CN104787359A - Small monitoring satellite structure - Google Patents
Small monitoring satellite structure Download PDFInfo
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- CN104787359A CN104787359A CN201410839174.7A CN201410839174A CN104787359A CN 104787359 A CN104787359 A CN 104787359A CN 201410839174 A CN201410839174 A CN 201410839174A CN 104787359 A CN104787359 A CN 104787359A
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- support beam
- bracing frame
- support
- trapezoidal bracing
- satellite platform
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Abstract
The invention discloses a small monitoring satellite structure. The small monitoring satellite structure comprises a front trapezoidal support frame, a back trapezoidal support frame, a first support beam, a second support beam, a third support beam and a fourth support beam, wherein the first support beam, the second support beam, the third support beam and the fourth support beam are uniformly distributed and fixed in the peripheral direction of a satellite main camera; and the front ends of the first support beam, the second support beam, the third support beam and the fourth support beam are respectively connected with the front trapezoidal support frame, and the back ends are respectively connected with the back trapezoidal support frame. The small monitoring satellite structure solves the limitations of a small monitoring satellite on the volume and the mass and the high requirements on the layout and mechanical performance; and in addition, the small monitoring satellite structure is more compact in layout and better in mechanical performance under the precondition of synchronously fixing a guide camera and a main camera.
Description
Technical field
The present invention relates to aerospace vehicle, particularly a kind of configuration of miniaturized surveillance satellite.
Background technology
1m camera satellite is the miniaturized surveillance satellite that China is grinding, have lightweight, volume is little, can rapid fire, possess the feature such as quick maneuverability in-orbit.Due to Small Launch Vehicle transmission envelop size and weight limits, under the prerequisite simultaneously can fixing guiding camera and principal phase machine, layout is compacter, mechanical property is better to require satellite configuration.
In this specification sheets, miniaturized surveillance satellite platform configuration refers to the satellite platform configuration for 1m camera satellite.
Summary of the invention
The problem that the present invention solves is miniaturized surveillance satellite to the high request of volume, matter quantitative limitation and layout, mechanical property; For solving described problem, the invention provides a kind of miniaturized surveillance satellite configuration.
Miniaturized surveillance satellite platform configuration provided by the present invention comprises: front trapezoidal bracing frame, rear trapezoidal bracing frame, the first support beam, the second support beam, the 3rd support beam, the 4th support beam; Described first support beam, the second support beam, the 3rd support beam, the 4th support beam are uniformly distributed and are fixed on the circumference of satellite principal phase machine; The front end of described first support beam, the second support beam, the 3rd support beam, the 4th support beam is connected with front trapezoidal bracing frame respectively, rear end is connected with rear trapezoidal bracing frame respectively.
Further, described front trapezoidal bracing frame center is the first circular port, and principal phase machine is fixed on described first circular port, and there is the second circular port described first circular port side, and described second circular port is used for fixing guiding camera.
Further, measure-alike between described first support beam, the second support beam, the 3rd support beam, the 4th support beam, be spear type support, described spear type support comprises the bearing surface that section is order font; Described principal phase machine is fixed in annular arrangement sleeve, annular arrangement sleeve has attachment face and described bearing surface cooperatively interact and is fixed.
Further, described first support beam, the second support beam, the 3rd support beam, the 4th support beam two ends have the round end for lifting respectively and are positioned at the screw attachment face of described round end root; Described front trapezoidal bracing frame, rear trapezoidal bracing frame there is the opening coordinated with described round end, after described round end is stuck in described opening, be fixedly connected with front trapezoidal bracing frame respectively by screw one end by the first support beam, the second support beam, the 3rd support beam, the 4th support beam, the other end is fixedly connected with rear trapezoidal bracing frame respectively.
Further, also comprise at least two lateral support framves, described lateral support frame installation direction is parallel to the high direction of front trapezoidal bracing frame, and described lateral support frame connects between adjacent spear type support.
Further, described lateral support frame is class I shape aluminum alloy support beam, and described lateral support frame two ends end face is designed with hole for hoist, and is provided with lifting adaptor.
Further, described lateral support frame is i section aluminium alloy structure.
Further, forward and backward trapezoidal bracing frame adopts hollow out to design under the prerequisite reaching functional requirement and rigidity requirement, and for six outer panels of fixing miniaturized surveillance satellite platform, top panel is for installing solar cell.
Further, the inner hollow out of described spear type support beam, bearing surface adopts the design of order font, and two ends end face is designed with hole for hoist.
Advantage of the present invention comprises:
Rational overall configuration, in overall configuration, cross-sectional plane adopts isosceles trapezoid design, top panel solar cell placement.
For expendable weight, multiple part have employed hollow out and adds beam design, under the prerequisite of expendable weight, ensure that global stiffness.
The Integration Design of part, such as front support stand supports outside shade, secures five outer panels, supports and guides camera and four support beams; This Integration Design makes satellite platform compact in design.
Lifting adaptor and hole for hoist for hoisting Design, not only practical, and highly versatile.
Design class I-shaped support beam not only further enhancing satellite global stiffness, and effectively reduces the distortion of principal phase machine set collar as the transmission channels of lifting and the power such as vibration, protects principal phase machine.
Accompanying drawing explanation
Fig. 1 is the birds-eye view of the miniaturized surveillance satellite configuration that the embodiment of the present invention provides.
Fig. 2 is the transparent view of the miniaturized surveillance satellite configuration that the embodiment of the present invention provides.
Fig. 3 is the front trapezoidal bracing frame schematic diagram of the miniaturized surveillance satellite configuration that the embodiment of the present invention provides.
Fig. 4 is a support beam schematic diagram in the miniaturized surveillance satellite configuration that provides of the embodiment of the present invention.
Fig. 5 is a principal phase machine clamping rings schematic diagram in the miniaturized surveillance satellite configuration that provides of the embodiment of the present invention.
Fig. 6 is lateral support frame schematic diagram in the miniaturized surveillance satellite configuration that provides of the embodiment of the present invention.
Fig. 7 is the lifting adaptor schematic diagram in the miniaturized surveillance satellite configuration that provides of the embodiment of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing and embodiment, the present invention is described in further detail.
In conjunction with reference to figure 1 and Fig. 2, miniaturized surveillance satellite platform configuration provided by the present invention comprises: front trapezoidal bracing frame 9, rear trapezoidal bracing frame 7, first support beam 8, second support beam, the 3rd support beam, the 4th support beam; Described first support beam 8, second support beam, the 3rd support beam, the 4th support beam are uniformly distributed and are fixed on the circumference of satellite principal phase machine 3; The front end of described first support beam 8, second support beam, the 3rd support beam, the 4th support beam is connected with front trapezoidal bracing frame 9 respectively, rear end is connected with rear trapezoidal bracing frame 7 respectively, forms stable six stent configuration; Six surfaces of described configuration can install 6 outer panels respectively, each outer panels are all provided with lifting adaptor 2 for lifting.Wherein top panel 1 is installed the solar cell array on celestial body.The main material of described miniaturized surveillance satellite platform configuration is aluminum alloy materials, for increasing rigidity, can install aluminium honeycomb panel on support.
The front trapezoidal bracing frame of the miniaturized surveillance satellite configuration that the embodiment of the present invention provides and rear trapezoidal bracing frame are the isosceles trapezoid of hollow out, and the two is measure-alike, adopt the design of triangle hollow out; Two sides, the upper right corner is flange face, and fixed satellite guides the clip of camera and the shade of satellite principal phase machine respectively.There is a large amount of tapped bore fixing for outer panels at the edge of forward and backward trapezoidal bracing frame.
Trapezoidal bracing frame schematic diagram before the miniaturized surveillance satellite configuration that Fig. 3 provides for the embodiment of the present invention, described front trapezoidal bracing frame also comprises the first circular port 101 for installing satellite principal phase machine, guide camera 4(to see Fig. 1 for installing) the second circular port 102, and the opening 103 for being connected respectively with the first support beam, the second support beam, the 3rd support beam, the 4th support beam.In conjunction with reference to figure 4, described first support beam, the second support beam, the 3rd support beam, the 4th support beam size are equal; Adjacent supports beam is symmetrical about their midperpendicalar, and described first support beam, the second support beam, the 3rd support beam, the 4th support beam have for fixing round end and the screw attachment face being positioned at described round end root respectively at two ends; The round end of one end is stuck in the opening part of front trapezoidal bracing frame and is connected with front trapezoidal bracing frame screw by the screw attachment face of round end root; The round end of the other end is stuck in the opening part of rear trapezoidal bracing frame and is connected with rear trapezoidal bracing frame screw by the screw attachment face of round end root.Described round end has hole for hoist, the lifting adaptor shown in described hole for hoist and Fig. 7 with the use of.
With reference to figure 5, described satellite principal phase machine is socketed with principal phase machine clamping rings, described principal phase machine clamping rings is connected with satellite principal phase machine by screw; Described principal phase machine clamping rings is also evenly distributed with 4 groups of adapter plates, often organizes on adapter plate and is furnished with screw; In conjunction with reference to figure 4, described first support beam, the second support beam, the 3rd support beam, the 4th support beam are spear type support, described spear type support comprises the bearing surface 91 that section is order font, described bearing surface and described adapter plate match, by screw, described bearing surface and adapter plate are fixed, thus realize spear type support to the main camera support of satellite.Order word-lifting formula can expendable weight under the prerequisite ensureing rigidity.
For increasing the rigidity of configuration entirety, in a preferred embodiment of the invention, between adjacent spear type support, lateral support frame is installed.For expendable weight, as shown in Figure 2, in the present embodiment, the lateral support frame 6 being parallel to the high direction of front trapezoidal bracing frame is only installed.Described lateral support frame is I-shape construction.Described I-shaped structure adopts the design of shearing weight, and the placement of I-shaped more enhances the global stiffness stretching out direction of spear type support beam.Described I-shaped structure two ends are processed with the mating holes of lifting, and the transmission channels as power such as lifting and vibrations effectively reduces the distortion of principal phase machine set collar, protects principal phase machine.
In conjunction with reference to figure 5; the lifting adaptor of design can be arranged on described I-shaped structure easily, and serves the effect of auxiliary fixing outer panels, protects outer panels and is subject to outside frictionally damage less; also facilitate the lifting of satellite platform, more enhance the commonality of whole satellite platform.
To sum up, the invention solves the high request of miniaturized surveillance satellite to volume, matter quantitative limitation and layout, mechanical property, in addition, layout under the prerequisite guiding camera and principal phase machine is compacter, the better problem of mechanical property can fix simultaneously for miniaturized surveillance satellite configuration.
Although the present invention with preferred embodiment openly as above; but it is not for limiting the present invention; any those skilled in the art without departing from the spirit and scope of the present invention; the Method and Technology content of above-mentioned announcement can be utilized to make possible variation and amendment to technical solution of the present invention; therefore; every content not departing from technical solution of the present invention; the any simple modification done above embodiment according to technical spirit of the present invention, equivalent variations and modification, all belong to the protection domain of technical solution of the present invention.
Claims (8)
1. a miniaturized surveillance satellite platform configuration, is characterized in that, comprising: front trapezoidal bracing frame, rear trapezoidal bracing frame, the first support beam, the second support beam, the 3rd support beam, the 4th support beam; Described first support beam, the second support beam, the 3rd support beam, the 4th support beam are uniformly distributed and are fixed on the circumference of satellite principal phase machine; The front end of described first support beam, the second support beam, the 3rd support beam, the 4th support beam is connected with front trapezoidal bracing frame respectively, rear end is connected with rear trapezoidal bracing frame respectively.
2. according to a kind of miniaturized surveillance satellite platform configuration according to claim 1, it is characterized in that, described front trapezoidal bracing frame center is the first circular port, principal phase machine is fixed on described first circular port, there is the second circular port described first circular port side, and described second circular port is used for fixing guiding camera.
3. according to a kind of miniaturized surveillance satellite platform configuration according to claim 1, it is characterized in that, measure-alike between described first support beam, the second support beam, the 3rd support beam, the 4th support beam, be spear type support, described spear type support comprises the bearing surface that section is order font; Described principal phase machine is fixed in annular arrangement sleeve, and annular arrangement sleeve has attachment face, and the bearing surface of described attachment face and spear type support beam cooperatively interacts, and support beam is fixed on annular arrangement sleeve.
4. according to a kind of miniaturized surveillance satellite platform configuration according to claim 1, it is characterized in that, described first support beam, the second support beam, the 3rd support beam, the 4th support beam two ends have the round end for lifting respectively and are positioned at the screw attachment face of described round end root; Described front trapezoidal bracing frame, rear trapezoidal bracing frame there is the opening coordinated with described round end, after described round end is stuck in described opening, be fixedly connected with front trapezoidal bracing frame respectively by screw one end by the first support beam, the second support beam, the 3rd support beam, the 4th support beam, the other end is fixedly connected with rear trapezoidal bracing frame respectively.
5. according to a kind of miniaturized surveillance satellite platform configuration according to claim 3, it is characterized in that, also comprise at least two lateral support framves, described lateral support frame installation direction is parallel to the high direction of front trapezoidal bracing frame, and described lateral support frame connects between adjacent spear type support.
6. according to miniaturized surveillance satellite platform configuration according to claim 5, it is characterized in that, described lateral support frame is class I shape aluminum alloy support beam, and described lateral support frame two ends end face is designed with hole for hoist, and is provided with lifting adaptor.
7. according to a kind of miniaturized surveillance satellite platform configuration according to claim 1, it is characterized in that, forward and backward trapezoidal bracing frame adopts hollow out to design under the prerequisite reaching functional requirement and rigidity requirement, and for six outer panels of fixing miniaturized surveillance satellite platform, top panel is for installing solar cell.
8. according to miniaturized surveillance satellite platform configuration according to claim 3, it is characterized in that, the inner hollow out of described spear type support beam, bearing surface adopts the design of order font, and two ends end face is designed with hole for hoist.
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| CN201410839174.7A CN104787359B (en) | 2014-12-30 | 2014-12-30 | A kind of miniaturized surveillance satellite configuration |
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| CN201410839174.7A CN104787359B (en) | 2014-12-30 | 2014-12-30 | A kind of miniaturized surveillance satellite configuration |
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| CN104787359B CN104787359B (en) | 2018-01-19 |
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Cited By (4)
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|---|---|---|---|---|
| CN105775166A (en) * | 2016-03-30 | 2016-07-20 | 上海卫星工程研究所 | I-shaped satellite platform |
| CN105811071B (en) * | 2016-04-19 | 2018-06-15 | 吉林大学 | The support device and its assembly method of circular loop antenna battle array |
| CN109335023A (en) * | 2018-08-31 | 2019-02-15 | 南京理工大学 | A kind of no cable high density cube star and its assembly method |
| CN109524758A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of Multi-Function Antenna mounting platform |
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| CN103482082A (en) * | 2013-08-12 | 2014-01-01 | 上海卫星工程研究所 | Modular micro-satellite platform configuration |
| CN203806149U (en) * | 2014-05-06 | 2014-09-03 | 上海卫星工程研究所 | Hexagonal frame main bearing satellite structure |
| CN104071354A (en) * | 2014-05-28 | 2014-10-01 | 上海微小卫星工程中心 | Satellite casing and satellite using same |
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| FR2748256A1 (en) * | 1996-05-03 | 1997-11-07 | Motorola Inc | Utility load e.g. satellite in low earth orbit placing method |
| FR2789652A1 (en) * | 1999-02-16 | 2000-08-18 | Matra Marconi Space France | Telecommunications payload low orbit satellite configuration having lengthened trapezoidal body with small upper rigid panel holding satellite controls and larger lower panel holding payload. |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775166A (en) * | 2016-03-30 | 2016-07-20 | 上海卫星工程研究所 | I-shaped satellite platform |
| CN105811071B (en) * | 2016-04-19 | 2018-06-15 | 吉林大学 | The support device and its assembly method of circular loop antenna battle array |
| CN109524758A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of Multi-Function Antenna mounting platform |
| CN109335023A (en) * | 2018-08-31 | 2019-02-15 | 南京理工大学 | A kind of no cable high density cube star and its assembly method |
| CN109335023B (en) * | 2018-08-31 | 2020-10-27 | 南京理工大学 | Cable-free high-density cube star and assembling method thereof |
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| CN104787359B (en) | 2018-01-19 |
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