CN113734472B - Satellite battery plate unfolding device - Google Patents
Satellite battery plate unfolding device Download PDFInfo
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- CN113734472B CN113734472B CN202111303020.2A CN202111303020A CN113734472B CN 113734472 B CN113734472 B CN 113734472B CN 202111303020 A CN202111303020 A CN 202111303020A CN 113734472 B CN113734472 B CN 113734472B
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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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
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Abstract
The utility model belongs to the technical field of space satellite technique and specifically relates to a satellite battery board expandes device is related to, and satellite battery board expandes device includes: a first hinge mechanism, the first hinge mechanism comprising: a first main hinge; the first auxiliary hinge is hinged with the first main hinge through a first hinge shaft and is connected with the battery panel; the angle adjusting mechanism is arranged on the first articulated shaft; the angle adjusting mechanism comprises an angle limiting piece, the angle limiting piece is provided with a limiting sliding groove, and the first auxiliary hinge is provided with a convex part positioned in the limiting sliding groove; the limiting chute has a plurality of preset lengths. The satellite panel expandes device that this application embodiment provided can be before the satellite rises to the sky, to the expansion angle of adjusting the relative satellite of panel such as design demand under the circumstances of the star is adorned to the sun wing, only change the angle locating part can, need not carry out whole change for the sun wing hinge, avoid the dismouting repeatedly between sun wing hinge and the sun wing to accommodation range is wide enough.
Description
Technical Field
The application relates to the technical field of space satellites, in particular to a satellite battery panel unfolding device.
Background
At present, the unfolding angle of a solar panel is required to be adjusted according to actual conditions before satellite launching after the solar panel is mounted on a satellite, namely, the rotation angle between a main hinge and an auxiliary hinge (also called a male hinge and a female hinge) of a solar wing hinge is required to be adjusted before launching, but the existing solar wing hinge does not have the structure and the function of angle adjustment, and due to the requirements of the processing precision and the like of the solar wing hinge, once the angle between the main hinge and the auxiliary hinge is required to be adjusted, the whole solar wing hinge is required to be replaced, so that the time and the labor are wasted, raw materials are consumed, and the cost is wasted.
Disclosure of Invention
An object of the application is to provide a satellite battery board expandes device to solve the technical problem that needs the whole change of solar wing hinge when the adjustment solar cell panel's that exists among the prior art expansion angle to a certain extent.
The application provides a satellite battery board expandes device includes:
a first hinge mechanism, the first hinge mechanism comprising:
a first main hinge;
the first auxiliary hinge is hinged with the first main hinge through a first hinge shaft and is connected with the battery panel;
the angle adjusting mechanism is arranged on the first articulated shaft;
the angle adjusting mechanism comprises an angle limiting piece, the angle limiting piece is provided with a limiting sliding groove, and the first auxiliary hinge is provided with a convex part positioned in the limiting sliding groove;
the limit chute has a plurality of different predetermined lengths, and the length of the path of movement of the boss within the limit chute matches the angle of rotation of the first secondary hinge.
In the above technical solution, further, the angle adjusting mechanism further includes:
a fixed member provided at the first hinge shaft, the fixed member being connected with the first sub hinge;
the first clamping piece is arranged on the fixed component, and the convex part is a guide pillar arranged on the first clamping piece; the first clamping piece is sequentially provided with a plurality of clamping parts along the rotating direction of the first auxiliary hinge;
the second clamping piece is arranged on the fixing component and is clamped with at least one clamping part in the plurality of clamping parts;
the angle limiting part is arranged on the fixed component.
In any of the above technical solutions, further, the satellite panel unfolding apparatus further includes:
the connecting component is connected with the angle limiting part;
the connecting bent rod, the one end of connecting the bent rod with first main hinged joint, the other end of connecting the bent rod with connecting elements connects.
In any one of the above technical solutions, further, the fixing member is provided with an installation part, and the fixing member is formed with a winding groove;
the installation part is provided with a threading guide rod for penetrating a thread, and the thread is wound in the winding groove.
In any of the above technical solutions, further, the first main hinge includes:
a first fixed part;
the first hinge part is connected with the first hinge shaft through an adapter;
the adaptor comprises a fixed part and a rotating part which is rotatably connected with the fixed part, the rotating part is connected with the first hinge shaft, and the fixed part is connected with the first fixed part;
the first secondary hinge comprises:
the second fixing part is connected with the battery plate;
and the second hinge part is hinged to the first hinge shaft.
In any of the above technical solutions, further, the first fixing portion further includes a first stopping portion, the second fixing portion further includes a second stopping portion, the first stopping portion and the second stopping portion are disposed opposite to each other, and when the first auxiliary hinge rotates to a predetermined maximum angle relative to the first main hinge, the first stopping portion abuts against the second stopping portion.
In any one of the above technical solutions, further, the satellite battery panel unfolding apparatus further includes a first driving member, where the first driving member acts on the first hinge shaft to drive the first auxiliary hinge to rotate relative to the first main hinge.
In any of the above technical solutions, further, the first driving member is a spiral spring, one end of the spiral spring is connected to the first hinge shaft, and the other end of the spiral spring is connected to the first fixing portion.
In any of the above technical solutions, further, the satellite panel deployment apparatus further includes a second hinge mechanism, where the second hinge mechanism includes:
a second main hinge;
the second auxiliary hinge is hinged with the second main hinge through a second hinge shaft, the second auxiliary hinge is arranged in parallel with the first auxiliary hinge, and the second auxiliary hinge and the first auxiliary hinge are connected with the same side of the battery panel;
and the second driving component acts on the second hinge shaft to drive the second auxiliary hinge to rotate relative to the second main hinge, and the second auxiliary hinge and the first auxiliary hinge synchronously rotate.
In any of the above claims, further, at least one of the first hinge mechanism and the second hinge mechanism includes a reach-indicating device.
Compared with the prior art, the beneficial effect of this application is:
the application provides a satellite battery board expandes device includes: a first hinge mechanism, the first hinge mechanism comprising: a first main hinge; the first auxiliary hinge is hinged with the first main hinge through a first hinge shaft and is connected with the battery panel; the angle adjusting mechanism is arranged on the first articulated shaft; the angle adjusting mechanism comprises an angle limiting piece, the angle limiting piece is provided with a limiting sliding groove, and the first auxiliary hinge is provided with a convex part positioned in the limiting sliding groove; the limiting sliding groove is provided with a plurality of preset lengths, and the length of the path of the convex part moving in the limiting sliding groove corresponds to the rotating angle of the first clamping piece.
The satellite panel expandes device that this application embodiment provided can be before the satellite rises to the sky, to the expansion angle of adjusting the relative satellite of panel such as design demand under the circumstances of the star is adorned to the sun wing, only change the angle locating part can, need not carry out whole change for the sun wing hinge, avoid the dismouting repeatedly between sun wing hinge and the sun wing to accommodation range is wide enough.
Drawings
In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings needed to be used in the detailed description of the present application or the prior art description will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural diagram of a satellite panel unfolding apparatus according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of a first hinge mechanism of a satellite panel unfolding apparatus according to an embodiment of the present disclosure;
figure 3 is a schematic partial structural view of a first hinge mechanism of a satellite panel deployment device provided in an embodiment of the present application;
figure 4 is another schematic structural view of a portion of a first hinge mechanism of a satellite panel deployment device provided in an embodiment of the present application;
figure 5 is a further part of a schematic structural diagram of a first hinge mechanism of a satellite panel deployment device according to an embodiment of the present application;
figure 6 is a schematic structural diagram of a securing member of a first hinge mechanism of a satellite panel deployment device according to embodiments of the present application;
figure 7 is a schematic structural view of a second hinge mechanism of a satellite panel deployment device according to an embodiment of the present disclosure;
figure 8 is a schematic diagram of a portion of a second hinge mechanism of a satellite panel deployment apparatus according to an embodiment of the present disclosure;
figure 9 is a schematic view from the perspective of a first hinge mechanism of a satellite panel deployment apparatus provided in embodiments of the present application;
figure 10 is another perspective view schematic diagram of the first hinge mechanism of the satellite panel deployment apparatus provided in an embodiment of the present application.
Reference numerals: 100-a first hinge mechanism, 1-a first main hinge, 101-a first fixed part, 102-a first hinge part, 1021-a notch part, 103-an adaptor, 104-a first stop part, 2-a first sub hinge, 201-a second fixed part, 202-a second hinge part, 2021-an articulated arm, 203-a second stop part, 204-a snap ring, 3-a first hinge shaft, 301-a first end cap, 302-a second end cap, 4-a fixation means, 401-an installation part, 402-a threading guide bar, 403-a winding groove, 404-a wire roller, 405-a snap groove, 5-a first snap means, 501-a guide post, 6-a second snap means, 7-an angle limiting part, 701-a limiting slide groove, 8-a connection means, 9-connecting bent rod, 10-first driving member, 200-second hinge mechanism, 11-second main hinge, 1101-pressing boss, 12-second auxiliary hinge, 13-second hinge shaft, 14-second driving member, 15-driving device, 16-in-place indicating device, 1601-switch arm and 300-battery plate.
Detailed Description
The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments.
The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application.
All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
Satellite panel deployment apparatus according to some embodiments of the present application are described below with reference to figures 1 to 10.
Referring to fig. 1 to 10, an embodiment of the present application provides a satellite panel deployment apparatus including a first hinge mechanism 100 and a second hinge mechanism 200, the first hinge mechanism 100 and the second hinge mechanism being disposed side by side between a satellite and a panel 300 (solar panel) to enable the panel 300 to be deployed with respect to the satellite.
Specifically, the first hinge mechanism 100 includes a first main hinge 1, a first hinge shaft 3, a first auxiliary hinge 2, an angle adjustment mechanism, and a first driving member 10, wherein the first main hinge 1 is connected to the satellite as a fixed hinge, the first auxiliary hinge 2 is connected to the battery panel 300, the first main hinge 1 and the first auxiliary hinge 2 are hinged to each other through the first hinge shaft 3, so that when the first auxiliary hinge 2 rotates relative to the first main hinge 1, the battery panel 300 is unfolded relative to the satellite, the angle adjustment mechanism acts on the first auxiliary hinge 2 to define a rotation path and a rotation angle of the first auxiliary hinge 2 relative to the first main hinge 1, and the first driving member 10 acts on the first hinge shaft 3 to drive the first hinge shaft 3 and the first auxiliary hinge 2 to rotate.
Further, the first main hinge 1 includes a first fixing portion 101, the first fixing portion 101 includes a fixing splint, the fixing splint cooperates with a pin, a rivet or other type of fastener to connect with a designated position of the satellite, a side wall of the first fixing portion 101 facing away from the satellite is provided with a first hinge portion 102, the first hinge portion 102 is formed with a connecting hole, the connecting hole is provided with an adaptor 103, the hinge plate is connected with a first hinge shaft 3 through the adaptor 103, the adaptor 103 can be a bearing in particular, the adaptor 103 includes a fixing portion, a rotating portion and a rolling body arranged therebetween, the rotating portion can rotate relative to the fixing portion, the connecting hole of the first hinge portion 102 is connected with the fixing portion, the first hinge shaft 3 penetrates through the rotating portion and is connected with the rotating portion, so that the first hinge shaft 3 and the first sub hinge 2 can rotate with respect to the first main hinge 1 in a state where the first hinge part 102 is kept stationary.
The first hinge part 102 is shaped like a special plate and is provided with an arc-shaped gap 1021, so that the interference generated when the first auxiliary hinge 2 rotates is avoided, the weight of the whole first main hinge 1 can be reduced, and the groove part is formed on the plate surface of the first hinge part 102, which is also beneficial to reducing the weight of the first main hinge 1.
Further, the first auxiliary hinge 2 includes a second fixing portion 201, the second fixing portion 201 is specifically a fixing splint, and is fixed with the battery panel 300 by a fastener such as a rivet, a second hinge portion 202 is disposed on a side of the second fixing portion 201 away from the battery panel 300, the second hinge portion 202 includes two hinge arms 2021 facing each other and disposed at an interval, the two hinge arms 2021 are both hinged with the first hinge shaft 3, and the adaptor 103 and a portion between the first hinge portion 102 and the two hinge arms 2021 of the first hinge shaft 3 are connected to ensure the stability and the structural strength of the whole satellite battery panel unfolding apparatus.
Further, in the state shown in fig. 10, a first stopping portion 104 is disposed at the bottom of the first hinge portion 102, and a second stopping portion 203 is disposed at the bottom of the second hinge portion 202, that is, the two hinge arms 2021, in an initial state where the battery panel 300 is in a locked state with respect to the satellite, the first stopping portion 104 and the second stopping portion 203 are at a farthest distance, as the first auxiliary hinge 2 gradually rotates, the battery panel 300 gradually unfolds with respect to the satellite, the second stopping portion 203 gradually approaches the first stopping portion 104, and when the first auxiliary hinge 2 rotates to a predetermined maximum angle with respect to the first main hinge 1, the first stopping portion 104 and the second stopping portion 203 abut against each other, so that the first auxiliary hinge 2 stops at the current position and cannot further rotate.
Furthermore, one side of one of the hinge arms 2021 facing the below-described fixing member 4 is provided with a snap ring 204, and the snap ring 204 is formed with at least one snap projection, preferably, the number of the snap projections is two, and preferably, two snap projections are formed on the outer circumferential side of the snap ring 204 opposite to each other.
Further, the angle adjusting mechanism includes: angle locating part 7, fixed component 4, first joint spare 5 and second joint spare 6, fixed component 4 has casing or cell body structure, the outer sole wall face that fixed component 4 set up in the face of articulated arm 2021 of first vice hinge 2 is provided with joint groove 405, the shape of joint groove 405 and the shape adaptation of joint ring 204, and joint groove 405 is formed with the same draw-in groove portion of the protruding quantity of joint, make joint ring 204 can inlay and establish in joint groove 405, the joint arch of joint ring 204 is located the draw-in groove portion, and fixed component 4 is worn to locate by first articulated shaft 3, thereby make fixed component 4 and first vice hinge 2 can synchronous rotation.
First joint spare 5 sets up in the inside of fixed component 4, and first joint spare 5 specifically can be the ratchet, and first articulated shaft 3 is located to the cover, and the one end of first articulated shaft 3 is located fixed component 4, and the part of first articulated shaft 3 in the face of first joint spare 5 forms the arch, and the inner ring of first joint spare 5 is formed with the breach with the protruding mutual joint of first joint spare 5 for first joint spare 5 rotates along with first articulated shaft 3 and fixed component 4 are synchronous.
Second joint spare 6 sets up the internal face at the lateral wall of fixed component 4, second joint spare 6 specifically be with ratchet (first joint spare 5) mating reaction's pawl, the quantity of second joint spare 6 is preferred two, two second joint spare 6 with first joint spare 5 go up along the wherein two joints in a plurality of joint portions (specifically be the rigidity tooth of ratchet) that first joint spare 5 circumference was arranged in order for fixed component 4, first joint spare 5 can rotate in step with first articulated shaft 3.
The angle limiting part 7 is arranged in the fixing member 4 and faces the first clamping member 5, the angle limiting part 7 is fixed through a connecting member 8 which is described below, and the angle limiting part 7 is not connected with the first clamping member 5, namely the angle limiting part 7 does not rotate along with the first clamping member 5, the first hinge shaft 3 and the like. The angle limiting member 7 is formed with an arc-shaped limiting sliding groove 701, a side wall surface of the first clamping member 5 facing the angle limiting member 7 is provided with a guide post 501, the guide post 501 is located in the limiting sliding groove 701, the length of the limiting sliding groove 701 defines a rotation path of the guide post 501, i.e. the first clamping member 5, the angle limiting member 7 is detachably disposed in the fixing member 4, the limiting sliding grooves 701 of different angle limiting members 7 have different lengths, the limiting sliding grooves 701 of different lengths define the length of the rotation path of the first clamping member 5, i.e. the rotation angle of the first auxiliary hinge 2, the first auxiliary hinge 2 can be adjusted and rotated to a predetermined angle relative to the first main hinge 1, the adjustment range is 0-180 °, for example, the lengths of the limiting sliding grooves 701 are set as 30 °, 60 °, 90 °, 120 °, 180 °, and the like, preferably, in this embodiment, the maximum rotation angle of the first auxiliary hinge 2 relative to the first main hinge 1 is 180 °, when the unfolding angle of the battery panel 300 needs to be adjusted and changed before satellite launching, the angle limiting piece 7 with the limiting sliding groove 701 with the corresponding length is replaced.
Further, the outer wall surface of the side wall of the fixing member 4 is formed with a winding groove 403, the end of the winding groove 403 is provided with a plurality of mounting portions 401, each mounting portion 401 is provided with a threading guide 402, the threading guide 402 is formed with a threading channel for threading a thread, the thread may be a kelafv rope, on one hand, the threading guide 402 is used for threading the kelafv rope, so that the kelaf rope can be wound in the winding grooves 403 and on the other hand the direction of extension of the kelaf rope can be guided, preferably the number of winding grooves 403 is at least two, so that the kelaf rope can be wound at least once (or at least once) on the fixing member 4, when the first driving member 10 drives the first auxiliary hinge 2 to rotate relative to the first main hinge 1, the kelafv rope can play a role in assisting in rotation and unfolding, and the battery panel 300 is prevented from being too fast along with the unfolding speed of the first auxiliary hinge 2.
Further, a wire roller 404 for guiding the kelaf rope and guiding the extending direction of the kelaf rope so that the end of the kelaf rope can be connected to a designated position is provided at a position of the first fixing portion 101 close to the winding groove 403 of the fixing member 4.
Further, the satellite panel unfolding apparatus provided by the embodiment of the present application further includes a connecting member 8 and a connecting bent rod 9, the connecting member 8 is used for fixing the angle limiting member 7, the connecting member 8 has a flat plate structure, and the shape of the connecting member 8 is the same as that of the angle limiting member 7, the connecting member 8 is disposed facing the angle limiting member 7, and the connecting member 8 and the angle limiting member 7 can be detachably connected by a bolt or other fasteners passing through the connecting member 8 and the angle limiting member 7 to be in threaded connection, the number of the fasteners is plural to ensure the connection strength, and the number of the fasteners is preferably four. One end of the connecting bent rod 9 is connected to the connecting member 8, the other end of the connecting bent rod 9 is connected to the first fixing portion 101, the connecting bent rod 9 and the connecting member 8 are in a relatively fixed state along with the first main hinge 1, as shown in fig. 2 to 4, after the fastener is removed, the connecting member 8 is disconnected from the angle limiting member 7, the first auxiliary hinge 2 is rotated properly, the angle limiting member 7 is disconnected from the position facing the connecting member 8, at this time, the corresponding angle limiting member 7 is replaced, and then the connecting member 8 is replaced with the replaced angle limiting member 7 again.
First articulated shaft 3 wholly has the rod structure, the both ends of rod structure are provided with first end cap 301 and second end cap 302 respectively, angle locating part 7 has the loop configuration, central point puts and forms the fretwork, first end cap 301 is located the fretwork department of the central point of angle locating part 7, the diameter of fretwork is not less than the diameter of first end cap 301, first end cap 301 neither influences connecting member 8 and angle locating part 7 be connected, also can not disturb first end cap 301 also be first articulated shaft 3 relative angle regulating part pivoted smooth and easy nature, furthermore, the diameter of first end cap 301 is not less than the fenestrate diameter that first joint spare 5 is used for passing first articulated shaft 3, make first end cap 301 can establish first joint spare 5 card in fixed component 4, avoid first joint spare 5 to drop. The second end cap 302 is used to block the first drive member 10 from falling out.
Further, first drive component 10 sets up the one end that is close to second end cap 302 at first articulated shaft 3, first drive component 10 specifically is the spiral spring, the one end that first articulated shaft 3 is close to second end cap 302 is provided with the support column, the one end and the first articulated shaft 3 fixed connection of spiral spring, the support column can support the spiral spring, the other end and the first fixed part 101 of first main hinge 1 of spiral spring are connected, under first vice hinge 2 is in the initial condition that is close to each other with first main hinge 1, the spiral spring is in the state of relaxing, when rolling up gradually through the external force action pulling spiral spring, first articulated shaft 3 of spiral spring pulling begins to rotate, first vice hinge 2 slowly rotates relative to first main hinge 1, and then makes panel 300 slowly expand.
It should be noted that, in the present embodiment, two sets of hinge mechanisms are provided, namely, the first hinge mechanism 100 and the second hinge structure, wherein the second hinge mechanism 200 is used as a driving source of the first hinge mechanism 100, and the second hinge mechanism 200 drives the first driving member 10 to roll up gradually, and the structure of the geothermal hinge mechanism will be described below.
The second hinge mechanism 200 includes: the contents of the first main hinge 1, the first sub hinge 2, and the first hinge shaft 3 can be referred to for the structure of the second main hinge 11, the structure of the second sub hinge 12, the connection manner between the second main hinge 11 and the second sub hinge 12, the connection relationship between the second main hinge and the second sub hinge 13, the connection relationship between the battery panel 300, and the like, as well as the second main hinge 11, the second sub hinge 12, the second hinge shaft 13, the second driving member 14, and the position indicating device 16. The second driving member 14 is also a scroll spring, one end of the scroll spring is provided with a driving device 15 for driving the second driving member 14 to perform a retracting action, and one end of the second driving member 14 provided with the driving device 15 is connected with the second hinge shaft 13, when the driving device 15 is started by an external control device, the second driving member 14 starts to retract gradually, simultaneously pulls the second hinge shaft 13 to rotate gradually, and the second auxiliary hinge 12 rotates slowly relative to the second main hinge 11, wherein the control device may be an external control device before the satellite launches, or a control device of a satellite internal console, which is not emphasized in the embodiment of the present application. Since the second auxiliary hinge 12 and the first auxiliary hinge 2 are connected to the panel 300 at the same time, the first driving member 10 is also rolled up synchronously with the second driving member 14 while the second auxiliary hinge 12 drives the panel 300 to be unfolded slowly, so as to play a role of assisting the panel 300 to be unfolded, and also make the side force of the panel 300 more uniform.
Further, the in-place indicating device 16 is arranged on the second auxiliary hinge 12, the in-place indicating device 16 includes a micro-control switch, the second main hinge 11 is provided with a pressing boss 1101, a switch arm 1601 of the micro-control switch is arranged in the pressing boss 1101 in a penetrating manner, the pressing boss 1101 includes a fixing rod with an integrated structure and a fixing end arranged on the fixing rod, the fixing rod is fixedly connected with the second main hinge 11, the fixing end forms a slot, the switch arm 1601 is arranged in the slot in a penetrating manner, when the second auxiliary hinge 12 rotates in place relative to the first main hinge 1, the switch arm 1601 is pressed by the pressing boss 1101 to trigger an in-place signal, the battery panel 300 is shown to be unfolded in place, and at the moment, the driving device 15 of the second driving member 14 stops working.
Preferably, the fixed end and the dead lever become angle setting, perhaps fixed end is protruding relative to the dead lever, and the diameter of fixed end is greater than the diameter of dead lever for fixed end can guarantee intensity after seting up the slot, avoids fixed end relative to the dead lever to take place deformation and impaired.
It should be noted that, after the angle limiting members 7 of the limiting chutes 701 with different lengths are replaced, the length of the switch arm 1601 should be adaptively adjusted.
To sum up, the satellite cell panel that this application embodiment provided expandes the device can be before the satellite rises to the sky, to the expansion angle of adjusting the relative satellite of cell panel such as design demand under the circumstances of the star is adorned to the sun wing, only change the angle locating part can, need not carry out whole change for the sun wing hinge, avoid relapseing the dismouting between sun wing hinge and the sun wing to accommodation is wide enough.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application.
Claims (8)
1. A satellite panel deployment apparatus, comprising: a first hinge mechanism, the first hinge mechanism comprising:
a first main hinge;
the first auxiliary hinge is hinged with the first main hinge through a first hinge shaft and is connected with the battery panel;
the angle adjusting mechanism is arranged on the first articulated shaft;
the angle adjusting mechanism comprises an angle limiting piece, the angle limiting piece is provided with a limiting sliding groove, and the first auxiliary hinge is provided with a convex part positioned in the limiting sliding groove;
the limiting sliding groove is provided with a plurality of different preset lengths, and the length of a path of the convex part moving in the limiting sliding groove is matched with the rotating angle of the first auxiliary hinge;
the angle adjustment mechanism further includes:
a fixing member having a housing or a groove structure, the first hinge shaft being inserted through the fixing member, the fixing member being connected with the first sub hinge, and the fixing member and the first sub hinge rotating in synchronization; the fixing component is provided with an installation part and is provided with a winding groove; the installation part is provided with a threading guide rod for threading a thread, and the thread is wound in the winding groove;
the first clamping piece is arranged inside the fixed component, and the convex part is a guide pillar arranged on the first clamping piece; the first clamping piece is sequentially provided with a plurality of clamping parts along the rotating direction of the first auxiliary hinge;
the second clamping piece is arranged on the inner wall surface of the side wall of the fixing component and is clamped with at least one clamping part in the plurality of clamping parts;
the angle limiting part is arranged inside the fixed component and faces the first clamping part.
2. The satellite panel deployment apparatus of claim 1, further comprising:
the connecting component is connected with the angle limiting part;
the connecting bent rod, the one end of connecting the bent rod with first main hinged joint, the other end of connecting the bent rod with connecting elements connects.
3. The satellite panel deployment apparatus of claim 1, wherein the first main hinge comprises:
a first fixed part;
the first hinge part is connected with the first hinge shaft through an adapter;
the adaptor comprises a fixed part and a rotating part which is rotatably connected with the fixed part, the rotating part is connected with the first hinge shaft, and the fixed part is connected with the first fixed part;
the first secondary hinge comprises:
the second fixing part is connected with the battery plate;
and the second hinge part is hinged to the first hinge shaft.
4. The satellite panel deployment device of claim 3, wherein the first securing portion further includes a first stop portion, the second securing portion further includes a second stop portion, the first stop portion and the second stop portion are disposed opposite to each other, and the first stop portion abuts the second stop portion when the first secondary hinge rotates to a predetermined maximum angle relative to the first primary hinge.
5. The satellite panel deployment device according to claim 3, further comprising a first drive member acting on the first hinge to drive the first hinge to rotate the first secondary hinge relative to the first primary hinge.
6. Satellite panel deployment device according to claim 5, wherein the first driving member is a spiral spring, one end of which is connected to the first hinge shaft and the other end of which is connected to the first fixing portion.
7. The satellite panel deployment apparatus of any one of claims 1 to 6, further comprising a second hinge mechanism, the second hinge mechanism comprising:
a second main hinge;
the second auxiliary hinge is hinged with the second main hinge through a second hinge shaft, the second auxiliary hinge is arranged in parallel with the first auxiliary hinge, and the second auxiliary hinge and the first auxiliary hinge are connected with the same side of the battery panel;
the second driving component acts on the second hinge shaft to drive the second auxiliary hinge to rotate relative to the second main hinge;
the second pair of hinges rotates synchronously with the first pair of hinges.
8. The satellite panel deployment device of claim 7, wherein at least one of the first hinge mechanism and the second hinge mechanism comprises a position indicating device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111303020.2A CN113734472B (en) | 2021-11-05 | 2021-11-05 | Satellite battery plate unfolding device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111303020.2A CN113734472B (en) | 2021-11-05 | 2021-11-05 | Satellite battery plate unfolding device |
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| Publication Number | Publication Date |
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| CN113734472A CN113734472A (en) | 2021-12-03 |
| CN113734472B true CN113734472B (en) | 2022-02-11 |
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| CN202111303020.2A Active CN113734472B (en) | 2021-11-05 | 2021-11-05 | Satellite battery plate unfolding device |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN204355286U (en) * | 2014-10-31 | 2015-05-27 | 北京空间飞行器总体设计部 | One is inserted into locking type solar wing hinge |
| CN105387064A (en) * | 2015-11-09 | 2016-03-09 | 北京空间飞行器总体设计部 | Unfolding hinge for quick connection and separation |
| CN212501117U (en) * | 2020-04-26 | 2021-02-09 | 长沙天仪空间科技研究院有限公司 | Synthetic aperture radar satellite with multi-angle solar wing |
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| CN201172484Y (en) * | 2008-01-31 | 2008-12-31 | 航天东方红卫星有限公司 | Satellite bias solar panel adapting for local times of different southbound nodes |
| KR101291593B1 (en) * | 2011-09-09 | 2013-08-01 | 한국항공우주연구원 | Solar panel unfolding apparatus for a satellite |
| CN103953639A (en) * | 2014-05-12 | 2014-07-30 | 北京空间飞行器总体设计部 | Repeatable expansion hinge for unfolding mechanism of spacecraft |
| CN204355286U (en) * | 2014-10-31 | 2015-05-27 | 北京空间飞行器总体设计部 | One is inserted into locking type solar wing hinge |
| CN105387064A (en) * | 2015-11-09 | 2016-03-09 | 北京空间飞行器总体设计部 | Unfolding hinge for quick connection and separation |
| CN212501117U (en) * | 2020-04-26 | 2021-02-09 | 长沙天仪空间科技研究院有限公司 | Synthetic aperture radar satellite with multi-angle solar wing |
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| CN113734472A (en) | 2021-12-03 |
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