CN115092425A - Filling interface propelling and separating device for distributed reconfigurable small satellite platform - Google Patents
Filling interface propelling and separating device for distributed reconfigurable small satellite platform Download PDFInfo
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- CN115092425A CN115092425A CN202210555215.4A CN202210555215A CN115092425A CN 115092425 A CN115092425 A CN 115092425A CN 202210555215 A CN202210555215 A CN 202210555215A CN 115092425 A CN115092425 A CN 115092425A
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- 239000007788 liquid Substances 0.000 claims abstract description 30
- 238000000034 method Methods 0.000 claims description 9
- 238000000926 separation method Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 108091092878 Microsatellite Proteins 0.000 claims description 2
- 230000003287 optical effect Effects 0.000 claims 1
- 230000002787 reinforcement Effects 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 4
- 210000001503 joint Anatomy 0.000 description 6
- 239000003380 propellant Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 108091092919 Minisatellite Proteins 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- B64G1/646—Docking or rendezvous systems
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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
A filling interface propelling and separating device for a distributed reconfigurable moonlet platform comprises a cross pushing device, a motor and a supporting structure; the supporting structure comprises a motor bracket and a first structural plate; the cross pushing device is of a symmetrical structure, 1 motor is symmetrically arranged at each of two ends of one edge of the cross pushing device, and interface mounting holes are symmetrically arranged at each of two ends of the other edge of the cross pushing device and are used for being connected with movable ends of the gas filling interface or the liquid filling interface respectively; the motors are respectively installed on the motor supports, and the motor supports are respectively installed on the first structural plate of the reconfigurable moonlet. The invention has convenient installation and convenient operation, and can realize high-precision adjustment with wider application range by combining the floating disconnection mechanism.
Description
Technical Field
The invention relates to a filling interface propelling and separating device.
Background
The spacecraft propellant in-orbit filling technology is one of main in-orbit service modes of a spacecraft, and is a main technical means for prolonging the effective service life of the spacecraft and improving the economic benefit of the spacecraft. For long-term operation of the spacecraft, the propellant carrying capacity influences the on-orbit service life and the orbit maintaining capacity of the spacecraft. The in-orbit propellant filling technology research must be carried out aiming at large reconfigurable spacecrafts, particularly small satellites based on space station application. Based on the design mode of the reconfigurable distributed spacecraft, the satellites or modules related to in-orbit propellant filling are called as a filling module and a propelling module, and the corresponding filling interfaces are also called as an active end and a passive end respectively.
In the current on-orbit filling technology research, the active ends (or the passive ends) of the gas filling interface and the liquid filling interface are usually installed on different pushing devices, and the active ends are pushed by different motors respectively, so that the gas filling interface and the liquid filling interface are sequentially connected and separated, namely 2 sets of filling interface pushing and separating devices are needed. At present, the method is mainly used for large and medium-sized spacecrafts, such as space stations, large satellites and the like. Due to the limitations of the size and the weight of the reconfigurable distributed microsatellite and the small satellite, the number, the configuration and the layout of the motors and other pushing devices can hardly ensure the sequential connection of the gas filling interface and the liquid filling interface.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention discloses a filling interface propelling and separating device for a distributed reconfigurable small satellite platform, which solves the problem of butt joint of gas and liquid end filling interfaces of an on-orbit filling system caused by space shortage of a small satellite module, and realizes the stress symmetry of mechanical connection of the gas filling interface and the liquid filling interface by adopting an interface propelling device with a symmetrical structure; 1 set of symmetrically installed motors is adopted to realize the synchronism of pushing of the gas and liquid filling interfaces. The whole device is convenient to install and operate, and high-precision adjustment with a wide application range can be realized by combining the floating disconnecting mechanism.
The technical scheme adopted by the invention is as follows: a filling interface propelling and separating device for a distributed reconfigurable minisatellite platform comprises a cross pushing device, a motor and a supporting structure; the supporting structure comprises a motor bracket and a first structural plate;
the cross pushing device is of a symmetrical structure, the end parts of two ends of one edge of the cross pushing device are respectively connected with the output end of the motor, and the two ends of the other edge of the cross pushing device are symmetrically provided with interface mounting holes for respectively connecting with the movable end of the gas filling interface or the liquid filling interface;
the motors are respectively arranged on the motor supports, and the motor supports are respectively arranged on the first structural plate of the reconfigurable moonlet.
Furthermore, the distance between the movable ends of the two gas filling interfaces or the liquid filling interfaces is equal to the distance between the fixed ends of the two gas filling interfaces or the liquid filling interfaces.
Furthermore, the motors arranged at the two ends of the cross pushing device adopt 2 motors with the same specification, the same stroke and the same torque, the two motors can work simultaneously through one driving signal, and the cross pushing device is ensured not to rotate along the Y axis in the advancing process.
Furthermore, a connecting lug is arranged at the position where the cross pushing device is connected with the motor, and a light hole is formed in the connecting lug.
Furthermore, the end part of the output shaft of the motor is provided with a mounting groove matched with the connecting lug pieces at the two ends of the cross pushing device, and the side wall of the mounting groove is provided with a through unthreaded hole.
Furthermore, the unthreaded hole of the motor is connected with the unthreaded hole of the cross pushing device through a bolt and is fixed through a nut.
Furthermore, the side surface of the connecting lug of the cross propulsion device is in clearance fit with the side surface of the mounting groove of the motor.
Furthermore, the end surface of the cross propulsion device is in clearance fit with the end surface of the mounting groove of the motor.
Furthermore, the cross pushing device is made of stainless steel materials, and local strengthening of the anti-torsion performance of the structure is achieved.
A method of installing a prime interface propulsion and separation apparatus for a distributed reconfigurable moonlet platform, comprising:
respectively mounting a motor on a motor bracket; respectively installing the movable ends of the gas filling interface and the liquid filling interface on the cross propulsion device; the distance between the movable ends of the two gas filling interfaces and the liquid filling interface is equal to the distance between the fixed ends of the two gas filling interfaces or the liquid filling interface;
installing motor supports on first structural plates of the reconfigurable moonlet respectively;
the cross propulsion devices are respectively connected with the motor.
Compared with the prior art, the invention has the advantages that:
(1) the gas filling interface and the liquid filling interface are symmetrically distributed on the same mounting surface, so that 2 filling interfaces are connected simultaneously, the problem that the space size of a small satellite is small is solved, and the applicability of the small satellite filling system is high.
(2) The movable ends of the gas filling interface and the liquid filling interface are arranged on the same module, namely are simultaneously arranged on the filling module or the propelling module, and 1 motor working group is adopted to realize the synchronous motion of 2 filling interfaces, thereby solving the problems of limited driving quantity of the small satellites and the like.
(3) The invention provides a plate type device for simultaneously pushing 2 filling interfaces based on symmetrical installation of a gas filling interface and a liquid filling interface, which realizes simultaneous advancing, butt joint and separation of active ends of the gas filling interface and the liquid filling interface, and improves the self-adaptive adjusting capacity of the filling interface and a cross pushing device in the advancing process through the relative installation relation of the cross pushing device and a motor.
Drawings
FIG. 1 is a view of a filling interface pushing and separating device;
FIG. 2 is a diagram of the relative assembly of the cross propulsion unit and the motor working group;
FIG. 3 is a diagram illustrating the assembly of the fixed end of the filling interface.
Detailed Description
The filling interface propelling and separating device for the distributed reconfigurable moonlet platform comprehensively considers the space problem of the module moonlet and the butt joint sequence problem of the on-orbit filling interface, integrates 2 sets of pushing devices into 1 set of pushing device, and realizes the mechanical connection of the gas filling interface and the liquid filling interface; the connection sequence of the gas filling interface and the liquid filling interface is changed from serial to synchronous connection and separation, so that the operations of butt joint, supply and separation in the in-orbit filling work are realized, and the in-orbit filling system is very suitable for the in-orbit filling system of the small module satellite.
The filling interface propelling and separating device for the distributed reconfigurable small satellite platform is combined with the floating butt joint device, so that the influence of assembly errors on accurate butt joint is completely avoided.
As shown in fig. 1, the filling interface propelling and separating device for the distributed reconfigurable moonlet platform comprises a cross pushing device 1, a motor 2 and a supporting structure. Wherein the support structure comprises a motor bracket 3, a first structural plate 4 and corresponding fasteners.
Wherein, the cross pushing device 1 adopts a symmetrical design structure. The X axis is along one side of the cross pushing device 1, and the Y axis is along the other side of the cross pushing device 1; in the structure of cross design, 1 motor 2 is connected respectively at the X axle both ends of symmetry, and 2 motors 2 constitute a motor unit, and the Y axle both ends of symmetry connect respectively in addition and annotate the movable end 5 of gas filling interface or liquid filling interface. The symmetrical design of the pushing device 1 ensures uniform stress in the advancing process, thereby ensuring the advancing synchronism of the gas filling interface and the liquid filling interface. The connection interface of the cross pushing device 1 and the motor 2 is a unthreaded hole. The cross pushing device 1 is connected with the motor 2 through a light hole, and an assembly gap exists between the plane of the light hole end of the cross pushing device 1 and the tail end of the motor 2, so that the cross pushing device 1 is guaranteed to have the capability of rotating along the X axis, and the gas filling interface and the liquid filling interface are guaranteed to have direction self-adaptive regulating energy-saving force.
The motor group adopts 2 motors 2 with the same stroke and the same torque and the same specification. The motors 2 are arranged at two ends of one shaft of the cross pushing device 1, and the two motors 2 work simultaneously through one driving signal, so that the pushing device 1 is ensured not to rotate along the Y axis in the advancing process. The connection interface of motor 2 and cross thrust unit 1 be the unthreaded hole, the unthreaded hole of motor 2 and the unthreaded hole of cross thrust unit 1 adopt bolt 7 to be connected, there is an assembly clearance side 11 of the connection auricle of cross thrust unit 1 and the side 21 of the mounting groove of motor 2, guaranteed that two motors 2 are under the condition that has the individual difference of performance, when motor 2 impels asynchronously, cross thrust unit 1 and motor 2 do not take place great interference and structural deformation.
In the filling interface propelling and separating device, two ends of an X shaft of a cross pushing device 1 are respectively connected with 1 motor 2, and two ends of a Y shaft are respectively connected with a movable end 5 of a gas filling interface or a liquid filling interface. The cross pushing device 1 is made of a material with good rigidity (such as stainless steel), and local strengthening of the anti-torsion performance of the structure is performed, so that the cross pushing device 1 cannot generate large deformation under the action of motor pushing force and filling interface inserting and pulling friction force in the pushing and separating processes.
During the assembly of the filling interface advancing and separating device, the operation steps are roughly as follows:
1) the motor 2 is respectively arranged on the motor bracket 3; installing a movable end 5 of a gas filling interface or a liquid filling interface on the cross propulsion device 1;
2) mounting the motor bracket 3 on the first structural plate 4;
3) the cross propulsion device 1 is mounted on the motor 2.
As shown in fig. 2, the relative assembly relationship between the cross propulsion device 1 and the motor 2 includes the relationship between the side surface 11 of the cross propulsion device 1 and the side surface 21 of the mounting groove of the motor 2, and the relationship between the end surface 12 of the cross propulsion device 1 and the end surface 22 of the mounting groove of the motor 2. The side surface 11 is in clearance fit with the side surface 21 of the mounting groove, and the end surface 12 is in clearance fit with the end surface 22 of the mounting groove. The cross propulsion device 1 is fixedly connected with the motor 2 by adopting the nut 6 and the bolt 7, so that the cross propulsion device 1 has the capability of transverse movement and the adjustment capability of axial rotation.
As shown in fig. 3, in order to install the fixed end 8 of the filling interface and the second structural plate 9, the fixed end 8 of the filling interface is installed on another structural plate of the moonlet platform. The connection relationship between the filling interface fixing end 8 and the second structural plate 9 of the small satellite platform is threaded connection. The installation interface of the filling interface fixing end 8 is connected by external threads, and the internal threads on the second structural plate 9 ensure that the fixing end 8 of the filling interface has the capability of being adjusted along the axial direction and ensure the adjustability of the plugging degree of the filling interface.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Parts of the invention not described in detail are known to the person skilled in the art.
Claims (10)
1. A filling interface propelling and separating device for a distributed reconfigurable moonlet platform is characterized by comprising a cross propelling device (1), a motor (2) and a supporting structure; the supporting structure comprises a motor bracket (3) and a first structural plate (4);
the cross pushing device (1) is of a symmetrical structure, the end parts of two ends of one edge of the cross pushing device (1) are respectively connected with the output end of the motor (2), and the two ends of the other edge are symmetrically provided with interface mounting holes for respectively connecting with a movable end (5) of an air filling interface or a liquid filling interface;
the motors (2) are respectively installed on the motor supports (3), and the motor supports (3) are respectively installed on the first structural plate (4) of the reconfigurable moonlet.
2. Filling interface pushing and separating device for a distributed reconfigurable moonlet platform according to claim 1, wherein the distance between the movable ends (5) of two gas or liquid filling interfaces is equal to the distance between the fixed ends (8) of two gas or liquid filling interfaces.
3. The filling interface propelling and separating device for the distributed reconfigurable moonlet platform according to claim 1, wherein the motors (2) installed at two ends of the cross propulsion device (1) adopt 2 motors with the same specification, the same stroke and the same torque, and the two motors (2) work simultaneously through one driving signal, so that the cross propulsion device (1) is ensured not to rotate along the Y axis in the advancing process.
4. The filling interface propelling and separating device for the distributed reconfigurable moonlet platform according to claim 1, wherein a connecting lug is arranged at a position where the cross-shaped propelling device (1) is connected with the motor (2), and an optical hole is formed in the connecting lug.
5. The filling interface propelling and separating device for the distributed reconfigurable moonlet platform according to claim 4, wherein an output shaft end of the motor (2) is provided with a mounting groove which is matched with connecting lugs at two ends of the cross pushing device (1), and a through light hole is formed in a side wall of the mounting groove.
6. The filling interface propelling and separating device for the distributed reconfigurable moonlet platform is characterized in that the unthreaded hole of the motor (2) is connected with the unthreaded hole of the cross pushing device (1) through a bolt (7) and is fixed through a nut (6).
7. A filling interface propelling and separating device for a distributed reconfigurable moonlet platform according to claim 6, wherein the side (11) of the connection tab of the cross propulsion device (1) and the mounting groove side (21) of the motor (2) adopt clearance fit so that the cross propulsion device (1) can move along the X axis.
8. The filling interface propelling and separating device for the distributed reconfigurable moonlet platform according to claim 7, wherein the end surface (12) of the cross propelling device (1) is in clearance fit with the end surface (22) of the mounting groove of the motor (2), so that the cross propelling device (1) can rotate around the X axis.
9. Filling interface propulsion and separation device for distributed reconfigurable microsatellite platforms according to claim 8 characterised in that said cross propulsion means (1) is made of stainless steel material and performs a local reinforcement of the anti-torsion performance of the structure.
10. A method of installing a prime interface propulsion and separation apparatus for a distributed reconfigurable moonlet platform, comprising:
the motor (2) is respectively arranged on the motor bracket (3); respectively installing the movable ends (5) of the gas filling interface and the liquid filling interface on the cross propulsion device (1); the distance between the movable ends (5) of the two gas filling interfaces and the liquid filling interface is equal to the distance between the fixed ends (8) of the two gas filling interfaces or the liquid filling interfaces;
installing motor supports (3) on first structural plates (4) of the reconfigurable moonlet respectively;
the cross propulsion device (1) is respectively connected with the motor (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210555215.4A CN115092425B (en) | 2022-05-19 | Filling interface propelling and separating device for distributed reconfigurable small satellite platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210555215.4A CN115092425B (en) | 2022-05-19 | Filling interface propelling and separating device for distributed reconfigurable small satellite platform |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115092425A true CN115092425A (en) | 2022-09-23 |
| CN115092425B CN115092425B (en) | 2024-06-25 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020179776A1 (en) * | 2001-04-23 | 2002-12-05 | Kistler Aerospace Corporation | Active satellite dispenser for reusable launch vehicle |
| CN107128514A (en) * | 2017-04-28 | 2017-09-05 | 西北工业大学 | The in-orbit assembly system of space truss and method of a kind of use robot for space |
| CN110104222A (en) * | 2019-04-25 | 2019-08-09 | 北京控制工程研究所 | A kind of modularization propulsion service system promoted based on mixed mode |
| CN110104221A (en) * | 2019-04-12 | 2019-08-09 | 北京控制工程研究所 | It is a kind of general in-orbit to add interface arrangement |
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020179776A1 (en) * | 2001-04-23 | 2002-12-05 | Kistler Aerospace Corporation | Active satellite dispenser for reusable launch vehicle |
| CN107128514A (en) * | 2017-04-28 | 2017-09-05 | 西北工业大学 | The in-orbit assembly system of space truss and method of a kind of use robot for space |
| CN110104221A (en) * | 2019-04-12 | 2019-08-09 | 北京控制工程研究所 | It is a kind of general in-orbit to add interface arrangement |
| CN110104222A (en) * | 2019-04-25 | 2019-08-09 | 北京控制工程研究所 | A kind of modularization propulsion service system promoted based on mixed mode |
Non-Patent Citations (1)
| Title |
|---|
| 丁凤林: "超声波流量计在航天器推进系统中的应用分析", 空间控制技术与应用, 15 December 2010 (2010-12-15), pages 258 - 262 * |
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