CN113784585A - High-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system - Google Patents
High-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system Download PDFInfo
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- CN113784585A CN113784585A CN202110983237.6A CN202110983237A CN113784585A CN 113784585 A CN113784585 A CN 113784585A CN 202110983237 A CN202110983237 A CN 202110983237A CN 113784585 A CN113784585 A CN 113784585A
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- measurement unit
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- 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
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
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- 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
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20172—Fan mounting or fan specifications
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- 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
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20181—Filters; Louvers
-
- 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
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20218—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant without phase change in electronic enclosures
-
- 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
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2039—Modifications to facilitate cooling, ventilating, or heating characterised by the heat transfer by conduction from the heat generating element to a dissipating body
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- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
A high-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system effectively solves the heat influence of a plurality of heating function modules on an integrated inertial measurement unit instrument part, reduces the temperature rise amplitude of an instrument and ensures the accuracy index of the instrument. The inertial measurement unit heat dissipation system comprises a case, an air inlet assembly and an air outlet assembly; the interior of the case is of a hollow structure, a first cavity for installing the instrument desk body assembly is arranged in the center of the interior of the case, a second cavity for installing the functional module is also arranged in the interior of the case, and the second cavity is distributed on the periphery of the first cavity and isolated from the first cavity; an air inlet component and an air outlet component are respectively arranged on the upper part and the lower part of the case corresponding to the two ends of the first cavity; the outer side of the case is also provided with a phase change material component, and the side surface without the phase change material component is provided with a heat dissipation groove. The invention is mainly used for heat dissipation of the satellite-rocket inertial measurement unit, and ensures normal work and precision maintenance of the inertial instrument in the whole flight process of the satellite-rocket from the ground atmosphere to the outer space.
Description
Technical Field
The invention relates to aerospace inertial navigation, in particular to a high-integration, multifunctional and miniaturized satellite-rocket inertial unit heat dissipation system.
Background
With the rapid development of the aerospace inertial technology, particularly the development and application of a carrier rocket for commercial satellite launching, in order to realize an operation mode of effective maximum carrying, minimum development time and maximum profit and income, the inertial navigation device is required to be designed in an integrated manner with low cost, miniaturization and high integration of multifunctional modules.
The highly integrated design subverts the development mode that the original inertial unit and the function modules respectively and independently form a single unit, and the function modules are heating sources with larger power consumption, which is a factor seriously influencing performance indexes for an inertial unit instrument sensitive to temperature change, so that the inertial unit is necessary to be subjected to heat dissipation design.
For circuits with different functions and larger power consumption, the traditional design idea is a two-body design, namely, the functional modules are combined and then independently designed into a single machine, the inertial unit is independently designed into another single machine, and the heat generated by the functional modules has smaller heat influence on the inertial unit. The self-power-consumption heating of the inertial measurement unit is conducted to the cabin section girder through the mounting part of the external case, or the radiation heat dissipation is carried out through the case shell.
The two-part design has the following drawbacks:
(1) the two-body structure needs to design two single machines, needs larger installation space at the same time, and the finally designed inertial unit and the heat dissipation system thereof have large space and heavy weight.
(2) The cable connection of the two single units has large interference to external electromagnetism.
(3) When a plurality of functional modules are needed in the two-body structure, a plurality of single machines need to be designed, and the occupied area is large.
Disclosure of Invention
The invention provides a high-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system, which effectively solves the heat influence of a plurality of heating function modules on the integrated inertial measurement unit instrument part, reduces the temperature rise speed of the instrument, realizes the heat balance inside the instrument and ensures the accuracy index of the instrument.
The technical solution of the invention is as follows:
a high-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system is characterized by comprising a case, an air inlet assembly and an air outlet assembly;
a first cavity for mounting the instrument desk body assembly is arranged in the center of the interior of the case;
a second cavity for installing a functional module is arranged in the case;
the second chambers are distributed on the periphery of the first chamber and are isolated from the first chamber;
an air inlet component and an air outlet component are respectively arranged on the case corresponding to two ends of the first cavity, and the direction of air flow in the case is opposite to the flying direction of the arrow body.
Furthermore, a phase change material component is arranged on the outer side face of the case corresponding to the cavity wall of the second cavity, and heat conduction silicone grease is filled between the phase change material component and the outer surface of the case.
Further, the instrument desk body assembly is connected with the case through the heat insulation pad.
Furthermore, the outer side surface of the case, on which the phase change material assembly is not arranged, is provided with a heat dissipation groove.
Furthermore, a heat insulating material is adhered to the wall of the second chamber.
Further, the air inlet subassembly includes apron and air inlet filter screen down, be provided with a plurality of filtered air's air inlet filter screen down on the apron.
Further, the air-out subassembly includes upper cover plate, fan and filter screen, and the upper cover plate is provided with the fan, and the fan can make the machine incasement outside carry out the air and exchange, and the fan inboard is provided with the filter screen, is equipped with the rubber slab between upper cover plate and the fan.
Further, the second chamber is provided with four.
Further, the outer surface of the case, the outer surfaces of the lower cover plate and the upper cover plate are subjected to black treatment.
The beneficial effects of the invention are as follows:
(1) the invention is designed with a cavity structure, a plurality of functional modules are arranged in the cavity, the plurality of functional modules realize integrated design, one single machine organization can realize a plurality of functions, meanwhile, the electrical functions are highly integrated, and the miniaturization and lightweight design of the inertial group is realized.
(2) By designing the phase-change material component, the invention solves the problems of heat dissipation at high temperature and heat dissipation in a vacuum environment, and effectively ensures the normal work and the precision maintenance of the inertial instrument in the whole flight process of the satellite and the rocket from the ground atmosphere to the outer space.
(3) The invention accelerates the air convection by additionally arranging the fan, so that the heat of the instrument part is taken away along with the flowing of the air.
(4) The heat dissipation groove and the surface black treatment are designed outside the case, and the heat dissipation of the case to the outside can be accelerated after the heat dissipation groove is designed and the surface black treatment is carried out.
Drawings
FIG. 1 is a schematic structural diagram of an inertial measurement unit heat dissipation system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a cabinet cavity structure according to an embodiment of the invention;
FIG. 3 is a schematic diagram of a three-dimensional structure of an air outlet assembly direction of an inertial measurement unit heat dissipation system according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a three-dimensional structure of an air intake assembly of the inertial measurement unit heat dissipation system according to an embodiment of the present invention.
The reference numerals are specifically as follows:
1. the air conditioner comprises a first chamber, a second chamber, a case, a heat dissipation groove.
Detailed Description
The following detailed description of the present invention is provided in conjunction with the accompanying drawings, but it should be understood that the scope of the present invention is not limited to the specific embodiments.
The invention provides a high-integration, multifunctional and small satellite-rocket inertial measurement unit heat dissipation system, which comprises a case 3, an air inlet assembly 4 for air convection and an air outlet assembly 5 for heat discharge, as shown in figure 1.
As shown in fig. 2, the inside of the case 3 is a hollow structure, the inside of the case 3 is provided with five chambers, namely a first chamber 1 and four second chambers 2, the five chambers are square, the first chamber 1 is placed in the five chambers according to the center, and the five chambers are arranged around the first chamber 1 attached to the center of each of the four second chambers 2. An instrument desk body assembly is installed in the first chamber 1, and a plurality of heating functional modules are installed in the second chamber 2. The cavity walls between the five chambers in the case 3 are not communicated with each other, so that the direct radiation of heat released by the functional modules in the four peripheral second chambers 2 to the instrument desk body assembly in the first chamber 1 is avoided.
The instrument desk body assembly is arranged in the first chamber 1 in the middle of the chassis 3, so that the influence of bias on the performance of the instrument is avoided; the functional modules are respectively arranged in the four second chambers 2 in the case 3, so that heat can be diffused to the periphery; the wall of the four second chambers 2 is adhered with a heat insulating material, which is beneficial to preventing the heat inside the second chambers 2 from being transferred to the first chamber 1.
A heat insulating pad 6 is arranged between the instrument desk body assembly and the case 3, and the heat insulating pad 6 prevents heat conducted to the case 3 by the functional module from being further conducted to the instrument desk body assembly.
Threaded holes are formed in the outer side face of the case 3 corresponding to the outermost side wall of each of the four second chambers 2, the phase change material assembly is installed on the outer side face of the case 3 through the threaded holes, and heat-conducting silicone grease is filled between the phase change material assembly and the outer side face of the case 3. The heat of the case 3 is dissipated by conduction into the phase change material assembly.
And the outer wall of the outer side surface of the case 3, which is not provided with the phase change material component, is provided with a heat dissipation groove 31, and the direction of the heat dissipation groove 31 is along the flight direction of the arrow body.
As shown in fig. 3 and 4, an air inlet component 4 and an air outlet component 5 are respectively installed on two end faces of the chassis 3.
The air inlet component 4 is arranged at the front end of the arrow body in the flight direction, and the air outlet component 5 is arranged at the rear end of the arrow body in the flight direction to prevent hot air at an air outlet from flowing reversely.
The intake assembly 4 includes a lower cover plate 41 and an intake screen 42.
The lower cover plate 41 is a bottom plate of the case 3 in the forward direction of the arrow body flight direction, a plurality of air inlet filter screens 42 are arranged on the lower cover plate 41, and the air entering the case 3 can be filtered by the air inlet filter screens 42.
The air outlet assembly 5 includes an upper cover plate 51, a fan 52 and a filter 53.
Five cavities of the case 3 are respectively communicated up and down, and form an air flow channel with the air inlet component 4 and the air outlet component 5.
When the fan 52 works, the air flow enters the case 3 from the air inlet assembly filter screen 42 and passes through the 5 cavities respectively, the heat at the instrument part is taken away when the air flow passes through the cavities, and the heat is discharged from the air outlet assembly 5.
The outer surfaces of the case 3, the upper cover plate 51 and the lower cover plate 41 are subjected to black treatment to increase the emissivity of heat. Wherein the black treatment method comprises plating and coating.
When the inertial measurement unit is below 50 ℃, heat dissipation is carried out through the work of a fan 52; when the inertial unit is at 50 ℃ or above, the heat is dissipated through the work of the phase-change material component 7, and the heat can also be dissipated through the simultaneous work of the fan 52 and the phase-change material component 7. The phase change material component can set the working temperature according to the inertial set environment so as to adjust the temperature working range. The fan 52 can adjust the air output according to the inertial group environment.
When the star and arrow fly in the ground atmosphere, the fan 52 works to accelerate the air convection to dissipate heat; when the satellite and the arrow fly in space, the heat cannot be dissipated through the fan 52, and the heat can be dissipated through self radiation and the work of the phase-change material component.
Claims (9)
1. A high-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system is characterized by comprising a case (3), an air inlet assembly (4) and an air outlet assembly (5);
a first chamber (1) for mounting an instrument desk body assembly is arranged at the center inside the case (3);
a second chamber (2) for installing a functional module is arranged in the case (3);
the second chambers (2) are distributed on the periphery of the first chamber (1) and are isolated from the first chamber (1);
an air inlet component (4) and an air outlet component (5) are respectively installed on the case (3) corresponding to the two ends of the first cavity, and the direction of air flow in the case (3) is opposite to the flying direction of the arrow body.
2. The highly-integrated, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system according to claim 1, wherein a phase-change material component (7) is arranged on the outer side surface of the case (3) corresponding to the cavity wall of the second cavity (2), and heat-conducting silicone grease is filled between the phase-change material component (7) and the outer surface of the case (3).
3. The highly integrated, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system as claimed in claim 1, wherein the instrument desk body assembly is connected with the case through a heat insulation pad (6).
4. The high-integration, multifunctional and small satellite-rocket inertial measurement unit heat dissipation system as claimed in claim 2, wherein a heat dissipation groove (31) is formed in an outer side surface of the case (3) where the phase change material component (7) is not arranged.
5. The high-integration, multifunctional and small satellite-rocket inertial measurement unit heat dissipation system as claimed in claim 1, wherein a heat insulation material is adhered on the cavity wall of the second chamber (2).
6. The highly-integrated, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system according to claim 1, wherein the air intake assembly (4) comprises a lower cover plate (41) and an air intake filter screen (42), and the air intake filter screen (42) for filtering air is arranged on the lower cover plate (41).
7. The high-integration, multifunctional and small satellite-rocket inertial measurement unit heat dissipation system according to claim 1, wherein the air outlet assembly (5) comprises an upper cover plate (51), a fan (52) and a filter screen (53), the upper cover plate (51) is provided with the fan (52), the fan (52) can enable air exchange between the inside and the outside of the case (3), the filter screen (53) is arranged on the inner side of the fan (52), and a rubber plate is arranged between the upper cover plate (51) and the fan (52).
8. The highly integrated, multifunctional and miniaturized satellite-rocket inertial group heat dissipation system according to claim 1, wherein four second chambers (2) are provided.
9. The highly integrated, multifunctional and miniaturized satellite-rocket inertial group heat dissipation system according to any one of claims 1 to 8, wherein the outer surface of the case (3), the outer surfaces of the lower cover plate (41) and the upper cover plate (51) are subjected to black treatment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110983237.6A CN113784585A (en) | 2021-08-25 | 2021-08-25 | High-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110983237.6A CN113784585A (en) | 2021-08-25 | 2021-08-25 | High-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system |
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| Publication Number | Publication Date |
|---|---|
| CN113784585A true CN113784585A (en) | 2021-12-10 |
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| CN202110983237.6A Pending CN113784585A (en) | 2021-08-25 | 2021-08-25 | High-integration, multifunctional and miniaturized satellite-rocket inertial measurement unit heat dissipation system |
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