Star finder with efficient heat dissipation and electromagnetic shielding structure

Abstract

The invention discloses a star finder with an efficient heat dissipation and electromagnetic shielding structure, and relates to the technical field of star finders. A built-in electrical element and an integrated assembly are arranged in the star finder body, a shielding laminated layer with an electromagnetic shielding effect is further arranged on the inner wall of the star finder body, broadband electromagnetic interference suppression is achieved through a double-layer composite structure of the shielding laminated layer and a cross-core filtering assembly, and it is ensured that a control circuit works stably; by means of magnetic attraction linkage of the electromagnetic propelling assembly, the permanent magnet plate and the blocking plate, airflow is started according to needs, and control is stable and reliable; the controller generates an alternating magnetic field according to a set time sequence to drive the permanent magnet plate to reciprocate to form forced convection, and energy-saving heat dissipation is achieved. The Kalman filtering controller and the sensor array collect temperature, pressure and flow data in real time, precise closed-loop thrust control is achieved through recursion estimation, and therefore cooperative operation of waste heat driving, intelligent heat dissipation and precise posture adjustment is completed on the premise that electromagnetic compatibility is guaranteed.

Description

Technical Field

[0001] This invention relates to the field of satellite finder technology, specifically a satellite finder with a highly efficient heat dissipation and electromagnetic shielding structure. Background Technology

[0002] Satellite finders, as satellite signal receiving devices, are widely used in mobile communications, emergency communications, and drone relay.

[0003] In existing technologies, the electromagnetic shielding of satellite finders mostly uses a single-layer metal shell, which has a certain suppression effect on high-frequency interference, but it is difficult to absorb low-frequency magnetic fields. Moreover, the cable entry point often forms a pigtail effect due to poor grounding of the shielding layer, which introduces common-mode interference and affects signal integrity. In terms of heat dissipation, most solutions use passive heat sinks or conventional fans for forced convection. The former has limited heat dissipation efficiency, while the latter has high energy consumption during continuous operation and cannot be dynamically adjusted according to heat load, resulting in energy waste. Summary of the Invention

[0004] Therefore, in order to overcome the above-mentioned shortcomings, the present invention provides a star finder with a high-efficiency heat dissipation and electromagnetic shielding structure.

[0005] The present invention is implemented as follows: a star finder with efficient heat dissipation and electromagnetic shielding structure is constructed. The device includes a star finder body; the star finder body is provided with built-in electrical components and integrated components, and the inner wall of the star finder body is also provided with a shielding layer with electromagnetic shielding function.

[0006] Preferably, the integrated component includes a heat sink fixedly disposed at a heat dissipation hole position inside the satellite finder body; a plug ring is fixedly installed at the air inlet of the heat sink by bolts, and the plug ring has a slot for fixing inside; an air outlet structure is fixedly installed inside the plug ring, and a propulsion component is fixedly installed on the middle side inside the heat sink; a sensor array is disposed on both sides of the propulsion component on the inner wall of the heat sink; and a microchannel array is fixedly installed at the air outlet of the heat sink.

[0007] Preferably, the air outlet structure includes a fixing plate that is inserted and fixed inside the insertion ring, and the fixing plate is provided with an array of airflow holes; an elastic wire with a resetting function is fixedly provided on the side of the airflow holes of the fixing plate, and the other end of the elastic wire is fixedly connected to the side of the sealing plate.

[0008] Preferably, the propulsion assembly includes a fin array fixedly disposed on the middle section inside the heat sink; the fin array is fixedly disposed on the outside of the outer shielding layer; an inner shielding layer is disposed inside the outer shielding layer, and an electromagnetic propulsion assembly is disposed inside the inner shielding layer; a permanent magnet plate is fixedly installed at the end of the push rod on the side of the electromagnetic propulsion assembly, and the side of the electromagnetic propulsion assembly is connected to the controller via a cable.

[0009] Preferably, the fins in the fin array are axially and equidistantly arranged on the outer surface of the outer shielding layer, and the electromagnetic propulsion assembly is specifically composed of two adjacent electromagnetic blocks composed of coils, and both sets of electromagnetic blocks of the electromagnetic propulsion assembly are fixedly connected to the controller via cables; the controller is specifically an electronically controlled switch with control current output.

[0010] Preferably, the microchannel array includes a sealing ring fixedly disposed at the air outlet of the heat sink; the sealing ring has through grooves arranged in annular shape at equal intervals at its edge, and a unidirectional structure is fixedly disposed inside the through grooves.

[0011] Preferably, an isolation shell is fixedly installed inside the middle side of the sealing ring, and an energy accumulator and an electronic control board are fixedly installed inside the isolation shell; the energy accumulator and the electronic control board are respectively fixedly connected to the controller via cables.

[0012] Preferably, the unidirectional structure specifically consists of a spring fixedly installed in the sealing ring groove and a sealing core fixedly installed at the other end of the spring.

[0013] Preferably, the microchannel array is further provided with a Kalman filter controller; the Kalman filter controller is electrically connected to a sensor array, the sensor array including a temperature sensor, a pressure sensor and a flow sensor disposed at the inlet of the push flow assembly.

[0014] Preferably, the shielding stack consists of inner and outer shielding layers, a through-hole filter component, and a grounding component.

[0015] Preferably, the through-hole filter assembly of the shielding stack includes a filter substrate, a through-hole capacitor, and a crimping ring; the filter substrate has multiple stepped holes, the through-hole capacitor is fixedly installed in the stepped holes, and the outer electrode of the through-hole capacitor is welded to the filter substrate to form a low-impedance ground.

[0016] The present invention has the following advantages: The present invention provides a satellite finder with a highly efficient heat dissipation and electromagnetic shielding structure, which, compared with similar devices, has the following improvements: The present invention discloses a satellite finder with a high-efficiency heat dissipation and electromagnetic shielding structure. Through a double-layer composite structure with shielding layers and a through-hole filter component, it achieves broadband electromagnetic interference suppression, ensuring stable operation of the control circuit. Utilizing the magnetic linkage between the electromagnetic propulsion component, permanent magnet plate, and sealing plate, airflow is opened on demand, ensuring stable and reliable control. The controller generates an alternating magnetic field according to a set sequence to drive the permanent magnet plate to reciprocate, forming forced convection and achieving energy-saving heat dissipation. A Kalman filter controller and sensor array collect temperature, pressure, and flow data in real time, and achieve precise closed-loop thrust control through recursive estimation. Thus, under the premise of ensuring electromagnetic compatibility, it completes the coordinated operation of waste heat drive, intelligent heat dissipation, and precise attitude adjustment. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the exploded structure of the star finder body of the present invention; Figure 3 This is a cross-sectional view of the integrated component of the present invention; Figure 4 This is an exploded structural diagram of the propulsion component of the present invention; Figure 5 This is the invention Figure 3 Enlarged structural diagram at point A; Figure 6 This is a cross-sectional structural diagram of the microchannel array device of the present invention.

[0018] The components include: satellite finder body-1, built-in electrical components-2, integrated components-3, shielding stack-4, heat dissipation cylinder-31, plug ring-32, air outlet structure-33, propulsion assembly-34, sensor array-35, microchannel array component-36, fixing plate-331, elastic wire-332, sealing plate-333, fin array-341, outer shielding layer-342, inner shielding layer-343, electromagnetic propulsion assembly-344, permanent magnet plate-345, controller-346, sealing ring-361, unidirectional structure-362, isolation shell-363, energy accumulator-364, and electronic control board-365. Detailed Implementation

[0019] The following is in conjunction with the appendix Figures 1-6 The principles and features of the present invention are described below. The examples given are for illustrative purposes only and are not intended to limit the scope of the invention. The invention is described more specifically in the following paragraphs by way of example with reference to the accompanying drawings. It should be noted that the drawings are in a very simplified form and use non-precise proportions, and are only used to facilitate and clarify the illustration of the embodiments of the invention.

[0020] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0021] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "setting" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances. The embodiments of this invention will now be described according to its overall structure.

[0022] Example 1:

[0023] Please see Figures 1-6 The present invention provides a satellite finder with a high-efficiency heat dissipation and electromagnetic shielding structure, comprising a satellite finder body 1; the satellite finder body 1 is provided with built-in electrical components 2 and integrated components 3, and the inner wall of the satellite finder body 1 is also provided with a shielding stack 4 with electromagnetic shielding function.

[0024] The integrated component 3 includes a heat sink 31 fixedly installed at the heat dissipation hole position inside the satellite finder body 1; a plug ring 32 is fixedly installed at the air inlet of the heat sink 31 by bolts, and the plug ring 32 is provided with a slot for fixing; an air outlet structure 33 is fixedly installed inside the plug ring 32, and a propulsion component 34 is fixedly installed in the middle of the heat sink 31; a sensor array 35 is provided on both sides of the propulsion component 34 on the inner wall of the heat sink 31; and a microchannel array 36 is fixedly installed at the air outlet of the heat sink 31.

[0025] The air outlet structure 33 includes a fixing plate 331 that is inserted and fixed inside the insertion ring 32, and airflow holes are arranged in an array on the fixing plate 331; an elastic wire 332 with a reset function is fixedly arranged on the side of the airflow hole of the fixing plate 331, and the other end of the elastic wire 332 is fixedly connected to the side of the sealing plate 333.

[0026] The propulsion assembly 34 includes a fin array 341 fixedly disposed on the middle section inside the heat sink 31; the fin array 341 is fixedly disposed on the outside of the outer shielding layer 342; an inner shielding layer 343 is disposed inside the outer shielding layer 342, and an electromagnetic propulsion assembly 344 is disposed inside the inner shielding layer 343; a permanent magnet plate 345 is fixedly installed at the end of the push rod on the side of the electromagnetic propulsion assembly 344, and the side of the electromagnetic propulsion assembly 344 is connected to the controller 346 via a cable; the fins in the fin array 341 are axially and equidistantly disposed on the outer surface of the outer shielding layer 342, and the electromagnetic propulsion assembly 344 is specifically composed of two adjacent electromagnetic blocks composed of coils, and both sets of electromagnetic blocks of the electromagnetic propulsion assembly 344 are fixedly connected to the controller 346 via cables; the controller 346 is specifically an electronically controlled switch with control current output.

[0027] The microchannel array 36 includes a sealing ring 361 fixedly disposed at the air outlet of the heat sink 31; the sealing ring 361 has annular grooves equidistantly arranged at its edge, and a unidirectional structure 362 is fixedly disposed inside the grooves; an isolation housing 363 is fixedly installed in the middle of the sealing ring 361, and an energy accumulator 364 and an electronic control board 365 are fixedly installed inside the isolation housing 363; the energy accumulator 364 and the electronic control board 365 are fixedly connected to the controller 346 via cables; the unidirectional structure 362 is specifically composed of a spring fixedly installed in the groove of the sealing ring 361 and a sealing core fixedly installed at the other end of the spring.

[0028] The microchannel array 36 also contains a Kalman filter controller; the Kalman filter controller is electrically connected to the sensor array 35, which includes a temperature sensor, a pressure sensor, and a flow sensor located at the inlet of the push assembly 34.

[0029] Example 2:

[0030] Please see Figures 1-6 The present invention provides a satellite finder with a high-efficiency heat dissipation and electromagnetic shielding structure. Compared with Embodiment 1, this embodiment further includes: the shielding stack 4 is composed of inner and outer shielding layers, a through-hole filter component, and a grounding component; the through-hole filter component of the shielding stack 4 includes a filter substrate, a through-hole capacitor, and a crimping ring; the filter substrate has multiple stepped holes, the through-hole capacitor is fixedly installed in the stepped holes, and the outer electrode of the through-hole capacitor is welded to the filter substrate to form a low-impedance ground.

[0031] The working principle of a satellite finder with efficient heat dissipation and electromagnetic shielding structure is as follows: First, when the satellite finder is working, the built-in electrical components 2 and the external environment will generate broadband electromagnetic interference. Here, the outer shielding layer of the shielding stack 4, specifically aluminum alloy, is used to reflect high-frequency electromagnetic waves; the inner shielding layer, specifically permalloy, is used to absorb the low-frequency magnetic field that penetrates the outer layer, forming a double-layer composite shield; at the same time, the through-hole filter component of the shielding stack 4 is set to connect to various cables, and the outer electrode is welded to the filter substrate to form a low-impedance grounding connection. Secondly, when the satellite finder is working, the built-in electrical components 2 generate a large amount of waste heat; the heat sink 31 of the integrated component 3 is fixedly installed at the heat dissipation hole position of the satellite finder body 1, forming a heat dissipation channel; when the temperature of the built-in electrical components 2 rises, the heat is transferred to the air outlet structure 33 through the heat sink 31. Here, the controller 346 controls the electronic control board 365 and the energy storage device 364 to input electrical energy from different directions to the two sets of electromagnetic blocks of the electromagnetic propulsion component 344, so that the two sets of electromagnetic blocks are energized and magnetized and form different and opposite magnetic field layouts, thereby realizing that the two sets of electromagnetic blocks are respectively placed on both ends of the inner shielding layer 343 and push the permanent magnet plate 345 close to the fixed plate 331. Here, the magnetic attraction action between the permanent magnet plate 345 and the sealing plate 333 causes the air hole of the fixed plate 331 to open, allowing airflow to enter the fin array 341. Here, since the sealing plate 333 is at the air outlet, and the heat generated by the built-in electrical components 2 is not too high, the magnetic field between the permanent magnet plate 345 and the sealing plate 333 will not weaken due to temperature. Third, when enhanced airflow is required, the controller 346 energizes the electromagnetic block according to a set sequence, generating an alternating magnetic field to drive the permanent magnet plate 345 to reciprocate, thereby accelerating the airflow inside the heat sink 31, forming forced convection, and enhancing the heat dissipation efficiency of the fin array 341. To achieve precise thrust control, a Kalman filter controller is installed inside the microchannel array 36. This controller is electrically connected to the sensor array 35, which is used to detect the temperature, pressure, and flow rate at the inlet of the thrust assembly 34. Due to the one-way structure 362, elastic wire 332, and sealing plate 333 installed at the air outlet of the heat sink 31, when the airflow pressure drawn into the heat sink 31 exceeds the spring preload of the one-way structure 362, the sealing core opens, and the airflow is ejected. After ejection, the pressure drops, and the spring resets and seals.

[0032] This invention provides a satellite finder with an improved structure featuring efficient heat dissipation and electromagnetic shielding. The double-layer composite structure of the shielding stack 4 and the through-hole filter component achieve wideband electromagnetic interference suppression, ensuring stable operation of the control circuit. The electromagnetic propulsion component 344, permanent magnet plate 345, and sealing plate 333 utilize magnetic linkage to enable on-demand airflow, ensuring stable and reliable control. The controller 346 generates an alternating magnetic field according to a set sequence, driving the permanent magnet plate 345 to reciprocate and form forced convection, achieving energy-saving heat dissipation. The Kalman filter controller and sensor array 35 collect temperature, pressure, and flow data in real time, achieving precise closed-loop thrust control through recursive estimation. Thus, under the premise of ensuring electromagnetic compatibility, it completes the coordinated operation of waste heat drive, intelligent heat dissipation, and precise attitude adjustment.

[0033] The above description shows and illustrates the basic principles, main features, and advantages of the present invention. Standard parts used in the present invention can be purchased from the market, and irregular parts can be customized according to the description and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts, and equipment adopt conventional models in the prior art, and the circuit connection adopts conventional connection methods in the prior art, which will not be described in detail here.

[0034] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A star finder with efficient heat dissipation and electromagnetic shielding structure, comprising a star finder body (1); the star finder body (1) is provided with built-in electrical components (2) and integrated components (3), and the inner wall of the star finder body (1) is also provided with a shielding stack (4) with electromagnetic shielding function. Its features are: The integrated component (3) includes a heat sink (31) fixedly installed at the heat dissipation hole position inside the satellite finder body (1); a plug ring (32) is fixedly installed at the air inlet of the heat sink (31) by bolts, and the plug ring (32) is provided with a slot for fixing; an air outlet structure (33) is fixedly installed inside the plug ring (32), and a propulsion component (34) is fixedly installed in the middle of the heat sink (31); a sensor array (35) is provided on both sides of the propulsion component (34) on the inner wall of the heat sink (31); and a microchannel array component (36) is fixedly installed at the air outlet of the heat sink (31).

2. The star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 1, characterized in that: The air outlet structure (33) includes a fixing plate (331) that is inserted and fixed in the insertion ring (32), and airflow holes are arranged in an array on the fixing plate (331); an elastic wire (332) with a reset function is fixedly arranged on the side of the airflow hole of the fixing plate (331), and the other end of the elastic wire (332) is fixedly connected to the side of the sealing plate (333).

3. The star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 2, characterized in that: The propulsion assembly (34) includes a fin array (341) fixedly disposed on the middle section inside the heat sink (31); the fin array (341) is fixedly disposed on the outside of the outer shielding layer (342); the outer shielding layer (342) is wrapped with an inner shielding layer (343), and an electromagnetic propulsion assembly (344) is disposed inside the inner shielding layer (343); a permanent magnet plate (345) is fixedly installed at the end of the push rod on the side of the electromagnetic propulsion assembly (344), and the side of the electromagnetic propulsion assembly (344) is connected to the controller (346) via a cable.

4. The star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 3, characterized in that: The fins in the fin array (341) are axially and equidistantly arranged on the outer surface of the outer shielding layer (342), and the electromagnetic propulsion assembly (344) is specifically composed of two adjacent electromagnetic blocks composed of coils, and both sets of electromagnetic blocks of the electromagnetic propulsion assembly (344) are fixedly connected to the controller (346) via cables; the controller (346) is specifically an electronically controlled switch with control current output.

5. The star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 4, characterized in that: The microchannel array (36) includes a sealing ring (361) fixedly disposed at the air outlet of the heat sink (31); the sealing ring (361) has a through groove arranged in an annular shape at equal intervals at its edge, and a one-way structure (362) is fixedly disposed inside the through groove.

6. The star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 5, characterized in that: An isolation shell (363) is fixedly installed inside the middle side of the sealing ring (361), and an energy accumulator (364) and an electronic control board (365) are fixedly installed inside the isolation shell (363); the energy accumulator (364) and the electronic control board (365) are fixedly connected to the controller (346) through cables.

7. A star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 6, characterized in that: The unidirectional structure (362) is specifically composed of a spring fixedly installed in the through groove of the sealing ring (361) and a sealing core fixedly installed at the other end of the spring.

8. The star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 7, characterized in that: The microchannel array (36) is also equipped with a Kalman filter controller; the Kalman filter controller is electrically connected to the sensor array (35), which includes a temperature sensor, a pressure sensor and a flow sensor located at the inlet of the push flow assembly (34).

9. A star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 8, characterized in that: The shielding stack (4) consists of inner and outer shielding layers, a through-hole filter component, and a grounding component.

10. A star finder with a high-efficiency heat dissipation and electromagnetic shielding structure according to claim 9, characterized in that: The through-hole filter assembly of the shielding stack (4) includes a filter substrate, a through-hole capacitor and a crimping ring; the filter substrate has multiple stepped holes, the through-hole capacitor is fixedly installed in the stepped holes, and the outer electrode of the through-hole capacitor is welded to the filter substrate to form a low-impedance ground.

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