CN209133672U - It is compound to cut hinge formula hoop truss deployable antenna mechanism - Google Patents
It is compound to cut hinge formula hoop truss deployable antenna mechanism Download PDFInfo
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- CN209133672U CN209133672U CN201920082888.6U CN201920082888U CN209133672U CN 209133672 U CN209133672 U CN 209133672U CN 201920082888 U CN201920082888 U CN 201920082888U CN 209133672 U CN209133672 U CN 209133672U
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- deployable
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Abstract
Compound hinge formula hoop truss deployable antenna mechanism is cut the utility model discloses a kind of, include the identical deployable mechanism unit of N number of structure, by sharing two upper and lower level node connectors and a middle layer node connector connection between adjacent deployable mechanism unit, multi-panel formula hoop truss mechanism is collectively constituted；Each deployable mechanism unit includes two scissors rods, four connecting rods, four reinforcing rods, four upper and lower level node connectors and two middle layer node connectors, and all revolute pair axis connected on the scissors rod, connecting rod and reinforcing rod in same deployable mechanism unit are parallel；Kinematic pair is revolute pair in overall mechanism, assembling manufacturing good manufacturability, and the structural symmetry with height, by the quantity and the wherein length of rod piece that change deployable mechanism unit, the hoop truss formula space development agency that different scale can be formed, can be used as supporting mechanism and is preferably applied on spaceborne hoop truss formula deployable antenna.
Description
Technical field
The present invention relates to a kind of deployable antenna mechanism, more particularly to a kind of compound cut the deployable day of hinge formula hoop truss
Line mechanism.
Background technique
Space development agency is to refer to be deployed into scheduled or desired structure type from rounding state, and can hold
By a kind of mechanism of specific load, it is widely used on the spacecrafts such as telecommunication satellite platform, space station, aerospace craft, is
One of research hotspot of space industry.With the needs of development and the national defense construction of space technology, various countries are for large space day
The demand of line is further urgent, but due to being limited by the space of space flight apparatus of transport, aerospace mechanism must in launching phase
It must fold up and collapse in radome fairing, being voluntarily deployed into working condition again after spacecraft injection, therefore it is folded
Than and quality etc. be all more crucial design parameter.
Hoop truss deployable antenna, which has, big folds that ratio, quality be smaller, quality does not increase substantially with bore increase
Feature, is the ideal structure form of tens meters Dao up to a hundred meters of space heavy caliber deployable antenna, and such antenna is usually by periphery
Deployable sub-truss and rope net system composition, the deployable sub-truss in periphery are generally polygonized structure, pass through periodicity
Repetition is interconnected to form a closed cyclic structure, and various countries related scientific research personnel go deep into such deployable antenna
Research, and the in-orbit application of success.
Although the research of existing hoop truss formula deployable antenna achieves a series of achievement, there are still such
Mechanism type is less in orbit for antenna, and bore increases the problems such as aft antenna Stiffness is more serious, and some annular truss can
Deployable antenna realizes the raising of antenna mechanism overall stiffness using tensioning zipper, but tensioning zipper is complex, is difficult to control,
Integrally-built reliability is also reduced, these problems will lead to antenna expansion failure, cause huge economic loss.Cause
This, needs to propose that some manufacturing process are good, rigidity is high, folds the deployable antenna mechanism than the function admirables such as big, to meet not
With the demand of space mission.
Summary of the invention
For overcome the deficiencies in the prior art, that the present invention provides a kind of freedom degrees is few, structure is simple, rigidity is higher, easy
Compound in control cuts hinge formula hoop truss deployable antenna mechanism.
To achieve the above object, the present invention is realized according to following technical scheme:
It is a kind of compound to cut hinge formula hoop truss deployable antenna mechanism, it is characterised in that: to open up comprising N number of structure is identical
Opening mechanism unit, wherein N is the positive integer more than or equal to 3, passes through two shared upper and lower levels between adjacent deployable mechanism unit
Node connector and a middle layer node connector connection, collectively constitute multi-panel formula hoop truss mechanism, wherein described can
Unfolding mechanism unit is including in two scissors rods, four connecting rods, four reinforcing rods, four upper and lower level node connectors and two
Interbed node connector；It is connected among two of them scissors rod by revolute pair, in addition four ends pass through revolute pair and upper and lower level section
Point connector connection；Four connecting rod head and the tail pass sequentially through revolute pair connection composition diamond shape frame, are in interposition in diamond shape frame
Two hinge joints set are connect by revolute pair with middle layer node connector, while the middle position of each connecting rod and scissors rod
It is connected at a quarter length by revolute pair；In pairs, end is connected four reinforcing rods by revolute pair, and in addition both ends are logical
Revolute pair is crossed to connect with upper and lower level node connector；Upper and lower level node connector and middle layer node connector all contain two respectively
Two branch fork of a branch fork, upper and lower level node connector and middle layer node connector be all with the plane for crossing bending part it is symmetrical,
It is respectively opened on two branch fork of upper and lower level node connector there are two open slot, two branch of middle layer node connector are pitched and respectively opened
There is an open slot, the open end of the open slot of upper and lower level node connector and middle layer node connector is each provided at the two of branch fork
Free end, the angle between two branch fork upper open slot median planes are (180-360/N) °, two of upper and lower level node connector
The open slot of branch fork inside is used to be inserted into one end of reinforcing rod and is connected by revolute pair, and the open slot in two branch fork outsides is used for
It is inserted into one end of scissors rod and is connected by revolute pair, four upper and lower level node connectors are symmetrically distributed on four vertex；
The open slot of two branch fork of middle layer node connector is for being inserted into two hinge joints in an intermediate position in diamond shape frame
And connected by revolute pair, two middle layer node connectors are symmetrically distributed in the middle position of deployable mechanism unit side
Place.
In above-mentioned technical proposal, connected on the scissors rod, connecting rod and reinforcing rod in the same deployable mechanism unit
All revolute pair axis it is parallel.
In above-mentioned technical proposal, reinforcing rod controls the expansion degree of deployable mechanism unit, adds when two interconnected
When bar is conllinear by force, deployable mechanism unit reaches fully expanded position；After deployable mechanism unit member size determines, pass through
The length for changing reinforcing rod changes the size after deployable mechanism unit is fully deployed, and then changes and whole compound cut hinge formula periphery
Truss deployable antenna mechanism be fully deployed after bore size.
Compared with prior art, the present invention having the following beneficial effects:
1, the configuration of the present invention is simple, contained kinematic pair are revolute pair, and assembling manufacturing craftsmanship is preferable.
2, the present invention has the characteristics that movement is flexible, it is bigger to fold, and overall structure rigidity is higher.
3, the deployable mechanism unit in the present invention and entire compound to cut hinge formula hoop truss deployable antenna mechanism equal
For mechanism with single degree of freedom, a driving is only needed to can be achieved with its whole expansion and collapse to move, expanding performance is good, reliability
It is high.
4, the present invention has the structural symmetry of height, by the quantity and wherein rod piece that change deployable mechanism unit
Length, the hoop truss formula space development agency of different scale can be formed, supporting mechanism is can be used as and be preferably applied to
On spaceborne hoop truss formula deployable antenna.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
Other attached drawings are obtained according to these attached drawings.
Fig. 1 is that the present invention is fully deployed stereoscopic schematic diagram；
Fig. 2 is half expansion stereoscopic schematic diagram of the present invention；
Fig. 3 is the stereoscopic schematic diagram of gathering completely of the invention；
Fig. 4 is that deployable mechanism unit of the invention is fully deployed stereoscopic schematic diagram；
Fig. 5 is that stereoscopic schematic diagram is partly unfolded in deployable mechanism unit of the invention；
Fig. 6 is that deployable mechanism unit of the invention collapses stereoscopic schematic diagram completely；
Fig. 7 is upper and lower level node connector stereoscopic schematic diagram of the invention；
Fig. 8 is middle layer node connector stereoscopic schematic diagram of the invention.
In figure: A: deployable mechanism unit；1: middle layer node connector, 2: reinforcing rod, 3: connecting rod, 4: scissors rod, 5:
Upper and lower level node connector.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.
In the description of the present invention, it is to be understood that, term " radial direction ", " axial direction ", "upper", "lower", "top", "bottom",
The orientation or positional relationship of the instructions such as "inner", "outside" is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of retouching
It states the present invention and simplifies description, rather than the device or element of indication or suggestion meaning must have a particular orientation, with specific
Orientation construction and operation, therefore be not considered as limiting the invention.In the description of the present invention, unless otherwise indicated,
The meaning of " plurality " is two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation " " is set
Set ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
It, can also be indirectly connected through an intermediary to be to be connected directly.It for the ordinary skill in the art, can basis
Concrete condition understands the concrete meaning of above-mentioned term in the present invention.
Fig. 1, Fig. 2 and it is shown in Fig. 3 it is compound cut in hinge formula hoop truss deployable antenna mechanism stereoscopic schematic diagram, wrap
12 deployable mechanism unit A are included, pass through shared two upper and lower level node connectors and one between adjacent deployable mechanism unit
A middle layer node connector connection, collectively constitutes multi-panel formula hoop truss mechanism.
In the stereoscopic schematic diagram of Fig. 4-deployable mechanism unit A shown in fig. 6, deployable mechanism unit A mainly includes
Two 3, four, connecting rod reinforcing rod, 2, four upper and lower level node connectors 5 of scissors rod 4, four and two middle layer node connections
Part 1.Two 4 structures of scissors rod are identical, intermediate to be connected by revolute pair, and in addition four ends pass through revolute pair and upper and lower node layer
Connector 5 connects；Four 3 structures of connecting rod are identical, pass sequentially through revolute pair connection composition diamond shape frame, diamond shape frame from beginning to end
In two hinge joints in an intermediate position connect by revolute pair with middle layer node connector 1, while in each connecting rod 3
Between position connect at a quarter length of scissors rod 4 by revolute pair；Four 2 structures of reinforcing rod are identical, and two-by-two one
Group, end are connected by revolute pair, and in addition both ends are connect by revolute pair with upper and lower level node connector 5；Four upper and lower level sections
Point 5 structure of connector is identical, and the angle between two branch fork upper open slot median planes is 150 °, opening on the inside of two branch forks
One end of mouth slot insertion reinforcing rod 2 is simultaneously connected by revolute pair, and the open slot in two branch fork outsides is inserted into one end of scissors rod 4 simultaneously
It is connected by revolute pair, four upper and lower level node connectors 5 are symmetrically distributed on four vertex of deployable mechanism unit A；
Two 1 structures of middle layer node connector are identical, and the angle between two branch fork upper open slot median planes is 150 °, two
The open slot of branch fork is inserted into two hinge joints in an intermediate position in diamond shape frame and passes through revolute pair and connects, two middle layers
Node connector 1 is symmetrically distributed in the side middle position of deployable mechanism unit A.
In Fig. 4-deployable mechanism unit A shown in fig. 6, the institute that is connected on scissors rod 4, connecting rod 3 and reinforcing rod 2
There is revolute pair axis parallel, and reinforcing rod 2 can control the expansion degree of deployable mechanism unit A, when interconnected two
When a reinforcing rod 2 is conllinear, deployable mechanism unit A reaches fully expanded position, when the scantling of deployable mechanism unit A is true
After fixed, pass through the length for changing reinforcing rod 2, thus it is possible to vary deployable mechanism unit A be fully deployed after size, and then can change
Become the whole compound size for cutting the bore after hinge formula hoop truss deployable antenna mechanism is fully deployed.
Fig. 1-it is shown in Fig. 3 it is compound cut in hinge formula hoop truss deployable antenna mechanism stereoscopic schematic diagram, when entire multiple
When conjunction is cut hinge formula hoop truss deployable antenna mechanism and is fully deployed, it is in Singular position shape state, overall mechanism is degenerated
The structure for being 0 for freedom degree can cancel themselves out the effect of external force, without providing additional driving by the rod piece in structure
Torque, it is whole that there is the preferable rigidity of structure and mechanical property.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by anyone skilled in the art,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with scope of protection of the claims
Subject to.
Claims (3)
1. one kind is compound to cut hinge formula hoop truss deployable antenna mechanism, it is characterised in that: identical deployable comprising N number of structure
Mechanism unit, wherein N is the positive integer more than or equal to 3, passes through two shared upper and lower level sections between adjacent deployable mechanism unit
Point connector and a middle layer node connector connection, collectively constitute multi-panel formula hoop truss mechanism, wherein described can open up
Opening mechanism unit includes two scissors rods, four connecting rods, four reinforcing rods, four upper and lower level node connectors and two centres
Node layer connector；It is connected among two of them scissors rod by revolute pair, in addition four ends pass through revolute pair and upper and lower node layer
Connector connection；Four connecting rods head and the tail pass sequentially through revolute pair connection composition diamond shape frame, in an intermediate position in diamond shape frame
Two hinge joints connect with middle layer node connector by revolute pair, while the middle position of each connecting rod and scissors rod four
It is connected at/mono- length by revolute pair；In pairs, end is connected four reinforcing rods by revolute pair, and in addition both ends pass through
Revolute pair is connect with upper and lower level node connector；There are two upper and lower level node connector and middle layer node connector all contain respectively
Branch fork, two branch fork of upper and lower level node connector and middle layer node connector be all with the plane for crossing bending part it is symmetrical, on
It is respectively opened on two branch fork of lower level node connector there are two open slot, two branch of middle layer node connector are pitched and are respectively provided with
The open end of the open slot of one open slot, upper and lower level node connector and middle layer node connector is each provided at branch is pitched two certainly
By holding, the angle between two branch fork upper open slot median planes is (180-360/N) °, two branch of upper and lower level node connector
The open slot of fork inside is used to be inserted into one end of reinforcing rod and is connected by revolute pair, and the open slot in two branch fork outsides is for inserting
Enter one end of scissors rod and connected by revolute pair, four upper and lower level node connectors are symmetrically distributed on four vertex；In
The open slot of two branch fork of interbed node connector is for being inserted into two hinge joints in an intermediate position in diamond shape frame simultaneously
It is connected by revolute pair, two middle layer node connectors are symmetrically distributed in the middle position of deployable mechanism unit side
Place.
Compound cut hinge formula hoop truss deployable antenna mechanism 2. according to claim 1, it is characterised in that: it is same can
All revolute pair axis connected on scissors rod, connecting rod and reinforcing rod in unfolding mechanism unit are parallel.
3. compound hinge formula hoop truss deployable antenna mechanism is cut according to claim 1, it is characterised in that: reinforcing rod control
The expansion degree of deployable mechanism unit processed, when two reinforcing rods interconnected are conllinear, deployable mechanism unit has been reached
Full expanded position；After deployable mechanism unit member size determines, the length by changing reinforcing rod changes deployable mechanism
Unit be fully deployed after size, and then change whole compound cut after hinge formula hoop truss deployable antenna mechanism is fully deployed
The size of bore.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920082888.6U CN209133672U (en) | 2019-01-18 | 2019-01-18 | It is compound to cut hinge formula hoop truss deployable antenna mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920082888.6U CN209133672U (en) | 2019-01-18 | 2019-01-18 | It is compound to cut hinge formula hoop truss deployable antenna mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN209133672U true CN209133672U (en) | 2019-07-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920082888.6U Withdrawn - After Issue CN209133672U (en) | 2019-01-18 | 2019-01-18 | It is compound to cut hinge formula hoop truss deployable antenna mechanism |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109860974A (en) * | 2019-01-18 | 2019-06-07 | 燕山大学 | It is compound to cut hinge formula hoop truss deployable antenna mechanism |
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2019
- 2019-01-18 CN CN201920082888.6U patent/CN209133672U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109860974A (en) * | 2019-01-18 | 2019-06-07 | 燕山大学 | It is compound to cut hinge formula hoop truss deployable antenna mechanism |
| CN109860974B (en) * | 2019-01-18 | 2023-10-03 | 燕山大学 | Composite shear hinge type perimeter truss expandable antenna mechanism |
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|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20190719 Effective date of abandoning: 20231003 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20190719 Effective date of abandoning: 20231003 |