CN202628736U - Elliptical head non-lug anchor self-locking nut - Google Patents
Elliptical head non-lug anchor self-locking nut Download PDFInfo
- Publication number
- CN202628736U CN202628736U CN 201120393819 CN201120393819U CN202628736U CN 202628736 U CN202628736 U CN 202628736U CN 201120393819 CN201120393819 CN 201120393819 CN 201120393819 U CN201120393819 U CN 201120393819U CN 202628736 U CN202628736 U CN 202628736U
- Authority
- CN
- China
- Prior art keywords
- earless
- supporting plate
- head
- oval head
- lock nut
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Abstract
The utility model discloses an elliptical head non-lug anchor self-locking nut connected with an airplane structural member. The head of the self-locking nut is an elliptic head, the elliptic head is matched with an elliptic nest of the structural member; and the internal of the self-locking nut is provided with a weakening region, which forms a bump under the effect of pulling force, finally realizing connection of the elliptical head non-lug anchor self-locking nut and the structural member.
Description
Technical field
The utility model relates to aircraft structure and connects the plate nut of using plate nut, especially aircraft flap etc. to repeat the application of dismounting place.
Background technique
At present, traditional plate nut has three rivet holes, utilizes rivet that it is riveted on the aircraft structure, and most applications needs two countersinks, thereby in order to plate nut and construct are realized stop.The tradition plate nut has three to limit to greatly, and the one, the space of using there is certain requirement, general little place, space can't be used; The 2nd, because the nail hole number is more, riveted joint efficient is low, and reduces the fatigue strength of structure easily; The 3rd, can not realize blind riveting.
Summary of the invention
For overcome traditional plate nut spatial requirement, can not blind riveting, cause the deficiency of aspects such as structural strength reduction; The utility model provides a kind of oval head earless supporting plate self-lock nut; This supporting plate self-lock nut not only takes up room little (only needing a mounting hole); Can realize automatic blind riveting, and, improve the fatigue strength of structure because the nail hole number is few.
The utility model patent is to overcome the technological scheme that deficiency adopted that exists in the existing technology problem to be:
The utility model solves the technological scheme that its technical problem adopted: the head at oval head earless supporting plate self-lock nut forms oval head; And this oval head head is immersed oneself in nest; When being connected with aircraft structure, the nest of immersing oneself in of nut head cooperates with the oval nest of aircraft structure; There is atenuator region at endoporus place at oval head earless supporting plate self-lock nut, and this weakening region forms bulge under tension, and bulge is connected oval head earless supporting plate self-lock nut with aircraft structure; The afterbody of nut has internal thread, and internal thread has auto-lock function, can prevent that bolt from coming off when being shaken, thereby improves the Security that is installed in the link on the aircraft structure.
The effect of this patent:
The beneficial effect of the utility model is when can realize with construct, only to need mounting hole of system, conserve space, raising structural strength; Accomplish connection from single face, simple to operate, help increasing work efficiency.
Description of drawings
Below in conjunction with accompanying drawing and instance the utility model is further specified.
Fig. 1 is the utility model oval head earless supporting plate self-lock nut plan view; Fig. 2 is the utility model oval head earless supporting plate self-lock nut sectional view; Fig. 3 is the sectional view after the utility model oval head earless supporting plate self-lock nut and aircraft structure are installed;
Fig. 4 is the afterbody view (from latching segment) of the utility model oval head earless supporting plate self-lock nut;
Description of reference numerals: structural member 1, oval head earless supporting plate self-lock nut 2, link 3, bolt 4, oval head 5, weakening region 6, locking zone 7, oval head major axis 8 is from latching segment 9.
Embodiment
The plan view of the utility model oval head earless supporting plate self-lock nut has been shown in Fig. 1, has shown the shape of head, oval head 5 is to be used for stop;
The sectional view of the utility model oval head earless supporting plate self-lock nut has been shown in Fig. 2, and weakening region 6 is used for bulge and is shaped, and locking zone 7 realization bolts 4 are threaded with oval head earless supporting plate self-lock nut 2; The working state of the utility model oval head earless supporting plate self-lock nut has been shown in Fig. 3; Oval head earless supporting plate self-lock nut 2 is put into the oval nest of aircraft structure 1; Oval head earless supporting plate self-lock nut 2 forms bulge with structural member 1 under tension; Realized the fixing of oval head earless supporting plate self-lock nut 2 and structural member 1, realized being connected and fixing of oval head earless supporting plate self-lock nut 2 and structural member 1, link 3 has been placed on the structural member 1; Bolt 4 is screwed into the earless supporting plate self-lock nut, has realized being connected of aircraft link and aircraft structure.
Claims (2)
1. oval head earless supporting plate self-lock nut, this self-locking nut is used for the connection of aircraft structure, it is characterized in that: the head of said oval head earless supporting plate self-lock nut forms oval head, cooperates with aircraft structure; There is weakening region at the endoporus place of nut, utilizes the bulge of nut weakening region be shaped to realize being connected of oval head earless supporting plate self-lock nut and aircraft structure; The afterbody of nut has internal thread, and internal thread has auto-lock function.
2. a kind of oval head earless supporting plate self-lock nut according to claim 1; It is characterized in that: the nest of immersing oneself in of the oval head of said oval head earless supporting plate self-lock nut cooperates with the oval nest of aircraft structure; The weakening region at said oval head earless supporting plate self-lock nut endoporus place forms the bulge form under tension, bulge is connected oval head earless supporting plate self-lock nut with aircraft structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120393819 CN202628736U (en) | 2011-10-09 | 2011-10-09 | Elliptical head non-lug anchor self-locking nut |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120393819 CN202628736U (en) | 2011-10-09 | 2011-10-09 | Elliptical head non-lug anchor self-locking nut |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202628736U true CN202628736U (en) | 2012-12-26 |
Family
ID=47381941
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120393819 Expired - Lifetime CN202628736U (en) | 2011-10-09 | 2011-10-09 | Elliptical head non-lug anchor self-locking nut |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202628736U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109185311A (en) * | 2018-10-30 | 2019-01-11 | 贵州航瑞科技有限公司 | Titanium alloy tail portion seals earless plate nut and its processing method |
| CN109210065A (en) * | 2018-10-30 | 2019-01-15 | 贵州航瑞科技有限公司 | Titanium alloy earless plate nut and its processing method |
-
2011
- 2011-10-09 CN CN 201120393819 patent/CN202628736U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109185311A (en) * | 2018-10-30 | 2019-01-11 | 贵州航瑞科技有限公司 | Titanium alloy tail portion seals earless plate nut and its processing method |
| CN109210065A (en) * | 2018-10-30 | 2019-01-15 | 贵州航瑞科技有限公司 | Titanium alloy earless plate nut and its processing method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121226 |