Missile-borne high-heat-storage soaking three-edged table based on 3D printing process

Abstract

The utility model discloses a missile-borne high-heat-storage uniform-heating triangular pyramid frustum based on a 3D printing process. The missile-borne high-heat-storage uniform-heating triangular pyramid frustum comprises a triangular pyramid frustum body, a supporting framework, a grid frame and a phase-change material. The side face of the triangular pyramid body is a thermal interface used for being in contact with a phased-array antenna heating device. The three side surfaces mutually form 90 degrees in the space, and the projection angles of the normal directions of the three side surfaces on the horizontal plane mutually form 120 degrees; the supporting framework and the grid frame are both arranged in the triangular pyramid frustum body and used for supporting and conducting heat. The three-edged frustum body is filled with the phase-change material; a filling opening is formed in the bottom surface of the triangular pyramid frustum body. The semi-spherical surface can be covered, and the heat storage and soaking effect is good.

Description

Technical Field

[0001] The utility model relates to the technical field of thermal control of missile-borne electronic equipment, and particularly relates to a missile-borne high heat storage and heat equalizing triangular prism based on 3D printing technology. Background Technique

[0002] In order to cover 360° of the horizontal plane, a missile-borne phased array antenna generally uses three phased array antennas as a group, which are mutually 120° in the horizontal plane projection to achieve the effect of covering 360°. At the same time, in order to cover the hemispherical surface, the three antenna arrays are arranged at a certain inclination angle with the horizontal plane. Because phased array antennas generally have large heat consumption and need to rely on the installed structural parts for heat dissipation, missile-borne equipment usually has a short working time, and is limited by the equipment installation and working conditions, and the heat dissipation capacity is generally poor. Therefore, the thermal control of missile-borne electronic equipment generally considers storing heat to ensure that the equipment temperature does not exceed the required value within the limited working time. The existing structural parts of missile-borne electronic equipment are usually machined parts, and the material mostly uses aluminum alloy. Aluminum alloy has a high thermal conductivity and a high heat conduction efficiency for heat; however, for machined parts, due to subtractive manufacturing, it is powerless if there are complex cavities inside the structural parts. For the structural parts of missile-borne electronic equipment with heat storage requirements, cavities are usually arranged inside the structural parts to fill phase change heat storage materials, and a large amount of heat is stored by using the latent heat of the phase change materials, so as to achieve the purpose of temperature control.

[0003] The thermal control structural parts of existing missile-borne electronic products are generally regular structures, which are machined from a kind of metal. Although the pure metal processed has good thermal conductivity, its heat capacity is relatively small, and the temperature rises relatively fast. For missile-borne thermal control products, it can only work for a short time. If the heat capacity needs to be increased, only the volume and weight can be increased, but weight is a very precious index for missile-borne products, and every additional gram of weight needs to be reduced from other components. For the thermal control structural parts filled with phase change materials in a metal matrix, due to the limitations of machining and welding, there are certain limitations on the complexity and volume size of the thermal control parts. If the internal cavity is too complex, internal machining cannot be realized, and welding is also very unreliable. Moreover, if the size is too large, the internal cavity cannot be machined and sealed, affecting the sealing performance of the phase change materials. If it is processed by splicing and welding of plates and completely filled with phase change heat storage materials in the internal cavity, although the weight and heat capacity can be guaranteed, the thermal conductivity of the phase change materials is generally very low. During the working process, the phase change materials close to the structural wall have already absorbed heat and undergone phase change and the temperature has risen, while the temperature of other parts of the phase change materials is still below the phase change temperature and is solid, and the unphase-changed phase change materials do not play a role in heat storage, and occupy weight, resulting in waste of weight and volume. Content of the Utility Model

[0004] In view of this, the present utility model provides a missile-borne high heat storage and heat equalization triangular prism based on 3D printing technology, which can cover a hemispherical surface and has good heat storage and heat equalization effects.

[0005] The technical solution adopted by the present utility model is as follows:

[0006] A missile-borne high heat storage and heat equalization triangular prism based on 3D printing technology, comprising a triangular prism body, a support skeleton, a grid frame and a phase change material;

[0007] The side surface of the triangular prism body is a heat interface for contacting the heat generating device of the phased array antenna; the three side surfaces are mutually perpendicular to each other by 90° in space, and the projection angles of the normal directions of the three side surfaces on the horizontal plane are mutually perpendicular to each other by 120°; the support skeleton and the grid frame are both arranged inside the triangular prism body for support and heat conduction; the phase change material is filled inside the triangular prism body; a filling port is provided at the bottom surface of the triangular prism body.

[0008] Further, the support skeleton is an integrated structure based on 3D printing, and is divided into a main rod, a secondary rod and a connecting rod;

[0009] The main rod is vertically arranged at the central axis of the triangular prism, and multiple secondary rods are horizontally radiated outward from the main rod at different heights until they contact the inner wall of the triangular prism body. The radiation directions of the upper and lower adjacent secondary rods are the same, and a connecting rod is provided between the upper and lower adjacent secondary rods.

[0010] Further, there are six secondary rods radiated at each height, and the connecting lines of the connecting rods provided at this height form a regular hexagon.

[0011] Further, the grid frame includes a grid panel formed by horizontally and vertically intersecting metal rods, and multiple layers of grid panels are arranged at intervals.

[0012] Further, there are two filling ports, which are arranged at two points on the bottom surface of the triangular prism body with the farthest distance.

[0013] Further, the material of the triangular prism body is aluminum silicon ten magnesium.

[0014] Beneficial effects:

[0015] 1. The beam coverage angle of a single phased array antenna is limited. To cover a hemispherical surface, if only one or two phased array antennas are used, a rotating mechanism is required, which will not only increase complexity and weight, but also reduce reliability, which is unrealistic for missile-borne equipment. The triangular prism structure adopted by the present utility model enables the three phased array antennas installed thereon to be mutually perpendicular to each other by 90° in space. The beam angles of the antennas can be well complemented to achieve the effect of covering a hemispherical surface, and there are no moving parts, so the reliability is high.

[0016] Secondly, based on the 3D printing process, complex support structures and curved surfaces inside the triangular prism frustum can be realized. For areas with little effect on structural strength and stiffness, they can be appropriately thinned and filled with phase change materials, which can not only effectively reduce the weight, but also increase the heat capacity, better control the heat, and after 3D printing, the structure is integrated without welds and other leakage risk points, increasing the reliability.

[0017] Furthermore, by using the support skeleton and grid frame for support and heat conduction, the temperature uniformity inside the phase change material can be increased, and the overall heat equalization ability of the triangular prism frustum can be improved.

[0018] 2. The support skeleton structure of the present utility model can not only increase the strength and stiffness of the entire triangular prism frustum body, but also serve as a heat transfer channel for increasing the heat conduction ability; the horizontal and vertical cross metal rods can greatly increase the temperature uniformity inside the phase change material because the thermal conductivity of the metal substrate is much higher than that of the phase change material, further improving the heat equalization ability of the triangular prism frustum and increasing the utilization rate of the phase change material.

[0019] 3. The filling ports of the present utility model are located at two points on the bottom surface of the triangular prism frustum body that are farthest apart, which can ensure that a sufficient amount of phase change material is poured into the interior and filled evenly. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of the present utility model.

[0021] Figure 2 It is the front view of the present utility model.

[0022] Figure 3 It is a schematic diagram of the angle between the side surface of the triangular prism frustum body of the present utility model and the horizontal plane.

[0023] Figure 4 It is the top view of the present utility model.

[0024] Figure 5 It is a schematic diagram of the internal structure of the present utility model.

[0025] Among them, 1 - triangular prism frustum body, 2 - thermal interface, 3 - mounting hole Ⅰ, 4 - mounting hole Ⅱ, 5 - support skeleton, 6 - grid frame, 7 - filling port, 8 - phase change material. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] The following combines the drawings and gives examples to describe the present utility model in detail.

[0027] The present utility model provides a missile-borne high heat storage and heat equalization triangular prism frustum based on the 3D printing process, which is used for the installation and thermal control of a missile-borne omnidirectional phased array antenna group. As Figure 1 、 Figure 2As shown, the missile-borne high heat storage and heat equalization triangular prism includes a triangular prism body 1, a support skeleton 5, a grid frame 6, and a phase change material 8. The triangular prism body 1, the support skeleton 5, and the grid frame 6 are all formed by 3D printing.

[0028] The material of the triangular prism body 1 is aluminum silicon ten magnesium. As Figure 3 , Figure 4 shown, the side surface of the triangular prism body 1 is a heat interface 2, which is used to contact the heat-generating device of the phased array antenna. There are three such surfaces in total. The three side surfaces are mutually perpendicular to each other at 90° in space, and the projection angles of the normal directions of the three side surfaces on the horizontal plane are mutually 120°. The angle between the side surface and the horizontal plane is 54.74°. After the 3D printing and stress relief of the heat interface 2 are completed, machining is used for secondary processing such as roughness and dimensions, so that this surface meets the installation requirements of the phased array antenna. The heat generated by the phased array antenna is in contact with the triangular prism body 1 through this surface and conducted to the inside of the triangular prism body 1.

[0029] The bottom of the triangular prism body 1 is provided with mounting holes Ⅰ3. After the secondary processing is completed, the triangular prism body 1 is fixed to the missile body through the mounting holes Ⅰ3. The side surface of the triangular prism body 1 is also provided with mounting holes Ⅱ4 for the phased array antenna. The layout of the mounting holes Ⅱ4 on the three side surfaces is the same.

[0030] As Figure 5 shown, both the support skeleton 5 and the grid frame 6 are arranged inside the triangular prism body 1. The support skeleton 5 plays a role in supporting and increasing strength and stiffness. At the same time, it can increase the internal heat conduction ability. Specifically, the support skeleton 5 is completed by 3D printing in one step and is divided into main rods, secondary rods, and connecting rods. The main rods are vertically arranged at the central axis of the triangular prism. Taking the main rod as the center, multiple secondary rods radiate horizontally outward at different heights of the main rod until they contact the inner wall of the triangular prism body 1. The radiation directions of the upper and lower adjacent secondary rods are the same, and connecting rods are provided between the upper and lower adjacent secondary rods. There are six secondary rods radiating at each height, and the connecting lines of the connecting rods provided at this height form a regular hexagon. In this embodiment, the secondary rods are arranged in four layers, and the connecting rods are arranged in two circles from the inside to the outside.

[0031] The grid frame 6 can increase the internal heat conduction coefficient and improve the heat equalization ability, and is completed in one step during the 3D printing process. Specifically, the grid frame 6 includes a grid panel formed by horizontally and vertically intersecting metal rods, and multiple layers of grid panels are arranged at intervals.

[0032] The bottom surface of the triangular prism body 1 is provided with a filling port 7, which is used to fill the phase change material 8 into the inside after the processing is completed. After the filling is completed, it is sealed and pressure-tested to ensure that there is no leakage when the internal phase change material 8 melts and the pressure increases after heating. There are two filling ports 7, which are arranged at the two points on the bottom surface of the triangular prism body 1 with the farthest distance.

[0033] The internal cavity area of the triangular prism frustum body 1 is filled with a phase change material 8. The filling mass of the phase change material 8 needs to be determined through calculation and simulation according to the heat generation amount of the phased array antenna, environmental factors, thermal control requirements, etc. The phase change material 8 is a solid-solid phase change material with a phase change temperature of 31-33 °C. The selection of the phase change material 8 also needs to be determined through calculation and simulation according to the thermal control elements. Thanks to the much higher heat capacity of the phase change material 8 than that of pure metal under the same mass (including the sensible heat absorbed during temperature rise and the latent heat absorbed during the phase change process), to achieve the same thermal control purpose, the form of filling the phase change material 8 has much smaller weight and volume than using pure metal, which brings high benefits for missile-borne equipment.

[0034] In summary, the above are only the preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A missile-borne high heat storage and heat dissipation triangular prism based on 3D printing technology, characterized in that, It includes a triangular prism frustum body, a support skeleton, a grid frame and a phase change material; The side surface of the triangular prism frustum body is a thermal interface for contacting the heat generating device of the phased array antenna; the three side surfaces are mutually perpendicular to each other at 90° in space, and the projection angles of the normal directions of the three side surfaces on the horizontal plane are mutually perpendicular to each other at 120°; the support skeleton and the grid frame are both arranged inside the triangular prism frustum body for support and heat conduction; the phase change material is filled inside the triangular prism frustum body; a filling port is provided at the bottom surface of the triangular prism frustum body.

2. The high-heat-storage and heat-uniforming triangular prism for projectile based on 3D printing process according to claim 1, wherein The support skeleton is an integrated structure based on 3D printing, and is divided into main rods, sub-rods and connecting rods; The main rods are vertically arranged at the central axis of the triangular prism frustum, and with the main rods as the center, multiple sub-rods are horizontally radiated outward at different heights of the main rods until they contact the inner wall of the triangular prism frustum body. The radiation directions of the upper and lower adjacent sub-rods are the same, and connecting rods are provided between the upper and lower adjacent sub-rods.

3. The high-heat-storage and heat-smoothing triangular prism for projectile based on 3D printing process according to claim 2, wherein Six sub-rods are radiated at each height, and the connecting lines of the connecting rods provided at this height form a regular hexagon.

4. The high-heat-storage and heat-uniforming bullet-borne triangular prism based on the 3D printing process according to claim 1, characterized in that, The grid frame includes grid panels formed by horizontally and vertically intersecting metal rods, and multiple layers of grid panels are arranged at intervals.

5. The high-heat-storage and heat-smoothing triangular prism for missile-borne applications based on 3D printing technology according to claim 1, wherein There are two filling ports, which are arranged at the two points on the bottom surface of the triangular prism frustum body with the farthest distance.

6. The high-heat-storage and heat-uniforming bullet-borne triangular prism based on 3D printing process according to any one of claims 1-5, characterized in that, The material of the triangular prism frustum body is aluminum silicon ten magnesium.

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