CN104477518A - Packaging box with active/passive temperature control combined control system - Google Patents
Packaging box with active/passive temperature control combined control system Download PDFInfo
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- CN104477518A CN104477518A CN201410643275.7A CN201410643275A CN104477518A CN 104477518 A CN104477518 A CN 104477518A CN 201410643275 A CN201410643275 A CN 201410643275A CN 104477518 A CN104477518 A CN 104477518A
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Abstract
The invention discloses a whole-spacecraft transport packaging box with an active/passive temperature control combined control system. The box body of the whole-spacecraft transport packaging box is divided into a packaging box bottom and a packaging box housing; the box wall is of a double-layer structure; an outer skin and a box housing framework are combined to form an airtight and rainproof cavity. A polyurethane foam board is arranged between skins; a thermal insulating layer is fixed on the inner surfaces of the skins; the passive temperature control is achieved; the active temperature control is realized by use of a closed-loop control system formed by a variable-frequency temperature control system and a temperature sensor; the temperature in the packaging box can be set arbitrarily within the range of 5-40 DEG C; in combination with a passive temperature control system, the temperature requirements within the whole process of remote sensing satellite transport are met and the accurate control on the temperatures within the range of 20+/-5 DEG C is realized.
Description
Technical field
The invention belongs to satellite packing box for transportation design field, be specifically related to a kind of main whole star transport package box of remote sensing class satellite being controlled to combine by dynamic temperature.
Background technology
Along with the development of spacecraft, the particularly development of high-resolution optical remote sensing satellite, microwave remote sensing satellite, satellite load is more and more higher to environmental requirement, requires that the temperature environment of spacecraft transportation is consistent with AIT hall environment, realizes the temperature objectives of 20 DEG C ± 5 DEG C under any environment.
Remote sensing satellite transports the transhipment and launch site transport that refer generally between factory building, and by transportation modes such as automobile, train and aircrafts, time span is generally 1 day ~ 3 days.The outer range of temperatures of packaging box is-40 DEG C ~ 50 DEG C, and temperature traverse is very big, and packing chest must have independently temperature to control and keeping system, meets transportation environment requirement.
At present, the packing chest of remote sensing satellite and other Platform Satellite generally carries out active temperature control by air-conditioning, does not generally have passive temperature control measure, and indivedual packing chest uses case clothing to carry out simply being controlled by dynamic temperature.May ~ August and November ~ March is when transporting, the requirement that temperature out of reach is 20 ± 5 DEG C; Civilian van cooler generally can only be lowered the temperature, and cannot carry out intensification at low temperatures and control, and more in outdoor temperature-40 DEG C of situations, cannot realize the requirement of packaging the temperature inside the box 20 DEG C ± 5 DEG C.
For the problems referred to above, propose a kind of remote sensing class satellite whole star transport package box temperature accuracy control method leading passive combination, take measures from active temperature control and passive temperature control two aspects, meet the temperature requirement of remote sensing satellite transportation.
Summary of the invention
The present invention seeks to propose a kind of main whole star transport package box of remote sensing class satellite being controlled to combine by dynamic temperature, be intended to solve the problem that in remote sensing satellite transportation, temperature does not meet the demands, the temperature realized in 20 ± 5 DEG C of remote sensing satellite transport overall process accurately controls.
To achieve these goals, present invention employs following technical scheme:
A kind of main whole star transport package box of remote sensing class satellite being controlled to combine by dynamic temperature, comprise at the bottom of case cover, case and spin manifold temperature key-course composition passive temperature system and active temperature control system, the tank wall of case cover is double-decker, jointly form airtight and rainproof cavity by inside panel one, exterior skin two with case cover skeleton, inside panel one and case cover frame welding form air tight housing; Exterior skin two and case cover skeleton are riveted, exterior skin two is bonding with the seam gluing of case cover skeleton, the thick polyurethane foam board of 80mm is filled to have passive heat insulation function between inside panel one, exterior skin two, the thick polyurethane foam board of 20mm is installed in packing chest cover inside, groove aluminium block is welded on inside panel one, polyurethane foam board covers the aluminium sheet that 0.5mm is thick, and aluminium sheet is fixed on groove aluminium block by self-plugging rivet;
It is double-decker at the bottom of case, inside panel three adopts welding manner to form airtight construction with skeleton at the bottom of case, rivet at the bottom of exterior skin four and case, the thick polyurethane foam board of 200mm is filled between skeleton at the bottom of case, at the bottom of case, the polyurethane foam board of inner mounting strap metallized film is to ensure the passive heat-insulating property of packing chest, contour bar flange at the bottom of case is equipped with, contour bar coordinates the flange of packaging box cover jointly to form sealing arrangement with seal ring, inside panel three be welded into as a whole after, again with frame welding at the bottom of case, wherein, active temperature controls to be form closed loop control system by frequency converting temperature control system and temperature sensor, to realize the setting arbitrarily of packaging the temperature inside the box 5-40 DEG C, by with passive temperature-controlling system in conjunction with work, accurately control with the temperature obtaining remote sensing satellite transport 20 ± 5 DEG C.
Wherein, active temperature control system refrigeration work consumption is 4000W, heats power 4000W, design temperature can between 5-40 DEG C free setting.
Wherein, active temperature control system is controlled by local control and notebook PC Long-distance Control two kinds of modes.
Wherein, covering one adopts the thick 5A06 aluminium sheet of 3mm, and covering two is the 5A06 aluminium sheet of thick 2mm.
Wherein, covering three and covering four are the 5A06 aluminium sheet that 5mm is thick.
The present invention can control whole for remote sensing satellite star transport package box temperature in 20 ± 5 DEG C, and can realize the setting of arbitrary temp in scope, realizes the environmental requirement of remote sensing satellite.
Accompanying drawing explanation
Fig. 1 is the whole luck of remote sensing satellite of the present invention defeated packaging box cover structure schematic diagram;
Fig. 2 is the whole luck of remote sensing satellite of the present invention defeated packaging box bottom structure schematic diagram;
Fig. 3 is remote sensing satellite of the present invention whole star transport package box passive temperature control heat-insulation layer schematic diagram.
Exterior skin at the bottom of skeleton, 15-case at the bottom of inside panel three, 14-case at the bottom of 1-inside panel one, 2-exterior skin two, 3-case cover skeleton, 4-case cover polyurethane foam board, the passive heat-insulation layer of 5-, 6-groove aluminium block, 7-self-plugging rivet, 8-heat-insulation layer cystosepiment, the thick aluminium sheet of 9-0.5mm, 10-sealing band, the contour bar of 11-, 12-case inner thermal insulating layer, 13-case.
Detailed description of the invention
What below introduce is detailed description of the invention as content of the present invention, further illustrates content of the present invention below by detailed description of the invention.Certainly, describe the content that following detailed description is only example different aspect of the present invention, and should not be construed as the restriction scope of the invention.
Being controlled by dynamic temperature of the whole star transport package box of remote sensing satellite of the present invention comprises the design of packaging box body structure, box sealing design, spin manifold temperature key-course designs.
As shown in Figure 1, the tank wall of case cover is double-decker, jointly forms airtight, rainproof cavity by inside panel 1, exterior skin 2 with case cover skeleton 3.Inside panel 1 adopts the thick 5A06 aluminium sheet of 3mm to weld with skeleton 3 to form air tight housing; Exterior skin 2 is that the 5A06 aluminium sheet of thick 2mm and skeleton 3 are riveted, and exterior skin 2 is bonding with the seam gluing of skeleton 3, plays rainproof effect, fills the thick polyurethane foam board of 80mm 4, have passive heat insulation function between inside panel 1, exterior skin 2.
As shown in Figure 2, be double-decker at the bottom of the case in packing chest of the present invention, inside panel 13 is the 5A06 aluminium sheet that 5mm is thick; Adopt welding manner to form airtight construction between each parts, rivet at the bottom of exterior skin 15 and case.Fill the thick polyurethane foam board of 200mm 12 between skeleton 14 at the bottom of case, at the bottom of case, the passive heat-insulation layer 5 of inner mounting strap metallized film, ensures the passive heat-insulating property of packing chest.Flange at the bottom of case is equipped with contour bar 11, contour bar 11 coordinates upper flange jointly to form sealing arrangement with seal ring 10.Inside panel 13 be welded into as a whole after, after school shape and stress relief, check the air-tightness of weld seam, inside panel 13 welds with skeleton 14 again.When inside panel 13 welds with skeleton 14, first by outside inside panel 13 with the intermittent weld of skeleton 14 periphery, then by inside panel 13 inner peripheral and skeleton 14 full weld (fillet weld), in welding process, control skin morph.Treat that casing inner covering welding is complete, after release stress, checked the air-tightness of weld seam by airtight test.
Fig. 3 is remote sensing satellite of the present invention whole star transport package box passive temperature control heat-insulation layer schematic diagram.Fig. 3 integral structure is the passive heat-insulation layer 5 in Fig. 1 and Fig. 2, for realizing better passive heat insulation effect, in packing chest cover inside, the thick polyurethane foam board 8 of 20mm is installed, installation method is that groove aluminium block 6 is welded on inside panel 1, cystosepiment 8 covers the thick aluminium sheet of 0.5mm 9, and aluminium sheet 9 is fixed on groove aluminium block 6 by self-plugging rivet 7.
Active temperature control system refrigeration work consumption: 4000W, heat power 4000W, design temperature can between 5-40 DEG C free setting, by this locality control and notebook PC Long-distance Control two kinds of modes carry out controlling, revising parameter, display system mode of operation etc.Temperature controlling system is carried out this locality by off-premises station and is controlled, and controller is controlled by long-range notebook PC, the mode of operation of the switch of control system, the working parameter arranging system, display do-nothing system and temperature.
The remote sensing class satellite whole star transport package box temperature accuracy control method of main passive combination comprises packing chest and is controlled by dynamic temperature control and active temperature.
Controlled to comprise the design of packaging box body structure by dynamic temperature, box sealing designs, spin manifold temperature key-course designs, can realize in packing chest, being filled with the high pure nitrogen that gauge pressure is 2000Pa, pressurize 24 hours, leak rate is not more than 150Pa/24h, by ensureing sealing structure, heat-insulation layer, structure particular design mode, realizing temperature and controlling.
Although give detailed description and explanation to the specific embodiment of the present invention above; but what should indicate is; we conception according to the present invention can carry out various equivalence change and amendment to above-mentioned embodiment; its function produced do not exceed that specification sheets and accompanying drawing contain yet spiritual time, all should within protection scope of the present invention.
Claims (5)
1. the main whole star transport package box of remote sensing class satellite being controlled to combine by dynamic temperature, comprise at the bottom of case cover, case and spin manifold temperature key-course composition passive temperature system and active temperature control system, the tank wall of case cover is double-decker, jointly form airtight and rainproof cavity by inside panel one, exterior skin two with case cover skeleton, inside panel one and case cover frame welding form air tight housing; Exterior skin two and case cover skeleton are riveted, exterior skin two is bonding with the seam gluing of case cover skeleton, the thick polyurethane foam board of 80mm is filled to have passive heat insulation function between inside panel one, exterior skin two, the thick polyurethane foam board of 20mm is installed in packing chest cover inside, groove aluminium block is welded on inside panel one, polyurethane foam board covers the aluminium sheet that 0.5mm is thick, and aluminium sheet is fixed on groove aluminium block by self-plugging rivet;
It is double-decker at the bottom of case, inside panel three adopts welding manner to form airtight construction with skeleton at the bottom of case, rivet at the bottom of exterior skin four and case, the thick polyurethane foam board of 200mm is filled between skeleton at the bottom of case, at the bottom of case, the polyurethane foam board of inner mounting strap metallized film is to ensure the passive heat-insulating property of packing chest, contour bar flange at the bottom of case is equipped with, contour bar coordinates the flange of packaging box cover jointly to form sealing arrangement with seal ring, inside panel three be welded into as a whole after, again with frame welding at the bottom of case, wherein, active temperature controls to be form closed loop control system by frequency converting temperature control system and temperature sensor, to realize the setting arbitrarily of packaging the temperature inside the box 5-40 DEG C, by with passive temperature-controlling system in conjunction with work, accurately control with the temperature obtaining remote sensing satellite transport 20 ± 5 DEG C.
2. packing chest as claimed in claim 1, wherein, active temperature control system refrigeration work consumption is 4000W, heats power 4000W, design temperature can between 5-40 DEG C free setting.
3. packing chest as claimed in claim 1, wherein, active temperature control system is controlled by local control and notebook PC Long-distance Control two kinds of modes.
4. the packing chest as described in any one of claim 1-3, wherein, covering one adopts the thick 5A06 aluminium sheet of 3mm, and covering two is the 5A06 aluminium sheet of thick 2mm.
5. the packing chest as described in any one of claim 1-3, wherein, covering three and covering four are the 5A06 aluminium sheet that 5mm is thick.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410643275.7A CN104477518A (en) | 2014-11-07 | 2014-11-07 | Packaging box with active/passive temperature control combined control system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410643275.7A CN104477518A (en) | 2014-11-07 | 2014-11-07 | Packaging box with active/passive temperature control combined control system |
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| CN104477518A true CN104477518A (en) | 2015-04-01 |
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| CN201410643275.7A Pending CN104477518A (en) | 2014-11-07 | 2014-11-07 | Packaging box with active/passive temperature control combined control system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107063656A (en) * | 2017-02-17 | 2017-08-18 | 安徽万瑞冷电科技有限公司 | A kind of low-temperature test groove |
| CN113173345A (en) * | 2021-05-27 | 2021-07-27 | 北京星途探索科技有限公司 | Simple aircraft packaging and transporting box with heat preservation function |
| CN114231958A (en) * | 2022-02-21 | 2022-03-25 | 北京航天天美科技有限公司 | Sealed energy-absorbing structure and have packing box body of this structure |
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2014
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Patent Citations (4)
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| WO2004113170A1 (en) * | 2003-06-19 | 2004-12-29 | Mohammad Anayet Rubby Ahad | Satellite launch apparatus |
| CN2915733Y (en) * | 2006-06-21 | 2007-06-27 | 孙运凤 | Vehicular blood plasma transportation box |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107063656A (en) * | 2017-02-17 | 2017-08-18 | 安徽万瑞冷电科技有限公司 | A kind of low-temperature test groove |
| CN113173345A (en) * | 2021-05-27 | 2021-07-27 | 北京星途探索科技有限公司 | Simple aircraft packaging and transporting box with heat preservation function |
| CN114231958A (en) * | 2022-02-21 | 2022-03-25 | 北京航天天美科技有限公司 | Sealed energy-absorbing structure and have packing box body of this structure |
| CN114231958B (en) * | 2022-02-21 | 2022-05-03 | 北京航天天美科技有限公司 | Sealed energy-absorbing structure and have packing box body of this structure |
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Application publication date: 20150401 |