CN115231004A - Connection and separation mechanism for stacked satellites - Google Patents
Connection and separation mechanism for stacked satellites Download PDFInfo
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- CN115231004A CN115231004A CN202211140673.8A CN202211140673A CN115231004A CN 115231004 A CN115231004 A CN 115231004A CN 202211140673 A CN202211140673 A CN 202211140673A CN 115231004 A CN115231004 A CN 115231004A
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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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Abstract
The invention provides a connection and separation mechanism for a stacked satellite, which mainly comprises: the device comprises a base, a spring, a swing hook, a swing rod, a connecting piece, a motor, a lead screw, a nut, a guide pin connecting rod, a guide pin and a positioning frame. The pressing force between the stacked satellites is automatically adjusted by adopting a motor driving mode and a nut screw transmission mode, so that the connection rigidity can be improved. The top frame structure is adopted to carry out multi-point limiting on the stacked satellites, and the number of mechanisms can be reduced. The form of adopting the electricity to drive pin puller unblocks, can effectively reduce the unblock and strike to it is measurable to realize functional performance can examine. The mechanism is connected with the carrier rocket by adopting a hinge sliding groove structure and a pressure spring design, can realize the rotation and automatic separation of the mechanism away from the satellite, and has simple structure and high reliability. The invention can realize the effects of high connection rigidity, low unlocking impact, automatic rotation and separation and the like, and is suitable for the technical field of space satellites.
Description
Technical Field
The invention relates to the technical field of space satellites, in particular to a connection and separation mechanism for a stacked satellite.
Background
In recent years, in order to overcome the problems that a ground communication base station is limited in coverage area and is easily interfered by the environment, satellite communication is increasingly emphasized, and the requirement for satellite transmission is rapidly increased. The stacked satellite group transmission can obviously improve the satellite transmission efficiency and reduce the transmission cost. However, the traditional satellite connection and separation design structure is complex, and the unlocking impact is large due to the fact that initiating explosive devices are used more.
Most of the traditional satellite connecting and separating mechanisms are arranged on the side surface of the stacked satellite, and apply pressing force and unlock the stacked satellite through explosive bolts; or the satellite is pressed between the rocket and the pressure plate and between the satellite and the pressure bearing body through the pull rod, and the connection between the pull rod and the rocket and the pressure bearing body is released through the initiating explosive device during separation; after unlocking, the pneumatic module is used for injecting air to enable the mechanism to rotate around the hinge seat and away from the satellite. However, the above structure has the following disadvantages: the pressing force of the stacked satellite cannot be automatically adjusted, the overall rigidity is low, the unlocking impact of an explosive bolt or an initiating explosive device is large, the structure is complex, and redundant objects are easily generated.
Disclosure of Invention
Aiming at the defects in the related art, the technical problem to be solved by the invention is as follows: the connection and separation mechanism for the stacked satellites is provided to achieve the effects of high connection rigidity, low unlocking impact and automatic rotation and separation.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
a connection and separation mechanism for a stacked satellite comprises a payload support, wherein at least two bases are symmetrically arranged on the payload support, each base is hinged with a swing hook through a hinge sliding groove structure, a swing rod is connected onto each swing hook, a connecting piece is arranged at the top of each swing rod, the stacked satellite is arranged on the payload support and located between the two bases, pressing force or unlocking is applied to the stacked satellite through a motor-screw rod mounting mechanism below the connecting piece, a pressure spring is further arranged on each base, the fixed end of the pressure spring is arranged on each base, and the free end of the pressure spring is connected with the swing hooks in a matched mode.
Preferably, the motor-screw mechanism includes a motor disposed at the bottom of the connecting member, an output shaft of the motor is connected with a screw, the screw is in screw transmission connection with a nut, two sides of the nut are respectively and vertically provided with a connecting rod, one end of the connecting rod is connected with the bottom of the connecting member, a guide pin is connected between the other ends of the two connecting rods, a long round through hole penetrating through the nut is vertically formed in the side wall of the nut, the guide pin penetrates through the nut through the long round through hole, the bottom of the nut is connected with a positioning frame, a plurality of force applying columns are disposed on the lower side of the positioning frame, a positioning pin is disposed below each force applying column, and the positioning pins are connected with the top of the stacked satellite.
Preferably, the hinge sliding groove structure includes an arc groove formed in the base, a first rolling bearing installed on the base through a first pin shaft, and second rolling bearings installed on two sides of the swing hook through a second pin shaft, one side of the arc groove, which is far away from the stacked satellite, is open, a hinge of the swing hook and the base is a semi-open arc, the semi-open arc is connected with an outer ring of the first rolling bearing in a matched manner, an outer ring of the second bearing is connected with the arc groove in a matched manner, and the arc groove is adapted to a motion track of the second bearing.
Preferably, install the socket on the base, install the plug on the pendulum hook, the socket is connected with the plug cooperation, the interior power supply line that has laid of pendulum hook, pendulum rod and connecting piece, the input of power supply line with the plug electricity is connected, the output of power supply line with the input electricity of motor is connected.
Preferably, the stacked satellite is formed by vertically stacking a plurality of independent satellites, four bearing columns are uniformly distributed on the periphery of each independent satellite in the circumferential direction, each bearing column is provided with a groove and a boss, each groove is connected with the boss of the independent satellite above in a matched mode, each boss is connected with the groove of the independent satellite below in a matched mode, each effective load support is provided with a groove corresponding to the boss of the independent satellite at the bottom end, and each independent satellite at the top end is provided with a bearing column connected with the corresponding positioning pin in a matched mode.
The invention has the beneficial technical effects that:
1. according to the invention, a scheme that explosion bolts are adopted to apply pressing force and unlock a stacked satellite or an initiating explosive device is adopted to unlock the stacked satellite in a traditional connection and separation mechanism is abandoned, a motor-screw mechanism is creatively adopted to apply pressing force and unlock the stacked satellite, specifically, when the connection and separation mechanism is required to be connected and pressed, a swing hook swings to a vertical position, a connecting piece is positioned right above the stacked satellite at the moment, an output shaft of a motor drives a screw to rotate, a nut presses down the stacked satellite under the screw transmission of the screw, and is matched with a bearing column at the top of the stacked satellite under the transmission of a positioning frame, the force application column and a positioning pin, so that the multi-point positioning and the application of pre-tightening force of the stacked satellite are realized, the height deviation of the stacked satellite can be adapted through the automatic adjustment of the pre-tightening force, and the connection rigidity of the stacked satellite can be improved; when the connection and separation mechanism bears the axial loads of the rocket body applied by the satellite, the spiral transmission can realize self-locking, a motor is not required to provide locking torque, and the locking reliability is high; when the connecting and separating mechanism is required to be unlocked, the motor only needs to rotate reversely, the nut and the positioning frame are further driven to move upwards, the positioning pin is pulled out of the force bearing column at the top of the stacked satellite, and unlocking is completed.
2. According to the invention, the long round through hole is formed in the side wall of the nut, the guide pin penetrates through the long round through hole in the side wall of the nut to limit the rotation of the nut, and the nut can be driven by the rotation of the lead screw to move along the axial direction. The length of the long round through hole in the side wall of the nut is consistent with the designed axial stroke of the nut, and the guide pin can simultaneously play a role in mechanical limit of axial movement, so that the axial movement of the nut is prevented from exceeding the designed stroke. Two ends of the guide pin are connected with the guide pin connecting rod and fixed on the connecting piece. When the screw rod drives the nut to move along the axial direction in a rotating mode, the nut can produce bending moment effect on the guide pin, and the connecting rod of the guide pin is designed symmetrically to ensure that the connecting rigidity of the guide pin meets requirements.
3. After the motor-screw mechanism unlocks the stacked satellite, the swing hook rotates around the hinged base in the direction far away from the stacked satellite, specifically, a semi-open type circular arc rotates around a first pin shaft through a first rolling bearing and is close to one side of the stacked satellite, a second rolling bearing moves in a circular arc groove until the swing hook is in a vertical state, the free end of a pressure spring is abutted against the swing hook in the rotation process of the swing hook until the free end of the pressure spring is pressed tightly, and when the motor-screw mechanism exerts the pretightening force on the stacked satellite, the limit locking is realized on a connecting and separating mechanism; after the connecting and separating mechanism is unlocked, the swing hook rotates around the first pin shaft under the action of the elastic force of the pressure spring, when the second pin shaft moves to be separated from the arc groove, the second pin shaft and the arc groove are released from restraint, the semi-open arc is separated from the first rolling bearing, and the swing hook is completely separated from the base under the action of inertia. The invention adopts the hinge sliding groove structure and the pressure spring design, can realize the rotation and automatic separation of the mechanism away from the satellite, and has simple structure and high reliability.
4. When the connection and separation mechanism is locked, the swing hook is in a vertical position, the plug is connected with the socket, a circuit is conducted, and a power supply line is connected with a motor through the swing hook, the swing rod and a connecting piece to supply power to the motor; after the connection and separation mechanism is unlocked, the swing hook rotates around the first pin shaft of the base, the plug is pulled out of the socket under the action of the elastic force of the pressure spring, the circuit is disconnected, and a power supply circuit on the mechanism and the mechanism are separated from the rocket body and the satellite. The invention adopts the form of electrically-driven pin puller for unlocking, effectively reduces unlocking impact compared with initiating explosive devices, and realizes the detectability of functional performance.
5. The use of the load bearing columns in the present invention eliminates the need for a distributor or greatly reduces the mass of the distributor to allow more satellites to be carried on the payload support.
Drawings
Fig. 1 is a schematic structural diagram of a connection and disconnection mechanism for a stacked satellite according to an embodiment of the present invention;
FIG. 2 is a schematic view of the connection structure of the swing hook and the base in the present invention;
FIG. 3 is a schematic view showing a locking state of the connection and disconnection mechanism of the present invention;
FIG. 4 is a schematic view showing a separation process of the coupling and decoupling mechanism according to the present invention;
FIG. 5 is a schematic view showing a process of detaching the connection and detachment mechanism according to the present invention;
fig. 6 is a schematic diagram of a connection and disconnection mechanism for a stacked satellite according to a second embodiment of the present invention;
in the figure: the device comprises a payload support 1, a base 2, a first pin shaft 2-1, a first rolling bearing 2-2, an arc groove 2-3, a socket 2-4, a pressure spring 3, a swing hook 4, a semi-open arc 4-1, a second pin shaft 4-2, a second rolling bearing 4-3, a plug 4-4, a swing rod 5, a connecting piece 6, a motor 7, a lead screw 8, a nut 9, a connecting rod 10, a guide pin 11, a positioning frame 12, a force application column 12-1, a positioning pin 12-2, a stacked satellite 13 and a bearing column 13-1.
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 embodiments, but not all embodiments, of the present 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.
Next, the present invention will be described in detail with reference to the drawings, wherein the cross-sectional views illustrating the structure of the device are not enlarged partially according to the general scale for convenience of illustration when describing the embodiments of the present invention, and the drawings are only examples, which should not limit the scope of the present invention. In addition, the three-dimensional dimensions of length, width and depth should be included in the actual fabrication.
An embodiment of the connection separation mechanism for stacked satellites is described in detail below with reference to the accompanying drawings.
Example one
As shown in fig. 1-5, a connection and separation mechanism facing a stacked satellite (hereinafter referred to as a connection and separation mechanism) includes a payload support 1, at least two bases 2 are symmetrically disposed on the payload support 1, and are further fixedly connected to a launch vehicle, each base 2 is hinged to a swing hook 4 through a hinge sliding groove structure, the swing hook is connected to a swing rod 5, a connecting member 6 is disposed on the top of the swing rod 5, the swing rod 5 is a slender rod, flanges are designed at two ends of the swing rod, a lower end of the swing rod is in threaded connection with the swing hook 4 through a flange, an upper end of the swing rod is in threaded connection with the connecting member 6 through a flange, a motor 7 is in threaded connection with the connecting member 6, the stacked satellite 13 is disposed on the payload support 1 and located between the two bases 2, a motor-screw mechanism is mounted below the connecting member 6 to apply pressing force or unlock the stacked satellite, and the swing hook 4 rotates around the hinged base 2 in a direction away from the stacked satellite 13 after the motor-screw mechanism unlocks the stacked satellite.
Further, the motor-screw mechanism comprises a motor 7 arranged at the bottom of the connecting piece 6, an output shaft of the motor 7 is connected with a screw 8, the screw 8 is designed with external threads, a nut 9 is designed with internal threads, the nut and the nut are matched to form screw transmission, two sides of the nut 9 are respectively and vertically provided with a connecting rod 10, one end of each connecting rod 10 is connected with the bottom of the connecting piece 6, a guide pin 11 is connected between the other ends of the two connecting rods 10, the side wall of the nut 9 is vertically provided with a long circular through hole penetrating through the nut 9, the guide pin 11 penetrates through the nut 9 through the long circular through hole, the width of the guide pin 11 is the same as that of the long circular through hole, the rotating motion of the nut 9 is limited, the nut 8 can rotate to drive the nut 9 to move axially, the length of the long circular through hole is the same as the designed axial stroke of the nut 9, the bottom of the nut 9 is connected with a positioning frame 12, a plurality of force application columns 12-1 are arranged at the lower side of the positioning frame, a positioning pin 12-2 is arranged below each force application column 12-1, and the positioning pin 12-2 is connected with the top of the stacked satellite 13.
According to the invention, the side wall of the nut 9 is provided with the long round through hole, the guide pin 11 penetrates through the long round through hole on the side wall of the nut 9 to limit the rotation of the nut 9, and the nut 9 can be driven to move axially by the rotation of the lead screw 8. The length of the long round through hole in the side wall of the nut 9 is consistent with the designed axial stroke of the nut 9, and the guide pin 11 can simultaneously play a role in mechanical limit of axial movement, so that the axial movement of the nut 9 is prevented from exceeding the designed stroke. The two ends of the guide pin 11 are connected with the guide pin 11 connecting rod 10 and fixed on the connecting piece 10. When the screw 8 rotates to drive the nut 9 to move along the axial direction, the nut 9 can generate a bending moment effect on the guide pin 11, and the symmetrical design of the guide pin 11 and the connecting rod 10 can ensure that the connection rigidity of the guide pin 11 meets the requirement.
According to the invention, a scheme that explosion bolts are adopted to apply pressing force and unlock the stacked satellite or an initiating explosive device is adopted to unlock the stacked satellite in a traditional connection and separation mechanism is abandoned, a motor-screw mechanism is creatively adopted to apply pressing force and unlock the stacked satellite, specifically, when the connection and separation mechanism is required to be connected and pressed, the swing hook 4 swings to a vertical position, the connecting piece 6 is positioned right above the stacked satellite 13, the output shaft of the motor 7 drives the screw 8 to rotate, the nut 9 presses the stacked satellite 13 downwards under the screw transmission of the screw 8, and is matched with the bearing column 13-1 at the top of the stacked satellite 13 under the transmission of the positioning frame 12, the force application column 12-1 and the positioning pin 12-2, so that the multi-point positioning and the application of the pre-tightening force of the stacked satellite are realized, the height deviation of the stacked satellite 13 can be adapted through the automatic adjustment of the pre-tightening force, and the connection rigidity of the stacked satellite 13 can be improved; when the connection and separation mechanism bears the axial arrow load applied by the stacked satellite 13, the spiral transmission can realize self-locking, the motor 7 is not required to provide locking torque, and the locking reliability is high; when the connecting and separating mechanism needs to be unlocked, the motor 7 is only required to rotate reversely, the nut 9 and the positioning frame 12 are further driven to move upwards, the positioning pin 12-2 is pulled out of the force bearing column 13-1 at the top of the stacked satellite 13, and unlocking is completed.
Furthermore, the positioning frame 12 may be designed to have an i-beam or truss structure, which is more rigid.
Further, the hinge sliding groove structure comprises an arc groove 2-3 formed in a base 2, a first rolling bearing 2-2 installed on the base 2 through a first pin shaft 2-1, and second rolling bearings 4-3 installed on two sides of a swing hook 4 through second pin shafts 4-2, one side, away from the stacked satellite 13, of the arc groove 2-3 is open, a hinged portion of the swing hook 4 and the base 2 is a semi-open arc 4-1, the semi-open arc 4-1 is connected with an outer ring of the first rolling bearing 2-2 in a matched mode, an outer ring of the second rolling bearing 4-3 is connected with the arc groove 2-3 in a matched mode, the arc groove 2-3 is matched with a moving track of the second rolling bearing 4-3, a pressure spring 3 is further arranged on the base 2, a fixed end of the pressure spring 3 is arranged on the base 2, and a free end of the pressure spring 3 is connected with the swing hook 4 in a matched mode.
After the motor-screw mechanism unlocks the stacked satellite 13, the swing hook 4 rotates around the hinged base 2 in the direction far away from the stacked satellite 13, specifically, the semi-open type circular arc 4-1 rotates around the first pin shaft 2-1 to the side close to the stacked satellite 13 through the first rolling bearing 2-2, the second rolling bearing 4-3 moves in the circular arc groove 2-3 until the swing hook 4 is in a vertical state, the free end of the pressure spring 3 is abutted against the swing hook 4 in the rotating process of the swing hook 4 until the free end is pressed tightly, and when the motor-screw mechanism finishes exerting of pretightening force on the stacked satellite 13, limiting locking is also realized on the connection and separation mechanism; after the connecting and separating mechanism is unlocked, the swing hook 4 rotates around the first pin shaft 2-1 under the action of the elastic force of the pressure spring 3, when the second pin shaft 4-2 moves to be separated from the arc groove 2-3, the second pin shaft and the arc groove are released from constraint, the semi-open arc 4-1 is separated from the first rolling bearing 2-2, and the swing hook 4 is completely separated from the base 2 under the action of inertia. The invention adopts the design of a hinge sliding groove structure and a pressure spring, can realize the rotation and automatic separation of the mechanism away from the satellite, and has simple structure and high reliability.
Furthermore, the semi-open type circular arc 4-1 of the swing hook 4 and the first pin shaft 2-1 of the base 2 are in rolling friction, the second pin shafts 4-2 on two sides of the swing hook 4 and the circular arc grooves 2-3 of the base 2 are in combination of rolling friction and sliding friction, and the relative movement resistance of the swing hook 4 and the base 2 is small.
Furthermore, a socket 2-4 is mounted on the base 2, a plug 4-4 is mounted on the swing hook 4, the socket 2-4 is connected with the plug 4-4 in a matching mode, a power supply line is arranged in the swing hook 4, the swing rod 5 and the connecting piece 6, the input end of the power supply line is electrically connected with the plug 4-4, and the output end of the power supply line is electrically connected with the input end of the motor 7.
A pair of electric connector sockets 2-4 and plugs 4-4 are mounted on a base 3 and a swing hook 4, when a connection separation mechanism is locked, the swing hook 4 is in a vertical position, the plugs 4-4 are connected with the sockets 2-4, a circuit is conducted, and a power supply line is connected with a motor 7 through the swing hook 4, a swing rod 5 and a connecting piece 6 to supply power to the motor 7; when the connection and separation mechanism is unlocked, the swing hook 4 rotates around the first pin shaft 2-1 of the base 2, the plug 4-4 is pulled out of the socket 2-4 under the action of the elastic force of the pressure spring 3, the circuit is disconnected, and a power supply circuit on the mechanism and the mechanism are separated from the rocket body and the satellite. The invention adopts the electrically-driven pin puller for unlocking, effectively reduces the unlocking impact compared with a initiating explosive device, and realizes the detectable and measurable functional performance.
Further, the motor-screw mechanism further includes a main control chip (not shown), and the main control chip can control the motor 7 to start, stop, and rotate in the forward/reverse direction after the motor 7 is powered. Specifically, when the connection and separation mechanism needs to apply a pretightening force to the stacked satellite 13, the motor 7 is powered on, the main control chip controls the motor 7 to rotate in the forward direction, the lead screw 8 is driven to rotate in the forward direction, and then the nut 9 and the positioning frame 12 are driven to move downwards to press the stacked satellite 13; after the connection and separation mechanism is locked, when the connection and separation mechanism bears the axial load of the rocket body applied by the stacked satellite 13, the spiral transmission can realize self-locking, at the moment, the motor 7 does not need to provide locking torque, and the main control chip controls the motor 7 to stop working; when the unlocking is needed, the main control chip controls the motor 7 to rotate reversely, the lead screw 8 is driven to rotate reversely, and then the nut 9 and the positioning frame 12 are driven to move upwards to complete the unlocking.
Further, the stacked satellite 13 is formed by vertically stacking a plurality of independent satellites, four bearing columns 13-1 are uniformly distributed on the periphery of each independent satellite in the circumferential direction, each bearing column 13-1 is provided with a groove and a boss, each groove is connected with a boss of an upper independent satellite in a matched mode, each boss is connected with a groove of a lower independent satellite in a matched mode, each effective load support 1 is provided with a groove corresponding to a boss of the lowermost independent satellite, and each independent satellite at the uppermost end is provided with a bearing column 13-1 connected with the corresponding positioning pin 12-2 in a matched mode.
The use of the load bearing columns 13-1 in the present invention eliminates the need for a distributor or significantly reduces the mass of the distributor to allow more satellites to be carried on the payload support.
Fig. 2 to 4 are schematic views of the locking, separating and disengaging states of the connection and separation mechanism, respectively, in sequence. The working principle of the connecting and separating mechanism is as follows:
when the stacked satellite is locked, the motor 7 drives the screw rod 8 to rotate, the screw drive nut 9 and the positioning frame 12 move downwards, the positioning pin 12-2 of the positioning frame 12 is inserted into a groove at the upper end of the bearing column 13-1 of the stacked satellite 13, and pretightening force is applied to the bearing column 13-1 of the stacked satellite 13 through the force applying column 12-1 of the positioning frame 12. The height deviation of the stacked satellite can be adapted through the automatic adjustment of the pre-tightening force, and meanwhile, the connection rigidity of the stacked satellite can be improved. The plurality of locating pins 12-2 of the locating frame 12 can perform multi-point locating on the stacked satellites.
During unlocking, the motor 7 drives the screw rod 8 to rotate reversely, so that the nut 9 and the positioning frame 12 are driven to move upwards, the positioning pin 12-2 of the positioning frame 12 is pulled out of the bearing column 13-1 of the stacked satellite 13, and unlocking is completed. And then the swing hook 4 rotates around the first pin shaft 2-1 of the base 2 under the action of the pressure spring 3, the plug 4-4 is pulled out of the socket 2-4 to automatically break the circuit connection, when the second pin shafts 4-2 on the two sides of the swing hook 4 move to be separated from the arc groove 2-3 of the base 2, the two pins are released from constraint, and the swing hook 4 is separated under the action of inertia.
In the embodiment, the connection and separation of the tandem stacked satellites can be realized by adopting two sets of connection and separation mechanisms, and the structure is simple and the reliability is high. The connecting and separating mechanism has no requirement on the height of the satellite, is suitable for releasing the layered small satellite and the large-size multifunctional special-shaped satellite, and has wide application range.
Example two
Fig. 6 shows another embodiment, as shown in fig. 6, on the basis of the first embodiment, a set of motor-screw mechanism is respectively designed at two ends of the positioning frame 12, and by means of a modular design, greater connection rigidity and bearing capacity can be achieved without changing the design of each part.
The key point of the invention is the design of the connection and separation mechanism for the stacked satellites. The pressing force between stacked satellites is automatically adjusted by adopting a motor driving and nut screw transmission mode, so that the connection rigidity can be improved. The top frame structure is adopted to carry out multi-point limiting on stacked satellites, and the number of mechanisms can be reduced. The form of adopting the electricity to drive pin puller unblocks, can effectively reduce the unblock and strike to it is measurable to realize functional performance can examine. The mechanism is connected with the carrier rocket by adopting a hinge sliding groove structure and a pressure spring design, can realize that the mechanism is far away from the satellite to rotate and automatically separate, and has simple structure, high reliability and very high practicability.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise explicitly stated or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly, e.g., as being permanently connected, detachably connected, or integral; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In the present invention, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the second feature or the first and second features may be indirectly contacting each other through intervening media. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature "under," "beneath," and "under" a second feature may be directly under or obliquely under the second feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
In the foregoing embodiments, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments.
It will be appreciated that the relevant features of the method, apparatus and system described above are referred to one another. In addition, "first", "second", and the like in the above embodiments are for distinguishing the embodiments, and do not represent merits of the embodiments.
It can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working processes of the system and the module described above may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and these modifications or substitutions do not depart from the spirit of the corresponding technical solutions of the embodiments of the present invention.
Claims (5)
1. A connection and separation mechanism for stacked satellites is characterized in that: the stacking satellite device is characterized by comprising a payload support (1), wherein at least two bases (2) are symmetrically arranged on the payload support (1), each base (2) is hinged with a swing hook (4) through a hinge sliding groove structure, a swing rod (5) is connected onto the swing hook, a connecting piece (6) is arranged at the top of the swing rod (5), the stacking satellite (13) is arranged on the payload support (1) and located between the two bases (2), a pressing force or unlocking is applied to the stacking satellite below the connecting piece (6) through installation of a motor-lead screw mechanism, a pressure spring (3) is further arranged on each base (2), the fixed end of the pressure spring (3) is arranged on each base (2), and the free end of the pressure spring (3) is connected with the swing hook (4) in a matched mode.
2. The stackable satellite based disconnect mechanism of claim 1, wherein: the motor-screw mechanism comprises a motor (7) arranged at the bottom of the connecting piece (6), an output shaft of the motor (7) is connected with a screw (8), the screw (8) is in screw transmission connection with a nut (9), two sides of the nut (9) are respectively and vertically provided with a connecting rod (10), one end of each connecting rod (10) is connected with the bottom of the connecting piece (6), a guide pin (11) is connected between the other ends of the two connecting rods (10), a long round through hole penetrating through the nut (9) is vertically formed in the side wall of the nut (9), the guide pin (11) penetrates through the nut (9) through the long round through hole, the length of the long round through hole is consistent with the designed axial stroke of the nut (9), the bottom of the nut (9) is connected with a positioning frame (12), a plurality of force applying columns (12-1) are arranged on the lower side of the positioning frame, a positioning pin (12-2) is arranged below each force applying column (12-1), and the positioning pin (12-2) is connected with the top of the stacked satellite (13).
3. The stackable satellite based disconnect mechanism of claim 1, wherein: the hinge sliding groove structure comprises an arc groove (2-3) formed in a base (2), a first rolling bearing (2-2) installed on the base (2) through a first pin shaft (2-1), and second rolling bearings (4-3) installed on two sides of a swing hook (4) through a second pin shaft (4-2), wherein one side, far away from a stacked satellite (13), of the arc groove (2-3) is open, a hinged part of the swing hook (4) and the base (2) is a semi-open arc (4-1), the semi-open arc (4-1) is connected with an outer ring of the first rolling bearing (2-2) in a matched mode, an outer ring of the second rolling bearing (4-3) is connected with the arc groove (2-3) in a matched mode, and the arc groove (2-3) is matched with a motion track of the second rolling bearing (4-3).
4. A stackable satellite oriented disconnect mechanism of claim 3, wherein: the power supply circuit is characterized in that a socket (2-4) is installed on the base (2), a plug (4-4) is installed on the swing hook (4), the socket (2-4) is connected with the plug (4-4) in a matched mode, a power supply circuit is arranged in the swing hook (4), the swing rod (5) and the connecting piece (6), the input end of the power supply circuit is electrically connected with the plug (4-4), and the output end of the power supply circuit is electrically connected with the input end of the motor (7).
5. The stackable satellite based disconnect mechanism of claim 2, wherein: the stacked satellite (13) is formed by vertically stacking a plurality of independent satellites, four bearing columns (13-1) are uniformly distributed on the periphery of each independent satellite in the circumferential direction, each bearing column (13-1) is provided with a groove and a boss, the grooves are matched and connected with the bosses of the independent satellites above, the bosses are matched and connected with the grooves of the independent satellites below, the effective load support (1) is provided with grooves corresponding to the bosses of the independent satellites at the bottom, and the independent satellites at the top are provided with the bearing columns (13-1) matched and connected with the positioning pins (12-2).
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| CN202211140673.8A CN115231004B (en) | 2022-09-20 | 2022-09-20 | Connection and separation mechanism for stacked satellites |
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| CN202211140673.8A CN115231004B (en) | 2022-09-20 | 2022-09-20 | Connection and separation mechanism for stacked satellites |
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| CN115231004B CN115231004B (en) | 2023-01-24 |
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| CN115675938A (en) * | 2022-11-21 | 2023-02-03 | 北京中科宇航技术有限公司 | Low-orbit mobile stack constellation satellite unlocking distributor |
| CN115783314A (en) * | 2022-11-21 | 2023-03-14 | 北京中科宇航技术有限公司 | Multi-flat-plate stacked satellite unlocking system |
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