Logic anti-misoperation type microsatellite on-orbit release device and microsatellite on-orbit release method

Abstract

The application provides a logic anti-misoperation microsatellite on-orbit release device and a microsatellite on-orbit release method. The device comprises a base, a push plate, an elastic element, a loading part, a pin base, an unlocking screw, an unlocking pin, an anti-misoperation cover plate and an anti-misoperation elastic element. The anti-misoperation cover plate is slidingly connected to the pin base and has a first position and a second position. In the first position, the driving port of the unlocking screw is exposed, and in the second position, the anti-misoperation cover plate blocks the driving port. The anti-misoperation elastic element applies a force to the anti-misoperation cover plate towards the second position. When the loading part is in the loading state, the top end of the loading part abuts against the anti-misoperation cover plate and drives the movement of the anti-misoperation cover plate to the first position. When the loading part is in the unloading state, the anti-misoperation cover plate is reset to the second position under the action of the anti-misoperation elastic element. The loading / unloading state of the loading part is linked to the position of the anti-misoperation cover plate, and the automatic exposure of the operation port during the loading process and the automatic closure after the loading is completed are realized by the pure mechanical structure, so that the risk of the in-cabin misrelease is fundamentally avoided.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft on-orbit release technology, and particularly relates to a logic-based anti-misoperation microsatellite on-orbit release device and microsatellite on-orbit release method. Background Technology

[0002] In-orbit release of micro-spacecraft is one of the important in-orbit applications of the International Space Station (ISS). After entering the ISS, the in-orbit release device is stored permanently within the station's modules. Once the micro-spacecraft arrives on a cargo spacecraft, astronauts manually install it onto the release device, then transport it outside the module and release it in orbit with the assistance of a robotic arm. Based on the ISS's in-orbit application experience, my country's space station, after completing in-orbit assembly, also possesses the capability for in-orbit release of micro-spacecraft. Micro-spacecraft mainly include microsatellites with non-standard shapes and CubeSats with standard shapes. Microsatellites are small, functional micro-spacecraft weighing between 10 and 100 kilograms. Their shape envelope and mass characteristics vary widely depending on functional requirements, placing high demands on the adaptability of the release mechanism.

[0003] Currently used on-orbit release devices for microsatellites pose a risk of accidental release inside the space station after on-orbit loading by astronauts. Because the release device requires the unlocking screw's operating interface to remain operable during the loading phase, astronauts might accidentally trigger the manual unlocking mechanism, leading to the unintended release of the microsatellite inside the station and potentially causing catastrophic consequences. Traditional solutions rely on operating procedures and astronaut discipline to prevent accidental release, lacking a physical layer of protection. Once human error occurs, the consequences are irreversible. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a logic-based anti-mistake microsatellite on-orbit release device and a microsatellite on-orbit release method, so as to solve the problem of the risk of accidental release inside the cabin due to the lack of physical anti-mistake mechanism in the existing scheme.

[0005] To solve the above problems, the technical solution of the present invention is: a logic-based anti-misoperation microsatellite on-orbit release device, comprising: Base; Push plates are spaced apart on the base, and at least one elastic element is provided between the base and the push plates; The loading unit is configured to drive the push plate to move relative to the base in a direction opposite to the release direction, so as to compress the elastic element to store energy; A pin base is fixedly connected to the base; The unlocking screw is rotatably connected to the pull pin base, and one end of the unlocking screw is provided with a drive port suitable for manual operation tools to access; The unlocking pin includes an unlocking slider and a pin body connected to the unlocking slider. The unlocking slider is threadedly engaged with the unlocking screw. The pin body passes through the pin base and slides with the pin base to be used for inserting or removing the locking hole of the microsatellite tail accessory. The unlocking screw is configured to rotate to drive the unlocking slider and the pin body to translate. The microsatellite tail accessory is used to connect to the microsatellite. An anti-misoperation cover is slidably connected to the pin base. The anti-misoperation cover has a first position and a second position. In the first position, the drive port is exposed to allow the manual operating tool to access it. In the second position, the anti-misoperation cover blocks the drive port. An anti-misoperation elastic element is installed between the anti-misoperation cover and the pull pin base, and is used to apply a force toward the second position to the anti-misoperation cover; The top end of the loading part is configured to abut against the anti-misoperation cover plate during loading to drive the anti-misoperation cover plate to move from the second position to the first position against the force of the anti-misoperation elastic member; when the loading part exits loading, the anti-misoperation cover plate moves from the first position to the second position under the action of the anti-misoperation elastic member.

[0006] This invention mechanically links the movement of the anti-misoperation cover with the loading / unloading state of the loading unit, automatically exposing the operating port of the unlocking screw during loading and automatically closing it after loading is completed. Loading (compressing the elastic element to store energy) is a necessary preliminary step in loading, and unloading is the inevitable result of loading completion. By anchoring the position switching of the anti-misoperation cover to these two necessary actions, a purely mechanical structure achieves physical logic-based anti-misoperation—the operating port automatically closes upon completion of loading, fundamentally eliminating the possibility of accidental release by human intervention inside the cabin, without relying on operating procedures or electronic control logic.

[0007] In one or more embodiments, the anti-misoperation cover includes a baffle portion and a sliding rod portion connected to the baffle portion; the pin base is provided with a guide hole, and the sliding rod portion is slidably engaged with the guide hole to allow the anti-misoperation cover to slide between the first position and the second position.

[0008] In one or more embodiments, the baffle portion is provided with a through hole; at the first position, the through hole is aligned with the axis of the unlocking screw, and the drive port is exposed through the through hole; at the second position, the baffle portion is offset from the axis of the unlocking screw to block the drive port.

[0009] In one or more embodiments, the anti-misoperation elastic element is a reset spring, which is connected between the anti-misoperation cover and the pin base.

[0010] In one or more embodiments, the loading part includes a loading screw and a limiting plate, the limiting plate being linked to the push plate and located on the side of the base opposite to the push plate; the loading screw is threadedly engaged with the limiting plate to drive the limiting plate and the push plate to move in the opposite direction to the release direction by rotation; the loading screw has a trapezoidal external thread in the middle, and the limiting plate has a trapezoidal internal thread, the trapezoidal external thread and the trapezoidal internal thread engaging to form a threaded pair.

[0011] In one or more embodiments, the sliding trajectory of the anti-misoperation cover is coaxial with the rotation axis of the loading screw.

[0012] In one or more embodiments, it further includes at least one guide rod and at least one spring guide cylinder, the spring guide cylinder being fixed to the base, one end of the guide rod being fixedly connected to the push plate, and the other end passing through the base and being fixedly connected to the limiting plate, the outer wall of the guide rod being slidably engaged with the inner wall of the spring guide cylinder; the elastic element is a separation spring, the separation spring being sleeved on the guide rod and the spring guide cylinder.

[0013] In one or more embodiments, a motor is further included, the motor being fixed to the base, and the output shaft of the motor being fixedly connected to the other end of the unlocking screw.

[0014] In one or more embodiments, the pull pin base, the unlocking screw, the unlocking pin, the anti-misoperation cover, and the anti-misoperation elastic element constitute an independent modular structure, which is detachably fixed to the base.

[0015] Based on the same inventive concept, the present invention also provides a microsatellite on-orbit release method for use with the logic-preventing microsatellite on-orbit release device as described in any of the above claims, comprising the following steps: Before loading, the loading unit performs loading, and the loading unit drives the anti-misoperation cover plate to move from the second position to the first position against the force of the anti-misoperation elastic element, and the driving port is exposed; the loading unit drives the push plate to move in the opposite direction to the release direction, and compresses the elastic element to store energy; During loading, the microsatellite tail accessory connected to the microsatellite is placed on the pin base. The unlocking screw is rotated through the drive port, which drives the pin body to move and insert into the locking hole of the microsatellite tail accessory. The loading part is unloaded, and the anti-misoperation cover plate moves from the first position to the second position under the action of the anti-misoperation elastic element, blocking the drive port. Upon release, the motor drives the unlocking screw to rotate in the opposite direction, causing the pin body to move in the opposite direction and exit the lock hole. The elastic element releases its stored energy, pushing the push plate to pop out along the release direction and launching the microsatellite.

[0016] Because the present invention adopts the above technical solution, it has the following advantages and positive effects compared with the prior art: I. One embodiment of the present invention, by setting an anti-misoperation cover and an anti-misoperation elastic element, mechanically links the position switching of the anti-misoperation cover with the loading / unloading state of the loading unit. That is, when the loading unit performs loading, its top end abuts against the anti-misoperation cover, placing it in the first position, with the drive port exposed; when the loading unit unloads, the anti-misoperation cover is reset to the second position under the action of the anti-misoperation elastic element, blocking the drive port. Loading is a necessary preliminary step for filling, and unloading is an inevitable result of the completion of filling. Thus, a purely mechanical structure achieves the physical logic of "automatic closure of the operation port upon completion of filling," fundamentally eliminating the possibility of human error in releasing the device inside the cabin. It does not rely on operating procedures or electronic control logic, avoiding the huge consequences of misoperation of the release device inside the cabin at a minimal cost.

[0017] II. One embodiment of the present invention, by configuring a standard tail accessory for a microsatellite, can achieve universal matching of microsatellites of different shapes and weights by only equipping the microsatellite with a standard tail accessory, thereby reducing the constraints on shape, envelope, interface, etc. in the satellite design process.

[0018] Third, in one embodiment of the present invention, one end of the unlocking screw is driven by a motor, and the other end is provided with a drive port suitable for manual operation tools, realizing dual-mode compatibility of manual loading inside the cabin and electric release outside the cabin. Astronauts complete satellite loading inside the cabin using manual tools, and release the satellite by motor drive after exiting the cabin. The entire device can return to the cabin after completing one release to prepare for the next release, realizing the function of repeated release of satellite in orbit.

[0019] IV. In one embodiment of the present invention, the pin-pulling base, unlocking screw, unlocking pin, anti-misoperation cover plate and anti-misoperation elastic element are assembled into an independent modular structure to uniformly realize the pin-pulling and anti-misoperation functions. This modular structure can be applied to other application scenarios with pin-pulling requirements. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structural composition of the logic-based anti-misoperation microsatellite on-orbit release device according to the present invention.

[0021] Figure 2 This is a cross-sectional view of the logic-based anti-misoperation microsatellite on-orbit release device according to the present invention.

[0022] Figure 3 This is a schematic diagram of the satellite release component of the logic-based anti-misoperation microsatellite on-orbit release device according to the present invention.

[0023] Figure 4 This is a schematic diagram of satellite loading for the logic-based anti-misoperation microsatellite on-orbit release device according to the present invention.

[0024] Figure 5 This is a schematic diagram of a standard tail attachment for a microsatellite, which is a logic-based anti-misoperation microsatellite on-orbit release device according to the present invention.

[0025] Figure 6 This is a structural diagram of the anti-misoperation cover plate component of the logic-based anti-misoperation microsatellite on-orbit release device according to the present invention.

[0026] Figure 7 This is a diagram showing the position of the anti-misoperation cover plate in the installation state of the loading screw of the logic-based anti-misoperation microsatellite on-orbit release device according to the present invention.

[0027] Figure 8 This is a diagram showing the position of the anti-misoperation cover plate in the contact state of the loading screw of the logic-based anti-misoperation microsatellite on-orbit release device according to the present invention.

[0028] Explanation of reference numerals in the attached drawings: 101, Loading screw; 102, Base; 103, Spring guide cylinder; 104, Separation spring; 105, Guide rod; 106, Push plate; 107, Limiting plate; 108, Bearing; 200, Satellite release assembly; 201, Motor; 202, Unlocking screw; 203, Unlocking pin; 204, Pin release base; 205, Bearing; 206, Protective shell; 207, Anti-misoperation cover; 208, Return spring; 300, Microsatellite; 301, Microsatellite standard tail accessory. Detailed Implementation

[0029] The embodiments of this application will be further described in detail below with reference to the accompanying drawings and examples. The detailed description of the following embodiments and the accompanying drawings are used to illustrate the principles of this application by way of example, but should not be used to limit the scope of this application. This application can be implemented in many different forms and is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

[0030] These embodiments are provided to make the application thorough and complete, and to fully express the scope of the application to those skilled in the art. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of components and steps illustrated in these embodiments should be interpreted as merely exemplary and not as limiting.

[0031] All terms used in this application have the same meaning as understood by one of ordinary skill in the art to which this application pertains, unless otherwise specifically defined. It should also be understood that terms defined in general dictionaries should be interpreted as having meanings consistent with their meanings in the context of the relevant art, and not as idealized or highly formalized, unless expressly defined herein.

[0032] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, they should be considered part of the specification.

[0033] Before describing this application, the following explanations are provided for certain terms. In this application, "release direction" refers to the direction in which the elastic element pushes the push plate to launch the microsatellite. In this application, "first position" refers to the position where the anti-misoperation cover is exposed at the drive port, allowing access for manual tools, corresponding to the upper limit position of the anti-misoperation cover during the loading process. In this application, "second position" refers to the position where the anti-misoperation cover is blocking the drive port, corresponding to the lower limit position of the anti-misoperation cover after loading is complete.

[0034] The technical solution of this application will be described layer by layer below with reference to the accompanying drawings.

[0035] Example 1 See Figures 1 to 8 In one embodiment, a logic-based anti-misoperation microsatellite on-orbit release device mainly includes a base 102, a push plate 106, at least one elastic element, a loading part, and a satellite release assembly 200.

[0036] Push plates 106 are spaced apart on the upper side of the base 102 to push the microsatellite 300 during release. An elastic element is disposed between the base 102 and the push plates 106 to apply an elastic force to the push plates 106 in the release direction, i.e., to lift the push plates 106 upwards. The loading unit is configured to move the push plates 106 relative to the base 102 in a direction opposite to the release direction to compress the elastic element and store energy.

[0037] The satellite release assembly 200 is fixedly connected to the base 102 and includes a pin release base 204, an unlocking screw 202, an unlocking pin 203, a motor 201, an anti-misoperation cover 207, and an anti-misoperation elastic element. The pin release base 204 is fixedly connected to the base 102. The unlocking screw 202 is rotatably connected to the pin release base 204, and one end of the unlocking screw 202 has a drive port suitable for manual operation tools. The unlocking pin 203 includes an unlocking slider and a pin body connected to the unlocking slider. The unlocking slider is threadedly engaged with the unlocking screw 202, and the pin body passes through and slides through the pin release base 204 to insert or withdraw from the locking hole of the microsatellite standard tail accessory 301. The unlocking screw 202 is configured to rotate to drive the unlocking slider and the pin body to translate. The microsatellite standard tail accessory 301 is used to connect to the microsatellite 300.

[0038] An anti-misoperation cover 207 is slidably connected to a pin-pulling base 204. The anti-misoperation cover 207 has a first position and a second position. In the first position, the drive port is exposed to allow access for manual tools. In the second position, the anti-misoperation cover 207 blocks the drive port. An anti-misoperation elastic element is installed between the anti-misoperation cover 207 and the pin-pulling base 204 to apply a force toward the second position to the anti-misoperation cover 207. The top end of the loading portion is configured to abut against the anti-misoperation cover 207 during loading to drive the anti-misoperation cover 207 to move from the second position to the first position against the force of the anti-misoperation elastic element.

[0039] During operation, the loading unit performs loading, driving the anti-mishap cover 207 to move from the second position to the first position against the force of the anti-mishap elastic element, exposing the drive port. The loading unit drives the push plate 106 to move in the opposite direction to the release direction, compressing the elastic element to store energy. During loading, the microsatellite standard tail accessory 301 connected to the microsatellite 300 is placed on the pin-pulling base 204. The unlocking screw 202 is rotated through the drive port, causing the unlocking slider and the pin body to translate. The pin body is inserted into the locking hole of the microsatellite standard tail accessory 301, completing the locking of the microsatellite 300. The loading unit exits loading, and the anti-mishap cover 207 moves from the first position to the second position under the action of the anti-mishap elastic element, blocking the drive port. At this time, the astronauts cannot unlock the cabin by manually driving the unlocking screw 202, and the motor 201 is not powered inside the space station cabin, thus completely preventing accidental release of the release device inside the cabin. During release, after satellite loading is complete, the combination of the release device and microsatellite 300 is transported out of the cabin, and the release direction is determined by an external robotic arm. Motor 201 drives the unlocking screw 202 to rotate in the opposite direction, causing the pin body to move in the opposite direction and exit the locking hole. The elastic element releases its stored energy, pushing the push plate 106 out along the release direction, thus launching the microsatellite 300. After completing the release action, the release device can return to the cabin to prepare for the next satellite release.

[0040] The specific structure of the logic-based anti-misoperation microsatellite on-orbit release device in this embodiment is further described below: In this embodiment, the anti-misoperation cover 207 may specifically include a baffle portion and a sliding rod portion connected to the baffle portion. The pin base is provided with a guide hole, and the sliding rod portion slides within the guide hole to allow the anti-misoperation cover 207 to slide between a first position and a second position.

[0041] In this embodiment, the baffle portion of the anti-misoperation cover 207 may also be provided with a through hole. In the first position, the through hole is aligned with the axis of the unlocking screw 202, and the drive port is exposed through the through hole; in the second position, the baffle portion is offset from the axis of the unlocking screw 202 to block the drive port. The anti-misoperation elastic element may be a return spring 208, which is connected between the anti-misoperation cover 207 and the pull-out pin base 204. Specifically, see... Figures 6 to 8 When the anti-accident cover 207 is in the first position, the through hole on the baffle is aligned with the axis of the unlocking screw 202, and the drive port is exposed through the through hole. Astronauts can manually operate the drive port to rotate the unlocking screw 202. When the anti-accident cover 207 is in the second position, the axis of the baffle is misaligned with the axis of the unlocking screw 202, and the baffle blocks the drive port, so astronauts cannot operate the unlocking screw 202 manually.

[0042] In this embodiment, the loading part may specifically include a loading screw 101 and a limiting plate 107. The limiting plate 107 is located on the side of the base 102 opposite to the push plate 106 and is linked to the push plate 106. The loading screw 101 is threadedly engaged with the limiting plate 107, so that the limiting plate 107 and the push plate 106 can be moved in the opposite direction to the release direction by rotation. The loading screw 101 has a trapezoidal external thread in its middle, and the limiting plate 107 has a trapezoidal internal thread. The trapezoidal external thread and the trapezoidal internal thread engage to form a threaded pair. Specifically, see [link to documentation]. Figure 2 The loading screw 101 and the limiting plate 107 form a threaded pair by engaging the trapezoidal internal thread at the central axis. The upper cylindrical surface of the loading screw 101 passes through the bearing 108 mounted on the lower side of the upper plane of the base 102. The loading screw 101 is configured to drive the limiting plate 107 and the push plate 106 to move by rotation, so as to compress the elastic element and store energy.

[0043] In this embodiment, the sliding trajectory of the anti-misoperation cover 207 is coaxially set with the rotation axis of the loading screw 101. Specifically, see... Figure 6 The sliding rod part of the anti-misoperation cover 207 is slidably engaged with the guide hole (cylindrical blind hole) on the lower side of the pin base 204. The sliding rod part is coaxial with the rotation axis of the loading screw 101 along the sliding direction of the guide hole, so that when the top end of the loading screw 101 abuts against the anti-misoperation cover 207 in the axial direction, it can directly drive the anti-misoperation cover 207 to move linearly in the guide hole along its sliding trajectory.

[0044] In this embodiment, the logic-based anti-misoperation microsatellite on-orbit release device may further include at least one guide rod 105 and at least one spring guide cylinder 103. The spring guide cylinder 103 is fixed to the base 102. One end of the guide rod 105 is fixedly connected to the push plate 106, and the other end passes through the base 102 and is fixedly connected to the limiting plate 107. The outer wall of the guide rod 105 is slidably engaged with the inner wall of the spring guide cylinder 103. The elastic element may be a separation spring 104, which is sleeved on the guide rod 105 and the spring guide cylinder 103. Specifically, see... Figure 2 The base 102 can be a cylindrical structure with three evenly distributed circular holes on its upper outer periphery. Three spring guide cylinders 103 are respectively fixedly installed in the aforementioned circular holes. Three guide rods 105 are fixedly installed on the lower surface of the push plate 106. The outer cylindrical surface of the guide rod 105 and the inner cylindrical surface of the spring guide cylinder 103 cooperate to form a sliding pair. After passing through the base 102, the guide rod 105 is fixedly connected to the limiting plate 107 located below the base 102, so that the push plate 106, the guide rod 105, and the limiting plate 107 form a linkage assembly. The elastic element is specifically a release spring 104. The three release springs 104 are respectively sleeved on the outside of the guide rod 105 and the spring guide cylinder 103, so that the above-mentioned linkage assembly has an upward reset tendency relative to the base 102, and the push plate 106 is supported upward under the action of the release springs 104.

[0045] In this embodiment, the logic-based anti-misoperation microsatellite on-orbit release device may further include a motor 201, which is fixed to the base 102, and the output shaft of the motor 201 is fixedly connected to the other end (i.e., the end away from the drive port) of the unlocking screw 202. The drive port of the unlocking screw 202 may be a regular hexagonal countersunk hole, serving as a standard interface for an internal hex wrench. Both the motor 201 and the drive port can be used as driving force input. Specifically, see [link to documentation]. Figure 3 The unlocking screw 202 is mounted in the transverse through-hole in the middle of the pin-pulling base 204 via the bearing 205, forming a rotating pair. The protective shell 206 is mounted on the outside of the pin-pulling base 204 and sleeved on the end of the unlocking screw 202 with the drive port, to prevent external parts from directly impacting the unlocking screw 202. The protective shell 206 has an operating opening corresponding to the drive port. The unlocking slider of the unlocking pin 203 is located on the lower side of the unlocking pin 203 and engages with the trapezoidal external thread in the middle of the unlocking screw 202 to form a threaded pair. The pin body is located on the upper side of the unlocking pin 203, has a cylindrical structure, passes through the transverse through-hole on the upper side of the pin-pulling base 204, and slides in engagement with the pin-pulling base 204. During the in-cabin loading phase, the astronauts manually operate a tool to connect to the drive port to drive the unlocking screw 202 to rotate; during the out-of-cabin release phase, the motor 201 serves as the drive source.

[0046] In this embodiment, the microsatellite standard tail accessory 301 is used to connect to the microsatellite 300. It has an I-shaped transverse hole as a locking hole, and the pin body of the unlocking pin 203 is used to insert into or retract from this I-shaped transverse hole. Specifically, see... Figure 4 and Figure 5 The upper end face of the microsatellite standard tail accessory 301 is mounted on the lower plane of the microsatellite 300. The lower part of the microsatellite standard tail accessory 301 is a cylindrical structure. The lower cylinder of the microsatellite standard tail accessory 301 is used to insert into the cylindrical blind hole on the upper side of the pin base 204, so that the I-type transverse hole is aligned with the pin body.

[0047] In this embodiment, the pin-pulling base 204, unlocking screw 202, unlocking pin 203, anti-misoperation cover 207, and return spring 208 can form an independent modular structure. The satellite release assembly 200 is detachably fixed to the base 102, thus uniformly realizing the pin-pulling and anti-misoperation functions. This modular structure can be applied to other application scenarios that require pin-pulling.

[0048] The following describes the operation of the logic-based anti-misoperation microsatellite on-orbit release device in this embodiment.

[0049] See Figure 7 The loading state is set up before loading. The loading screw 101 is rotated around its axis, spiraling upwards through the center threaded hole of the limiting plate 107. The upper end of the loading screw 101 passes through the bearing 108, and its top end abuts against the anti-misoperation cover 207, driving the anti-misoperation cover 207 to move upwards from the second position to the first position against the force of the return spring 208. At this time, the through hole on the baffle of the anti-misoperation cover 207 is aligned with the axis of the unlocking screw 202, and the drive port is exposed. The loading screw 101 continues to rotate, and under the action of the trapezoidal thread, the limiting plate 107 moves downwards. The limiting plate 107, through the guide rod 105, drives the push plate 106 to move downwards in the opposite direction to the release direction, compressing the separation spring 104 and causing the separation spring 104 to be pressed and stored. This completes the pre-loading state setting.

[0050] See Figure 4 , Figure 5 and Figure 7Satellite loading. Move the microsatellite 300 above the push plate 106, so that the lower surface of the microsatellite 300 is in contact with the upper surface of the push plate 106. Insert the lower cylinder of the microsatellite standard tail accessory 301 into the cylindrical blind hole on the upper side of the pin-pulling base 204, aligning the I-shaped transverse hole of the microsatellite standard tail accessory 301 with the pin body of the unlocking pin 203. The astronaut connects to the drive port of the unlocking screw 202 by manually operating a tool (e.g., using an Allen wrench inserted into the countersunk hole of a regular hexagonal prism), rotates the unlocking screw 202, causing the unlocking slider to move along with the pin body, inserting the pin body into the I-shaped transverse hole of the microsatellite standard tail accessory 301, completing the locking of the microsatellite 300. Rotate the loading screw 101 in the opposite direction to unscrew and remove the loading screw 101 from the limiting plate 107.

[0051] See Figure 8 After the loading screw 101 is released, the anti-accidental release cover 207 moves from the first position to the second position (lower limit position) under the action of the return spring 208. Its baffle part is misaligned with the axis of the unlocking screw 202, and the baffle part blocks the drive port. At this time, the astronauts cannot unlock the cabin by manually driving the unlocking screw 202, and the motor 201 is not powered inside the space station cabin. Therefore, accidental release of the release device inside the cabin can be completely avoided, thus preventing catastrophic consequences.

[0052] See Figure 8 Satellite Release. After satellite loading is completed, the release device and microsatellite 300 assembly are transported out of the cabin, and the release direction is determined by an external robotic arm. Motor 201 drives the unlocking screw 202 to rotate in the opposite direction, and the pin body of the unlocking pin 203 is pulled out from the I-shaped transverse hole of the microsatellite standard tail accessory 301; the stored energy of the separation spring 104 is released, and the separation spring 104 pushes the push plate 106 to pop out rapidly in the release direction. The push plate 106 simultaneously pushes the microsatellite 300 and provides it with a certain initial velocity, and the microsatellite 300 completes directional release. After popping out, the push plate 106 continues to move upward and contacts the limiting plate 107, which brakes the push plate 106. After completing the release action, the release device can return to the cabin to prepare for the next satellite release.

[0053] In this embodiment, the release device can release microsatellites of various sizes. Under normal operating conditions, the release process is completed by the motor 201 driving the unlocking pin 203 to move. The release kinetic energy of the microsatellite 300 is provided by the elastic potential energy of the separation spring 104. The installation and locking of the microsatellite 300 are both completed manually. In case of failure, the microsatellite can be released manually.

[0054] In this embodiment, during satellite loading, the loading screw 101 is in the screw-in state. Due to the self-locking characteristic of the trapezoidal thread pair, the release spring 104 is reliably locked in the compressed energy storage state, and the release action will not be accidentally triggered. Under this safety premise, the microsatellite's pin locking action is completed by the astronaut in the cabin using a manual operating tool to drive the unlocking screw 202. The motor 201 is not powered throughout the process, ensuring the safety of the pin action. After the pin is locked, the loading screw 101 is screwed out in the reverse direction and removed. At this time, the compressive elastic force (energy storage) formed by the compression of the release spring 104 is completely borne by the pin (the pin shaft body of the unlocking pin 203). If the astronaut accidentally operates the unlocking screw 202 in the cabin and pulls out the pin, the compressive elastic force of the release spring 104 will be immediately released and push the push plate 106 out, causing a microsatellite accidental release. To address this, an anti-misoperation cover 207 is provided on the pin-pulling base 204 in this embodiment. After the loading screw 101 is unscrewed, the anti-misoperation cover 207 automatically moves to the second position under the action of the return spring 208, sealing the drive port of the unlocking screw 202. This purely mechanical structure fundamentally prevents the risk of accidental release of the microsatellite due to astronauts accidentally operating the unlocking screw 202 inside the cabin, ensuring the safety of the loading process. The pin-pulling release action of the microsatellite is completed by the motor 201 driving the unlocking screw 202 to rotate in the opposite direction after the device is transported outside the cabin, realizing automatic release outside the cabin.

[0055] Example 2 See Figure 7 and Figure 8 This embodiment provides a microsatellite on-orbit release method based on the above embodiment one, used in the logic-preventing microsatellite on-orbit release device as described in embodiment one, including the following steps: Pre-loading status settings. See [link / reference] Figure 7 The loading screw 101 is rotated so that it spirals upward through the center threaded hole of the limiting plate 107. The upper end of the loading screw 101 passes through the bearing 108, and its top end abuts against the anti-misoperation cover 207. This drives the anti-misoperation cover 207 to move upward from the second position to the first position, overcoming the force of the return spring 208. The through hole is aligned with the axis of the unlocking screw 202, and the drive port is exposed. Continuing to rotate the loading screw 101, the limiting plate 107 moves downward under the action of the trapezoidal thread. This, through the guide rod 105, drives the push plate 106 to move downward in the opposite direction to the release direction, compressing the release spring 104 and causing the release spring 104 to be pressed and stored.

[0056] Satellite loading. See also Figure 4 , Figure 5 and Figure 7Move the microsatellite 300 above the push plate 106, ensuring its lower surface aligns with the upper surface of the push plate 106. Insert the lower cylinder of the microsatellite standard tail accessory 301 into the cylindrical blind hole on the upper side of the pin-pulling base 204, aligning the I-shaped transverse hole with the pin body. The astronaut rotates the unlocking screw 202 via the drive port, causing the unlocking slider and pin body to translate, inserting the pin body into the I-shaped transverse hole, thus locking the microsatellite 300. Rotate the loading screw 101 in the opposite direction to remove it from the limiting plate 107.

[0057] See Figure 8 After the loading screw 101 is released from loading, the anti-accidental release cover 207 moves from the first position to the second position under the action of the return spring 208. The baffle part is misaligned with the axis of the unlocking screw 202, blocking the drive port. Astronauts cannot unlock the cabin by manually driving the unlocking screw 202, and the motor 201 is not powered inside the space station cabin, completely avoiding accidental release inside the cabin.

[0058] Satellite released. See also Figure 8 After satellite loading is completed, the release device and microsatellite 300 assembly are transported out of the cabin, and the release direction is determined by an external robotic arm. Motor 201 drives the unlocking screw 202 to rotate in the opposite direction, pulling the pin body out of the I-shaped transverse hole. The release spring 104 releases its stored energy, pushing the push plate 106 out along the release direction and ejecting the microsatellite 300. The push plate 106 contacts the limiting plate 107 to achieve braking. After completing the release action, the release device can return to the cabin to prepare for the next satellite release.

[0059] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they shall still fall within the protection scope of the present invention.

Claims

1. A logic-based anti-misoperation microsatellite on-orbit release device, characterized in that, include: Base; Push plates are spaced apart on the base, and at least one elastic element is provided between the base and the push plates; The loading unit is configured to drive the push plate to move relative to the base in a direction opposite to the release direction, so as to compress the elastic element to store energy; A pin base is fixedly connected to the base; The unlocking screw is rotatably connected to the pull pin base, and one end of the unlocking screw is provided with a drive port suitable for manual operation tools to access; The unlocking pin includes an unlocking slider and a pin body connected to the unlocking slider. The unlocking slider is threadedly engaged with the unlocking screw. The pin body passes through the pin base and slides with the pin base to be used for inserting or removing the locking hole of the microsatellite tail accessory. The unlocking screw is configured to rotate to drive the unlocking slider and the pin body to translate. The microsatellite tail accessory is used to connect to the microsatellite. An anti-misoperation cover is slidably connected to the pin base. The anti-misoperation cover has a first position and a second position. In the first position, the drive port is exposed to allow the manual operating tool to access it. In the second position, the anti-misoperation cover blocks the drive port. An anti-misoperation elastic element is installed between the anti-misoperation cover and the pull pin base, and is used to apply a force toward the second position to the anti-misoperation cover; The top end of the loading part is configured to abut against the anti-misoperation cover plate during loading to drive the anti-misoperation cover plate to move from the second position to the first position against the force of the anti-misoperation elastic member; when the loading part exits loading, the anti-misoperation cover plate moves from the first position to the second position under the action of the anti-misoperation elastic member.

2. The logic-based anti-misoperation microsatellite on-orbit release device according to claim 1, characterized in that, The anti-misoperation cover includes a baffle portion and a sliding rod portion connected to the baffle portion; the pin base is provided with a guide hole, and the sliding rod portion slides in cooperation with the guide hole to allow the anti-misoperation cover to slide between the first position and the second position.

3. The logic-based anti-misoperation microsatellite on-orbit release device according to claim 2, characterized in that, The baffle portion is provided with a through hole; at the first position, the through hole is aligned with the axis of the unlocking screw, and the drive port is exposed through the through hole; at the second position, the baffle portion is offset from the axis of the unlocking screw to block the drive port.

4. The logic-based anti-misoperation microsatellite on-orbit release device according to claim 1, characterized in that, The anti-misoperation elastic element is a reset spring, which is connected between the anti-misoperation cover and the pin base.

5. The logic-based anti-misoperation microsatellite on-orbit release device according to claim 1, characterized in that, The loading part includes a loading screw and a limiting plate. The limiting plate is linked to the push plate and is located on the side of the base away from the push plate. The loading screw is threadedly engaged with the limiting plate so that the limiting plate and the push plate can be moved in the opposite direction to the release direction by rotation. The loading screw has a trapezoidal external thread in the middle and the limiting plate has a trapezoidal internal thread. The trapezoidal external thread and the trapezoidal internal thread engage to form a threaded pair.

6. The logic-based anti-misoperation microsatellite on-orbit release device according to claim 5, characterized in that, The sliding trajectory of the anti-misoperation cover is coaxial with the rotation axis of the loading screw.

7. The logic-based anti-misoperation microsatellite on-orbit release device according to claim 5, characterized in that, It also includes at least one guide rod and at least one spring guide cylinder, the spring guide cylinder being fixed to the base, one end of the guide rod being fixedly connected to the push plate, and the other end passing through the base and being fixedly connected to the limiting plate, the outer wall of the guide rod being slidably engaged with the inner wall of the spring guide cylinder; the elastic element is a separation spring, the separation spring being sleeved on the guide rod and the spring guide cylinder.

8. The logic-based anti-misoperation microsatellite on-orbit release device according to claim 1, characterized in that, It also includes a motor, which is fixed to the base, and the output shaft of the motor is fixedly connected to the other end of the unlocking screw.

9. The logic-based anti-misoperation microsatellite on-orbit release device according to claim 1, characterized in that, The pull pin base, the unlocking screw, the unlocking pin, the anti-misoperation cover, and the anti-misoperation elastic element form an independent modular structure, which is detachably fixed to the base.

10. A method for releasing a microsatellite in orbit, used in the logic-based, error-proof microsatellite in-orbit release device as described in any one of claims 1 to 9, characterized in that, Includes the following steps: Before loading, the loading unit performs loading, and the loading unit drives the anti-misoperation cover to move from the second position to the first position against the force of the anti-misoperation elastic element, and the driving port is exposed; The loading part drives the push plate to move in the opposite direction to the release direction, compressing the elastic element to store energy; During loading, the microsatellite tail accessory connected to the microsatellite is placed on the pin base. The unlocking screw is rotated through the drive port, which drives the pin body to move and insert into the locking hole of the microsatellite tail accessory. The loading part is unloaded, and the anti-misoperation cover plate moves from the first position to the second position under the action of the anti-misoperation elastic element, blocking the drive port. Upon release, the motor drives the unlocking screw to rotate in the opposite direction, causing the pin body to move in the opposite direction and exit the lock hole. The elastic element releases its stored energy, pushing the push plate to pop out along the release direction and launching the microsatellite.

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