CN109204889A - A kind of flexibility sun wing mechanism - Google Patents
A kind of flexibility sun wing mechanism Download PDFInfo
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- CN109204889A CN109204889A CN201811320480.4A CN201811320480A CN109204889A CN 109204889 A CN109204889 A CN 109204889A CN 201811320480 A CN201811320480 A CN 201811320480A CN 109204889 A CN109204889 A CN 109204889A
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Classifications
-
- 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
-
- 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
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Photovoltaic Devices (AREA)
Abstract
The present invention discloses a kind of flexible sun wing mechanism, is related to space technology field, including solar collecting device；Extending apparatus, the extending apparatus are made of shape-memory polymer, and the extending apparatus is beanpod rod-type, and the extending apparatus drives the solar collecting device to collapse and be unfolded；Heating device, extending apparatus described in the heating devices heat.Flexibility sun wing mechanism of the present invention, there is apparent advantage using mechanical unfolding mechanism compared to traditional, complicated in mechanical structure degree and expansion difficulty can be effectively reduced, its expansion process slowly, to spacecraft impact it is small, may be implemented from lock and self-deploy, structure it is simple, and cost is lower, rigidity is higher after expansion, improves the stability of solar wing spreading.
Description
Technical field
The present invention relates to space technology fields, and in particular to a kind of flexibility sun wing mechanism.
Background technique
With the development of Space Science and Technology, the requirement with people to unfolding mechanism is higher and higher, to the power of solar wing and
Quality requirement is higher and higher, but traditional mechanical rigid solar wing is with the increase of power, solar wing panel quality also line
Property increase, and the increase of quality can reduce satellite overall frequency.Traditional solar wing mostly uses mechanical expansion, and there are mechanical knots
Structure is complicated, vulnerable to impact failure, quality is big, at high cost the disadvantages of.
In view of the above drawbacks, creator of the present invention obtains the present invention by prolonged research and practice finally.
Summary of the invention
To solve above-mentioned technological deficiency, the technical solution adopted by the present invention is, provides a kind of flexible sun wing mechanism, packet
It includes
Solar collecting device；
Extending apparatus, the extending apparatus are made of shape-memory polymer, and the extending apparatus is beanpod rod-type, described
Extending apparatus drives the solar collecting device to collapse and be unfolded；
Heating device, extending apparatus described in the heating devices heat.
Further, the solar collecting device includes solar battery film, the extending apparatus have it is multiple, it is described too
Positive energy battery membranes are fixed between the two neighboring extending apparatus.
Further, the sun wing mechanism further includes substrate, and the extending apparatus is fixedly connected with the substrate.
Further, the extending apparatus is fixedly connected by connector with the substrate, and the connector includes inner core
With bluff piece, the inner core and the bluff piece clamp and fix the extending apparatus.
Further, the sun wing mechanism further includes sleeve, the extending apparatus drive the solar battery film around
The sleeve is collapsed into curly.
Further, the sleeve is equipped with slot, and the extending apparatus is equipped with the inserted sheet to match with the slot,
The inserted sheet is inserted into the slot and is fixedly connected.
Further, the heating device includes heating film, the heating film be arranged in the extending apparatus surface and/
Or it is internal.
Further, the heating film passes through polyimides double-sided adhesive resistant to high temperature or the two-sided gluing of acrylic acid resistant to high temperature
The surface and/or the heating film for being attached to the extending apparatus are fixed on inside the extending apparatus.
Further, the shape-memory polymer includes epoxies shape-memory polymer or cyanate shape memory
Polymer.
Further, fibre reinforced composites or particulate reinforced composite are contained in the shape-memory polymer.
Compared with the prior art the beneficial effects of the present invention are:
1, a kind of flexible sun wing mechanism of the present invention, compared to it is traditional have using mechanical unfolding mechanism it is bright
Aobvious advantage, can be effectively reduced complicated in mechanical structure degree and expansion difficulty, and expansion process slowly, to spacecraft is impacted
It is small, may be implemented from lock and self-deploy, structure it is simple, and cost is lower, and rigidity is higher after expansion, improves solar wing spreading
Stability.
2, a kind of flexible sun wing mechanism of the present invention, locks the shape having certainly, process control is unfolded before expansion,
Quick rigidifying and rigidity are big after expansion, can be formed with large scale, and beanpod it is rod-shaped extending apparatus it is rod-shaped in beanpod, Ke Yi great
Amplitude improve material deformation state storage strain energy and unfolded state rigidity, the adaptivity of the unfolding mechanism make its
Flexible solar wing spreading technically has great application prospect.
Detailed description of the invention
It, below will be to required in embodiment description in order to illustrate more clearly of the technical solution in various embodiments of the present invention
The attached drawing used is briefly described.
Fig. 1 is extending apparatus schematic diagram of the invention；
Fig. 2 is extending apparatus sectional view of the invention；
Fig. 3 is extending apparatus schematic cross-section of the invention；
Fig. 4 is flexible solar wing spreading schematic diagram of the invention；
Fig. 5 is slot schematic diagram of the invention；
Fig. 6 is connector schematic diagram of the invention；
Fig. 7 is that flexible solar wing of the invention collapses schematic diagram；
Fig. 8 is shape memory hinge expanded schematic diagram of the invention；
Fig. 9 is that shape memory hinge of the invention collapses schematic diagram；
Figure 10 is expanded schematic diagram when shape memory hinge of the invention is connected in series；
Figure 11 is that shape memory hinge of the invention collapses schematic diagram when being connected in series；
Figure 12 is expanded schematic diagram when shape memory hinge of the invention is connected in parallel；
Figure 13 is that shape memory hinge of the invention collapses schematic diagram when being connected in parallel.
Digital representation in figure:
1- extending apparatus, arc portion in 11-, the side 12- arc portion, the straight portion in the end 13-, 2- heating film, 3- solar battery film, 4- connect
Fitting, 41- inner core, 411- annular protrusion, 42- bluff piece, 5- sleeve, 51- slot, 6- substrate, 7- fixture.
Specific embodiment
Below in conjunction with attached drawing, the forgoing and additional technical features and advantages are described in more detail.
Embodiment one
The present invention provides a kind of flexible sun wing mechanism, including extending apparatus, solar collecting device and heating device,
Extending apparatus can be motivated to occur to collapse for heating device or expansion, solar collecting device are fixedly connected with extending apparatus, stretching, extension dress
It sets and solar collecting device is driven to collapse and be unfolded, when not needing solar wing work, solar energy can be driven by extending apparatus
Collection device is collapsed into lesser volume, when spacecraft runs to formulation track, and solar wing is needed to collect solar energy, stretching, extension dress
It sets and drives solar collecting device expansion, expand the receiving area of solar collecting device, complete the expansion of flexible solar wing.
In conjunction with shown in Fig. 1-Fig. 4, extending apparatus 1 is elongated rod shape, and the cross section of extending apparatus 1 is pod-like, stretching, extension dress
1 is set as hollow beanpod rod-type structure, extending apparatus 1 is made of shape memory polymer material, specifically uses epoxies shape
Shape memory polymers resin or cyanate shape-memory polymer resin, epoxies shape-memory polymer resin or cyanate
The glass transition temperature of class shape-memory polymer resin is chosen according to actual needs；Shape memory polymer material is a kind of
Novel intelligent material with shape memory effect, the first material can be prepared into the ontology with original shape, when this kind of material
When the temperature of material is higher than its intrinsic glass transition temperature Tg, material will be flexibility by rigid transition, at this time can be in outer masterpiece
The deformation such as it is bent or is crimped under, after temperature reduces and is lower than glass transition temperature Tg, even if removing external force, the material
Material can also keep the shape after deformation and in rigid state, turn when the temperature of the material increases and is higher than its intrinsic vitrifying
After temperature Tg, when influencing without external force, this kind of material becomes flexible and can be self-healing original shape, and temperature reduces again
And lower than after glass transition temperature Tg, which restores rigidity and keeps initial shape.
The present embodiment utilizes the special nature of shape-memory polymer, and the stretching, extension of shape memory polymer material preparation is filled
It sets 1 to use in the device for needing to be unfolded in spacecraft, and cooperates the temperature of heating device control extending apparatus 1, in initial shape
Under state, extending apparatus 1 is the direct rod shape of expansion, heating devices heat extending apparatus 1, when the temperature of extending apparatus 1 increases and surpasses
When crossing the glass transition temperature Tg of shape-memory polymer, extending apparatus 1 is changed into flexible state, is bent under external force
Or curling is collapsed, after bending to predetermined shape, heater stop heating, extending apparatus 1 is restored to rigid state, removes outer
Power, extending apparatus 1 will keep being bent collapsing shape, and extending apparatus 1 can drive other devices to be co-located on rounding state at this time, reduce
The developed area of spacecraft, spacecraft are collapsed into lesser volume；It needs to fill composition when spacecraft enters planned orbit
When setting expansion, heating device heats extending apparatus 1 again, when extending apparatus 1 meets and exceeds shape-memory polymer again
When glass transition temperature Tg, extending apparatus 1 automatically restores to initial expansion shape, the device for needing to be unfolded in spacecraft at this time
Reach expansion shape.
Outer patch heating film can be used in heating device, embedded resistors silk heats, outer painting conducting resinl heats, sunlight irradiates, is ultraviolet
One or more combinations such as light irradiation driving, field drives or microwave-driven heat extending apparatus 1, wherein heating
Device may be provided at 1 outside of extending apparatus, may also be arranged on 1 inside of extending apparatus；In the present embodiment, heating device is added using electricity
The mode of heat heats extending apparatus 1, specific in the fixed heating film 2 in the outer surface of extending apparatus 1, heating film 2 is viscous
It is attached on the curved surface sidewall of extending apparatus 1, bonding method is to use polyimides double-sided adhesive resistant to high temperature or propylene resistant to high temperature
Sour sticking double faced adhesive tape improves the connectivity robustness of heating film 2 Yu extending apparatus 1, will not cause to heat because of the raising of temperature
Film 2 falls off.
Flexible sun wing mechanism described in the present embodiment, being applied to technical field of aerospace, that mechanical structure can be effectively reduced is multiple
Miscellaneous degree and expansion difficulty have apparent advantage, shape-memory polymer using mechanical extending apparatus compared to traditional
Damping it is larger, expansion process is more slow, impacts to spacecraft small, may be implemented from locking and self-deploy, and structure is simple,
Figuration be can according to need when heating into desired shape, rounding state can be kept after cooling, when needing to be unfolded, heating can again
The stretching, extension of shape memory beanpod bar is completed, provides new approaches for following space deployable structure；And the present invention is by extending apparatus 1
It is designed to that beanpod is rod-shaped, the strain energy of the deformation state storage of extending apparatus 1 and the rigidity of unfolded state is greatly improved.
Embodiment two
A kind of specific structure of flexible solar wing is present embodiments provided, as shown in connection with fig. 4, including extending apparatus 1, heating
Film 2, solar battery film 3, connector 4, sleeve 5 and substrate 6, solar battery film 3 are flexible battery film, and curling etc. can occur
Deformation, in the present embodiment, extending apparatus 1 is beanpod rod-type made of shape memory polymer material, improves the change of extending apparatus 1
The strain energy of shape state and the rigidity of unfolded state, extending apparatus 1 altogether there are two, solar battery film 3 is fixed on two stretching, extensions
Between device 1；The energisation mode of extending apparatus 1 is surface mount heating film 2 in the present embodiment；Sleeve 5 is hollow cylinder
Structure, extending apparatus 1 are fixed on the curved surface at 5 both ends of sleeve, and preferably, as shown in connection with fig. 5, sleeve 5 is in connection extending apparatus 1
Place is equipped with slot 51, and the top of extending apparatus 1 is equipped with the inserted sheet 11 to match with slot 51, and inserted sheet 11 is the rod-shaped stretching, extension of beanpod
Device 1 cuts away intermediate beanpod form part and the straight piece part in remaining both ends, inserted sheet 11 are inserted into slot 51, and passes through spiral shell
Nail realization extending apparatus 1 is fixedly connected with sleeve 5；The lower end of extending apparatus 1 is fixedly connected by connector 4 with substrate 6, is tied
It closes shown in Fig. 6, connector 4 includes inner core 41 and bluff piece 42, and inner core 41 is equipped with an annular protrusion 411, and annular protrusion 411 is inserted into
To the bottom end of extending apparatus 1, the outer circumferential of annular protrusion 411 is set there are two bluff piece 42, realizes bluff piece 42, stretching, extension by screw
Device 1 is fixedly connected with inner core 21, and then realizes being fixedly connected for extending apparatus 1 and connector 4, preferably, solar-electricity
The bottom end corner of pond film 3 is inserted between bluff piece 42 and inner core 41, then realizes solar battery film 3 and connector 4 by screw
Be fixedly connected；The bottom end of connector 4 is fixedly connected by screw with substrate 6, and substrate 6 is fixed on spacecraft.
Flexible solar wing described in the present embodiment before the Spacecraft Launch where it, will stretch as shown in connection with fig. 7
Device 1 is heated to be crimped into cylindrical shape around the sleeve 5 of end after the vitrifying glass transition temperature Tg of material, at this time
Flexible solar wing is in rounding state；After spacecraft enters planned orbit, heating film 2 gives extending apparatus 1 Temperature Excitation, this
When rolled state extending apparatus 1 will be returned to original straight-bar state, to drive the exhibition of middle flexible solar battery film 3
It opens.
The screw connection in the present embodiment is only that one kind described in example is fixedly connected with mode, plays and is fixedly connected
The connection type of effect is used equally for the present invention, and not limiting the mode that is fixedly connected of the invention is only screw connection.
Embodiment three
On the basis of the above embodiments, extending apparatus 1 is made the present embodiment of shape memory polymer composite material, shape
Shape memory composites include basis material and reinforcing material, basis material using epoxies shape-memory polymer or
Cyanate shape-memory polymer resin, the glass transition temperature Tg of epoxies shape-memory polymer are 80 DEG C, 100
DEG C, 120 DEG C, 150 DEG C or 170 DEG C etc.；Cyanate type is that glass transition temperature Tg is 180 DEG C or 210 DEG C etc., specifically can root
It is chosen according to the glass transition temperature Tg of needs；Reinforcing material is fibre reinforced composites or particulate reinforced composite, tool
Optional glass fibre, carbon fiber, aramid fiber, boron fibre, graphene, nickel powder, carbon nanotube or the hollow Nano four of body aoxidize
One or more combinations of three iron particles.
In the present embodiment, shape memory polymer composite material preparation can take the methods of vacuum assisted resin molding,
When composite material enhancing can take the continuous fiber reinforcements mode such as continuous carbon fibre or glass fiber reinforcement, effect of fibrous orientation angles
Can be Orthogonal Symmetric laying or angle symmetric layups, ply angle may be selected 0 °, 45 °, 90 ° angularly.
Example IV
On the basis of the above embodiments, as shown in connection with fig. 3, the section of extending apparatus 1 is symmetrical beanpod to the present embodiment
Shape, extending apparatus 1 are made of the flaky material of two and half pod-likes, preferably, constitute the flaky material thickness of extending apparatus 1
T is within the scope of 0.5-1.5mm, and extending apparatus 1 includes middle arc portion 11, side arc portion 12 and holds straight portion 13, and middle arc portion 11 is located at two
Between side arc portion 12, the straight portion 13 in two ends is located at the outboard end of two side arc portions 12, and holding straight portion 13 is tabular.
It is obtained according to flexural rigidity of section calculation formula EI=M/ (1/r)=M/ φ of beam, when the timing of maximal bending moment M mono-,
Sectional curvature radius r is bigger, i.e., sectional curvature is smaller, and then keeps section rigidity EI bigger, in the present embodiment, the circle of middle arc portion 11
Arc radius R1 and the arc radius R2 of side arc portion 12 are bigger, and the section rigidity of the extending apparatus 1 constituted is bigger；Middle part arc chord angle
The size for spending β influences the circularity of cross section, and middle part arc angle β is smaller, and the bending figuration of extending apparatus 1 is simpler.
Extending apparatus 1 in the present embodiment is that symmetrical beanpod is rod-shaped, when production, first makes half of beanpod bar part, so
Two and half beanpod bar parts are utilized into the bonding solidification of identical shape-memory polymer afterwards, or directlys adopt integration and is laid with fibre
Tie up curing molding.
Embodiment five
The present embodiment on the basis of the above embodiments, wraps up heat-shrink tube outside heating film 2 and laminate, while in heat-shrink tube
Upper suit heat-barrier material or aluminium foil, it is possible to reduce the heat dissipation of heater and laminate improves the heating efficiency of heating film 2.
Embodiment six
On the basis of the above embodiments, extending apparatus 1 described in above-described embodiment can form a kind of shape to the present embodiment
Hinge deployed configuration is remembered, in conjunction with shown in Fig. 8-Fig. 9, including extending apparatus 1 described in any of the above-described embodiment, extending apparatus 1
Both ends be provided with fixture 7, fixture 7 is for connecting other devices of the both ends of extending apparatus 1, and in the present embodiment, fixture is only indicated
The structure that extending apparatus 1 is connect with other devices of both ends can be used equally for the present embodiment by a kind of embodiment, realize this
Shape memory hinge deployed configuration described in embodiment, extending apparatus 1 are heated by heating device, and are more than its glass in temperature
Bending Deformation is at rounding state, such as U-shaped shape when glass transition temperature Tg, and extending apparatus 1 keeps rounding state, hinge after temperature reduces
The gathering of two end devices is realized in the bending of chain；When spacecraft enters space and runs to predetermined trajectory, heating device adds again
Hot stretched device 1, after temperature is more than its glass transition temperature Tg, extending apparatus 1 is unfolded, and hinge drives two sides device to realize
The expansion of device in spacecraft, in the present embodiment, to extending apparatus by the way of the surface mount heating film in extending apparatus 1
It is heated.
Embodiment seven
On the basis of the above embodiments, hinge deployed configuration when in use, can be used alone the present embodiment, can also be multiple
Serial or parallel connection uses, and when being used in series, in conjunction with shown in Figure 10-Figure 11, between two extending apparatus 1 and both ends pass through folder
The fixed connecting rod of tool 7, constitutes the connection type that three connecting rods are connected in series in two extending apparatus 1, in the initial stage, hinge and connecting rod
For straight-bar state, heating film is gradually heated up the extending apparatus 1 in hinge, when being more than its glass transition temperature Tg, in outer masterpiece
Extending apparatus 1 is bent into U-typed with lower, the two of connection function hinge is bending direction opposite two U-shaped at this time, so that
Overall structure is similar " S " type structure, and three connecting rods be in rounding state at this time, when to enter space pre- for spacecraft drive hinge
Behind orbit determination road, heating film is gradually heated up the extending apparatus 1 in hinge, and extending apparatus 1 gradually spreads out and is restored to initial straight-bar
State, for realizing that the expansion of connecting rod, the present embodiment use connecting rod, the hinge for not limiting tandem is only used for such device
Connection less limits the quantity of hinge deployed configuration.
The present embodiment, hinge deployed configuration is when used in parallel, and in conjunction with shown in Figure 12-13, two hinge deployed configurations are same
To one end connect a solar panels, the other end of two hinge deployed configurations connects another solar panels, two hinges expansion
Structure is used in parallel, the bonding strength after being capable of increasing the expansion stability of solar panels, and expansion.
The foregoing is merely presently preferred embodiments of the present invention, is merely illustrative for the purpose of the present invention, and not restrictive
's.Those skilled in the art understand that in the spirit and scope defined by the claims in the present invention many changes can be carried out to it,
It modifies or even equivalent, but falls in protection scope of the present invention.
Claims (10)
1. a kind of flexibility sun wing mechanism, which is characterized in that including
Solar collecting device；
Extending apparatus (1), the extending apparatus (1) are made of shape-memory polymer, and the extending apparatus (1) is beanpod bar
Type, the extending apparatus (1) drive the solar collecting device to collapse and be unfolded；
Heating device, extending apparatus (1) described in the heating devices heat.
2. flexibility sun wing mechanism as described in claim 1, which is characterized in that the solar collecting device includes solar energy
Battery membranes (3), the extending apparatus (1) have multiple, and the solar battery film (3) is fixed on the two neighboring extending apparatus
(1) between.
3. flexibility sun wing mechanism as described in claim 1, which is characterized in that the sun wing mechanism further includes substrate (6),
The extending apparatus (1) is fixedly connected with the substrate (6).
4. flexibility sun wing mechanism as claimed in claim 3, which is characterized in that the extending apparatus (1) passes through connector (4)
Be fixedly connected with the substrate (6), the connector (4) includes inner core (41) and bluff piece (42), the inner core (41) with it is described
Bluff piece (42) clamps and the fixed extending apparatus (1).
5. flexibility sun wing mechanism as claimed in claim 2, which is characterized in that the sun wing mechanism further includes sleeve (5),
It is curly that the extending apparatus (1) drives the solar battery film (3) to be collapsed into around the sleeve (5).
6. flexibility sun wing mechanism as claimed in claim 5, which is characterized in that the sleeve (5) is equipped with slot (51), institute
It states extending apparatus (1) and is equipped with the inserted sheet (11) to match with the slot (51), the inserted sheet (11) is inserted into the slot
(51) it is fixedly connected in.
7. flexibility sun wing mechanism as described in claim 1, which is characterized in that the heating device includes heating film (2), institute
Heating film (2) are stated to be arranged on the surface and/or inside of the extending apparatus (1).
8. flexibility sun wing mechanism as claimed in claim 7, which is characterized in that the heating film (2) passes through resistant to high temperature poly-
The surface and/or the heating film of acid imide double-sided adhesive or acrylic acid sticking double faced adhesive tape resistant to high temperature in the extending apparatus (1)
(2) it is internal to be fixed on the extending apparatus (1).
9. flexibility sun wing mechanism as described in claim 1, which is characterized in that the shape-memory polymer includes epoxies
Shape-memory polymer or cyanate shape-memory polymer.
10. flexibility sun wing mechanism as claimed in claim 9, which is characterized in that contain fibre in the shape-memory polymer
Dimension enhancing composite material or particulate reinforced composite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811320480.4A CN109204889B (en) | 2018-11-07 | 2018-11-07 | Flexible solar wing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811320480.4A CN109204889B (en) | 2018-11-07 | 2018-11-07 | Flexible solar wing mechanism |
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| Publication Number | Publication Date |
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| CN109204889A true CN109204889A (en) | 2019-01-15 |
| CN109204889B CN109204889B (en) | 2024-02-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811320480.4A Active CN109204889B (en) | 2018-11-07 | 2018-11-07 | Flexible solar wing mechanism |
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| CN (1) | CN109204889B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078778A (en) * | 2019-06-13 | 2020-12-15 | 海鹰航空通用装备有限责任公司 | Folding expansion device of intelligence |
| CN114162351A (en) * | 2021-12-31 | 2022-03-11 | 中国航天空气动力技术研究院 | Pod-shaped supporting rod device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103240894A (en) * | 2013-05-06 | 2013-08-14 | 南京航空航天大学 | Pod rod pultrusion device and method capable of ensuring straightness accuracy |
| CN107628270A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of bean-pod shaped bracing stick casts development mechanism aside |
| CN209225429U (en) * | 2018-11-07 | 2019-08-09 | 哈尔滨工业大学 | A kind of flexibility sun wing mechanism |
-
2018
- 2018-11-07 CN CN201811320480.4A patent/CN109204889B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103240894A (en) * | 2013-05-06 | 2013-08-14 | 南京航空航天大学 | Pod rod pultrusion device and method capable of ensuring straightness accuracy |
| CN107628270A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of bean-pod shaped bracing stick casts development mechanism aside |
| CN209225429U (en) * | 2018-11-07 | 2019-08-09 | 哈尔滨工业大学 | A kind of flexibility sun wing mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078778A (en) * | 2019-06-13 | 2020-12-15 | 海鹰航空通用装备有限责任公司 | Folding expansion device of intelligence |
| CN114162351A (en) * | 2021-12-31 | 2022-03-11 | 中国航天空气动力技术研究院 | Pod-shaped supporting rod device |
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| CN109204889B (en) | 2024-02-09 |
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