CN115313016A - Satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting - Google Patents
Satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting Download PDFInfo
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- CN115313016A CN115313016A CN202210999350.8A CN202210999350A CN115313016A CN 115313016 A CN115313016 A CN 115313016A CN 202210999350 A CN202210999350 A CN 202210999350A CN 115313016 A CN115313016 A CN 115313016A
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 136
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- 239000000463 material Substances 0.000 claims description 9
- 150000001875 compounds Chemical class 0.000 claims 1
- 238000005056 compaction Methods 0.000 abstract 1
- 230000000977 initiatory effect Effects 0.000 description 5
- 239000002360 explosive Substances 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 239000007769 metal material Substances 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
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- 238000005516 engineering process Methods 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 229920000271 Kevlar® Polymers 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000004761 kevlar Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/08—Means for collapsing antennas or parts thereof
- H01Q1/10—Telescopic elements
- H01Q1/103—Latching means; ensuring extension or retraction thereof
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/1235—Collapsible supports; Means for erecting a rigid antenna
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Abstract
The invention discloses a satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting, and relates to the technical field of satellite antenna pressing and unfolding. An alternative technical approach is provided for the compaction, release, deployment and locking of the deployable antenna mechanism of the spacecraft. The satellite antenna unfolding device is arranged on a satellite body and comprises a top end antenna array carbon fiber frame, a side end outer side antenna array carbon fiber frame, a side end inner side antenna array carbon fiber frame, a telescopic rod mechanism and a hot knife locking mechanism. At the moment when the hot knife locking mechanism cuts off the binding rope, the antenna array surface carbon fiber frame on the inner side of the side end and the antenna array surface carbon fiber frame on the outer side of the side end start to rotate under the action of the hinge and the moment of the composite hinge, meanwhile, the telescopic rod stretches under the driving of the movement of the antenna array surface carbon fiber frame on the outer side of the side end, when the upper surface and the lower surface of the antenna array surface carbon fiber frame on the inner side of the side end and the upper surface and the lower surface of the antenna array surface carbon fiber frame on the outer side of the side end are correspondingly parallel, the telescopic rod is locked, and the antenna finishes the whole unfolding process.
Description
Technical Field
The invention relates to the technical field of satellite antenna compression and unfolding, in particular to a locking and unfolding device for a non-fire spacecraft mechanism.
Background
With the development of aerospace technology, more and more spacecrafts need to be unfolded in orbit, and the deployable spacecraft structures need to be provided with corresponding locking and releasing devices. The device is a mechanical device which is used for realizing the fastening connection between a body and an accessory or between a component and a part when a spacecraft is launched and releasing the constraint according to the established requirement after the spacecraft is in orbit. Due to the different mass of the spacecraft components and their sensitivity to the impact environment, the required lock release devices also differ. According to different unlocking modes, the locking and releasing device can be divided into an initiating device and a non-initiating device. The initiating explosive device is the earliest used on the spacecraft and is the most commonly used locking and releasing device, has the outstanding advantages of light weight, small volume, large specific energy, high reliability, capability of realizing multipoint synchronous unlocking and releasing and the like, but also has some insurmountable defects, such as: the unlocking impact on the structure is large during unlocking, the gas generated after explosion has chemical pollution, the disposable use and high cost, and the like, and the method is not suitable for some spacecrafts. Compared with the initiating device, the non-initiating device generally has the advantages of small impact, no pollution, repeated use, low cost and the like.
Therefore, the application of the non-explosive device is receiving more and more attention, and the hot knife type locking and releasing device is a typical non-explosive device, and has significant advantages compared with an explosive unlocking device, such as: the device is insensitive to electromagnetic interference, small in unlocking impact, small in pollution, simple in structure, capable of repeatedly testing and the like, and has high application value. The hot knife type locking and releasing technology at home and abroad mainly utilizes a high-temperature co-fired ceramic electric heating element (blade-shaped structure) to cut off a Kevlar rope (the melting point is more than 500 ℃), but the structure is relatively complex, and the mass, the volume, the required power and the working voltage are large. Because of the sharp blade configuration, vibration friction tends to damage the lashing wire and is sensitive to creep and tension in the lashing wire, which severely limits the application of hot knife lock release devices.
Disclosure of Invention
Aiming at the problems, the invention provides a satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting, and provides a selectable technical approach for pressing, releasing, unfolding and locking a deployable antenna mechanism of a spacecraft.
The technical scheme of the invention is as follows: the satellite antenna unfolding device is arranged on a star body 8 and comprises a top end antenna array surface carbon fiber frame 1, a side end outer side antenna array surface carbon fiber frame 7, a side end inner side antenna array surface carbon fiber frame 9, a telescopic rod mechanism and a hot knife locking mechanism;
the top antenna array surface carbon fiber frame 1 is fixedly connected to the star 8, one end of the antenna array surface carbon fiber frame 9 on the inner side of the side end is hinged to the top antenna array surface carbon fiber frame 1, and the other end of the antenna array surface carbon fiber frame 9 on the outer side of the side end is hinged to the antenna array surface carbon fiber frame 7 on the outer side of the side end;
a hot knife locking mechanism is arranged between the star body 8 and the carbon fiber frame 9 of the antenna array surface on the inner side of the side end, and the carbon fiber frame 9 of the antenna array surface on the inner side of the side end is locked before the antenna is unfolded;
a hot knife locking mechanism is also arranged between the star body 8 and the antenna array carbon fiber frame 7 outside the side end, and the antenna array carbon fiber frame 7 outside the side end is locked before the antenna is unfolded;
the telescopic rod mechanism is connected between the star body 8 and the side end outer side antenna array surface carbon fiber frame 7, extends and guides in the antenna unfolding process, and locks the side end outer side antenna array surface carbon fiber frame 7 after the antenna is unfolded.
Further, the hot knife locking mechanism comprises a hot knife 11, a pulley 12 and a rope 14, the hot knife 11 is fixedly connected to the star 8, the pulley 12 is fixedly connected to the antenna array carbon fiber frame 7 on the outer side of the side end or the antenna array carbon fiber frame 9 on the inner side of the side end, and the rope 14 is annularly wound on the hot knife 11 and the pulley 12. Therefore, after the hot knife heats up, the rope can be cut off to unlock the array antenna surface carbon fiber frame 9 at the inner side of the side end.
Further, telescopic link mechanism includes telescopic link 10, telescopic link sliding pin 4 and slide 5, and one end and the star 7 of telescopic link 10 are articulated to other end fixed connection telescopic link sliding pin 4, slide 5 fixed connection are on side outside antenna array face carbon fiber frame 7, telescopic link sliding pin 4 sliding connection in slide 5.
Further, the telescopic link 10 includes the flexible inner tube and the flexible urceolus of pegging graft each other, the bottom and the star 8 of flexible urceolus are articulated, telescopic link sliding pin 4 fixed connection is on the top of flexible inner tube, the top mouth fixedly connected with of flexible urceolus rather than vertically bulb lock, the draw-in groove with bulb lock adaptation is seted up to the bottom of flexible inner tube. Therefore, when the telescopic rod 10 is extended to a fully unfolded state, the ball head in the ball head lock extends into the clamping groove to lock the length of the telescopic rod 10.
Further, the top antenna array surface carbon fiber frame 1 and the side end inner side antenna array surface carbon fiber frame 9 are hinged through a hinge 3, the hinge 3 comprises two hinges hinged through a hinge shaft, and the two hinges are respectively and fixedly connected with the top antenna array surface carbon fiber frame 1 and the side end inner side antenna array surface carbon fiber frame 9;
the hinged shaft is further sleeved with a first torsion spring, and two ends of the first torsion spring respectively abut against the top end antenna array surface carbon fiber frame 1 and the side end inner side antenna array surface carbon fiber frame 9, so that the two keep moving trends towards a mutual horizontal state; or, a first rotary power source is installed on the top antenna array surface carbon fiber frame 1, an output shaft of the first rotary power source is connected with a hinge shaft, and the hinge shaft is fixedly connected with an antenna array surface carbon fiber frame 9 on the inner side of the side end through one hinge. Thereby, after the rope is cut by the hot knife, a moment is generated to move the top array antenna carbon fiber frame 1 and the side end inner side array carbon fiber frame 9 to a mutually horizontal state.
Further, the side end inner side antenna array carbon fiber frame 9 is hinged with the side end outer side antenna array carbon fiber frame 7 through a composite hinge 13;
the composite hinge 13 comprises a plurality of pairs of supporting rods, wherein two supporting rods in the same pair are hinged through a rotating shaft and are respectively hinged with the antenna array surface carbon fiber frame 9 on the inner side of the side end and the antenna array surface carbon fiber frame 7 on the outer side of the side end;
the rotating shaft is further sleeved with a second torsion spring, and two ends of the second torsion spring respectively prop against the antenna array surface carbon fiber frame 7 on the outer side of the side end and the antenna array surface carbon fiber frame 9 on the inner side of the side end, so that the two tend to move towards a mutually horizontal state; or a second rotary power source is arranged on the antenna array surface carbon fiber frame 9 on the inner side of the side end, an output shaft of the second rotary power source is connected with a rotating shaft, and the rotating shaft is fixedly connected with the antenna array surface carbon fiber frame 7 on the outer side of the side end through one of the supporting rods. Thereby, after the rope is cut by the hot knife, a moment is generated to move the side end inner side array surface carbon fiber frame 9 and the side end outer side array surface carbon fiber frame 7 to a mutually horizontal state.
Further, the top end antenna array carbon fiber frame 1, the side end outer antenna array carbon fiber frame 7 and the side end inner antenna array carbon fiber frame 9 are all made of carbon fiber materials.
When the satellite antenna needs to be unfolded, at the moment that the hot knife locking mechanism cuts off the binding rope, the antenna array surface carbon fiber frame on the inner side of the side end and the antenna array surface carbon fiber frame on the outer side of the side end start to rotate under the action of the torque of the hinge and the composite hinge, meanwhile, the telescopic rod stretches under the driving of the movement of the antenna array surface carbon fiber frame on the outer side of the side end, when the upper surfaces and the lower surfaces of the antenna array surface carbon fiber frame on the inner side of the side end and the antenna array surface carbon fiber frame on the outer side of the side end are correspondingly parallel, the hinge and the composite hinge lock the antenna mechanism through the self-carried locking mechanism, meanwhile, the telescopic rod stretches to the longest limit position, the self-carried locking mechanism locks, the rigidity and the shape precision of the unfolded antenna are improved, and the whole unfolding process of the antenna is completed.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2a is a schematic view of a hinge according to the present invention;
FIG. 2b is a schematic side view of the hinge of the present invention;
FIG. 3a is a schematic view of a composite hinge structure according to the present invention;
FIG. 3b is a side view of the composite hinge structure of the present invention;
FIG. 4a is a schematic view of a hot knife according to the present invention;
FIG. 4b is a schematic side view of a hot knife configuration of the present invention;
FIG. 5 is a schematic view of a chute of the present invention;
FIG. 6 is a partial schematic view of the hot knife, antenna frame and compression cord in compression
FIG. 7 is a drawing of the retractable support rod, the sliding slot mechanism and the antenna frame
FIG. 8 is a diagram of the expansion of the retractable support rod, the sliding slot mechanism and the antenna frame
In the figure: the antenna array comprises 1-a top antenna array carbon fiber frame, 2-an antenna array carbon fiber frame support, 3-a hinge, 4-a telescopic rod sliding pin, 5-a slide way, 6-a telescopic rod, 7-a side end outer side antenna array carbon fiber frame, 8-a star, 9-a side end inner side antenna array carbon fiber frame, 10-a telescopic rod, 11-a hot knife, 12-a pulley, 13-a composite hinge and 14-a rope.
Detailed Description
In order to clearly explain the technical features of the present patent, the following detailed description of the present patent is provided in conjunction with the accompanying drawings.
As shown in fig. 1, the satellite antenna unfolding device including hot knife pressing and telescopic rod supporting comprises a top antenna array surface carbon fiber frame 1, a side end outer side antenna array surface carbon fiber frame 7, a side end inner side antenna array surface carbon fiber frame 9, a star body 8, a telescopic rod mechanism, a hot knife locking mechanism and a hinge mechanism;
the hot knife locking mechanism comprises a hot knife 11 and a pulley 12, as shown in fig. 4a and 4 b. The hot knife 11 is connected with the star body 8 through bolts, the rope 14 is wound on the hot knife heating rod and the pulley 12 to be compressed, and the pulley 12 is connected with the antenna array surface carbon fiber frame 9 on the inner side of the side end through bolts.
The hinge mechanism comprises a hinge 3 between the top antenna array surface carbon fiber frame 1 and the side end inner side antenna array surface carbon fiber frame 9 and a composite hinge 13 between the side end inner side antenna array surface carbon fiber frame 9 and the side end outer side antenna array surface carbon fiber frame 7, the hinge of the hinge 3 is in bolt connection with the surface of the top antenna array surface carbon fiber frame 1 and the surface of the side end inner side antenna array surface carbon fiber frame 9, the composite hinge is embedded into the side end outer side antenna array surface carbon fiber frame 7 and the side end inner side antenna array surface carbon fiber frame 9, and the schematic diagrams of the composite hinge are shown in fig. 3a and fig. 3 b.
The telescopic rod mechanism comprises a telescopic rod 10, a telescopic rod sliding pin 4 and a slide way 5, the telescopic rod 10 is hinged to the star body 8, the telescopic rod sliding pin 4 is fixed on the telescopic rod 10, the slide way 5 is welded on the antenna array surface carbon fiber frame 7 on the outer side of the side end, the telescopic rod sliding pin 4 and the slide way 5 form pin connection, and the slide way is as shown in fig. 5.
Hinge 3 and top antenna array carbon fiber frame 1, the inboard antenna array carbon fiber frame 9 of side are fixed continuous, or set up in the connecting seat and be used for driving hinge 3 initiative rotation power source.
At the moment when the hot knife locking mechanism cuts off the binding rope, the side end inner side antenna array surface carbon fiber frame 9 and the side end outer side antenna array surface carbon fiber frame 7 start to rotate under the moment action of the hinge and the composite hinge, meanwhile, the telescopic rod is driven by the side end outer side antenna array surface carbon fiber frame 7 to move to extend, when the upper surface and the lower surface of the side end inner side antenna array surface carbon fiber frame 9 and the side end outer side antenna array surface carbon fiber frame 7 are correspondingly parallel, the hinge and the composite hinge lock the antenna mechanism through the self-carried locking mechanism, namely, after being unfolded, the two hinges rotate along the shaft, and when the completely unfolded state is reached, the planes connected with the shaft are mutually extruded, so that seamless self-locking is realized; meanwhile, the telescopic rod stretches to the longest limit position and is locked through the self-locking mechanism, the rigidity and the shape precision of the unfolded antenna are improved, and the whole unfolding process of the antenna is completed.
The top end antenna array carbon fiber frame 1, the side end outer antenna array carbon fiber frame 7 and the side end inner antenna array carbon fiber frame 9 are all made of carbon fiber materials. The satellite-mounted antenna is required to maintain a stable shape in a space environment where temperature is drastically changed, and thus a material having an extremely small linear expansion coefficient, i.e., having a good thermal stability, is required. The required stiffness, strength and minimal linear expansion coefficient of the antenna can be achieved by selecting the single layer lay angle, ply ratio and ply sequence of the carbon fibers. The antenna generally adopts a high-strength and high-rigidity carbon fiber honeycomb sandwich structure, and can bear static and dynamic loads of an active section, good microwave reflection characteristics and the like. The density of the carbon fiber is basically equivalent to that of magnesium and plating, and is 0.20 to 0.57 times (calculated as carbon fiber M40 JB) that of other metal materials, and generally, the mass of the structure can be reduced by 30 to 40 percent by adopting the carbon fiber as a structural material. The specific strength and specific modulus are high. The superiority of carbon fiber in terms of light weight and high strength is well illustrated by the comparison of specific strength (tensile strength to density ratio of the material) and specific modulus (elastic modulus to density ratio). The carbon fiber has the most remarkable light weight and high strength performance, and the specific strength of the carbon fiber is 5 times higher than that of steel and 4 times higher than that of aluminum alloy; the specific modulus is 1.3 to 12.3 times of that of other structural materials. The carbon fiber reinforced composite material is an anisotropic material, shows obvious anisotropy, and has obvious differences in electric, magnetic, heat conduction, specific heat, thermal expansion coefficient, mechanical properties and the like along the fiber axis direction and the direction perpendicular to the fiber axis direction. The fatigue resistance of composite materials is much higher than that of metallic materials. Generally, the fatigue limit of the metal material is 40% -50% of the ultimate tensile strength, and the fatigue limit of the carbon fiber reinforced polymer composite material can reach 70% -80% of the ultimate tensile strength, so that the service life of the composite material member is longer than that of the traditional material member when the composite material member works under the condition of long-term alternating load. The high temperature performance is good. At 400 ℃, the elastic modulus of the aluminum alloy is reduced to almost zero, and the strength is also obviously reduced. The carbon fiber has basically unchanged strength and elastic modulus at the high temperature of 400 ℃.
The hinge 3 and the composite hinge 13 are hidden hinges, and the hidden hinges have the characteristic that all parts of the hinges are not exposed when the antenna is completely unfolded, so that the mounting difficulty of the effective load on the working surface of the antenna can be reduced, the integral shape and surface precision of the working surface of the antenna can be improved, and the detection performance of the antenna can be improved.
The telescopic rod mechanism comprises two telescopic sleeve rods, and the two small-diameter sleeve rods are accommodated in the large-diameter sleeve rods when the antenna is in a folded state; after the antenna is completely unfolded, the small-diameter sleeve rod extends out of the large-diameter sleeve rod completely and is locked through the spherical lock at the end part of the small-diameter sleeve rod, the whole telescopic rod mechanism supports the antenna array surface, and the rigidity and the shape surface precision of the working surface of the antenna are improved.
The bottom end of the top antenna array carbon fiber frame 1 is welded on the star body 8 through the antenna array carbon fiber frame support 2.
And the hinges of the hinge hinges 3 are connected with the top end antenna array carbon fiber frame 1 and the side end inner side antenna array carbon fiber frame 9 through bolts.
The telescopic rod 10 is hinged with the star body 8, and a telescopic rod sliding pin 4 on the telescopic rod 10 is in pin connection with a slide way 5 on the antenna array surface carbon fiber frame 7 on the outer side of the side end.
The composite hinges 13 are embedded in the side end outside antenna array carbon fiber frames 7 and the side end inside antenna array carbon fiber frames 9.
While the invention has been described in terms of its preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.
Claims (7)
1. A satellite antenna unfolding device comprising a hot knife pressing and telescopic rod supporting function is characterized in that the satellite antenna unfolding device is installed on a star body (8) and comprises a top end antenna array surface carbon fiber frame (1), a side end outer side antenna array surface carbon fiber frame (7), a side end inner side antenna array surface carbon fiber frame (9), a telescopic rod mechanism and a hot knife locking mechanism;
the top antenna array carbon fiber frame (1) is fixedly connected to the star body (8), one end of the side end inner side antenna array carbon fiber frame (9) is hinged to the top antenna array carbon fiber frame (1), and the other end of the side end inner side antenna array carbon fiber frame is hinged to the side end outer side antenna array carbon fiber frame (7);
a hot knife locking mechanism is arranged between the star body (8) and the side end inner side antenna array surface carbon fiber frame (9), and the side end inner side antenna array surface carbon fiber frame (9) is locked before the antenna is unfolded;
a hot knife locking mechanism is also arranged between the star body (8) and the side end outer antenna array surface carbon fiber frame (7), and the side end outer antenna array surface carbon fiber frame (7) is locked before the antenna is unfolded;
the telescopic rod mechanism is connected between the star body (8) and the antenna array carbon fiber frame (7) on the outer side of the side end, extends and guides in the antenna unfolding process, and locks the antenna array carbon fiber frame (7) on the outer side of the side end after the antenna is unfolded.
2. The satellite antenna unfolding apparatus comprising hot knife pressing and telescopic rod supporting according to claim 1, wherein the hot knife locking mechanism comprises a hot knife (11), a pulley (12) and a rope (14), the hot knife (11) is fixedly connected to the star body (8), the pulley (12) is fixedly connected to the side end outer antenna array carbon fiber frame (7) or the side end inner antenna array carbon fiber frame (9), and the rope (14) is annularly wound on the hot knife (11) and the pulley (12).
3. The satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting according to claim 1, wherein the telescopic rod mechanism comprises a telescopic rod (10), a telescopic rod sliding pin (4) and a slide way (5), one end of the telescopic rod (10) is hinged with the star body (7), the other end of the telescopic rod is fixedly connected with the telescopic rod sliding pin (4), the slide way (5) is fixedly connected on the antenna array surface carbon fiber frame (7) outside the side end, and the telescopic rod sliding pin (4) is slidably connected in the slide way (5).
4. The satellite antenna unfolding device comprising the hot knife pressing and telescopic rod supporting function as claimed in claim 3, wherein the telescopic rod (10) comprises a telescopic inner cylinder and a telescopic outer cylinder which are inserted into each other, the bottom end of the telescopic outer cylinder is hinged to the star body (8), the telescopic rod sliding pin (4) is fixedly connected to the top end of the telescopic inner cylinder, the top opening of the telescopic outer cylinder is fixedly connected with a ball head lock perpendicular to the telescopic outer cylinder, and the bottom end of the telescopic inner cylinder is provided with a clamping groove matched with the ball head lock.
5. The satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting is characterized in that the top antenna array carbon fiber frame (1) and the side end inner antenna array carbon fiber frame (9) are hinged through a hinge (3), the hinge (3) comprises two hinges hinged through a hinge shaft, and the two hinges are fixedly connected with the top antenna array carbon fiber frame (1) and the side end inner antenna array carbon fiber frame (9) respectively;
the hinged shaft is further sleeved with a first torsion spring, and two ends of the first torsion spring respectively abut against the top end antenna array surface carbon fiber frame (1) and the side end inner side antenna array surface carbon fiber frame (9) so that the two keep moving trends towards a mutual horizontal state; or a first rotary power source is arranged on the carbon fiber frame (1) of the antenna array surface at the top end, an output shaft of the first rotary power source is connected with a hinged shaft, and the hinged shaft is fixedly connected with the carbon fiber frame (9) of the antenna array surface at the inner side of the side end through one hinge.
6. The satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting is characterized in that the side end inner antenna array carbon fiber frame (9) is hinged with the side end outer antenna array carbon fiber frame (7) through a compound hinge (13);
the composite hinge (13) comprises a plurality of pairs of supporting rods, wherein two supporting rods in the same pair are hinged through a rotating shaft and are respectively hinged with the side end inner side antenna array surface carbon fiber frame (9) and the side end outer side antenna array surface carbon fiber frame (7);
the rotating shaft is further sleeved with a second torsion spring, and two ends of the second torsion spring are respectively abutted against the side end outer side antenna array carbon fiber frame (7) and the side end inner side antenna array carbon fiber frame (9) so that the two parts keep a movement trend towards a mutual horizontal state; or a second rotary power source is arranged on the antenna array carbon fiber frame (9) on the inner side of the side end, an output shaft of the second rotary power source is connected with a rotating shaft, and the rotating shaft is fixedly connected with the antenna array carbon fiber frame (7) on the outer side of the side end through one of the support rods.
7. The satellite antenna deployment device comprising hot knife pressing and telescopic rod supporting according to any one of claims 1 to 6, wherein the top end antenna array carbon fiber frame (1), the side end outer antenna array carbon fiber frame (7) and the side end inner antenna array carbon fiber frame (9) are made of carbon fiber materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210999350.8A CN115313016A (en) | 2022-08-19 | 2022-08-19 | Satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210999350.8A CN115313016A (en) | 2022-08-19 | 2022-08-19 | Satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting |
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| CN115313016A true CN115313016A (en) | 2022-11-08 |
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| CN202210999350.8A Pending CN115313016A (en) | 2022-08-19 | 2022-08-19 | Satellite antenna unfolding device comprising hot knife pressing and telescopic rod supporting |
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| CN117039392A (en) * | 2023-08-30 | 2023-11-10 | 西安电子科技大学 | Deployable structure for circular planar phased array antennas |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117039392A (en) * | 2023-08-30 | 2023-11-10 | 西安电子科技大学 | Deployable structure for circular planar phased array antennas |
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