1. An efficient expansion type heat pipe radiation radiator is characterized in that: the heat-control heat-radiating plate comprises a base heat-radiating plate (1), an expansion heat-radiating plate (2), a flexible heat-conducting cable (3) and an unlocking device (4), wherein one end of the base heat-radiating plate (1) is connected with one end of the expansion heat-radiating plate (2) through two rotary connecting pieces (5), the base heat-radiating plate (1) and the expansion heat-radiating plate (2) are relatively expanded through the rotary connecting pieces (5), each heat-radiating plate comprises a honeycomb plate (6) and pre-embedded heat pipes (7) embedded in the honeycomb plate (6), and the surface of each heat-radiating plate is coated with a heat-control coating,

the flexible heat conducting cables (3) are connected between the substrate radiation heat-dissipating plate (1) and the expansion radiation heat-dissipating plate (2), and heat is conducted from the substrate radiation heat-dissipating plate (1) to the expansion radiation heat-dissipating plate (2) through the flexible heat conducting cables (3);

the unlocking device (4) is fixedly arranged on the substrate radiation heat dissipation plate (1), through holes with the number equal to that of the unlocking devices (4) are formed in the unfolded radiation heat dissipation plate (2), and the unlocking devices (4) are correspondingly arranged in the through holes in a penetrating mode under the folded state of the radiator.

2. A high efficiency expanding heat pipe radiant heat sink as recited in claim 1 wherein: the flexible heat conducting cable (3) comprises a flexible belt (32) and rigid terminals (31) fixedly arranged at two ends of the flexible belt (32), wherein one rigid terminal (31) is fixedly arranged on the substrate radiation heat dissipation plate (1), the other rigid terminal (31) is fixedly arranged on the unfolded radiation heat dissipation plate (2), the rigid terminals (31) are made of aluminum alloy, and the flexible belt (32) is made of pyrolytic graphite sheets.

3. A high efficiency expanding heat pipe radiant heat sink as recited in claim 2 wherein: the flexible strip (32) is formed from a stack of multiple sheets of pyrolytic graphite.

4. A high efficiency expanding heat pipe radiant heat sink as recited in claim 1, 2 or 3 wherein: one end part of the flexible heat conducting cable (3) is pressed on the embedded heat pipe (7) of the substrate radiation heat dissipation plate (1) through a screw, and the other end part is pressed on the embedded heat pipe (7) of the unfolded radiation heat dissipation plate (2) through a screw.

5. A high efficiency expanding heat pipe radiant heat sink as recited in claim 1 wherein: the number of the flexible heat conducting cables (3) is at least two.

6. A high efficiency expanding heat pipe radiant heat sink as recited in claim 1, 2, 3 or 5 wherein: the number of the embedded heat pipes (7) on each radiation heat dissipation plate is at least one.

7. A high efficiency expanding heat pipe radiant heat sink as recited in claim 1 wherein: the embedded heat pipe (7) is of a U-shaped structure.

8. A high efficiency expanding heat pipe radiant heat sink as recited in claim 1 wherein: the embedded heat pipe (7) is an aluminum ammonia heat pipe.

9. A high efficiency expanding heat pipe radiant heat sink as recited in claim 1 wherein: the thickness of the honeycomb plate (6) is 15 mm.

Background

There are several forms for the extended radiant heat sink, which are generally implemented by the extended radiant panel form. However, the innovation point of the heat dissipation plate is to realize a two-dimensional steering mechanism, the purpose is to realize the two-dimensional rotation of the heat dissipation plate, the heat dissipation plate can only realize heat control in a minimum temperature range, and the limit heat dissipation capacity of the spacecraft can not be effectively improved, wherein the most critical problem is that the efficient transmission of heat is difficult to realize. Therefore, a radiation heat sink capable of solving the problem of insufficient heat dissipation capability of high-power communication satellites and microsatellites is urgently needed.

Disclosure of Invention

The invention aims to solve the problem that the heat dissipation capacity of the existing high-power communication satellite and the existing microsatellite is insufficient, and further provides an efficient expanded heat pipe radiation radiator.

The technical scheme adopted by the invention for solving the technical problems is as follows:

an efficient expansion type heat pipe radiation radiator comprises a base radiation heat dissipation plate, an expansion radiation heat dissipation plate, a flexible heat conducting cable and an unlocking device, wherein one end of the base radiation heat dissipation plate is connected with one end of the expansion radiation heat dissipation plate through two rotary connecting pieces, the base radiation heat dissipation plate and the expansion radiation heat dissipation plate are expanded relatively through the rotary connecting pieces, each radiation heat dissipation plate comprises a honeycomb plate and pre-embedded heat pipes embedded in the honeycomb plate, and the surface of each radiation heat dissipation plate is coated with a thermal control coating,

the flexible heat conducting cables are connected between the substrate radiation heat-dissipating plate and the expansion radiation heat-dissipating plate, and heat is conducted from the substrate radiation heat-dissipating plate to the expansion radiation heat-dissipating plate through the flexible heat conducting cables;

the unlocking device is fixedly arranged on the substrate radiation heat dissipation plate, through holes with the number equal to that of the unlocking devices are formed in the unfolded radiation heat dissipation plate, and the unlocking devices are correspondingly arranged in the through holes in a penetrating mode in the folded state of the radiator.

Further, the flexible heat conducting cable comprises a flexible belt and rigid terminals fixedly arranged at two ends of the flexible belt, one of the rigid terminals is fixedly arranged on the substrate radiation heat dissipation plate, the other rigid terminal is fixedly arranged on the unfolded radiation heat dissipation plate, the rigid terminals are made of aluminum alloy, and the flexible belt is made of pyrolytic graphite sheets.

Further, the flexible tape is formed by stacking a plurality of pyrolytic graphite sheets.

Furthermore, one end part of the flexible heat conducting cable is in pressure joint with the embedded heat pipe of the substrate radiation heat dissipation plate through screws, and the other end part of the flexible heat conducting cable is in pressure joint with the embedded heat pipe of the unfolded radiation heat dissipation plate through screws.

Further, the number of the flexible heat conducting cables is at least two.

Furthermore, the number of the embedded heat pipes on each radiation cooling plate is at least one.

Furthermore, the pre-buried heat pipe is of a U-shaped structure.

Furthermore, the embedded heat pipe is an aluminum-ammonia heat pipe.

Further, the thickness of the honeycomb panel was 15 mm.

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

the structure is simple and convenient, and the realization is easy. Meanwhile, the system does not occupy satellite control resources, and does not need special control after reaching the specified orbit and being unfolded.

Through flexible heat conduction cable, can realize the high-efficient transmission of heat between two heating panels. Through embedding the pre-buried heat pipe in the honeycomb panel, the limit heat dissipation capacity of the satellite can be further improved.

Drawings

Fig. 1 is a first perspective view of the present application (when the deployment angle is acute);

FIG. 2 is a schematic structural view of the present application in a fully deployed state;

FIG. 3 is a second perspective view of the present application (in a folded state);

FIG. 4 is a schematic front view of a base radiation plate;

fig. 5 is a schematic front view of an unfolded radiation cooling plate;

fig. 6 is a side view schematic diagram of a flexible thermal conductor cable.

Detailed Description

The first embodiment is as follows: the embodiment is described with reference to fig. 1 to 6, and a high-efficiency expansion type heat pipe radiation radiator comprises a base radiation heat dissipation plate 1, an expansion radiation heat dissipation plate 2, a flexible heat conducting cable 3 and an unlocking device 4, wherein one end of the base radiation heat dissipation plate 1 is connected with one end of the expansion radiation heat dissipation plate 2 through two rotating connectors 5, the base radiation heat dissipation plate 1 and the expansion radiation heat dissipation plate 2 are relatively expanded through the rotating connectors 5, each radiation heat dissipation plate comprises a honeycomb plate 6 and pre-embedded heat pipes 7 embedded in the honeycomb plate 6, and the surface of each radiation heat dissipation plate is coated with a thermal control coating,

the flexible heat conducting cables 3 are connected between the substrate radiation heat-dissipation plate 1 and the expansion radiation heat-dissipation plate 2, and heat is conducted from the substrate radiation heat-dissipation plate 1 to the expansion radiation heat-dissipation plate 2 through the flexible heat conducting cables 3;

the unlocking device 4 is fixedly arranged on the substrate radiation heat dissipation plate 1, through holes with the number equal to that of the unlocking devices 4 are formed in the unfolded radiation heat dissipation plate 2, and the unlocking devices 4 correspondingly penetrate through the through holes in the folded state of the radiator.

The base radiation heat dissipation plate 1 is installed with the satellite cabin plate in a heat conduction mode. The heat conducting device can be installed on the surface of a satellite, can also be used as an installation surface of a radiator, and is installed with a high-power heating single machine in the satellite in a heat conducting mode.

The rotating connecting piece 5 adopts the prior art, and before the two radiation heat dissipation plates are installed, the pre-tightening force is applied to the rotating connecting piece 5 to control the unfolding angles of the two radiation heat dissipation plates. The rotating connecting piece 5 may be a torsion spring, or may be another hinge structure that can realize the unfolding of the two radiation heat dissipation plates and can determine the unfolding angle after the unfolding. The maximum rotation angle of the rotary connecting piece 5 is 0-180 degrees. The specific angle can be determined according to the arrangement of the satellite structure and the heat dissipation requirement. The rotary joint 5 is not modifiable after determining the deployment angle, and the deployed heat pipe radiation cooling plate is not retractable.

The honeycomb plate 6 is specifically a honeycomb aluminum plate, and takes on a main heat dissipation function. The internal heat conductivity is enhanced by adopting the pre-buried heat pipe 7. The surface of the heat dissipation plate is coated with a thermal control coating with low absorption-emission ratio. The thermal control coating is SR107 organic white paint with high infrared emissivity and low solar absorptivity.

One side of the heat dissipation plate is a mounting surface used for heat conduction mounting with the satellite cabin plate, and the other side of the heat dissipation plate is a heat dissipation surface.

The unlocking device 4 used in the present application is the prior art, and the structure and the working principle thereof will not be described herein again. The unlocking device 4 is mounted on the base radiation heat-dissipating plate 1 by screws. Under the radiator fold condition, connect through the fuse between two radiation heating panels, unlocking device 4 corresponds the dress of wearing in the through-hole, makes the laminating that two radiation heating panels can be better, practices thrift the space, prevents because of the folding effect of two radiation heating panels of unlocking device 4's high influence. Before the radiator is put into the track and unfolded, the unlocking device 4 fuses the fuse through current, and the unfolded radiation heat dissipation plate 2 is unfolded under the action of the pretightening force of the rotary connecting piece 5.

The flexible heat conducting cable 3 is a high-performance heat conducting cable.

The number of the heat pipes 7 embedded in each radiation heat dissipation plate is at least one. The heat conduction inside the honeycomb plate 6 can be effectively increased by using the embedded heat pipe 7, and the temperature is ensured to be uniform and stable.

The structure is simple and convenient, and the realization is easy. Meanwhile, the system does not occupy satellite control resources, and does not need special control after reaching the specified orbit and being unfolded.

Through flexible heat conduction cable 3, can realize the high-efficient transmission of heat between two heating panels. The embedded heat pipe 7 is embedded in the honeycomb plate 6, so that the limit heat dissipation capacity of the satellite can be further improved.

The flexible heat conducting cable 3 comprises a flexible belt 32 and rigid terminals 31 fixedly arranged at two ends of the flexible belt 32, wherein one rigid terminal 31 is fixedly arranged on the substrate radiation heat dissipation plate 1, the other rigid terminal 31 is fixedly arranged on the unfolded radiation heat dissipation plate 2, the rigid terminals 31 are made of aluminum alloy, and the flexible belt 32 is made of pyrolytic graphite sheets. The rigid terminal 31 is clamped to an end of the flexible tape 32. The rigid terminal 31 and the radiation heat sink plate are preferably mounted by screw press-fitting. The flexible strip 32 is made of pyrolytic graphite sheet with high thermal conductivity, i.e. PGS, and is characterized by high flexibility, can be unfolded at any angle along with the radiation radiator, and has a thermal conductivity effect superior to that of metals such as copper under the same quality. The deployment angle is determined according to the deployment angle that can be achieved by rotating the link 5. The rigid terminal 31 is processed by light weight, and the total mass of the satellite is reduced.

The flexible strip 32 is formed by stacking a plurality of sheets of pyrolytic graphite.

One end of the flexible heat conducting cable 3 is pressed on the embedded heat pipe 7 of the base radiation heat-dissipating plate 1 by a screw, and the other end is pressed on the embedded heat pipe 7 of the unfolded radiation heat-dissipating plate 2 by a screw. Each radiation heat dissipation plate is provided with a screw hole for mounting a high-performance flexible heat conducting cable 3.

The number of the flexible heat-conducting cables 3 is at least two.

The number of the embedded heat pipes 7 on each radiation heat dissipation plate is at least one.

The embedded heat pipe 7 is of a U-shaped structure.

The embedded heat pipe 7 is an aluminum ammonia heat pipe.

The thickness of the honeycomb panel 6 was 15 mm.