CN109515753A - A kind of load plate expansion module of spacecraft - Google Patents
A kind of load plate expansion module of spacecraft Download PDFInfo
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- CN109515753A CN109515753A CN201811495675.2A CN201811495675A CN109515753A CN 109515753 A CN109515753 A CN 109515753A CN 201811495675 A CN201811495675 A CN 201811495675A CN 109515753 A CN109515753 A CN 109515753A
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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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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Abstract
The present invention relates to a kind of load plate expansion modules of spacecraft, including load single-blade, load single-blade includes successively hinged at least four groups of load board groups, load board group includes two pieces of hinged load plates, it is articulated with the strut I of load board group left and right ends, hinge between at least one Active plate is provided between the adjacent load plate of load single-blade, one end of strut I is articulated with the end of load plate, the other end and another strut I with group load board group are hinged, intermediate strut group is provided between the adjacent load board group of load single-blade, and being located at most intermediate intermediate strut group is the first intermediate strut group, other intermediate strut groups are the second intermediate strut group, first intermediate strut group includes symmetrically arranged two groups of connecting rod groups, every group of connecting rod group includes strut IV and strut V, second intermediate strut group includes two strut II.The load plate expansion module of spacecraft of the invention is unfolded for multi-load plate and has high storage ratio.
Description
Technical field
The present invention relates to a kind of load plate expansion modules of spacecraft, more particularly to one kind to be directed to load single wing plate quantity not
Compare unfolding mechanism less than four pieces and for the high storage of even number.
Background technique
With the diversification and the increasingly raising of Functional Requirement of military, civilian spacecraft function, the load of spacecraft configuration
The space scales parameter such as length, area is significantly promoted, and the radome fairing envelope of vehicle, large scale load are limited to
It can not be emitted with working condition, need load piecemeal to be load plate, implement configuration conversion using unfolding mechanism after entering the orbit.
Single-blade veneer and the double plate unfolding mechanisms of single-blade, but plate more for single-blade are largely used in current spacecraft, i.e., more than four plate of single-blade
Unfolding mechanism, the extension that can not pass through the double plate unfolding mechanisms of single-blade veneer or single-blade realizes design.Meanwhile multi-load plate quantity
Also the storage ratio of unfolding mechanism is required to improve as far as possible.Therefore, it needs to develop one kind and is provided simultaneously with scalability and high storage ratio
Multi-load plate unfolding mechanism.
Summary of the invention
It is unfolded for multi-load plate in order to solve the above technical problems, the object of the present invention is to provide one kind and there is high storage
The load plate expansion module of the spacecraft of ratio.
The load plate expansion module of spacecraft of the invention, including load single-blade, the load single-blade include successively hinged
At least four groups of load board groups, the load board group includes two pieces of hinged load plates, is articulated with load board group left and right ends
Strut I is provided with hinge between at least one Active plate, one end of the strut I between the adjacent load plate of the load single-blade
It is articulated with the end of load plate, the other end of strut I and another strut I of same group of load board group are hinged, the load list
Intermediate strut group is provided between the adjacent load board group of the wing, and being located at most intermediate intermediate strut group is support among first
Bar group, other intermediate strut groups are the second intermediate strut group, and the first intermediate strut group includes symmetrically arranged two groups of connections
Bar group, every group of connecting rod group include strut IV and strut V, and one end of the strut IV is articulated with the top of adjacent struts I, strut
The other end of IV and strut V are hinged, and the other end of strut V and the strut V of another group of connecting rod group are hinged, support among described second
Bar group includes two strut II, and wherein a strut II is articulated with the top of adjacent strut I, another strut II with should
Another strut II of the second intermediate strut group is hinged.
Wherein, hinge refers to the hinge with driving motor between Active plate, and the hinge of hinge can be driven by driving motor
It separates or is closed, so that load plate connected to it be driven to be unfolded or be closed.
The total length of first intermediate strut group is long compared with the total length of the second intermediate strut group.And when load single-blade is unfolded,
First intermediate strut group and two adjacent strut I surround to form a diamond structure, the second intermediate strut group and adjacent two
Root strut surrounds to form an isosceles triangle.Structure is more firm after load single-blade is unfolded, while being also conducive to
It is collapsed.It is specific when collapsing, load single-blade gradually folding shrinking under the driving of hinge between Active plate, until load single-blade is complete
It is parallel to each other to collapse to each load plate.Its shared small volume at this time.
Further, the load plate expansion module of spacecraft of the invention, between the adjacent load plate of the load single-blade
It is additionally provided with hinge between passive plate.
Hinge refers to the hinge without driving motor between passive plate, opens and closes under the driving of hinge between Active plate.One side
Face strengthens the connective stability between load plate, on the other hand also functions to the effect of auxiliary drive, the hinge difference of two sides
It is connected with adjacent load plate.
Further, the load plate expansion module of spacecraft of the invention is located at load board group left end, load board group right end
The number of strut I be two, and two strut I are set in parallel in the front and rear sides of load plate, correspondingly, per adjacent
The number of intermediate strut group between load board group is also two groups, and every group of load board group further includes one and its width direction
Parallel strut III, one end of the strut III respectively with the strut I and adjacent strut that are located on front side of this group of load board group
II is hinged, and the other end and the strut I and adjacent strut II that are located on rear side of this group of load board group are hinged.
This design, so that entire strut group connection is more firm.Wherein, every group of load board group includes four strut I, wherein
Two are located at the left end of load board group, and another two are located at the right end of load board group.
Further, the load plate expansion module of spacecraft of the invention, between the Active plate hinge include articulated shaft, point
Not first hinge hinged with articulated shaft, the second hinge and the driving for driving the first hinge or the second hinge to rotate relative to articulated shaft
Motor.
The setting of driving motor realizes the active drive to load plate.Specifically, the first hinge, the second hinge difference
It is connected with adjacent load plate, when gathering, driving motor drives the first hinge or the rotation of the second hinge, with the first hinge or second
The connected load plate of hinge just starts turning, and drives another load plate and conjunction connected to it by strut I, intermediate strut group
Page rotation, until entire load is generally collapsed and finished.On the contrary, the general expansion of load is opposite with the above process.
Further, the load plate expansion module of spacecraft of the invention, hinge includes shell between the Active plate, described
Driving motor is set in shell, and the articulated shaft is connect by bearing with shell, and first hinge and shell are connected, described
Driving motor passes through gear and the hinged axis connection.
When specific works, the output shaft of driving motor drives first gear rotation connected to it, due on articulated shaft
It is installed with second gear and second gear is engaged with first gear, in this way, with the rotation of first gear, driving motor, shell
And rotated with the first hinge that driving motor is connected relative to articulated shaft, so that the load plate being connected with the first hinge be driven to rotate.
Further, the both ends of the load plate expansion module of spacecraft of the invention, the load single-blade are additionally provided with bar
Between hinge I.
According to the above aspect of the present invention, the present invention has at least the following advantages: the load plate expansion module of spacecraft of the invention is used
After realizing that spacecraft is entered the orbit, multiple tactic load plates are converted from the configuration that gathering state is expanded to deployed condition.Space flight
The load plate expansion module of device, basic principle are that the expansion of concatenated four-bar mechanism is locked as concatenated triangular structure,
By hinge etc. is formed between hinge, passive plate between hinge, Active plate between different types of strut, bar.Single-blade load plate can be
The arbitrary shapes such as plane, spherical surface, paraboloid, irregular face, quantity are no less than four pieces and are even number.Every two pieces of adjacent load
Plate is by hinge is connected between hinge and a passive plate between an Active plate.It is cut with scissors between hinge, passive plate between hinge, Active plate between bar
Chain is contractd using coaxial design implementation mechanism freedom degree, and strut is arranged in the side of load plate, realizes high storage ratio
Collapse expansion.
Wherein, various struts play linkage and support function in unfolding mechanism, and hinge plays in unfolding mechanism between bar
The functions such as strut, auxiliary output torque, locking are connected, hinge plays connection load plate, output in unfolding mechanism between Active plate
The functions such as driving moment, locking, between passive plate hinge played in unfolding mechanism connection load plate, auxiliary output driving torque,
The functions such as locking.
In conclusion the load plate expansion module of spacecraft of the invention is able to carry out the expansion of multi-load plate, have simultaneously
Height storage ratio.
The above description is only an overview of the technical scheme of the present invention, in order to better understand the technical means of the present invention,
And can be implemented in accordance with the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention and the accompanying drawings.
Detailed description of the invention
Fig. 1 is the unfolded state schematic diagram of the load plate expansion module of spacecraft；
Fig. 2 is the rounding state schematic diagram of the load plate expansion module of spacecraft；
Fig. 3 is the basic principle schematic of the load plate expansion module of spacecraft；
Fig. 4 is the front view of the load plate expansion module unfolded state of spacecraft；
Fig. 5 is the three-dimensional structure diagram of hinge between passive plate；
Fig. 6 is the three-dimensional structure diagram of hinge between bar；
Fig. 7 is the three-dimensional structure diagram of hinge between Active plate.
Wherein, 01- load plate；11- strut I；12- strut II；13- strut III；14- strut IV；15- strut V；21- bar
Between hinge I；Hinge II between 22- bar；Hinge III between 23- bar；Hinge IV between 24- bar；Hinge V between 25- bar；It is cut with scissors between 31- Active plate
Chain I；Hinge II between 32- Active plate；Hinge III between 33- Active plate；Hinge I between 41- passive plate；Hinge II between 42- passive plate；
Hinge III between 43- passive plate；5: load board group；6: the first intermediate strut groups；7: the second intermediate strut groups；8: connecting rod group；9:
Articulated shaft；10: the first hinges；16: the second hinges；17: shell.
Specific embodiment
With reference to the accompanying drawings and examples, specific embodiments of the present invention will be described in further detail.Implement below
Example is not intended to limit the scope of the invention for illustrating the present invention.
Referring to Fig. 1 to Fig. 7, the load plate expansion module of the spacecraft of a preferred embodiment of the present invention, the present embodiment is used
Four pieces of plane load board group unfolding mechanisms of single-blade are illustrated, and referring to the attached drawing of the embodiment of the present invention, will hereafter be retouched in more detail
State the present invention.However, the present invention can realize in many different forms, and it should not be construed as the embodiment herein proposed
Limitation.On the contrary, proposing that these embodiments are and to keep those skilled in the art complete to reach sufficiently and complete disclosure
It is complete to understand the scope of the present invention.These attached drawings may be exaggerated the size and relative size in layer and region for clarity.
Referring to Fig.1 with expansion shown in Fig. 2 and rounding state, the present invention provides a kind of load plate expansion groups of spacecraft
After entering the orbit for realizing spacecraft, multiple tactic load plates are converted from the configuration for collapsing state to deployed condition for part.This reality
It applies in example, the unfolding mechanism of 8 pieces of load plates (01), by 16 strut I (11), 8 strut II (12), 4 strut III (13), 4
Hinge III between hinge II (22), 4 bars between hinge I (21), 2 bars between root strut IV (14), 4 strut V (15), 4 bars
(23), hinge between hinge I (31), 2 Active plates between hinge V (25), 4 Active plates between hinge IV (24), 4 bars between 8 bars
Hinge II (42), 1 between hinge I (41), 2 passive plates between hinge III (33), 4 passive plates between II (32), 1 Active plate
Hinge III (43) is formed between passive plate.
Basic principle of the invention is that concatenated four-bar mechanism expansion is locked as concatenated triangular structure.It is high to realize
The gathering expansion for storing ratio, hinge II between hinge V (25), Active plate between hinge III (23), bar between hinge I (21), bar between bar
(32), hinge III (43) is real using coaxial design between hinge II (42), passive plate between hinge III (33), passive plate between Active plate
Contracing for existing mechanism freedom, is arranged in load plate for strut I (11), strut II (12), strut IV (14), strut V (15)
(01) side.
Strut plays linkage and support function in unfolding mechanism.Strut I (11) totally 16, not according to placement position
Together, having 4 its both ends, hinge V (25) is connected between hinge I (21) and bar between bar respectively, have 2 its both ends respectively with it is active
Hinge II (32) is connected with hinge V (25) between bar between plate, has 2 its both ends respectively between passive plate between hinge II (42) and bar
Hinge V (25) is connected, and having 2 its both ends, hinge III (23) is connected between hinge II (32) and bar between Active plate respectively, has
Hinge III (23) is connected between hinge II (42) and bar between passive plate respectively at 2 its both ends, have 2 its both ends respectively with have
Hinge III (33) is connected with hinge III (23) between bar between source plate, there is 2 its both ends (43) hinge III between passive plate respectively
Hinge III (33) is connected between bar.Strut II (12) totally 8, according to the difference of placement position, have 4 its both ends respectively with
Hinge V (25) is connected with hinge IV (24) between bar between bar, has 4 its both ends to cut with scissors between hinge III (23) and bar between bar respectively
Chain IV (24) is connected.Strut III (13) totally 4, according to the difference of placement position, there are 2 its both ends respectively between two bars
Hinge III (23) is connected, and having 2 its both ends, hinge V (25) is connected between two bars respectively.Strut IV (14) totally 4,
Hinge IV (24) is connected between hinge III (23) and bar between bar respectively at both ends；Strut V (15) totally 4, both ends respectively with bar
Between hinge II (22) be connected with hinge IV (24) between bar；
Hinge plays the functions such as connection strut, auxiliary output torque, locking in unfolding mechanism between bar.Hinge I between bar
(21) totally 4, it is connected with load plate (01), strut I (11).Hinge II (22) totally 2 between bar, with spacecraft platform, strut V
(15) it is connected.Hinge III (23) totally 4 between bar are connected with two strut I (11), strut II (12), strut IV (14).
Hinge IV totally 8 between bar have 4 to be connected with strut IV (14) and strut V (15) according to the difference of placement position, have 4 with
Two strut II (12) are connected.Hinge V totally 4 between bar are connected with two strut I (11) and strut II (12).
Hinge plays the functions such as connection load plate, output driving torque, locking in unfolding mechanism between Active plate.Active plate
Between hinge I (31) totally 4, the load plate adjacent with two pieces (01) is connected.Hinge II (32) totally 2 between Active plate, with two pieces
Adjacent load plate (01), two strut I (11) are connected.Hinge III (33) totally 1 between Active plate, with spacecraft platform, two
The adjacent load plate of block (01), two strut I (11) are connected.
Hinge plays the functions such as connection load plate, auxiliary output driving torque, locking in unfolding mechanism between passive plate.Nothing
Hinge I (41) totally 4 between source plate, the load plate adjacent with two pieces (01) are connected.(42) hinge II between passive plate, with two pieces of phases
The load plate (01) of neighbour, two strut I (11) are connected.(43) hinge III between passive plate, with spacecraft platform, two pieces it is adjacent
Load plate (01), two strut I (11) are connected.
Wherein, the load plate of 8 pieces of connections forms load single-blade, and load single-blade includes four groups of successively hinged load board groups 5,
Load board group includes two pieces of hinged load plates, the strut I for being articulated with load board group left and right ends, the adjacent load of load single-blade
Hinge between at least one Active plate is provided between plate, one end of strut I is articulated with the end of load plate, the other end of strut I
It is hinged with another strut I of same group of load board group, intermediate strut is provided between the adjacent load board group of load single-blade
Group, and being located at most intermediate intermediate strut group is the first intermediate strut group 6, and other intermediate strut groups are the second intermediate strut group
7, the first intermediate strut group includes symmetrically arranged two groups of connecting rod groups 8, and every group of connecting rod group includes strut IV and strut V, support
One end of bar IV is articulated with the top of adjacent struts I, and the other end and strut V of strut IV is hinged, the other end of strut V with it is another
The strut V of group connecting rod group is hinged, and the second intermediate strut group includes two strut II, and wherein a strut II is articulated with phase
Another strut II of the top of adjacent strut I, another strut II and the second intermediate strut group is hinged.
Wherein, hinge refers to the hinge with driving motor between Active plate, and the hinge of hinge can be driven by driving motor
It separates or is closed, so that load plate connected to it be driven to be unfolded or be closed.
The total length of first intermediate strut group is long compared with the total length of the second intermediate strut group.And when load single-blade is unfolded,
First intermediate strut group and two adjacent strut I surround to form a diamond structure, the second intermediate strut group and adjacent two
Root strut surrounds to form an isosceles triangle.Structure is more firm after load single-blade is unfolded, while being also conducive to
It is collapsed.It is specific when collapsing, load single-blade gradually folding shrinking under the driving of hinge between Active plate, until load single-blade is complete
It is parallel to each other to collapse to each load plate.Its shared small volume at this time.
Further, the load plate expansion module of spacecraft of the invention is also set between the adjacent load plate of load single-blade
It is equipped with hinge between passive plate.
Hinge refers to the hinge without driving motor between passive plate, opens and closes under the driving of hinge between Active plate.One side
Face strengthens the connective stability between load plate, on the other hand also functions to the effect of auxiliary drive, the hinge difference of two sides
It is connected with adjacent load plate.
Further, the load plate expansion module of spacecraft of the invention is located at load board group left end, load board group right end
The number of strut I be two, and two strut I are set in parallel in the front and rear sides of load plate, correspondingly, per adjacent
The number of intermediate strut group between load board group is also two groups, and every group of load board group further includes one and its width direction
Parallel strut III, one end of strut III are cut with scissors with the strut I and adjacent strut II being located on front side of this group of load board group respectively
It connects, the other end and the strut I and adjacent strut II that are located on rear side of this group of load board group are hinged.
This design, so that entire strut group connection is more firm.Wherein, every group of load board group includes four strut I, wherein
Two are located at the left end of load board group, and another two are located at the right end of load board group.
Further, the load plate expansion module of spacecraft of the invention, hinge includes articulated shaft 9, respectively between Active plate
First hinge 10, second hinge 16 and the drive that drives first hinge or second hinge relative to articulated shaft rotate hinged with articulated shaft
Dynamic motor.
The setting of driving motor realizes the active drive to load plate.Specifically, the first hinge, the second hinge difference
It is connected with adjacent load plate, when gathering, driving motor drives the first hinge or the rotation of the second hinge, with the first hinge or second
The connected load plate of hinge just starts turning, and drives another load plate and conjunction connected to it by strut I, intermediate strut group
Page rotation, until entire load is generally collapsed and finished.On the contrary, the general expansion of load is opposite with the above process.
Further, the load plate expansion module of spacecraft of the invention, hinge includes shell 17 between Active plate, driving electricity
Machine is set in shell, and articulated shaft connect by bearing with shell, and the first hinge and shell are connected, driving motor pass through gear and
Hinged axis connection.
When specific works, the output shaft of driving motor drives first gear rotation connected to it, due on articulated shaft
It is installed with second gear and second gear is engaged with first gear, in this way, with the rotation of first gear, driving motor, shell
And rotated with the first hinge that driving motor is connected relative to articulated shaft, so that the load plate being connected with the first hinge be driven to rotate.
Further, the load plate expansion module of spacecraft of the invention, the both ends of load single-blade are cut with scissors between being additionally provided with bar
Chain I.
With reference to Fig. 3, the basic principle of the load plate expansion module of spacecraft is that concatenated four-bar mechanism expansion is locked as
Triangular structure, working principle are as follows.
The first step, hinge output driving torque between Active plate, hinge assists output driving torque between passive plate, pushes load
Plate expansion；
Second step, load plate expansion drive hinge movement between each strut and each bar, and hinge assists output driving power between each bar
Square；
Third step, after adjacent load plate expands in place, hinge locks respectively between hinge and passive plate between Active plate, is given to
Position signal；
4th step, hinge locks between bar, so that cutting with scissors between hinge, strut, bar between hinge, passive plate between load plate, Active plate
Chain forms rock-steady structure；
5th step, hinge stops output driving torque between Active plate.,
With reference to Fig. 4, hinge utilizes coaxial design implementation mechanism freedom degree between hinge, passive plate between hinge, Active plate between bar
Contract, strut is arranged in the side of load plate, realizes the gathering expansion of high storage ratio.
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, Er Qie
In the case where spirit or essential attributes of the invention, those skilled in the art can realize this in other specific forms
Invention.Therefore, in all respects, the present embodiments are to be considered as illustrative and not restrictive, the present invention
Protection scope be indicated by the appended claims rather than the foregoing description.
In addition, being not intended to restrict the invention the above is only the preferred embodiment of the present invention, it is noted that for this
For the those of ordinary skill of technical field, without departing from the technical principles of the invention, several improvement can also be made
And modification, these improvements and modifications also should be regarded as protection scope of the present invention.Although it will also be appreciated that this specification according to
Embodiment is described, and every embodiment includes only a single technical solution, this narration of specification
Mode is merely for the sake of clarity, and the skilled in the art should refer to the specification as a whole, the technology in each embodiment
Scheme may also be suitably combined to form that other embodiments which can be understood by those skilled in the art.
Claims (6)
1. a kind of load plate expansion module of spacecraft, it is characterised in that: including load single-blade, the load single-blade includes successively
Hinged at least four groups of load board groups, the load board group include two pieces of hinged load plates, are articulated with load board group or so two
The strut I at end is provided with hinge between at least one Active plate between the adjacent load plate of the load single-blade, the strut I's
One end is articulated with the end of load plate, and the other end of strut I and another strut I of same group of load board group are hinged, the load
Intermediate strut group is provided between the adjacent load board group of lotus single-blade, and being located at most intermediate intermediate strut group is in first
Between strut group, other intermediate strut groups be the second intermediate strut group, the first intermediate strut group includes symmetrically arranged two groups
Connecting rod group, every group of connecting rod group include strut IV and strut V, and one end of the strut IV is articulated with the top of adjacent struts I,
The other end of strut IV and strut V are hinged, and the other end of strut V and the strut V of another group of connecting rod group are hinged, in described second
Between strut group include two strut II, and wherein a strut II is articulated with the top of adjacent strut I, another strut II
It is hinged with another strut II of the second intermediate strut group.
2. the load plate expansion module of spacecraft according to claim 1, it is characterised in that: the load single-blade it is adjacent
Hinge between passive plate is additionally provided between load plate.
3. the load plate expansion module of spacecraft according to claim 1, it is characterised in that: be located at load board group left end,
The number of the strut I of load board group right end is two, and two strut I are set in parallel in the front and rear sides of load plate,
Correspondingly, the number of the intermediate strut group between every adjacent load board group is also two groups, and every group of load board group further includes one
The root strut III parallel with its width direction, one end of the strut III respectively with the strut that is located on front side of this group of load board group
I and adjacent strut II are hinged, and the other end and the strut I and adjacent strut II that are located on rear side of this group of load board group are hinged.
4. the load plate expansion module of spacecraft according to claim 1, it is characterised in that: hinge packet between the Active plate
It is opposite hinged to include articulated shaft, hinged with articulated shaft respectively the first hinge, the second hinge and the first hinge of driving or the second hinge
The driving motor of axis rotation.
5. the load plate expansion module of spacecraft according to claim 4, it is characterised in that: hinge packet between the Active plate
Shell is included, the driving motor is set in shell, and the articulated shaft is connect by bearing with shell, first hinge and shell
Body is connected, and the driving motor passes through gear and the hinged axis connection.
6. the load plate expansion module of spacecraft according to claim 1, it is characterised in that: the both ends of the load single-blade
It is additionally provided with hinge I between bar.
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| CN201811495675.2A CN109515753A (en) | 2018-12-07 | 2018-12-07 | A kind of load plate expansion module of spacecraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112298610A (en) * | 2020-09-30 | 2021-02-02 | 北京空间飞行器总体设计部 | Solar wing and sectional type secondary unfolding hinge thereof |
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