CN115231002A - Space station satellite-flying micro-nano satellite inertia release device and method based on primary and secondary satellites - Google Patents
Space station satellite-flying micro-nano satellite inertia release device and method based on primary and secondary satellites Download PDFInfo
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- CN115231002A CN115231002A CN202210987920.1A CN202210987920A CN115231002A CN 115231002 A CN115231002 A CN 115231002A CN 202210987920 A CN202210987920 A CN 202210987920A CN 115231002 A CN115231002 A CN 115231002A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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Abstract
The invention discloses a space station flight micro-nano satellite inertia release device and method based on a primary-secondary satellite, and the device comprises the following steps: the mother satellite is provided with a release device; the sub-satellite is arranged in the release device; the main board is arranged on the base, the butt joint mechanism is arranged on one side of the mother satellite, and the main board is connected with the bent board through a rotating shaft; the electromagnet is arranged on the main board and controls the switch of the bent plate and the butt joint mechanism, so that the mother satellite is controlled to be on the spring tray; the first steering engine is arranged on a groove of the primary satellite and is connected with the barrier strip; the barrier strips are arranged on the edges around the mother satellite and used for preventing the child satellite from being separated from the release mechanism; the spring tray is used for supporting the mother satellite, and the second steering engine is connected with the bobbin and used for controlling the rotation of the bobbin; one end of the rope system is fixed on the mother satellite, and the other end of the rope system is fixed on the spool; the power supply supplies power to the second steering engine; the satellite tracking method and the satellite tracking system can enable the child satellite and the mother satellite to form the accompanying relationship and complete data interaction between the child satellite and the mother satellite.
Description
Technical Field
The invention belongs to the technical field of on-orbit deployment of micro-nano satellites, and relates to a space station flight-accompanying micro-nano satellite inertia release device and method based on a primary and secondary satellite.
Background
Due to the breakthrough of the carrier rocket technology, the rocket has larger load capacity at present, and space actuating mechanisms such as the freight ship and the like also have the capability of executing more additional tasks, so the size and the launching mode of the satellite are not limited to the launching mode of one rocket and one satellite in the past, and a plurality of means such as one rocket and more satellites, the release of the freight ship satellite, the release of the primary and secondary satellite, the release of the space station satellite and the like are introduced more.
However, throughout the history of many successful in-orbit satellite release tasks, there is little research on satellite-flying space stations, and most tasks are only to release the satellite-flying space stations and leave the main load away from the current position after the satellite-flying space stations stay above the designated orbit, to prevent a conflict between the terrestrial transmission of the command for the primary load and the release of the satellite, it is generally provided that the control command for the satellite is transmitted 45 minutes after the satellite is separated from the primary load, so that it performs its task. In the current release scheme of the satellite, the satellite and a main load such as a space station cannot form a satellite-accompanying relationship to form a constellation so as to realize a certain task; meanwhile, in a practical task, if a satellite and a space station need to be in a satellite-to-flight relationship and even a certain position and speed of the satellite relative to the space station under an initial condition are often required, the current satellite release device obviously cannot be controlled precisely, and even researches on relevant aspects are not made. Therefore, a method for releasing and recovering the space station satellite is needed.
Disclosure of Invention
The invention aims to solve the problems in the prior art and provides a space station satellite-accompanying micro/nano satellite inertia release device and method based on a primary and secondary satellite, which can form an accompanying relationship between a secondary satellite and a primary satellite and complete data interaction between the secondary satellite and the primary satellite.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
space station companion flight micro-nano satellite inertia release based on primary and secondary satellite includes: the device comprises a mother satellite, a child satellite, a base, a butt joint piece, a rope system and a release device;
the mother satellite comprises a data connector and a Hall effect thruster;
the Hall effect thruster is arranged around the mother satellite and used for pushing the mother satellite to rotate; the data connector is positioned at one side of the mother satellite and connected with the data interface of the child satellite; the mother satellite is connected with the base through a butt joint piece, and the butt joint piece is arranged on the base; the mother satellite is provided with a release device; the sub-satellite is arranged in the releasing device; one end of the rope is fixed on the base, and the other end of the rope is connected to the mother satellite and used for recovering the mother satellite to the base.
The invention is further improved in that:
the primary satellite also comprises a first steering engine, a barrier strip, a solar cell panel and a butt joint mechanism; the base comprises a bobbin, a bottom plate, a spring tray, a power supply and a second steering engine; the butt joint part comprises a bent plate, an electromagnet and a main plate; the base comprises a bobbin, a bottom plate, a spring tray, a power supply and a second steering engine;
the main board is arranged on the base, the butt joint mechanism is arranged on one side of the mother satellite, and the main board is connected with the bent board through a rotating shaft; the electromagnet is arranged on the main board and controls the switch of the bent plate and the butt joint mechanism, so that the mother satellite is controlled to be on the spring tray;
the first steering engine is arranged on a groove of the primary satellite and is connected with the barrier strip; the barrier strips are arranged on the edges around the mother satellite and used for preventing the child satellite from being separated from the release mechanism; the solar cell panel is used for converting solar energy into electric energy and supplying power to the mother satellite;
the spring tray, the power supply and the second steering engine are positioned on one side of the bottom plate, and the spring tray is used for supporting the mother satellite; the second steering engine is connected with the bobbin and controls the rotation of the bobbin; one end of the rope system is fixed on the mother satellite, and the other end of the rope system is fixed on the spool; the power supply supplies power to the second steering engine.
The releasing devices are arranged on four side surfaces of the mother satellite; the releasing device comprises: a first release and a second release; the first release device is arranged at the upper end of the second release device; the accommodating space of the second releasing device is equivalent to the accommodating space of the two first releasing devices; the second release device is formed by overlapping two first release devices;
the first release device includes: a platform and a slide rail; the slide rails are arranged oppositely and fixedly connected with one side of the platform, and the slide rails are used for placing the sub-satellites.
The Hall effect thruster adopts an HEP-100MF model and is used for controlling the attitude and the self-rotation power of the mother satellite.
The mother satellite also comprises a release mechanism mounting hole; the first release device also comprises a mounting threaded through hole; the mounting thread through hole is matched with the mounting hole of the releasing mechanism, and the screw penetrates through the mounting thread through hole and the mounting hole of the releasing mechanism to fix the releasing mechanism.
The bobbin includes: a driving spool and a driven spool; the base still includes: a drive 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 bottom plate, the second steering engine is connected with 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 with the driven gear, and the driving gear drives the driven gear to rotate so as to drive the driven spool to rotate.
The rope system is designed into double ropes; one end of one rope is connected to the driving spool, the other end of the rope is connected to the mother satellite, one end of the other rope is connected to the driven spool, and the other end of the other rope is connected to the mother satellite. The electromagnet is connected with the battery and supplies power to the electromagnet.
A space station satellite-flying micro-nano satellite inertial release method based on a primary-secondary satellite comprises the following steps:
s1, unreleased: in the initial state, the barrier strip is in a closed state, so that the child satellite is prevented from sliding off the release device; the rope system is wound on the driving spool and the driven spool, the electromagnet is electrified, the butt joint mechanism presses down the bent plate, the parent satellite is arranged on the spring tray, and the spring tray is in a pressing state;
s2, to-be-released: when the electromagnet is powered off, the butt joint mechanism is separated from the bent plate, the primary satellite is released to be far away from the base under the action of the spring tray, and the rope is released from the driving spool and the driven spool under the driving of the primary satellite; the first steering engine drives the barrier strip to rotate to open, and the primary satellite starts to rotate under the action of the Hall effect thruster; the inertial subsatellite is thrown out, so that a satellite relationship is formed between the subsatellite and the parent satellite; after a specified number of sub-satellites are released, the first steering engine drives the blocking strips to rotate to be closed;
s3, data docking: the child satellite returns to the parent satellite after completing the task, the data connector is connected with the data interface to complete charging and data transfer of the child satellite, meanwhile, the first steering engine drives the gear strip to rotate to open, the child satellite returns to the release device, and the gear strip rotates to close the release device;
s4, recovering: all child satellite return release, the second steering wheel drives the initiative spool and rotates, and the driving gear drives driven gear simultaneously and rotates, and then drives driven spool and rotate, sets up and withdraws at the tether of initiative spool and driven spool, and female satellite withdraws under the effect of tether to the bottom plate on, and the bending plate starts the electro-magnet to adsorb to initial position, and the hold-down spring tray is in order to prepare for the transmission next time.
Compared with the prior art, the invention has the following beneficial effects:
the invention realizes the release and fixation of the mother satellite by arranging the child satellite in the release device of the mother satellite and fixing and releasing the butt joint piece and the base; under the action of the Hall effect thruster, the parent satellite rotates, the child satellite is released from the release device, and a satellite-following relationship is formed between the child satellite and the parent satellite; the invention can fix the primary satellite on the base again through the tether, and meanwhile, the secondary satellite can return to the primary satellite to supplement energy sources and upload task data in time to complete data interaction between the secondary satellite and the primary satellite.
Furthermore, the sub-satellite has the advantages of simple release principle, stable execution, difficult failure and the like.
Drawings
In order to more clearly explain the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a general schematic;
FIG. 2 is a schematic diagram of a parent satellite;
FIG. 3 is a schematic diagram of a sub-satellite;
FIG. 4 is a schematic view of a base;
FIG. 5 is a schematic view of the interface element;
FIG. 6 is a schematic view of a release device;
fig. 7 is a schematic diagram of a satellite workflow.
The system comprises a mother satellite 1, a son satellite 2, a base 3, a butt joint 4, a rope 5, a first release device 6, a second release device 7, a release mechanism 1.2, a data joint 1.3, a first steering engine 1.4, a barrier strip 1.5, a Hall effect propeller 1.6, a butt joint mechanism 1.7 and a solar panel 1.8; 2.1-data interface, 3.1-driving gear; 3.2-driven spool; 3.3-a base plate; 3.4-spring tray; 3.5-a second steering engine, 4.1-a bent plate, 4.2-an electromagnet, 4.3-a main plate, 6.1-a slide rail and 6.3-a mounting threaded through hole.
Detailed Description
In order to make the objects, 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 with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. are used for indicating the orientation or positional relationship based on the orientation or positional relationship shown in the drawings or the orientation or positional relationship which is usually arranged when the product of the present invention is used, the description is merely for convenience and simplicity, and the indication or suggestion that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, cannot be understood as limiting the present invention. Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
Furthermore, the term "horizontal", if present, does not mean that the component is required to be absolutely horizontal, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The invention is described in further detail below with reference to the accompanying drawings:
referring to fig. 1, the invention discloses a space station satellite-flying micro-nano satellite inertial release device based on a primary-secondary satellite, which comprises: the system comprises a mother satellite 1, a child satellite 2, a base 3, a butt joint piece 4, a rope 5 and a release device;
the primary satellite 1 comprises a data connector 1.3, a first steering engine 1.4, a barrier strip 1.5, a Hall effect propeller 1.6 and a butt joint mechanism 1.7; the base 3 comprises a bobbin, a bottom plate 3.3, a spring tray 3.4, a power supply and a second steering engine 3.5; the butt joint part 4 comprises a bent plate 4.1, an electromagnet 4.2 and a main plate 4.3;
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 butt joint mechanism 1.7 is arranged on one side of the mother satellite 1, and the main board 4.3 is connected with the bent board 4.1 through a rotating shaft; the electromagnet 4.2 is arranged on the main board 4.3, the electromagnet 4.2 controls the switch of the bent plate 4.1 and the butt joint mechanism 1.7, and then the mother satellite 1 is arranged on the spring tray 3.4; under the unstressed free state, the bent plate 4.1 and the main plate 4.3 form an included angle of 90 degrees.
The Hall effect thruster 1.6 is arranged around the mother satellite 1 and used for pushing the mother satellite 1 to rotate; the first steering engine 1.4 is arranged on a groove of the mother satellite 1 and is connected with the stop bar 1.5; the barrier strips 1.5 are arranged on the edges around the mother satellite 1 and used for preventing the child satellite 2 from being separated from the release mechanism; the data connector 1.3 is positioned at one side of the mother satellite 1 and is connected with the data interface 2.1 of the child satellite; data connector 1.3 and data interface 2.1 all adopt inside radius design, collision when avoiding the butt joint. The data interface 2.1 is horn-shaped.
The spring tray 3.4, the power supply and the second steering engine 3.5 are positioned on one side of the bottom plate 3.3, and the spring tray 3.4 is used for supporting the mother satellite 1; the bobbin is positioned on the other side of the bottom plate 3.3, and the second steering engine 3.5 is connected with the bobbin and used for controlling the rotation of the bobbin; one end of the rope system 5 is fixed on the mother satellite 1, and the other end is fixed on the bobbin; the power supply supplies power to the second steering engine 3.5. The two spring trays 3.4 can share the weight of the mother satellite 1.
The mother satellite 1 also comprises a solar panel 1.8; the solar cell panel 1.8 is used for converting solar energy into electric energy and supplying power to the mother satellite 1.
The mother satellite 1 is in a cubic structure; wherein the solar cell panel 1.8 is arranged on the top surface of the mother satellite 1;
four sides of the mother satellite 1 are provided with a data connector 1.3, a Hall effect propeller 1.6 and a butt joint mechanism 1.7, and a first steering engine 1.4 and a barrier strip 1.5 are arranged on the intersected edge of each side.
The release devices are arranged on four sides of the mother satellite 1 and can accommodate a large number of child satellites. The releasing device comprises: a first release 6 and a second release 7; the first releasing device 6 is arranged at the upper end of the second releasing device 7; the housing space of the second release means 7 corresponds to the housing space of the two first release means 6; the second release device 7 is formed by overlapping two first release devices 6; the first release device 6 comprises: platform and slide 6.1; the slide rails 6.1 are arranged oppositely and fixedly connected with one side of the platform, and the slide rails 6.1 are used for placing the sub-satellites 2.
The Hall effect thruster 1.6 is of HEP-100MF type and is used for controlling the attitude and the self-rotation power of the mother satellite 1.
The mother satellite 1 also comprises a release mechanism mounting hole 1.2; the first release means 6 further comprise a mounting threaded through hole 6.3; the mounting thread through hole 6.3 is matched with the mounting hole 1.2 of the releasing mechanism, and the screw penetrates through the mounting thread through hole 6.3 and the mounting hole 1.2 of the releasing mechanism to fix the releasing mechanism.
The bobbin includes: a driving spool and a driven spool 3.2; the base 3 further 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 positioned on the other side of the bottom plate 3.3, the second steering gear 3.5 is connected with 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 with the driven gear, and the driving gear 3.1 drives the driven gear to rotate so as to drive the driven spool 3.2 to rotate.
The rope system 5 is designed by double ropes; one end of one rope is connected to the driving spool, the other end of the other rope is connected to the mother satellite 1, one end of the other rope is connected to the driven spool 3.2, and the other end of the other rope is connected to the mother satellite 1. The electromagnet 4.2 is connected with a battery and supplies power to the electromagnet 4.2.
A space station satellite-flying micro-nano satellite inertial release method based on a primary-secondary satellite comprises the following steps:
s1, unreleased: in the initial state, the barrier 1.5 is in the closed state, preventing the subsatellite 2 from sliding off the release device; the rope system 5 is wound on the driving spool and the driven spool 3.2, the electromagnet 4.2 is electrified, the butt joint mechanism 1.7 presses down the bent plate 4.1, the mother satellite 1 is arranged on the spring tray 3.4, and the spring tray 3.4 is in a pressing state;
s2, to-be-released: the electromagnet 4.2 is powered off, the butt joint mechanism 1.7 is separated from the bent plate 4.1, the mother satellite 1 is released to be far away from the base 3 under the action of the spring tray 3.4, and the rope system 5 is released from the driving spool and the driven spool 3.2 under the drive of the mother satellite 1; the first steering engine 1.4 drives the barrier strip 1.5 to rotate for opening, and the primary satellite 1 starts to rotate under the action of the Hall effect thruster 1.6; the sub-satellites 2 are thrown out due to inertia, and after a specified number of sub-satellites are released, the first steering engine 1.4 drives the blocking strips 1.5 to rotate to close;
s3, data docking: the child satellite 2 returns to the mother satellite 1 after completing the task, the data connector 1.3 is connected with the data interface 2.1 to complete charging and data transfer of the child satellite 2, meanwhile, the first steering engine 1.4 drives the stop strip 1.5 to rotate to open, the child satellite 2 returns to the release device, and the stop strip 1.5 rotates to close the release device;
s4, recovering: all child satellite 2 return release, second steering wheel 3.5 drives the initiative spool and rotates, and driving gear 3.1 drives driven gear simultaneously and rotates, and then drives driven spool 3.2 and rotates, sets up and withdraws at the tether 5 of initiative spool and driven spool 3.2, and mother satellite 1 withdraws under the effect of tether 5 to bottom plate 3 on, and the pressure bend plate 4.1 is adsorbed to initial position start-up electro-magnet 4.2, and the pressure spring tray 3.4 is in order to launch next time.
In the recovery process of the mother satellite 1, the Hall effect thruster 1.6 can continuously adjust the flight state and the flight speed of the mother satellite 1, and meanwhile, the driving gear 3.1 and the driven gear shrinkage rope system 5 continuously enable the mother satellite 1 to be close to the bottom plate 3, and finally the mother satellite 1 and the mother satellite land on the bottom plate 3.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. Space station companion flies to receive and receives satellite inertia release device a little based on primary and secondary formula satellite, its characterized in that includes: the satellite comprises a mother satellite (1), a child satellite (2), a base (3), a butt joint piece (4), a rope system (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 thruster (1.6) is arranged around the mother satellite (1) and is used for pushing the mother satellite (1) to rotate; the data connector (1.3) is positioned at one side of the mother satellite (1) and is connected with the data interface (2.1) of the child satellite; the mother satellite (1) is connected with the base (3) through a butt joint piece (4), and the butt joint 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 a release device; one end of the rope system (5) is fixed on the base (3), and the other end of the rope system is connected to the mother satellite (1) and used for recovering the mother satellite (1) to the base (3).
2. The primary satellite-based space station satellite-flying micro-nano satellite inertial release device based on the primary and secondary satellite is characterized in that the primary satellite (1) further comprises a first steering engine (1.4), a barrier strip (1.5), a solar panel (1.8) and a docking mechanism (1.7); the base (3) comprises a spool, a bottom plate (3.3), a spring tray (3.4), a power supply and a second steering engine (3.5); the butt joint part (4) comprises a bent plate (4.1), an electromagnet (4.2) and a main plate (4.3); the base (3) comprises a spool, a bottom plate (3.3), a spring tray (3.4), a power supply and a second steering engine (3.5);
the main board (4.3) is arranged on the base (3), the butt joint mechanism (1.7) is arranged on one side of the mother satellite (1), and the main board (4.3) is connected with the bent board (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 bent plate (4.1) and the butt joint mechanism (1.7) so as to control the parent satellite (1) to be arranged on the spring tray (3.4);
the first steering engine (1.4) is arranged on a groove of the primary satellite (1) and is connected with the barrier strip (1.5); the barrier strips (1.5) are arranged on the edges of the periphery of the primary satellite (1) and are used for preventing the secondary satellite (2) from being separated from the release mechanism; the solar cell panel (1.8) is used for converting solar energy into electric energy and supplying power to the mother satellite (1);
the spring tray (3.4), the power supply and the second steering engine (3.5) are positioned on one side of the bottom plate (3.3), and the spring tray (3.4) is used for supporting the mother satellite (1); the bobbin is positioned on the other side of the bottom plate (3.3), and the second steering engine (3.5) is connected with the bobbin and used for controlling the rotation of the bobbin; one end of the rope system (5) is fixed on the satellite (1), and the other end of the rope system is fixed on the bobbin; the power supply supplies power to the second steering engine (3.5).
3. The primary and secondary satellite-based space station satellite-based micro/nano satellite inertial release device is characterized in that the release devices are arranged on four sides of a primary satellite (1); the release device includes: 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 the two first release devices (6); the second release device (7) is formed by overlapping two first release devices (6);
the first release means (6) comprises: a platform and a slide rail (6.1); the sliding rails (6.1) are arranged oppositely and fixedly connected with one side of the platform, and the sliding rails (6.1) are used for placing the sub-satellites (2).
4. The primary and secondary satellite-based space station satellite-flying micro/nano satellite inertial release device is characterized in that the Hall effect thruster (1.6) is of HEP-100MF type and is used for controlling the attitude and the self-rotation power of the primary satellite (1).
5. The satellite inertial release unit of satellite-based space station satellite-associated micro/nano satellite of claim 4, 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 thread through hole (6.3) is matched with the mounting hole (1.2) of the release mechanism, and the screw penetrates through the mounting thread through hole (6.3) and the mounting hole (1.2) of the release mechanism to fix the release mechanism.
6. The satellite inertial release device of a satellite according to claim 5, wherein 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 with 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 with the driven gear, and the driving gear (3.1) drives the driven gear to rotate so as to drive the driven spool (3.2) to rotate.
7. The primary and secondary satellite-based space station satellite-flying micro/nano satellite inertial release device according to claim 6, wherein the tether (5) is of a double-rope design; one end of one rope is connected to the driving spool, the other end of the other rope is connected to the mother satellite (1), one end of the other rope is connected to the driven spool (3.2), and the other end of the other rope is connected to the mother satellite (1).
8. The primary and secondary satellite-based space station satellite-based micro/nano satellite inertial release device is characterized in that the electromagnet (4.2) is connected with a battery and supplies power to the electromagnet (4.2).
9. The primary and secondary satellite-based space station satellite-flying micro/nano satellite inertial release method according to claim 8, characterized by comprising:
s1, unreleased: in the initial state, the barrier strip (1.5) is in a closed state, so that the subsatellite (2) is prevented from sliding off the release device; the rope system (5) is wound on the driving spool and the driven spool (3.2), the electromagnet (4.2) is electrified, the butt joint mechanism (1.7) presses down the bent plate (4.1), the mother satellite (1) is arranged on the spring tray (3.4), and the spring tray (3.4) is in a pressing state;
s2, to-be-released: the electromagnet (4.2) is powered off, the butt joint mechanism (1.7) is separated from the bent plate (4.1), the mother satellite (1) is released to be far away from the base (3) under the action of the spring tray (3.4), and the ropes (5) are released from the driving spool and the driven spool (3.2) under the driving of the mother satellite (1); the first steering engine (1.4) drives the barrier strip (1.5) to rotate to open, and the primary satellite (1) starts to rotate under the action of the Hall effect thruster (1.6); the inertia subsatellite (2) is thrown out, so that a satellite flight relationship is formed between the subsatellite and the parent satellite; after a specified number of sub-satellites are released, the first steering engine (1.4) drives the blocking strips (1.5) to rotate to close;
s3, data docking: the child satellite (2) returns to the parent satellite (1) after completing a task, the data connector (1.3) is connected with the data interface (2.1) to complete charging and data transfer of the child satellite (2), meanwhile, the first steering engine (1.4) drives the stop bar (1.5) to rotate to open, the child satellite (2) returns to the release device, and the stop bar (1.5) rotates to close the release device;
s4, recovering: all secondary satellite (2) return release, second steering wheel (3.5) drive the initiative spool and rotate, driving gear (3.1) drive driven gear simultaneously and rotate, and then drive driven spool (3.2) and rotate, set up and withdraw in tether (5) of initiative spool and driven spool (3.2), primary satellite (1) is withdrawn to bottom plate (3) under the effect of tether (5) on, bend board (4.1) start electromagnet (4.2) adsorb to initial position, hold-down spring tray (3.4) are in order to be equipped with next transmission.
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| CN202210987920.1A CN115231002A (en) | 2022-08-17 | 2022-08-17 | Space station satellite-flying micro-nano satellite inertia release device and method based on primary and secondary satellites |
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| CN202210987920.1A CN115231002A (en) | 2022-08-17 | 2022-08-17 | Space station satellite-flying micro-nano satellite inertia release device and method based on primary and secondary satellites |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115959308A (en) * | 2023-01-31 | 2023-04-14 | 北京理工大学 | Low-cost electrically-driven electrodynamic force rope releasing device and off-track experimental device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115959308A (en) * | 2023-01-31 | 2023-04-14 | 北京理工大学 | Low-cost electrically-driven electrodynamic force rope releasing device and off-track experimental device |
| CN115959308B (en) * | 2023-01-31 | 2024-03-22 | 北京理工大学 | Low-cost electrically-driven electrodynamic force rope release device and off-track experimental device |
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