CN115610701A - Extensible three-dimensional foldable truss bearing structure for space - Google Patents
Extensible three-dimensional foldable truss bearing structure for space Download PDFInfo
- Publication number
- CN115610701A CN115610701A CN202211017987.9A CN202211017987A CN115610701A CN 115610701 A CN115610701 A CN 115610701A CN 202211017987 A CN202211017987 A CN 202211017987A CN 115610701 A CN115610701 A CN 115610701A
- Authority
- CN
- China
- Prior art keywords
- truss
- trusses
- bearing structure
- circumferential
- dimensional
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 13
- 238000010276 construction Methods 0.000 claims description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 230000000712 assembly Effects 0.000 claims description 5
- 238000000429 assembly Methods 0.000 claims description 5
- 239000004917 carbon fiber Substances 0.000 claims description 5
- 239000002131 composite material Substances 0.000 claims description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 229910001220 stainless steel Inorganic materials 0.000 claims description 5
- 239000010935 stainless steel Substances 0.000 claims description 5
- 239000000446 fuel Substances 0.000 claims description 4
- 238000010248 power generation Methods 0.000 claims description 4
- 238000009434 installation Methods 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 2
- 210000001503 joint Anatomy 0.000 description 13
- 230000005540 biological transmission Effects 0.000 description 8
- 238000000034 method Methods 0.000 description 4
- 229920001967 Metal rubber Polymers 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000003032 molecular docking Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The invention discloses an expandable three-dimensional foldable truss bearing structure for a space. The invention uses the vertical truss, the radial truss, the central truss and the circumferential truss as main supports, the upper truss and the lower truss are respectively connected with other structures through flexible connecting mechanisms, the middle truss storage box is provided with the rail-controlled electric thruster assembly, and electromechanical equipment installation positions are reserved at other parts of the trusses. The large-scale three-dimensional foldable truss bearing structure with high storage ratio can be launched at one time, and is formed at one time after being unfolded on a rail, so that the modular assembly capacity of an ultra-large space system is greatly improved, the requirements on strength and light weight are met, and the large-scale three-dimensional foldable truss bearing structure has the characteristics of flexible electromechanical connection, omnidirectional independent rail maintenance thruster structure, flexible equipment installation and the like.
Description
Technical Field
The invention relates to an expandable three-dimensional foldable and unfoldable truss bearing structure for a space, which is used for designing and constructing a structure of an ultra-large space system such as a solar power station, meets the requirements of modularization and light weight, and has the characteristics of electromechanical connection, omnidirectional independent track maintenance thruster structure, flexible equipment installation and the like.
Background
Due to the development of spacecrafts, the demand for ultra-large structures is more and more urgent, which brings great challenges to the design and manufacture of the spacecraft structures. The structure scale of a space ultra-large system such as a space solar power station and the like reaches hundreds of meters, the space ultra-large system is constructed by multiple times of emission and space assembly, and in order to reduce the weight of the system, the preferable main structure form is a truss structure. But the conventional large-scale cylindrical force-bearing structure cannot be adopted due to the limitation of carrying envelope and the requirement of space assembly. The existing design is generally a one-dimensional expandable truss or a three-dimensional bar-type structure, and the invention of a three-dimensional foldable truss bearing structure is not provided. However, the bar-type structure is difficult to be made into an oversized structure, and the end part is not easy to be provided with a butt joint mechanism, so that the expandability of the whole structure is poor, and the bar-type structure cannot be applied to the construction of a spatial oversized structure.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, the extensible three-dimensional foldable truss bearing structure for the space is provided, and the problems of unfolding, modularization, light weight and the like of a large aerospace main bearing structure are solved.
The technical solution of the invention is as follows:
an expandable three-dimensional foldable and unfoldable truss bearing structure for space comprises: the system comprises a vertical truss, a circumferential truss, a radial truss, a central truss, an electric power guide truss, a truss storage box and an electromechanical interface;
the circumferential trusses are annular, the upper, middle and lower circumferential trusses are connected through eight vertical trusses, and truss storage boxes are arranged at the connecting positions; crossed radial trusses are arranged in the upper circumferential truss and the lower circumferential truss, and a central truss is arranged between the cross point of the crossed radial trusses in the upper circumferential truss and the cross point of the crossed radial trusses in the lower circumferential truss; and the cross points are provided with truss storage boxes; the middle part of the central truss is also provided with a truss storage box, and the middle part is connected with eight truss storage boxes distributed on the circumferential truss through a plurality of electric power guide trusses; a motor is arranged in the truss storage box to provide power for unfolding the truss;
the electromechanical interfaces are of annular buckle structures, are arranged on the upper end faces of the truss storage boxes distributed on the upper circumferential truss and the lower end faces of the truss storage boxes distributed on the lower circumferential truss, and are used for connecting other parts by the three-dimensional foldable truss.
Furthermore, the three-dimensional foldable and unfoldable truss bearing structure can be unfolded in three dimensions, and the construction of a large-size three-dimensional bearing structure is realized by a small launching volume; wherein the configuration of the central truss is the same as that of the vertical trusses.
Furthermore, before launching, the vertical truss, the central truss, the circumferential truss, the radial truss and the electric power guide truss are all collected and stored in the truss storage box.
Furthermore, when the rail is unfolded, the rail is unfolded in the X direction, the Y direction and the Z direction in sequence to form a cylindrical barrel-shaped structure.
Furthermore, the axis of the central truss coincides with the axis of the cylindrical barrel-shaped structure, and the central truss is parallel to the eight vertical trusses.
Furthermore, the three-dimensional foldable and unfoldable truss bearing structure is connected with the solar power generation array and the microwave antenna respectively through the flexible connecting mechanism from top to bottom, so that the construction of the ultra-large spacecraft is realized.
Furthermore, 8 groups of rail-controlled electric thruster assemblies are distributed at the connecting positions of the middle circumferential truss and the eight vertical trusses; each group of electric thruster components comprises a plurality of electric thrusters, a fuel supply system and a power supply system, and the electric thrusters work independently or cooperatively and are used for adjusting the on-orbit attitude.
Furthermore, the truss storage box is of a square thin-wall structure, the trusses are stored in the box before being unfolded, and meanwhile the truss storage box is also used as a connecting component of the trusses in all directions.
Furthermore, the vertical truss, the circumferential truss, the radial truss, the central truss and the electric power guide truss are all made of carbon fiber composite materials, the connecting joints are made of stainless steel, a skin-free structure is adopted, and all devices are subjected to distributed thermal control.
Furthermore, the vertical truss, the circumferential truss, the radial truss, the central truss and the electric power guide truss are all formed by connecting a plurality of truss basic units, and each truss basic unit comprises a longitudinal beam, a spherical hinge joint, a stay cable and a rigid frame; the longitudinal beams are connected with the rigid frames through ball joints, and diagonal lines are connected through stay cables in a quadrilateral structure formed by the two longitudinal beams and the two rigid frames.
Compared with the prior art, the invention has the beneficial effects that:
1) Large three-dimensional foldable truss structure with high storage ratio: the on-track is sequentially unfolded along the X/Y/Z directions to form a cylindrical barrel structure with the diameter and the height of tens of meters, so that one-time unfolding and forming on the track after one-time emission are realized;
2) The omnidirectional independent track control thruster structure comprises: and 8 groups of rail-controlled electric thruster assemblies are arranged at the connecting sections of the middle circumferential truss and the 8 vertical trusses. Each group consists of a plurality of electric thrusters, a fuel supply system and a power supply system, and can work independently;
3) Flexible electromechanical connection and active vibration control: the three-dimensional foldable truss structure is connected with the solar power generation array and the large microwave antenna up and down through the flexible connecting mechanisms respectively and has an active vibration suppression function, and the hierarchical attitude control of the ultra-large spacecraft is realized, wherein the difference between the upper control precision and the lower control precision reaches 2 orders of magnitude.
4) Equipment distributed thermal control and independent environmental effect protection: the truss material is made of carbon fiber composite ingredients, all equipment carries out distributed thermal control and independent environmental effect protection, and a skin structure is omitted, so that the weight and complexity of the system are greatly reduced, and the ultra-strong lightweight design is realized.
5) The invention can bear the force in all directions, is very thin when compressed, is very large when opened, and is easy to shape after being extended. The structure can be made into an oversized structure, the end part is easy to install a butt joint mechanism, the expandability of the whole structure is high, and the structure can be applied to the construction of a spatial oversized structure.
Drawings
FIG. 1 is a schematic drawing showing a three-dimensional foldable truss folded;
FIG. 2 is a schematic view of the three-dimensional foldable truss being unfolded;
FIG. 3 is a schematic view of the basic unit of the truss (in an unfolded state);
fig. 4 is a schematic view of the basic unit of the truss (in a collapsed state);
FIG. 5 is a schematic view of a stringer assembly and a stringer joint;
FIG. 6 is a schematic view of the hinge position and the components of the ball joint;
FIG. 7 is a schematic illustration of the position of two stay cables;
FIG. 8 is a schematic diagram of a mechanical interface layout;
FIG. 9 is a schematic view of a modular mechanical interface assembly;
FIG. 10 is a schematic diagram of an electrical interface layout.
Detailed Description
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
The invention provides a high-storage-ratio three-dimensional foldable truss force bearing structure constructed by a space super-large system, which is folded according to the enveloping of a carrier in the launching process, sequentially unfolded in the X/Y/Z three directions behind a rail to form a column barrel structure with the diameter and the height of tens of meters, wherein 9 vertical trusses, 4 radial trusses and three circumferential trusses are used as main supports, the upper truss and the lower truss are respectively connected with other structures through flexible connecting mechanisms, a rail electric control thruster assembly is arranged in a middle truss storage box, and electromechanical equipment installation positions are reserved at other parts of the trusses. The large-scale three-dimensional foldable truss bearing structure with high storage ratio can be launched at one time and is formed at one time after being unfolded on a rail, so that the modular assembly capacity of an ultra-large space system is greatly improved.
As shown in figures 1, 3 and 4, the invention can bear the force in all directions, is very thin when compressed, is very large when opened, is easy to shape after being extended, has small rebound attraction, and the final product structure is integrally firm, stable and reliable, even can be disassembled, can be compressed, folded and extended, is convenient to carry and has the products with heat preservation and good stress.
As shown in fig. 2, the invention provides an expandable three-dimensional foldable truss bearing structure for space, which comprises: the system comprises a vertical truss 1, a circumferential truss 2, a radial truss 3, a central truss 4, an electric power guide truss 5, a truss storage box 6 and an electromechanical interface 7;
the circumferential trusses are annular, the upper, middle and lower circumferential trusses are connected through eight vertical trusses, and truss storage boxes are arranged at the connecting positions; crossed radial trusses are arranged in the upper circumferential truss and the lower circumferential truss, and a central truss is arranged between the cross point of the crossed radial trusses in the upper circumferential truss and the cross point of the crossed radial trusses in the lower circumferential truss; and the cross points are provided with truss storage boxes; the middle part of the central truss is also provided with a truss storage box, and the middle part is connected with eight truss storage boxes distributed on the circumferential truss through a plurality of electric power guide trusses; a motor is arranged in the truss storage box to provide power for unfolding the truss;
the electromechanical interfaces are of annular buckle structures, are arranged on the upper end faces of the truss storage boxes distributed on the upper circumferential truss and the lower end faces of the truss storage boxes distributed on the lower circumferential truss, and are used for connecting other parts by the three-dimensional foldable truss.
As shown in fig. 3 and 4, the three-dimensional foldable truss bearing structure can be unfolded in three dimensions, and the construction of a large-size three-dimensional bearing structure is realized by a small launching volume; wherein the configuration of the central truss is the same as that of the vertical trusses.
Before launching, the vertical trusses, the central truss, the circumferential trusses, the radial trusses and the electric power guide trusses are all folded and stored in the truss storage box. When the rail is unfolded, the rail is unfolded in the X direction, the Y direction and the Z direction in sequence to form a cylindrical barrel-shaped structure. At the moment, the axis of the central truss coincides with the axis of the cylindrical barrel-shaped structure, and the central truss is parallel to the eight vertical trusses.
The three-dimensional foldable and unfoldable truss bearing structure is connected with the solar power generation array and the microwave antenna respectively through the flexible connecting mechanism from top to bottom, and construction of the ultra-large spacecraft is achieved.
Arranging rail-controlled electric thruster assemblies at the connecting positions of the middle circumferential truss and the eight vertical trusses, wherein the number of the rail-controlled electric thruster assemblies is 8; each group of electric thruster components comprises a plurality of electric thrusters, a fuel supply system and a power supply system, and the electric thrusters work independently or cooperatively and are used for adjusting the on-orbit attitude.
The truss storage box is of a square thin-wall structure, the trusses are stored in the box before being unfolded, and meanwhile the truss storage box is also used as a connecting component of the trusses in all directions.
In the invention, the vertical truss, the circumferential truss, the radial truss, the central truss and the electric power guide truss are all made of carbon fiber composite materials, the connecting joint is made of stainless steel, a skin-free structure is adopted, and all equipment is subjected to distributed thermal control.
As shown in fig. 3, the vertical truss, the circumferential truss, the radial truss, the central truss and the electric power guiding truss are all formed by connecting a plurality of truss basic units, and each truss basic unit comprises a longitudinal beam 31, a ball joint 32, a stay cable 33, a rigid frame 34 and a lock body 35; the longitudinal beam is connected with the rigid frame through a spherical hinge joint, the diagonal line is connected through a stay cable, and a lock body 35 is arranged at the intersection of the stay cable.
The embodiment is as follows:
the scheme comprises 9 vertical trusses (comprising 1 central truss), 4 radial trusses and 3 circumferential trusses, the vertical trusses are collected and stored in a storage box before being launched, and the unfolding process is correspondingly divided into two stages. The first stage, the vertical truss is unlocked, and the self-driven synchronous mechanism assists the unfolding hinge to drive the unfolding hinge to unfold and lock; in the second stage, the folding mechanisms of the circumferential trusses and the radial trusses are unlocked, the 3 circumferential trusses and the 4 radial trusses are synchronously unfolded in place under the driving of a motor, and then the mechanisms are kept locked;
the truss storage box is of a square thin-wall structure, the trusses are stored in the box before being unfolded, meanwhile, the storage box is also a connecting component of the trusses in all directions, and the motors are distributed in the storage box to provide power for unfolding of the trusses.
As shown in fig. 3, in the present invention, the basic units of the vertical truss, the circumferential truss and the radial truss are all square structures, and one truss basic unit includes rigid frames 30, 34, a longitudinal beam 31, a stay cable 33 and a lock body 35. The corresponding vertexes of the rigid frames 30 and 34 are connected by 4 longitudinal beams 31; the rigid frame is in a left and right symmetrical structure; the central line of the active end of the locking mechanism is superposed with the central line of the passive end; when the active end and the passive end of the lock body 35 are locked, the truss basic unit is in an unfolded and locked state; when folding is needed, the active end and the passive end of the locking mechanism are separated, force is applied to the normal direction of the rigid frame, and the truss basic unit is folded, as shown in fig. 4.
The beam assembly (longitudinal beam, rigid frame) is formed by the articulation of the longitudinal joints in the beam and ball joints, as shown in figure 5. The cross section of the beam is a thin-wall round tube, and the beam material is made of carbon fiber/epoxy resin composite material. The rigid frame is actually a square frame structure formed by combining four beams.
The ball joints are respectively hinged with the longitudinal beam and the rigid frame to form a unit framework, as shown in fig. 6. The longitudinal beam joints are hinged and then arranged on a straight line, and the ball joint 32 is made of stainless steel.
The plane formed by the central lines of the beams (on the same side) between the adjacent beams is the central plane of the stay cable, as shown in fig. 7. When the truss module is unfolded and locked, the stay cable is tensioned to reinforce the truss module, and the stay cable is made of stainless steel.
As shown in fig. 2. The three-dimensional foldable truss bearing structure butt joint interfaces are positioned at the two ends and at the center above the cross sections of the 9 vertical trusses; the docking interface is a modular electromechanical interface that provides mechanical locking and power transfer connections for the connection components.
The mechanical interface in the modular interface is a high-rigidity self-adaptive butt-joint locking device, and as shown in fig. 8, except for the passive end of the part, other parts all belong to the active end of the connecting and separating device. The driving end is driven by the mechanical arm to be matched with the driven end through guiding, and the driving end just completes guiding and fitting with the driven end and is in the stage of being prepared for locking.
As shown in fig. 9 (a), the nut barrel is connected with the sleeve through two deep groove ball bearings and a thrust ball bearing, and the thrust ball bearing is mainly used for bearing the locking pulling force in the X direction in the locking process. The cover plate is fixed with the nut barrel in a threaded connection mode, the connecting plate 1 is connected with the sleeve through threads, the motor is fixed on the connecting plate 1, an output shaft of the motor is inserted into a D-shaped hole of the cover plate, and the motor drives the nut barrel to rotate through the cover plate. The T-shaped screw rod is matched with the nut barrel through self-locking threads, and only one section of the T-shaped screw rod is provided with a thread structure. The metal rubber is fixed on the inner wall of the nut barrel and is in close fit with the T-shaped screw rod, and the T-shaped screw rod is of a polished rod structure in a relative sliding area of the T-shaped screw rod and the T-shaped screw rod; when the T-shaped screw is in a free state, the nut barrel can drive the T-shaped screw to rotate together through the metal rubber, and when the T-shaped screw is restrained and can not rotate, the metal rubber and the T-shaped screw rotate relatively, and at the moment, the T-shaped screw only moves left and right along the X direction under the side effect of the thread of the nut barrel. A section of blind hole is processed at the left end of the T-shaped screw, and a cylindrical structure protruding from the cover plate is inserted into the blind hole at the left end of the T-shaped screw to support the T-shaped screw.
The guide cone cylinder and the sleeve are matched in a groove pair mode, relative movement can be achieved only between the guide cone cylinder and the sleeve, relative rotation cannot be achieved, a cylindrical compression spring is installed between the guide cone cylinder and the sleeve, the guide cone cylinder is similar to a floating buffering guide cylinder, and in the locking process, the guide cone cylinder compression cylindrical spring is gradually attached to the sleeve. Two conical heads are arranged on the outer edge of the guide conical cylinder, and two conical sockets are arranged at the same position on the outer edge of the driven end matched with the guide conical cylinder, so that when the guide conical cylinder slides into the large conical socket of the driven end, the two conical heads of the outer edge of the guide conical cylinder are matched with the two conical sockets of the outer edge of the driven end to limit circumferential rotation between the two conical heads, and a determined relative pose is formed between the two conical heads.
As shown in fig. 9 (b), two faces arranged at 90 ° are provided inside the guide cone, and these two faces are engaged with two side faces of the rectangular block protruding from the right end of the T-shaped screw to limit the rotational degree of freedom of the T-shaped screw (the T-shaped screw can only rotate within 90 °).
In the state of fig. 9 (a), the head of the rightmost end of the T-shaped screw can slide along the X direction into the rectangular hole of the passive end (the width of the rectangular hole is larger than the diameter of the cylindrical section of the T-shaped screw), and after the T-shaped screw rotates 90 degrees, the T-shaped screw can be attached to the passive end when sliding along the-X direction, and the degree of freedom of the T-shaped screw in sliding along the-X direction is limited.
An electrical interface in the modular interface is used for meeting the requirement of system electrical connection, so that energy transmission connection and controllable disconnection are realized, and the requirement of truss electromechanical assembly butt joint is met, as shown in fig. 10. The electric interface realizes power transmission of the power supply under the guarantee of mechanical docking precision. For the MW level power transmission requirement provided by the system, the assembly interface provides the idea of power interface modularization and layout integration according to requirements for the functional layout of the interface. The main truss of the power station system is the only channel for power transmission, so that the energy transmission requirements of the butt joint surfaces of the main truss are consistent. Therefore, the number of the power supply device interface sub-modules with the same assembly truss unit and different butt joint surfaces can be configured by standardizing the power supply device interfaces, and the configuration number depends on the transmission power of a single device interface and the overall power transmission requirement of the assembly butt joint surface, so that the power supply transmission requirement of truss assembly of the power station system is met.
The invention is not described in detail and is within the knowledge of a person skilled in the art.
Claims (10)
1. The utility model provides a space is with scalable three-dimensional truss load-bearing structure that can expand which characterized in that includes: the system comprises a vertical truss, a circumferential truss, a radial truss, a central truss, an electric power guide truss, a truss storage box and an electromechanical interface;
the circumferential trusses are annular, the upper, middle and lower three circumferential trusses are connected through eight vertical trusses, and truss storage boxes are arranged at the connecting positions; crossed radial trusses are arranged in the upper circumferential truss and the lower circumferential truss, and a central truss is arranged between the cross point of the crossed radial trusses in the upper circumferential truss and the cross point of the crossed radial trusses in the lower circumferential truss; and the cross points are provided with truss storage boxes; the middle part of the central truss is also provided with a truss storage box, and the middle part is connected with eight truss storage boxes distributed on the circumferential truss through a plurality of electric power guide trusses; a motor is arranged in the truss storage box to provide power for unfolding the truss;
the electromechanical interfaces are of annular buckle structures, are arranged on the upper end faces of the truss storage boxes distributed on the upper circumferential truss and the lower end faces of the truss storage boxes distributed on the lower circumferential truss, and are used for connecting other parts by the three-dimensional foldable truss.
2. The expandable three-dimensional foldable truss bearing structure for the space according to claim 1, wherein: the three-dimensional foldable and unfoldable truss bearing structure can be unfolded in three dimensions, and the construction of a large-size three-dimensional bearing structure is realized by a small launching volume; wherein the configuration of the central truss is the same as that of the vertical trusses.
3. The expandable three-dimensional foldable truss bearing structure for the space according to claim 1, wherein: before launching, the vertical truss, the central truss, the circumferential truss, the radial truss and the electric power guide truss are all collected and stored in the truss storage box.
4. The expandable three-dimensional foldable truss bearing structure for the space according to claim 1, wherein: when the rail is unfolded, the rail is unfolded in the X direction, the Y direction and the Z direction in sequence to form a cylindrical barrel-shaped structure.
5. The expandable three-dimensional foldable truss bearing structure for the space according to claim 4, wherein: the central truss is superposed with the axis of the cylindrical barrel-shaped structure, and the central truss is parallel to the eight vertical trusses.
6. The expandable three-dimensional foldable truss bearing structure for the space according to claim 1, wherein: the three-dimensional foldable truss bearing structure is connected with the solar power generation array and the microwave antenna through the flexible connecting mechanism from top to bottom, and the construction of the ultra-large spacecraft is realized.
7. The expandable three-dimensional foldable truss bearing structure for the space according to claim 1, wherein: connecting positions of the middle circumferential truss and the eight vertical trusses are provided with 8 groups of rail-controlled electric thruster assemblies; each group of electric thruster components comprises a plurality of electric thrusters, a fuel supply system and a power supply system, and the electric thrusters work independently or cooperatively and are used for adjusting the on-orbit attitude.
8. The expandable three-dimensional foldable truss bearing structure for the space according to claim 1, wherein: the truss storage box is of a square thin-wall structure, the trusses are stored in the box before being unfolded, and meanwhile the truss storage box is also used as a connecting component of the trusses in all directions.
9. The expandable three-dimensional foldable truss bearing structure for the space according to claim 1, wherein: the vertical truss, the circumferential truss, the radial truss, the central truss and the electric power guide truss are all made of carbon fiber composite materials, the connecting joints are made of stainless steel, a skin-free structure is adopted, and all equipment is subjected to distributed thermal control.
10. The expandable three-dimensional foldable truss bearing structure for the space according to claim 1, wherein: the vertical truss, the circumferential truss, the radial truss, the central truss and the electric power guide truss are formed by connecting a plurality of truss basic units, and each truss basic unit comprises a longitudinal beam, a spherical hinge joint, a stay cable and a rigid frame; the longitudinal beams are connected with the rigid frames through the spherical hinges, and diagonal lines are connected through stay cables in a quadrilateral structure formed by the two longitudinal beams and the two rigid frames.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211017987.9A CN115610701A (en) | 2022-08-24 | 2022-08-24 | Extensible three-dimensional foldable truss bearing structure for space |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211017987.9A CN115610701A (en) | 2022-08-24 | 2022-08-24 | Extensible three-dimensional foldable truss bearing structure for space |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115610701A true CN115610701A (en) | 2023-01-17 |
Family
ID=84856835
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211017987.9A Pending CN115610701A (en) | 2022-08-24 | 2022-08-24 | Extensible three-dimensional foldable truss bearing structure for space |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115610701A (en) |
-
2022
- 2022-08-24 CN CN202211017987.9A patent/CN115610701A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9676501B1 (en) | Space solar array architecture for ultra-high power applications | |
| Zhang et al. | Deployable structures: structural design and static/dynamic analysis | |
| CN106542089A (en) | Variable geometry aircraft | |
| CN206691377U (en) | A kind of in-orbit assembly system of space truss using robot for space | |
| CN113772128B (en) | Separated double-shaft space solar cell array | |
| CN105857643A (en) | Flexible solar wing used for satellite power supply and two-degree-of-freedom storage device applied to flexible solar wing | |
| CN110450983B (en) | Agile satellite configuration | |
| CN105966640A (en) | Repeatable variable configuration truss type spacecraft structure | |
| CN113589517B (en) | Separable modularized sub-mirror structure of large space telescope and on-orbit replacement method | |
| CN107128514A (en) | The in-orbit assembly system of space truss and method of a kind of use robot for space | |
| CN112404984A (en) | Ultra-large space telescope on-orbit assembly system based on multi-space robot | |
| CN112319855A (en) | Spatial extensible prism unit for on-orbit assembly | |
| CN113675574B (en) | Bidirectional flat plate folding and unfolding unit and bidirectional flat plate folding and unfolding antenna mechanism | |
| CN110329542B (en) | Satellite configuration suitable for cooperative control of ultra-large flexible satellite | |
| Cline et al. | Tritruss packaging and deployment trade study | |
| CN112124639B (en) | Screw nut clamping type docking mechanism and working method thereof | |
| CN115610701A (en) | Extensible three-dimensional foldable truss bearing structure for space | |
| CN112357118B (en) | Manned lunar surface lander based on truss structure | |
| US20230344110A1 (en) | Hexagonal frustum deployable unit and deployable mechanism formed by the same | |
| CN115101918B (en) | Two-dimensional folding and unfolding mechanism for flat satellite antenna and working method thereof | |
| CN114802815B (en) | Shear hinge type universal module based on water chestnut lock butt joint and oriented to on-orbit assembly | |
| CN217881915U (en) | Large-size expandable loop antenna mechanism | |
| Adler et al. | Novel phased array antenna structure design | |
| CN114962438B (en) | Flexible deployable mechanism based on paper folding principle and soft hinge | |
| CN115469427A (en) | Space telescope and back frame unfolding method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |