CN209133672U - Composite scissor hinged perimeter truss deployable antenna mechanism - Google Patents

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

Composite scissor hinged perimeter truss deployable antenna mechanism

technical field

The invention relates to a deployable antenna mechanism, in particular to a composite scissor hinge type peripheral truss deployable antenna mechanism.

Background technique

A space deployable mechanism refers to a type of mechanism that can be deployed from a folded state to a predetermined or desired structural form and can withstand a specific load. one of the research hotspots. With the development of space technology and the needs of national defense construction, the demand for large space antennas in various countries is more and more urgent. However, due to the space limitation of space vehicles, the space agency must be folded and folded in the fairing during the launch phase. The device enters the orbit and then unfolds to the working state by itself, so its folding ratio and quality are the key design parameters.

The surrounding truss deployable antenna has the characteristics of large folding ratio, small mass, and the mass does not increase greatly with the increase of the aperture. It consists of a peripheral deployable support truss and a cable net system. The peripheral deployable support truss is generally a polygonal structure. It forms a closed ring structure through periodic repeated interconnection. Relevant researchers from various countries have carried out in-depth research on this type of deployable antenna. research and successful in-orbit application.

Although a series of achievements have been made in the research on the existing peripheral truss-type deployable antennas, there are still problems such as fewer types of such antennas operating in orbit, and the antenna stiffness decreases more seriously after the diameter increases. Some annular truss deployable antennas The overall stiffness of the antenna mechanism is improved by using the tensioning zipper, but the tensioning zipper is complicated and difficult to control, and also reduces the reliability of the overall structure. All these problems will lead to the failure of the antenna deployment and cause huge economic losses. Therefore, it is urgent to propose some deployable antenna mechanisms with good manufacturing process, high stiffness, and large folding ratio to meet the needs of different space missions.

SUMMARY OF THE INVENTION

In order to overcome the deficiencies of the prior art, the present invention provides a composite scissor hinge type peripheral truss deployable antenna mechanism with few degrees of freedom, simple structure, high rigidity and easy control.

To achieve the above object, the present invention is realized according to the following technical solutions:

A composite scissor hinge type peripheral truss deployable antenna mechanism is characterized in that: it includes N deployable mechanism units with the same structure, wherein N is a positive integer greater than or equal to 3, and adjacent deployable mechanism units pass through the shared two The upper and lower layer node connectors and one middle layer node connector are connected to form a multi-faceted peripheral truss mechanism, wherein the deployable mechanism unit includes two scissor rods, four connecting rods, four reinforcing rods, four upper and lower Layer node connectors and two intermediate layer node connectors; two of the scissor bars are connected by a rotating pair in the middle, and the other four ends are connected with the upper and lower node connectors by a rotating pair; the head and tail of the four connecting rods are connected by a rotating pair in turn. Diamond-shaped frame, the two hinge points in the middle of the diamond-shaped frame are connected with the middle layer node connecting piece through the rotating pair, and the middle position of each connecting rod is connected with the quarter length of the scissor rod through the rotating pair; four reinforced The rods are set in two groups, the ends are connected by the rotating pair, and the other two ends are connected with the upper and lower node connectors through the rotating pair; the upper and lower node connectors and the middle layer node connectors respectively contain two forks, and the upper and lower nodes are connected The two forks of the joint piece and the middle layer node connecting piece are symmetrical with the plane at the bending point, the two forks of the upper and lower node connecting piece Each fork is provided with an opening groove, the open ends of the open grooves of the upper and lower node connecting pieces and the middle node connecting piece are all set at the two free ends of the forks, and the clamps between the central surfaces of the opening grooves on the two forks are provided. The angle is (180-360/N)°, the opening grooves on the inside of the two forks of the upper and lower node connectors are used to insert one end of the reinforcing rod and are connected by a rotating pair, and the opening grooves on the outside of the two forks are used for inserting shears One end of the fork rod is connected by a rotating pair, and the four upper and lower node connectors are symmetrically distributed on the four vertices; the opening slots of the two forks of the middle node connector are used to insert the two middle positions in the diamond frame. There are two hinge points and are connected by a rotating pair, and the two intermediate layer node connecting pieces are symmetrically distributed at the middle position of the side of the deployable mechanism unit.

In the above technical solution, all the pivot axes connected to the scissor rod, the connecting rod and the reinforcing rod in the same deployable mechanism unit are parallel.

In the above technical solution, the reinforcing rod controls the degree of deployment of the deployable mechanism unit. When the two interconnected reinforcing rods are collinear, the deployable mechanism unit reaches the fully deployed position; The length of the rod changes the size of the fully-deployed unit of the deployable mechanism, which in turn changes the size of the fully-deployed caliber of the integral composite scissor hinged peripheral truss deployable antenna mechanism.

Compared with the prior art, the present invention has the following beneficial effects:

1. The structure of the present invention is simple, the moving pairs included are all rotating pairs, and the assembly and manufacturing process is good.

2. The present invention has the characteristics of flexible movement, relatively large folding, and high overall structural rigidity.

3. The deployable mechanism unit and the entire composite scissor hinge type peripheral truss deployable antenna mechanism in the present invention are all single-degree-of-freedom mechanisms, and only one drive can realize the overall deployment and retraction movement, with good deployment performance and reliability. high.

4. The present invention has a high degree of structural symmetry. By changing the number of deployable mechanism units and the length of the rods, peripheral truss-type space deployable mechanisms of different scales can be formed, which can be better used as a support mechanism for spaceborne vehicles. On the perimeter truss-type deployable antenna.

Description of drawings

In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention, and for those of ordinary skill in the art, other drawings can also be obtained from these drawings without creative effort.

Fig. 1 is the fully expanded three-dimensional schematic diagram of the present invention;

Fig. 2 is the semi-expanded perspective schematic diagram of the present invention;

Fig. 3 is the three-dimensional schematic diagram of the present invention fully folded;

FIG. 4 is a perspective schematic view of the fully unfolded mechanism unit of the present invention;

FIG. 5 is a perspective schematic diagram of a semi-deployed mechanism unit of the present invention;

6 is a perspective schematic view of the fully folded deployable mechanism unit of the present invention;

Fig. 7 is the perspective schematic diagram of the upper and lower node connectors of the present invention;

FIG. 8 is a three-dimensional schematic diagram of a middle-layer node connector of the present invention.

In the figure: A: Deployable mechanism unit; 1: middle layer node connector, 2: reinforcing rod, 3: connecting rod, 4: scissor bar, 5: upper and lower node connector.

Detailed ways

In order to make the purposes, 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 accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments These are some embodiments of the present invention, but not all embodiments.

In the description of the present invention, it is to be understood that the terms "radial", "axial", "upper", "lower", "top", "bottom", "inner", "outer", etc. refer to orientations Or the positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation. , so it should not be construed as a limitation of the present invention. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

In the description of the present invention, it should be noted that, unless otherwise expressly specified and limited, the terms "installation", "arrangement" and "connection" should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection connected, or integrally connected; either directly or indirectly through an intermediary. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

In the three-dimensional schematic diagram of the composite scissor hinged peripheral truss deployable antenna mechanism shown in Figure 1, Figure 2 and Figure 3, it includes 12 deployable mechanism units A, and two upper and lower nodes are shared between adjacent deployable mechanism units. The connector and an intermediate layer node connector are connected to form a multi-faceted peripheral truss mechanism.

In the three-dimensional schematic diagrams of the deployable mechanism unit A shown in FIGS. 4-6 , the deployable mechanism unit A mainly includes two scissor bars 4 , four connecting rods 3 , four reinforcing bars 2 , and four upper and lower nodes. Connector 5 and two intermediate layer node connectors 1 . The two scissor rods 4 have the same structure, the middle is connected by a rotating pair, and the other four ends are connected with the upper and lower node connectors 5 through the rotating pair; The two hinge points in the middle position in the rhombus frame are connected with the middle layer node connector 1 through the rotating pair, and the middle position of each link 3 is connected with the quarter length of the scissor rod 4 through the rotating pair; four The structure of the reinforcing rods 2 is exactly the same, and the two ends are connected by a rotating pair, and the other two ends are connected with the upper and lower node connectors 5 through the rotating pair; the four upper and lower node connectors 5 have the same structure, and two forks The angle between the center planes of the upper opening grooves is 150°, the opening grooves on the inside of the two forks are inserted into one end of the reinforcing rod 2 and connected by a rotating pair, and the opening grooves on the outside of the two forks are inserted into one end of the scissor rod 4 and are connected. The four upper and lower node connectors 5 are symmetrically distributed on the four vertices of the deployable mechanism unit A through the rotating pair connection; the two middle layer node connectors 1 have exactly the same structure, and the center surfaces of the opening grooves on the two forks are located between the center planes. The included angle between them is 150°, the opening slots of the two forks are inserted into the two hinge points in the middle position in the diamond frame and connected by a rotating pair, and the two middle layer node connectors 1 are symmetrically distributed on the deployable mechanism unit A. in the middle of the side.

In the deployable mechanism unit A shown in FIGS. 4 to 6 , the scissor rod 4, the connecting rod 3 and all the rotational axes connected to the reinforcing rod 2 are parallel, and the reinforcing rod 2 can control the deployable mechanism unit A When the two reinforcing rods 2 connected to each other are collinear, the deployable mechanism unit A reaches the fully deployed position. When the size of the components of the deployable mechanism unit A is determined, by changing the length of the reinforcing rods 2, the expandable mechanism unit A can be changed. The size of the deployment mechanism unit A after it is fully unfolded can further change the size of the caliber of the fully unfolded antenna mechanism of the overall composite scissor hinge type peripheral truss deployable antenna mechanism.

In the three-dimensional schematic diagram of the composite scissor hinged peripheral truss deployable antenna mechanism shown in Figures 1 to 3, when the entire composite shear hinged peripheral truss deployable antenna mechanism is fully deployed, it is in a boundary singular configuration state, and the overall mechanism is degraded For a structure with 0 degrees of freedom, the rods in the structure can be used to counteract the effect of external forces without the need to provide additional driving torque, and the overall structural stiffness and mechanical properties are good.

The above description is only a preferred embodiment of the present invention, but the protection scope of the present invention is not limited to this. Substitutions should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims (3)

1. A composite scissor hinge type peripheral truss deployable antenna mechanism, characterized in that: it comprises N deployable mechanism units with the same structure, wherein N is a positive integer greater than or equal to 3, and adjacent deployable mechanism units are shared by sharing The two upper and lower layer node connectors and one middle layer node connector are connected to form a multi-faceted peripheral truss mechanism, wherein the deployable mechanism unit includes two scissor rods, four connecting rods, four reinforcing rods, four Two upper and lower node connectors and two middle layer node connectors; two of the scissor rods are connected by a rotating pair in the middle, and the other four ends are connected with the upper and lower node connectors by a rotating pair; the four connecting rods are connected by the rotating pair. Connected to form a rhombus frame, the two hinge points in the middle position in the rhombus frame are connected with the middle layer node connecting piece through the rotating pair, and the middle position of each connecting rod is connected with the quarter length of the scissor bar through the rotating pair; four The root reinforcement rods are set in two groups, the ends are connected by a rotating pair, and the other two ends are connected with the upper and lower node connecting pieces through the rotating pair; The two forks of the node connector and the middle layer node connector are symmetrical with the plane at the bending place. Each of the two forks is provided with an open groove, the open ends of the open grooves of the upper and lower node connecting pieces and the intermediate node connecting pieces are all set at the two free ends of the forks, between the center surfaces of the open grooves on the two forks. The included angle is (180-360/N)°, the opening grooves on the inner sides of the two forks of the upper and lower node connectors are used to insert one end of the reinforcing rod and connect through the rotating pair, and the opening grooves on the outside of the two forks are used for Insert one end of the scissor rod and connect it through the rotating pair, the four upper and lower node connectors are symmetrically distributed on the four vertices; the opening slots of the two forks of the middle layer node connector are used for inserting into the diamond frame in the middle position The two hinge points are connected by a rotating pair, and the two intermediate layer node connectors are symmetrically distributed at the middle position of the side of the deployable mechanism unit. 2. The composite scissor hinge type peripheral truss deployable antenna mechanism according to claim 1, characterized in that: the scissor rods, the connecting rods and the reinforcing rods in the same deployable mechanism unit are connected with all the rotation pairs of axes. parallel. 3. The composite scissor hinge type peripheral truss deployable antenna mechanism according to claim 1, wherein the reinforcing rod controls the degree of deployment of the deployable mechanism unit, and when the two mutually connected reinforcing rods are collinear, the deployable mechanism The unit reaches the fully deployed position; after the size of the deployable mechanism unit is determined, the fully deployed size of the deployable mechanism unit can be changed by changing the length of the reinforcing rod, thereby changing the fully deployed size of the overall composite scissor hinged peripheral truss deployable antenna mechanism. The size of the caliber.