CN110683077A - Trapezoidal satellite structure suitable for radar antenna and manufacturing method - Google Patents
Trapezoidal satellite structure suitable for radar antenna and manufacturing method Download PDFInfo
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- CN110683077A CN110683077A CN201910888298.7A CN201910888298A CN110683077A CN 110683077 A CN110683077 A CN 110683077A CN 201910888298 A CN201910888298 A CN 201910888298A CN 110683077 A CN110683077 A CN 110683077A
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 10
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 56
- 239000004917 carbon fiber Substances 0.000 claims description 56
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 56
- 238000005192 partition Methods 0.000 claims description 55
- 239000010410 layer Substances 0.000 claims description 35
- 229910000838 Al alloy Inorganic materials 0.000 claims description 32
- 239000003431 cross linking reagent Substances 0.000 claims description 18
- 238000004026 adhesive bonding Methods 0.000 claims description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 239000011229 interlayer Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 2
- 238000009933 burial Methods 0.000 claims 1
- 108010066114 cabin-2 Proteins 0.000 abstract description 42
- 108010066057 cabin-1 Proteins 0.000 abstract description 36
- 238000001514 detection method Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract description 3
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
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Abstract
The invention provides a trapezoidal satellite structure suitable for a radar antenna and a manufacturing method thereof, wherein the trapezoidal satellite structure comprises: a cabin, a first side plate 15 and a second side plate 16; the cabin body comprises: an upper cabin 1, a middle cabin 2 and a lower cabin 3; the upper cabin 1, the middle cabin 2 and the lower cabin 3 are connected in sequence; the upper cabin 1, the middle cabin 2 and the lower cabin 3 are of a trapezoidal structure; the first side plate 15 is attached to the side surfaces of the upper cabin 1, the middle cabin 2 and the lower cabin 3, and the second side plate 16 is attached to the side surfaces of the upper cabin 1, the middle cabin 2 and the lower cabin 3; the plane of the central plane of the first side plate 15 intersects the plane of the central plane of the second side plate 16. The invention can ensure the reliable installation of the synthetic aperture radar antenna and can reduce the mass center of the whole satellite and the response of the synthetic aperture radar antenna; the invention can ensure that the fundamental frequency of the whole satellite meets the requirements of a carrier rocket and the thermal dimension stability of the whole satellite meets the detection precision index requirements of a synthetic aperture radar satellite.
Description
Technical Field
The invention relates to the field of satellite structures, in particular to a trapezoidal satellite structure suitable for a radar antenna and a manufacturing method thereof, and particularly relates to a foldable and foldable trapezoidal satellite structure of a large-size synthetic aperture radar antenna.
Background
When the large-size synthetic aperture radar antenna works in orbit, the large-size synthetic aperture radar antenna is usually in a rectangular configuration and is limited by the internal space of a fairing of a carrier rocket, and the synthetic aperture radar antenna needs to be folded and divided into two wings which are respectively installed on two sides of a satellite structure in a pressing mode through explosion bolts. After the synthetic aperture radar antenna is folded, the number and the positions of the pressing points distributed on the synthetic aperture radar antenna are determined, and after the synthetic aperture radar antenna is arranged on a satellite structure, the mass center, the fundamental frequency, the thermal dimension stability performance and the response of the synthetic aperture radar antenna are completely determined by the satellite structure. For some large-size synthetic aperture radar antennas, after being folded, folded and pressed on a satellite structure, the traditional rectangular and hexagonal satellite structures can not ensure the fundamental frequency and the thermal dimensional stability of the whole satellite and the response requirements of the synthetic aperture radar antenna. The trapezoidal satellite structure is an effective solution for successfully realizing engineering development of the large-size radar antenna satellite.
Patent document CN103963998B discloses a hexagonal frame main bearing satellite structure, which comprises two hexagonal frames, a plurality of adjustable cross bars and six longitudinal special-shaped bars, wherein the angle ends of the two hexagonal frames are respectively connected into a hexagonal frame through the six longitudinal special-shaped bars, the longitudinal special-shaped bars are provided with a plurality of mounting holes which are symmetrical structures, and the two special-shaped bars are respectively and adjustably connected with one end of the adjustable cross bar through two corresponding mounting holes. The patent cannot guarantee the fundamental frequency and the thermal dimension stability of the whole satellite and the response requirements borne by the synthetic aperture radar antenna.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a trapezoidal satellite structure suitable for a radar antenna and a manufacturing method thereof.
The invention provides a trapezoidal satellite structure suitable for a radar antenna, which comprises: a cabin, a first side plate 15 and a second side plate 16;
the cabin body comprises: an upper cabin 1, a middle cabin 2 and a lower cabin 3;
the upper cabin 1, the middle cabin 2 and the lower cabin 3 are connected in sequence;
the upper cabin 1, the middle cabin 2 and the lower cabin 3 are of a trapezoidal structure;
the lower surface of the upper cabin 1 is connected with the upper surface of the middle cabin 2, and the upper surface of the middle cabin 2 completely or partially covers the lower surface of the upper cabin 1;
the lower surface of the middle cabin 2 is connected with the upper surface of the lower cabin 3, and the upper surface of the lower cabin 3 completely or partially covers the lower surface of the middle cabin 2;
the first side plate 15 is attached to the side surfaces of the upper cabin 1, the middle cabin 2 and the lower cabin 3, and the second side plate 16 is attached to the side surfaces of the upper cabin 1, the middle cabin 2 and the lower cabin 3;
the plane of the central plane of the first side plate 15 intersects the plane of the central plane of the second side plate 16.
Preferably, the upper deck 1 comprises an upper deck roof 4, a deck-related part;
the upper cabin roof 4 is arranged on the lower bottom surface of the upper cabin 1, the cabin related part is arranged above the upper cabin roof 4, and the cabin related part is arranged between the upper bottom surface and the lower bottom surface of the upper cabin 1 or on the lower bottom surface of the upper cabin 1.
Preferably, the middle compartment 2 comprises a middle compartment middle deck 12, a partition member and a compartment body-related part;
the middle cabin middle layer plate 12 is arranged on the lower surface of the middle cabin 2, and the plane of the central plane of the partition plate is vertical to the lower surface of the middle cabin 2;
the cabin-related part is arranged above the middle cabin middle layer plate 12, and the cabin-related part is arranged between the upper bottom surface and the lower bottom surface of the middle cabin 2 or on the lower bottom surface of the middle cabin 2.
Preferably, said lower compartment 3 comprises: a lower deck floor 13, a partition member and a deck-related part;
the lower cabin bottom plate 13 is arranged on the lower surface of the lower cabin 3, and the plane of the central plane of the partition plate is vertical to the lower surface of the lower cabin 3;
the cabin-related part is arranged above the lower cabin bottom plate 13;
the cabin-related part is arranged between the upper bottom surface and the lower bottom surface of the lower cabin 3 or on the lower bottom surface of the lower cabin 3.
Preferably, the partition member 10 employs: a first divider member 101 and a second divider member 102;
the plane of the central plane of the first partition plate member 101 is intersected with the plane of the central plane of the second bottom plate 102;
the cabin body related parts adopt: the joint 7, the round rod 5, the square rod 6, the purlins 9, the embedded part 17 and the external pasted part 8;
the joint 7 is arranged at the joint of the round rod 5 and the square rod 6;
the round rods 5 and the square rods 6 are intersected on the plane of the central plane of the upper cabin top plate 4, the middle cabin middle layer plate 12 or the lower cabin bottom plate 13;
the stringers 9 are arranged on the outer surface of the square bar 6 or the upper cabin roof 4 or the middle cabin middle layer plate 12 or the lower cabin floor 13;
the embedded part 17 is arranged inside the round rod 5 and the square rod 6, and the embedded part 17 completely or partially covers the inner surfaces of the round rod 5 and the square rod 6; the external pasting piece 8 is arranged outside the round rod 5 and the square rod 6, and the external pasting piece 8 completely or partially covers the joint of the round rod 5 and the square rod 6.
Preferably, the partition member 10 includes any one of:
-a median bulkhead piece;
-a lower deck bulkhead piece;
the cabin related part comprises any one of the following components:
-upper nacelle body related components;
-the middle compartment body related components;
-lower nacelle body related components.
Preferably, the upper cabin roof 4, the middle cabin middle layer plate 12 and the lower cabin bottom plate 13 are provided with aluminum alloy skin aluminum honeycomb sandwich layers;
the joint 7 is a carbon fiber joint 7;
the round rod 5 is a carbon fiber round rod 5;
the square rod 6 is a carbon fiber square rod 6;
the stringer 9 is a carbon fiber stringer 9;
the embedded part 17 is an aluminum alloy embedded part 17;
the outer piece 8 is an aluminum alloy outer piece 8.
Preferably, the upper cabin roof 4, the joint 7, the round rod 5, the square rod 6, the stringer 9, the embedded part 17 and the external part 8 are glued into the upper cabin 1 by using a cross-linking agent;
the middle cabin middle layer plate 12, the partition plate 10, the joint 7, the round rod 5, the square rod 6, the stringer 9, the embedded part 17 and the external pasting part 8 are glued into the middle cabin 2 by adopting a cross-linking agent;
the lower cabin bottom plate 13, the partition plate pieces 10, the joints 7, the round rods 5, the square rods 6, the stringers 9, the embedded pieces 17 and the external sticking pieces 8 are glued into the lower cabin 3 by adopting a cross-linking agent.
The invention provides a manufacturing method of a trapezoidal satellite structure suitable for a radar antenna, which comprises the following steps: an upper cabin forming step, a middle cabin forming step, a lower cabin forming step and a side plate connecting step;
upper cabin forming: gluing an upper cabin top plate 4, a joint 7, a round rod 5, a square rod 6, a stringer 9, an embedded part 17 and an external pasting part 8 into an upper cabin 1 by adopting a cross-linking agent; the upper cabin roof 4 is arranged on the lower bottom surface of the upper cabin 1;
a middle cabin forming step: gluing a middle cabin middle layer plate 12, a middle cabin partition plate piece 10, a joint 7, a round rod 5, a square rod 6, a stringer 9, an embedded piece 17 and an external pasting piece 8 into a middle cabin 2 by using a cross-linking agent, wherein the middle cabin middle layer plate 12 is arranged on the lower surface of the middle cabin 2, and the plane of the center plane of the partition plate piece 10 is vertical to the lower surface of the middle cabin 2;
a lower cabin forming step: bonding a lower cabin bottom plate 13, a lower cabin partition plate piece, a joint 7, a round rod 5, a square rod 6, a stringer 9, an embedded part 17 and an external pasting piece 8 into a lower cabin 3 by adopting a cross-linking agent, wherein the lower cabin bottom plate 13 is arranged on the lower surface of the lower cabin 3, and the plane of the central plane of the partition plate piece 10 is vertical to the lower surface of the lower cabin 3;
a side plate connecting step: the first side plate 15 and the second side plate 16 are attached to the upper compartment 1, the middle compartment 2 and the lower compartment 3 by screws.
Preferably, the partition member 10 includes: a middle compartment partition plate and a lower compartment partition plate;
the partition plate adopts: a first divider member 101 and a second divider member 102;
the plane of the central plane of the first partition plate member 101 is intersected with the plane of the central plane of the second bottom plate 102;
the joint 7 is arranged at the joint of the round rod 5 and the square rod 6;
the round rods 5 and the square rods 6 are intersected on the plane of the central plane of the upper cabin top plate 4, the middle cabin middle layer plate 12 or the lower cabin bottom plate 13;
the stringers 9 are arranged on the outer surface of the square bar 6 or on the upper cabin roof 4 or on the middle cabin middle layer plate 12 or on the lower cabin floor 13;
the embedded part 17 is arranged inside the round rod 5 and the square rod 6, and the embedded part 17 completely or partially covers the inner surfaces of the round rod 5 and the square rod 6;
the external pasting piece 8 is arranged outside the round rod 5 and the square rod 6, and the external pasting piece 8 completely or partially covers the joint of the round rod 5 and the square rod 6;
the upper cabin roof 4, the middle cabin middle layer plate 12 and the lower cabin bottom plate 13 are provided with aluminum alloy skin aluminum honeycomb interlayers;
the joint 7 is a carbon fiber joint 7;
the round rod 5 is a carbon fiber round rod 5;
the square rod 6 is a carbon fiber square rod 6;
the stringer 9 is a carbon fiber stringer 9;
the embedded part 17 is an aluminum alloy embedded part 17;
the outer piece 8 is an aluminum alloy outer piece 8.
Compared with the prior art, the invention has the following beneficial effects:
1. the reliable installation of the synthetic aperture radar antenna is ensured, and the mass center of the whole satellite and the response of the synthetic aperture radar antenna can be reduced;
2. the fundamental frequency of the whole satellite can meet the requirements of a carrier rocket and the thermal dimensional stability of the whole satellite can meet the detection accuracy index requirements of a synthetic aperture radar satellite;
3. the invention has reasonable combination, and can achieve ideal effect when applied to the satellite structure of the large-size synthetic aperture radar antenna which can be folded in China.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic structural view of the present invention.
Fig. 2 is an exploded schematic view of the upper, middle and lower compartments provided by the present invention.
Fig. 3 is a schematic composition diagram of the upper deck provided by the present invention.
Fig. 4 is a schematic diagram of the composition of the middle compartment provided by the present invention.
Fig. 5 is a schematic view of the composition of the lower chamber provided by the present invention.
FIG. 6 is a schematic view of the front and rear side plates and the left and right side plates according to the present invention.
Fig. 7 is a schematic composition diagram of a carbon fiber joint and an aluminum alloy embedded part thereof provided by the invention.
In the figure:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, 2, 3, 4, 5, 6 and 7, the invention provides a trapezoidal satellite structure suitable for a radar antenna, comprising: a cabin, a first side plate 15 and a second side plate 16;
the cabin body comprises: an upper cabin 1, a middle cabin 2 and a lower cabin 3;
the upper cabin 1, the middle cabin 2 and the lower cabin 3 are connected in sequence;
the upper cabin 1, the middle cabin 2 and the lower cabin 3 are of a trapezoidal structure;
the lower surface of the upper cabin 1 is connected with the upper surface of the middle cabin 2, and the upper surface of the middle cabin 2 completely or partially covers the lower surface of the upper cabin 1;
the lower surface of the middle cabin 2 is connected with the upper surface of the lower cabin 3, and the upper surface of the lower cabin 3 completely or partially covers the lower surface of the middle cabin 2;
the first side plate 15 is attached to the side surfaces of the upper cabin 1, the middle cabin 2 and the lower cabin 3, and the second side plate 16 is attached to the side surfaces of the upper cabin 1, the middle cabin 2 and the lower cabin 3;
the plane of the central plane of the first side plate 15 intersects the plane of the central plane of the second side plate 16.
Preferably, the upper deck 1 comprises an upper deck roof 4, a deck-related part;
the upper cabin roof 4 is arranged on the lower bottom surface of the upper cabin 1, the cabin related part is arranged above the upper cabin roof 4, and the cabin related part is arranged between the upper bottom surface and the lower bottom surface of the upper cabin 1 or on the lower bottom surface of the upper cabin 1.
Preferably, the middle compartment 2 comprises a middle compartment middle deck 12, a partition member and a compartment body-related part;
the middle cabin middle layer plate 12 is arranged on the lower surface of the middle cabin 2, and the plane of the central plane of the partition plate is vertical to the lower surface of the middle cabin 2;
the cabin-related part is arranged above the middle cabin middle layer plate 12, and the cabin-related part is arranged between the upper bottom surface and the lower bottom surface of the middle cabin 2 or on the lower bottom surface of the middle cabin 2.
Preferably, said lower compartment 3 comprises: a lower deck floor 13, a partition member and a deck-related part;
the lower cabin bottom plate 13 is arranged on the lower surface of the lower cabin 3, and the plane of the central plane of the partition plate is vertical to the lower surface of the lower cabin 3;
the cabin-related part is arranged above the lower cabin bottom plate 13;
the cabin-related part is arranged between the upper bottom surface and the lower bottom surface of the lower cabin 3 or on the lower bottom surface of the lower cabin 3.
Preferably, the partition member 10 employs: a first divider member 101 and a second divider member 102;
the plane of the central plane of the first partition plate member 101 is intersected with the plane of the central plane of the second bottom plate 102;
the cabin body related parts adopt: the joint 7, the round rod 5, the square rod 6, the purlins 9, the embedded part 17 and the external pasted part 8;
the joint 7 is arranged at the joint of the round rod 5 and the square rod 6;
the round rods 5 and the square rods 6 are intersected on the plane of the central plane of the upper cabin top plate 4, the middle cabin middle layer plate 12 or the lower cabin bottom plate 13;
the stringers 9 are arranged on the outer surface of the square bar 6 or the upper cabin roof 4 or the middle cabin middle layer plate 12 or the lower cabin floor 13;
the embedded part 17 is arranged inside the round rod 5 and the square rod 6, and the embedded part 17 completely or partially covers the inner surfaces of the round rod 5 and the square rod 6; the external pasting piece 8 is arranged outside the round rod 5 and the square rod 6, and the external pasting piece 8 completely or partially covers the joint of the round rod 5 and the square rod 6.
Preferably, the partition member 10 includes any one of:
-a median bulkhead piece;
-a lower deck bulkhead piece;
the cabin related part comprises any one of the following components:
-upper nacelle body related components;
-the middle compartment body related components;
-lower nacelle body related components.
Preferably, the upper cabin roof 4, the middle cabin middle layer plate 12 and the lower cabin bottom plate 13 are provided with aluminum alloy skin aluminum honeycomb sandwich layers;
the joint 7 is a carbon fiber joint 7;
the round rod 5 is a carbon fiber round rod 5;
the square rod 6 is a carbon fiber square rod 6;
the stringer 9 is a carbon fiber stringer 9;
the embedded part 17 is an aluminum alloy embedded part 17;
the outer piece 8 is an aluminum alloy outer piece 8.
Preferably, the upper cabin roof 4, the joint 7, the round rod 5, the square rod 6, the stringer 9, the embedded part 17 and the external part 8 are glued into the upper cabin 1 by using a cross-linking agent;
the middle cabin middle layer plate 12, the partition plate 10, the joint 7, the round rod 5, the square rod 6, the stringer 9, the embedded part 17 and the external pasting part 8 are glued into the middle cabin 2 by adopting a cross-linking agent;
the lower cabin bottom plate 13, the partition plate pieces 10, the joints 7, the round rods 5, the square rods 6, the stringers 9, the embedded pieces 17 and the external sticking pieces 8 are glued into the lower cabin 3 by adopting a cross-linking agent.
As shown in fig. 3, the upper cabin 1 is mainly formed by 1 upper cabin top plate 4, 12 carbon fiber joints 7, 10 carbon fiber round rods 5, 13 carbon fiber square rods 6, 4 carbon fiber stringers 9, aluminum alloy embedded parts 17 of a plurality of carbon fiber joints and rod parts, and a plurality of aluminum alloy externally attached parts 8 which are positioned by special tools and then glued by Redux420 adhesive.
As shown in fig. 4, the middle tank 2 is composed of 1 middle tank middle layer plate 12, 3 middle tank partition plate members 10, 10 carbon fiber joints 7, 8 carbon fiber round rods 5, 6 carbon fiber square rods 6, 12 carbon fiber stringers 9, a plurality of aluminum alloy embedded members 17 of the carbon fiber joints and the rod members, and a plurality of aluminum alloy externally attached members 8.
As shown in fig. 5, the lower chamber 3 is composed of 1 lower chamber including a lower chamber bottom plate 13, 5 lower chamber partition plate members 14, 14 carbon fiber joints 7, 12 carbon fiber round rods 5, 10 carbon fiber square rods 6, 20 carbon fiber stringers 9, a plurality of aluminum alloy embedded members 17 of carbon fiber joints and rod members, and a plurality of aluminum alloy externally attached members 8.
As shown in fig. 6, the first side plate 15 is a front and rear side plate, and the second side plate 16 is a left and right side plate.
As shown in fig. 7, the aluminum alloy insert 17 is provided inside the carbon fiber connector 7.
The invention provides a manufacturing method of a trapezoidal satellite structure suitable for a radar antenna, which comprises the following steps: an upper cabin forming step, a middle cabin forming step, a lower cabin forming step and a side plate connecting step;
upper cabin forming: gluing an upper cabin top plate 4, a joint 7, a round rod 5, a square rod 6, a stringer 9, an embedded part 17 and an external pasting part 8 into an upper cabin 1 by adopting a cross-linking agent; the upper cabin roof 4 is arranged on the lower bottom surface of the upper cabin 1;
a middle cabin forming step: gluing a middle cabin middle layer plate 12, a middle cabin partition plate piece 10, a joint 7, a round rod 5, a square rod 6, a stringer 9, an embedded piece 17 and an external pasting piece 8 into a middle cabin 2 by using a cross-linking agent, wherein the middle cabin middle layer plate 12 is arranged on the lower surface of the middle cabin 2, and the plane of the center plane of the partition plate piece 10 is vertical to the lower surface of the middle cabin 2;
a lower cabin forming step: bonding a lower cabin bottom plate 13, a lower cabin partition plate 14, a joint 7, a round rod 5, a square rod 6, a stringer 9, an embedded part 17 and an external pasting part 8 into a lower cabin 3 by adopting a cross-linking agent, wherein the lower cabin bottom plate 13 is arranged on the lower surface of the lower cabin 3, and the plane of the central plane of the partition plate 10 is vertical to the lower surface of the lower cabin 3;
a side plate connecting step: the first side plate 15 and the second side plate 16 are attached to the upper compartment 1, the middle compartment 2 and the lower compartment 3 by screws.
Preferably, the partition member 10 includes: middle and lower deck bulkhead pieces 14;
the partition plate adopts: a first divider member 101 and a second divider member 102;
the plane of the central plane of the first partition plate member 101 is intersected with the plane of the central plane of the second bottom plate 102;
the joint 7 is arranged at the joint of the round rod 5 and the square rod 6;
the round rods 5 and the square rods 6 are intersected on the plane of the central plane of the upper cabin top plate 4, the middle cabin middle layer plate 12 or the lower cabin bottom plate 13;
the stringers 9 are arranged on the outer surface of the square bar 6 or on the upper cabin roof 4 or on the middle cabin middle layer plate 12 or on the lower cabin floor 13;
the embedded part 17 is arranged inside the round rod 5 and the square rod 6, and the embedded part 17 completely or partially covers the inner surfaces of the round rod 5 and the square rod 6;
the external pasting piece 8 is arranged outside the round rod 5 and the square rod 6, and the external pasting piece 8 completely or partially covers the joint of the round rod 5 and the square rod 6;
the upper cabin roof 4, the middle cabin middle layer plate 12 and the lower cabin bottom plate 13 are provided with aluminum alloy skin aluminum honeycomb interlayers;
the joint 7 is a carbon fiber joint 7;
the round rod 5 is a carbon fiber round rod 5;
the square rod 6 is a carbon fiber square rod 6;
the stringer 9 is a carbon fiber stringer 9;
the embedded part 17 is an aluminum alloy embedded part 17;
the outer piece 8 is an aluminum alloy outer piece 8.
Specifically, in one embodiment, the method for manufacturing the trapezoidal satellite structure suitable for the radar antenna includes:
and (3) an upper cabin forming step, namely gluing 1 upper cabin top plate 4, 12 carbon fiber joints 7, 10 carbon fiber round rods 5, 13 carbon fiber square rods 6, 4 carbon fiber purlins 9, a plurality of carbon fiber joints, aluminum alloy embedded parts 17 of rod pieces and a plurality of externally-adhered aluminum alloy parts 8 into the upper cabin 1 by adopting Redux420 adhesive after being positioned by special tools. (ii) a
A middle cabin forming step, namely on the basis of the upper cabin forming step, gluing 1 middle cabin middle layer plate 12, 3 middle cabin partition plate pieces 10, 10 carbon fiber joints 7, 8 carbon fiber round rods 5, 6 carbon fiber square rods 6, 12 carbon fiber stringers 9, aluminum alloy embedded pieces 17 of a plurality of carbon fiber joints and rod pieces, a plurality of externally-adhered aluminum alloy pieces 8 and the upper cabin into a combination body of the upper cabin 1 and the middle cabin 2 by Redux420 adhesive after being positioned by special tools;
and a lower cabin forming step, namely on the basis of the middle cabin forming step, gluing 1 lower cabin comprising a lower cabin bottom plate 13, 5 lower cabin partition plate pieces 14, 14 carbon fiber joints 7, 12 carbon fiber round rods 5, 10 carbon fiber square rods 6 and 20 carbon fiber stringers 9, aluminum alloy embedded pieces 17 of a plurality of carbon fiber joints and rod pieces, a plurality of externally attached aluminum alloy pieces 8, an upper cabin and a middle cabin into a combination of the upper cabin 1, the middle cabin 2 and the lower cabin 3 by Redux420 adhesive after being positioned by special tools.
And a side plate connecting step, namely connecting 4 front and rear side plates 15 and 4 left and right side plates 16 to the upper cabin 1, the middle cabin 2 and the lower cabin 3 through screws to form the whole trapezoidal satellite structure on the basis of the lower cabin forming step.
The invention can ensure the reliable installation of the synthetic aperture radar antenna and can reduce the mass center of the whole satellite and the response of the synthetic aperture radar antenna; the invention can ensure that the fundamental frequency of the whole satellite meets the requirements of a carrier rocket and the thermal dimension stability of the whole satellite meets the detection precision index requirements of a synthetic aperture radar satellite; the invention has reasonable combination, and can achieve ideal effect when applied to the foldable large-size synthetic aperture radar antenna satellite structure in China.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A trapezoidal satellite structure adapted for use with a radar antenna, comprising: the cabin body, a first side plate (15) and a second side plate (16);
the cabin body comprises: an upper cabin (1), a middle cabin (2) and a lower cabin (3);
the upper cabin (1), the middle cabin (2) and the lower cabin (3) are connected in sequence;
the upper cabin (1), the middle cabin (2) and the lower cabin (3) are of a trapezoidal structure;
the lower surface of the upper cabin (1) is connected with the upper surface of the middle cabin (2), and the upper surface of the middle cabin (2) completely or partially covers the lower surface of the upper cabin (1);
the lower surface of the middle cabin (2) is connected with the upper surface of the lower cabin (3), and the upper surface of the lower cabin (3) completely or partially covers the lower surface of the middle cabin (2);
the first side plate (15) is attached to the side surfaces of the upper cabin (1), the middle cabin (2) and the lower cabin (3), and the second side plate (16) is attached to the side surfaces of the upper cabin (1), the middle cabin (2) and the lower cabin (3);
the plane of the central plane of the first side plate (15) is intersected with the plane of the central plane of the second side plate (16).
2. The trapezoidal satellite structure adapted for radar antennas of claim 1, characterized in that said upper tank (1) comprises an upper tank ceiling (4), a tank related part;
the upper cabin roof (4) is arranged on the lower bottom surface of the upper cabin (1), the cabin related part is arranged above the upper cabin roof (4), and the cabin related part is arranged between the upper bottom surface and the lower bottom surface of the upper cabin (1) or on the lower bottom surface of the upper cabin (1).
3. The trapezoidal satellite structure adapted for radar antennas of claim 1, characterized in that said middle compartment (2) comprises a middle compartment middle plate (12), a partition and a compartment body related part;
the middle cabin middle layer plate (12) is arranged on the lower surface of the middle cabin (2), and the plane of the central plane of the partition plate is vertical to the lower surface of the middle cabin (2);
the related part of the cabin body is arranged above a middle cabin middle layer plate (12), and the related part of the cabin body is arranged between the upper bottom surface and the lower bottom surface of the middle cabin (2) or on the lower bottom surface of the middle cabin (2).
4. Trapezoidal satellite structure suitable for radar antennas, according to claim 1, characterized in that said lower chamber (3) comprises: a lower cabin floor (13), a partition and a cabin-related part;
the lower cabin bottom plate (13) is arranged on the lower surface of the lower cabin (3), and the plane of the central plane of the partition plate is vertical to the lower surface of the lower cabin (3);
the cabin related part is arranged above the lower cabin bottom plate (13);
the related part of the cabin body is arranged between the upper bottom surface and the lower bottom surface of the lower cabin (3) or on the lower bottom surface of the lower cabin (3).
5. Trapezoidal satellite structure suitable for radar antenna according to any one of claims 2 to 4,
the partition plate member (10) adopts: a first divider member (101) and a second divider member (102);
the plane of the central plane of the first partition plate member (101) is intersected with the plane of the central plane of the second bottom plate (102);
the cabin body related parts adopt: the device comprises a joint (7), a round rod (5), a square rod (6), a stringer (9), an embedded part (17) and an external pasting part (8);
the joint (7) is arranged at the joint of the round rod (5) and the square rod (6);
the round rod (5) and the square rod (6) are intersected on the plane of the central plane of the upper cabin top plate (4), the middle cabin middle layer plate (12) or the lower cabin bottom plate (13);
the stringers (9) are arranged on the outer surface of the square rod (6) or the upper cabin top plate (4) or the middle cabin middle plate (12) or the lower cabin bottom plate (13);
the embedded part (17) is arranged inside the round rod (5) and the square rod (6), and the embedded part (17) completely or partially covers the inner surfaces of the round rod (5) and the square rod (6); the external pasting piece (8) is arranged outside the round rod (5) and the square rod (6), and the external pasting piece (8) completely or partially covers the joint of the round rod (5) and the square rod (6).
6. Trapezoidal satellite structure adapted for radar antennas, according to claim 5, characterized in that said baffle element (10) comprises any one of the following:
-a median bulkhead piece;
-a lower deck bulkhead piece;
the cabin related part comprises any one of the following components:
-upper nacelle body related components;
-the middle compartment body related components;
-lower nacelle body related components.
7. The trapezoidal satellite structure suitable for radar antennas of claim 5, characterized in that the upper tank ceiling (4), the middle tank middle plate (12) and the lower tank bottom plate (13) have an aluminum alloy skin aluminum honeycomb sandwich;
the joint (7) is a carbon fiber joint (7);
the round rod (5) is a carbon fiber round rod (5);
the square rod (6) is a carbon fiber square rod (6);
the stringer (9) is a carbon fiber stringer (9);
the embedded part (17) is an aluminum alloy embedded part (17);
the external pasting piece (8) is an aluminum alloy external pasting piece (8).
8. The trapezoidal satellite structure suitable for radar antennas of claim 5, characterized in that the upper cabin roof (4), the joints (7), the round rods (5), the square rods (6), the stringers (9), the inner burial (17) and the outer stickers (8) are glued to the upper cabin (1) with a cross-linking agent;
the middle cabin middle layer plate (12), the partition plate piece (10), the joint (7), the round rod (5), the square rod (6), the stringer (9), the embedded piece (17) and the external pasting piece (8) are glued into the middle cabin (2) by adopting a cross-linking agent;
the lower cabin bottom plate (13), the partition plate piece (10), the joint (7), the round rod (5), the square rod (6), the stringer (9), the embedded piece (17) and the external pasting piece (8) are glued into the lower cabin (3) by adopting a cross-linking agent.
9. A manufacturing method of a trapezoidal satellite structure suitable for a radar antenna is characterized by comprising the following steps: an upper cabin forming step, a middle cabin forming step, a lower cabin forming step and a side plate connecting step;
upper cabin forming: gluing an upper cabin top plate (4), a joint (7), a round rod (5), a square rod (6), a stringer (9), an embedded part (17) and an external part (8) into an upper cabin (1) by using a cross-linking agent; the upper cabin top plate (4) is arranged on the lower bottom surface of the upper cabin (1);
a middle cabin forming step: bonding a middle cabin middle layer plate (12), a middle cabin partition plate piece (10), a joint (7), a round rod (5), a square rod (6), a stringer (9), an embedded piece (17) and an external pasting piece (8) into a middle cabin (2) by adopting a cross-linking agent, wherein the middle cabin middle layer plate (12) is arranged on the lower surface of the middle cabin (2), and the plane of the center plane of the partition plate piece (10) is vertical to the lower surface of the middle cabin (2);
a lower cabin forming step: bonding a lower cabin bottom plate (13), a lower cabin partition plate piece, a joint (7), a round rod (5), a square rod (6), a stringer (9), an embedded piece (17) and an external pasting piece (8) into a lower cabin (3) by adopting a cross-linking agent, wherein the lower cabin bottom plate (13) is arranged on the lower surface of the lower cabin (3), and the plane of the center plane of the partition plate piece (10) is vertical to the lower surface of the lower cabin (3);
a side plate connecting step: the first side plate (15) and the second side plate (16) are connected to the upper cabin (1), the middle cabin (2) and the lower cabin (3) through screws.
10. Method for manufacturing a trapezoidal satellite structure suitable for a radar antenna according to claim 9, wherein the partition member (10) comprises: a middle compartment partition plate and a lower compartment partition plate;
the partition plate adopts: a first divider member (101) and a second divider member (102);
the plane of the central plane of the first partition plate member (101) is intersected with the plane of the central plane of the second bottom plate (102);
the joint (7) is arranged at the joint of the round rod (5) and the square rod (6);
the round rod (5) and the square rod (6) are intersected on the plane of the central plane of the upper cabin top plate (4), the middle cabin middle layer plate (12) or the lower cabin bottom plate (13);
the stringers (9) are arranged on the outer surface of the square rod (6) or on the upper cabin top plate (4) or on the upper or lower cabin bottom plate (13) of the middle cabin middle layer plate (12);
the embedded part (17) is arranged inside the round rod (5) and the square rod (6), and the embedded part (17) completely or partially covers the inner surfaces of the round rod (5) and the square rod (6);
the external pasting piece (8) is arranged outside the round rod (5) and the square rod (6), and the external pasting piece (8) completely or partially covers the joint of the round rod (5) and the square rod (6);
the upper cabin top plate (4), the middle cabin middle layer plate (12) and the lower cabin bottom plate (13) are provided with aluminum alloy skin aluminum honeycomb interlayers;
the joint (7) is a carbon fiber joint (7);
the round rod (5) is a carbon fiber round rod (5);
the square rod (6) is a carbon fiber square rod (6);
the stringer (9) is a carbon fiber stringer (9);
the embedded part (17) is an aluminum alloy embedded part (17);
the external pasting piece (8) is an aluminum alloy external pasting piece (8).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910888298.7A CN110683077A (en) | 2019-09-19 | 2019-09-19 | Trapezoidal satellite structure suitable for radar antenna and manufacturing method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910888298.7A CN110683077A (en) | 2019-09-19 | 2019-09-19 | Trapezoidal satellite structure suitable for radar antenna and manufacturing method |
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| CN110683077A true CN110683077A (en) | 2020-01-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910888298.7A Pending CN110683077A (en) | 2019-09-19 | 2019-09-19 | Trapezoidal satellite structure suitable for radar antenna and manufacturing method |
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| RU230876U1 (en) * | 2024-10-24 | 2024-12-23 | Акционерное Общество Научно-Производственный Концерн "Барл" | Spacecraft for integrated observation of the Earth's surface in the visible, infrared and ultra-high frequency ranges "EOS-R" |
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