CN107933971B - Solar wing unfolding and locking mechanism based on spring driving - Google Patents
Solar wing unfolding and locking mechanism based on spring driving Download PDFInfo
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- CN107933971B CN107933971B CN201711078799.6A CN201711078799A CN107933971B CN 107933971 B CN107933971 B CN 107933971B CN 201711078799 A CN201711078799 A CN 201711078799A CN 107933971 B CN107933971 B CN 107933971B
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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
- B64G1/443—Photovoltaic cell arrays
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Abstract
The invention provides a spring-driven solar wing unfolding and locking mechanism, which comprises a torsion spring, an end rotating seat, a middle rotating seat, a torsion spring limiting seat, a torsion spring pressing cover plate, an aramid fiber wire, a special adhesive tape and a locking mechanism, wherein the end rotating seat is arranged at the upper end of the torsion spring; the end rotating seats are positioned at the upper end and the lower end of the solar wing, are matched with each other left and right through the two-fold solar wing, provide unfolding axes and binding points, and are used as installation planes of the locking mechanism; the middle rotating seat is positioned in the middle of the solar wing, and an unfolding axis and binding points are provided by the left and right matching of the two folded solar wings; the torsion spring compression seat is a fixed plane of the straight section of the end part of the torsion spring, and compresses the torsion spring through the groove shape of the torsion spring compression cover plate; the torsional spring limiting seats are distributed on the two-fold solar wing in a staggered manner to complete limiting in the rotation process of the torsional spring; the driving moment when the solar wing is unfolded is provided by potential energy when the torsion spring is twisted, the locking mechanism completes locking after the solar wing is unfolded in place, and the spacing and the rigidity among the wings are kept through aramid fiber lines and special adhesive tapes.
Description
Technical Field
The invention relates to the technical field of spacecrafts, in particular to a solar wing unfolding and locking mechanism for spaceflight.
Background
The solar wing unfolding and locking mechanism is widely used in aerospace, particularly in the field of satellites, and is mainly used for providing a mounting plane for a solar cell system and ensuring that a folding wing is smoothly unfolded in an orbit. Taking a solar wing of a satellite in the aerospace field as an example, an unfolding mechanism of the solar wing mainly adopts the forms of a hinge type, a lotus leaf type, a rotary joint, a spring type and the like, and a locking mechanism mainly has the advantages of mechanical locking, friction self-locking, rigidity locking of a hinge and the like; comprehensively, the spring type unfolding mechanism is the simplest, but the existing spring type unfolding mechanism can only provide unfolding moment, the solar panels cannot bear force after being unfolded, data are not checked for the connection structures between the panels and the installation and matching relation of the springs and the panels temporarily, the locking degree of friction locking in the locking mechanism can change along with the surface state and installation of contact parts, complete quantitative effective control is difficult to achieve, the self rigidity of the hinge is guaranteed, the locking mechanism is only applied to the hinge type mechanism, the hinge has strict requirements on selection and installation, mechanical locking is more applied, the locking mechanism mainly comprises a connecting rod type, a pin hole type, a clamping groove type and the like, each application occasion is different, and how to achieve simplicity, small size and adaptation of the unfolding structure is the core of locking.
Therefore, in order to meet the requirements of a spacecraft solar cell array structure mechanism with high efficiency, reliability, simplicity, rapidness and light weight, the design of the cooperation of spring type, inter-plate connection structure and mechanical locking realizes the folding and effective unfolding and locking of the solar wing at all angles.
Patent document 1 (chinese patent publication No. CN1696012A) discloses a solar cell sailboard unfolding mechanism, which includes a straightening torsion spring, a tightening nylon belt fusing mechanism, and a solar cell sailboard unfolding positioning mechanism; wherein the straightening torsion springs connect the solar cell sailboards in a face-to-face or back-to-back manner; the tying nylon belt overcomes the tension of the straightening torsion spring to tie the solar cell sailboards folded in a reciprocating manner; the solar cell sailboard straightening and positioning mechanism comprises positioning pins and positioning pipes, wherein the positioning pins are arranged on the solar cell sailboards and can automatically extend out along with the straightening of the solar cell sailboards, and the positioning pipes are arranged on the adjacent solar cell sailboards. After the solar cell sailboard enters the outer space, the resistance wire is electrified to burn off the nylon belt, and the solar cell sailboard is unfolded under the elastic action of the torsion spring. After the solar cell sailboards are unfolded, the solar cell sailboards are pulled into the positioning pipes by the positioning pins, so that the solar cell sailboards form a planar array. However, the unfolding mechanism is mechanically locked, so that only manual folding can be performed, and automatic folding driven by a motor cannot be realized.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a solar wing spreading mechanism based on double torsion spring driving and aramid fiber wire connection fastening and a pin hole matching type locking mechanism based on a single spring, and the invention adopts the following technical scheme:
a spring-driven solar wing unfolding and locking mechanism comprises a torsion spring, an end rotating seat, a middle rotating seat, a torsion spring pressing cover plate, aramid fiber wires, a special adhesive tape and a locking mechanism; the end rotating seats are positioned at the upper end and the lower end of the solar wing, are matched with each other left and right through the two-fold solar wing, provide unfolding axes and binding points, and are used as installation planes of the locking mechanism; the middle rotating seat is positioned in the middle of the solar wing, and an unfolding axis and binding points are provided by the left and right matching of the two folded solar wings; the torsion spring compression seat is a fixed plane of the straight section of the end part of the torsion spring, and compresses the torsion spring through the groove shape of the torsion spring compression cover plate; the driving moment of the solar wing during unfolding is provided by potential energy of the torsion spring during torsion, the locking mechanism completes locking after the solar wing is unfolded in place, and the spacing and rigidity among the wings are kept through the aramid fiber line and the special adhesive tape.
Furthermore, the locking mechanism is positioned on the upper end surface and the lower end surface of the double-folding solar wing, and locking is completed simultaneously.
Further, the double-folding solar wing comprises a fixed solar wing and an unfolded solar wing, wherein the fixed solar wing is fixed on the spacecraft.
Furthermore, the locking mechanism comprises a hollow taper pin, a pin seat, a pressure spring seat, a pull rope, a pull ball and a locking rotary seat; one end of the pull rope is connected with the pressure spring, and the other end of the pull rope is connected with the pull ball; the other end of the pressure spring is fixedly connected with the pressure spring seat; the rotation axis of the locking rotary seat is the same as the unfolding axis of the solar wing, and the locking rotary seat and the pin seat are respectively positioned on the double-folding solar wing; when the solar wing is in a compressed state, the hollow taper pin enters the cylindrical groove of the pressure spring seat under the action of the pressure spring, slides along the cylindrical surface of the locking rotary seat in the unfolding process, and enters the round hole of the locking rotary seat after being in place.
Furthermore, the top surface of the pin seat is provided with an operation groove, and the taper pin is manually pulled out through a round hole extending into the hollow taper pin.
Further, the unfolding and locking mechanism further comprises torsion spring limiting seats, and the torsion spring limiting seats are distributed on the two-fold solar wing in a staggered mode to finish limiting in the torsion spring rotating process.
Further, the size and the number of the torsion springs are calculated according to the weight of the solar panel and the required unfolding angular speed.
Furthermore, the number and the unfolding angle of the unfolded solar wings are designed according to the requirements of an actual power supply system.
Further, set up corresponding connecting hole on the seam both sides of two solar wings for the fastening of aramid fiber line, aramid fiber rope positive and negative adopts different ligature forms, can keep rigidity and do not influence around the axis rotation process, and the supplementary special stickness area of using simultaneously connects the panel, further improves connection rigidity.
The invention has the beneficial effects that: the solar wing unfolding and locking mechanism has the advantages of simple structure, small size, light weight, reliable unfolding and convenience in installation. When the movable wing and the spacecraft are released from the compaction relationship, the movable wing opens a fixed angle through the potential energy of a torsion spring, the opened wings are connected with a special sticky tape through aramid fiber wires, and the torsion spring only provides an unfolding moment and does not bear the force between the plates; the locking mechanism works after being unfolded in place, and is characterized in that a locking rotary seat of the locking mechanism rotates around an unfolding axis along with a movable wing, and a hollow taper pin circularly moves along a cylinder of the locking rotary seat under the action of a pressure spring until the locking rotary seat enters a circular groove of the locking rotary seat after being unfolded.
Drawings
FIG. 1 is a front view of the solar wing deployment and locking mechanism of the present invention after deployment;
FIG. 2 is a side view of the solar wing deployment and locking mechanism of the present invention after deployment;
FIG. 3 is a cross-sectional view of the locking mechanism of the present invention;
FIG. 4 is a schematic view of the locking mechanism of the present invention when locked;
FIG. 5 is a schematic view of the solar wing rotated at an angle when folded;
FIG. 6 is a schematic diagram of binding of front aramid threads of a solar wing;
fig. 7 is a schematic diagram of binding of aramid wires on the back of the solar wing.
The locking mechanism comprises a base 1, a locking mechanism 2, a torsion spring limiting base 3, a torsion spring pressing base 4, a torsion spring pressing cover plate 5, a fixed solar wing 6, a middle rotating base 7, a torsion spring 8, an expanded solar wing 9, an aramid fiber wire 10, a special sticky tape 11, a locking rotating base 21, a hollow taper pin 22, a pin base 23, a pressure spring 24, a pressure spring base 25, a pull rope 26 and a pull ball 27.
Detailed Description
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
Fig. 1 is a schematic view showing a state where a solar wing is completely unfolded and a cell sheet is attached to the opposite side of the solar wing, and fig. 2 is a side view of the solar wing unfolding and locking mechanism of the present invention after the solar wing is unfolded.
The invention discloses a spring-drive-based solar wing unfolding and locking mechanism, which comprises an end rotating seat 1, a middle rotating seat 7, a torsion spring limiting seat 3, a torsion spring pressing seat 4, a torsion spring pressing cover plate 5, a fixed solar wing 6, an unfolded solar wing 9, an aramid fiber wire 10, a special adhesive tape 11 and a locking mechanism 2. The driving moment of the unfolded solar wing is provided by potential energy generated when a spring is twisted, the locking mechanism 2 completes locking after the unfolded solar wing is in place, and the spacing and the rigidity among the wings are kept through aramid fiber lines 10 and special adhesive tapes 11.
The end rotating seats 1 are located at the upper end and the lower end of the solar wing, are matched with the solar wing in a left-right mode through two folds, provide unfolding axes and binding points, and serve as installation planes of the locking mechanism. The middle rotating seat 7 is positioned in the middle of the solar wing, and provides an unfolding axis and binding points through left and right matching of the two folded solar wings. The torsion spring compression seat 4 is a fixed plane of a straight section of the end part of the torsion spring, and compresses the torsion spring through a groove type of the torsion spring compression cover plate 5. The torsion spring limiting seats 3 are distributed on the two-fold solar wing in a staggered mode, and limiting in the torsion spring rotating process is completed.
The upper end face and the lower end face of the solar panel (namely the solar wing) are respectively provided with a locking device, and the locking rotating seat 21 and the pin seat 23 are respectively positioned on the two solar panels and are used in a matching way. As shown in fig. 3, the locking mechanism 2 includes a hollow taper pin 22, a pin seat 23, a pressure spring 24, a pressure spring seat 25, a pull rope 26, a pull ball 27 and a locking rotary seat 21. The locking mechanism 2 is positioned on the upper end surface and the lower end surface of the double-folding solar wing for contact, and simultaneously locking is completed. When the solar wing is in a compressed state, the hollow taper pin 22 enters the cylindrical groove of the pressure spring seat 25 under the action of the pressure spring 24, slides along the cylindrical surface of the locking rotary seat 21 in the unfolding process, and enters the circular hole of the locking rotary seat 21 after being in place. One end of the pull rope 24 is connected with the pressure spring 24, and the other end is connected with the pull ball 27. The other end of the pressure spring 24 is fixedly connected with a pressure spring seat 25. The axis of rotation of the locking swivel is the same as the sun wing opening axis. The top surface of the pin seat 23 is provided with an operation groove, and the taper pin can be manually pulled out by extending into the round hole of the hollow taper pin 22. The locking mechanism completes the locking when fully deployed, see fig. 4.
When the solar wings are pressed tightly, the solar plates on the two sides can rotate for a fixed angle around the rotating shaft in the figure 5, and the device can realize any angle within 180 degrees. If the selected spring has longer free length, in order to prevent the instability of the torsion spring in the rotating process, the torsion spring limiting seats 3 are arranged on two sides of the torsion spring.
The torsion springs 8 are compressed through the torsion spring compression seats 4, the torsion springs have certain potential energy, and the size and the number of the torsion springs can be calculated according to the weight of the solar panel and the required expansion angular speed. The number and the unfolding angle of the unfolded solar wings can be designed according to the requirements of an actual power supply system.
Fig. 3 is a schematic diagram of a locking state of the locking mechanism, in an embodiment, when the sun panel is driven by the torsion spring to be 180 degrees, the hollow taper pin 22 slides into the pin hole of the locking rotary seat 21 under the action of the compression spring 24, and the front end of the hollow taper pin can be made into a spherical shape or have a larger radius, so that the insertion of the pin is facilitated. When the solar wing is pressed, the hollow taper pin 22 is manually withdrawn from the pin hole, the solar panel is rotated, and the taper pin rotates around the cylindrical surface of the locking rotating seat 21 until the required pressing angle is reached. Fig. 5 is a schematic diagram of the solar cell array at a 90 ° angle.
The unfolding and locking mechanism only provides unfolding and locking functions, the connection rigidity between the two battery plates is not large, the connection state of the two battery plates in the unfolding state is shown in the figures 6 and 7, the two sides of the joint of the two solar plates are provided with corresponding connecting holes for fastening the aramid fiber wire 10, the front and back surfaces of the aramid fiber rope adopt different binding forms, the rigidity can be kept, the rotation process around an axis is not influenced, meanwhile, a special adhesive tape 11 is used for connecting the battery plates in an auxiliary mode, and the connection rigidity is further improved.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (6)
1. The utility model provides a solar wing expandes and locking mechanism based on spring drive which characterized in that: the solar wing unfolding and locking mechanism comprises a torsion spring, an end rotating seat, a middle rotating seat, a torsion spring pressing cover plate, an aramid fiber wire, a special adhesive tape and a locking mechanism; the end rotating seats are positioned at the upper end and the lower end of the solar wing, are matched with each other left and right through the two-fold solar wing, provide unfolding axes and binding points, and are used as installation planes of the locking mechanism; the middle rotating seat is positioned in the middle of the solar wing, and an unfolding axis and binding points are provided by the left and right matching of the two folded solar wings; the torsion spring compression seat is a fixed plane of the straight section of the end part of the torsion spring, and compresses the torsion spring through the groove shape of the torsion spring compression cover plate; drive moment when the sun wing expandes is by potential energy when the torsional spring twists reverse provides, expand to target in place the back by locking mechanism accomplishes the locking, spacing and rigidity keep passing through between the wing aramid yarn and special stickness area realize, locking mechanism is located the upper and lower terminal surface of two books sun wing contacts, accomplishes the locking simultaneously, two books sun wing are including fixed sun wing, expansion formula sun wing, and wherein, fixed sun wing is fixed on the spacecraft, expand and locking mechanism still includes the spacing seat of torsional spring, the spacing seat of torsional spring staggers the distribution on two books sun wing, and it is spacing to accomplish the torsional spring rotation process.
2. The solar wing deploy and lock mechanism of claim 1, wherein: the locking mechanism comprises a hollow taper pin, a pin boss, a pressure spring seat, a pull rope, a pull ball and a locking rotating seat; one end of the pull rope is connected with the pressure spring, and the other end of the pull rope is connected with the pull ball; the other end of the pressure spring is fixedly connected with the pressure spring seat; the rotation axis of the locking rotary seat is the same as the unfolding axis of the solar wing, and the locking rotary seat and the pin seat are respectively positioned on the double-folding solar wing; when the solar wing is in a compressed state, the hollow taper pin enters the cylindrical groove of the pressure spring seat under the action of the pressure spring, slides along the cylindrical surface of the locking rotary seat in the unfolding process, and enters the round hole of the locking rotary seat after being in place.
3. The solar wing deploy and lock mechanism of claim 2, wherein: the top surface of the pin seat is provided with an operation groove, and the taper pin is manually pulled out through a round hole extending into the hollow taper pin.
4. The solar wing deploy and lock mechanism of claim 1, wherein: the size and the number of the torsion springs are calculated according to the weight of the solar panel and the required unfolding angular speed.
5. The solar wing deploy and lock mechanism of claim 1, wherein: the number and the unfolding angle of the unfolded solar wings are designed according to the requirements of an actual power supply system.
6. The solar wing deploy and lock mechanism of claim 1, wherein: set up corresponding connecting hole on the seam both sides of two solar wings for the fastening of aramid fiber line, aramid fiber line positive and negative adopts different ligature forms, can keep rigidity and do not influence around axis rotation process, and the special stickness area of supplementary use simultaneously connects the panel, further improves connection rigidity.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711078799.6A CN107933971B (en) | 2017-11-06 | 2017-11-06 | Solar wing unfolding and locking mechanism based on spring driving |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711078799.6A CN107933971B (en) | 2017-11-06 | 2017-11-06 | Solar wing unfolding and locking mechanism based on spring driving |
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| CN107933971A CN107933971A (en) | 2018-04-20 |
| CN107933971B true CN107933971B (en) | 2020-11-24 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109204890B (en) * | 2018-11-16 | 2024-03-29 | 北京微分航宇科技有限公司 | Solar wing unlocking and unfolding mechanism |
| CN109649696B (en) * | 2018-12-29 | 2022-05-31 | 西北工业大学 | Tray type micro-nano satellite separation device capable of roughly controlling angular velocity of rotation |
| CN110260727A (en) * | 2019-07-05 | 2019-09-20 | 贵州航天控制技术有限公司 | A kind of small-sized rudder face fold mechanism component |
| CN112009725A (en) * | 2020-09-02 | 2020-12-01 | 中国电子科技集团公司第十八研究所 | Memory alloy space solar wing unfolding device |
| CN113212810B (en) * | 2021-04-30 | 2023-06-20 | 北京吾天科技有限公司 | Compression release device of folding solar wing |
| CN114506475B (en) * | 2021-08-20 | 2022-11-11 | 北京博瑞原子空间能源科技有限公司 | Sun wing spreading mechanism, power supply device and spacecraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2371343A1 (en) * | 1976-11-17 | 1978-06-16 | Aerospatiale | DEVICE FOR THE SYNCHRONIZED DEPLOYMENT OF ARTICULATED ELEMENTS CARRYING SOLAR CELLS IN A PANEL SHAPED BY A SUCCESSION OF SUCH ELEMENTS |
| CN1696012A (en) * | 2005-05-31 | 2005-11-16 | 重庆大学 | Mechanism for outspreading sailboard of solar cell |
| CN105539885A (en) * | 2015-12-25 | 2016-05-04 | 南京理工大学 | Locking and releasing mechanism for expandable solar cell array of cubic satellite |
| CN106628267B (en) * | 2016-10-28 | 2019-04-09 | 浙江大学 | A kind of expansion of skin Nano satellite solar energy turnover panel and locking device |
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Address after: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Shenzhen Aerospace Dongfanghong Satellite Co.,Ltd. Address before: 518057 satellite building, 2002 Keyuan Road, Nanshan District, Shenzhen City, Guangdong Province Patentee before: AEROSPACE DONGFANGHONG DEVELOPMENT Ltd. |