CN108860664B - Novel thermal control device for space flexible mechanism - Google Patents

Novel thermal control device for space flexible mechanism Download PDF

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Publication number
CN108860664B
CN108860664B CN201810636146.3A CN201810636146A CN108860664B CN 108860664 B CN108860664 B CN 108860664B CN 201810636146 A CN201810636146 A CN 201810636146A CN 108860664 B CN108860664 B CN 108860664B
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copper
temperature control
control heating
type temperature
film
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CN108860664A (en
Inventor
孙伟伟
赵吉喆
杜忠选
顾燕萍
徐涛
翟载腾
曹建光
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Shanghai Institute of Satellite Engineering
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Shanghai Institute of Satellite Engineering
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/54—Protection against radiation
    • G—PHYSICS
    • G02—OPTICS
    • G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
    • G02B5/00—Optical elements other than lenses
    • G02B5/08—Mirrors
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B1/00—Details of electric heating devices
    • H05B1/02—Automatic switching arrangements specially adapted to apparatus ; Control of heating devices
    • H05B1/0202—Switches
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/40—Heating elements having the shape of rods or tubes
    • H05B3/54—Heating elements having the shape of rods or tubes flexible
    • H05B3/58—Heating hoses; Heating collars
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields
    • H05K9/0073—Shielding materials
    • H05K9/0081—Electromagnetic shielding materials, e.g. EMI, RFI shielding

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  • Engineering & Computer Science (AREA)
  • Health & Medical Sciences (AREA)
  • Physics & Mathematics (AREA)
  • General Health & Medical Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Critical Care (AREA)
  • Emergency Medicine (AREA)
  • Remote Sensing (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Electromagnetism (AREA)
  • General Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Toxicology (AREA)
  • Surface Heating Bodies (AREA)
  • Optical Elements Other Than Lenses (AREA)

Abstract

The invention discloses a novel thermal control device for a space flexible mechanism, which comprises a film type temperature control heating belt, copper-nickel plain conductive cloth and an F46 film silver-plated secondary surface mirror, wherein the film type temperature control heating belt is adhered and wound on the flexible mechanism through GD414C silicon rubber; 6 layers of copper-nickel plain conductive cloth are wound on the film type temperature control heating belt; and a layer of F46 film silver-plated secondary surface mirror is wound on the surface of the copper-nickel plain fabric. The invention utilizes the copper-nickel plain conductive cloth and the F46 film silver-plated secondary surface mirror to wholly coat the space flexible mechanism, thereby not only preventing external heat flow but also resisting irradiation, and simultaneously effectively reducing the power of the temperature control heating belt and saving energy. In addition, the film type temperature control heating belt, the copper-nickel plain weave conductive cloth and the F46 film silver plating secondary surface mirror have flexibility, and can be suitable for space flexible mechanisms with various structures, including rotating cables and the like.

Description

Novel thermal control device for space flexible mechanism
Technical Field
The invention relates to a thermal control product for a space aircraft, in particular to a novel thermal control device for a space flexible mechanism.
Background
The conventional thermal control measures of the satellite extravehicular space flexible mechanism (such as extravehicular cables, flexible waveguides and the like) are mainly to coat a plurality of layers of heat insulation components on the outer surface. However, because some extra-cabin cables or movable flexible waveguides have rotation requirements, the rotation requirements can be met only by maintaining a certain temperature, low-temperature compensation is needed, and the conventional measures cannot meet the thermal control requirements at the moment. Some extravehicular flexible waveguides have higher internal heat consumption, cannot dissipate heat by internal heat dissipation when being coated with a multilayer heat insulation assembly, and cannot meet the heat dissipation requirements of heat control by conventional heat control measures. In addition, flexible mechanisms such as cables exposed in space have the radiation resistance requirement. Therefore, a new thermal control measure needs to be taken for space flexible mechanisms such as a rotating cable or an extra-cabin movable flexible waveguide, the temperature requirement required by rotation can be maintained, heat flow outside the space can be effectively prevented, and meanwhile, the radiation protection requirement is met. The novel thermal control device for the space flexible mechanism can meet the technical requirements simultaneously, and the space flexible mechanism is flexible and applicable to various structures.
Disclosure of Invention
In order to solve the problems of low-temperature compensation, high-temperature protection and irradiation resistance which cannot be solved by a space flexible mechanism under conventional thermal control measures, the invention provides a novel thermal control device for the space flexible mechanism, which is suitable for the requirements of low-temperature compensation, high-temperature protection and irradiation resistance of flexible mechanisms outside cabins with various shapes and is used for integral coating.
The purpose of the invention is realized by the following technical scheme:
the novel thermal control device for the space flexible mechanism comprises a film type temperature control heating tape, copper-nickel plain woven conductive cloth and an F46 film silver-plated secondary surface mirror, wherein the film type temperature control heating tape is adhered and wound on the flexible mechanism through GD414C silicon rubber; 6 layers of copper-nickel plain-weave conductive cloth are wound on the film type temperature-control heating belt; and a layer of F46 film silver-plated secondary surface mirror is wound on the surface of the copper-nickel plain fabric.
Preferably, GD414C silicon rubber is fully coated when the film type temperature control heating tape is pasted and wound on the flexible mechanism, the film type temperature control heating tape is wound on the mechanism, and when the film type temperature control heating tape is wound, two adjacent circles cannot be overlapped, and a certain gap is reserved; and the flexible mechanism is adhered with a thermistor and used for controlling the switch of the film type temperature control heating belt.
Preferably, the overlapping area of the copper-nickel plain weave conductive cloth winding is 10% -20%.
Preferably, the F46 film silvered secondary surface mirror is of a conductive type, the winding density is one ring, the coverage rate is about 50% when winding, the tightness is moderate, and the secondary surface mirror is not suitable for being too tight.
The invention has the following beneficial effects:
the film type temperature control heating belt, the copper-nickel plain weave conductive cloth and the F46 film silver-plated secondary surface mirror are used for completely coating the space flexible mechanism, the film type temperature control heating belt is used for low-temperature compensation, the copper-nickel plain weave conductive cloth is used for space irradiation resistance, and meanwhile the F46 film silver-plated secondary surface mirror is used for reducing the high-temperature influence of heat flow outside the space on the mechanism due to lower solar absorptivity. Meanwhile, by utilizing the flexibility of the film type temperature control heating belt, the copper-nickel plain weave conductive cloth and the F46 film silver-plated secondary surface mirror, the thermal control device can meet the requirements of various flexible mechanism appearance structures and sizes and can also meet the rotation requirement. Therefore, the invention has the advantages of universality, high-efficiency thermal control, radiation resistance and the like.
Drawings
FIG. 1 is a schematic structural diagram of a novel thermal control film for a space according to an embodiment of the present invention.
In the figure: 1-F46 film silver-plated secondary surface mirror; 2-copper-nickel plain conductive cloth; 3-film type temperature control heating belt;
4-GD414C silicone rubber; 5-thermistor for controlling temperature.
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 variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the embodiment of the present invention provides a novel thermal control device for a space flexible mechanism, which includes a thin film type temperature-controlled heating tape 3 completely adhered to the mechanism through GD414C silicone rubber 4, a plain copper-nickel conductive fabric 2 wound outside the thin film type temperature-controlled heating tape 3, and a silver-plated secondary surface mirror 1 wound on the outermost F46 thin film, and further includes a thermistor 5 for controlling the on/off of the thin film type temperature-controlled heating tape.
The invention firstly fully coats and winds the film type temperature control heating belt 3 on the mechanism by GD414C silicon rubber 4, two adjacent windings can not be overlapped, and a certain gap is left. Meanwhile, a thermistor 5 is adopted to control a heating belt switch, and the thermistor 5 is also adhered to a space flexible mechanism by GD414C silicon rubber adhesive and is adhered to a gap of a film type temperature control heating belt to avoid a heating belt resistance wire by more than 10 mm. Preferably, the thermistor is of the MF5802 type.
Further, the copper-nickel plain weave conductive fabric 2 is wound on the surface of the film type temperature control heating belt 3, and the winding overlapping area is as follows: 10 to 20 percent. Preferably, the copper-nickel plain woven conductive fabric 2 is wound by 6 layers.
Further, the F46 film silver-plated secondary surface mirror 1 is wound on the outer surface of the copper-nickel plain conductive cloth 2, the winding density is one ring, the coverage rate is about 50% when winding, the tightness is moderate, and the tightness is not suitable for being too tight. Preferably, the F46 thin film silver-plated secondary surface mirror 1 is of a conductive type.
Referring to fig. 1, the F46 film silver-plated secondary surface mirror 1 may be replaced with a polyimide germanium-plated film, a polyimide aluminum-plated secondary surface mirror, or the like, as needed.
With continued reference to fig. 1, the copper-nickel plain conductive fabric may have other number of layers according to the requirement of radiation resistance, and 6 layers are selected according to the test in the present invention.
Ground tests and thermal simulation calculation show that 1) the method can realize effective control of high and low temperatures of the space flexible mechanism; 2) the device is suitable for bending or rotating the flexible mechanism outside the cabin with large radius, has high flexibility, and is suitable for various complex bending or rotating conditions.
The specific implementation can provide a thermal control measure for a space flexible mechanism with an exposed space, the space flexible mechanism is integrally coated by the copper-nickel plain conductive cloth and the F46 film silver-plated secondary surface mirror, the influence of heat flow outside the space on the mechanism can be effectively prevented, and the mechanism is protected from space irradiation; and low-temperature compensation is carried out through a film type temperature control heating belt, and the working environment temperature of the space flexible mechanism is maintained. The space flexible mechanism is integrally coated by the copper-nickel plain conductive cloth and the F46 film silver-plated secondary surface mirror, so that external heat flow and radiation resistance can be prevented, the power of a temperature control heating belt can be effectively reduced, and energy is saved. In addition, the film type temperature control heating belt, the copper-nickel plain weave conductive cloth and the F46 film silver plating secondary surface mirror have flexibility, and can be suitable for space flexible mechanisms with various structures, including rotating cables and the like.
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 and 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.

Claims (1)

1. The thermal control device of the space flexible mechanism is characterized by comprising a film type temperature control heating belt, copper-nickel plain woven conductive cloth and an F46 film silver-plated secondary surface mirror; the thin film type temperature control heating belt is adhered and wound on the flexible mechanism through GD414C silicon rubber; 6 layers of copper-nickel plain-weave conductive cloth are wound on the film type temperature-control heating belt; a layer of F46 film silver-plated secondary surface mirror is wound on the surface of the copper-nickel plain fabric;
the GD414C silicon rubber is fully coated when the film type temperature control heating tape is pasted and wound on the flexible mechanism, and two adjacent circles can not be overlapped and a gap is reserved when the film type temperature control heating tape is wound;
the overlapping area of the copper-nickel plain conductive cloth during winding is 10% -20%;
the winding density of the silver-plated secondary surface mirror of the F46 film is one ring, the coverage rate is about 50% when winding, and the tightness is moderate; the F46 film silver-plated secondary surface mirror is conductive;
and the flexible mechanism is adhered with a thermistor and used for controlling the switch of the film type temperature control heating belt.
CN201810636146.3A 2018-06-20 2018-06-20 Novel thermal control device for space flexible mechanism Active CN108860664B (en)

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Families Citing this family (3)

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Publication number Priority date Publication date Assignee Title
CN109484680B (en) * 2018-12-21 2021-12-14 深圳航天东方红卫星有限公司 Radiant heat control mechanism based on three-pump folding
CN109648971A (en) * 2019-01-09 2019-04-19 上海卫星工程研究所 A kind of space heat controlled thin film
CN113401369A (en) * 2021-06-07 2021-09-17 长光卫星技术有限公司 High-efficient expansion heat pipe radiation radiator

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