Inertial release device and method for micro-nano satellite accompanying space station based on mother-and-child satellite

Abstract

The invention discloses an inertial release device and method for a space station accompanying micro-nano satellite based on a mother-and-child type satellite, comprising: a mother satellite is provided with a release device; a sub-satellite is arranged in the release device; a main board is arranged on a base, a docking mechanism is arranged on one side of the mother satellite, and the main board is connected with a bent plate through a rotating shaft; an electromagnet is arranged on the main board, and the electromagnet controls the switch of the bent plate and the docking mechanism, thereby controlling the mother satellite on a spring tray; a first steering gear is arranged on a groove of the mother satellite and connected with a baffle; the baffle is arranged on the edges around the mother satellite, and is used to prevent the sub-satellite from detaching from the release mechanism; the spring tray is used to hold the mother satellite, and a second steering gear is connected to a bobbin to control the rotation of the bobbin; one end of a rope system is fixed on the mother satellite, and the other end is fixed on the bobbin; a power supply supplies power to the second steering gear; the invention can form an accompanying relationship between the sub-satellite and the mother satellite, and complete data interaction between the sub-satellite and the mother satellite.

Description

Technical Field

[0001] The present invention belongs to the technical field of micro-nano satellite on-orbit deployment, and relates to an inertial release device and method for a micro-nano satellite accompanying a space station based on a mother-and-child satellite. Background Art

[0002] Due to breakthroughs in launch vehicle technology, today's rockets have a larger payload, and space actuators such as cargo spacecraft have the ability to perform more additional tasks. Therefore, satellite size and launch methods are no longer limited to the previous one-satellite-per-rocket launch method. More methods have been introduced, such as multiple satellites per rocket, releasing satellites from cargo spacecraft, releasing mother-and-daughter satellites, and releasing satellites from space stations.

[0003] However, looking back at the many successful on-orbit satellite release missions in history, there are few studies on space station companion satellites. Most of the missions are only to release the companion satellite to stay on the designated orbit and then the main payload will leave the current position. In order to prevent the conflict between the ground launch command for the main payload and the released companion satellite, it is generally stipulated that the control command for the companion satellite will be launched 45 minutes after the companion satellite is separated from the main payload to enable it to perform the mission. In today's companion satellite release scheme, it is impossible to form a companion relationship between the satellite and the main payload, such as the space station, to form a constellation to achieve a certain task; at the same time, in actual tasks, if a companion relationship between the satellite and the space station is required, it is often necessary for the satellite to have a certain position and speed relative to the space station under initial conditions. Today's satellite release device is obviously unable to achieve such precise control, and it can even be said that no relevant research has been done. Therefore, there is an urgent need for a release and recovery method for a space station companion satellite. Summary of the invention

[0004] The purpose of the present invention is to solve the problems in the prior art and to provide a space station companion micro-nano satellite inertial release device and method based on a mother-and-child satellite, which can form a companion flight relationship between the child satellite and the mother satellite and complete data exchange between the child satellite and the mother satellite.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] The inertial release device for the micro-nano satellite accompanying the space station based on the mother-and-child satellite includes: a mother satellite, a child satellite, a base, a docking piece, a tether and a release device;

[0007] The mother satellite includes data connectors and Hall effect thrusters;

[0008] Hall effect thrusters are arranged around the mother satellite to promote the rotation of the mother satellite; the data connector is located on one side of the mother satellite and is connected to the data interface of the sub-satellite; the mother satellite is connected to the base through a docking piece, and the docking piece is arranged on the base; the mother satellite is provided with a release device; the sub-satellite is arranged in the release device; one end of the rope is fixed on the base, and the other end is connected to the mother satellite, which is used to recover the mother satellite to the base.

[0009] A further improvement of the present invention is:

[0010] The mother satellite also includes a first steering gear, a baffle, a solar panel and a docking mechanism; the base includes a bobbin, a bottom plate, a spring tray, a power supply and a second steering gear; the docking piece includes a bending plate, an electromagnet and a main board; the base includes a bobbin, a bottom plate, a spring tray, a power supply and a second steering gear;

[0011] The main board is arranged on the base, the docking mechanism is arranged on one side of the mother satellite, and the main board is connected to the bending plate through a rotating shaft; the electromagnet is arranged on the main board, and the electromagnet controls the switch of the bending plate and the docking mechanism, thereby controlling the mother satellite on the spring tray;

[0012] The first servo is arranged on the groove of the mother satellite and connected to the baffle; the baffle is arranged on the edges around the mother satellite to prevent the sub-satellite from detaching from the release mechanism; the solar panel is used to convert solar energy into electrical energy to supply power to the mother satellite;

[0013] The spring tray, power supply and second servo are located on one side of the base plate, and the spring tray is used to hold the mother satellite; the spool is located on the other side of the base plate, and the second servo is connected to the spool to control the rotation of the spool; one end of the rope is fixed on the mother satellite, and the other end is fixed on the spool; the power supply supplies power to the second servo.

[0014] The release device is arranged on four sides of the mother satellite; the release device comprises: a first release device and a second release device; the first release device is arranged on the upper end of the second release device; the accommodation space of the second release device is equivalent to the accommodation space of two first release devices; the second release device is equivalent to the superposition of two first release devices;

[0015] The first releasing device comprises: a platform and a slide rail; there are a plurality of slide rails which are arranged opposite to each other and fixedly connected to one side of the platform, and the slide rails are used to place the sub-satellite.

[0016] The Hall effect thruster adopts the HEP-100MF model, which is used to control the attitude of the mother satellite and its own rotational power.

[0017] The mother satellite also includes a release mechanism mounting hole; the first release device also includes a mounting threaded through hole; the mounting threaded through hole matches the release mechanism mounting hole, and screws pass through the mounting threaded through hole and the release mechanism mounting hole to fix the release mechanism.

[0018] The spool includes: a driving spool and a driven spool; the base also includes: a driving gear and a driven gear; the driving gear, the driving spool, the driven gear and the driven spool are located on the other side of the base plate, the second servo is connected to the driving spool, the driving gear is sleeved on the driving spool, and the driven gear is sleeved on the driven spool; the driving gear is connected to the driven gear, the driving gear drives the driven gear to rotate, and then drives the driven spool to rotate.

[0019] The rope system is a double rope design; one end of one rope is connected to the active spool and the other end is connected to the mother satellite, and one end of the other rope is connected to the driven spool and the other end is connected to the mother satellite. The electromagnet is connected to a power source to supply power to the electromagnet.

[0020] A method for inertial release of a micro-nano satellite accompanying a space station based on a mother-and-child satellite, comprising:

[0021] S1, not released: In the initial state, the barrier is closed to prevent the sub-satellite from slipping off the release device; the rope is wound around the active and driven spools, the electromagnet is energized, the docking mechanism presses down the bent plate, the mother satellite is on the spring tray, and the spring tray is in a compressed state;

[0022] S2, waiting for release: the electromagnet is powered off, the docking mechanism is separated from the bending plate, and the mother satellite is released away from the base under the action of the spring tray. The rope is released from the active and driven shafts driven by the mother satellite; the first servo drives the baffle to rotate and open, and the mother satellite starts to rotate under the action of the Hall effect thruster; the sub-satellite is thrown out due to inertia, and a flying relationship is formed between the sub-satellite and the mother satellite; after releasing the specified number of sub-satellites, the first servo drives the baffle to rotate and close;

[0023] S3, data docking: after completing the mission, the sub-satellite returns to the mother satellite, the data connector is connected to the data interface, the sub-satellite is charged and the data is transferred, and at the same time, the first steering gear drives the baffle to rotate and open, the sub-satellite returns to the release device, and the baffle rotates to close the release device;

[0024] S4. Recovery: All sub-satellites return to the release device, the second servo drives the active line shaft to rotate, and the active gear drives the driven gear to rotate, and then drives the driven line shaft to rotate, and the rope system set on the active line shaft and the driven line shaft is recovered. The mother satellite is recovered to the base under the action of the rope system, and the bending plate is pressed to the initial position to start the electromagnet adsorption, and the spring tray is compressed to prepare for the next launch.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] The present invention arranges the sub-satellite in the release device of the mother satellite, and realizes the release and fixation of the mother satellite by fixing and releasing the docking piece and the base; under the action of the Hall effect thruster, the mother satellite rotates, and the sub-satellite is released from the release device, forming a flying companion relationship between the sub-satellite and the mother satellite; the present invention can re-fix the mother satellite on the base through the rope system, and the sub-satellite can return to the mother satellite in time to replenish energy and upload mission data, thereby completing the data interaction between the sub-satellite and the mother satellite.

[0027] Furthermore, the sub-satellite has the advantages of simple release principle, stable execution, and low malfunction. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0029] Figure 1 It is an overall schematic diagram;

[0030] Figure 2 This is a schematic diagram of the mother satellite;

[0031] Figure 3 is a schematic diagram of a sub-satellite;

[0032] Figure 4 is a schematic diagram of the base;

[0033] Figure 5 is a schematic diagram of the docking parts;

[0034] Figure 6 is a schematic diagram of the release device;

[0035] Figure 7 Schematic diagram of satellite workflow.

[0036] Among them, 1-mother satellite, 2-sub-satellite, 3-base, 4-docking piece, 5-tether, 6-first release device, 7-second release device, 1.2-release mechanism mounting hole, 1.3-data connector, 1.4-first servo, 1.5-blocking bar, 1.6-Hall effect thruster, 1.7-docking mechanism, 1.8-solar panel; 2.1-data interface, 3.1-driving gear; 3.2-driven bobbin; 3.3-bottom plate; 3.4-spring tray; 3.5-second servo, 4.1-bending plate, 4.2-electromagnet, 4.3-main board, 6.1-slide rail, 6.3-installation threaded through hole. DETAILED DESCRIPTION

[0037] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0038] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0039] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0040] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0041] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0042] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it 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 it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] The present invention is further described in detail below in conjunction with the accompanying drawings:

[0044] See also Figure 1 The present invention discloses an inertial release device for a space station flying micro-nano satellite based on a mother-and-child satellite, comprising: a mother satellite 1, a child satellite 2, a base 3, a docking piece 4, a tether 5 and a release device;

[0045] The mother satellite 1 includes a data connector 1.3, a first steering gear 1.4, a stop bar 1.5, a Hall effect thruster 1.6 and a docking mechanism 1.7; the base 3 includes a bobbin, a bottom plate 3.3, a spring tray 3.4, a power supply and a second steering gear 3.5; the docking member 4 includes a bent plate 4.1, an electromagnet 4.2 and a main board 4.3;

[0046] The mother satellite 1 is provided with a release device; the sub-satellite 2 is arranged in the release device; the main board 4.3 is arranged on the base 3, the docking mechanism 1.7 is arranged on one side of the mother satellite 1, and the main board 4.3 is connected with the bending plate 4.1 through a rotating shaft; the electromagnet 4.2 is arranged on the main board 4.3, and the electromagnet 4.2 controls the switch of the bending plate 4.1 and the docking mechanism 1.7, so that the mother satellite 1 is on the spring tray 3.4; in the free state without force, the bending plate 4.1 and the main board 4.3 form an angle of 90 degrees.

[0047] The Hall effect thrusters 1.6 are arranged around the mother satellite 1 to drive the mother satellite 1 to rotate. The first servo 1.4 is arranged on the groove of the mother satellite 1 and connected to the stop bar 1.5. The stop bar 1.5 is arranged on the edge around the mother satellite 1 to prevent the sub-satellite 2 from detaching from the release mechanism. The data connector 1.3 is located on one side of the mother satellite 1 and connected to the data interface 2.1 of the sub-satellite. The data connector 1.3 and the data interface 2.1 are both designed with internal rounded corners to avoid collision during docking. The data interface 2.1 is horn-shaped.

[0048] The spring tray 3.4, the power supply and the second steering gear 3.5 are located on one side of the bottom plate 3.3. The spring tray 3.4 is used to hold the mother satellite 1. The spool is located on the other side of the bottom plate 3.3. The second steering gear 3.5 is connected to the spool to control the rotation of the spool. One end of the rope 5 is fixed on the mother satellite 1, and the other end is fixed on the spool. The power supply supplies power to the second steering gear 3.5. There are two spring trays 3.4 to share the weight of the mother satellite 1.

[0049] The mother satellite 1 further comprises a solar panel 1.8; the solar panel 1.8 is used to convert solar energy into electrical energy to supply power to the mother satellite 1.

[0050] The mother satellite 1 is a cubic structure, wherein the solar panels 1.8 are arranged on the top surface of the mother satellite 1;

[0051] Data connectors 1.3, Hall effect thrusters 1.6 and docking mechanisms 1.7 are arranged on the four sides of the mother satellite 1, and the first steering gear 1.4 and the stop bar 1.5 are arranged on the edges where each side intersects.

[0052] The release device is arranged on the four sides of the mother satellite 1, and can accommodate a large number of sub-satellites. The release device includes: a first release device 6 and a second release device 7; the first release device 6 is arranged on the upper end of the second release device 7; the accommodation space of the second release device 7 is equivalent to the accommodation space of two first release devices 6; the second release device 7 is equivalent to the stacking of two first release devices 6; the first release device 6 includes: a platform and a slide rail 6.1; the slide rail 6.1 is a plurality of rails, which are arranged opposite to each other and fixedly connected to one side of the platform, and the slide rail 6.1 is used to place the sub-satellite 2.

[0053] The Hall Effect Thruster 1.6 adopts the HEP-100MF model and is used to control the attitude of the mother satellite 1 and its own rotational power.

[0054] The mother satellite 1 also includes a release mechanism mounting hole 1.2; the first release device 6 also includes a mounting threaded through hole 6.3; the mounting threaded through hole 6.3 matches the release mechanism mounting hole 1.2, and screws pass through the mounting threaded through hole 6.3 and the release mechanism mounting hole 1.2 to fix the release mechanism.

[0055] The spool includes: a driving spool and a driven spool 3.2; the base 3 also includes: a driving gear 3.1 and a driven gear; the driving gear 3.1, the driving spool, the driven gear and the driven spool 3.2 are located on the other side of the bottom plate 3.3, the second steering gear 3.5 is connected to the driving spool, the driving gear 3.1 is sleeved on the driving spool, and the driven gear is sleeved on the driven spool 3.2; the driving gear 3.1 is connected to the driven gear, the driving gear 3.1 drives the driven gear to rotate, and then drives the driven spool 3.2 to rotate.

[0056] The rope system 5 is a double rope design; one end of one rope is connected to the driving line shaft and the other end is connected to the mother satellite 1, and one end of the other rope is connected to the driven line shaft 3.2 and the other end is connected to the mother satellite 1. The electromagnet 4.2 is connected to the battery to supply power to the electromagnet 4.2.

[0057] A method for inertial release of a micro-nano satellite accompanying a space station based on a mother-and-child satellite, comprising:

[0058] S1, not released: in the initial state, the barrier bar 1.5 is in a closed state to prevent the sub-satellite 2 from slipping off the release device; the rope 5 is wound around the active spool and the driven spool 3.2, the electromagnet 4.2 is energized, the docking mechanism 1.7 presses down the bent plate 4.1, the mother satellite 1 is on the spring tray 3.4, and the spring tray 3.4 is in a compressed state;

[0059] S2, waiting for release: the electromagnet 4.2 is powered off, the docking mechanism 1.7 is separated from the bent plate 4.1, and the mother satellite 1 is released away from the base 3 under the action of the spring tray 3.4. The tether 5 is released from the active line shaft and the driven line shaft 3.2 driven by the mother satellite 1; the first steering gear 1.4 drives the baffle 1.5 to rotate and open, and under the action of the Hall effect thruster 1.6, the mother satellite 1 starts to rotate; due to inertia, the sub-satellites 2 are thrown out, and after the specified number of sub-satellites are released, the first steering gear 1.4 drives the baffle 1.5 to rotate and close;

[0060] S3, data docking: after completing the mission, the sub-satellite 2 returns to the mother satellite 1, the data connector 1.3 is connected to the data interface 2.1, the charging of the sub-satellite 2 and the data transfer are completed, and at the same time, the first steering gear 1.4 drives the stop bar 1.5 to rotate and open, the sub-satellite 2 returns to the release device, and the stop bar 1.5 rotates to close the release device;

[0061] S4, recovery: All sub-satellites 2 return to the release device, the second steering gear 3.5 drives the active line shaft to rotate, and at the same time the active gear 3.1 drives the driven gear to rotate, and then drives the driven line shaft 3.2 to rotate, and the rope 5 set on the active line shaft and the driven line shaft 3.2 is recovered. The mother satellite 1 is recovered to the base 3 under the action of the rope 5, and the bending plate 4.1 is pressed to the initial position to start the electromagnet 4.2 to adsorb, and the spring tray 3.4 is compressed to prepare for the next launch.

[0062] During the recovery process of the mother satellite 1, the Hall effect thruster 1.6 will continuously adjust the flight state and flight speed of the mother satellite 1. At the same time, the driving gear 3.1 and the driven gear will retract the rope 5 to continuously move the mother satellite 1 closer to the base 3, and finally the mother satellite 1 will land on the base 3.

[0063] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A space station companion micro-nano satellite inertial release device based on a mother-and-child satellite, characterized in that: include: A mother satellite (1), a daughter satellite (2), a base (3), a docking piece (4), a tether (5) and a release device; The mother satellite (1) comprises a data connector (1.3) and a Hall effect thruster (1.6); The Hall effect thrusters (1.6) are arranged around the mother satellite (1) and are used to propel the mother satellite (1) to rotate. The data connector (1.3) is located on one side of the mother satellite (1) and is connected to the data interface (2.1) of the sub-satellite. The mother satellite (1) is connected to the base (3) via a docking piece (4), and the docking piece (4) is arranged on the base (3). The mother satellite (1) is provided with a release device. The sub-satellite (2) is arranged in the release device. One end of the tether (5) is fixed to the base (3), and the other end is connected to the mother satellite (1), and is used to recover the mother satellite (1) to the base (3). The mother satellite (1) further comprises a first steering gear (1.4), a stop bar (1.5), a solar panel (1.8) and a docking mechanism (1.7); the base (3) comprises a bobbin, a bottom plate (3.3), a spring tray (3.4), a power source and a second steering gear (3.5); the docking member (4) comprises a bent plate (4.1), an electromagnet (4.2) and a main board (4.3); the base (3) comprises a bobbin, a bottom plate (3.3), a spring tray (3.4), a power source and a second steering gear (3.5); The main board (4.3) is arranged on the base (3), the docking mechanism (1.7) is arranged on one side of the mother satellite (1), and the main board (4.3) is connected to the bending plate (4.1) via a rotating shaft; the electromagnet (4.2) is arranged on the main board (4.3), and the electromagnet (4.2) controls the switch of the bending plate (4.1) and the docking mechanism (1.7), thereby controlling the mother satellite (1) on the spring tray (3.4); The first steering gear (1.4) is arranged on a groove of the mother satellite (1) and is connected to a stop bar (1.5); the stop bar (1.5) is arranged on the edges around the mother satellite (1) and is used to prevent the sub-satellite (2) from detaching from the release mechanism; the solar panel (1.8) is used to convert solar energy into electrical energy to supply power to the mother satellite (1); The spring tray (3.4), the power supply and the second steering gear (3.5) are located on one side of the base plate (3.3); the spring tray (3.4) is used to hold the mother satellite (1); the spool is located on the other side of the base plate (3.3); the second steering gear (3.5) is connected to the spool to control the rotation of the spool; one end of the rope (5) is fixed to the mother satellite (1) and the other end is fixed to the spool; the power supply supplies power to the second steering gear (3.5); The release device is arranged on four sides of the mother satellite (1); the release device comprises: a first release device (6) and a second release device (7); the first release device (6) is arranged at the upper end of the second release device (7); the accommodation space of the second release device (7) is equivalent to the accommodation space of two first release devices (6); the second release device (7) is equivalent to the stacking of two first release devices (6); The first release device (6) comprises: a platform and a slide rail (6.1); the slide rail (6.1) comprises a plurality of slide rails (6.1) which are arranged opposite to each other and fixedly connected to one side of the platform; the slide rail (6.1) is used to place the sub-satellite (2).

2. The inertial release device for accompanying micro-nano satellites for a space station based on a mother-and-child satellite according to claim 1 is characterized in that: The Hall effect thruster (1.6) is a HEP-100MF model and is used to control the attitude and rotational power of the mother satellite (1).

3. The inertial release device for accompanying micro-nano satellites for a space station based on a mother-and-child satellite according to claim 2 is characterized in that: The mother satellite (1) further comprises a release mechanism mounting hole (1.2); the first release device (6) further comprises a mounting threaded through hole (6.3); the mounting threaded through hole (6.3) matches the release mechanism mounting hole (1.2), and a screw passes through the mounting threaded through hole (6.3) and the release mechanism mounting hole (1.2) to fix the release mechanism.

4. The inertial release device for accompanying micro-nano satellites for a space station based on a mother-and-child satellite according to claim 3 is characterized in that: The spool comprises: a driving spool and a driven spool (3.2); the base (3) further comprises: a driving gear (3.1) and a driven gear; the driving gear (3.1), the driving spool, the driven gear and the driven spool (3.2) are located on the other side of the bottom plate (3.3); the second steering gear (3.5) is connected to the driving spool; the driving gear (3.1) is sleeved on the driving spool; the driven gear is sleeved on the driven spool (3.2); the driving gear (3.1) is connected to the driven gear; the driving gear (3.1) drives the driven gear to rotate, thereby driving the driven spool (3.2) to rotate.

5. The inertial release device for accompanying micro-nano satellites for a space station based on a mother-and-child satellite according to claim 4 is characterized in that: The rope system (5) is a double-rope design; one end of one rope is connected to the active line shaft, and the other end is connected to the mother satellite (1); one end of the other rope is connected to the driven line shaft (3.2), and the other end is connected to the mother satellite (1).

6. The inertial release device for accompanying micro-nano satellites for a space station based on a mother-and-child satellite according to claim 5 is characterized in that: The electromagnet (4.2) is connected to a power source to supply power to the electromagnet (4.2).

7. A method for releasing a space station companion micro-nano satellite inertial release device based on a mother-and-child satellite according to claim 6, characterized in that: include: S1, not released: in the initial state, the blocking bar (1.5) is in a closed state to prevent the sub-satellite (2) from slipping off the release device; the rope (5) is wound around the driving line shaft and the driven line shaft (3.2), the electromagnet (4.2) is energized, the docking mechanism (1.7) presses down the bending plate (4.1), the mother satellite (1) is on the spring tray (3.4), and the spring tray (3.4) is in a compressed state; S2, waiting for release: the electromagnet (4.2) is powered off, the docking mechanism (1.7) is separated from the bending plate (4.1), the mother satellite (1) is released away from the base (3) under the action of the spring tray (3.4), the rope system (5) is released from the driving line shaft and the driven line shaft (3.2) driven by the mother satellite (1); the first steering gear (1.4) drives the baffle (1.5) to rotate to open, and under the action of the Hall effect thruster (1.6), the mother satellite (1) starts to rotate; due to the inertia of the sub-satellite (2) being thrown out, a flying relationship is formed between the sub-satellite and the mother satellite; after releasing a specified number of sub-satellites, the first steering gear (1.4) drives the baffle (1.5) to rotate to close; S3, data docking: after completing the mission, the sub-satellite (2) returns to the mother satellite (1), the data connector (1.3) is connected to the data interface (2.1), the charging of the sub-satellite (2) and the data transfer are completed, and at the same time, the first steering gear (1.4) drives the blocking bar (1.5) to rotate and open, the sub-satellite (2) returns to the release device, and the blocking bar (1.5) rotates to close the release device; S4, recovery: All sub-satellites (2) return to the release device, the second steering gear (3.5) drives the active line shaft to rotate, and at the same time the active gear (3.1) drives the driven gear to rotate, thereby driving the driven line shaft (3.2) to rotate, and the rope system (5) set on the active line shaft and the driven line shaft (3.2) is recovered. Under the action of the rope system (5), the mother satellite (1) is recovered to the base (3), the bending plate (4.1) is pressed to the initial position, the electromagnet (4.2) is activated for adsorption, and the spring tray (3.4) is compressed to prepare for the next launch.

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