CN208134652U - Can in-orbit allosteric modular space aircraft - Google Patents

Abstract

The utility model discloses a modular space vehicle capable of changing configurations in orbit. The modular space vehicle includes a basic module cell body, the basic module cell body includes a frame and a functional module, and the frame is provided with a magnetic attraction As for the connector, the two basic module cell bodies can be connected through the magnetic connection, the functional modules are installed on the frame, and the functional modules can be used to complete the predetermined tasks of the basic module cell bodies. According to the on-orbit variable-configuration modular space vehicle according to the embodiment of the utility model, the functional modules on the basic module cell body can make the basic module cell body complete the predetermined task, and the magnetic attraction connector on the frame can connect multiple basic module The modular cell body is connected, so the modular space vehicle has flexible structure, low cost, fast on-orbit response, and long service life, which overcomes the problems of complex design, high cost and difficult replacement of parts in the past.

Description

A Modular Space Vehicle That Can Be Changed in Orbit

technical field

The utility model patent relates to the overall design technology of a space vehicle, in particular to a modular space vehicle that can be reconfigured in orbit.

Background technique

With the rapid development of aerospace technology, information technology, new materials and advanced manufacturing technology, the use of outer space will undergo revolutionary changes, and the miniaturization and low-cost launch of space systems will become an important trend in future aerospace development. In the future "elastic dispersion" type space system, various space vehicles will be able to complete. From the perspective of technological development trends, it will have the characteristics of modularization, intelligence, reconfigurability, maintainability, and recombination.

For the design and connection technology of reconfigurable multi-agents, there is no perfect solution yet. Existing programs at home and abroad, such as "Phoenix Project", "F6", "iBOSS" program, "Space Robot" program, etc., basically all adopt heterogeneous design, and none of them have passed the in-orbit test and failed to achieve isomorphism In-orbit assembly and splicing of modular satellites, as well as the completion of specific tasks.

Utility model content

The utility model aims at at least solving one of the technical problems existing in the prior art. For this reason, the utility model proposes a modular space vehicle capable of changing configurations in orbit. The modular space vehicle has a simple structure, good versatility, and low cost.

According to the embodiment of the utility model, the modular space vehicle capable of changing configurations in orbit includes a basic module cell body, and the basic module cell body includes: a frame, a magnetic connection piece is provided on the frame, and two basic module cell bodies are provided. The modular cell body can be connected through the magnetic connection; the functional module, the functional module is installed on the frame, and the functional module can be used to complete the predetermined task of the basic module cell body.

According to the on-orbit variable-configuration modular space vehicle according to the embodiment of the utility model, the functional modules on the basic module cell body can make the basic module cell body complete the predetermined task, and the magnetic attraction connector on the frame can connect multiple basic module The modular cell body is connected, so the modular space vehicle has flexible structure, low cost, fast on-orbit response, and long service life, which overcomes the problems of complex design, high cost and difficult replacement of parts in the past.

In some embodiments, the frame includes: a core hollow cube, two half-enclosed outer frames, and the two half-enclosed outer frames are plugged on the core hollow cube; wherein, each of the half-enclosed outer frames The frame is generally formed in a C-shape, and the two semi-surrounding outer frames are plugged into the core hollow cube opposite to each other in a staggered manner at 90°.

Specifically, each of the semi-enclosed outer frames includes: a connection part, on which the magnetic connection is provided to connect the frames of the two basic module cell bodies; two extension parts , the two extension parts are respectively formed by extending upward from the two opposite sides of the connecting part, wherein, when each of the semi-surrounding outer frames is plugged into the core hollow cube, each of the extension parts located inside the core hollow cube.

In some optional embodiments, a first installation hole is opened on each of the extension parts, and the first installation hole is used to install a detection part to realize the detection function of the cell body of the basic module, and the connection part A second installation hole is opened on the top, and the second installation hole is used for installing an electric control board controlling the cell body of the basic module and a propeller providing power for the cell body of the basic module.

In some optional embodiments, a first positioning member is provided on the connecting portion, and a second positioning member that cooperates with the first positioning member is provided on the core hollow cube.

In some embodiments, each connecting portion is provided with a first installation mark, and the core hollow cube is provided with a second installation mark, and when each of the semi-surrounding outer frames is plugged into the core hollow cube, The first installation identifier and the second installation identifier correspond to each other.

In some embodiments, the basic module cell body further includes a protection plate for installing an electric control board controlling the basic module cell body, and the protection plate is detachably arranged on the frame.

In some embodiments, the on-orbit variable-configurable modular space vehicle further includes two solar sails, and the two solar sails are respectively installed on two opposite sides of the frame. border.

In some embodiments, the two half-surrounding frames have the same structure.

In some embodiments, the functional module includes at least one of a power supply system, a power system, a power supply system, a detection system and a control system.

Additional aspects and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

Description of drawings

The above and/or additional aspects and advantages of the present utility model will become apparent and easy to understand from the description of the embodiments in conjunction with the following drawings, wherein:

Fig. 1 is a schematic diagram of the overall structure of a modular space vehicle capable of changing configurations in orbit according to an embodiment of the present invention.

Fig. 2 is a schematic diagram of the structure of the basic module cell body of the embodiment of the present invention.

Fig. 3 is a schematic diagram of the basic module cell body structure of another embodiment of the present invention.

Fig. 4 is a schematic diagram of the frame structure of the basic module cell body of the embodiment of the present invention.

FIG. 5 is an exploded exploded schematic diagram of the frame described in FIG. 4 .

Reference signs:

Modular space vehicle 1,

Basic module cell body 10,

frame 100,

The core hollow cube 110, the second positioning part 111, the second installation mark 112,

Semi-surrounding the outer frame 120, the extension part 121, the first installation hole 1211, the connection part 122, the second installation hole 1221, the first positioning part 1222, the first installation mark 1223,

protection plate 130,

Magnetic connection device 140,

Main thruster 210, bionic adsorption mechanism 220, laser warning device 230, laser rangefinder 240, laser 250, multi-faceted camera 260, attitude control thruster 270, electric control board 280, solar sail 290.

Detailed ways

Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present utility model, but should not be construed as limiting the present utility model.

In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "Back", "Left", "Right", "Vertical", "Horizontal", "Top", "Bottom", "Inner", "Outer", "Clockwise", "Counterclockwise", "Axial" The orientation or positional relationship indicated by , "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the utility model and simplifying the description, rather than indicating or implying the referred device Or elements must have a specific orientation, be constructed and operate in a specific orientation, and thus should not be construed as limiting the invention. In addition, the features defined as "first" and "second" may explicitly or implicitly include one or more of these features. In the description of the present utility model, unless otherwise specified, "plurality" means two or more.

In the description of the present utility model, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a flexible connection. Detachable connection, or integral connection; it can be mechanical connection or electrical connection; it can be direct connection or indirect connection through an intermediary, and it can be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

The following describes a modular space vehicle 1 that can be reconfigured on orbit according to an embodiment of the present invention with reference to FIGS. 1-5 .

As shown in Fig. 1 , the modular space vehicle 1 capable of changing configurations on orbit according to the embodiment of the present invention includes a basic module cell body 10, the basic module cell body 10 includes a frame 100 and functional modules, and the frame 100 is provided with a magnetic attraction The connecting piece 140 , the two basic module cell bodies 10 can be connected through the magnetic connection piece 140 , the functional modules are installed on the frame 100 , and the functional modules can be used to complete the predetermined tasks of the basic module cell bodies 10 .

It can be understood that the functional modules on the basic module cell body 10 can enable the basic module cell body 10 to complete the predetermined task, and the magnetic connection 140 on the frame 100 can connect multiple basic module cell bodies 10, which means Multiple basic module cell bodies 10 can be combined arbitrarily, and after being aggregated, they become a more functional and powerful aircraft to perform complex on-orbit tasks. Compared with traditional spacecraft, the use of multiple basic module cell bodies 10 simplifies the structure of the modular spacecraft 1 . At the same time, when performing tasks, the modular space vehicle 1 according to the embodiment of the utility model changes the relative positions of a plurality of basic module cell bodies 10 according to the complexity of the surrounding environment of the landing site, so that the modular space vehicle 1 can adapt to more complex tasks condition.

According to the modular space vehicle 1 that can be configured on-orbit according to the embodiment of the present invention, the functional modules on the basic module cell body 10 can make the basic module cell body 10 complete the predetermined task, and the magnetic attraction connector 140 on the frame 100 Multiple basic module cell bodies 10 can be connected, so the modular spacecraft 1 has flexible structure, low cost, fast on-orbit response, and long service life, overcoming the problems of complex design, high cost, and difficult replacement of parts in the past.

What needs to be added here is that the multiple basic module cell bodies 10 are an independent aircraft, and the shells are equipped with different functional modules, so that each basic module cell body 10 has a specific function.

In some embodiments, as shown in FIGS. 4-5 , the frame 100 includes a core hollow cube 110 and two half-enclosed outer frames 120, and the two half-enclosed outer frames 120 are inserted on the core hollow cube 110, each The half-enclosed outer frame 120 is generally formed in a C-shape, and the two half-enclosed outer frames 120 are inserted into the core hollow cube 110 opposite to each other in a staggered manner at 90°. Such a structure is relatively convenient to process and assemble, thereby not only simplifying the assembly process of the frame 100 , but also reducing the production cost of the frame 100 .

Specifically, each semi-enclosed outer frame 120 includes a connection portion 122 and two extension portions 121 , and the connection portion 122 is provided with a magnetic connection piece 140 to connect the frames 100 of the two basic module cell bodies 10 . The two extensions 121 are respectively formed by extending upwards from the two opposite sides of the connecting portion 122, wherein, when each half-enclosed outer frame 120 is plugged into the core hollow cube 110, each extension 121 is located at the center of the core hollow cube 110. inside. Thus, the stability of the connection between the semi-surrounding outer frame 120 and the core hollow cube 110 can be ensured. Of course, in other embodiments of the present utility model, the magnetic connection part 140 can also be provided on the two extension parts 121 .

In some optional embodiments, as shown in FIG. 5 , each extension 121 is provided with a first installation hole 1211, and the first installation hole 1211 is used to install a detection piece to realize the detection function of the basic module cell body 10, A second installation hole 1221 is opened on the connection part 122 , and the second installation hole 1221 is used for installing the electric control board 280 controlling the cell body 10 of the basic module and the propeller providing power for the cell body 10 of the basic module. It can be understood that the detection part, the electric control board 280 and the pusher are installed on different parts of the outer frame surrounded by the board, so as to avoid adverse effects between the detection part and the electric control board 280 or the pusher. In addition, installing the detection part on the extension part 121 is beneficial to the detection of the detection part, and installing the electric control board 280 on the connection part 122 is beneficial to the protection of the electric control board 280 .

Specifically, the detection element may be a camera, a laser, or a sensor for measuring light, electricity, or force.

Advantageously, the electric control board 280 is fixed on the extension part 121 of one half-enclosed frame 100 , and the payload/thrust is inserted on the extension part 121 of the other half-enclosed frame 100 . In this way, the subsequent separate operation of the internal and external components is facilitated. If the internal circuit part is damaged, all external fixing devices can be removed, and the half-enclosed frame 1003 on the side that fixes the internal circuit can be pulled out for repairing.

In some optional embodiments, as shown in FIG. 5 , the connecting portion 122 is provided with a first positioning member 1222 , and the core hollow cube 110 is provided with a second positioning member 111 cooperating with the first positioning member 1222 . Thus, the connection between the connecting portion 122 and the core hollow cube 110 is ensured, and the phenomenon that the connecting portion 122 falls out of the core hollow cube 110 is avoided. It should be noted that the first positioning member 1222 and the second positioning member 111 can have various forms. For example, in some embodiments, the first positioning member 1222 is formed as a locking protrusion, and the second positioning member 111 is formed as a locking protrusion. hole. In some embodiments, the first positioning member 1222 is formed as a bolt, and the second positioning member 111 is formed as a nut or the like.

In some embodiments, as shown in FIG. 5 , each connecting portion 122 is provided with a first installation mark 1223 , the core hollow cube 110 is provided with a second installation mark 112 , and each semi-surrounding outer frame 120 is plugged into the core When on the hollow cube 110, the first installation mark 1223 and the second installation mark 112 correspond to each other. Thus, construction personnel can insert the semi-surrounding outer frame 120 onto the core hollow cube 110 in an extremely direction. The first installation mark 1223 and the second installation mark 112 only serve to prompt the installation position, and the specific forms of the first installation mark 1223 and the second installation mark 112 are not limited here.

In some embodiments, as shown in Figure 3, the basic module cell body 10 also includes a protection plate 130, the protection plate 130 is used to install the electric control board 280 controlling the basic module cell body 10, the protection plate 130 is detachably arranged on the frame 100. Thus, the electric control board 280 can be well protected. It should be noted that when the modular space vehicle 1 is assembled in orbit, the electric control board 280 can be fixed on the protection board 130 first, and then fixed on a certain semi-surrounding frame 100 through the first installation hole 1211 and rivets. , and then plug the two half-surrounding frames 100 together.

In some embodiments, the structures of the two half-enclosed outer frames 120 are the same. Therefore, only one mold is needed to produce the semi-enclosed outer frame 120, which reduces the production cost.

It should be noted that, in some cases where the strength requirements are not high, the hollow core cube 110 can be removed from the frame 100 , and the two semi-surrounding frames 100 can be inserted and fixed directly to form the frame 100 .

In some embodiments, as shown in FIG. 3 , the modular space vehicle 1 that can be configured on orbit further includes two solar sails 290, and the two solar sails 290 are installed on opposite sides of the frame 100 respectively. on a border.

In some embodiments, the functional module includes at least one of a power supply system, a power system, a power supply system, a detection system and a control system.

It should be added that the detection parts, the solar sail 290 and the thrusters can be installed in all directions of the frame 100, thereby ensuring that the basic module cell body 10 has higher flexibility, safety and sufficient energy supply.

The following describes a modular spacecraft 10 that can be reconfigured in orbit according to a specific embodiment of the present invention with reference to FIGS. 1-5 .

The modular space vehicle 1 that can be configured on-orbit in this embodiment includes four basic module cell bodies 10, and each basic cell body includes a frame 100 and a functional module.

As shown in Figures 4-5, the frame 100 includes a hollow cube 110 and two half-enclosed outer frames 120, the two half-enclosed outer frames 120 are all plugged on the core hollow cube 110, and each half-enclosed outer frame 120 generally forms It is C-shaped, and the two half-surrounding outer frames 120 are inserted into the core hollow cube 110 opposite to each other in a staggered manner of 90°. Each semi-enclosed outer frame 120 includes a connection part 122 and two extension parts 121 , and the connection part 122 is provided with a magnetic connection part 140 to connect the frames 100 of the two basic module cell bodies 10 . The two extension parts 121 are respectively formed by extending upward from two opposite sides of the connecting part 122 . When each semi-surrounding outer frame 120 is plugged onto the core hollow cube 110 , each extension 121 is located inside the core hollow cube 110 .

Functional modules include a separate power supply system, power system, power supply system, detection system and control system, as shown in Figures 1-3, each basic cell body has the basic functions of a modular space vehicle 1, such as detection, communication, power Wait. The payload on the surface of the frame 100 of each basic cell body includes a main thruster 210, a bionic adsorption mechanism 220, a laser warning device 230, a laser range finder 240, a laser 250, a multi-faceted camera 260, an attitude control thruster 270, etc., to For the aircraft to complete the established mission.

In the aggregation stage of the basic module cell body 10, first select a main cell body (master star) among all the basic module cell bodies 10 to be aggregated, and other slave stars are all close to the main star, and after communicating and negotiating with the main star, determine the specific Plan the route, accurately locate the relative pose state with the main star through the laser range finder 240 and the multi-faceted camera 260 on the surface, cooperate with the main thruster 210 and the attitude control thruster 270, control the magnetism and strength of the magnetic connection device, and finally complete the aggregation. Form the desired configuration, as shown in Figure 2. When the basic module cell body 10 needs to be replaced, the magnetic connection device can be controlled, and the main thruster 210 and the attitude control thruster 270 can be used to complete the separation one by one. After the replacement and repair of the specific basic module cell body 10 is completed, they can be assembled one by one.

The modular space vehicle 1 capable of changing configurations on orbit in this embodiment has the following advantages:

1) The hardware is flexible, light and small: the isomorphic cell body design method is adopted, so that the basic module cell body 10 has the same structure, and complex functions can be completed through self-organization. The plug-in structure ensures the strength and flexibility of the basic module cell body 10 and reduces the cost.

2) Rapid on-orbit response: Since the height of each basic module cell body 10 is the same, the modular space vehicle 1 obtains on-orbit allosteric ability through self-organization. During launch or mission execution, the modular space vehicle 1 can be configured in orbit to complete specific tasks according to the complexity of the surrounding environment at the landing site during mission execution.

3) Prolonging the on-orbit lifespan: through the plug-in frame 100 structure, the cell body 10 of the basic module can be quickly replaced on-orbit when the cell body 10 fails. When the basic module cell body 10 is damaged as a whole, any healthy cell body can be selected for replacement, thereby prolonging the service life of the aircraft.

In the description of this specification, references to the terms "one embodiment," "some embodiments," "exemplary embodiments," "example," "specific examples," or "some examples" are intended to mean that the implementation Specific features, structures, materials or characteristics described in an embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

Although the embodiments of the present invention have been shown and described, those skilled in the art can understand that various changes, modifications, substitutions and modifications, the scope of the present invention is defined by the claims and their equivalents.

Claims (10)

1. A modular space vehicle capable of changing configurations in orbit, characterized in that it comprises a basic module cell body, and the basic module cell body includes: A frame, the frame is provided with a magnetic connector, and the two basic module cell bodies can be connected through the magnetic connector; A functional module, the functional module is installed on the frame, and the functional module can be used to complete the predetermined task of the basic module cell body. 2. The on-orbit variable-configurable modular space vehicle according to claim 1, wherein the frame comprises: core hollow cube, Two half-enclosed outer frames, the two half-enclosed outer frames are plugged on the core hollow cube; wherein, each of the half-enclosed outer frames is generally formed in a C shape, and the two half-enclosed outer frames The frames are inserted into the core hollow cube opposite to each other in a staggered manner of 90°. 3. The on-orbit variable-configurable modular space vehicle according to claim 2, wherein each of the semi-enclosed outer frames comprises: A connection part, the magnetic connection part is provided on the connection part to connect the frames of the two basic module cell bodies; Two extension parts, the two extension parts are respectively formed by the upward extension of the two opposite sides of the connecting part, wherein, when each of the semi-surrounding outer frames is inserted into the core hollow cube, each The extension is located inside the core hollow cube. 4. The on-orbit variable-configurable modular space vehicle according to claim 3, wherein a first installation hole is opened on each of the extension parts, and the first installation hole is used for installing a detection element to To realize the detection function of the cell body of the basic module, a second installation hole is opened on the connecting part, and the second installation hole is used for installing an electric control board controlling the cell body of the basic module, and for the basic module The cell body powers the thrusters. 5. The on-orbit variable-configurable modular space vehicle according to claim 3, characterized in that, the connecting portion is provided with a first positioning member, and the core hollow cube is provided with a spacer corresponding to the first positioning member. The second positioning part that fits the part. 6. The on-orbit variable-configurable modular space vehicle according to claim 3, characterized in that, each connecting portion is provided with a first installation mark, and the core hollow cube is provided with a second installation mark, each When one of the semi-enclosed outer frames is plugged into the core hollow cube, the first installation mark and the second installation mark correspond to each other. 7. The on-orbit variable-configurable modular space vehicle according to claim 1, wherein the basic module cell body also includes a protective plate, and the protective plate is used for installing and controlling the basic module cell body. The electric control board, the protection board is detachably arranged on the frame. 8. The on-orbit variable-configurable modular space vehicle according to claim 1, further comprising two solar sails, and the two solar sails are respectively installed on the frame on the two opposite borders. 9. The on-orbit variable-configurable modular space vehicle according to claim 2, wherein the structures of the two half-enclosed outer frames are the same. 10. The modular space vehicle that can be configured on-orbit according to any one of claims 1-9, wherein the functional modules include power supply system, power system, power supply system, detection system and control system at least one of the .