A bionic 4D printed multi-factor triggered satellite locking and releasing device

Abstract

The present invention discloses a bionic 4D printing multi-factor triggered satellite locking and releasing device, belonging to the field of aerospace and bionic 4D printing technology. It comprises: an electromagnetic radiation-proof heat-insulating shell, an upper shape memory bionic locking mechanism, a satellite buffer heat-insulating fixing platform, a lower shape memory bionic locking mechanism, a telescopic energy storage ejection mechanism, and a rocket connection base. The upper shape memory bionic locking mechanism is an electrostrictive shape memory structure, which serves as the satellite's primary locking and releasing mechanism. The satellite buffer heat-insulating fixing platform is evenly distributed with locking grooves, which serves as the satellite's lower shape memory bionic locking mechanism. The satellite is locked or separated with the device through the magnetic shape memory T-shaped locking parts evenly distributed at the bottom, which serves as the satellite's secondary locking and releasing mechanism. The lower side of the satellite buffer heat-insulating fixing platform is evenly distributed with a telescopic energy storage ejection mechanism, which is composed of a shape memory spring and a shape memory electrostrictive sheet, and is connected to the lower end of the electromagnetic radiation-proof heat-insulating shell. The device has fast response, low impact, and high reliability.

Description

Technical Field

[0001] The present invention belongs to the field of bionic 4D printing and aerospace technology, and particularly relates to a bionic 4D printing multi-factor triggered satellite locking and releasing device. Background Art

[0002] As a traditional satellite locking and releasing device, the pyrotechnic locking and releasing mechanism is the most widely used in space locking and releasing mechanisms. However, with the continuous improvement of safety requirements for rocket and satellite launch in the orbit phase, especially in the context of the rapid development of microsatellites in the new era, the pyrotechnic locking and releasing mechanism has gradually exposed its limitations. The impact of its release device is large and may affect the separation posture of the satellite. For microsatellites, this impact force may cause damage to the precision parts of the microsatellites.

[0003] Shape memory polymer satellite locking and release devices are an advanced technology that has played a vital role in satellite launches in recent years. Their primary function is to provide and achieve high-rigidity locking to ensure satellite stability during launch. Once the satellite successfully enters orbit, the device enables stable, impact-free unlocking and release.

[0004] The key is to incorporate shape memory polymer components into the locking and release mechanisms. The shape memory polymer composite material used is a fast-response memory material. When the satellite needs to be released, the locking and release mechanisms can be automatically deformed through electrical, magnetic, or thermal actuation. This allows for minimal or even no impact unlocking of the satellite, preventing damage to the satellite's structure and function during the unlocking process and ensuring the normal operation and use of the satellite after release. Summary of the Invention

[0005] In order to solve the problems of release impact force, non-repeatable locking and releasing faced by traditional satellite locking and releasing devices during use, a bionic 4D printed multi-factor triggered satellite locking and releasing device is proposed.

[0006] A bionic 4D printed multi-factor triggered satellite locking and releasing device, comprising:

[0007] The invention relates to an electromagnetic radiation-proof heat-insulating shell 1, an upper shape memory bionic locking mechanism 2, a satellite buffer heat-insulating fixing platform 3, a lower shape memory bionic locking mechanism 4, a telescopic energy storage ejection mechanism 5, and a rocket connection base 6, wherein: the satellite buffer heat-insulating fixing platform 3 is located in the electromagnetic radiation-proof heat-insulating shell 1, and the two are slidably connected; the upper shape memory bionic locking mechanism (2) is a lockable and release memory structure, which is integrally printed with the upper port of the electromagnetic radiation-proof heat-insulating shell 1; the satellite buffer heat-insulating fixing platform 3 is uniformly distributed with lower shape memory bionic locking mechanisms. The satellite is locked or separated from the locking groove 401 of the shape memory bionic locking mechanism 4 by the shape memory T-shaped locking member 402 of the lower shape memory bionic locking mechanism 4 uniformly distributed on its lower part; the telescopic energy storage ejection mechanism 5 with the same structure is uniformly distributed on the circumference of the lower side of the satellite buffer and heat insulation fixed platform 3. The telescopic energy storage ejection mechanism 5 is composed of a spring 501 and a shape memory telescopic sheet 502. The upper ends of both are fixed to the lower side of the satellite buffer and heat insulation fixed platform 3, and the lower ends are fixed to the rocket connection base 6. The upper shape memory telescopic energy storage mechanism 2 is a three-layer structure in the shape of a "spring sheet", consisting of a shape memory layer I 201, an insulating layer 202, and a shape memory layer II 203. The shape memory layer I 201 and the shape memory layer II 203 are made of nickel-titanium memory alloy. Both are equipped with a heating wire and a power supply circuit I on the outside. When powered on, they will expand, and when powered off, they will contract and return to their initial state.

[0008] The shape memory T-shaped locking piece 402 of the lower shape memory bionic locking mechanism 4 is composed of a support and a shape memory bending piece. The shape memory T-shaped locking piece 402 has two states, one is the upward bending state 402a of the shape memory bending piece and the other is the downward bending state 402b of the shape memory bending piece. The shape memory bending piece is located at the lower end of the T-shaped locking piece 402 and is in the shape of a strip, and is made of magneto-memory material. When positive and negative electric fields are added, the two ends of the strip-shaped shape memory bending piece will bend downward and upward.

[0009] The shape memory expansion piece 502 of the telescopic energy storage ejection mechanism 5 is composed of alternating vertical short plates 502b and vertical long plates 502a, with both ends being vertical short plates 502b. A heating wire and a power supply circuit II are provided on the outside of the telescopic energy storage ejection mechanism 5. When powered on and heated, the shape memory expansion piece 502 contracts and deforms into a multi-Z shape, compressing the spring 501. After power is turned off and cooled, the expansion piece 502 returns to its initial vertical state.

[0010] The vertical short plate (502b) is printed along a horizontal path, and the vertical long plate (502a) is printed along a vertical path, and the horizontal and vertical paths are alternately printed to form an integrated telescopic energy storage ejection mechanism (5);

[0011] The power supply circuit I in the upper shape memory bionic locking mechanism 2 and the power supply circuit II in the telescopic energy storage ejection mechanism 5 are synchronously powered by the same power supply to ensure the synchronization of deformation and energy storage of the device.

[0012] The satellite buffer insulation fixing platform 3 is a truncated platform with shaft-connected pulleys 301 evenly distributed on it. The pulleys 301 are all located in the slide rails of the cylindrical anti-electromagnetic radiation insulation shell 1; the surface of the pulleys 301 is provided with an anti-electromagnetic radiation insulation coating.

[0013] Another object of the present invention is to provide a method for using a bionic 4D printed multi-factor triggered satellite locking and releasing device:

[0014] 1) Satellite Locking: The shape memory layer II 203 of the upper shape memory bionic locking mechanism 2 is energized to bend downward, achieving primary locking of the satellite. After cooling, it can be restored to its initial horizontal position by reheating. A positive magnetic field is applied to the shape memory bending sheet, causing its ends to bend upward. The satellite is aligned with the locking groove 401 through the shape memory T-shaped locking member 402 at the lower end and inserted. The magnetic field is then disconnected or reversed, completing secondary locking of the satellite relative to the satellite buffer and thermal insulation mounting platform 3.

[0015] 2) Energy storage for satellite ejection and release: Power is supplied to the power supply circuit I in the shape memory bionic locking mechanism 2 and the power supply circuit II in the telescopic energy storage ejection mechanism 5 simultaneously through the same power supply. The heating wire is heated, and the shape memory expansion piece 502 of the telescopic energy storage ejection mechanism 5 contracts and deforms into a multi-Z shape due to the heat. At the same time, a downward force is applied to the spring 501, storing energy for the satellite ejection and release.

[0016] 3) Unlocking and ejection release of the satellite: Power is supplied to the power supply circuit I in the upward shape memory bionic locking mechanism 2 and the power supply circuit II in the telescopic energy storage ejection mechanism 5. At the same time, a reverse magnetic field is applied to the shape memory T-shaped locking member 402 of the lower shape memory bionic locking mechanism 4. The shape memory layer I 201 is energized to bend upward, providing a channel for the release of the satellite, performing a first unlocking operation. After cooling and reheating, it can be restored to its initial horizontal state. The shape memory T-shaped locking member 402 is bent downward to form the downwardly bent shape 402b of the shape memory bending piece, disengaging from the locking groove 401, performing a second unlocking operation. The shape memory telescopic piece 502 of the telescopic energy storage ejection mechanism 5 is energized to restore its initial vertical state, releasing the force of the spring 501, releasing elastic potential energy and pushing the satellite upward. When the satellite reaches a certain position, it separates from the satellite buffer and thermal insulation fixing platform 3, completing the ejection release of the satellite.

[0017] The invention discloses a bionic 4D printing multi-factor triggered satellite locking and releasing device, which belongs to the field of bionic 4D printing technology. The device comprises: an electromagnetic radiation-proof heat-insulating shell, an upper shape-memory bionic locking mechanism, a satellite buffer and heat-insulating fixing platform, a lower shape-memory bionic locking mechanism, a telescopic energy storage ejection mechanism, a rocket connection base, and a satellite, wherein: the satellite buffer and heat-insulating fixing platform is located in the electromagnetic radiation-proof heat-insulating shell and slides; the upper shape-memory bionic locking mechanism is an electrostrictive shape memory structure, which bends and deforms upward or downward to become a primary locking and releasing mechanism of the satellite, and is integrally formed and printed with the electromagnetic radiation-proof heat-insulating shell; locking grooves are evenly distributed on the satellite buffer and heat-insulating fixing platform, which serve as the satellite's lower shape-memory bionic locking mechanism, and the satellite is locked or separated therefrom by magnetic shape-memory T-shaped locking pieces evenly distributed on the lower part, which serve as the satellite's secondary locking and releasing mechanism; the telescopic energy storage ejection mechanism is evenly distributed on the lower side of the satellite buffer and heat-insulating fixing platform, which is composed of a shape-memory spring and a shape-memory electrostrictive sheet, and is connected to the lower end of the electromagnetic radiation-proof heat-insulating shell at the lower end. In summary, this device can realize the locking and ejection release of the satellite with fast response, small impact and high reliability.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The device of the present invention adopts bionic thinking and special materials of 4D printing to design a new satellite locking and ejection release mechanism. The satellite locking and ejection release are achieved through the deformation of magneto- and electro-mechanical shape memory composite materials, achieving intelligent and rapid response and enhancing the applicability of the device.

[0020] 2. The device of the present invention has a sophisticated structure and can be designed and manufactured in a miniaturized and lightweight manner compared to traditional locking mechanisms, making it more competitive in micro-satellite applications. It also has a high degree of integration and is easy to operate and control.

[0021] 3. The device of the present invention cleverly utilizes the deformation of shape-memory composite materials and springs to elastically store energy. The three-layer "spiral-shaped" structure of the upper portion is designed to mimic the up-and-down swinging motion of a fish's tail, while the multiple sets of shape-memory telescopic energy storage mechanisms in the lower portion are designed to mimic the tentacles of an octopus. After elastic energy storage, it is released to apply the force to the satellite for catapult launch. The present invention greatly reduces the impact force on the satellite during the release process, thereby improving safety and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the overall structure of a bionic 4D printing multi-factor triggered satellite locking and releasing device of the present invention;

[0023] Figure 2 This is a schematic diagram of the specific structure of the upper shape memory bionic locking mechanism of a bionic 4D printing multi-factor triggered satellite locking and releasing device of the present invention;

[0024] Figure 3 This is a schematic diagram of the three-dimensional structure of a satellite buffer fixing platform and a telescopic energy storage ejection mechanism of a bionic 4D printing multi-factor triggered satellite locking and releasing device of the present invention;

[0025] Figure 4 This is a schematic diagram of the lower shape memory bionic locking mechanism and its operating principle of a bionic 4D printed multi-factor triggered satellite locking and releasing device of the present invention;

[0026] Figure 5 This is a schematic diagram of the specific structure of the telescopic energy storage ejection mechanism of the bionic 4D printing multi-factor triggered satellite locking and releasing device of the present invention.

[0027] In the accompanying drawings

[0028] 1. Anti-electromagnetic radiation heat insulation shell; 6 rocket connection base;

[0029] 2. Upper shape memory bionic locking mechanism; 201. Shape memory layer I; 202. Insulation layer; 203. Shape memory layer II;

[0030] 3. Satellite buffer insulation fixed platform; 301. Pulley;

[0031] 4. Lower shape memory bionic locking mechanism; 401. Locking groove; 402. Shape memory T-shaped locking member; 402a. Shape memory bending piece in upward bending state; 402b. Shape memory bending piece in downward bending state;

[0032] 5. Telescopic energy storage ejection mechanism; 501. Spring; 502. Shape memory telescopic sheet; 502a. Vertical long plate; 502b. Vertical short plate. DETAILED DESCRIPTION

[0033] Below in conjunction with the present invention Figure 1-5 The present invention is further described in detail with reference to the following specific embodiments. It should be noted that the following embodiments are only some embodiments of the present invention.

[0034] Example 1

[0035] A bionic 4D printing multi-factor triggered satellite locking and releasing device comprises: an anti-electromagnetic radiation heat-insulating shell 1, an upper shape memory bionic locking mechanism 2, a satellite buffer heat-insulating fixing platform 3, a lower shape memory bionic locking mechanism 4, a telescopic energy storage ejection mechanism 5, and a rocket connection base 6, wherein: the satellite buffer heat-insulating fixing platform 3 is located in the anti-electromagnetic radiation heat-insulating shell 1, and the two are slidably connected; the upper shape memory bionic locking mechanism 2 is a lockable and release memory structure, which is integrally printed with the upper port of the anti-electromagnetic radiation heat-insulating shell 1; ... lower shape memory bionic locking mechanism 4 is a telescopic energy storage ejection mechanism 5, and a rocket connection base 6. The locking grooves 401 of the lower shape memory bionic locking mechanism 4 are evenly distributed on the thermal insulation fixed platform 3, and the satellite is locked or separated from the locking groove 401 by the shape memory T-shaped locking parts 402 of the lower shape memory bionic locking mechanism 4 evenly distributed on its lower part; the telescopic energy storage ejection mechanism 5 with the same structure is evenly distributed on the circumference of the lower side of the satellite buffer thermal insulation fixed platform 3, and the telescopic energy storage ejection mechanism 5 is composed of a spring 501 and a shape memory telescopic piece 502, the upper ends of both are fixed to the lower side of the satellite buffer thermal insulation fixed platform 3, and the lower ends are fixed to the rocket connection base 6.

[0036] The upper shape memory bionic locking mechanism 2 is composed of three stacked layers: shape memory layer I 201, insulating and heat-insulating layer 202, and shape memory layer II 203. The shape memory layer I 201 and shape memory layer II 203 are made of shape memory polymer materials. Both layers of shape memory material are provided with heating wires and power supply circuit I. When the shape memory layer II 203 is energized, it can bend downward, and after cooling and heating again, it can be restored to its initial horizontal state. When the shape memory layer I 201 is energized, it can bend upward, and after cooling and heating again, it can be restored to its initial horizontal state. In the actual manufacturing of the insulating and heat-insulating layer 202, polyimide (PI)-based composite materials can be selected.

[0037] The four shape memory T-shaped locking members 402 of the lower shape memory bionic locking mechanism 4 are composed of pillars and shape memory bending pieces. The height of the pillars is consistent with the thickness of the satellite buffer and thermal insulation fixing platform 3. The shape memory bending piece is located at the lower end of the T-shaped locking member 402 and is in the shape of a strip. Figure 4 In actual manufacturing, it is made of magnetic shape memory polymer material (such as SMPs + magnetic particles, with a magnetic particle content of 20%-40%) and printed horizontally and reciprocatingly; when a magnetic field is applied, the two ends of the strip-shaped shape memory bending piece will bend upward, and at this time the distance between the two ends is smaller than the scale of the locking groove 401, and the piece can enter the locking groove 401; after the magnetic field is cut off, the shape memory bending piece will return to its original straight state; when the magnetic field is applied again, the two ends of the strip-shaped shape memory bending piece will bend downward, and at this time the distance between the two ends is still smaller than the scale of the locking groove 401, and the piece can go out of the locking groove 401; after the magnetic field is cut off, the shape memory bending piece will return to its original straight state; the applied magnetic field is located on the pillar.

[0038] The shape memory expansion piece 502 of the lower shape memory expansion energy storage mechanism 5 is composed of alternately connected vertical short plates 502b and vertical long plates 502a, and both ends are vertical short plates 502b; the shape memory expansion piece 502 is made of shape memory polymer according to the attached Figure 5 The shape memory expansion sheet 502 is printed with an alternating vertical and horizontal printing path; a heating wire and a power supply circuit II are provided on the outside of the shape memory expansion sheet 502. When the electric heating is applied, the angle between the vertical short plate 502b and the oblique long plate 502a changes from 180° to 135°, and the shape memory expansion sheet 502 becomes a multi-"Z" shape, i.e., it shrinks and deforms; after the power is turned off and the sheet cools down, it returns to its initial vertical state; in actual manufacturing, the angle between the vertical short plate 502b and the vertical long plate 502a is controlled to be a minimum of 135° to avoid breakage or permanent deformation of the shape memory expansion sheet 502.

[0039] The power supply circuit I in the upper shape memory bionic locking mechanism 2 and the power supply circuit II in the telescopic energy storage ejection mechanism 5 are synchronously powered by the same power supply to ensure the synchronization of deformation and energy storage of the device.

[0040] The satellite buffering and heat-insulating fixed platform 3 is circular and has four pulleys 301 evenly distributed on it. The pulleys 301 are all located in the slide rails at corresponding positions on the inner side of the cylindrical anti-electromagnetic radiation heat-insulating shell 1. The surface of the pulley 301 is provided with an anti-electromagnetic radiation heat-insulating coating; the satellite buffering and heat-insulating fixed platform 3 slides linearly on the inner side of the anti-electromagnetic radiation heat-insulating shell 1.

[0041] Example 2

[0042] In this embodiment, after the magnetic field shape memory bending piece enters the locking groove 401, a reverse magnetic field is applied, and the shape memory bending piece returns to its initial flat state, further strengthening the locking force between the satellite buffer insulation fixing station 3 and the satellite.

[0043] The present invention provides a bionic 4D printing multi-factor triggered satellite locking and releasing device, and its specific use method is as follows:

[0044] Step 1: Locking the Satellite

[0045] The shape memory layer II (203) of the upper shape memory bionic locking mechanism (2) is energized to bend downward, and the satellite enters for a primary locking, and after cooling and reheating, it can be restored to its initial horizontal state. A positive magnetic field is applied to the shape memory bending sheet, and its two ends are bent upward; the satellite is aligned with the locking groove 401 through the shape memory T-shaped locking piece 402 at the lower end and inserted, and then the reverse magnetic field is cut off or applied to complete the secondary locking of the satellite relative to the satellite buffer and thermal insulation fixing platform 3;

[0046] Step 2: Stored energy released by satellite ejection

[0047] The power supply circuit I in the shape memory bionic locking mechanism 2 and the power supply circuit II in the telescopic energy storage ejection mechanism 5 are powered synchronously by the same power supply, the electric heating wire is heated, and the shape memory telescopic sheet (502) of the telescopic energy storage ejection mechanism 5 shrinks and deforms into a multi-Z shape due to the heat, and at the same time exerts a downward force on the spring 501, thereby performing the stored energy for satellite ejection and release;

[0048] Step 3: Unlocking and ejecting the satellite

[0049] The power supply circuit I in the upper shape memory bionic locking mechanism 2 and the power supply circuit II in the telescopic energy storage ejection mechanism 5 are powered, and at the same time, a reverse magnetic field is passed through the shape memory T-shaped locking piece 402 of the shape memory bionic locking mechanism 4. The shape memory layer I 201 can bend upward when energized, providing a channel for the release of the satellite, performing one unlocking, and can be restored to the initial horizontal state after cooling and reheating; the shape memory T-shaped locking piece 402 bends downward to become the downward bent form 402b of the shape memory bending piece, disengaging from the locking groove 401, and performing a second unlocking; the shape memory telescopic piece 502 of the telescopic energy storage ejection mechanism 5 is energized to restore to the initial vertical state, releasing the force of the shape memory spring 501, releasing the elastic potential energy to push the satellite upward. When it reaches a certain position, the satellite separates from the satellite buffer and thermal insulation fixing platform 3 to complete the ejection release of the satellite.

Claims

1. A bionic 4D printed multi-factor triggered satellite locking and releasing device, comprising: An electromagnetic radiation-proof heat-insulating shell (1), an upper shape memory bionic locking mechanism (2), a satellite buffer heat-insulating fixed platform (3), a lower shape memory bionic locking mechanism (4), a telescopic energy storage ejection mechanism (5), and a rocket connection base (6), wherein: the satellite buffer heat-insulating fixed platform (3) is located in the electromagnetic radiation-proof heat-insulating shell (1), and the two are slidably connected; the upper shape memory bionic locking mechanism (2) is a lockable and releaseable memory structure, which is integrally printed with the upper port of the electromagnetic radiation-proof heat-insulating shell (1); the satellite buffer heat-insulating fixed platform (3) is uniformly distributed with lower shape memory bionic locking mechanisms. The satellite is locked or separated from the locking groove (401) by a shape memory T-shaped locking piece (402) of the lower shape memory bionic locking mechanism (4) uniformly distributed on the lower part thereof; a telescopic energy storage ejection mechanism (5) having the same structure and uniformly distributed on the circumference of the lower side of the satellite buffer and heat insulation fixed platform (3); the telescopic energy storage ejection mechanism (5) is composed of a spring (501) and a shape memory telescopic piece (502), the upper ends of which are fixedly connected to the lower side of the satellite buffer and heat insulation fixed platform (3), and the lower ends of which are fixedly connected to the rocket connection base (6); The upper shape memory bionic locking mechanism (2) is a three-layer structure in the shape of a spiral sheet, and is composed of a shape memory layer I (201), an insulating and heat-insulating layer (202), and a shape memory layer II (203). The shape memory layer I (201) and the shape memory layer II (203) are made of a shape memory polymer material. Both layers of shape memory material are provided with a heating wire and a power supply circuit I. When the shape memory layer II (203) is energized, it can bend downward, and after cooling, it can be heated again to restore to its initial horizontal state. When the shape memory layer I (201) is energized, it can bend upward, and after cooling, it can be heated again to restore to its initial horizontal state. The shape memory T-shaped locking member (402) of the lower shape memory bionic locking mechanism (4) is composed of a support and a shape memory bending piece. The shape memory T-shaped locking member (402) is composed of two states, namely, a shape memory bending piece bending upward (402a) and a shape memory bending piece bending downward (402b). The shape memory bending piece is located at the lower end of the T-shaped locking member (402) and is strip-shaped and made of magneto-memory material. When positive and negative electric fields are applied, the ends of the strip-shaped shape memory bending piece will bend downward and upward.

2. The bionic 4D printing multi-factor triggered satellite locking and releasing device according to claim 1, characterized in that: The shape memory telescopic piece (502) of the telescopic energy storage ejection mechanism (5) is composed of alternately connected vertical short plates (502b) and vertical long plates (502a), with both ends being vertical short plates (502b); The vertical short plate (502b) is printed along a horizontal path, and the vertical long plate (502a) is printed along a vertical path, and the horizontal and vertical paths are alternately printed to form an integrated telescopic energy storage ejection mechanism (5); The outer side of the telescopic energy storage ejection mechanism (5) is provided with a heating wire and a power supply circuit II. When the power is turned on and heated, the shape memory telescopic sheet (502) contracts and deforms into a multi-"Z" shape, compressing the spring (501); after the power is turned off and cooled, the sheet returns to its initial vertical state.

3. The bionic 4D printing multi-factor triggered satellite locking and releasing device according to claim 2, characterized in that: The power supply circuit I in the upper shape memory bionic locking mechanism (2) and the power supply circuit II in the telescopic energy storage ejection mechanism (5) are synchronously powered by the same power supply, thereby ensuring the synchronization of deformation and energy storage of the device.

4. The bionic 4D printing multi-factor triggered satellite locking and releasing device according to claim 3, characterized in that: The satellite buffer heat-insulating fixed platform (3) is a circular platform on which shaft-connected pulleys (301) are evenly distributed. The pulleys (301) are all located in the slide rails of the columnar anti-electromagnetic radiation heat-insulating shell (1); and the surface of the pulleys (301) is provided with an anti-electromagnetic radiation heat-insulating coating.

5. A bionic 4D printing multi-factor triggered satellite locking and releasing method, characterized by: A bionic 4D printing multi-factor triggered satellite locking and releasing device as described in claim 4 is used; 1) Locking of the satellite: the shape memory layer II (203) of the upper shape memory bionic locking mechanism (2) is energized to bend downward, and the satellite is locked once. After cooling, it can be heated again to restore to its initial horizontal state; a positive magnetic field is applied to the shape memory bending piece, and its two ends are bent upward; the satellite is aligned with the locking groove (401) through the shape memory T-shaped locking piece (402) at the lower end and inserted, and then the reverse magnetic field is cut off or applied to complete the secondary locking of the satellite relative to the satellite buffer and thermal insulation fixing platform (3); 2) Energy storage for satellite ejection and release: The power supply circuit I in the shape memory bionic locking mechanism (2) and the power supply circuit II in the telescopic energy storage ejection mechanism (5) are powered synchronously by the same power supply, the heating wire is heated, and the shape memory expansion piece (502) of the telescopic energy storage ejection mechanism (5) shrinks and deforms into a multi-"Z" shape due to the heat, and at the same time, a downward force is applied to the spring (501), thereby performing energy storage for satellite ejection and release; 3) Unlocking and ejection release of the satellite: power is supplied to the power supply circuit I in the upward shape memory bionic locking mechanism (2) and the power supply circuit II in the telescopic energy storage ejection mechanism (5), and at the same time, a reverse magnetic field is applied to the shape memory T-shaped locking member (402) of the lower shape memory bionic locking mechanism (4), so that the shape memory layer I (201) is energized to bend upward, providing a channel for the release of the satellite, performing one unlocking, and then being cooled and heated again to restore to the initial horizontal state; the shape memory T-shaped locking member (402) is bent downward to become a downwardly bent shape (402b) of the shape memory bending piece, and is separated from the locking groove (401), performing a second unlocking; the shape memory telescopic piece (502) of the telescopic energy storage ejection mechanism (5) is energized to restore to the initial vertical state, releasing the force of the spring (501), releasing the elastic potential energy and pushing the satellite upward. When the satellite reaches a certain position, the satellite is separated from the satellite buffer and heat insulation fixing platform (3), completing the ejection release of the satellite.

Images