CN109625339B - Micro-nano satellite separation device capable of controlling rotation angular velocity - Google Patents
Micro-nano satellite separation device capable of controlling rotation angular velocity Download PDFInfo
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- CN109625339B CN109625339B CN201811641477.2A CN201811641477A CN109625339B CN 109625339 B CN109625339 B CN 109625339B CN 201811641477 A CN201811641477 A CN 201811641477A CN 109625339 B CN109625339 B CN 109625339B
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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
Abstract
The invention provides a micro-nano satellite separation device with controllable rotation angular velocity, which comprises a base, a separation device, a connecting column, a positioning device and a pin puller, wherein the base is provided with a plurality of connecting columns; the positioning device is fixedly connected with the pin pulling device, a U-shaped groove is formed in the positioning device, and the opening direction of the U-shaped groove is the same as the rotating direction of the cube star; before separation, the connecting column is arranged in the U-shaped groove, and the end part of the pin poking device plug pin can extend into the U-shaped groove to position the connecting column; the separating device is obliquely arranged on the substrate, the upper end of the separating device is in contact with the cubic star, and the separating device is used for providing kinetic energy required by separation for the cubic star, and the direction of the kinetic energy is the axial direction of the separating device. The invention effectively solves the problem of unreliable separation caused by using reed separation in the traditional method, improves the success rate of separating the nano satellite from the parent body and has stronger compatibility.
Description
Technical Field
The invention relates to the technical field of space satellites, in particular to a micro-nano satellite separation device capable of controlling a rotation angular velocity.
Background
With the rapid development of the space technology, the space system has more and more prominent effect in the daily life of human beings, the current research situation of the space technology has been gradually expanded from exploring and utilizing space to exploring, utilizing and controlling space, and the development speed of the artificial satellite, especially the artificial micro-nano satellite, is particularly rapid in recent years.
The micro-nano satellite is generally separated from a mother satellite after the satellite is launched and lifted off, the existing separation method mainly adopts reed compression to connect the body with the micro-nano satellite, elastic potential energy is released by utilizing the deformation recovery process of the reed to separate the micro-nano satellite from the body, and the reed has the power supply function.
With the rapid development of aerospace technology, spacecrafts such as artificial satellites, space stations, space shuttles and the like are put into use in succession. However, the development of aerospace technology is restricted by huge cost and expensive cost. It is calculated that a satellite weighing 1000 kg is launched at a cost of at least $ 1 billion, and commercial operations have led to a need for lower cost and higher efficiency in aerospace technology. In this context, microsatellites have been rapidly developed on the basis of rapid development of science and technology.
While many microsatellites (especially micro-nano satellites such as cuboids) do not carry a power system by themselves, the motion attitude of the microsatellites needs to be provided by the body when the microsatellites are separated from the body, especially the starting of the cuboids is difficult, so that a mechanical device for separating the cuboids from the main body and endowing the cuboids with rotation angular velocity needs to be designed.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a micro-nano satellite separation device with controllable rotation angular velocity, which improves the success rate of separation of a cubic satellite and a matrix.
The invention is realized by the following technical scheme:
a micro-nano satellite separation device with controllable rotation angular velocity comprises a base, a separation device and a fixing device; the plurality of separating devices and the plurality of fixing devices are symmetrically arranged, and the number of the separating devices are even;
the fixing device comprises a connecting column, a positioning device and a pin puller, wherein the connecting column is vertically arranged on the side wall of the micro-nano satellite, the pin puller is arranged on the base, the positioning device is fixedly connected with the pin puller, a U-shaped groove is formed in the positioning device, and the opening direction of the U-shaped groove is the same as the rotation direction of the micro-nano satellite; before separation, the connecting column is arranged in the U-shaped groove, and the end part of the pin puller bolt can extend into the U-shaped groove to position the connecting column;
the separating device is obliquely arranged on the base, the upper end of the separating device is in contact with the micro-nano satellite, the separating device is used for providing kinetic energy required by separation for the micro-nano satellite, and the direction of the kinetic energy is the axial direction of the separating device.
Optionally, a radial connecting hole is formed in the connecting column, and a plug pin of the pin puller extends into the connecting hole.
Optionally, a round hole is formed in the side wall of the U-shaped groove, and a bolt of the pin puller penetrates through the round hole and extends into the connecting hole of the connecting column.
Optionally, a horizontal connecting sheet is arranged at the bottom of the side wall of the micro/nano satellite, and the upper end of the positioning column is fixedly connected with the connecting sheet.
Optionally, positioning pieces are respectively arranged on the micro-nano satellite and the base, each positioning piece comprises a horizontal piece and an inclined piece connected with the horizontal piece, and the lower end of the separation device is fixedly connected with the inclined piece of the positioning piece on the base; before separation, the inclined sheet of the positioning sheet on the micro-nano satellite is pressed at the upper end of the separation device.
Optionally, the included angle between the inclined plate and the horizontal plate is equal to the included angle between the separating device and the horizontal plane.
Optionally, a plurality of support columns for supporting the micro-nano satellite are arranged at the corners of the base.
Optionally, the base is a hollow structure.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a micro/nano satellite separation device which comprises a base, a fixing device and a separation device, wherein a pin puller and a positioning device of the fixing device are installed on the base, a connecting column is fixedly connected to the side wall of a cubic satellite, the connecting column is arranged in a U-shaped groove of the positioning device before separation, and a bolt of the pin puller is connected with the connecting column to realize the connection of the micro/nano satellite and a mother satellite; during separation, the two separation devices are obliquely arranged, so that longitudinal acting force and a pair of lateral force couples can be provided for the cuboids, and the micro-nano satellite is separated and revolved. The problem of unreliable separation caused by using reed separation in the traditional method is effectively solved; in addition, the ejection force of the separation device is calculated through the axial elastic force required during the launching, and the separation speed and the separation angular speed during the separation of the micro-nano satellite are further controlled; the problem that the separation speed and the separation angular speed cannot be controlled by a traditional method is solved, the success rate of separating the micro-nano satellite from the parent body is improved, and meanwhile, the separation mechanism is suitable for the existing micro-nano satellite and the parent body, does not need to make excessive adjustment on the structure, and has high compatibility.
Drawings
FIG. 1 is a schematic view of the structure of the separation apparatus of the present invention;
FIG. 2 is a top view of the separation device of the present invention;
FIG. 3 is an enlarged view of the lower portion of the separation device of the present invention;
FIG. 4 is a schematic view of the pin puller and locating tab of the present invention installed;
FIG. 5 is an enlarged view of a portion of FIG. 4;
FIG. 6 is a schematic structural diagram of the positioning device of the present invention 1;
FIG. 7 is a schematic structural diagram of the positioning device of the present invention shown in FIG. 2;
FIG. 8 is a schematic view of the structure of the positioning plate of the present invention;
FIG. 9 is a schematic view of the structure of the separation apparatus of the present invention;
in the figure: 1. a base; 2. a separation device; 3. a cube star; 4. positioning plates; 5. a positioning device; 6. a pin puller; 7. and (4) bolts.
Detailed Description
The present invention will now be described in further detail with reference to the attached drawings, which are illustrative, but not limiting, of the present invention.
The following is a detailed description of the structure and the working principle of the device, taking the application of the device on a cube star as a specific embodiment.
As shown in fig. 1-9, a micro/nano satellite separation device with controllable rotation angular velocity comprises a base 1, a separation device 2, a fixing device and a cube star 3.
The two separation devices and the two fixing devices are symmetrically arranged, as shown in fig. 2, the two fixing devices are arranged on the upper side and the lower side of the cube star 3, and the separation devices are rotationally symmetrically arranged on the two sides of the cube star 3.
Wherein, base 1 is connected with mother's star, and base 1 is square flat structure, and four turnings of base 1 are provided with the support column that is used for supporting the cube star respectively, and the cube star sets up on the support column of base 1.
The fixing device comprises a bolt 7, a positioning device 5 and a pin puller 6; pin puller 6 and bolt 7 are used for with cube star 3 and 1 fixed connection of base, pin puller 6 sets up on the base, 5 fixed connection of positioner are on pin puller 6, be provided with the U type groove that runs through perpendicularly on positioner 5, the opening side in U type groove sets up on positioner 5's the lateral wall, its opening direction is the same with cube star 3's direction of rotation, be provided with the horizontally round hole on positioner 5's the lateral wall, the tip of the bolt of pin puller 6 can pass the round hole and get into in the U type groove, two fixing device's positioner's the direction in U type groove is same direction of rotation, guarantee when cube star spin-out, two bolts 7 can be simultaneously rather than the positioner separation that is connected.
The bottom of the side wall of the cube star 3 is provided with a connecting sheet, a bolt 7 is vertically arranged on the connecting sheet, the lower end of the bolt 7 can vertically go deep into the U-shaped groove, the lower part of the bolt 7 is provided with a radial connecting hole, and a bolt of the pin puller 6 can extend into the connecting hole of the bolt 7 to realize the connection of the cube star 3 and the base 1. When the cubic star 3 starts to revolve, the bolt 7 is separated from the U-shaped groove, and the width of the U-shaped groove is larger than that of the bolt, so that the interference between the cubic star 3 and the U-shaped groove when the cubic star starts to revolve is avoided.
The lateral surface in this U type groove is the arcwall face, and the lateral surface is the lateral wall far away from the cube star lateral wall in the U type groove, and when separator started, the arcwall face can be used for leading to the rotation of cube star.
The separation devices are used for providing kinetic energy for the cubic star when the cubic star starts rotating, the two separation devices are respectively arranged on two parallel side walls of the cubic star and are positioned at two opposite angle positions, and the ejection directions of the two separation devices are opposite; the separating device is installed at the bottom of the side wall of the cube star, the separating device is installed in an inclined mode, and two ends of the separating device are connected with the base 1 and the cube star 3 through locating pieces respectively.
The installation angle of the separation device is set according to the elasticity required when the micro-nano satellite is launched.
The positioning piece 4 comprises a horizontal piece and an inclined piece connected with the horizontal piece. The first positioning piece is arranged at the upper end of the separating device, and the second positioning piece is arranged at the lower end of the separating device.
The horizontal piece of the second positioning piece is connected with the base 1 through a bolt, and the lower end of the separating device 2 is connected with the inclined piece of the second positioning piece through a bolt; the side wall of the horizontal sheet of the first positioning sheet is connected with the side wall of the cube star, and when the cube star is separated, the inclined sheet of the first positioning sheet presses the top of the separating device to bear the ejection force of the separating device.
The position of the support column on the base 1 is matched with the position of the corner at the bottom of the cube star, and the base is of a hollow structure and is used for increasing strength and reducing weight.
The above cube star is 1u cube star.
The working principle of the micro/nano satellite separation device with controllable rotation angular velocity provided by the invention is explained in detail below.
Before the cubic star is launched, the lower end of the cubic star 7 is installed on a support column of a base, a bolt 7 positioned on the cubic star extends into a U-shaped groove of a positioning device 5, and a round hole of the positioning device of a pin puller 6 is inserted into a connecting hole of the bolt, so that the connection between the cubic star 7 and the base 1 is realized; meanwhile, the inclined piece of the first positioning piece is in contact with the top of the separating device.
When the satellite sends a separation instruction, the two pin extractors 6 work, the inserted pins of the pin extractors 6 are pulled out from the bolts and the positioning devices, the cube star is in locking contact with the base, the two separation devices start to work, longitudinal acting force and a pair of lateral force couples are provided for the cube star, and the cube star is separated and starts to rotate. Because the positioning device adopts the opening design in the rotating direction of the cube star, the bolt can be directly separated from the U-shaped groove of the positioning device when the start of rotation is started, and the separation and the start of rotation are smoothly completed.
The separation device effectively solves the problem of unreliable separation caused by the separation of the reed used in the traditional method, and in addition, the ejection force of the separation device is calculated through the axial elastic force required during launching, so that the separation speed and the separation angular speed during separation of the cubic satellite are controlled, the problem that the separation speed and the separation angular speed cannot be controlled in the traditional method is solved, and the success rate of separation of the nano satellite from the mother body is improved. The separating mechanism is suitable for the existing nano-satellite and the mother satellite, does not need to make excessive adjustment on the structure, and has strong compatibility.
The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.
Claims (7)
1. A micro-nano satellite separation device with controllable rotation angular velocity is characterized by comprising a base (1), a separation device (2) and a fixing device; the plurality of separating devices and the plurality of fixing devices are symmetrically arranged, and the number of the separating devices (2) and the number of the fixing devices are both double;
the fixing device comprises a connecting column, a positioning device (5) and a pin puller (6), the connecting column is vertically arranged on the side wall of the micro-nano satellite, the pin puller (6) is arranged on the base (1), the positioning device (5) is fixedly connected with the pin puller (6), a U-shaped groove is formed in the positioning device (5), and the opening direction of the U-shaped groove is the same as the rotation direction of the micro-nano satellite; before separation, the connecting column is arranged in the U-shaped groove, and the end part of the bolt of the pin puller (6) can extend into the U-shaped groove to position the connecting column;
positioning pieces (4) are respectively arranged on the micro-nano satellite and the base (1), each positioning piece comprises a horizontal piece and an inclined piece connected with the horizontal piece, and the lower end of the separation device (2) is fixedly connected with the inclined piece of the positioning piece on the base; before separation, an inclined sheet of a positioning sheet on the micro/nano satellite is pressed at the upper end of the separation device;
the separation device (2) is obliquely arranged on the base, the upper end of the separation device is in contact with the micro-nano satellite, the separation device is used for providing kinetic energy required by the micro-nano satellite during separation, and the direction of the kinetic energy is the axial direction of the separation device.
2. The micro-nano satellite separation device with the controllable rotation angular velocity according to claim 1, wherein the connecting column is provided with a radial connecting hole, and a plug pin of the pin puller (6) extends into the connecting hole.
3. The micro-nano satellite separation device with the controllable rotation angular velocity according to claim 1, wherein a circular hole is formed in the side wall of the U-shaped groove, and a plug pin of the pin puller (6) penetrates through the circular hole and extends into a connecting hole of the connecting column.
4. A micro-nano satellite separation device with a controllable rotation angular velocity according to claim 2, wherein a horizontal connecting piece is arranged at the bottom of the side wall of the micro-nano satellite, and a connecting column is fixedly connected with the connecting piece.
5. A micro-nano satellite separation device with controllable rotation angular velocity according to claim 1, wherein the included angle between the inclined plate and the horizontal plate is equal to the included angle between the separation device and the horizontal plane.
6. The micro-nano satellite separation device with controllable rotation angular velocity according to claim 1, characterized in that a plurality of support columns for supporting micro-nano satellites are arranged at the corners of the base (1).
7. The micro-nano satellite separation device with controllable rotation angular velocity according to claim 1, wherein the base (1) is a hollow structure.
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| CN201811641477.2A CN109625339B (en) | 2018-12-29 | 2018-12-29 | Micro-nano satellite separation device capable of controlling rotation angular velocity |
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| CN201811641477.2A CN109625339B (en) | 2018-12-29 | 2018-12-29 | Micro-nano satellite separation device capable of controlling rotation angular velocity |
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| CN109625339B true CN109625339B (en) | 2022-04-15 |
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