a poking sheet (6), an aircraft head (7) and a left tooth sheet and a right tooth sheet (8);
a rotating shaft hole is formed in the center of the shifting piece (6), and the shifting piece (6) is sleeved on the middle rotating shaft (5) through the rotating shaft hole; the outer side edge of the shifting sheet (6) is provided with a convex part;
a slotted hole is formed in the center of the airplane head (7) and matched with the shifting sheet (6), the shifting sheet (6) is driven to rotate when the central rotating shaft (5) rotates, and the slotted hole is pushed to enable the airplane head (7) to move when the convex part of the shifting sheet (6) rotates; locking convex parts (71) are further arranged on two side edges of the airplane head (7), and a locking groove is formed between the tail end of each locking convex part and the side edge of the airplane head (7);
about, teeth piece (8) are axisymmetric setting two teeth pieces of aircraft head (7) both sides, the outside of controlling teeth piece (8) is provided with the external tooth respectively, the outside limit of controlling teeth piece (8) with the inboard meshing that has tooth lid (1) is connected, the inboard of controlling teeth piece (8) is equipped with respectively and colludes type convex part (81), when aircraft head (7) reciprocated, collude type convex part (81) can insert or leave the locked groove.
2. A safety recliner core according to claim 1 wherein:
the outer side edge of the locking convex part of the airplane head (7) is a bevel edge, and the inner side edges of the left tooth piece and the right tooth piece (8) are matched with the outer side edge of the locking convex part (71) and are also bevel edges.
3. A safety recliner core according to claim 1 wherein:
still include static spacing dish (9), static spacing dish (9) middle part is equipped with and passes the through-hole of countershaft (5), static spacing dish (9) are fixed through the bolt be used for compressing tightly aircraft head (7), plectrum (6) and the top of controlling tooth piece (8).
4. A safety recliner core according to any one of claims 1 to 3 wherein:
the lower side of the aircraft head (7) is provided with a lightening hole (72) for reducing gravity.
5. A safety recliner core according to any one of claims 1 to 3 wherein:
an edge wrapping ring (10) is further sleeved between the outer sides of the toothed cover (1) and the toothless cover (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921896089.9U CN211252297U (en) | 2019-11-05 | 2019-11-05 | Safe type angle modulation ware core spare |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921896089.9U CN211252297U (en) | 2019-11-05 | 2019-11-05 | Safe type angle modulation ware core spare |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211252297U true CN211252297U (en) | 2020-08-14 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921896089.9U Active CN211252297U (en) | 2019-11-05 | 2019-11-05 | Safe type angle modulation ware core spare |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211252297U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110758187A (en) * | 2019-11-05 | 2020-02-07 | 景德镇浮梁颢迪汽车座椅内饰件有限公司 | Safe type angle modulation ware core spare |
-
2019
- 2019-11-05 CN CN201921896089.9U patent/CN211252297U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110758187A (en) * | 2019-11-05 | 2020-02-07 | 景德镇浮梁颢迪汽车座椅内饰件有限公司 | Safe type angle modulation ware core spare |
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