CN203876992U - Repeatedly folding and unfolding mechanism for fan-shaped solar wings - Google Patents
Repeatedly folding and unfolding mechanism for fan-shaped solar wings Download PDFInfo
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- CN203876992U CN203876992U CN201420179685.6U CN201420179685U CN203876992U CN 203876992 U CN203876992 U CN 203876992U CN 201420179685 U CN201420179685 U CN 201420179685U CN 203876992 U CN203876992 U CN 203876992U
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- static plate
- guide plate
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- main backstop
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Abstract
The utility model discloses a repeatedly folding and unfolding mechanism for fan-shaped solar wings. Most solar wings for spacecrafts adopt disposable unfolding and locking mechanisms. When the spacecrafts transfer the orbits or the postures of the spacecrafts are adjusted, the stability of the spacecrafts can be influenced. Supporting bracket assemblies are respectively connected with the inner side walls of a moving guide plate and a stationary plate in a sliding way; one end of the stationary plate is fixed with a stationary plate connecting bracket, and both ends of the stationary plate connecting bracket are respectively connected with a spacecraft main body connecting bracket in a hinge way; a driven belt wheel and a driving belt wheel are connected through a conveying belt; the center position of the driven belt wheel is connected with the other end of the stationary plate in a hinge way, and the wheel rim position of the driven belt wheel is connected with the moving guide plate in a hinge way; a wedge block is fixed with the moving guide plate; two spring mounting bases are fixed on the stationary plate, and the inner side of each spring mounting base is respectively connected with a clamping block through an unlocking spring; and the clamping block close to the spacecraft main body is connected with the stationary plate in a hinge way, the other clamping block is connected with an unlocking slide block in a hinge way, and the unlocking slide block is connected with the stationary plate in a sliding way. Through the repeatedly folding and unfolding mechanism disclosed by the utility model, the repeated folding and unfolding of the fan-shaped solar wings can be realized.
Description
Technical field
The utility model belongs to space technology field, relates to the fan-shaped sun wing, is specifically related to a kind of fan-shaped sun wingheaviness Fu Zhezhan mechanism.
Background technology
The sun wing is to provide a kind of principal mode of spacecraft space power system.At present, most of spacecrafts use the sun wing to adopt rigid substrates, and the disposable expansion lockout mechanisms of the many employings of its expansion, and the sun wing folds and draws in fairing at launching phase, and after entering the orbit, disposable expansion is locked to mode of operation.Because solar cell substrate is rigid substrates, its weight and gathering volume are larger, and bearing space has been proposed to corresponding requirement.When spacecraft becomes rail or attitude regulation control, the flutter of the solar panel of expansion self will produce disturbance to this posture of spacecraft, affect the attitude stability of spacecraft.
Summary of the invention
The purpose of this utility model is for the deficiencies in the prior art, a kind of fan-shaped sun wingheaviness Fu Zhezhan mechanism is provided, this mechanism can realize the folding exhibition that repeats that spacecraft becomes fan-shaped sun wing when rail moves or attitude regulation controls, and reduces the harmful effect that while becoming rail, the flutter of the sun wing produces spacecraft body.
The utility model comprises that spacecraft body link span, static plate link span, sun wing bracing frame are overall, satellite gear development mechanism, synchronous belt drive mechanism, trapezoidal Suo Xie mechanism and motor; Described sun wing bracing frame totally comprises bracket assembly, motion guide plate and static plate; Described bracket assembly is arranged between motion guide plate and static plate, with the equal sliding block joint of madial wall of motion guide plate and static plate, and is connected with motion guide plate and static plate by satellite gear development mechanism; The sidewall of one end of described static plate and static plate link span is fixed, and the two ends of static plate link span are hinged with a stop pin respectively, and two stop pins are all fixed with spacecraft body link span; Between described static plate link span and spacecraft body link span, be provided with blocking device; Spacecraft body link span and spacecraft body are fixed; Described synchronous belt drive mechanism comprises driving pulley, driven pulley and belt conveyor; Described driving pulley is connected by coupler with the output shaft of motor, and the base of motor is fixed on spacecraft body link span; Driven pulley is connected by belt conveyor with driving pulley; The center of described driven pulley and the other end of static plate are hinged, and one end of wheel rim place and motion guide plate is hinged by STATEMENT OF FEDERALLY SPONSORED, and the other end of motion guide plate freely arranges; Described trapezoidal Suo Xie mechanism comprises that voussoir and lock separate assembly, and lock is separated assembly and comprised that lock separates spring, clamp and lock solution slide block, and voussoir and motion guide plate are fixed; In described static plate, be fixed with two spring mounting seats, the inner side of each spring mounting seat is separated spring with a clamp by lock respectively and is connected; Clamp and static plate near spacecraft body are hinged, and another clamp is hinged with lock solution slide block, and lock is separated slide block and static plate sliding block joint; Under deployed condition, voussoir embeds between two clamps completely, and two clamps compress voussoir.
Described voussoir comprises integrated wedge handle and wedge head; Described wedge handle and motion guide plate are fixed, and the two sides of tail of described wedge head and wedge handle junction are equipped with release and draw inclined-plane, and the head both sides of wedge head are equipped with locking and import inclined-plane; The outside of described clamp is provided with voussoir and imports inclined-plane, and inner side is provided with voussoir and derives inclined-plane.
Described blocking device comprises locking pellet and locking spring, and two locking pellets are separately positioned on the two ends of static plate link span; One end of each locking pellet is connected with static plate link span by locking spring, the other end respectively with the sidewall contact of corresponding stop pin, and the lock pin holes of offering with stop pin sidewall is mated setting.
Described bracket assembly comprises first connecting rod, second connecting rod, connection bracing frame, main backstop, the first slide block and the second slide block; The both sides of described main backstop are equipped with a plurality of connection bracing frames, and the two ends of adjacent two connection bracing frames are all hinged by pin, all hinged by pin near the two ends of two connection bracing frames and the two ends of main backstop of main backstop; Hinged near the connection bracing frame of motion guide plate and one end of first connecting rod, the other end of first connecting rod and the first slide block are hinged, and the first slide block is connected by sliding pair with the chute of motion guide plate; Hinged near the connection bracing frame of static plate and one end of second connecting rod, the other end of second connecting rod and the second slide block are hinged, and the second slide block is connected by sliding pair with the chute of static plate.The two ends of described main backstop are equipped with main backstop lug; The top of main backstop and all connection bracing frames all offers solar cell mounting hole.
Described satellite gear development mechanism comprises the first support, the second support, pinion carrier, incomplete planet gear, incomplete sun gear and locating dowel pin; Described pinion carrier comprises integrated main backstop mounting rod and is arranged on two gear hold-down arms at main backstop mounting rod two ends; The two ends of described main backstop mounting rod are fixed with the main backstop lug at main backstop two ends respectively; Two described gear hold-down arms are hinged with the two ends of the first support and the second support respectively, and the sidewall of the first support and motion guide plate are fixed, and sidewall and the static plate of the second support are fixed; Two incomplete planet gears are fixed with the two ends of the first support respectively, and all by locating dowel pin, locate; Two incomplete sun gears are fixed with the two ends of the second support respectively, and all by locating dowel pin, locate.Two described incomplete planet gears mesh with corresponding incomplete sun gear respectively; Not exclusively the rotating speed of planet gear is n
1, the rotating speed of pinion carrier is n
2, n
1: n
2=2:1.
The beneficial effects of the utility model:
1, adopt synchronous belt drive mechanism and satellite gear development mechanism, can realize and repeat to launch with folding, and launch accurate positioning; Satellite gear development mechanism and sun wing bracing frame are totally symmetrical structure, have increased the stability of expansion process;
2, by control, lock and separate the coupling mechanism force that the rigidity of spring and the bevel angle of clamp regulate trapezoidal Suo Xie mechanism, be easy to realize locking and release;
3, adopt thin-film solar cells to replace solar panel, reduce volume and weight, reduce costs;
While 4, folding, take up room little, during expansion, working area is large, has saved the enveloping space of spacecraft;
5, under complete deployed condition, bracket assembly is uniformly distributed along the circumference, and has higher rigidity and stability;
6, applied range, except can be applicable to the fan-shaped sun wing of repetition fold-playing, also can be applicable to deployable antenna and ground moving solar power supply apparatus etc. and repeats development mechanism.
Accompanying drawing explanation
Fig. 1 is integral structure assembling stereogram of the present utility model;
Fig. 2-1 starts lock-out state schematic diagram for trapezoidal Suo Xie mechanism in the utility model;
Fig. 2-2 are the complete lock-out state schematic diagram of trapezoidal Suo Xie mechanism in the utility model;
Fig. 3-1 is blocking device unlocked state cutaway view in the utility model;
Fig. 3-2 are blocking device lock-out state cutaway view in the utility model;
Fig. 4-1 is the overall folded state block diagram of sun wing bracing frame in the utility model;
Fig. 4-2 are the overall deployed condition block diagram of sun wing bracing frame in the utility model;
Fig. 5 is the deployed condition block diagram of bracket assembly in the utility model;
Fig. 6 is the structural perspective of main backstop in the utility model;
Fig. 7 is the assembling stereogram of satellite gear development mechanism in the utility model;
Fig. 8 is the sectional arrangement drawing of satellite gear development mechanism in the utility model;
Fig. 9 is the structural perspective of pinion carrier in Fig. 7;
Figure 10-1 is folded state schematic diagram of the present utility model;
Figure 10-2 are a view in the utility model expansion process;
Launch and the schematic diagram of lock-out state completely for the utility model Figure 10-3.
In figure: 1, spacecraft body, 2, spacecraft body link span, 3, static plate link span, 4, motion guide plate, 5, voussoir, 5-1, wedge handle, 5-2, wedge head, 5-2-1, inclined-plane is drawn in release, 5-2-2, locking imports inclined-plane, 6, bracket assembly, 6-1, first connecting rod, 6-2, second connecting rod, 6-3, connect bracing frame, 6-4, main backstop, 6-4-1, solar cell mounting hole, 6-4-2, main backstop lug, 6-5, the first slide block, 6-6, the second slide block, 7, satellite gear development mechanism, 7-1, the first support, 7-2, the second support, 7-3, pinion carrier, 7-3-1, main backstop mounting rod, 7-3-2, gear hold-down arm, 7-4, incomplete planet gear, 7-5, incomplete sun gear, 7-6, locating dowel pin, 8, STATEMENT OF FEDERALLY SPONSORED, 9, driven pulley, 10, belt conveyor, 11, static plate, 11-1, spring mounting seat, 12, lock is separated assembly, 12-1, lock is separated spring, 12-2, clamp, 12-2-1, voussoir imports inclined-plane, 12-2-2, voussoir is derived inclined-plane, 12-3, lock is separated slide block, 13, driving pulley, 14, motor, 15, stop pin, 16, locking pellet, 17, locking spring.
The specific embodiment
Below in conjunction with drawings and Examples, the utility model is described in further detail.
As shown in Fig. 1,2-1 and 2-2, fan-shaped sun wingheaviness Fu Zhezhan mechanism comprises that spacecraft body link span 2, static plate link span 3, sun wing bracing frame are overall, satellite gear development mechanism 7, synchronous belt drive mechanism, trapezoidal Suo Xie mechanism and motor 14; Sun wing bracing frame totally comprises bracket assembly 6, motion guide plate 4 and static plate 11; Bracket assembly 6 is arranged between motion guide plate 4 and static plate 11, with the equal sliding block joint of madial wall of motion guide plate 4 and static plate 11, and is connected with motion guide plate 4 and static plate 11 by satellite gear development mechanism 7; The sidewall of one end of static plate 11 and static plate link span 3 is fixed, and the two ends of static plate link span 3 are hinged with a stop pin 15 respectively, and two stop pins 15 are all fixing with spacecraft body link span 2; Between static plate link span 3 and spacecraft body link span 2, be provided with blocking device; Spacecraft body link span 2 is fixing with spacecraft body 1; Synchronous belt drive mechanism comprises driving pulley 13, driven pulley 9 and belt conveyor 10; Driving pulley 13 is connected by coupler with the output shaft of motor 14, and the base of motor 14 is fixed on spacecraft body link span 2; Driven pulley 9 is connected by belt conveyor 10 with driving pulley 13; The other end of the center of driven pulley 9 and static plate 11 is hinged, and one end of wheel rim place and motion guide plate 4 is hinged by STATEMENT OF FEDERALLY SPONSORED 8, and the other end of motion guide plate 4 freely arranges.Trapezoidal Suo Xie mechanism comprises that voussoir 5 and lock separate assembly 12, and lock is separated assembly 12 and comprised that lock is separated spring 12-1, clamp 12-2 and lock is separated slide block 12-3; In static plate 11, be fixed with two spring mounting seat 11-1, the inner side of each spring mounting seat 11-1 is separated spring 12-1 with a clamp 12-2 by lock respectively and is connected; Clamp 12-2 and static plate 11 near spacecraft body 1 are hinged, and another clamp 12-2 is hinged with lock solution slide block 12-3, and lock is separated slide block 12-3 and static plate 11 sliding block joints; Voussoir 5 comprises integrated wedge handle 5-1 and wedge head 5-2; Wedge handle 5-1 and motion guide plate 4 are fixing, and the two sides of tail of wedge head 5-2 and wedge handle 5-1 junction are equipped with release and draw inclined-plane 5-2-1, and the head both sides of wedge head 5-2 are equipped with locking and import inclined-plane 5-2-2; The outside of clamp 12-2 is provided with voussoir and imports inclined-plane 12-2-1, and inner side is provided with voussoir and derives inclined-plane 12-2-2.Under the overall deployed condition completely of sun wing bracing frame, the voussoir that the locking of wedge head 5-2 imports inclined-plane 5-2-2 extruding clamp 12-2 imports inclined-plane 12-2-1, reduces the insertion resistance of wedge head 5-2; When wedge head 5 inserts completely, two clamp 12-2 clamping wedge handle 5-1, realize locking; In releasing process, the release of wedge head 5-2 is drawn the voussoir of inclined-plane 5-2-1 extruding clamp 12-2 and is derived inclined-plane 12-2-2, reduces the pull-out resistance of wedge head 5-2.
As shown in Fig. 3-1 and 3-2, blocking device comprises that locking pellet 16 and 17, two locking pellets 16 of locking spring are separately positioned on the two ends of static plate link span 3; One end of each locking pellet 16 is connected with static plate link span 3 by locking spring 17, the other end respectively with the sidewall contact of corresponding stop pin 15, and the lock pin holes of offering with stop pin 15 sidewalls is mated setting.
As shown in Fig. 4-1,4-2 and 5, bracket assembly 6 comprises first connecting rod 6-1, second connecting rod 6-2, connects bracing frame 6-3, main backstop 6-4, the first slide block 6-5 and the second slide block 6-6; The both sides of main backstop 6-4 are equipped with four connection bracing frame 6-3, and the two ends of adjacent two connection bracing frame 6-3 are all hinged by pin, all hinged by pin near the two ends of two connection bracing frame 6-3 and the two ends of main backstop 6-4 of main backstop 6-4; Hinged near the connection bracing frame 6-3 of motion guide plate 4 and one end of first connecting rod 6-1, the other end of first connecting rod 6-1 and the first slide block 6-5 are hinged, and the first slide block 6-5 is connected by sliding pair with the chute of motion guide plate 4; Hinged near the connection bracing frame 6-3 of static plate 11 and one end of second connecting rod 6-2, the other end of second connecting rod 6-2 and the second slide block 6-6 are hinged, and the second slide block 6-6 is connected by sliding pair with the chute of static plate 11.
As shown in Figure 6, the two ends of main backstop 6-4 are equipped with main backstop lug 6-4-2; The top of main backstop 6-4 and all connection bracing frame 6-3 all offers solar cell mounting hole 6-4-1.
As shown in Fig. 7,8 and 9, satellite gear development mechanism 7 comprises the first support 7-1, the second support 7-2, pinion carrier 7-3, incomplete planet gear 7-4, incomplete sun gear 7-5 and locating dowel pin 7-6; Pinion carrier 7-3 comprises integrated main backstop mounting rod 7-3-1 and is arranged on two gear hold-down arm 7-3-2 at main backstop mounting rod two ends; The two ends of main backstop mounting rod 7-3-1 are fixed with the main backstop lug 6-4-2 at main backstop 6-4 two ends respectively; Two gear hold-down arm 7-3-2 are hinged with the two ends of the first support 7-1 and the second support 7-2 respectively, and the sidewall of the first support 7-1 and motion guide plate 4 are fixing, and the sidewall of the second support 7-2 and static plate 11 are fixing; Two incomplete planet gear 7-4 fix with the two ends of the first support 7-1 respectively, and all by locating dowel pin 7-6, locate; Two incomplete sun gear 7-5 fix with the two ends of the second support 7-2 respectively, and all by locating dowel pin 7-6, locate.Two incomplete planet gear 7-4 mesh with corresponding incomplete sun gear 7-5 respectively; Not exclusively the rotating speed of planet gear 7-4 is n
1, the rotating speed of pinion carrier 7-3 is n
2, n
1: n
2=2:1.
The principle of work of this fan-shaped sun wingheaviness Fu Zhezhan mechanism:
This fan-shaped sun wingheaviness Fu Zhezhan mechanism is not pressed on spacecraft body 1 surface while launching, and arrives after planned orbit, receives telecommand, is released and rotates to predetermined angular; Now, two locking pellets 16 in static plate link span 3 embed respectively in the lock pin holes of corresponding stop pin 15, and static plate link span 3 is fixing with spacecraft body link span 2.
As shown in Figure 10-1, sun wing bracing frame is totally in folded state, and thin-film solar cells is drawn between motion guide plate 4 and static plate 11.
As Fig. 1,2-1,8 and 10-2 as shown in, motor 14 forwards, drive driving pulley 13 to rotate, and drive driven pulleys 9 to rotate, thereby actuation movement guide plate 4 launch through belt conveyor 10.Motion guide plate 4 is fixed by the first support 7-1 and incomplete planet gear 7-4, not exclusively planet gear 7-4 makes planet motion, each connects bracing frame 6-3 and main backstop 6-4 launches with motion guide plate 4 by first connecting rod 6-1, thereby drive each thin-film solar cells to launch simultaneously, arrive after assigned position, motor 14 stalls, the voussoir 5 being fixed on motion guide plate 4 embeds between two clamp 12-2, two clamp 12-2 compress voussoir 5, realize and launch locking.As shown in Figure 10-3, sun wing bracing frame is totally in complete deployed condition.When motor reversal, voussoir 5 is extracted from two clamp 12-2,4 reversions of motion guide plate, and each connects bracing frame 6-3 and main backstop 6-4 drives each thin-film solar cells to draw between motion guide plate 4 and static plate 11.
Not exclusively planet gear is identical with scantling of structure and the number of teeth of incomplete sun gear, not exclusively the revolution ratio of planet gear and pinion carrier is 2:1, realize pinion carrier and turn over 180 °, and not exclusively planet gear turns over 360 °, guarantee that under complete deployed condition, motion guide plate is parallel with static plate, realize locking.
Claims (5)
1. fan-shaped sun wingheaviness Fu Zhezhan mechanism, comprises that spacecraft body link span, static plate link span, sun wing bracing frame are overall, satellite gear development mechanism, synchronous belt drive mechanism, trapezoidal Suo Xie mechanism and motor, it is characterized in that:
Described sun wing bracing frame totally comprises bracket assembly, motion guide plate and static plate; Described bracket assembly is arranged between motion guide plate and static plate, with the equal sliding block joint of madial wall of motion guide plate and static plate, and is connected with motion guide plate and static plate by satellite gear development mechanism; The sidewall of one end of described static plate and static plate link span is fixed, and the two ends of static plate link span are hinged with a stop pin respectively, and two stop pins are all fixed with spacecraft body link span; Between described static plate link span and spacecraft body link span, be provided with blocking device; Spacecraft body link span and spacecraft body are fixed; Described synchronous belt drive mechanism comprises driving pulley, driven pulley and belt conveyor; Described driving pulley is connected by coupler with the output shaft of motor, and the base of motor is fixed on spacecraft body link span; Driven pulley is connected by belt conveyor with driving pulley; The center of described driven pulley and the other end of static plate are hinged, and one end of wheel rim place and motion guide plate is hinged by STATEMENT OF FEDERALLY SPONSORED, and the other end of motion guide plate freely arranges; Described trapezoidal Suo Xie mechanism comprises that voussoir and lock separate assembly, and lock is separated assembly and comprised that lock separates spring, clamp and lock solution slide block, and voussoir and motion guide plate are fixed; In described static plate, be fixed with two spring mounting seats, the inner side of each spring mounting seat is separated spring with a clamp by lock respectively and is connected; Clamp and static plate near spacecraft body are hinged, and another clamp is hinged with lock solution slide block, and lock is separated slide block and static plate sliding block joint; Under deployed condition, voussoir embeds between two clamps completely, and two clamps compress voussoir.
2. fan-shaped sun wingheaviness Fu Zhezhan according to claim 1 mechanism, is characterized in that: described voussoir comprises integrated wedge handle and wedge head; Described wedge handle and motion guide plate are fixed, and the two sides of tail of described wedge head and wedge handle junction are equipped with release and draw inclined-plane, and the head both sides of wedge head are equipped with locking and import inclined-plane; The outside of described clamp is provided with voussoir and imports inclined-plane, and inner side is provided with voussoir and derives inclined-plane.
3. fan-shaped sun wingheaviness Fu Zhezhan according to claim 1 mechanism, is characterized in that: described blocking device comprises locking pellet and locking spring, and two locking pellets are separately positioned on the two ends of static plate link span; One end of each locking pellet is connected with static plate link span by locking spring, the other end respectively with the sidewall contact of corresponding stop pin, and the lock pin holes of offering with stop pin sidewall is mated setting.
4. fan-shaped sun wingheaviness Fu Zhezhan according to claim 1 mechanism, is characterized in that: described bracket assembly comprises first connecting rod, second connecting rod, connection bracing frame, main backstop, the first slide block and the second slide block; The both sides of described main backstop are equipped with a plurality of connection bracing frames, and the two ends of adjacent two connection bracing frames are all hinged by pin, all hinged by pin near the two ends of two connection bracing frames and the two ends of main backstop of main backstop; Hinged near the connection bracing frame of motion guide plate and one end of first connecting rod, the other end of first connecting rod and the first slide block are hinged, and the first slide block is connected by sliding pair with the chute of motion guide plate; Hinged near the connection bracing frame of static plate and one end of second connecting rod, the other end of second connecting rod and the second slide block are hinged, and the second slide block is connected by sliding pair with the chute of static plate; The two ends of described main backstop are equipped with main backstop lug; The top of main backstop and all connection bracing frames all offers solar cell mounting hole.
5. fan-shaped sun wingheaviness Fu Zhezhan according to claim 4 mechanism, is characterized in that: described satellite gear development mechanism comprises the first support, the second support, pinion carrier, not exclusively planet gear, not exclusively sun gear and locating dowel pin; Described pinion carrier comprises integrated main backstop mounting rod and is arranged on two gear hold-down arms at main backstop mounting rod two ends; The two ends of described main backstop mounting rod are fixed with the main backstop lug at main backstop two ends respectively; Two described gear hold-down arms are hinged with the two ends of the first support and the second support respectively, and the sidewall of the first support and motion guide plate are fixed, and sidewall and the static plate of the second support are fixed; Two incomplete planet gears are fixed with the two ends of the first support respectively, and by locating dowel pin, it are positioned; Two incomplete sun gears are fixed with the two ends of the second support respectively, and by locating dowel pin, it are positioned; Two described incomplete planet gears mesh with corresponding incomplete sun gear respectively; Not exclusively the rotating speed of planet gear is n
1, the rotating speed of pinion carrier is n
2, n
1: n
2=2:1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420179685.6U CN203876992U (en) | 2014-04-14 | 2014-04-14 | Repeatedly folding and unfolding mechanism for fan-shaped solar wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420179685.6U CN203876992U (en) | 2014-04-14 | 2014-04-14 | Repeatedly folding and unfolding mechanism for fan-shaped solar wings |
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| Publication Number | Publication Date |
|---|---|
| CN203876992U true CN203876992U (en) | 2014-10-15 |
Family
ID=51677519
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420179685.6U Withdrawn - After Issue CN203876992U (en) | 2014-04-14 | 2014-04-14 | Repeatedly folding and unfolding mechanism for fan-shaped solar wings |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103950558A (en) * | 2014-04-14 | 2014-07-30 | 浙江理工大学 | Fan-shaped solar wing repetitive folding and unfolding mechanism |
| CN104925272A (en) * | 2015-05-13 | 2015-09-23 | 上海宇航系统工程研究所 | Solar wing folding and unfolding mechanism based on planet band wheel transmission |
| CN105227083A (en) * | 2015-09-30 | 2016-01-06 | 黑龙江兴安新能源股份有限公司 | A kind of folding and expanding formula solar power plant with crank and rocker mechanism |
| CN107255149A (en) * | 2017-07-19 | 2017-10-17 | 浙江理工大学 | Planetary gear train type rolls over extending apparatus and its folding exhibition method |
| CN109367775A (en) * | 2018-12-07 | 2019-02-22 | 吉林大学 | A kind of folded fan type folding wing mechanism for foldable flapping-wing MAV |
| CN115384814A (en) * | 2022-08-09 | 2022-11-25 | 重庆开拓卫星科技有限公司 | Flexible solar wing mechanism capable of being repeatedly folded along shaft |
-
2014
- 2014-04-14 CN CN201420179685.6U patent/CN203876992U/en not_active Withdrawn - After Issue
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103950558A (en) * | 2014-04-14 | 2014-07-30 | 浙江理工大学 | Fan-shaped solar wing repetitive folding and unfolding mechanism |
| CN103950558B (en) * | 2014-04-14 | 2015-12-30 | 浙江理工大学 | A kind of fan-shaped solar wing repeats Zhe Zhan mechanism |
| CN104925272A (en) * | 2015-05-13 | 2015-09-23 | 上海宇航系统工程研究所 | Solar wing folding and unfolding mechanism based on planet band wheel transmission |
| CN105227083A (en) * | 2015-09-30 | 2016-01-06 | 黑龙江兴安新能源股份有限公司 | A kind of folding and expanding formula solar power plant with crank and rocker mechanism |
| CN107255149A (en) * | 2017-07-19 | 2017-10-17 | 浙江理工大学 | Planetary gear train type rolls over extending apparatus and its folding exhibition method |
| CN109367775A (en) * | 2018-12-07 | 2019-02-22 | 吉林大学 | A kind of folded fan type folding wing mechanism for foldable flapping-wing MAV |
| CN109367775B (en) * | 2018-12-07 | 2024-01-30 | 吉林大学 | Folding fan type folding wing mechanism for foldable flapping wing micro air vehicle |
| CN115384814A (en) * | 2022-08-09 | 2022-11-25 | 重庆开拓卫星科技有限公司 | Flexible solar wing mechanism capable of being repeatedly folded along shaft |
| CN115384814B (en) * | 2022-08-09 | 2024-01-26 | 重庆开拓卫星科技有限公司 | Flexible solar wing mechanism capable of being folded along axis repeatedly |
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