CN212501117U - Synthetic aperture radar satellite with multi-angle solar wing - Google Patents
Synthetic aperture radar satellite with multi-angle solar wing Download PDFInfo
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- CN212501117U CN212501117U CN202020652365.3U CN202020652365U CN212501117U CN 212501117 U CN212501117 U CN 212501117U CN 202020652365 U CN202020652365 U CN 202020652365U CN 212501117 U CN212501117 U CN 212501117U
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Abstract
The utility model relates to a synthetic aperture radar satellite with multi-angle sun wing, at least including star (300) and the sun wing of synthetic aperture radar satellite, the sun wing includes main sun wing (400), first pair sun wing (500) and the vice sun wing of second (600), first pair sun wing (500) and/or the vice sun wing of second (600) with main sun wing (400) are connected through first angle adjustment mechanism (100) that can be at first degree of freedom and second degree of freedom angle of regulation, main sun wing (400) with star (300) are connected through second angle adjustment mechanism (200) that can be at second degree of freedom angle of regulation. The utility model discloses a composite mounting of a plurality of solar wings and the application of the angle adjustment mechanism of different characteristics for the solar wings can shorten the distance of whole barycenter and celestial body through changing the structure, reduces the vibration influence of celestial body operation to solar wing panel.
Description
Technical Field
The utility model relates to an aerospace technical field especially relates to a synthetic aperture radar satellite with multi-angle sun wing.
Background
With the rapid development of aerospace technology, light weight and integration gradually become the development trend of satellite loading technology. At present, the traditional satellite sun-facing directional driving mechanism and the solar wing body are independently designed and installed, so that the interface between the solar wing and the driving mechanism is complex, the weight is large, the light and small size are not facilitated, and the solar wing is often unfolded by adopting a passive mechanism, so that the unfolding reliability is poor. In the aspect of video monitoring technology, it has become a development trend to install video monitoring equipment on satellites, cameras are installed on space mechanical arms in foreign countries such as canada, japan and europe to realize inspection tour of space station cabins, and video monitoring equipment is gradually installed on rockets and satellites in China and shows a trend of miniaturization. The microminiature video monitoring equipment arranged on the satellite can be applied to daily monitoring and test observation of the satellite, and can also be used for fault diagnosis and non-cooperative satellite investigation of the satellite. The monitoring cameras are mostly directly installed on the surface of the satellite, cannot move, and only can carry out video monitoring on the condition within a certain range, and if multi-point monitoring is to be realized, a plurality of monitoring cameras must be installed. The solar wing is a load which almost all satellites must have, and the solar wing which can realize active unfolding and multi-angle rotation is designed, so that the solar wing has great significance for realizing light and small size and function integration for pushing the satellite load, reducing the launching cost and improving the satellite performance.
Chinese patent CN 106945848B discloses a sun wing spreading linkage, comprising: the device comprises a fixed wheel, a movable wheel, a fixed wheel linkage rope, a movable wheel linkage rope, a fixed wheel guide wheel, a movable wheel guide wheel and a limiting column; the fixed wheel includes: the rotating shaft and the fixed wheel arc groove; the driving wheel includes: the rotating shaft of the driving wheel, the circular arc groove of the driving wheel and the cavity are arranged on the driving wheel; the fixed wheel is fixedly arranged on a root hinge of the solar wing; the rotating shaft is coaxial with the root hinge rotating shaft of the root hinge; the driving wheel is connected with the fixed wheel through a driving wheel rotating shaft; one end of the fixed wheel linkage rope is connected to the fixed wheel, and the other end of the fixed wheel linkage rope is connected to the inter-plate hinge linkage wheel after changing the direction through the fixed wheel guide wheel; one end of the driving wheel linkage rope is wound in the driving wheel arc groove and fixed at the tail end of the driving wheel arc groove, and the other end of the driving wheel linkage rope is connected to the inter-plate hinge linkage wheel of the solar wing after the direction is changed through the driving wheel guide wheel. Although the solar wing unfolding linkage device realizes the constraint on the solar wing unfolding track, the disturbance and the unfolding locking impact of the solar wing unfolding process on the spacecraft posture are reduced. However, the solar wing can be unfolded in one direction only, and the angle cannot be changed, so that the solar wing is not beneficial to a satellite, particularly a small satellite such as a meteorological satellite, and is easy to shake, and the accuracy of observation of the satellite can be interfered when the solar wing is transferred to the satellite by shaking.
Furthermore, on the one hand, due to the differences in understanding to the person skilled in the art; on the other hand, since the inventor studied a lot of documents and patents when making the present invention, but the space did not list all details and contents in detail, however, this is by no means the present invention does not possess these prior art features, but on the contrary the present invention has possessed all features of the prior art, and the applicant reserves the right to increase the related prior art in the background art.
SUMMERY OF THE UTILITY MODEL
To the deficiency of the prior art, the utility model provides a synthetic aperture radar satellite with multi-angle sun wing includes synthetic aperture radar satellite's celestial body and sun wing at least, a serial communication port, the sun wing includes main sun wing, first pair sun wing and the vice sun wing of second, first pair sun wing and/or the vice sun wing of second with main sun wing is connected through the first angle adjustment mechanism that can be at first degree of freedom and second degree of freedom angle regulation, main sun wing with the celestial body is connected through the second angle adjustment mechanism that can be at second degree of freedom angle regulation.
Preferably, in the sun wing spread state, the first sub-sun wing and the second sub-sun wing are respectively disposed at both sides of the main sun wing in a symmetrical manner,
in a folded state of the sun wings, the first auxiliary sun wing and the second auxiliary sun wing rotate in the opposite directions of the second degree of freedom through the first angle adjusting mechanism and are respectively folded on two different side surfaces of the main sun wing.
Preferably, in the sun wing open state, the first and second secondary sun wings are disposed on the same side of the main sun wing, wherein,
the first auxiliary sun wing is arranged between the main sun wing and the second auxiliary sun wing, the first auxiliary sun wing and the second auxiliary sun wing are connected through a first angle adjusting mechanism,
in a folded state of the solar wings, the first pair of solar wings and the second pair of solar wings are opposite in rotation direction of the second degree of freedom, and the first pair of solar wings and the second pair of solar wings are folded on the same side of the main solar wing and are positioned between the main solar wing and the second pair of solar wings.
Preferably, the first sub-sun wing and the second sub-sun wing are respectively rotated in a second degree of freedom perpendicular to the plane of the main sun wing based on the first angle adjustment mechanism.
Preferably, the two first angle adjusting mechanisms on both sides of the main solar wing are symmetrical with the center of the main solar wing as the center and are not symmetrical with the central axis,
in a state that the solar wings are folded, the first auxiliary solar wing and the second auxiliary solar wing are folded and folded on the same side face of the main solar wing opposite to the star body in a non-overlapping mode,
the main solar wing rotates towards the star body and is attached to the side wall of the star body, and at the moment, the first auxiliary solar wing and the second auxiliary solar wing are respectively located between the main solar wing and the star body.
Preferably, the first angle adjusting mechanism at least comprises a first connecting seat and a second connecting seat for fixing on the solar wing, and a first joint mechanism and a second joint mechanism are arranged between the first connecting seat and the second connecting seat, wherein,
the first connecting seat is connected with the first joint mechanism, the first joint mechanism is connected with the second joint mechanism, and the second joint mechanism is connected with the second connecting seat.
Preferably, the first joint mechanism comprises a first connecting shaft, a first driving motor, a first motor flange and a connecting piece,
the first connecting shaft is arranged between the first connecting seat and the connecting piece,
an output shaft of the first driving motor penetrates through the first connecting shaft through a bearing, so that the first connecting shaft rotates around a first rotating shaft line of the first driving motor, and a shell of the first driving motor is connected with the first joint shell through the first motor flange.
Preferably, the second joint mechanism comprises a fixed flange, a second motor flange and a second driving motor,
the connecting piece is connected with the fixed flange, the fixed flange is connected with an output shaft of the second driving motor through a second motor flange, so that the first joint mechanism rotates around a second rotating axis of the second driving motor, and a first rotating axis of the first joint mechanism is perpendicular to the second rotating axis.
Preferably, the second angle adjusting mechanism at least comprises a moving mechanism arranged in the outer wall of the star body, a bearing seat and a rotating shaft, one end of the rotating shaft is provided with a first gear, the rotating shaft penetrates through the bearing seat through a bearing, the bearing seat is arranged in an installation frame welded on the inner wall of the star body, the other end of the rotating shaft is connected with the main sun wing, wherein,
the moving mechanism is internally provided with a rack, the outer wall of the moving mechanism is provided with a slide rail, a lower slide block in the slide rail is welded with the rack, the middle part of the outer wall of the moving mechanism is provided with a through hole, and a first gear is meshed with the rack through the through hole.
Preferably, the second angle adjusting mechanism further comprises an upper slide rail embedded into the upper slide block, the lower portion of the upper slide block is connected with the rack, the second angle adjusting mechanism further comprises an upper bracket and a lower bracket, the upper bracket is provided with a first reel, the lower bracket is provided with a second reel, the first reel and the second reel are connected through a pull wire connected with a moving block, and the moving block is connected with the rack.
The utility model has the advantages of:
the utility model discloses a composite mounting of a plurality of solar wings and the application of the angle adjustment mechanism of different characteristics for the solar wings can shorten the distance of whole barycenter and celestial body through changing the structure, reduces the vibration influence of celestial body operation to solar wing panel. In particular, the adjustment of the angle of at least one of the secondary solar wing panels also allows to adjust the variation of the centre of mass of the solar wing as a whole, so that it is realistic to select a better angle of the solar wing as an optimal solution between the solar energy acquisition and the shortening of the distance between the centre of mass and the star.
Drawings
FIG. 1 is a schematic view of the overall structure of a solar wing;
FIG. 2 is a schematic view of the angular variation of the sun wing;
FIG. 3 is a schematic view of a first angle adjustment mechanism;
FIG. 4 is a schematic perspective view of the first angle adjustment mechanism; and
fig. 5 is a schematic structural view of the second angle adjustment mechanism.
List of reference numerals
100: a first angle adjustment mechanism; 200: a second angle adjustment mechanism; 300: a star body; 400: a main solar wing; 500: a first pair of solar wings; 600: a second subsidiary solar wing; 101: a first connecting seat; 102: a second connecting seat; 103: a first connecting shaft; 104: a first drive motor; 105: a first axis of rotation; 106: a first joint housing; 107: a first motor flange; 108: a connecting member; 109: a fixed flange; 110: a second motor flange; 111: a second axis of rotation; 112: a second drive motor; 201: an outer wall; 202: a moving mechanism; 203: a first electric reel; 204: a lower bracket; 205: a second electric reel; 206: a pull wire; 207: moving block, 208: a long rack; 209: upper slide rail, 210: upper slider, 211: lower slide rail, 212: lower slider, 213: through-hole, 214: mounting frame, 215: bearing seat, 216: shaft, 218: first gear, 219: slider, 291: mounting block, 292: groove, 220: guide holder, 221: arc slide rail, 222: arc rack, 223: third drive motor, 224: second gear, 266: and (4) an upper bracket.
Detailed Description
The following detailed description is made with reference to fig. 1 to 5 of the drawings.
A synthetic aperture radar satellite having a multi-angle sun wing, comprising at least a satellite body 300 of the synthetic aperture radar satellite and a sun wing, as shown in fig. 1.
As shown in fig. 1 to 2, the sun wings include a main sun wing 400, a first sub-sun wing 500, and a second sub-sun wing 600. The first sub-sun wing 500 and/or the second sub-sun wing 600 are connected to the main sun wing 400 via a first angle adjustment mechanism 100 capable of adjusting an angle in a first degree of freedom and a second degree of freedom. The main sun wing 400 and the star 300 are connected by a second angle adjusting mechanism 200 capable of adjusting an angle in a second degree of freedom. The utility model discloses well first angle adjustment mechanism and second angle adjustment mechanism and the fixed of sun wing can be the bolt fastening, also can be the welding, can also be the bolt and weld and use simultaneously. Preferably, the center of mass of the solar wing overall structure is the center point of a triangle formed by the three center of mass of the three solar wings. By changing the positions of the first sub-sun wing 500 and the second sub-sun wing 600, the center of mass of the whole structure of the sun wing is changed. The distance between the center of mass of the whole structure of the solar wing and the star body is changed. The shorter the distance between the mass center of the whole structure of the solar wing and the star body is, the less the solar wing is influenced by the load vibration in the star body.
Preferably, the first and second sub-sun wings 500 and 600 are symmetrically disposed on both sides of the main sun wing 400 in the sun wing spread state. In the sun wing closed state, the first sub sun wing 500 and the second sub sun wing 600 are rotated in the opposite direction to each other in the second degree of freedom by the first angle adjusting mechanism 100 and are folded on two different sides of the main sun wing 400, respectively. The advantage that so set up lies in, the structure of symmetry can make solar wing overall structure more stable, and the barycenter is better to be adjusted, and the angular variation of vice solar wing can change the volume of receiving solar energy, also provides more detection angle for a plurality of detectors that carry on the solar wing.
Preferably, in the sun wing open state, the first sub-sun wing 500 and the second sub-sun wing 600 are disposed on the same side of the main sun wing 400. The first sub-sun wing 500 is disposed between the main sun wing 400 and the second sub-sun wing 600, and the first sub-sun wing 500 and the second sub-sun wing 600 are connected by the first angle adjustment mechanism 100. In the sun wing closed state, the rotation directions of the first sub-sun wing 500 and the second sub-sun wing 600 in the second degree of freedom are opposite, the first sub-sun wing 500 and the second sub-sun wing 600 are folded on the same side of the main sun wing 400, and the first sub-sun wing 500 is located between the main sun wing 400 and the second sub-sun wing 600. The advantage of so setting up lies in, can be when main sun wing draws in, vice sun wing does not draw in and cladding star, provides help for keeping out the cold and keeping apart cold of star. The auxiliary solar wing farthest from the main solar wing is minimally affected by the vibration of the satellite main body, and is beneficial to carrying a detector needing to avoid the vibration. Preferably, the first sub-sun wing 500 and the second sub-sun wing 600 can rotate arbitrarily in both directions of the first degree of freedom.
Preferably, the first sub-sun wing 500 and the second sub-sun wing 600 are rotated in the second degree of freedom perpendicular to the plane of the main sun wing 400 based on the first angle adjustment mechanism 100, respectively. Therefore, the angle of the auxiliary solar wing can be flexibly changed at two degrees of freedom, and more directions can be obtained.
Preferably, the two first angle adjusting mechanisms 100 on both sides of the main solar wing 400 are symmetrical about the center of the main solar wing 400 and are not symmetrical about the central axis, and in the folded state of the solar wings, the first sub solar wing 500 and the second sub solar wing 600 are folded and folded on the same side of the main solar wing 400 opposite to the star body 300 in a non-overlapping manner. The main sun wing 400 rotates toward the star body 300 and is attached to the side wall of the star body 300, and at this time, the first sub sun wing 500 and the second sub sun wing 600 are respectively positioned between the main sun wing 400 and the star body 300. The arrangement has the advantages that the thickness of the sun wing during folding can be reduced, and the attachment of the main sun wing to the star body is facilitated.
The first angle adjusting mechanism has two degrees of freedom and can also be arranged between the main solar wing and the star body, so that the main solar wing and the auxiliary solar wing have more angles. The utility model discloses still select second angle adjustment mechanism to set up the advantage between main solar wing and the celestial body to lie in, main solar wing single degree of freedom and vice solar wing two degrees of freedom's cooperation is used and has been satisfied the demand that the solar wing angle changes and the regulation of solar wing barycenter and change, also is favorable to reducing the operation of data. Meanwhile, the adjustment of single degree of freedom is more beneficial to the stability of the main solar wing, and the defects of instability and aggravation of vibration caused by the adjustment of multiple degrees of freedom are avoided. For the angle adjustment of the auxiliary solar wing, the volume of the auxiliary solar wing is not larger than that of the main solar wing under the normal condition (except special requirements). The vibration of the angle change is slight and can be ignored.
Preferably, as shown in fig. 3, the first angle adjusting mechanism includes at least a first connecting seat 101 and a second connecting seat 102 for fixing to the solar wing. The first joint mechanism and the second joint mechanism are disposed between the first link base 101 and the second link base 102. The first connecting seat 101 is connected to a first joint mechanism, the first joint mechanism is connected to a second joint mechanism, and the second joint mechanism is connected to the second connecting seat 102.
The first joint mechanism includes a first connecting shaft 103, a first drive motor 104, a first motor flange 107, and a connecting member 108. The first connecting shaft 103 is between the first connecting seat 101 and the connecting member 108. An output shaft of the first drive motor 104 penetrates the first connecting shaft 103 via a bearing so that the first connecting shaft 103 rotates about a first axis of rotation 105 of the first drive motor 104, and a first motor flange 107 connects the housing of the first drive motor 104 to a first joint housing 106. Only the outer structure is shown in fig. 2, as the view is limited, of which the output shaft structure is not shown.
The second joint mechanism includes a fixing flange 109, a second motor flange 110, and a second drive motor 112. The connecting member 108 is connected to a fixed flange 109, and the fixed flange 109 is connected to an output shaft of a second driving motor 112 via a second motor flange 110. So that the first joint mechanism rotates about the second rotation axis 111 of the second drive motor 112. The first axis of rotation 105 of the first joint mechanism is perpendicular to the second axis of rotation 111.
The connection between each part in the first angle adjusting mechanism is bolted connection, and is fixed as bolted fixation or welding. The skilled person can select the connection mode based on the needs and does not need to specify it.
The first angle adjusting mechanism has the advantages that the light and small load is effectively realized, the function integration level is improved, and the unfolding reliability is high. Through the application of the first angle adjusting mechanism, the adjustment of the center of mass of the integral structure of the solar wing is realized by adjusting the angle and the position of the auxiliary solar wing.
As shown in fig. 4 and 5, the second angle adjusting mechanism 200 at least includes a moving mechanism 202 disposed in the outer wall 201 of the star, a bearing seat 215, and a rotating shaft 216 having a first gear 218 disposed at one end. The rotating shaft penetrates through a bearing seat 215 through a bearing, the bearing seat 215 is arranged in an installation frame 214 welded on the inner wall of the star body, and the other end of the rotating shaft is connected with the main solar wing. Wherein, a rack 208 is arranged in the moving mechanism 202. The outer wall 201 is provided with a slide rail 211, and a lower slider 212 in the slide rail 211 is welded with the rack 208. The outer wall 201 is provided with a through hole 213 in the middle. The first gear 218 is engaged with the rack 208 through the through hole 213.
The second angle adjustment mechanism 200 further includes an upper rail 209 embedded in the upper slider 210, and a lower portion of the upper slider 210 is connected to the rack 208. The second angle adjustment mechanism 200 also includes an upper bracket 266 and a lower bracket 204. The upper bracket 266 is provided with a first reel 203, the lower bracket 204 is provided with a second reel 205, and the first reel 203 and the second reel 205 are connected by a pull line 206 connected with a moving block 207. The moving block 207 is connected to a rack 208.
From the perspective of fig. 4 and 5, the second angle adjusting mechanism 200 further includes a slider 219, a mounting block 291, a guide holder 220, an arc-shaped slide rail 221, an arc-shaped rack 222, a third driving motor 223, and a second gear 224. The main solar wing 400 is provided with a mounting block 291. The mounting block 191 is provided with a slider 219. The main sun wing 400 is provided with a groove 292, and the groove 292 is positioned at the right of the sliding block 219. The inner wall of the star body is also provided with a guide seat 220. An arc-shaped sliding rail 221 is slidably arranged in the guide seat 220. The upper part of the arc-shaped sliding rail 221 is matched with the sliding block 219, the upper end of the arc-shaped sliding rail 221 is positioned in the groove 292, and the inner side of the arc-shaped sliding rail 221 is provided with an arc-shaped rack 222. The inner side of the star is provided with a third drive motor 223. An output shaft of the third driving motor 223 penetrates through the outer wall of the star body, a second gear 224 is connected to the output shaft of the third driving motor 223, and the second gear 224 is meshed with the arc-shaped rack 222.
The connection between each part in the first angle adjusting mechanism is bolted connection, and is fixed as bolted fixation or welding. The skilled person can select the connection mode based on the needs and does not need to specify it.
The utility model provides an each driving motor passes through the wire and is connected with the power of main solar wing or vice solar wing, and this power is formed by the solar energy conversion that the solar wing received, for the mature technique, does not give unnecessary details here. Or, each driving motor is directly connected to a wire of the solar wing for transmitting electric energy, which is a connection that can be performed by a person skilled in the art as needed and is not described herein. The utility model provides a connection of each driving motor's signal line, the corresponding device of field technical personnel in demand connection in the satellite, no longer describe here.
Preferably, the utility model provides a driving motor can be accord with any type of driving motor of national aerospace technical standard, for example one or several kinds in miniature hybrid step motor, the permanent magnetism synchronous electric drive motor and the alternating current asynchronous electric drive motor that the satellite was used, has simple structure, advantage that occupation space is little.
The utility model discloses a theory of operation:
when a signal instruction is received and the moving mechanism 202 is required to move upwards, the first electric reel 203 and the second electric reel 205 start to operate, the first electric reel 203 and the second electric reel 205 rotate anticlockwise, the pull wire 206 rotates anticlockwise, the moving block 207 drives the long rack 208 to move upwards, when the signal instruction is received and the moving mechanism 202 needs to move downwards, the first electric reel 203 and the second electric reel 205 start to operate, the first electric reel 203 and the second electric reel 205 rotate clockwise, the pull wire 206 rotates clockwise, the moving block 207 drives the long rack 208 to move downwards, the long rack 208 can move up and down, and when the moving is not required, the first electric reel 203 and the second electric reel 205 stop operating.
Before a signal is received and the main solar wing 400 needs to be unfolded, the third driving motor 223 starts to operate, the third driving motor 223 drives the second gear 224 to rotate clockwise, so that the arc-shaped rack 222 drives the upper part of the arc-shaped slide rail 221 to rotate out together, the arc-shaped slide rail 221 slides through the sliding block 219 and passes through the groove 292, after the arc-shaped rack 222 rotates out for a proper distance, the third driving motor 223 stops operating, the arc-shaped rack 222 and the arc-shaped slide rail 221 keep the rotating-out state, at this time, the main solar wing 400 starts to be unfolded and rotates, and the sliding block 219 moves on the arc-shaped slide rail 221, so that the guiding and supporting effects are achieved. After the main solar wing 400 is reset, the third driving motor 223 starts to work again, the third driving motor 223 drives the second gear 224 to rotate anticlockwise, so that the arc-shaped rack 222 drives the upper portion of the arc-shaped sliding rail 221 to rotate back together, the guide seat 220 plays a role in guiding and supporting the moving arc-shaped rack 222 and the moving arc-shaped sliding rail 221, after the arc-shaped rack 222 and the arc-shaped sliding rail 221 are reset, the third driving motor 223 stops working, the shape of the mounting block 291 is matched with the right side of the upper portion of the outer wall of the star body, and when the main solar wing 400 retracts to a vertical angle, the mounting block 291 is just clamped on the right side of the upper portion of the outer wall of the star.
When the main solar wing 400 reaches a designated angle, the electric push rod 225 is started to shorten, the fixture block 226 and the friction pad 227 are driven to move inwards, the friction pad 227 presses the arc-shaped rack 222 and the arc-shaped slide rail 221, and then the electric push rod 225 is closed, so that the sliding between the slide block 219 and the arc-shaped slide rail 221 is prevented, when the sliding between the slide block 219 and the arc-shaped slide rail 221 needs to move, the electric push rod 225 is started to extend, the fixture block 226 and the friction pad 227 are driven to move outwards, the friction pad 227 does not press the arc-shaped rack 222 and the arc-shaped slide rail 221 any more, then the electric push rod 225 is closed, and at this time, the slide.
When the main sun wing is unfolded to a set angle or completely unfolded, the first and second sub-sun wings 500 and 600 start to be unfolded. I.e. the first angle adjustment mechanism starts to work. The first driving motor and the second driving motor of the first driving motor 200 start to rotate, and the angle of the auxiliary sun wing is adjusted until the required angle position is reached. For example, the first and second sub-sun wings are identical and distributed on either side of the main sun wing. The first auxiliary solar wing and the second auxiliary solar wing rotate towards each other and form an included angle of 60 degrees with the main solar wing, and at the moment, the three centroids form a regular triangle. At this time, if the base angle of the triangle of the auxiliary solar wing is increased, the mass center approaches the main solar wing, namely approaches the star, otherwise, the mass center is far away from the main solar wing and the star. In the case where both sufficient solar energy reception and vibration reduction are required, it is necessary to adjust the center of mass of the entire structure of the solar wing. In particular, the same principle is also adopted only by adjusting the change of the mass center of the auxiliary solar wing, and the distance between the mass center of the auxiliary solar wing and the star body can be adjusted. After the adjustment is completed, the mass center of the whole structure of the solar wing is closer to the star body, and the main solar wing and the auxiliary solar wing are less influenced by the vibration of the satellite star body. Especially, the auxiliary solar wing is not integrally connected with the main solar wing, so that the influence of the vibration of a satellite star on the auxiliary solar wing is smaller and very little, and the auxiliary solar wing is more suitable for carrying a detector needing to avoid the vibration.
It should be noted that the above-mentioned embodiments are exemplary, and those skilled in the art can devise various solutions in light of the present disclosure, which are also within the scope of the present disclosure and fall within the scope of the present disclosure. It should be understood by those skilled in the art that the present specification and drawings are illustrative only and are not limiting upon the claims. The scope of the invention is defined by the claims and their equivalents.
Claims (10)
1. A synthetic aperture radar satellite with a multi-angle sun wing, comprising at least a satellite body (300) of the synthetic aperture radar satellite and the sun wing, characterized in that,
the solar wings comprise a main solar wing (400), a first auxiliary solar wing (500) and a second auxiliary solar wing (600),
the first and/or second secondary sun wing (500, 600) is connected to the main sun wing (400) by means of a first angle adjustment mechanism (100) which can adjust the angle in a first and a second degree of freedom,
the main sun wing (400) and the star body (300) are connected by a second angle adjusting mechanism (200) capable of adjusting an angle in a second degree of freedom.
2. The SAR satellite according to claim 1, characterized in that the first sub-sun wing (500) and the second sub-sun wing (600) are symmetrically disposed on both sides of the main sun wing (400) in the sun wing open state,
in the state that the solar wings are folded, the first auxiliary solar wing (500) and the second auxiliary solar wing (600) are rotated in the opposite directions of the second degree of freedom through the first angle adjusting mechanism (100) and are respectively folded on two different side surfaces of the main solar wing (400).
3. The synthetic aperture radar satellite with multi-angle sun wing according to claim 1, characterized in that the first and second sub-sun wings (500, 600) are arranged on the same side of the main sun wing (400) in the sun wing open state, wherein,
the first sub-sun wing (500) is arranged between the main sun wing (400) and the second sub-sun wing (600), the first sub-sun wing (500) and the second sub-sun wing (600) are connected through a first angle adjusting mechanism (100),
in the folded state of the sun wings, the rotation directions of the first and second sub-sun wings (500, 600) are opposite in the second degree of freedom, the first and second sub-sun wings (500, 600) are folded on the same side of the main sun wing (400) and the first sub-sun wing (500) is located between the main sun wing (400) and the second sub-sun wing (600).
4. The SAR satellite according to claim 2 or 3, wherein the first sub-sun wing (500) and the second sub-sun wing (600) are respectively rotated in a second degree of freedom perpendicular to the plane of the main sun wing (400) based on the first angle adjustment mechanism (100).
5. The SAR satellite according to claim 4, wherein the two first angle adjusting mechanisms (100) on both sides of the main solar wing (400) are symmetric around the center of the main solar wing (400) and not to the central axis,
in the state that the solar wings are folded, the first auxiliary solar wing (500) and the second auxiliary solar wing (600) are folded and folded on the same side face of the main solar wing (400) opposite to the star body (300) in a non-overlapping mode,
the main solar wing (400) rotates towards the star body (300) and is attached to the side wall of the star body (300), and at the moment, the first auxiliary solar wing (500) and the second auxiliary solar wing (600) are respectively positioned between the main solar wing (400) and the star body (300).
6. The SAR satellite with multi-angle sun wing according to claim 5, characterized in that the first angle adjusting mechanism comprises at least a first connection seat (101) and a second connection seat (102) for fixing on the sun wing, a first joint mechanism and a second joint mechanism are arranged between the first connection seat (101) and the second connection seat (102), wherein,
the first connecting seat (101) is connected with a first joint mechanism, the first joint mechanism is connected with a second joint mechanism, and the second joint mechanism is connected with a second connecting seat (102).
7. The SAR satellite with multi-angle sun wing according to claim 6, characterized in that the first joint mechanism comprises a first connection shaft (103), a first driving motor (104), a first motor flange (107) and a connection (108),
the first connecting shaft (103) being between the first connecting seat (101) and the connecting piece (108),
an output shaft of the first driving motor (104) penetrates through the first connecting shaft (103) through a bearing, so that the first connecting shaft (103) rotates around a first rotating shaft line (105) of the first driving motor (104), and a first motor flange (107) connects a shell of the first driving motor (104) with a first joint shell (106).
8. The SAR satellite with multi-angle sun wing according to claim 6, characterized in that the second joint mechanism comprises a fixed flange (109), a second motor flange (110) and a second driving motor (112),
the connecting piece (108) is connected with a fixed flange (109), the fixed flange (109) is connected with an output shaft of the second driving motor (112) through a second motor flange (110), so that the first joint mechanism rotates around a second rotating axis (111) of the second driving motor (112),
the first axis of rotation (105) of the first joint mechanism is perpendicular to the second axis of rotation (111).
9. The synthetic aperture radar satellite with multi-angle sun wing of claim 6,
the second angle adjusting mechanism (200) at least comprises a moving mechanism (202) arranged in the outer wall (201) of the star body, a bearing seat (215) and a rotating shaft (216) of which one end is provided with a first gear (218), the rotating shaft penetrates through the bearing seat (215) through a bearing, the bearing seat (215) is arranged in a mounting rack (214) welded on the inner wall of the star body, the other end of the rotating shaft is connected with the main sun wing, wherein,
a rack (208) is arranged in the moving mechanism (202), a sliding rail (211) is arranged on the outer wall (201), a lower sliding block (212) in the sliding rail (211) is welded with the rack (208), a through hole (213) is formed in the middle of the outer wall (201), and the first gear (218) is meshed with the rack (208) through the through hole (213).
10. The SAR satellite according to claim 9, wherein the second angle adjusting mechanism (200) further includes an upper rail (209) embedded in an upper slider (210), a lower portion of the upper slider (210) is connected to a rack (208),
the second angle adjusting mechanism (200) further comprises an upper bracket (266) and a lower bracket (204), the upper bracket (266) is provided with a first reel (203), the lower bracket (204) is provided with a second reel (205), the first reel (203) and the second reel (205) are connected through a pull wire (206) connected with a moving block (207), and the moving block (207) is connected with a rack (208).
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113734472A (en) * | 2021-11-05 | 2021-12-03 | 北京微焓科技有限公司 | Satellite battery plate unfolding device |
| CN116674769A (en) * | 2023-06-08 | 2023-09-01 | 重庆开拓卫星科技有限公司 | Solar wing multi-degree-of-freedom driving device |
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2020
- 2020-04-26 CN CN202020652365.3U patent/CN212501117U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113734472A (en) * | 2021-11-05 | 2021-12-03 | 北京微焓科技有限公司 | Satellite battery plate unfolding device |
| CN113734472B (en) * | 2021-11-05 | 2022-02-11 | 北京微焓科技有限公司 | Satellite battery plate unfolding device |
| CN116674769A (en) * | 2023-06-08 | 2023-09-01 | 重庆开拓卫星科技有限公司 | Solar wing multi-degree-of-freedom driving device |
| CN116674769B (en) * | 2023-06-08 | 2024-01-30 | 重庆开拓卫星科技有限公司 | Solar wing multi-degree-of-freedom driving device |
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