Air floatation simulation satellite unlocking and separating device

Abstract

The invention discloses an air floatation simulation satellite unlocking and separating device which comprises a frame, an ejection separation mechanism is slidably arranged in the frame, a mounting plate is arranged at the top of the ejection separation mechanism, the top of the mounting plate is used for mounting an air floatation simulation satellite, and a locking and releasing mechanism is arranged at the bottom in the frame. The locking and releasing mechanism is used for tightly pressing the mounting plate at the top of the ejection separation mechanism, the locking and releasing mechanism is further used for releasing the mounting plate so that the mounting plate can be ejected out under the ejection acting force of the ejection separation mechanism, and the device has the advantages that the universality is improved, and the device can be suitable for on-orbit separation deployment simulation verification of air floatation simulation satellites of different structures.

Description

Technical Field

[0001] The present application relates to the technical field of satellite launch simulation, and in particular to an air-floating simulation satellite unlocking and separation device. Background Art

[0002] In recent years, with the rapid development of space applications, the research and development and application of micro-nano satellites have received more and more attention. In order to verify the performance of micro-nano satellites in complex mission scenarios such as on-orbit services, formation flying, docking and control, most studies use air flotation devices suspended on a marble platform to simulate a microgravity environment for the development, testing and verification of GNC algorithms.

[0003] At present, the simulation verification of the in-orbit separation and deployment of micro-nano satellites in ground tests can use the separation and deployment device of ground-based air-floating simulation satellites. However, the existing separation and deployment devices have poor versatility and are difficult to apply to the in-orbit separation and deployment simulation verification of air-floating simulation satellites with different structures. Summary of the invention

[0004] The main purpose of the present application is to provide an unlocking and separation device for an air-floating simulated satellite, aiming to solve the technical problem that the existing separation and deployment devices have poor versatility and are difficult to apply to the on-orbit separation and deployment simulation verification of air-floating simulated satellites with different structures.

[0005] To achieve the above-mentioned purpose, the present application provides an unlocking and separating device for an air-floating simulated satellite, comprising a frame, a launching separation mechanism slidingly arranged inside the frame, a mounting plate arranged on the top of the launching separation mechanism, the top of the mounting plate being used to install the air-floating simulated satellite, and a locking and releasing mechanism being arranged on the bottom of the frame, the locking and releasing mechanism being used to press the mounting plate against the top of the launching separation mechanism, and the locking and releasing mechanism being also used to release the mounting plate so that the mounting plate is ejected under the launching force of the launching separation mechanism.

[0006] Optionally, the locking release mechanism includes a support frame arranged at the inner bottom, a shell is arranged on the support frame, a locking groove connected to the interior of the shell is arranged at the top of the shell, a locking assembly is arranged in the shell, and a locking pull ring is arranged at the bottom of the mounting plate. The locking assembly is used to lock the locking pull ring in the locking groove, and the locking assembly is also used to release the lock of the locking pull ring.

[0007] Optionally, the locking assembly includes a locking plate and an unlocking rod, both of which are rotatably connected to the inner wall of the shell. A locking column and a limiting column are provided on one side of the locking plate close to the locking groove. There is a spacing between the locking column and the limiting column. The locking column is used to pass through the locking pull ring and the locking groove at the same time to lock the locking pull ring in the locking groove. The rotating position of the locking plate is connected to a first torsion spring, one end of the first torsion spring is clamped into the outer wall of the limiting column, and the other end of the first torsion spring is pressed against the inner wall of the shell. A limiting groove is provided on one side of the unlocking rod, which is engaged with the end of the limiting column. The rotating position of the unlocking rod is connected to a second torsion spring, one end of the second torsion spring is clamped into the outer wall of the unlocking rod, and the other end of the second torsion spring is connected to the inner wall of the shell.

[0008] Optionally, the locking assembly also includes a traction wheel movably connected to the shell and an electrical interface arranged on the side wall of the shell, a memory alloy wire is wound around the traction wheel, one end of the memory alloy wire is connected to the electrical interface, and the other end of the memory alloy wire is connected to the unlocking rod, and the connection point, the traction wheel and the electrical interface are arranged in a triangle; wherein the connection point is the connection position between the memory alloy wire and the unlocking rod.

[0009] Optionally, a charging plate is provided on the support frame, and a circuit docking plate electrically connected to the charging plate is provided on the mounting plate. The circuit docking plate is used to form a passage with the charging plate to power the battery pack of the air-floating simulation satellite.

[0010] Optionally, a micro switch is provided on the mounting plate, and the micro switch is used to turn on the power state of the air-floating simulation satellite. A start-stop mechanism is also provided on the mounting plate, and the start-stop mechanism is used to control the opening and closing of the micro switch.

[0011] Optionally, the start-stop mechanism includes a push rod, a contact block that contacts the micro switch is connected to the top of the push rod, a movable sleeve on the push rod is provided with a shaft sleeve and a compression spring, the compression spring is located between the contact block and the shaft sleeve, a limiting hole is provided on the mounting plate, the shaft sleeve movably passes through the limiting hole and extends out from the bottom of the mounting plate, the contact block is located above the limiting hole, and the width of the contact block is greater than the diameter of the limiting hole.

[0012] Optionally, the ejection separation mechanism includes a guide frame slidably connected to the inner wall of the frame, a mounting plate is arranged on the top of the guide frame, an ejection spring is connected to the top of the guide frame, the bottom of the ejection spring is pressed against the bottom of the frame, and the locking release mechanism is located inside the ejection spring.

[0013] Optionally, the guide frame includes a lower bottom support plate and an upper bottom support plate located above the lower bottom support plate, support columns are connected between the four corners of the lower bottom support plate and the upper bottom support plate, and the side walls of the support columns are provided with sliding components that slide with the inner wall of the frame.

[0014] Optionally, the sliding assembly includes at least two bearings that slide with the inner wall of the frame, the inner rings of the bearings are connected to support shafts, both ends of the support shafts are connected to support plates, the bearings are located between the two support plates, and the support plates are connected to the side walls of the support columns.

[0015] Optionally, stop blocks are provided at the four corners of the top of the frame, and the stop blocks are used to limit the lower bottom support plate.

[0016] Optionally, the frame includes a bottom plate, the locking and releasing mechanism is arranged on the bottom plate, the four corners of the bottom plate are connected with vertical beams, the ejection separation mechanism is slidably arranged between the four vertical beams, and the tops of the four vertical beams are connected with top frames.

[0017] The beneficial effects that this application can achieve are as follows:

[0018] The present application includes a frame, in which an ejection separation mechanism is slidably arranged, a mounting plate is arranged on the top of the ejection separation mechanism, the top of the mounting plate is used to install an air-floating simulation satellite, a locking release mechanism is arranged on the bottom of the frame, the locking release mechanism is used to press the mounting plate against the top of the ejection separation mechanism, and the locking release mechanism is also used to release the mounting plate so that the mounting plate is ejected by the ejection force of the ejection separation mechanism. The present application uses the mounting plate as an intermediate docking piece between the air-floating simulation satellite and the ejection separation mechanism. For air-floating simulation satellites with different mounting structures, it is only necessary to replace the mounting plate of the corresponding mounting structure without changing the structure of the ejection separation mechanism, thereby improving the versatility to meet the requirements of on-orbit separation deployment simulation verification for air-floating simulation satellites with different structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following is a brief introduction to the drawings required for the specific embodiments or the prior art description. In all drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, the elements or parts are not necessarily drawn according to the actual scale.

[0020] Figure 1 This is a schematic structural diagram of an air-floating simulated satellite unlocking and separation device in an embodiment of the present application;

[0021] Figure 2 This is a schematic diagram of the connection structure between the locking and releasing mechanism and the base plate in an embodiment of the present application;

[0022] Figure 3 Schematic diagram of the connection structure between the locking assembly and the housing in the embodiment of the present application (in the locked state);

[0023] Figure 4 Schematic diagram of the connection structure between the locking assembly and the housing in the embodiment of the present application (in unlocked state);

[0024] Figure 5 It is a structural schematic diagram of a mounting plate in an embodiment of the present application;

[0025] Figure 6 It is a schematic diagram of the arrangement structure of the start-stop mechanism and the micro switch in the embodiment of the present application;

[0026] Figure 7 It is a schematic diagram of the connection structure between the support column and the sliding assembly in an embodiment of the present application.

[0027] Reference numerals:

[0028] 100-frame, 110-bottom plate, 120-vertical beam, 130-top frame, 200-ejection separation mechanism, 210-guide frame, 211-lower bottom support plate, 212-upper bottom support plate, 213-support column, 220-ejection spring, 300-mounting plate, 310-locking pull ring, 320-circuit docking plate, 400-locking release mechanism, 410-support frame, 420-housing, 421-locking groove, 430-locking assembly, 431-locking sheet, 4311-locking column , 4312-limiting column, 432-unlocking rod, 4321-limiting groove, 433-first torsion spring, 434-second torsion spring, 435-traction wheel, 436-electrical interface, 437-memory alloy wire, 500-charging plate, 600-micro switch, 700-start-stop mechanism, 710-top rod, 720-contact block, 730-sleeve, 740-compression spring, 800-sliding assembly, 810-bearing, 820-support shaft, 830-support plate, 900-stop block.

[0029] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0031] It should be noted that all directional indications in the embodiments of the present application (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0032] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0033] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present application, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing in the full text includes three parallel schemes. Taking "A and / or B" as an example, it includes scheme A, or scheme B, or a scheme that satisfies both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in the field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.

[0034] Example

[0035] Reference Figure 1-Figure 7 The present embodiment provides an air-floating simulated satellite unlocking and separation device, including a frame 100, a ejection separation mechanism 200 is slidably arranged in the frame 100, a mounting plate 300 is arranged on the top of the ejection separation mechanism 200, and the top of the mounting plate 300 is used to install the air-floating simulated satellite, and a locking and releasing mechanism 400 is arranged on the bottom of the frame 100, and the locking and releasing mechanism 400 is used to lock the mounting plate 300 on the top of the ejection separation mechanism 200, and the locking and releasing mechanism 400 is also used to release the mounting plate 300, so that the mounting plate 300 is ejected under the ejection force of the ejection separation mechanism 200.

[0036] In this embodiment, the mounting plate 300 is provided as an intermediate docking piece between the air-floating simulation satellite and the ejection separation mechanism 200. For air-floating simulation satellites with different mounting structures, it is only necessary to replace the mounting plate 300 of the corresponding mounting structure without changing the structure of the ejection separation mechanism 200, thereby improving the versatility to meet the requirements of on-orbit separation deployment simulation verification for air-floating simulation satellites with different structures. In addition, the device adopts a frame structure, which has the characteristics of being simple and compact, small in size, and small in mass, and has high reliability for detachable deployment.

[0037] Working principle: When conducting an on-orbit separation and deployment simulation verification of an air-floating simulated satellite, the air-floating simulated satellite is suspended on an air-floating platform, such as a marble platform, and the device is placed on its side and installed on a release platform. The mounting plate 300 is fixed to the side end of the simulated air-floating satellite. When in a locked state, the mounting plate 300 is pressed against the side end of the ejection separation mechanism 200 through the locking release mechanism 400. When a separation signal is received, the locking release mechanism 400 releases the mounting plate 300, and the mounting plate 300 is ejected horizontally together with the air-floating simulated satellite under the ejection action of the ejection separation mechanism 200 to complete the ground deployment of the air-floating simulated satellite.

[0038] As an optional embodiment, the locking release mechanism 400 includes a support frame 410 arranged at the inner bottom, a shell 420 is arranged on the support frame 410, a locking groove 421 connected to the interior of the shell 420 is arranged at the top of the shell 420, a locking assembly 430 is arranged in the shell 420, and a locking pull ring 310 is arranged at the bottom of the mounting plate 300. The locking assembly 430 is used to lock the locking pull ring 310 in the locking groove 421, and the locking assembly 430 is also used to release the lock of the locking pull ring 310.

[0039] In this embodiment, the support frame 410 is used to increase the support height of the shell 420 so that the locking assembly 430 in the shell 420 can be connected to the locking pull ring 310 at the bottom of the mounting plate 300, thereby generating a pulling force on the locking pull ring 310. When in the locked state, the locking assembly 430 provides a pulling force to the locking pull ring 310 to lock it in the locking groove 421. When in the unlocked state, the locking pull ring 310 is unlocked by the locking assembly 430, so that the mounting plate 300 loses the tension restriction, thereby realizing the locking and unlocking separation effect of the mounting plate 300.

[0040] It should be noted that the locking pull ring 310 should be set at the geometric center of the mounting plate 300 or close to the geometric center, so that the locking assembly 430 can provide a stable pulling force to the mounting plate 300, so that the mounting plate 300 can be stably and securely attached to the ejection separation mechanism 200.

[0041] As an optional embodiment, the locking assembly 430 includes a locking piece 431 and an unlocking rod 432 which are both rotatably connected to the inner wall of the housing 420. A locking column 4311 and a limiting column 4312 are provided on the side of the locking piece 431 close to the locking groove 421. There is a distance between the locking column 4311 and the limiting column 4312. The locking column 4311 is used to pass through the locking pull ring 310 and the locking groove 421 at the same time to lock the locking pull ring 310 in the locking groove 421. The first torsion spring 433 is connected to the rotation position of 1, one end of the first torsion spring 433 is clamped into the outer wall of the limiting column 4312, and the other end of the first torsion spring 433 is pressed against the inner wall of the shell 420. A limiting groove 4321 is formed on one side of the unlocking rod 432 to be clamped with the end of the limiting column 4312. The rotation position of the unlocking rod 432 is connected to the second torsion spring 434, one end of the second torsion spring 434 is clamped into the outer wall of the unlocking rod 432, and the other end of the second torsion spring 434 is connected to the inner wall of the shell 420.

[0042] In this embodiment, since the mounting plate 300 is used as the intermediate docking piece between the air-floating simulation satellite and the ejection separation mechanism 200, a locking assembly 430 of a corresponding structure needs to be configured to provide a stable and reliable pulling force to the locking pull ring 310, so that the mounting plate 300 is stably and firmly attached to the ejection separation mechanism 200. At the same time, it is also necessary to have an instantaneous unlocking function to improve the unlocking efficiency. Therefore, based on the locking assembly 430 of this embodiment, in the locked state, the locking plate 431 is clamped in the limiting groove 4321 of the unlocking rod 432 through the limiting column 4312, so that the unlocking rod 432 remains stationary, thereby keeping the locking plate 431 stationary. The locking pin 310 is located in the locking groove 421 and is sleeved on the locking pin 4311, thereby realizing the locking effect on the locking pin 310. When unlocking is required, the unlocking rod 432 is rotated to make the limiting pin 4312 of the locking pin 431 disengage from the limiting groove 4321, thereby releasing the limiting effect on the locking pin 431. At the same time, under the ejection thrust of the ejection separation mechanism 200 on the mounting plate 300, the locking pin 310 generates an outward pulling force on the locking pin 431, so that the locking pin 310 The locking piece 431 is pulled to rotate, and the torsional action of the first torsion spring 433 on the locking piece 431 further promotes its rotation, so that the locking piece 431 can rotate instantly. At this time, the locking column 4311 rotates and disengages from the locking groove 421, and the locking pull ring 310 also slides out of the locking column 4311 to release the locking effect on the locking pull ring 310, so that the mounting plate 300 is ejected under the ejection thrust of the ejection separation mechanism 200. The unlocking process is efficient and fast, with instant unlocking capability, and when unlocking, it is only necessary to control the rotation of the unlocking rod 432, which is convenient and quick to operate. When it needs to be locked again, the locking pull ring 310 is inserted into the lock The locking post 4312 is locked and released when the locking member 431 is unlocked.

[0043] As an optional embodiment, the locking assembly 430 also includes a traction wheel 435 movably connected to the shell 420 and an electrical interface 436 arranged on the side wall of the shell 420, and a memory alloy wire 437 is wound around the traction wheel 435, one end of the memory alloy wire 437 is connected to the electrical interface 436, and the other end of the memory alloy wire 437 is connected to the unlocking rod 432, and the connection point, the traction wheel 435 and the electrical interface 436 are arranged in a triangle; wherein the connection point is the connection position between the memory alloy wire 437 and the unlocking rod 432.

[0044] In this embodiment, in order to improve the degree of automation and realize automatic control of the rotation of the unlocking rod 432, when this embodiment is in the locked state, the electrical interface 436 is closed, the memory alloy wire 437 has no force on the unlocking rod 432, and the unlocking rod 432 is in the locked position with respect to the locking plate 431. When the electrical interface receives the separation electrical signal, the memory alloy wire 437 can be electrically heated to shrink it, thereby generating a pulling force on the unlocking rod 432 to rotate it away from the unlocking plate, thereby realizing the automatic unlocking effect of the unlocking rod 432 on the locking plate 431, realizing separation unlocking, and being controlled by electrical signals with fast response speed and high unlocking efficiency.

[0045] As an optional embodiment, a charging plate 500 is provided on the support frame 410, and a circuit docking plate 320 electrically connected to the charging plate 500 is provided on the mounting plate 300. The circuit docking plate 320 is used to form a passage with the charging plate 500 to power the battery pack of the floating simulation satellite.

[0046] In this embodiment, when in a locked state, the mounting plate 300 is attached to the ejection separation mechanism 200. At this time, the circuit docking plate 320 on the mounting plate 300 can be docked with the charging plate 500, thereby forming a passage to supply power to the battery pack of the air-floating simulation satellite, thereby realizing the charging function. When unlocked and separated, the circuit docking plate 320 is separated from the charging plate 500, and the power subsystem on the air-floating simulation satellite is no longer charged.

[0047] It should be noted that the charging board 500 here includes a circuit board and spring pins, and the spring pins are used to contact the contacts on the circuit docking board 320 to achieve power supply.

[0048] As an optional implementation, a micro switch 600 is provided on the mounting plate 300, and the micro switch 600 is used to turn on the power-on state of the air-floating simulated satellite. A start-stop mechanism 700 is also provided on the mounting plate 300, and the start-stop mechanism 700 is used to control the opening and closing of the micro switch 600. When the air-floating simulated satellite is ejected and separated, the micro switch 600 can be controlled to be turned on by the start-stop mechanism 700, so that the air-floating simulated satellite enters the power-on state.

[0049] As an optional embodiment, the start-stop mechanism 700 includes a push rod 710, and a contact block 720 that contacts the micro switch 600 is connected to the top of the push rod 710. A movable sleeve is provided on the push rod 710 with a shaft sleeve 730 and a compression spring 740. The compression spring 740 is located between the contact block 720 and the shaft sleeve 730. A limiting hole is opened on the mounting plate 300. The shaft sleeve 730 movably passes through the limiting hole and extends out of the bottom of the mounting plate 300. The contact block 720 is located above the limiting hole, and the width of the contact block 720 is greater than the diameter of the limiting hole.

[0050] In the present embodiment, in order to further improve the degree of automation, the start-stop mechanism 700 is optimized and designed. In the locked state, the mounting plate 300 is pressed against the ejection separation mechanism 200, and the sleeve 730 is also pressed against the ejection separation mechanism 200. The sleeve 730 squeezes the compression spring 740, so that under the action of the compression spring 740, the contact block 720 is pressed against the paddle of the microswitch 600, and the microswitch 600 is always in a closed state. When the air-floating simulated satellite is ejected and separated, the pressing effect of the ejection separation mechanism 200 on the sleeve 730 is released at the same time. Under the reaction force of the compression spring 740, the sleeve 730 and the push rod 710 are driven to move away from the microswitch 600 at the same time, so that the contact block 720 is separated from the paddle of the microswitch 600. After the paddle returns to its position, the microswitch 600 is turned on to realize the automatic power-on of the air-floating simulated satellite. The structural design is ingenious and meets the use requirements.

[0051] It should be noted that, mutually cooperating limit steps can be provided at the ends of the sleeve 730 and the push rod 710, so that the sleeve 730 will not separate from the push rod 710; the width of the contact block 720 is greater than the diameter of the limit hole, so that after the contact block 720 separates from the micro switch 600, it can be pressed against the end face of the mounting plate 300 and will not enter the limit hole, so that the entire start-stop mechanism 700 will not fall off the mounting plate 300, so that it can be reused.

[0052] As an optional embodiment, the ejection separation mechanism 200 includes a guide frame 210 slidably connected to the inner wall of the frame 100, the mounting plate 300 is arranged on the top of the guide frame 210, the top of the guide frame 210 is connected to the ejection spring 220, the bottom of the ejection spring 220 is pressed against the bottom of the frame 100, and the locking release mechanism 400 is located inside the ejection spring 220.

[0053] In this embodiment, when ejection separation is performed, the ejection thrust is provided by the ejection spring 220 to push the guide frame 210 to slide along the inner wall of the frame 100, and the guide frame 210 provides a stable guiding thrust to the mounting plate 300. When the guide frame 210 slides to a critical position, the mounting plate 300 is separated from the guide frame 210 under the action of inertia, so that the mounting plate 300 and the air-floating simulated satellite are horizontally pushed out as a whole to complete the ground deployment of the air-floating simulated satellite.

[0054] It should be noted that when the ejection spring 220 is used as the power for ejecting the air-floating simulated satellite, the ejection spring 220 can be replaced, that is, the power can be adjusted to achieve the adjustability of the ejection speed of the air-floating simulated satellite, thereby meeting different experimental simulation requirements.

[0055] As an optional embodiment, the guide frame 210 includes a lower bottom support plate 211 and an upper bottom support plate 212 located above the lower bottom support plate 211, and support columns 213 are connected between the four corners of the lower bottom support plate 211 and the upper bottom support plate 212. The side walls of the support columns 213 are provided with sliding components 800 that slide with the inner wall of the frame 100.

[0056] In this embodiment, the ejection spring 220 is located between the four support columns 213. When the guide frame 210 slides, it can be stably guided and slid by the sliding assembly 800 on the side wall of the support column 213, and the sliding assembly 800 can reduce the friction of the support column 213, thereby reducing the power loss of the ejection spring 220 and improving the accuracy of the simulation experiment.

[0057] As an optional embodiment, the sliding assembly 800 includes at least two bearings 810 (ball bearings can be used) that are slidably matched with the inner wall of the frame 100, the inner rings of the bearings 810 are connected to the support shafts 820, both ends of the support shafts 820 are connected to support plates 830, the bearings 810 are located between the two support plates 830, and the support plates 830 are connected to the side walls of the support columns 213. Here, a guide groove that matches the bearings 810 is provided on the inner wall of the frame 100, and the support column 213 can slide through the rolling match between the bearings 810 and the inner wall of the frame 100, with low wear and reliable sliding.

[0058] As an optional embodiment, stop blocks 900 are provided at the four corners of the top of the frame 100. The stop blocks 900 are used to limit the lower bottom support plate 211. The setting of the stop blocks 900 can restrict the lower bottom support plate 211, thereby preventing the guide frame 210 from sliding out of the frame 100, which is convenient for subsequent reuse.

[0059] As an optional embodiment, the frame 100 includes a base plate 110, a locking and releasing mechanism 400 is arranged on the base plate 110, four corners of the base plate 110 are connected to vertical beams 120, an ejection separation mechanism 200 is slidably arranged between the four vertical beams 120, and the top of the four vertical beams 120 is connected to a top frame 130. It has the characteristics of being simple and compact, small in size, and small in mass, and has high reliability of detachable deployment.

[0060] The above are only preferred embodiments of the present application, and are not intended to limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. An air-floating simulated satellite unlocking and separation device, characterized in that: It includes a frame, in which an ejection separation mechanism is slidably arranged, a mounting plate is arranged on the top of the ejection separation mechanism, the top of the mounting plate is used to install an air-floating simulation satellite, a locking and releasing mechanism is arranged on the bottom of the frame, the locking and releasing mechanism is used to press the mounting plate on the top of the ejection separation mechanism, and the locking and releasing mechanism is also used to release the mounting plate so that the mounting plate is ejected under the ejection force of the ejection separation mechanism.

2. The air-floating simulated satellite unlocking and separation device according to claim 1, characterized in that: The locking release mechanism includes a support frame arranged at the inner bottom, a shell is arranged on the support frame, a locking groove connected to the interior of the shell is arranged at the top of the shell, a locking assembly is arranged in the shell, a locking pull ring is arranged at the bottom of the mounting plate, the locking assembly is used to lock the locking pull ring in the locking groove, and the locking assembly is also used to release the lock of the locking pull ring.

3. The air-floating simulated satellite unlocking and separation device according to claim 2, characterized in that: The locking assembly includes a locking plate and an unlocking rod, both of which are rotatably connected to the inner wall of the shell, and a locking column and a limiting column are provided on one side of the locking plate close to the locking groove, and there is a spacing between the locking column and the limiting column, and the locking column is used to simultaneously pass through the locking pull ring and the locking groove to lock the locking pull ring in the locking groove, and the rotating position of the locking plate is connected to a first torsion spring, one end of the first torsion spring is clamped into the outer wall of the limiting column, and the other end of the first torsion spring is pressed against the inner wall of the shell, and a limiting groove is provided on one side of the unlocking rod to engage with the end of the limiting column, and the rotating position of the unlocking rod is connected to a second torsion spring, one end of the second torsion spring is clamped into the outer wall of the unlocking rod, and the other end of the second torsion spring is connected to the inner wall of the shell.

4. The air-floating simulated satellite unlocking and separation device as claimed in claim 3, characterized in that: The locking assembly also includes a traction wheel movably connected to the shell and an electrical interface arranged on the side wall of the shell, a memory alloy wire is wound around the traction wheel, one end of the memory alloy wire is connected to the electrical interface, and the other end of the memory alloy wire is connected to the unlocking rod, and the connection point, the traction wheel and the electrical interface are arranged in a triangle; wherein the connection point is the connection position between the memory alloy wire and the unlocking rod.

5. The air-floating simulated satellite unlocking and separation device as claimed in claim 2, characterized in that: The support frame is provided with a charging plate, and the mounting plate is provided with a circuit docking plate electrically connected to the charging plate. The circuit docking plate is used to form a passage with the charging plate to supply power to the battery pack of the air-floating simulation satellite.

6. The air-floating simulated satellite unlocking and separation device according to claim 1 or 5, characterized in that: The mounting plate is provided with a micro switch, and the micro switch is used to turn on the power-on state of the air-floating simulation satellite. The mounting plate is also provided with a start-stop mechanism, and the start-stop mechanism is used to control the opening and closing of the micro switch.

7. The air-floating simulated satellite unlocking and separation device according to claim 6, characterized in that: The start-stop mechanism includes a push rod, the top of the push rod is connected to a contact block that contacts the micro switch, a movable sleeve on the push rod is provided with a shaft sleeve and a compression spring, the compression spring is located between the contact block and the shaft sleeve, a limiting hole is provided on the mounting plate, the shaft sleeve movably passes through the limiting hole and extends out of the bottom of the mounting plate, the contact block is located above the limiting hole, and the width of the contact block is greater than the diameter of the limiting hole.

8. An air-floating simulated satellite unlocking and separation device as claimed in any one of claims 1 to 5, characterized in that: The ejection separation mechanism includes a guide frame slidably connected to the inner wall of the frame, the mounting plate is arranged on the top of the guide frame, the top of the guide frame is connected to an ejection spring, the bottom of the ejection spring is pressed against the bottom of the frame, and the locking release mechanism is located in the ejection spring.

9. The air-floating simulated satellite unlocking and separation device as claimed in claim 8, characterized in that: The guide frame includes a lower bottom support plate and an upper bottom support plate located above the lower bottom support plate, support columns are connected between the four corners of the lower bottom support plate and the upper bottom support plate, and the side walls of the support columns are provided with sliding components that slide with the inner wall of the frame.

10. The air-floating simulated satellite unlocking and separation device according to claim 9, characterized in that: The sliding assembly includes at least two bearings that slide with the inner wall of the frame, the inner rings of the bearings are connected to support shafts, both ends of the support shafts are connected to support plates, the bearings are located between the two support plates, and the support plates are connected to the side walls of the support columns.

11. The air-floating simulated satellite unlocking and separation device according to claim 9, characterized in that: Stop blocks are arranged at the four corners of the top of the frame, and the stop blocks are used to limit the lower bottom supporting plate.

12. The air-floating simulated satellite unlocking and separation device according to claim 1, characterized in that: The frame includes a bottom plate, the locking and releasing mechanism is arranged on the bottom plate, the four corners of the bottom plate are connected with vertical beams, the ejection separation mechanism is slidably arranged between the four vertical beams, and the tops of the four vertical beams are connected with top frames.

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