CN113251064B - Folding pivot means that expandes based on joint bearing - Google Patents
Folding pivot means that expandes based on joint bearing Download PDFInfo
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- CN113251064B CN113251064B CN202110670698.8A CN202110670698A CN113251064B CN 113251064 B CN113251064 B CN 113251064B CN 202110670698 A CN202110670698 A CN 202110670698A CN 113251064 B CN113251064 B CN 113251064B
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- joint bearing
- rotating shaft
- wing
- outer ring
- unfolding
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- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C11/00—Pivots; Pivotal connections
- F16C11/04—Pivotal connections
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Sliding-Contact Bearings (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention discloses a folding and unfolding rotating shaft device based on a joint bearing, which comprises a rotating shaft and the joint bearing; the first end of the rotating shaft is fixedly connected with the machine body; the joint bearing comprises a joint bearing inner ring and a joint bearing outer ring, the joint bearing inner ring is sleeved on the outer wall of the second end of the rotating shaft, and the joint bearing outer ring is connected with the elastic wing. When the missile wing is unfolded and folded, the missile wing rotates around the rotating shaft through the joint bearing, and a part of pneumatic load borne by the missile wing is transmitted to the rotating shaft through the joint bearing; the knuckle bearing has the characteristics that the outer ring can incline and slide relative to the inner ring, so that the load transmitted by the missile wing can be transferred and dispersed to other wing body connecting structures, the load is prevented from being transmitted to the rotating shaft, and the problems that the rotating shaft deforms to cause mechanism clamping stagnation and the missile wing cannot be unfolded and folded smoothly are avoided; the wing folding and unfolding device has the advantages of simple and light structure, miniaturization, strong universality, low cost and high reliability, can be applied to folding and unfolding of wings of various aircrafts such as missiles, unmanned planes and the like, and has wide application range.
Description
Technical Field
The invention relates to the technical field of missile wing folding and unfolding mechanisms, in particular to a folding and unfolding rotating shaft device based on a joint bearing.
Background
The foldable missile wing has the advantages of reducing the size of the missile and the launching device, improving the operational capacity of the missile and the like, and is widely applied to national defense. As an important component of the wing body connecting structure and the missile wing folding and unfolding mechanism, the wing root rotating shaft is required to meet the requirement that the missile wing can flexibly rotate around the wing root rotating shaft while transmitting the missile wing load. For a thin wing type missile wing bearing high wing load, the stress surface of a wing root rotating shaft is small due to the limitation of layout space and wing type thickness, large local deformation can occur when large load is transferred, and then the missile wing cannot flexibly rotate around the rotating shaft, and cannot be smoothly unfolded and folded.
Therefore, it is necessary to develop a folding and unfolding rotating shaft device based on a joint bearing to solve the above problems.
Disclosure of Invention
The invention aims to solve the problems and designs a folding and unfolding rotating shaft device based on a joint bearing.
The invention realizes the purpose through the following technical scheme:
a folding and unfolding rotating shaft device based on a joint bearing comprises:
a rotating shaft; the first end of the rotating shaft is fixedly connected with the machine body;
a knuckle bearing; the joint bearing comprises a joint bearing inner ring and a joint bearing outer ring, the joint bearing inner ring is sleeved on the outer wall of the second end of the rotating shaft, and the joint bearing outer ring is connected with the elastic wings.
Preferably, the missile wing is provided with a through hole, the through hole is perpendicular to the wing surface of the missile wing, the rotating shaft is arranged in the through hole, and the outer ring of the joint bearing is connected with the wall of the through hole.
Preferably, the axis of the through hole is collinear with the axis of the rotating shaft.
Preferably, the inner ring of the joint bearing is in interference fit with the rotating shaft, and the outer ring of the joint bearing is in interference fit with the wall of the through hole.
Preferably, grease is arranged between the joint bearing inner ring and the joint bearing outer ring.
Preferably, the missile wing is placed in the wing box when not deployed, and during deployment, the missile wing deflects into contact with the wing box for load transfer distribution.
The invention has the beneficial effects that:
1. the thin wing type missile wing under high wing load can be rapidly and stably unfolded and folded, and the thin wing type missile wing under high wing load is simple in structure, low in cost and high in reliability;
2. the dimensional rigidity of the rotating shaft can be ensured under the severe load working condition, and the use requirements under more extreme flight conditions are met;
3. the mechanical design is more compact, the structure is more miniaturized, and the assembly, the disassembly and the maintenance are more convenient;
4. the application range is wide, and the wing folding and unfolding device can be applied to folding and unfolding of wings of various aircrafts such as missiles, unmanned planes and the like.
Drawings
FIG. 1 is a schematic diagram of the components of a missile wing folding and unfolding mechanism according to the invention;
fig. 2 is a schematic diagram of the components of the bearing assembly of the present invention.
Wherein, 1-missile wing; 2-a rotating shaft device; 201-a rotating shaft; 202-knuckle bearing; 20201-knuckle bearing inner race; 20202-knuckle bearing outer race; 3-a connecting rod; 4-an actuator cylinder; 5-a slide block.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "inside", "outside", "left", "right", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the present invention are conventionally placed in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be further noted that, unless otherwise explicitly stated or limited, the terms "disposed" and "connected" and the like are to be broadly construed, for example, "connected" may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The following describes in detail embodiments of the present invention with reference to the drawings.
As shown in fig. 1-2, a folding and unfolding rotating shaft 201 device based on a joint bearing 202 comprises:
a rotating shaft 201; the first end of the rotating shaft 201 is fixedly connected to the machine body;
a joint bearing 202; the knuckle bearing 202 comprises a knuckle bearing inner ring 20201 and a knuckle bearing outer ring 20202, the knuckle bearing inner ring 20201 is sleeved on the outer wall of the second end of the rotating shaft 201, a through hole is formed in the missile wing 1 and is perpendicular to the wing surface of the missile wing 1, the rotating shaft 201 is arranged in the through hole, and the knuckle bearing outer ring 20202 is connected with the wall of the through hole. Wherein, the axis of the through hole is collinear with the axis of the rotating shaft 201.
The joint bearing inner ring 20201 is in interference fit with the rotating shaft 201, and the joint bearing outer ring 20202 is in interference fit with the wall of the through hole. By cooling the knuckle bearing 202, the inner surface of the inner ring is in interference fit with the rotating shaft 201 and keeps a static state, and the outer surface of the outer ring is in interference fit with the hole wall of the through hole of the missile wing 1 and rotates along with the missile wing 1. The contact surfaces of the inner ring 20201 and the outer ring 20202 of the knuckle bearing 202 and the outer ring 20201 of the knuckle bearing are spherical surfaces, and grease is filled between the inner ring 20201 of the knuckle bearing and the outer ring 20202 of the knuckle bearing, so that the inner ring and the outer ring can freely slide and incline with each other within the maximum adjustment angle range.
When the missile wing 1 is unfolded and folded, the missile wing 1 rotates around the rotating shaft 201 through the knuckle bearing 202, and a part of the aerodynamic load applied to the missile wing 1 needs to be transmitted to the rotating shaft 201 through the knuckle bearing 202. The knuckle bearing 202 has the characteristic that the outer ring can incline and slide relative to the inner ring, so that the load transmitted by the missile wing 1 can be transferred and dispersed to other wing body connecting structures (such as wing boxes), the load is prevented from being transmitted to the rotating shaft 201, and the problems that the rotating shaft 201 deforms to cause mechanism clamping and the missile wing 1 cannot be unfolded and folded smoothly are avoided. The missile wing 1 is placed in the wing box when not unfolded, and the inner ring 20201 of the joint bearing and the outer ring 20202 of the joint bearing deflect relatively in the unfolding process of the missile wing 1, so that the missile wing 1 deflects to contact with the wing box for load transfer and dispersion.
As shown in fig. 1, a rotating shaft device 2, a connecting rod 3, an actuating cylinder 4 and a sliding block 5 are also shown, wherein the rotating shaft 201 device comprises a rotating shaft 201 and a joint bearing 202.
The technical solution of the present invention is not limited to the limitations of the above specific embodiments, and all technical modifications made according to the technical solution of the present invention fall within the protection scope of the present invention.
Claims (5)
1. A folding and unfolding rotating shaft device based on a joint bearing is characterized by comprising:
a rotating shaft; the first end of the rotating shaft is fixedly connected with the machine body;
a knuckle bearing; the joint bearing comprises a joint bearing inner ring and a joint bearing outer ring, the joint bearing inner ring is sleeved on the outer wall of the second end of the rotating shaft, and the joint bearing outer ring is connected with the elastic wing; the contact surface of the joint bearing inner ring and the joint bearing outer ring is a spherical surface; the missile wing is placed in the wing box when not unfolded, and during the unfolding process of the missile wing, the missile wing deflects to be in contact with the wing box for load transfer and dispersion.
2. The joint bearing based folding and unfolding rotating shaft device as claimed in claim 1, wherein the missile wing is provided with a through hole, the through hole is perpendicular to the wing surface of the missile wing, the rotating shaft is arranged in the through hole, and the outer ring of the joint bearing is connected with the wall of the through hole.
3. The joint bearing based folding and unfolding rotating shaft device according to claim 2, wherein the axis of the through hole is collinear with the axis of the rotating shaft.
4. The joint bearing-based folding and unfolding rotating shaft device according to claim 2, wherein an inner ring of the joint bearing is in interference fit with the rotating shaft, and an outer ring of the joint bearing is in interference fit with the wall of the through hole.
5. The joint bearing based folding and unfolding rotating shaft device according to any one of claims 1 to 4, wherein lubricating grease is arranged between the joint bearing inner ring and the joint bearing outer ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110670698.8A CN113251064B (en) | 2021-06-17 | 2021-06-17 | Folding pivot means that expandes based on joint bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110670698.8A CN113251064B (en) | 2021-06-17 | 2021-06-17 | Folding pivot means that expandes based on joint bearing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113251064A CN113251064A (en) | 2021-08-13 |
| CN113251064B true CN113251064B (en) | 2022-11-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110670698.8A Active CN113251064B (en) | 2021-06-17 | 2021-06-17 | Folding pivot means that expandes based on joint bearing |
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Citations (6)
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|---|---|---|---|---|
| DE10033592A1 (en) * | 2000-07-11 | 2002-02-07 | Daimler Chrysler Ag | Gearshift lever bearing arrangement has vibration damper packet comprising two separate identically designed vibration damper flange bushes plugged with radial pre-tension into bearing eye |
| WO2003004122A1 (en) * | 2001-06-30 | 2003-01-16 | Sinclair Peter | Motion assisting apparatus |
| CN207274957U (en) * | 2017-09-12 | 2018-04-27 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of aerofoil |
| CA3046912A1 (en) * | 2018-09-20 | 2020-03-20 | The Boeing Company | Manufacture and process for inhibiting wear in a latch system |
| CN210707855U (en) * | 2019-09-09 | 2020-06-09 | 湖南航天机电设备与特种材料研究所 | Folding and unfolding mechanism of double-layer wing unmanned aerial vehicle |
| CN111516853A (en) * | 2019-02-01 | 2020-08-11 | 波音公司 | Aircraft, foldable aircraft wing and related methods |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| DE10317258B4 (en) * | 2003-04-14 | 2006-09-07 | Eads Deutschland Gmbh | Adjustment mechanism for a shape-variable wing |
| US8708286B2 (en) * | 2012-06-21 | 2014-04-29 | The Boeing Company | Swing tip assembly rotation joint |
| CN202833603U (en) * | 2012-07-02 | 2013-03-27 | 江西洪都航空工业集团有限责任公司 | Pivot structure for longitudinally folding missile wing |
| CN102767560B (en) * | 2012-07-02 | 2015-02-25 | 江西洪都航空工业集团有限责任公司 | Pivot structure with longitudinally-foldable missile swing |
| CN104976926B (en) * | 2015-07-15 | 2017-07-21 | 江西洪都航空工业集团有限责任公司 | A kind of unilateral aerofoil fold mechanism of missile wing |
| CN206889470U (en) * | 2017-06-29 | 2018-01-16 | 中国工程物理研究院总体工程研究所 | It is a kind of for protective cover without the passive arming mechanism of pin type hinge |
| CN110588953A (en) * | 2019-10-25 | 2019-12-20 | 中国工程物理研究院总体工程研究所 | Folding wing mechanism |
-
2021
- 2021-06-17 CN CN202110670698.8A patent/CN113251064B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10033592A1 (en) * | 2000-07-11 | 2002-02-07 | Daimler Chrysler Ag | Gearshift lever bearing arrangement has vibration damper packet comprising two separate identically designed vibration damper flange bushes plugged with radial pre-tension into bearing eye |
| WO2003004122A1 (en) * | 2001-06-30 | 2003-01-16 | Sinclair Peter | Motion assisting apparatus |
| CN207274957U (en) * | 2017-09-12 | 2018-04-27 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of aerofoil |
| CA3046912A1 (en) * | 2018-09-20 | 2020-03-20 | The Boeing Company | Manufacture and process for inhibiting wear in a latch system |
| CN111516853A (en) * | 2019-02-01 | 2020-08-11 | 波音公司 | Aircraft, foldable aircraft wing and related methods |
| CN210707855U (en) * | 2019-09-09 | 2020-06-09 | 湖南航天机电设备与特种材料研究所 | Folding and unfolding mechanism of double-layer wing unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| CN113251064A (en) | 2021-08-13 |
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