CN112937925B - Thermal control method for aerospace equipment - Google Patents

Abstract

One embodiment of the invention discloses a thermal control method of aerospace equipment, which comprises the following steps: s100, arranging a first filler on a cabin board of a spacecraft at a position corresponding to space equipment to be installed; s102, applying pressure to exhaust air between the first filler and the cabin board; s104, arranging a thin film type electric heater on the first filler; s106, setting a second filler on the thin film type electric heater; s108, applying pressure to exhaust air between the first filler, the second filler and the thin film type electric heater; s110, arranging the space equipment to be installed on the second filler, and discharging air between the second filler and the equipment by pressing. The invention has the following advantages: the implementation process of the electric heater and the installation process of the equipment are synchronously carried out, and a traditional gluing mode is not used, so that the curing time of glue is saved; the whole implementation process has extremely strong operability, and can effectively remove the air at the contact interface of the heater and the filler.

Description

Thermal control method for aerospace equipment

Technical Field

The invention relates to the field of implementation of thermal control measures of aerospace equipment. And more particularly to a thermal control method for an aerospace device.

Background

At present, the aerospace technology is an important means for quickly acquiring and transmitting information, has wide application requirements in the military and commercial fields, and has high requirements on adaptability of aircrafts, aerospace equipment and loads to space thermal environments in severe operation environments. In order to ensure that the temperature level and stability of the aircraft and key equipment thereof meet the normal working requirements, the design of the thermal control system becomes the key of the overall system design research and development link. The heat control system design comprises an active heat control design and a passive heat control design, wherein the passive heat control measures inhibit or strengthen the heat exchange relation between the controlled object and the outside by utilizing auxiliary measures without energy consumption or changing the thermophysical properties of the controlled object, and the active heat control measures mainly refer to utilizing an electric heater to carry out local temperature compensation on the controlled object.

The flexible thin film electric heating device is mainly formed by laminating a resistance element generated by etching an electrothermal alloy foil and a polyimide insulating film, has the advantages of high heating speed, long service life, light weight, thin thickness, radiation resistance, good insulativity, good flexibility, easiness in installation and implementation and the like, and is an active heat control device most widely applied in the aerospace field.

Under the traditional mode, the fixation between film type electric heater and the controlled object is carried out by using the gluing mode, and the method is specifically divided into the following two types: 1) The heater with double pressure-sensitive adhesive on the back can be directly adhered to the surface of a controlled object, and 2) the heater without pressure-sensitive adhesive on the back is usually adhered to the surface of the controlled object by using room temperature vulcanized silicone rubber. The double-sided pressure-sensitive adhesive is inferior in stability and is not generally used in the aerospace field, and the reliability of room temperature vulcanized silicone rubber in a space environment is higher than that of the double-sided pressure-sensitive adhesive, so that the latter is a common embodiment, specifically, the room temperature vulcanized silicone rubber 4 is uniformly coated on the adhesive surface of the film heater 2 and placed on the surface of the aerospace device 1 (i.e. the controlled object) to be installed, wherein the heater leads 3 are used for connecting a power supply, as shown in fig. 1 (a) and (b). The room temperature curing time of the silicone rubber is generally 24-48 hours, and the implementation process requires: in the process of coating the silicone rubber, repeated scraping and standing are carried out for deflation, in the process of curing the silicone rubber, repeated rolling of the rubber is carried out for exhausting, and sand bags or bandages can be used for compressing and fixing for auxiliary curing and exhausting. The conventional process flow is shown in fig. 2.

In order to ensure that the working state and the working life of the heater can meet design expectations, heat generated by the heater can be fully transferred to the surface of a controlled object, and the adhesive surface is in flat contact with the surface of the controlled object; meanwhile, the thin film type electric heater applied to the space field can expand and expand rapidly under vacuum or low pressure environment due to little gas between the adhesive surface and the surface of the controlled object, and the silicon rubber does not have secondary bonding or filling effect on the heater after solidification, so that the heater cannot be attached to the surface of the object, the normal heat discharging and conveying path of the heater is blocked, and the burning of resistance wires inside the heater is caused, therefore, the thin film type electric heater used in the space field should be completely prevented from air retention between the two adhesive surfaces during implementation. Because the inside of the silicone rubber is reserved with air, and the process of rolling the silicone rubber is difficult to ensure thorough air exhaust in the silicone rubber, the traditional implementation process is difficult to ensure that the technical requirement is met.

In addition, the conventional thin film electric heater implementation process has a plurality of defects:

from the implementation process:

in order to ensure the flatness of the coated silicone rubber and facilitate the implementation of sand bag pressurization auxiliary fixation and glue solidification, the gluing surface of the controlled object has the requirement of being perpendicular to the gravity direction;

when a plurality of surfaces of the controlled object need to be provided with heaters, the surfaces need to be pasted and solidified with the heaters in sequence, and the serial implementation process consumes longer time;

from the implementation result, the implementation effect under the current common heater pasting technology is not stable, the probability of larger bubbles or more small bubbles occurring during the solidification of the silicon rubber is high, the heat transfer relation between the heater and the surface of the controlled object is hindered, and the resistor element at the bubble position is blown when the heat transfer relation is serious, so that the active thermal control loop is disabled.

Disclosure of Invention

The invention aims to provide a thermal control method for aerospace equipment. To solve at least one of the problems with the prior art.

In order to achieve the above purpose, the invention adopts the following technical scheme:

the invention provides a thermal control method of aerospace equipment, which comprises the following steps:

s100, arranging a first filler on a cabin board of a spacecraft at a position corresponding to space equipment to be installed;

s102, applying pressure to exhaust air between the first filler and the cabin board;

s104, arranging a thin film type electric heater on the first filler;

s106, setting a second filler on the thin film type electric heater;

s108, applying pressure to exhaust air between the first filler, the second filler and the thin film type electric heater;

s110, arranging the space equipment to be installed on the second filler, and discharging air between the second filler and the equipment by pressing.

In a specific embodiment, after S102, the method further comprises:

s103, detecting whether the first filler and the cabin board have a filling effect meeting a first requirement, and if so, turning to S104; if not, continuing to apply pressure.

In a specific embodiment, after S108, the method further comprises:

s109, detecting whether the first filler, the second filler and the thin film type electric heater have a filling effect meeting a second requirement, and if so, turning to S110; if not, continuing to apply pressure.

In a specific embodiment, the method further comprises S112:

the mounting screws of the device are passed through the first and second packing and fastened to the deck so that the mounting planes on both sides apply a constant pressure to the first and second packing.

In a specific embodiment, the first filler is a silica gel thermal pad, a non-silica gel thermal pad, or a preformed thermal mud pad.

In a specific embodiment, the second filler is a silica gel thermal pad, a non-silica gel thermal pad, or a preformed thermal mud pad.

The beneficial effects of the invention are as follows:

the invention provides a thermal control method of aerospace equipment, in particular to a novel process for fixing a thin film type electric heater, which replaces the traditional process for sticking a heater by using room temperature vulcanized silicone rubber. The invention utilizes various low interface thermal resistance fillers such as silica gel heat conduction pads, non-silica gel heat conduction pads, preformed heat conduction mud gaskets and the like, and the thin film type electric heater is fixed between the equipment installation surface and the cabin plate by the pressure between the installation surface and the cabin plate surface during equipment installation, thereby meeting the necessary requirements of the technological process and simultaneously having the following advantages: the implementation process of the electric heater and the installation process of the equipment are synchronously carried out, and a traditional gluing mode is not used, so that the curing time of glue is saved; according to the characteristics of softness, low stress, light pressure, good filling capacity and the like of the low-interface thermal resistance filler, the whole implementation process has extremely strong operability, and the air of a contact interface between the heater and the filler can be effectively removed.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

Fig. 1 (a) and (b) are schematic views showing the state of a controlled object implementing heater under the conventional implementing process.

Fig. 2 shows an implementation procedure using a silicone paste heater in a conventional manner.

FIG. 3 illustrates a process flow diagram for implementing a novel heater according to one embodiment of the present application.

Fig. 4 is a schematic diagram showing a state of the controlled object implementing the heater under the novel implementation process according to one embodiment of the present application.

Reference numerals illustrate: 1 is aviation equipment to be installed, 2 is a film type electric heater main body, 3 is a heater lead, 4 is room temperature vulcanized silicone rubber, 5 is low-interface thermal resistance filler, 6 is a cabin board, 7 is a mounting screw, and 8 is low-interface thermal resistance filler.

Detailed Description

In order to make the technical scheme and advantages of the present invention more apparent, embodiments of the present invention will be described in further detail with reference to the accompanying drawings. Like parts in the drawings are denoted by the same reference numerals. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and that this invention is not limited to the details given herein.

A thermal control method for an aerospace device according to one embodiment of the invention is described with reference to fig. 3 and 4. The method comprises the following steps:

and S100, arranging the first filler 5 at a position on the cabin board 6 corresponding to the installation surface of the spaceflight equipment (namely the controlled object) to be installed.

In one particular example, the first filler is a low interface thermal resistance filler, such as a thermal pad. More preferably, the first filler is a silica gel thermal pad, a non-silica gel thermal pad, or a preformed thermal mud pad.

And S102, applying a certain pressure to discharge air between the first packing 5 and the cabin board 6.

Optionally, the method of the present application further includes step S103 after step S102: and detecting whether the first filling material and the cabin board have a filling effect meeting the first requirement, and if not, continuing to apply pressure.

In a specific embodiment, the detection method may be: whether the first required filling effect is satisfied is judged by looking at the deformation amount of the first filler 5, for example, the flatness of the deck is 0.1mm/100mm x 100mm, and when the deformation amount (thickness variation) of the first filler 5 is greater than this value, the first required filling effect is satisfied.

If the result of the detection is yes, S104 is performed, and the thin film electric heater 2 is provided on the first filler 5.

Next, step S106 is performed to dispose the second filler 8 on the thin film type electric heater 2.

In one specific example, the second filler is a low interface thermal resistance filler, such as a thermal pad. More preferably, the second filler is a silica gel thermal pad, a non-silica gel thermal pad, or a preformed thermal mud pad.

S108, applying a certain pressure to discharge air between the first filler, the second filler and the thin film type electric heater.

Thus, the film-shaped electric heater 2 is embedded between the first filler 5 and the second filler 8.

Optionally, after step S108, the method of the present invention may further include step S109:

detecting whether the first filler, the second filler and the thin film type electric heater have a filling effect meeting a second requirement, and if not, continuing to apply pressure.

In a specific embodiment, the detection method may be: judging whether the filling effect of the second requirement is met or not by looking at the deformation amount of the first filler and the deformation amount of the second filler, and when the deformation amount of the first filler and the deformation amount (thickness change) of the second filler are larger than the thickness of the thin film type electric heater, the filling effect of the second requirement is met.

If the result of the detection is yes, S110 is executed: the space device 1 to be installed is arranged on the second filler 8, and air between the second filler 8 and the device 1 is discharged by pressing.

In a preferred embodiment, the method further comprises S112: by passing the mounting screws 7 of the device through the first and second packing and fastening them to the deck plate 6, the two side mounting planes are made to exert a constant pressure on the first and second packing, ensuring that the two sheets of packing have a long-lasting effective filling effect for the deck plate mounting location and the thin film type electric heater, and the thin film type electric heater and the device mounting surface, respectively. When the filler is obviously overflowed from the edge of the equipment, the filling effect is good.

The invention provides a thermal control method of aerospace equipment, in particular to a novel process for fixing a thin film type electric heater, which replaces the traditional process for sticking a heater by using room temperature vulcanized silicone rubber. The method is mainly aimed at the implementation of the thin film type electric heater of the equipment on the spacecraft such as the satellite, and the thin film type electric heater is fixed between the equipment installation surface and the cabin plate by the pressure between the installation surface and the cabin plate surface during the equipment installation by utilizing low interface thermal resistance fillers such as various silica gel heat conduction pads, non-silica gel heat conduction pads, preformed heat conduction mud gaskets and the like. The method meets the necessary requirements of the technological process and has the following advantages: the implementation process of the electric heater and the installation process of the equipment are synchronously carried out, and a traditional gluing mode is not used, so that the curing time of glue is saved; according to the characteristics of softness, low stress, light pressure, good filling capacity and the like of the low-interface thermal resistance filler, the whole implementation process has extremely strong operability, and the air of a contact interface between the heater and the filler can be effectively removed.

It should be understood that the foregoing examples of the present invention are provided merely for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention, and that various other changes and modifications may be made therein by one skilled in the art without departing from the spirit and scope of the present invention as defined by the appended claims.

Claims (2)

1. A method of thermally controlling a spacecraft, comprising:

s100, arranging a first filler on a cabin board of a spacecraft at a position corresponding to space equipment to be installed;

s102, applying pressure to exhaust air between the first filler and the cabin board;

s104, arranging a thin film type electric heater on the first filler;

s106, setting a second filler on the thin film type electric heater;

s108, applying pressure to exhaust air between the first filler, the second filler and the thin film type electric heater;

s110, arranging the aerospace equipment to be installed on the second filler, and discharging air between the second filler and the equipment by pressing;

after S102, the method further comprises:

s103, detecting whether the first filler and the cabin board have a filling effect meeting a first requirement, and if so, turning to S104; if not, continuing to apply pressure;

after S108, the method further comprises:

s109, detecting whether the first filler, the second filler and the thin film type electric heater have a filling effect meeting a second requirement, and if so, turning to S110; if not, continuing to apply pressure;

the first filler is a silica gel heat conduction pad, a non-silica gel heat conduction pad or a preformed heat conduction mud gasket;

the second filler is a silica gel heat conduction pad, a non-silica gel heat conduction pad or a preformed heat conduction mud gasket.

2. The method according to claim 1, characterized in that the method further comprises S112:

the mounting screws of the device are passed through the first and second packing and fastened to the deck so that the mounting planes on both sides apply a constant pressure to the first and second packing.

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