CN213800234U - Pneumatic sliding unfolding device for nano satellite - Google Patents
Pneumatic sliding unfolding device for nano satellite Download PDFInfo
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- CN213800234U CN213800234U CN202022669375.0U CN202022669375U CN213800234U CN 213800234 U CN213800234 U CN 213800234U CN 202022669375 U CN202022669375 U CN 202022669375U CN 213800234 U CN213800234 U CN 213800234U
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Abstract
The utility model relates to a terminal crimping technical field specifically is a pneumatic type slip expansion device that receives satellite usefulness, and it includes: the gas cabin comprises a gas cabin outer surface, a first accommodating chamber part, a second accommodating chamber part, a partition plate, a reaction part, a supporting plate, a gas inlet, a circular hole, a supporting rod and a third accommodating chamber part, wherein the outer surface of the gas cabin is provided with an electromagnet, the first accommodating chamber part and the second accommodating chamber part are respectively used for placing chemical potassium peroxide and water, and chemical reaction can not react in the gas cabin under the gravity condition due to the blocking of the partition plate, when the satellite got into the track, the inside of gas cabin was in the weightlessness condition, and stopping that the baffle can be crossed to the chemical reaction in reaction department, and the oxygen that the reaction produced gets into the gas port, and the bracing piece is made by air-tight flexible material, and the bracing piece is shaft-like structure under the gas filled condition, the utility model discloses need not switch on and control division, the subassembly is simple, the utility model discloses it is lower to compare with the prior art quality, and stability is higher, and the structure is simpler.
Description
Technical Field
The utility model relates to a satellite technology field, concretely relates to receive pneumatic type slip expansion device that satellite was used.
Background
Very small satellites with wet masses (wet mass) between 1kg and 10kg (2 to 22lbs) are commonly referred to as "nano-satellites". Such satellites can be as small as or smaller than a single bread, are relatively inexpensive to build, but are typically very delicate in structure. They may be configured to carry an onboard computer adapted to interface with a communication system designed to not only control directional stability including orbital commands, but also to allow deployment of onboard equipment, such as solar panels and antennas, from their pre-launch stowed state to their operational state on an orbiting satellite.
One known deployment system used in existing nano-satellite structures involves the use of a thinned coiled nichrome wire configured to melt nylon fishing line (nylon fishing line) adapted to release or deploy deployment devices such as solar panels and antennas. The problems with coils, including overheating, dissolving and/or cracking nylon before they are heated sufficiently to their melting point, and the lack of system reproducibility, have created a need for more reliable deployed structures.
It is therefore desirable to provide an improved deployment system for a nano-satellite.
In order to make up for the above-mentioned deficiency, the utility model discloses a Chinese granted patent No. CN105523199B 'nano satellite electric heating development system'
The device is provided with a coil bound on the outer side of the structural plate and is heated by a heating rod on a support rod near the satellite element, so that the coil is broken.
The technical effect achieved by the device is that the structural plate is unfolded.
When the device is heated, heat can be conducted to the satellite element through the supporting rod, and the satellite element is damaged.
The device is electrified through the remote control device after reaching a preset track, and a broken coil is heated, so that a large amount of energy is consumed, and meanwhile, harmful resource heat is generated.
The device can unlock and unfold the box body only by matching a plurality of assemblies together, and the assemblies are complex and have low stability.
The device can unlock and unfold the box body only by electrifying and heating, and the electrifying and heating needs to arrange a circuit, so that the cost is increased, and meanwhile, the satellite mass is increased, and the emission cost is increased.
The device is electrified through the remote control device after reaching the expected orbit, but the remote control device needs a corresponding control room to increase the satellite mass, the satellite is far away from the earth, and a remote control system is unstable, so that the coordination among the components of the device is poor, the expansion process is complicated, and the controllability of the device is low.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a pneumatic type that receives satellite usefulness slides expandes device and consumes energy when having solved heating fusing coil high, and stability is low, and the subassembly harmony is poor, and the quality is heavy, produces the problem that harmful substance harmd the satellite component when the unblock expandes.
A pneumatic sliding unfolding device for a nano satellite comprises an air chamber, a box body and a structural plate;
the gas cabin comprises a gas cabin outer surface, a first accommodating chamber part, a second accommodating chamber part, a partition plate, a reaction part, a supporting plate, a gas inlet, a circular hole, a supporting rod and a third accommodating chamber part, wherein an electromagnet is arranged on the gas cabin outer surface;
the first accommodating chamber part and the second accommodating chamber part are respectively provided with a chemical potassium peroxide and water, so that chemical reaction can not be carried out in the gas cabin under the gravity condition due to the blocking of the partition plate, when the satellite enters the orbit, the interior of the gas cabin is in a weightless condition, the chemical can cross the blocking of the partition plate to carry out reaction at the reaction position, and oxygen generated by the reaction enters the gas inlet;
the support rod is made of an airtight flexible material; the support rod is of a rod-shaped structure under the condition of inflation and is in a contracted state under the condition of non-inflation, the support rod is arranged on the air inlet, the support rod is inflated into a rod shape by oxygen flowing into the air inlet, and the support rod inflated into the rod shape extends out of the air cabin through the circular hole;
the supporting rod is used for accommodating the three parts of the accommodating chamber, the gas inlet is formed in the supporting plate, the box body comprises a sliding groove and a sliding groove surface, the sliding groove is provided with an electromagnet on the surface, the sliding groove is provided with a gas cabin on the surface, the structural plate is provided with a structural plate upper surface, the structural plate upper surface is provided with an electromagnet, and when the box body is not unlocked, the electromagnet on the structural plate upper surface and the electromagnet on the sliding groove surface are attracted to achieve the effect of connecting the structural plate and the box body. The electromagnet on the outer surface of the air cabin is absorbed on the structural plate, and the effect of reinforcing the connection of the structural plate and the box body is achieved.
The utility model discloses beneficial effect:
prior art needs the effect that the ohmic heating made the coil fracture in order to reach the expansion box, the utility model discloses an electro-magnet fastening structure board is connected with the box, and the not hard up that becomes of being connected between box and the structural slab after the outage, this moment the utility model discloses utilize gas to blow the structural slab and expand the box, the utility model discloses do not need the energy consumption during the unblock box, the utility model discloses it is lower to compare with prior art power consumption.
The heat that prior art heating produced can conduct to the satellite component, leads to damaging the satellite component, the utility model discloses during the unblock box, not produce harmful resources, the utility model discloses compare with prior art danger lower, the reliability is higher.
The utility model discloses need not switch on and control part, the subassembly is simple, the utility model discloses it is lower to compare with the prior art quality, and stability is higher, and the structure is simpler.
Prior art need mutually support through remote control unit and heating rod and just can reach the effect of launching the box, the utility model discloses a magnetic force suction fastening box utilizes the outage to lose suction, and gas cabin release gas unblock box, the utility model discloses compare still less with the prior art subassembly, the box launches the flow and optimizes more, and the controllability is higher, and harmony is higher between the subassembly.
The utility model discloses unlocking device sets up and does not occupy box inner space resource on structural slab and box, and space utilization is high.
Drawings
Fig. 1 is a first schematic view of a first unlocking box of a pneumatic sliding deployment device for a nano-satellite of the present invention.
Fig. 2 is a second schematic view of the box unlocking of the pneumatic sliding deployment device for the nano-satellite of the present invention.
Fig. 3 is a front view of the casing of the pneumatic sliding deployment device for nano-satellites according to the present invention.
Fig. 4 is a schematic view of the gas chamber of the pneumatic sliding deployment device for the nano-satellite of the present invention.
Fig. 5 is a third schematic view of the unlocking of the box body of the pneumatic sliding unfolding device for the nano satellite of the present invention.
Description of the drawings: 11. a gas cabin; 110. an outer surface of the gas cabin; 111. a first accommodating chamber; 112. a second accommodating chamber; 113. a partition plate; 114. a reaction site; 115. a support plate; 116. an air inlet; 117. a circular hole; 118. a support bar; 119. a third accommodating chamber; 12. a box body; 121. a chute; 1211. a chute surface; 13. a structural panel; 131. the upper surface of the structural panel.
Detailed Description
The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, which are easily implemented by those having ordinary skill in the art to which the present invention pertains.
As shown in fig. 1 and 3, a pneumatic sliding unfolding device for a nano-satellite comprises an air chamber 11, a box body 12 and a structural plate 13;
as shown in fig. 4, the gas chamber 11 includes a gas chamber outer surface 110, a first accommodating chamber 111, a second accommodating chamber 112, a partition 113, a reaction site 114, a support plate 115, a gas inlet 116, a circular hole 117, a support rod 118, and a third accommodating chamber 119;
an electromagnet is arranged on the outer surface 110 of the gas cabin;
as shown in fig. 4, the first container portion 111 and the second container portion 112 are respectively filled with potassium peroxide and water, which are chemical reagents, and the chemical reaction equation is 2K2O2+2H2O＝4KOH+O2；
As shown in fig. 4, due to the blocking of the partition 113, the chemical reaction does not react in the gas cabin 11 under the gravity condition, when the satellite enters the orbit, the inside of the gas cabin 11 is in the weightless condition, the chemical can pass through the blocking of the partition 113 to react at the reaction site 114, and the oxygen generated by the reaction enters the gas inlet 116;
as shown in fig. 4, the support rod 118 is made of a flexible material that is impermeable to air; the support rod 118 is a rod-shaped structure when inflated and is contracted when not inflated;
as shown in fig. 4, the air inlet 116 is provided with a support rod 118, the oxygen flowing into the air inlet 116 inflates the support rod 118 into a rod shape, and the rod 118 inflated into the rod shape extends out of the air chamber 11 through the circular hole 117;
as shown in fig. 4, the third portion 119 of the accommodating chamber is used for accommodating a support rod 118, and an air inlet 116 is formed on the support plate 115;
as shown in fig. 2, the case 12 includes a chute 121, a chute surface 1211;
an electromagnet is arranged on the chute surface 1211;
as shown in fig. 5, an air chamber 11 is provided on the chute surface 1211;
as shown in fig. 1, the structural plate 13 is provided with a structural plate upper surface 131;
an electromagnet is arranged on the upper surface 131 of the structural plate;
when the case 12 is not unlocked, the electromagnet on the upper surface 131 of the structural plate attracts the electromagnet on the sliding slot surface 1211 to connect the structural plate 13 with the case 12. The electromagnet on the outer surface 110 of the air chamber is attracted to the structural plate 13, which has the effect of reinforcing the connection between the structural plate 13 and the box body 12.
The utility model discloses the theory of operation:
as shown in fig. 1 and 5, after the satellite enters the orbit, the inside of the gas cabin 11 is in a weightless condition, chemicals cross the partition 113 to react at the reaction site 114, the gas generated by the reaction enters the gas inlet 116, the support rods 118 on the gas inlet 116 are inflated into a rod shape and extend out of the gas cabin 11 through the circular holes 117, the support rods 118 extending out of the gas cabin 11 prop against the structural plate 13, so that the structural plate 13 moves towards two sides along the direction of the sliding groove 121, and the box body 12 is unlocked and unfolded.
Claims (4)
1. A pneumatic sliding deployment device for a nano-satellite, comprising: the air chamber (11), the box body (12) and the structural plate (13); the method is characterized in that: the box body (12) comprises a sliding groove (121) and a sliding groove surface (1211), wherein an air chamber (11) is arranged on the sliding groove surface (1211), the air chamber (11) comprises an air chamber outer surface (110), a first accommodating chamber part (111), a second accommodating chamber part (112), a partition plate (113), a reaction part (114), a support plate (115), an air inlet (116), a circular hole (117), a support rod (118) and a third accommodating chamber part (119), the partition plate (113) is arranged between the first accommodating chamber part (111) and the second accommodating chamber part (112), the reaction part (114) is arranged on the partition plate (113), the support plate (115) is arranged between the second accommodating chamber part (112) and the third accommodating chamber part (119), the air inlet (116) is arranged on the support plate (115), the support rod (118) is arranged on one side of the air inlet (116) and inside the third accommodating chamber part (119), and the circular hole (117) is arranged on the side wall of the air chamber (11), the positions of the air inlets (116) correspond to the positions of the circular holes (117), and the structural plate (13) is provided with a structural plate upper surface (131).
2. A pneumatic sliding deployment device for nanosatellites according to claim 1, wherein: electromagnets are arranged on the outer surface (110) of the air chamber, the surface (1211) of the sliding chute and the upper surface (131) of the structural plate, and the three groups of electromagnets are matched with each other.
3. A pneumatic sliding deployment device for nanosatellites according to claim 1, wherein: the first container part (111) and the second container part (112) are respectively filled with potassium peroxide and water.
4. A pneumatic sliding deployment device for nanosatellites according to claim 1, wherein: the support rod (118) is made of an airtight flexible material, the support rod (118) is of a rod-shaped structure in the inflated condition, and the support rod (118) is contracted in the uninflated condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022669375.0U CN213800234U (en) | 2020-11-19 | 2020-11-19 | Pneumatic sliding unfolding device for nano satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022669375.0U CN213800234U (en) | 2020-11-19 | 2020-11-19 | Pneumatic sliding unfolding device for nano satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213800234U true CN213800234U (en) | 2021-07-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022669375.0U Active CN213800234U (en) | 2020-11-19 | 2020-11-19 | Pneumatic sliding unfolding device for nano satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213800234U (en) |
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2020
- 2020-11-19 CN CN202022669375.0U patent/CN213800234U/en active Active
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