A cubic simulation satellite model

Abstract

The application relates to the technical field of spacecraft ground simulation and demonstration, in particular to a cubic simulation satellite model, which comprises a plurality of prisms, a plurality of side panels, a vibration test assembly, a thermal control visualization assembly and a pop-off assembly.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of spacecraft ground simulation and demonstration, in particular to a cubic simulation satellite model. BACKGROUND

[0002] Since the CubeSat was jointly proposed by Stanford University and California Institute of Technology in 1999, it has become an important platform for space science research, technology verification and commercial application as a kind of mini-satellite adopting a standardized size. The standard specification of the CubeSat is based on units (U), the volume of 1U is about 10cm*10cm*10cm, and the weight is not more than 1.33kg. The CubeSat can be expanded to 2U, 3U or even larger specifications according to the task requirements. As a kind of mini-satellite adopting a standardized size, the CubeSat has become an important platform for universities, scientific research institutions and commercial companies to carry out space science experiments, technology verification and education and teaching due to its low cost, rapid development and modularization advantages. Under this background, the cubic simulation satellite model for teaching demonstration, popular science exhibition and scientific research has emerged as the times require.

[0003] However, the existing cubic satellite models are generally similar in appearance and can only show the external shape and approximate internal layout of the satellite. They can also support the disassembly and installation of internal components for people to practice, but these models are more like a "toy" similar to building blocks, and there is a huge gap with the real engineering practice. The thermal control system is the "life support" of the satellite, because the real satellite in orbit will experience severe temperature changes (temperature rises sharply in the sunlit area, and temperature drops sharply in the shadow area), and since there is no air convection, its heat transfer completely depends on conduction and radiation. The core task of the thermal control system is to maintain the temperature of the satellite internal equipment within a safe range through passive and active means. The existing model cannot simulate this process. In addition, heat itself is invisible, and the traditional model cannot show how heat accumulates, conducts and dissipates inside the satellite. People can only understand this principle through theoretical explanation, lacking direct understanding. People cannot understand why the "thermal control system" is the "life support" of the satellite. Therefore, the effect of teaching and popular science research is not good. At the same time, the separation of the CubeSat from the carrier is a key dynamic event. The existing model is either fixed or the separation action is extremely simple and childish, such as magnetic attraction disconnection and plug-in separation, which cannot reflect the real physical process of storing energy and releasing instantaneously to produce impact. The simulation effect is poor. In addition, during the launch process, the satellite will withstand severe vibration and impact to ensure that the satellite will not break, loosen or fail in function. However, the existing cubic satellite model cannot perform environmental tests on itself after being assembled by people themselves. It cannot verify whether the model structure designed by people is solid and can survive in the simulated launch environment. It lacks effective engineering practice. SUMMARY

[0004] The purpose of this invention is to provide a cube-shaped simulated satellite model to solve the above-mentioned problems.

[0005] To achieve the above objectives, the present invention provides a cube-shaped simulated satellite model, comprising:

[0006] Several prisms, arranged in a square pattern;

[0007] Several side panels are installed between several prisms, and the several side panels and several prisms together form a cube;

[0008] Several partitions are sequentially arranged inside a cubic body composed of several side panels and several prisms;

[0009] A vibration testing assembly, wherein several prisms are mounted on the vibration testing assembly, and the vibration testing assembly is capable of exciting several prisms, several side panels and several partitions to induce resonance;

[0010] A thermal control visualization component is disposed on the side panel, the partition, and the vibration test component. The thermal control visualization component is used to actively absorb and release heat, accompanied by changes in physical state and color.

[0011] A spring-off assembly is connected below the vibration test assembly. The spring-off assembly can accumulate energy under the action of external force and use it to push the vibration test assembly upward, so as to move the vibration test assembly.

[0012] Furthermore, the thermal control visualization component includes:

[0013] A sealed container is installed on the outside of one of the side panels and is close to several high heat-dissipating devices disposed on the partitions.

[0014] An observation window is provided on the sealed container;

[0015] Paraffin wax, wherein several pieces of said paraffin wax are filled in the sealed container, and several pieces of said paraffin wax are colored;

[0016] A collection component is installed on the partition and surrounds the high heat-dissipating device on three sides. The collection component is inserted into the sealed container and is made of copper.

[0017] Furthermore, the thermal control visualization component also includes: a thermochromic ink layer coated on the outer surface of the sealed container;

[0018] The thermochromic ink layer changes color as the temperature of the sealed container changes.

[0019] Furthermore, the ejection assembly includes:

[0020] A base, which is placed horizontally and has a handle on its side;

[0021] Several base components are mounted on the base and arranged in a square pattern;

[0022] A plurality of sliding members are slidably inserted into a plurality of bottom components, and the vibration test assembly is mounted on top of the plurality of sliding members.

[0023] A top plate, which is centrally attached to the bottom of the vibration test assembly;

[0024] A first spring, which is mounted on the base and connected to the top plate;

[0025] A vertical rail, which is fixed to the side of the base;

[0026] A handle is connected to the top plate and slides along the vertical rail.

[0027] Furthermore, the vibration testing component includes:

[0028] Several connecting units are respectively installed on the top of several sliding members;

[0029] A plurality of second springs are respectively mounted on a plurality of connecting platforms;

[0030] The platform is mounted on several second springs, several prisms are mounted on the platform, and the top plate is centrally attached to the bottom of the platform;

[0031] Side suspension plate, the side suspension plate being connected to the side of the platform;

[0032] A vibrator is mounted on the side suspension plate.

[0033] Furthermore, the thermal control visualization component also includes:

[0034] A gooseneck tube, one end of which is connected to the side of the platform;

[0035] A heat-generating vessel is connected to the other end of the gooseneck tube. A heat source is disposed inside the heat-generating vessel, and the heat-generating vessel and the heat source face the sealed container.

[0036] Furthermore, the high heat dissipation device is a surface mount resistor;

[0037] An aluminum shell is provided between the two prisms on the opposite side of the high heat dissipation device and the sealed container, and the aluminum shell is coated with a high emissivity coating.

[0038] Furthermore, the ejection assembly also includes:

[0039] Two impact cylinders are mounted on the base and located on either side of the first spring, with the output shafts of the two impact cylinders facing the bottom of the platform.

[0040] Furthermore, a telescopic rod is provided inside the first spring;

[0041] The telescopic rod is mounted on the base and connected upwards to the top plate.

[0042] Furthermore, thick rubber sheets are mounted on the output shafts of the two impact cylinders.

[0043] Compared with the prior art, the present invention has the following beneficial effects:

[0044] 1. This invention establishes a thermal control visualization component that actively absorbs the heat of a target object when the temperature rises, and then orderly transfers the stored heat to the target object as the temperature drops, thereby controlling the temperature of the target object. This simulates the working principle of a satellite's "thermal control system." Furthermore, this process can be transformed into a visible dynamic phenomenon through both changes in physical state and color, thus indirectly and intuitively demonstrating the working principle of a satellite's "thermal control system." This effectively helps people understand why the "thermal control system" is the "lifeline" of a satellite, greatly improving the effectiveness of its application in teaching, popular science research, and other practical applications.

[0045] 2. This invention allows people to manually accumulate energy through the ejection component and autonomously trigger the release of energy. This energy is used to eject the vibration test component and a cubic body composed of several prisms, thereby simulating the key action of the CubeSat being ejected and separated from the launch vehicle. It reflects the real physical process of storing energy and releasing it instantaneously to generate impact, and has a very good simulation effect.

[0046] 3. This invention uses a vibration testing component to generate high-frequency vibrations, which cause a cubic body composed of several prisms to vibrate synchronously. This causes all components on the cubic body to vibrate continuously and at high frequency, thereby enabling people to conduct vibration tests on the CubeSat model immediately after assembly. This simulates the environmental factors affecting the CubeSat model under launch conditions, helping people to conduct effective engineering practices to verify whether their designed model structure is robust and can survive in the launch environment.

[0047] 4. The cube satellite simulation model of the present invention not only has a similar appearance and can show the external shape and approximate internal layout of the satellite, but also simulates the operation of key components, the actions of the launch process, and the launch environment when the satellite is in orbit. It also integrates environmental testing into itself, so that people can have a more comprehensive and immersive understanding of cube satellites. Attached Figure Description

[0048] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0049] Figure 1 A perspective view of the present invention is shown;

[0050] Figure 2 A second perspective view of the present invention is shown;

[0051] Figure 3 A third perspective view of the present invention is shown;

[0052] Figure 4 A fourth perspective view of the present invention is shown;

[0053] Figure 5 A fifth perspective view of the present invention is shown;

[0054] Figure 6 A sixth perspective view of the present invention is shown;

[0055] Figure 7 The present invention is shown. Figure 3 Enlarged view of point A;

[0056] Figure 8 The present invention is shown. Figure 5 Enlarged view of point B.

[0057] In the figure, the same reference numerals represent the same structural element, wherein:

[0058] 1. Prism; 2. Side panel; 3. Partition; 4. Vibration test assembly; 41. Connecting platform; 42. Second spring; 43. Platform; 44. Side hanging plate; 45. Vibrator; 5. Thermal control visualization assembly; 51. Sealed container; 52. Observation window; 53. Paraffin wax; 54. Collector; 55. Gooseneck tube; 56. Loading dish; 6. Spring-release assembly; 61. Base; 62. Bottom kit; 63. Sliding component; 64. Top plate; 65. First spring; 66. Vertical rail; 67. Handle; 68. Impact cylinder; 7. High heat dissipation device; 8. Aluminum shell; 9. Telescopic rod; 10. Rubber sheet. Detailed Implementation

[0059] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, illustrating only the basic structure of the invention, and therefore only show the components relevant to the invention.

[0060] like Figures 1-8 As shown, a cube satellite simulation model includes:

[0061] Several prisms 1 are arranged in a square;

[0062] Several side panels 2 are installed between several prisms 1, and the several side panels 2 and several prisms 1 together form a cube;

[0063] Several partitions 3 are sequentially arranged inside a cubic body composed of several side panels 2 and several prisms 1. Other sub-components required for the CubeSat, such as power systems, communication systems, database management systems, and payloads, are also installed on the prisms 1, side panels 2, and partitions 3. These sub-components, together with the prisms 1, side panels 2, and partitions 3, form a basic cubic model, thereby ensuring that the shape is similar and that the external shape and approximate internal layout of the satellite can be shown. This is existing technology and will not be elaborated on here. Among these sub-components are high-heat-consuming devices 7 that generate a lot of heat during operation.

[0064] Vibration test component 4, several prisms 1 are installed on vibration test component 4, and vibration test component 4 can excite several prisms 1, several side panels 2 and several partitions 3 to induce resonance.

[0065] Thermal control visualization component 5 is installed on side panel 2, partition 3 and vibration test component 4. Thermal control visualization component 5 is used to actively absorb and release heat and is accompanied by changes in physical state and color.

[0066] The ejection component 6 is connected below the vibration test component 4. The ejection component 6 can accumulate energy under external force and use it to push the vibration test component 4, causing it to move. This invention includes a thermal control visualization component 5, which actively absorbs heat from the target object when the temperature rises, and then orderly transfers the stored heat to the target object when the temperature drops, controlling its temperature. This simulates the working principle of a satellite's "thermal control system." This process can be transformed into a visible dynamic phenomenon through changes in state and color, indirectly and intuitively demonstrating the working principle of the satellite's "thermal control system." This effectively helps people understand why the "thermal control system" is the "lifeline" of a satellite, greatly improving its application in teaching, popular science research, and other practical applications. The ejection component 6 allows people to manually accumulate energy and autonomously trigger its release, using this energy to launch the vibration test component 4 and a cubic structure composed of several prisms 1, thus simulating... The crucial action of the CubeSat's ejection and separation from the launch vehicle demonstrates the real physical process of storing energy and releasing it instantaneously to generate impact, providing excellent simulation results. The vibration test component 4 generates high-frequency vibrations, causing synchronous excitation of the cube composed of several prisms 1, resulting in continuous and high-frequency vibrations of all components on the cube. This allows for vibration testing of the CubeSat model immediately after assembly, simulating the environmental factors affecting the CubeSat model under launch conditions. This helps in effective engineering practice, verifying the robustness of the designed model structure and its survival under launch conditions. The CubeSat simulation model of this invention not only resembles the satellite in appearance, showcasing its external shape and approximate internal layout, but also simulates the operation of key components during satellite orbit, the actions during launch, and the launch environment, integrating environmental testing into its design. This allows for a more comprehensive and immersive understanding of CubeSats.

[0067] Optional, the thermal control visualization component 5 includes:

[0068] The sealed container 51 is installed on the outside of one of the side panels 2, and the sealed container 51 is close to the high heat dissipation devices 7 arranged on several partitions 3.

[0069] Observation window 52 is provided on the sealed container 51;

[0070] Paraffin 53, several pieces of paraffin 53 are filled in a sealed container 51, and the several pieces of paraffin 53 are colored. Paraffin 53 is an existing mixture, and its characteristics such as large latent heat of phase change and stable chemical properties will not be elaborated here.

[0071] The collector 54 is installed on the partition 3 and surrounds the high-heat-dissipation device 7 on three sides. The collector 54 is inserted into the sealed container 51 and is made of copper. When the assembled cube model is started, or when the high-heat-dissipation device 7, which is close to the sealed container 51, is started alone, the heat emitted by the high-heat-dissipation device 7 is absorbed by the collector 54 as it continues to operate and generate heat. The collector 54 then transfers the heat to the sealed container 51. As the temperature rises, the paraffin 53 in the sealed container 51 begins to melt from the edge until it becomes liquid. This solid-liquid transition process can be clearly observed through the observation window 52. At this time, even if the high-heat-dissipation device 7 continues to generate heat and the surrounding heat flow continues, the rate of temperature rise of the high-heat-dissipation device 7 will be significantly slowed down. After the high-heat-dissipation device 7 is turned off, as the heat source disappears, the paraffin 53 in the sealed container 51 will gradually cool and solidify until it becomes solid again. During the solidification process of the paraffin 53, its latent heat releases... Heat is continuously transferred to the high heat-dissipating device 7 through the collecting component 54, thereby achieving the effect of heating the high heat-dissipating device 7, significantly slowing down the rate of temperature drop of the high heat-dissipating device 7, vividly simulating the working principle of the satellite's "thermal control system", and this process can be expressed through changes in the state of matter, indirectly and intuitively demonstrating the working principle of the satellite's "thermal control system", effectively helping people understand why the "thermal control system" is the "life guarantee" of the satellite, greatly improving the effect of practical application in teaching or popular science research; the use of colored paraffin 53 makes people more clearly and intuitively see the process of paraffin 53 absorbing heat and melting to cool the high heat-dissipating device 7, and then dissipating heat to heat the high heat-dissipating device 7; the sealed container 51 is installed on the outside of the side panel 2 so that it protrudes from the cube satellite model, so that the sealed container 51 is not obstructed by other parts, making it easy for people to observe, or the sealed container 51 can be installed inside the cube satellite model, making it easier for people to understand the internal layout of the cube satellite.

[0072] Optionally, the thermal control visualization component 5 also includes: a thermochromic ink layer coated on the outer surface of the sealed container 51;

[0073] The thermochromic ink layer changes color with the temperature of the sealed container 51. At low temperatures (below 30 degrees Celsius), the ink layer displays one color; at high temperatures (above 70 degrees Celsius), it changes to another color. During the heat absorption and melting process of the paraffin wax 53, the color of the thermochromic ink layer gradually changes from the low-temperature representative color to the high-temperature representative color. This visually indicates the heat absorption of the sealed container 51 and the rising temperature of the high-heat-dissipation device 7. As the paraffin wax 53 begins to dissipate heat and solidify, the color of the thermochromic ink layer again gradually changes from the high-temperature representative color to the low-temperature representative color. This demonstrates the transfer of heat from the sealed container 51 and paraffin 53 to the high-heat-loss device 7. The thermochromic ink layer can also be directly applied to the high-heat-loss device 7, allowing for a more direct observation of the temperature change process of the high-heat-loss device 7. Based on the morphological changes of paraffin 53, color changes are used again to explain the working principle of the satellite's "thermal control system," more vividly simulating the working principle of the satellite's "thermal control system." This process is transformed into a dynamic phenomenon visible to the naked eye through both changes in physical state and color changes, further aiding in understanding.

[0074] Optionally, the ejection component 6 includes:

[0075] Base 61, which is placed horizontally and has a handle on its side;

[0076] Several foundation kits 62 are mounted on the base 61 and arranged in a square pattern;

[0077] Several sliding members 63 are respectively slidably inserted into several bottom parts 62, and the vibration test assembly 4 is installed on top of several sliding members 63.

[0078] Top plate 64, top plate 64 is centered and attached to the bottom of vibration test component 4;

[0079] The first spring 65 is mounted on the base 61 and connected to the top plate 64;

[0080] Vertical rail 66 is fixed to the side of base 61;

[0081] Pull handle 67 is connected to top plate 64 and slides along vertical rail 66. In normal operation, first spring 65 is fully extended, lifting vibration test component 4 and its cube satellite model. Holding pull handle 67 and pulling it down moves it downwards along vertical rail 66, pulling down top plate 64 and compressing first spring 65. This causes several sliding members 63 to re-insert into several bottom components 62 until all sliding members 63 are fully inserted into the bottom components 62, completing the accumulation of elastic energy of first spring 65. This lowers vibration test component 4 and its cube satellite model to their lowest position. Releasing pull handle 67 causes first spring 65 to instantly rebound, the rebound force pushing the sliding members... The 63 mechanism quickly lifts up the vibration test component 4 and the CubeSat model on it, thus simulating the crucial action of the CubeSat's ejection and separation from the launch vehicle. During this process, people can manually accumulate energy and trigger its release, demonstrating the realistic physical process of storing energy and releasing it instantaneously to generate impact, resulting in excellent simulation effects. The tails of the several sliding components 63 must not detach from the several base components 62 to ensure that the vibration test component 4 and the CubeSat model on it do not fall off. The spring force coefficient of the first spring 65 must ensure that the vibration test component 4 and the CubeSat model are ejected instantaneously to ensure the simulation of the CubeSat's ejection and separation from the launch vehicle.

[0082] Optionally, vibration testing component 4 includes:

[0083] Several connecting units 41 are respectively installed on the top of several sliding parts 63;

[0084] Several second springs 42 are respectively installed on several connecting platforms 41;

[0085] Platform 43 is mounted on several second springs 42, several prisms 1 are mounted on platform 43, and top plate 64 is centered on the bottom of platform 43;

[0086] Side hanging plate 44, the side hanging plate 44 is connected to the side of the platform 43;

[0087] The vibrator 45 is mounted on the side hanging plate 44. The vibrator 45 is an existing mechanical device, which will not be described in detail here. Activating the vibrator 45 can generate excitation force, thereby causing the platform 43 and the cube satellite model to vibrate. This causes the cube satellite model to vibrate at a high frequency, which in turn causes several prisms 1, several side panels 2, several partitions 3, and all the sub-parts on them to vibrate continuously and at a high frequency. This simulates the launch environment of the cube satellite model, enabling people to conduct vibration tests on the cube satellite model immediately after assembly. It simulates the environmental factors affecting the cube satellite model under launch conditions, helping people to conduct effective engineering practice to verify whether the designed model structure is robust and can survive in the launch environment.

[0088] Optionally, the thermal control visualization component 5 also includes:

[0089] Gooseneck tube 55, one end of which is connected to the side of platform 43;

[0090] The carrier dish 56 is connected to the other end of the gooseneck tube 55. A heat source is installed inside the carrier dish 56, and the carrier dish 56 and the heat source face the sealed container 51. The heat source can be a high-power incandescent lamp, heating wire, etc. The heat source is activated at the same time as the high heat dissipation device 7, so that it irradiates one side of the sealed container 51 from the outside, thereby simulating the solar radiation heating received by the satellite in orbit. At this time, the high heat dissipation device 7 will heat up more rapidly under the irradiation of the heat source, making the simulation environment closer to the actual situation. On the one hand, it improves the simulation effect, and on the other hand, it makes the changes of paraffin 53 and thermochromic ink layer more obvious, further helping people to observe and understand better. The gooseneck tube 55 can be twisted and shaped at will, so that the heat source can irradiate the sealed container 51 from different angles to obtain a more realistic simulation effect. When the vibrator 45 is activated, the heat source can be removed from the carrier dish 56 to prevent the heat source from malfunctioning due to violent vibration.

[0091] Optionally, the high heat dissipation device 7 is a surface mount resistor. A surface mount resistor is an existing type of resistor. Using a surface mount resistor as the high heat dissipation device 7, the power of the surface mount resistor can be controlled by adjusting the circuit, thereby adjusting the heat generation and heating temperature, and thus simulating different working states of a CubeSat. It can also make the simulation effect more apparent in a short period of time.

[0092] An aluminum shell 8 is provided between two prisms 1 on opposite sides of the high heat dissipation device 7 and the sealed container 51. The aluminum shell 8 is coated with a high emissivity coating to simulate the heat dissipation surface of the satellite, making the simulation effect closer to reality.

[0093] Optionally, the ejection component 6 also includes:

[0094] Two impact cylinders 68 are mounted on the base 61 and located on both sides of the first spring 65. The output shafts of the two impact cylinders 68 face the bottom of the platform 43. The impact cylinders 68 are existing actuators with high impact force. When the handle 67 is released and the first spring 65 rebounds, the two impact cylinders 68 are activated, causing their output shafts to complete a push-out and retraction action. Together with the first spring 65, they quickly push the platform 43 upward, ensuring that the CubeSat model is ejected instantly to simulate the ejection and separation of the CubeSat from the launch vehicle. At the same time, the impact force of the two impact cylinders 68 is used to realistically simulate the impact force and motion state of the CubeSat during separation, and can also realize environmental testing of the assembled CubeSat model.

[0095] Optionally, a telescopic rod 9 is provided inside the first spring 65;

[0096] The telescopic rod 9 is installed on the base 61 and connected upward to the top plate 64. The first spring 65 is in contact with the telescopic rod 9. When the top plate 64 moves down, the telescopic rod 9 can be compressed to shorten it. The telescopic rod 9 is used to shape the first spring 65, ensuring that the first spring 65 moves straight up and down without deformation.

[0097] Optionally, rubber sheets 10 are installed on the output shafts of the two impact cylinders 68 to prevent excessive noise from the output shafts of the two impact cylinders 68 after impacting the platform 43, and to prevent the hard output shafts from directly acting on the platform 43 and causing damage to it.

[0098] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A cube-shaped simulated satellite model, characterized in that, include: Several prisms (1), and several of the prisms (1) are arranged in a square; Several side panels (2) are installed between several prisms (1), and the several side panels (2) and several prisms (1) together form a cube; Several partitions (3) are arranged sequentially inside a cubic body composed of several side panels (2) and several prisms (1); Vibration test assembly (4), several prisms (1) are mounted on the vibration test assembly (4), the vibration test assembly (4) can excite several prisms (1), several side panels (2) and several partitions (3) to cause them to resonate; Thermal control visualization component (5), the thermal control visualization component (5) is disposed on the side panel (2), the partition (3) and the vibration test component (4), the thermal control visualization component (5) is used to actively absorb and release heat and accompany changes in physical state and color; The spring-off component (6) is connected below the vibration test component (4). The spring-off component (6) can accumulate energy under the action of external force and use it to push the vibration test component (4) upward so that the vibration test component (4) can move. The thermal control visualization component (5) includes: a sealed container (51), which is installed on the outside of one of the side panels (2) and is close to the high heat dissipation devices (7) disposed on several of the partitions (3). An observation window (52) is provided on the sealed container (51); Paraffin wax (53), several pieces of said paraffin wax (53) are filled in the sealed container (51), and several pieces of said paraffin wax (53) are colored; The collecting component (54) is installed on the partition (3) and surrounds the high heat loss device (7) on three sides. The collecting component (54) is inserted into the sealed container (51) and the material of the collecting component (54) is copper. The thermal control visualization component (5) further includes: a thermochromic ink layer coated on the outer surface of the sealed container (51); The thermochromic ink layer changes color as the temperature of the sealed container (51) changes; The thermal control visualization component (5) further includes: a gooseneck tube (55), one end of which is connected to the side of the vibration test component (4); The carrier dish (56) is connected to the other end of the gooseneck tube (55). A heat source is provided inside the carrier dish (56). The carrier dish (56) and the heat source face the sealed container (51).

2. The cube-shaped satellite simulation model as described in claim 1, characterized in that, The ejection assembly (6) includes: The base (61) is horizontally placed and has a handle on its side; A plurality of base kits (62) are mounted on the base (61) and arranged in a square pattern; A plurality of sliding members (63) are slidably inserted into a plurality of bottom parts (62), and the vibration test assembly (4) is installed on top of the plurality of sliding members (63); Top plate (64), which is centrally attached to the bottom of the vibration test assembly (4); A first spring (65) is mounted on the base (61) and connected to the top plate (64). A vertical rail (66) is fixed to the side of the base (61); A handle (67) is connected to the top plate (64) and slides through the vertical rail (66).

3. The cube-shaped satellite simulation model as described in claim 2, characterized in that, The vibration testing component (4) includes: A plurality of connecting platforms (41) are respectively installed on the top of a plurality of sliding members (63); A plurality of second springs (42) are respectively mounted on a plurality of the aforementioned connecting platforms (41); Platform (43), the platform (43) is mounted on several second springs (42), several prisms (1) are mounted on the platform (43), the top plate (64) is centrally attached to the bottom of the platform (43), and the gooseneck tube (55) is connected to the side of the platform (43); Side hanging plate (44), the side hanging plate (44) is connected to the side of the platform (43); Vibrator (45), which is mounted on the side hanging plate (44).

4. The cube-shaped satellite simulation model as described in claim 3, characterized in that: The high heat dissipation device (7) is a chip resistor; An aluminum shell (8) is provided between the two prisms (1) on the opposite side of the high heat dissipation device (7) and the sealed container (51), and the aluminum shell (8) is coated with a high emissivity coating.

5. The cube-shaped satellite simulation model as described in claim 4, characterized in that, The ejection assembly (6) also includes: Two impact cylinders (68) are mounted on the base (61) and located on both sides of the first spring (65), with the output shafts of the two impact cylinders (68) facing the bottom of the platform (43).

6. The cube-shaped satellite simulation model as described in claim 5, characterized in that: The first spring (65) has a telescopic rod (9) inside; The telescopic rod (9) is mounted on the base (61) and connected upward to the top plate (64).

7. The cube-shaped satellite simulation model as described in claim 6, characterized in that: Rubber sheets (10) are mounted on the output shafts of the two impact cylinders (68).

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