CN109484677A - For the solar wing spreading mechanism and installation method of microsatellite - Google Patents
For the solar wing spreading mechanism and installation method of microsatellite Download PDFInfo
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- CN109484677A CN109484677A CN201811588585.8A CN201811588585A CN109484677A CN 109484677 A CN109484677 A CN 109484677A CN 201811588585 A CN201811588585 A CN 201811588585A CN 109484677 A CN109484677 A CN 109484677A
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- pedestal
- solar wing
- unfolding mechanism
- female
- male
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The present invention provides a kind of solar wing spreading mechanisms and installation method for microsatellite, including female pedestal, male pedestal, rotary shaft, the anti-cold weld pad of T-type, a word gasket, left-handed torsional spring, dextrorotation torsional spring, pressure spring, lock shaft, locking nut；Rotary shaft passes through in the five coaxial earholes complemented each other to form by female pedestal with male pedestal；Left-handed torsional spring and dextrorotation torsional spring are installed across axisymmetry, and the extension arm of torsional spring respectively enters in the arm slot of female pedestal and male pedestal；Lock shaft and pressure spring are installed in the hole of public pedestal, and during solar wing spreading, the movement that track is circle is done along the cylindrical face of female pedestal in the head of lock shaft, and after expanding in place, lock shaft, which enters, under the squeezing action of pressure spring realizes locking in the hole of female pedestal；Locking nut is mounted on the both ends of rotary shaft.Installation method of the present invention is simple, and high reliablity, volume and weight are small, it is possible to provide 0 ° -180 ° solar wing spreadings at any angle can dramatically improve microsatellite solar wing pieces of cloth area.
Description
Technical field
The present invention relates to spacecraft technology field more particularly to a kind of solar wing spreading mechanism and installation methods.
Background technique
Solar wing converts the solar into electric energy on space orbit and uses for satellite, is the energy basis of satellite.Due to
It is limited by carrying space, solar wing need to fold gathering in satellite side wall in launching phase.After satellite and Separation, satellite
Solar wing spreading is at planar and lock.
Common solar wing spreading driving is divided into two kinds at present: it is active with it is passive, it is active to be commonly used as repeatable fold and solve
Locking-type sun wing mechanism uses motor driven unfolding mechanism, but also deposit using more in large satellite or manned space flight airship
In corresponding cost, such as power consumption, weight increases.
And for microsatellite, passive drive deploying solar wing is generallyd use, the potential energy storing mechanism of such as similar tape measure is answered
Become hinge, traditional hinge and rope linkage mechanism, torsion spring type hinge etc..Wherein, strain-type hinge is pacified in two pieces of sun interplanes
Dress, needs relatively large placement space, i.e. solar wing intermediate space is larger.Traditional hinge carrys out the satellite less than 50kg
It says, shows slightly heavy and complex.Torsion spring type hinge is using more in cube star, and structure type is varied, in solar wing
In the case that pieces of cloth are not especially nervous, conventional structure type can meet, and universality is preferable, but when the requirement of pieces of cloth rate
When high and volume weight requires extremely stringent, conventional structure type is then unable to satisfy, while two torsion spring type hinge unwinder
Structure is up and down when installing, concentricity it is difficult to ensure that, to increase mounted resistance and risk.
Therefore, how to design it is a kind of it is light-weight, space is small, structure is simple, easy for installation and reliable operation the sun span
Opening mechanism is particularly important for microsatellite.
Summary of the invention
In order to solve the problems in the prior art, the present invention provides it is a kind of it is light-weight, space is small, easy for installation and work
Reliable solar wing spreading mechanism and installation method.The present invention is realized especially by following technical solution:
A kind of solar wing spreading mechanism for microsatellite, the unfolding mechanism include: female pedestal, male pedestal, rotation
The anti-cold weld pad of axis, T-type, a word gasket, left-handed torsional spring, dextrorotation torsional spring, pressure spring, lock shaft, locking nut；The rotary shaft passes through
In the five coaxial earholes complemented each other to form by female pedestal with male pedestal, the anti-cold pad installation of T-type is in rotary shaft and public affairs
In the annular gap that pedestal is formed, the word gasket is mounted between female pedestal and male pedestal or more earhole；The left-handed torsional spring
It is installed with dextrorotation torsional spring across axisymmetry, the extension arm of torsional spring respectively enters in the arm slot of female pedestal and male pedestal；It is described
Lock shaft and pressure spring are installed in the hole of public pedestal, during solar wing spreading, the head of lock shaft along female pedestal column
The movement that track is circle is done in shape face, and after expanding in place, lock shaft enters in the hole of female pedestal under the squeezing action of the pressure spring,
Realize locking；The locking nut is mounted on the both ends of rotary shaft, prevents female pedestal from sliding axially with male pedestal.
As a further improvement of the present invention, female pedestal has three earholes of upper, middle and lower, and public pedestal has upper and lower two
A earhole.
As a further improvement of the present invention, there is retention bead on the earhole up and down of female pedestal.
As a further improvement of the present invention, the mounting surface of female pedestal and male pedestal is respectively provided with two through-holes, uses
It is connect in solar wing.
As a further improvement of the present invention, female pedestal, male pedestal material be titanium alloy, the rotary shaft, lock
The material of mandrel is stainless steel, and the material of the anti-cold weld pad of the T-type and a word gasket is polytetrafluoroethylene (PTFE).
As a further improvement of the present invention, the unfolding mechanism is mountable between two folding solar wings or single folding sun
Between the wing and structure.
As a further improvement of the present invention, the material of the torsional spring is spring steel or stainless steel.
As a further improvement of the present invention, the lock shaft includes guide section, interlude, pressure spring access section, guide section
Facilitate slide-in locking hole with fillet；Interlude has endless groove, transfers to lock shaft to unlock by endless groove after locking；
Pressure spring access section is pressure spring unstability in order to prevent, and the pressure spring that pressure spring is inserted in lock shaft is accessed section.
As a further improvement of the present invention, the unfolding mechanism carries out dual anti-cold welding design, i.e. coating and anti-cold welding
Pad improves reliability.
As a further improvement of the present invention, the rotary shaft has locking section, female/male pedestal and T-type/word pad
Piece cooperates section, which is variable diameters Step Shaft, and both ends have thread segment, limits rotary shaft play using locking nut；The rotation
Axis nut installation site has limit design, prevents from compressing T-type pad, increases mounted resistance.
As a further improvement of the present invention, the unfolding mechanism two matches, i.e. installation up and down.
The present invention separately provides a kind of installation method of above-mentioned solar wing spreading mechanism, and the method guarantees the pairs of sun span
Opening mechanism alignment, which comprises step 1: single unfolding mechanism assembly；Step 2: two unfolding mechanisms are installed simultaneously
In tooling 1, tooling 1 is close to side datum level, guarantees to be located on same axis；Step 3: unfolding mechanism is mounted on celestial body
In structure, tooling 1 and unfolding mechanism are mounted on simultaneously in celestial body structure when installation；Step 4: removing tooling 1；Step 5: erector
2 are filled, and solar wing side benchmark is close to tooling 2；Step 6: connection solar wing and unfolding mechanism；Step 7: removing tooling 2.
The beneficial effects of the present invention are: the solar wing spreading mechanism for microsatellite of the invention, high reliablity, volume
It is small with weight, it is possible to provide 0-180 ° of solar wing spreading at any angle can dramatically improve microsatellite solar wing cloth
Piece area；Unfolding mechanism installation method of the invention is simple, can reduce expansion process resistance, reduces because unfolding mechanism is different
Risk of failure is unfolded in axis bring.
Detailed description of the invention
Fig. 1 is structural schematic diagram when unfolding mechanism of the invention is unfolded 60 °；
Fig. 2 is the cross-sectional view along unfolding mechanism locking axis and rotation axis of the invention；
Fig. 3 is top view when unfolding mechanism of the invention collapses；
Top view when Fig. 4 is unfolding mechanism expansion of the invention；
Fig. 5 is the assembly method flow chart of unfolding mechanism of the invention；
Fig. 6 is the assembling process schematic diagram of unfolding mechanism of the invention.
Specific embodiment
The present invention is further described for explanation and specific embodiment with reference to the accompanying drawing.
As shown in Figs. 1-2, the solar wing spreading mechanism for microsatellite of the invention includes including female pedestal 1, male bottom
Seat 2, rotary shaft 3, dextrorotation torsional spring 4, left-handed torsional spring 5, locking nut 6, the anti-cold weld pad 7 of T-type, a word gasket 8, lock shaft 9, pressure spring
10.Entire unfolding mechanism carries out dual anti-cold welding design, i.e. coating and anti-cold weld pad, improves reliability.
Female pedestal 1 and male pedestal 2 are connect by rotary shaft 3, and rotary shaft 3 passes through male and female pedestal, at the both ends of rotary shaft 3,
The anti-cold weld pad 7 of T-type is installed in i.e. public pedestal earhole and rotary shaft annular gap, between about 1 earhole of male pedestal 2 and female pedestal
One word gasket 8 is installed.The unfolding mechanism general two match, i.e. installation up and down, and when solar wing compresses, lock shaft 9 is located at
On the outside of the intermediate earhole of female pedestal 1, solar wing is fixed on celestial body texture edge by hold-down mechanism, after unlock, in left-right rotary torsional spring
Solar wing spreading is driven under the action of storage potential energy, lock shaft 9 does circular motion on the outside of intermediate earhole, locks afterwards in place
Mandrel 9 enters in the locking hole of female pedestal 1.
Female pedestal 1 has three earholes of upper, middle and lower, wherein intermediate earhole provides the sliding cylinder curved surface of lock shaft 9, the song
When face has the locking hole cooperated with lock shaft 9, i.e. expansion fixed angle after expanding in place, under the action of pressure spring, it will lock
Mandrel, which is pushed into locking hole, completes locking.Earhole and rotary shaft 3, lock shaft 9 and locking hole etc. be all made of H8 f7 small―gap suture match
It closes, female about 1 earhole of pedestal designs corresponding retention bead, as shown in figure 3, being with 60 ° according to the needs of practical expanded angle
Example is illustrated, and after being fully deployed, limit work is as shown in Figure 4.It in actual work, can be according to specific angle design protrusion position
It sets.
Public pedestal 2 has upper and lower two earholes, and the earhole and rotary shaft 3 have biggish annular gap, the anti-cold weld pad of T-type
7 it is mountable wherein, install latter three between for H8 f7 small―gap suture cooperation.The middle position of public pedestal 2, i.e., and in female pedestal 1
Between the opposite position setting lock shaft and pressure spring mounting hole of earhole, operating groove is opened in mounting hole upper surface, for lock shaft after locking
Extraction.
Female pedestal 1 and male 2 mounting surface of pedestal are respectively provided with two through-holes, for connecting with solar wing.
The rotary shaft 3 can choose different materials with female pedestal 1, male pedestal 2 from lock shaft 9, prevent cold welding, this reality
The pedestal that provides selects titanium alloy in example, and axial workpiece can choose stainless steel, while in order to increase the reliability of expansion, can be
The outer application coating of axis.
According to presently preferred embodiments of the present invention, the unfolding mechanism, unfolded state largest enveloping (when being unfolded 180 °)
For 32 × 58mm, spacing is 1mm, the weight < 25g of unfolding mechanism after the installation of two folding expansion solar wings.
According to presently preferred embodiments of the present invention, it is described mother pedestal, male pedestal base thickness be 2mm, in order to mitigate weight,
Two kinds of pedestals can be carried out with structural weight reduction optimization, titanium alloy can be selected in material, while the bottom surface of pedestal and side are benchmark face.
According to preferred embodiments of the invention, stainless steel material is can be selected in the rotary shaft, lock shaft, prevents from generating with pedestal
Cold welding, while cold welding in order to prevent increase the anti-cold weld pad of nonmetallic T-type and a word gasket, the pad between female pedestal and male pedestal
Polytetrafluoroethylene (PTFE) etc. can be selected in the material of piece.
According to preferred embodiments of the present invention, the unfolding mechanism it is mountable between two folding solar wings or single folding solar wing with
Between structure.
According to preferred embodiments of the present invention, the rotary shaft has locking section, and female/male pedestal and T-type/word gasket are matched
Section is closed, which is variable diameters Step Shaft, and both ends have thread segment, limits rotary shaft play using locking nut；The rotary shaft spiral shell
Female installation site has limit design, prevents from compressing T-type pad, increases mounted resistance.
According to preferred embodiments of the invention, spring steel or stainless steel is can be selected in the torsional spring, according to actually required driving
Margin design parameter, the pressure spring only provide lock shaft axial force, and when motive force margin design considers lock shaft axial friction
?.
According to preferred embodiments of the invention, the lock shaft includes guide section, interlude, pressure spring access section, guide section band
There is fillet to facilitate slide-in locking hole；Interlude has endless groove, lock shaft can be transferred to unlock by endless groove after locking,
It is mainly used for terrestrial operation, pressure spring access section is pressure spring unstability in order to prevent, and the pressure spring that pressure spring is inserted in lock shaft is accessed section.
The present invention gives a kind of Fixture Design and installation method for guaranteeing expansion hinge installation alignment simultaneously.With reference to figure
5 with flow chart shown in fig. 6 and schematic diagram, including tooling 1 (11), celestial body structure (12), unfolding mechanism (13), tooling 2 (14),
Solar wing (15).Specific installation steps are as follows:
S101: single unfolding mechanism (13) itself assembly.
S102: two unfolding mechanisms (13) are mounted in tooling 1 (11) simultaneously, tooling 1 is close to side datum level
(11), guarantee to be located on same axis.
S103: unfolding mechanism (13) is mounted on celestial body structure (12), tooling 1 (11) and unfolding mechanism (12) when installation
(12) are mounted in celestial body structure simultaneously.
S104: and remove tooling 1 (11).
S105: mounting tool 2 (14), and solar wing (15) side benchmark is close to tooling 2 (14).
S106: connection solar wing (15) and unfolding mechanism (12).
S107: it removes tooling 2 (14).
As being also connected with solar wing on the outside of solar wing (15), unfolding mechanism installation method is similar.
The above description is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all utilizations
Equivalent structure or equivalent flow shift made by description of the invention and accompanying drawing content is applied directly or indirectly in other correlations
Technical field, be included within the scope of the present invention.
For those of ordinary skill in the art, without departing from the inventive concept of the premise, if can also make
Simple deduction or replace are done, all shall be regarded as belonging to protection scope of the present invention.
Claims (10)
1. a kind of solar wing spreading mechanism for microsatellite, it is characterised in that: the unfolding mechanism includes female pedestal, male bottom
The anti-cold weld pad of seat, rotary shaft, T-type, a word gasket, left-handed torsional spring, dextrorotation torsional spring, pressure spring, lock shaft, locking nut；The rotation
Shaft passes through in the five coaxial earholes complemented each other to form by female pedestal with male pedestal, and the anti-cold pad installation of T-type is being revolved
In the annular gap that shaft and public pedestal are formed, the word gasket is mounted between female pedestal and male pedestal or more earhole；It is described
Left-handed torsional spring and dextrorotation torsional spring are installed across axisymmetry, and the extension arm of torsional spring respectively enters the arm slot of female pedestal Yu male pedestal
It is interior；The lock shaft and pressure spring are installed in the hole of public pedestal, and during solar wing spreading, the head of lock shaft is along female bottom
The cylindrical face of seat does the movement that track is circle, and after expanding in place, lock shaft enters female pedestal under the squeezing action of the pressure spring
Hole in, realize locking；The locking nut is mounted on the both ends of rotary shaft, prevents female pedestal from sliding axially with male pedestal.
2. unfolding mechanism according to claim 1, it is characterised in that: mother's pedestal has three earholes of upper, middle and lower, public
Pedestal has upper and lower two earholes；There is retention bead on the earhole up and down of mother's pedestal.
3. unfolding mechanism according to claim 1, it is characterised in that: the mounting surface of the mother pedestal and male pedestal has respectively
There are two through-holes, for connecting with solar wing.
4. unfolding mechanism according to claim 1, it is characterised in that: it is described mother pedestal, male pedestal material be titanium alloy,
The rotary shaft, lock shaft material be stainless steel, the material of the anti-cold weld pad of the T-type and a word gasket is polytetrafluoroethylene (PTFE).
5. unfolding mechanism according to claim 1, it is characterised in that: the unfolding mechanism it is mountable two folding solar wings it
Between or single folding solar wing and structure between.
6. unfolding mechanism according to claim 1, it is characterised in that: the material of the torsional spring is spring steel or stainless steel.
7. unfolding mechanism according to claim 1, it is characterised in that: the lock shaft includes guide section, interlude, pressure spring
Section is accessed, guide section facilitates slide-in locking hole with fillet；Interlude has endless groove, transfers to and locks by endless groove after locking
Mandrel unlocks；Pressure spring access section is pressure spring unstability in order to prevent, and the pressure spring that pressure spring is inserted in lock shaft is accessed section.
8. unfolding mechanism according to claim 1, it is characterised in that: the unfolding mechanism carries out dual anti-cold welding design,
That is coating and anti-cold weld pad improve reliability.
9. unfolding mechanism according to claim 1, it is characterised in that: the rotary shaft has locking section, female/male pedestal
And T-type/word gasket cooperates section, which is variable diameters Step Shaft, and both ends have thread segment, is limited and is rotated using locking nut
Axis play；The rotary shaft nut installation site has limit design, prevents from compressing T-type pad, increases mounted resistance.
10. a kind of installation method based on the described in any item solar wing spreading mechanisms of such as claim 1-9, it is characterised in that:
The method guarantees pairs of solar wing spreading mechanism alignment, which comprises step 1: single unfolding mechanism assembly；Step
2: two unfolding mechanisms being mounted in tooling 1 simultaneously, tooling 1 is close to side datum level, guarantee to be located on same axis；Step
Rapid 3: unfolding mechanism being mounted in celestial body structure, tooling 1 and unfolding mechanism are mounted on simultaneously in celestial body structure when installation；Step
4: removing tooling 1；Step 5: mounting tool 2, and solar wing side benchmark is close to tooling 2；Step 6: connection solar wing and exhibition
Opening mechanism；Step 7: removing tooling 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811588585.8A CN109484677B (en) | 2018-12-24 | 2018-12-24 | Sun wing opening mechanism for microsatellite and installation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811588585.8A CN109484677B (en) | 2018-12-24 | 2018-12-24 | Sun wing opening mechanism for microsatellite and installation method |
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| Publication Number | Publication Date |
|---|---|
| CN109484677A true CN109484677A (en) | 2019-03-19 |
| CN109484677B CN109484677B (en) | 2022-01-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811588585.8A Active CN109484677B (en) | 2018-12-24 | 2018-12-24 | Sun wing opening mechanism for microsatellite and installation method |
Country Status (1)
| Country | Link |
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| CN (1) | CN109484677B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110304273A (en) * | 2019-06-06 | 2019-10-08 | 浙江大学 | A kind of expansion locking device of the solar energy sailboard of skin Nano satellite |
| CN113267093A (en) * | 2020-03-13 | 2021-08-17 | 北京星际荣耀空间科技股份有限公司 | Grid rudder structure and rocket with same |
| CN113665793A (en) * | 2021-08-12 | 2021-11-19 | 广东空天科技研究院 | Thin folding wing and spring driving mechanism thereof |
| WO2022047551A1 (en) * | 2020-09-02 | 2022-03-10 | "Endurosat" Joint Stock Company | System for deployable solar panels for nanosatellites |
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| US5037043A (en) * | 1989-08-24 | 1991-08-06 | Messerschmitt-Boelkow-Blohm | Locking arrangement for unfolded solar generators |
| US6158088A (en) * | 1999-04-05 | 2000-12-12 | Lockheed Martin Corporation | Deployable hinge assembly providing end of travel damping |
| CN105840647A (en) * | 2016-05-31 | 2016-08-10 | 南京理工大学 | Self-locking type hinge and cubic star battery array adopting self-locking type hinge |
| CN106763131A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | A kind of light-duty small hinge for being applied to moonlet development mechanism |
| CN107933972A (en) * | 2017-12-05 | 2018-04-20 | 中国科学院沈阳自动化研究所 | A kind of outspreading sailboard of solar cell position-limit mechanism |
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2018
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5037043A (en) * | 1989-08-24 | 1991-08-06 | Messerschmitt-Boelkow-Blohm | Locking arrangement for unfolded solar generators |
| US6158088A (en) * | 1999-04-05 | 2000-12-12 | Lockheed Martin Corporation | Deployable hinge assembly providing end of travel damping |
| CN105840647A (en) * | 2016-05-31 | 2016-08-10 | 南京理工大学 | Self-locking type hinge and cubic star battery array adopting self-locking type hinge |
| CN106763131A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | A kind of light-duty small hinge for being applied to moonlet development mechanism |
| CN107933972A (en) * | 2017-12-05 | 2018-04-20 | 中国科学院沈阳自动化研究所 | A kind of outspreading sailboard of solar cell position-limit mechanism |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110304273A (en) * | 2019-06-06 | 2019-10-08 | 浙江大学 | A kind of expansion locking device of the solar energy sailboard of skin Nano satellite |
| CN113267093A (en) * | 2020-03-13 | 2021-08-17 | 北京星际荣耀空间科技股份有限公司 | Grid rudder structure and rocket with same |
| WO2022047551A1 (en) * | 2020-09-02 | 2022-03-10 | "Endurosat" Joint Stock Company | System for deployable solar panels for nanosatellites |
| CN113665793A (en) * | 2021-08-12 | 2021-11-19 | 广东空天科技研究院 | Thin folding wing and spring driving mechanism thereof |
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|---|---|
| CN109484677B (en) | 2022-01-11 |
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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: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee before: AEROSPACE DONGFANGHONG DEVELOPMENT Ltd. |
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