A vibration isolation device for manually unlocking a spacecraft

Abstract

A manual unlocking vibration isolation device for spacecraft comprises a bottom plate (1), a machined spring (2), a rigid part (3), and a top plate (4) arranged in sequence from bottom to top; the bottom plate (1) of the vibration isolation device is connected and installed with the spacecraft through a central through hole, the lower end of the machined spring (2) is installed on a shorter square block of the bottom plate (1), the lower square block of the rigid part (3) is installed on a longer square block of the bottom plate (1), the upper end of the machined spring (2) is tightly connected to a higher square block of the upper stepped structure of the rigid part (3), and the top plate (4) is installed to the upper surface of the lower square block of the upper stepped structure of the rigid part (3), at which time the machined spring (2) is in a compressed state. The vibration isolation device of the present invention can withstand the launch load of the spacecraft in a locked state, and after the vibration isolation device is unlocked, the vibration source equipment, the vibration isolation device and the installation foundation form a completely elastic vibration isolation system. By adjusting the structural parameter design stiffness of the machined spring, it can adapt to the on-orbit vibration isolation of vibration source equipment of different spacecrafts.

Description

Technical Field

[0001] The invention belongs to the field of mechanical vibration isolation and relates to a spacecraft manual unlocking vibration isolation device, which is installed below a spacecraft vibration source device and isolates the disturbance output by the vibration source device after being manually unlocked by an astronaut in orbit. Technical Background

[0002] There are a large number of platforms and experimental payload equipment installed on manned spacecraft, space stations and other spacecraft, many of which are vibration source equipment with vibration disturbance, such as fans, fluid circuit pumps, compressors, momentum wheels, control torque gyroscopes, centrifuges, etc. The vibration caused by the operation of these equipment will put the sealed cabin in a high-noise environment, affecting the work and life of astronauts. At the same time, it will also increase the vibration of the spacecraft platform, making it impossible for high-precision and sensitive payloads to work normally. In order to reduce the interference of equipment vibration, vibration isolation is usually adopted for the vibration source equipment.

[0003] According to the literature "Testing and characterization of ISS pressurized modules vs. on-orbit

[0004] According to the report of the International Space Station, the vibration isolation equipment of the vibration source equipment adopts the vibration isolation equipment developed by the Italian Alenia Aerospace Company, as shown in the attached figure. Figure 1 The isolator is shown. The launch status is shown in the attached Figure 1 In the left picture, the mounting screws are tightened, the rubber is pressed, and the ear piece of the vibration source equipment is rigidly connected to the mounting base, which can resist the flight load of the spacecraft launch stage. See the attached figure for the weightlessness state on orbit. Figure 1 In the right picture, the astronaut loosens the mounting screw and the rubber rebounds after the screw returns 1mm, isolating the lower surface of the device ear from the mounting base by the rubber material, reducing the vibration transmitted to the mounting base when the device is working.

[0005] The vibration isolator solution used in the International Space Station has the following shortcomings: 1) After the screw returns 1mm, the upper surface of the device ear piece contacts the screw through the gasket, and the lower end of the screw is still connected to the screw hole of the installation foundation. Therefore, the vibration of the equipment can still be transmitted to the foundation through the upper surface of the ear piece through the screw, affecting the vibration isolation effect. 2) The elastic element is made of rubber material, which has nonlinear characteristics. When the vibration source equipment vibrates slightly (displacement is less than 10 microns), the stiffness of the rubber material is difficult to control, and the vibration isolation characteristics of the vibration isolation system cannot be accurately designed. 3) The distance of 1mm of the screw back screwed by the tool on orbit is difficult to control, which will affect the compression of the rubber element, thereby affecting its stiffness, making the vibration isolation performance of the vibration isolation system uncertain. In order to solve the above problems, it is necessary to invent a vibration isolation device for spacecraft vibration source equipment to achieve complete elastic isolation between the vibration source equipment and the installation foundation. The elastic element has linear stiffness characteristics under the condition of slight vibration. The vibration isolation characteristics of the vibration isolation system can be accurately designed to achieve an ideal vibration isolation effect. Summary of the invention

[0006] The technical problem solved by the present invention is: in view of the problems that the existing vibration isolator solutions for space stations have vibration transmission paths, nonlinear characteristics of rubber elements and uncontrollable compression that affect the vibration isolation effect, the present invention proposes a manual unlocking vibration isolation device for spacecraft, which realizes complete elastic isolation between the vibration source equipment and the installation base when the spacecraft is flying in orbit, and adopts a machined spring with linear stiffness characteristics as an elastic element, so that the vibration isolation system can achieve an ideal vibration isolation effect.

[0007] The technical solution of the present invention is: a manual unlocking vibration isolation device for spacecraft, comprising: a bottom plate, a machined spring, a rigid member, and a top plate arranged in sequence from bottom to top; wherein,

[0008] The bottom plate is composed of two square blocks of different lengths connected in the same plane, the longer square block has a through hole in the center, and the shorter square block has a threaded through hole matched with the machined spring;

[0009] The rigid member is composed of a lower square block, a middle cylindrical structure and an upper stepped structure, the three of which have concentric through holes passing through them, and the upper stepped structure has a threaded through hole that cooperates with the machined spring;

[0010] The top plate is formed by stacking two square blocks up and down, the length of the upper square block is smaller than the length of the lower square block, and the center of the top plate has a threaded through hole for installing and connecting the vibration source equipment;

[0011] The through hole passes through the bottom plate, the rigid member, and the top plate, and the centers of the holes coincide with each other;

[0012] The central through hole of the base plate is connected to the spacecraft through a screw and gasket combination, the lower end of the machined spring is installed on the threaded hole of the base plate, the lower square block of the rigid part is installed on the threaded hole of the longer square block of the base plate, and the top of the screw and gasket combination connected to the spacecraft is located in the through hole of the rigid part; the upper end of the machined spring is installed on the threaded hole of the upper stepped structure of the rigid part, and the machined spring is in a compressed state; the top plate is installed to the upper surface of the lower square block of the upper stepped structure of the rigid part.

[0013] Furthermore, the two square blocks of the bottom plate have rounded corners, and the two sides of the longer square block each have a threaded through hole; and the two sides of the shorter square block have threaded through holes.

[0014] Furthermore, the machine-added spring is of a stacked configuration, with a lug with a through hole extending outwardly from both sides of the upper and lower ends.

[0015] Furthermore, the lower square block of the rigid part has rounded corners and a threaded through hole on each side; the length of the upper stepped structure is smaller than that of the lower square block, and the upper stepped structure has two upper and lower square blocks and a facade vertically connected to the two, the upper and lower square blocks have rounded corners, the lower square block is provided with two threaded through holes, and the upper square block has a threaded through hole on each side of the circular hole.

[0016] Furthermore, when the spacecraft is launched, the vibration isolation device is in a locked state, at which time the machined spring is compressed, the rigid part is connected in parallel with the machined spring, and the rigid part bears the flight load.

[0017] Furthermore, after the spacecraft is launched into orbit, the two screw gasket combinations in the threaded through holes between the rigid part and the bottom plate are manually removed, the machined spring rebounds, the vibration isolation device is unlocked, and the combination of the rigid part, the top plate and the vibration source device is lifted.

[0018] Furthermore, after the vibration isolation device is unlocked, a gap of 1 mm is generated between the rigid part and the bottom plate part.

[0019] Furthermore, the transmission ratio T of the vibration isolation device and the stiffness k of the machined spring are determined according to the weight of the vibration source equipment and the magnitude and frequency of the vibration.

[0020]

[0021] Where T is the vibration transfer ratio, f is the disturbance frequency of the vibration source equipment, f0 is the natural frequency of the vibration isolation system, ξ is the damping ratio of the vibration isolation system, and the range of f / f0 is 2.5 to 5;

[0022] k=m(2πf0) 2

[0023] Where m is the weight of the vibration source equipment.

[0024] Furthermore, the base plate, rigid part and top plate are made of 2A14 aluminum alloy, and the machined spring is made of TC4 titanium alloy and is a transverse groove type machined spring.

[0025] Furthermore, the central through hole of the bottom plate of the vibration isolation device is connected and installed with the spacecraft through an M5 screw-gasket combination, the lower end of the machined spring is installed on the shorter square block of the bottom plate through two M3 screw-gasket combinations, the lower square block of the rigid part is installed on the longer square block of the bottom plate through two M4 screw-gasket combinations, the upper end of the machined spring is connected to the upper square block of the upper stepped structure of the rigid part through two M3 screw-gasket combinations, and the top plate is installed to the upper surface of the lower square block of the upper stepped structure of the rigid part through two M4 screw-gasket combinations; the vibration source equipment is installed on the upper end of the top plate of the vibration isolation device through an M5 screw-gasket combination.

[0026] The advantages of the present invention compared with the prior art are:

[0027] (1) After the vibration isolation device is manually unlocked on the track, the vibration source equipment, the vibration isolation device and the installation foundation form a completely elastic vibration isolation system. There is no other rigid connection path between the vibration source equipment and the installation foundation that affects the vibration isolation effect;

[0028] (2) The vibration isolator uses a machined spring as an elastic element, and the micro-vibration in the micrometer range has a linear stiffness characteristic without introducing nonlinear characteristics;

[0029] (3) The vibration isolation characteristics of the vibration isolation system can be precisely designed. By adjusting the structural parameters and design stiffness of the machine-added spring, it can adapt to the vibration isolation of equipment with different weights and disturbance frequencies to achieve an ideal vibration isolation effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 Vibration isolators developed for the Italian company Alenia Aerospace for use on the International Space Station.

[0031] Figure 2 Manually unlock the vibration isolation device components for the spacecraft.

[0032] Figure 3 Schematic diagram before and after unlocking the vibration isolation device installed on the vibration source equipment, (a) the two M4 screw-washer combinations 5 in the locked state of the vibration isolation device are removed on the track, (b) the vibration source equipment is lifted by 1 mm and a 1 mm gap is generated between the rigid part 3 and the base plate 1.

[0033] Figure 4 The diagram shows the working principle of the locking and unlocking states of the vibration isolation device, (a) the flight load transfer path in the launch locking state, and (b) the vibration transfer path of the equipment in the vibration isolation state after being unlocked on orbit.

[0034] Figure 5Vibration transfer ratio of the vibration isolation system and finite element mechanical analysis of the machined spring. (a) Vibration transfer ratio of the vibration isolation system, (b) finite element mechanical analysis of the spring.

[0035] Figure 6 It is a two-dimensional diagram of the vibration isolation device (locked state).

[0036] Figure 7 Schematic diagram of base plate 1.

[0037] Figure 8 are the structural parameters of machined spring 2.

[0038] Fig. 9 It is a schematic diagram of rigid part 3.

[0039] Fig.10 It is a schematic diagram of the top plate 4.

[0040] Fig.11 Schematic diagram of the assembly process of the vibration isolation device.

[0041] Fig.12 Schematic diagram of the installation and unlocking process of the vibration isolation device on the instrument panel. DETAILED DESCRIPTION

[0042] The components of the manual unlocking vibration isolation device for spacecraft of the present invention are shown in the attached Figure 2 , including: a bottom plate 1, a machined spring 2, a rigid part 3, a top plate 4, a plurality of M4 screw gasket assemblies 5, a plurality of M3 screw gasket assemblies 6, and an M5 screw gasket assembly 7. The bottom plate 1, the machined spring 2, the rigid part 3, and the top plate 4 are arranged in sequence from bottom to top.

[0043] The bottom plate 1 is a part composed of two square blocks of different lengths with rounded corners connected in the same plane. The center of the longer square block is the first through hole, and there is a threaded through hole on each side; the shorter square block extends outwardly into an arc structure, contains a lightening hole concentric with the arc structure, and has a threaded through hole on each side.

[0044] The machined spring 2 is a transverse groove type machined spring with a stacked configuration, a solid structure at the upper end and a hollow structure at the lower end, with a lug with a through hole extending outwardly from each side of the upper and lower ends.

[0045] The rigid part 3 is a part composed of a lower square block with rounded corners, a middle cylindrical structure and an upper stepped structure. The lower square block, the upper stepped structure and the middle cylindrical structure have concentric second through holes that penetrate the entire part. There is a threaded through hole on each side of the lower square block. The upper stepped structure is shorter than the lower square block and consists of three square blocks with rounded corners. The lower square block has a threaded through hole on each side. The higher square block has an extended arc structure, which contains a lightening hole concentric with the arc structure and has a threaded through hole on each side.

[0046] The top plate 4 is composed of two stacked square blocks. The length of the upper square block is smaller than that of the lower square block. The third through hole in the center of the top plate 4 runs through the entire part. This through hole is used to install and connect the vibration source equipment. There is a threaded through hole on each side of the longer square block below. The first, second, and third through holes run through the bottom plate 1, the rigid part 3, and the top plate 4, and the centers of the circles coincide.

[0047] The central through hole of the base plate 1 of the vibration isolation device is connected to the spacecraft instrument panel through an M5 screw-gasket combination 7; the lower end of the machined spring 2 is mounted on a shorter square block of the base plate 1; the lower square block of the rigid part 3 is mounted on a longer square block of the base plate 1; the upper end of the machined spring 2 is fastened to a higher square block of the upper stepped structure of the rigid part 3; and the top plate 4 is mounted to the upper surface of a lower square block of the upper stepped structure of the rigid part 3.

[0048] After the vibration isolation device is assembled and all fasteners are fastened in place, the machined spring 2 is in a compressed state, which is 1mm compressed compared to its free state. At this time, the vibration isolation device is in a locked state, and the rigid part 3 is connected in parallel with the machined spring 2. The rigid part 3 bears most of the flight load, which can prevent the machined spring 2 from being damaged by excessive load during the launch section. The bottom surface of the bottom plate 1 is the bottom surface for the installation of the vibration isolation device. The vibration isolation device is installed on the instrument board of the spacecraft through the M5 screw gasket combination 7 on the bottom plate 1. The upper end surface of the top plate 4 is the equipment installation surface of the vibration isolation device, and there is an M5 threaded through hole in the center. The vibration source equipment is installed on the upper end of the top plate 4 of the vibration isolation device through M5 screws.

[0049] The launch section vibration isolation device (locked state) of the spacecraft is installed on the instrument board of the spacecraft, and the vibration source equipment is installed on the upper end of the vibration isolation device. After the spacecraft is launched into orbit, the astronauts remove the two M4 screw gasket assemblies 5 between the rigid part 3 of the vibration isolation device and the bottom plate 1 on orbit, see the attached Figure 3 (a). In the weightless state, there is no gravity static load, the preload spring is released and returns to its original height, the rigid part 3 of the vibration isolation device and the combined connection structure of the top plate 4 and the vibration source equipment are lifted by 1mm, and a 1mm gap is generated between the rigid part 3 and the bottom plate 1, see the attached Figure 3 (b) Unlock the vibration isolation device. The vibration source device will vibrate when working. The vibration amplitude is generally below 10 microns. The 1 mm gap between the rigid part 3 and the bottom plate 1 provides space for the vibration source device to vibrate after isolation. The vibration isolation device can play a normal vibration isolation role.

[0050] See the attached diagram for the working principle of the vibration isolation device. Figure 4 .

[0051] When the spacecraft is launched, the vibration isolation device is locked, and the flight load of the spacecraft is rigidly transmitted to the equipment ear piece through the path of "bottom plate 1-rigid part 3-top plate 4", see the attached Figure 4As shown in the left figure, in this state, the vibration isolation device can resist the flight load of the launch section. The rigid part 3 is connected in parallel with the machined spring 2. The rigid part 3 bears most of the flight load, thereby preventing the machined spring 2 from being damaged by excessive load during the launch section.

[0052] After being manually unlocked by the astronauts on orbit, the vibration isolation device is in the vibration isolation state. The vibration of the vibration source equipment is transmitted to the instrument board through the path of "top plate 4-machined spring 2-bottom plate 1". See attached. Figure 4 In the right figure, the vibration source device and the instrument panel are elastically connected by machined spring 2 without any other rigid connection path, forming an ideal vibration isolation system, which can greatly attenuate the vibration of the vibration source device before it is transmitted to the instrument panel, thus playing a vibration isolation role.

[0053] According to the weight of the vibration source equipment and the magnitude and frequency of vibration, the structural parameters of the machined spring 2 are reasonably designed to accurately adjust the stiffness, so that the vibration isolation system can achieve the required low on-orbit transfer ratio. The transfer ratio of the vibration isolation system is calculated as follows:

[0054]

[0055] Where: T is the vibration transmission ratio, f is the disturbance frequency of the vibration source equipment (in Hertz (Hz)), f0 is the natural frequency of the vibration isolation system (in Hertz (Hz)), and ξ is the damping ratio of the vibration isolation system (valued at 0.03). According to the low vibration transmission ratio T to be achieved (such as 10%) and the known disturbance frequency f of the vibration source equipment, the natural frequency f0 of the vibration isolation system is selected. Generally, the range of f / f0 is 2.5 to 5. Then, according to f0, the stiffness k of spring 2 can be calculated as follows:

[0056] k=m(2πf0) 2 (2)

[0057] Where k is the spring stiffness and m is the weight of the vibration source equipment. The structural parameter design of the machined spring is completed based on k and finite element mechanics analysis.

[0058] For vibration source equipment using multiple vibration isolation devices, the finite element method can be used to complete the vibration transfer ratio calculation. After determining the spring stiffness, the vibration isolation system transfer ratio calculation results are shown in the attached Figure 5 (a) When the disturbance frequency of the vibration source equipment is higher than 100Hz, the vibration transmission ratio is lower than 10%. See the attached figure for the machined spring 2 designed based on finite element mechanical analysis. Figure 5 (b).

[0059] The dimensions of the vibration isolation device in the locked state are: 60mm (length) × 44mm (width) × 34mm (height, bottom to top), see the attached two-dimensional diagram Figure 6 , height 35mm after unlocking.

[0060] The base plate 1 is made of 2A14 aluminum alloy, with two M3 threaded holes on one side and one Φ5.5mm through hole and two M4 threaded through holes on the other side. Figure 7 .

[0061] The material of machined spring 2 is TC4 titanium alloy, which is a transverse groove machined spring. The main parameters are shown in the attached Figure 8 , typical parameters: outer diameter D is 20mm, inner diameter d is 16mm, layer height H is 3.3mm, slot width h is 2mm. The upper and lower ends of the spring each extend two lugs, and a Φ3.5mm through hole is set on the lug. See attached Figure 7 The finite element method is used to carry out calculation and analysis and optimize the structural parameters of the transverse groove machined spring (including outer diameter, inner diameter, layer height, groove width and other parameters) to make the spring stiffness reach the design target value, so that the vibration isolation system can achieve the required low transmission rate.

[0062] The material of rigid part 3 is 2A14 aluminum alloy, see the attached two-dimensional diagram Fig. 9 There is a cylindrical structure with an outer diameter of Φ20mm and an inner diameter of Φ13mm in the middle. In the locked state, the cylindrical structure provides high connection stiffness between the top plate and the bottom plate of the vibration isolation device, and the hollow part with an inner diameter of Φ13mm provides installation space for M5 screws on the bottom plate.

[0063] The top plate 4 is made of 2A14 aluminum alloy, with a height of 10.5 mm, an M5 threaded through hole in the middle, and two Φ4.5 mm through holes on both sides, see attached. Fig.10 .

[0064] The assembly process of the vibration isolation device is shown in the attached Fig.11 First, install the M5 screw gasket combination 7 into the central through hole of the bottom plate 1, and use two M3 screw gasket combinations 6 to install the lower end of the machined spring 2 on the bottom plate 1, and then use two M4 screw gasket combinations 5 to install the rigid part 3 on the bottom plate 1, and fasten the upper end of the machined spring 2 to the rigid part 3 with two M3 screw gasket combinations 6. At this time, the machined spring 2 is pre-compressed (compression amount 1mm), and then install the top plate 4 on the rigid part 3 with two M4 screw gasket combinations 5. After the assembly is completed, the vibration isolation device is in a locked state.

[0065] See the attached diagram for the installation and unlocking process of the vibration isolation device on the spacecraft instrument panel. Fig.12 , the description is as follows:

[0066] 1) Remove the top plate 4 and two M4 screw-washer assemblies 5 from the vibration isolation device. Fig.12 (a);

[0067] 2) Use the M5 screw and washer combination 7 to install the bottom plate 1 of the remaining part of the vibration isolation device on the spacecraft instrument panel, see the attached Fig.12 (b);

[0068] 3) Use two M4 screws and washers 5 to fix the top plate 4 to the upper end of the rigid part 3 of the vibration isolation device, see attached. Fig.12 (c) At this point, the vibration isolation device (locked state) has been installed on the instrument panel. See attached Fig.12 (d);

[0069] 4) Install the equipment on the upper end of the vibration isolation device with M5 screws. Fig.12 (e);

[0070] 5) After the spacecraft is launched into orbit, the astronauts use tools to remove the 2 M4 screw washers and 5 screws on the vibration isolation device, see attached Fig.12 (f) The vibration isolation device is unlocked and plays the role of on-track vibration isolation.

[0071] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A spacecraft manual unlocking vibration isolation device, characterized in that: include: A bottom plate (1), a machined spring (2), a rigid member (3), and a top plate (4) are arranged in sequence from bottom to top; wherein: The bottom plate (1) is composed of two square blocks of different lengths connected in the same plane, the longer square block having a through hole in the center, and the shorter square block having a threaded through hole matching the machined spring (2); the machined spring (2) is a stacked structure, with a lug with a through hole extending outwards from both sides of the upper and lower ends; The rigid part (3) is composed of a lower square block, a middle cylindrical structure and an upper stepped structure, the three of which have concentric through holes passing through them, and the upper stepped structure has a threaded through hole that matches the machined spring (2); the lower square block of the rigid part (3) has rounded corners and has a through hole on each side; the upper stepped structure is shorter than the lower square block, and has two upper and lower square blocks and a vertical surface vertically connected to the two blocks, the upper and lower square blocks have rounded corners, the lower square block is provided with two threaded through holes, and the upper square block has a threaded through hole on each side of the circular hole; The top plate (4) is formed by stacking two square blocks up and down, the length of the upper square block is smaller than the length of the lower square block, and the center of the top plate (4) is provided with a threaded through hole for installing and connecting a vibration source device; The through hole penetrates the bottom plate (1), the rigid member (3), and the top plate (4), and the centers of the circles coincide with each other; The central through hole of the bottom plate (1) is connected and installed with the spacecraft through a screw gasket combination (7); the lower end of the machined spring (2) is installed on the threaded through hole of the bottom plate through a threaded hole; the lower square block of the rigid component (3) is installed on the threaded hole of the longer square block of the bottom plate (1); the top of the screw gasket combination (7) connected and installed with the spacecraft is located in the through hole of the rigid component (3); the upper end of the machined spring (2) is installed on the threaded through hole of the upper stepped structure of the rigid component (3), and the machined spring (2) is in a compressed state; the top plate (4) is installed on the upper surface of the lower square block of the upper stepped structure of the rigid component (3); After the vibration isolation device is unlocked, a gap of 1 mm is created between the rigid part (3) and the bottom plate (1); The transmission ratio T of the vibration isolation device and the stiffness k of the machined spring (2) are determined according to the weight of the vibration source equipment and the magnitude and frequency of the vibration. Where T is the vibration transfer ratio, f is the disturbance frequency of the vibration source equipment, f0 is the natural frequency of the vibration isolation system, ξ is the damping ratio of the vibration isolation system, and the range of f / f0 is 2.5 to 5; k=m(2πf0) 2 Where m is the weight of the vibration source equipment.

2. The spacecraft manual unlocking vibration isolation device according to claim 1, characterized in that: The two square blocks of the bottom plate (1) have rounded corners, and the two sides of the longer square block each have a threaded through hole; the two sides of the shorter square block have threaded through holes.

3. The spacecraft manual unlocking vibration isolation device according to claim 1, characterized in that: When the spacecraft is launched, the vibration isolation device is in a locked state, at which time the machined spring (2) is compressed, the rigid part (3) is connected in parallel with the machined spring (2), and the rigid part (3) bears the flight load.

4. The spacecraft manual unlocking vibration isolation device according to claim 1, characterized in that: After the spacecraft is launched into orbit, two M4 screw gasket assemblies (5) in the threaded through holes between the rigid part (3) and the bottom plate (1) are manually removed, the machined spring (2) rebounds, the vibration isolation device is unlocked, and the assembly of the rigid part (3), the top plate (4) and the vibration source device is lifted.

5. The spacecraft manual unlocking vibration isolation device according to claim 1, characterized in that: The base plate (1), the rigid part (3) and the top plate (4) are made of 2A14 aluminum alloy, and the machined spring (2) is made of TC4 titanium alloy and is a transverse groove type machined spring.

6. The spacecraft manual unlocking vibration isolation device according to claim 1, characterized in that: The central through hole of the vibration isolation device bottom plate (1) is connected and installed with the spacecraft through an M5 screw gasket combination, the lower end of the machined spring (2) is installed on the shorter square block of the bottom plate (1) through two M3 screw gasket combinations (6), the lower square block of the rigid part (3) is installed on the longer square block of the bottom plate (1) through two M4 screw gasket combinations (5), the upper end of the machined spring (2) is connected to the upper square block of the upper step structure of the rigid part (3) through two M3 screw gasket combinations (6), and the top plate (4) is installed to the upper surface of the lower square block of the upper step structure of the rigid part (3) through two M4 screw gasket combinations; the vibration source equipment is installed on the upper end of the top plate (4) of the vibration isolation device through an M5 screw gasket combination (7).

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