CN110510097B - Large-scale dabber structure elastic support ball pivot connected node - Google Patents
Large-scale dabber structure elastic support ball pivot connected node Download PDFInfo
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- CN110510097B CN110510097B CN201910791129.1A CN201910791129A CN110510097B CN 110510097 B CN110510097 B CN 110510097B CN 201910791129 A CN201910791129 A CN 201910791129A CN 110510097 B CN110510097 B CN 110510097B
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- node
- bearing
- mandrel
- truss
- hub
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/08—Framework construction
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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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
- F16C11/06—Ball-joints; Other joints having more than one degree of angular freedom, i.e. universal joints
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Joining Of Building Structures In Genera (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention discloses an elastic supporting spherical hinge connecting node of a large mandrel structure, which relates to the technical field of composite material structures and comprises the following components: the mandrel truss structure comprises a mandrel truss top end node, a hub shaft end node, a hub plate, a bearing frame, a pressure-bearing ball socket and a limiting cover plate; the end part of the hub shaft end node is provided with a boss bearing surface, the hub disc and the bearing frame are connected with the boss bearing surface, the bearing ball socket is connected with the bearing frame, and the mandrel truss top end node and the limiting cover plate are connected with the bearing ball socket; the top end node of the mandrel truss comprises a node main body, a threaded sleeve insert and a bolt spherical hinge; the node main body is in a triangular pyramid structure, and a three-leg sleeve is extended outwards from the bottom edge and is used for connecting the CFRP pipe truss; the screw end of the bolt spherical hinge is connected with the swivel nut insert, the ball end is connected with the pressure-bearing ball socket, and the swivel nut insert is embedded into the joint main body. The invention can realize the complex connection of the composite material structure of the mandrel, can bear large axial pressure, release bending moment, ensure limited rotation, clear force transmission path, clear movement limit, light weight, simple manufacture and reliable assembly and connection.
Description
Technical Field
The invention relates to the technical field of composite material structures, in particular to an elastic supporting spherical hinge connecting node of a large mandrel structure.
Background
The composite material has the advantages of light weight, high rigidity, vibration resistance, fatigue resistance and the like, while the thin-wall circular tube and the truss structure formed by the thin-wall circular tube have the characteristics of large scale, light weight, high rigidity and the like, but the connection between the truss chord member and the web member and the connection between the truss members are always the technical difficulties in the field of composite material structural engineering due to geometrical, mechanical and process limitations.
Rainer Sch tze & Hans Christian Goetting, entitled "carbon fiber-Based Structural Elements used in the Truss Structures of the Zeppelin NT and Future Applications of Active Structures" (3rd International air front Convention and inhibition, 2000, Paper A-25), describes the combined connection between two longitudinal aluminum alloy trusses of Zeppelin NT Airship keel and two circular tube CFRP triangularly braced trusses.
Rainer Schu tze entitled "light weight carbon fiber rods and truss structures" (Materials & Design,1997,18 (4/6): 231) describes a foam sandwich tube composite truss and details a composite node Design and forming process, but the forming process is very complicated, resulting in unreliable stress and low load bearing.
Chinese patent CN201910275705.7, a large-scale semi-rigid airship, discloses a semi-rigid airship mainly composed of a tension integral keel, whose keel mandrel is a continuous contact pressure bearing member, and is formed by hinging a multi-section hub shaft and a mandrel truss, the hinging can release a bidirectional bending moment and bear a smaller limit torque, and mainly bear a larger pressure and a smaller rotation, however, the patent does not give a specific type and connection.
Therefore, those skilled in the art are dedicated to develop a large mandrel structure elastic support spherical hinge connection node, which has the advantages of simple manufacture, reasonable stress and force transmission, and simple and reliable connection, so as to solve the problems of complex connection configuration, difficult manufacture and small bearing capacity of a composite material structure in the prior art.
Disclosure of Invention
In view of the above defects in the prior art, the technical problem to be solved by the present invention is that the prior art has the problems of complex connecting configuration, difficult manufacturing and small bearing capacity of the composite material structure.
In order to achieve the above object, the present invention provides an elastic support spherical hinge connection node of a large mandrel structure, comprising: the mandrel truss structure comprises a mandrel truss top end node, a hub shaft end node, a hub plate, a bearing frame, a pressure-bearing ball socket and a limiting cover plate;
the end part of the hub shaft end node is provided with a boss bearing surface, the hub disc is provided with an excircle connected with the boss bearing surface, the bearing frame is provided with an inner circle connected with the boss bearing surface, the bearing ball socket is connected with the bearing frame, the top end node of the mandrel truss is connected with the bearing ball socket, and the limiting cover plate is connected with the bearing ball socket;
the top end node of the mandrel truss comprises a node main body, a swivel nut insert and a bolt spherical hinge; the node main body is in a triangular pyramid structure, a hexagonal prism central body is arranged at the top end of the node main body, and three edges of the node main body are connected to the hexagonal prism central body in an intersecting manner; the bottom edge of the node main body is in a regular triangle shape, a three-leg sleeve extends outwards from the bottom edge, and the three-leg sleeve is used for connecting three chord tubes of the CFRP tube truss; the screw end of the bolt spherical hinge is connected with the swivel nut insert, the ball end of the bolt spherical hinge is connected with the pressure-bearing ball socket, and the swivel nut insert is embedded into the hexagonal prism central body.
Furthermore, the outer surface of the three-leg sleeve is provided with vertical uniform grooves, the three-leg sleeve is connected with the three chord tubes in a sleeved mode in a cementing mode, and the cementing sections of the chord tubes are locally thickened.
Furthermore, radial pull rods are uniformly arranged in the circumferential direction of the hub plate and connected with the hub plate.
Furthermore, the pressure-bearing ball socket is disc-shaped, the periphery of the pressure-bearing ball socket is a circular ring plane plate, the center of the pressure-bearing ball socket is a concave spherical crown shell, and the inner pressure-bearing surface is sputtered by MoS 2.
Furthermore, the bearing frame comprises two circular plates which are oppositely arranged in parallel, rib plates are uniformly arranged between the two circular plates in the circumferential direction to be connected, the rib plates are perpendicular to the circular plates, and the number of the rib plates is more than 6.
Furthermore, the limiting cover plate is formed by splicing two symmetrical parts, the outer ring is circular, and the middle part is hexagonal.
Furthermore, the connecting surfaces of the hub shaft end node, the hub disc and the bearing frame are in clearance fit.
Further, the ball surface of the bolt ball hinge is sputtered by MoS 2.
Further, the hub shaft end node and the limiting cover plate are made of CFRP composite materials, the bearing frame, the bearing ball socket, the bolt ball hinge and the turnbuckle insert are made of titanium alloy, and the node main body, the hexagonal prism central body, the three-leg sleeve and the hub plate are made of aluminum alloy; the joint main body, the hexagonal prism central body, the three-leg sleeve, the bearing frame and the pressure-bearing ball socket are integrally formed.
Further, the radial tie rod is made of a CFRP composite material.
The invention can realize complex connection of large-scale elastic support mandrel composite material structures, can bear large axial pressure, release bending moment, ensure limited rotation, has clear force transmission path, clear motion limit, light weight, simple manufacture and reliable assembly and connection, and can be applied to large-scale aviation aircraft structures, such as airships, unmanned aerial vehicles and the like.
The conception, the specific structure and the technical effects of the present invention will be further described with reference to the accompanying drawings to fully understand the objects, the features and the effects of the present invention.
Drawings
FIG. 1 is an exploded view of a large mandrel structure spring-loaded ball-and-socket joint in an elevated elevation in accordance with a preferred embodiment of the present invention;
FIG. 2 is a three-dimensional exploded view of a large mandrel structure elastic support ball-and-socket joint according to a preferred embodiment of the present invention;
FIG. 3 is a cross-sectional view of a large mandrel structure spring-loaded ball-and-socket joint according to a preferred embodiment of the present invention;
figure 4 is a three-dimensional exploded view of a mandrel truss top node according to a preferred embodiment of the present invention.
The structure comprises a 1-mandrel truss top end node, a 101-node main body, a 102-thread insert, a 103-bolt ball hinge, a 104-CFRP pipe truss, a 105-tripod sleeve, a 106-hexagonal prism central body, a 2-hub shaft end node, a 21-boss bearing surface, a 3-hub plate, a 4-bearing frame, a 5-bearing ball socket, a 6-limiting cover plate and a 7-radial pull rod.
Detailed Description
The technical contents of the preferred embodiments of the present invention will be more clearly and easily understood by referring to the drawings attached to the specification. The present invention may be embodied in many different forms of embodiments and the scope of the invention is not limited to the embodiments set forth herein.
In the drawings, elements that are structurally identical are represented by like reference numerals, and elements that are structurally or functionally similar in each instance are represented by like reference numerals. The size and thickness of each component shown in the drawings are arbitrarily illustrated, and the present invention is not limited to the size and thickness of each component. The thickness of the components may be exaggerated where appropriate in the figures to improve clarity.
As shown in fig. 1, fig. 2 and fig. 3, the elastic support ball joint connection node of the large mandrel structure in the embodiment comprises: the mandrel truss structure comprises a mandrel truss top end node 1, a hub shaft end node 2, a hub plate 3, a bearing frame 4, a pressure-bearing ball socket 5 and a limiting cover plate 6. The end of the hub shaft end node 2 is provided with a boss bearing surface 21, the hub plate 3 is provided with an excircle connecting boss bearing surface 21, the bearing frame 4 is provided with an inner circle connecting boss bearing surface 21, the bearing ball socket 5 is connected with the bearing frame 4, the mandrel truss top end node 1 is connected with the bearing ball socket 5, and the limiting cover plate 6 is connected with the bearing ball socket 5. The connecting surfaces of the hub shaft end node 2, the hub plate 3 and the bearing frame 4 are in clearance fit.
As shown in fig. 4, mandrel truss top end node 1 includes a node body 101, a thread insert 102, and a bolt ball hinge 103; the node main body 101 is in a triangular pyramid structure, a hexagonal prism central body 106 is arranged at the top end of the node main body 101, and three edges of the node main body 101 are connected to the hexagonal prism central body 106 in an intersecting manner; the bottom edge of the node main body 101 is in a regular triangle shape, and a three-leg sleeve 105 is extended out from the bottom edge and is used for connecting three chord tubes of the CFRP tube truss 104; the screw end of the bolt spherical hinge 103 is connected with the threaded sleeve insert 102, the ball end of the bolt spherical hinge 103 is connected with the pressure-bearing ball socket 5, and the threaded sleeve insert 102 is embedded into the hexagonal prism central body 106. The spherical surface of the spherical end of the bolt spherical hinge 103 is sputtered by MoS 2.
The outer surface of the three-leg sleeve 105 is provided with vertical uniform grooves which are obtained by milling; the three-leg sleeve 105 is sleeved in the three chord tubes connected with the CFRP tube truss 104, the connection mode is cementing, and preferably, the cementing part of the chord tubes can be locally thickened to achieve a more stable cementing effect.
The pressure-bearing ball socket 5 is disc-shaped, the periphery of the pressure-bearing ball socket is a circular ring plane plate, the center of the pressure-bearing ball socket is a concave spherical crown shell, and MoS2 sputtering processing is carried out on an inner pressure-bearing surface.
The limiting cover plate 6 is formed by splicing two symmetrical parts, the outer ring is circular, and the middle part is hexagonal.
The hub shaft end node 2, the limiting cover plate 6 and the radial pull rod 7 are all made of CFRP high-performance composite materials, the bearing frame 4, the bearing ball socket 5, the bolt ball hinge 103 and the thread insert 102 are all made of high-strength light titanium alloy, and the node main body 101, the three-leg sleeve 105 and the hub 3 are all made of high-strength light aluminum alloy.
The node main body 101, the hexagonal prism central body 106, the three-leg sleeve 105, the bearing frame 4 and the pressure-bearing ball socket 5 are integrally processed and formed.
The structure size and the process design of the invention can be determined according to actual requirements. The composite material thin-walled tube and the carbon fiber model, the resin model, the layering design, the forming process design and the like adopted by the connection of the composite material thin-walled tube can be determined according to actual requirements.
The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concept. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (10)
1. The utility model provides a large-scale dabber structure elastic support ball pivot connected node which characterized in that includes:
the mandrel truss structure comprises a mandrel truss top end node, a hub shaft end node, a hub plate, a bearing frame, a pressure-bearing ball socket and a limiting cover plate;
the end part of the hub shaft end node is provided with a boss bearing surface, the hub disc is provided with an excircle connected with the boss bearing surface, the bearing frame is provided with an inner circle connected with the boss bearing surface, the bearing ball socket is connected with the bearing frame, the top end node of the mandrel truss is connected with the bearing ball socket, and the limiting cover plate is connected with the bearing ball socket;
the top end node of the mandrel truss comprises a node main body, a threaded sleeve insert and a bolt spherical hinge; the node main body is in a triangular pyramid structure, a hexagonal prism central body is arranged at the top end of the node main body, and three edges of the node main body are connected to the hexagonal prism central body in an intersecting manner; the bottom edge of the node main body is in a regular triangle shape, a three-leg sleeve extends outwards from the bottom edge, and the three-leg sleeve is used for connecting three chord tubes of the CFRP tube truss; the screw end of the bolt spherical hinge is connected with the swivel nut insert, the ball end of the bolt spherical hinge is connected with the pressure-bearing ball socket, and the swivel nut insert is embedded into the hexagonal prism central body.
2. The large mandrel structure elastic support spherical hinge connection node according to claim 1, wherein a vertical uniform groove is formed in the outer surface of the three-leg sleeve, the three-leg sleeve is connected with the three chord tubes in a sleeved mode in a cementing mode, and cemented sections of the chord tubes are locally thickened.
3. The large mandrel structure elastic support ball and socket joint as recited in claim 1, wherein said hub has radial tie bars uniformly arranged in a circumferential direction, said radial tie bars being connected to said hub.
4. The large mandrel structure elastic support ball and socket joint as recited in claim 1 wherein said bearing ball socket is a disc with a circular ring flat plate at the periphery and a concave spherical crown shell at the center, and the inner bearing surface is sputtered with MoS 2.
5. The large mandrel structure elastic support spherical hinge connection node as claimed in claim 1, wherein the carrier comprises two parallel ring plates which are arranged oppositely, rib plates are uniformly arranged between the two ring plates along the circumferential direction for connection, the rib plates are perpendicular to the ring plates, and the number of the rib plates is greater than 6.
6. The large mandrel structure elastic support ball and socket joint as defined in claim 1, wherein said limiting cover plate is made by symmetrically splicing two parts, the outer ring is circular and the middle part is hexagonal.
7. The large mandrel structure elastic support spherical hinge connection node as claimed in claim 1, wherein the connection surfaces of the hub shaft end node, the hub plate and the bearing frame are in clearance fit.
8. The large mandrel structure elastic support ball joint according to claim 1, wherein the spherical surface of said bolt ball joint is sputtered by MoS 2.
9. The large mandrel structure elastic support ball hinge connection node according to claim 1, wherein said hub shaft end node, said retainer cover plate are made of CFRP composite material, said carrier, said bearing ball socket, said bolt ball hinge, said swivel insert are made of titanium alloy, said node body, said hexagonal prism central body, said tripod sleeve, said hub plate are made of aluminum alloy; the joint main body, the hexagonal prism central body, the three-leg sleeve, the bearing frame and the pressure-bearing ball socket are integrally formed.
10. A large mandrel structure elastic support ball and socket joint as defined in claim 3 wherein said radial tie rods are made of CFRP composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910791129.1A CN110510097B (en) | 2019-08-26 | 2019-08-26 | Large-scale dabber structure elastic support ball pivot connected node |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910791129.1A CN110510097B (en) | 2019-08-26 | 2019-08-26 | Large-scale dabber structure elastic support ball pivot connected node |
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| Publication Number | Publication Date |
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| CN110510097A CN110510097A (en) | 2019-11-29 |
| CN110510097B true CN110510097B (en) | 2022-08-26 |
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| CN201910791129.1A Active CN110510097B (en) | 2019-08-26 | 2019-08-26 | Large-scale dabber structure elastic support ball pivot connected node |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB233021A (en) * | 1924-01-26 | 1925-04-27 | Airship Guarantee Co Ltd | Improvements in or relating to the framework of rigid airships |
| CN1172053A (en) * | 1996-06-10 | 1998-02-04 | 汉密尔顿飞艇有限公司 | Airship |
| CN103711640A (en) * | 2012-09-28 | 2014-04-09 | 张向增 | Horizontal axis wind generating set blade and blade shank segment truss structure and manufacturing method |
| CN103968209A (en) * | 2014-05-20 | 2014-08-06 | 上海交通大学 | Active node for changing octahedral truss unit into geometric truss |
| CN109969373A (en) * | 2019-04-08 | 2019-07-05 | 上海交通大学 | A kind of compression bar contact-type tension integral structure and integrated and tension force applying method |
| CN110040234A (en) * | 2019-04-08 | 2019-07-23 | 上海交通大学 | A kind of spliced triangular truss of large scale stiffening ring |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8973865B2 (en) * | 2010-08-10 | 2015-03-10 | IREL Solutions Group Ltd. | Tri-hull dirigible airship |
-
2019
- 2019-08-26 CN CN201910791129.1A patent/CN110510097B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB233021A (en) * | 1924-01-26 | 1925-04-27 | Airship Guarantee Co Ltd | Improvements in or relating to the framework of rigid airships |
| CN1172053A (en) * | 1996-06-10 | 1998-02-04 | 汉密尔顿飞艇有限公司 | Airship |
| CN103711640A (en) * | 2012-09-28 | 2014-04-09 | 张向增 | Horizontal axis wind generating set blade and blade shank segment truss structure and manufacturing method |
| CN103968209A (en) * | 2014-05-20 | 2014-08-06 | 上海交通大学 | Active node for changing octahedral truss unit into geometric truss |
| CN109969373A (en) * | 2019-04-08 | 2019-07-05 | 上海交通大学 | A kind of compression bar contact-type tension integral structure and integrated and tension force applying method |
| CN110040234A (en) * | 2019-04-08 | 2019-07-23 | 上海交通大学 | A kind of spliced triangular truss of large scale stiffening ring |
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| Publication number | Publication date |
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| CN110510097A (en) | 2019-11-29 |
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