阅读说明：本技术 一种空间行波管收集极凹球表面散热器 (Concave ball surface radiator for collector of space traveling wave tube ) 是由 沈理达 汪杰坤 李军 吕非 周凯 王鸿哲 柏华文 于 2021-05-12 设计创作，主要内容包括：本发明公开了一种空间行波管收集极凹球表面散热器,涉及航天热控技术及真空电子技术领域,包括位于所述散热器中央的金属套筒以及环绕该金属套筒布置的若干个翅片,所述翅片表面设有呈阵列分布的凹球形凹坑,凹坑大幅度增加了用于辐射的散热器表面积,同时减轻了散热器的重量。受益于表面积的增加,本发明可以显著增强散热器的辐射散热效果,同时减轻散热器的重量,减轻空间行波管的整体重量,从而间接减小卫星的重量并提高其运行的可靠性。(The invention discloses a concave spherical surface radiator for a collector of a space traveling wave tube, which relates to the technical field of aerospace thermal control and vacuum electronics. The invention can obviously enhance the radiation heat dissipation effect of the radiator, simultaneously reduce the weight of the radiator and the whole weight of the space traveling wave tube, thereby indirectly reducing the weight of the satellite and improving the operation reliability of the satellite.)

1. The utility model provides a space travelling wave tube collector concave sphere surface radiator which characterized in that: the radiator comprises a metal sleeve positioned in the center of the radiator and a plurality of fins arranged around the metal sleeve, wherein concave spherical pits distributed in an array form are formed in the surfaces of the fins.

2. The concave spherical surface heat sink for the collector of the space traveling wave tube according to claim 1, wherein: the number of the fins is plural, and the fins surround the outer diameter surface of the metal sleeve at equal intervals.

3. The concave spherical surface heat sink for the collector of the space traveling wave tube according to claim 2, wherein: the thickness of the fins of the radiator is 2mm, the number of the fins is 10, the fins are uniformly distributed outside the metal sleeve, and the angle interval between the adjacent fins is 36 degrees.

4. The concave spherical surface heat sink for the collector of the space traveling wave tube according to claim 2, wherein: the front surface and the back surface of the fin are respectively provided with concave spherical pits distributed in an array mode, the size of each concave ball is changed according to the radius of each concave ball, and the depth of each concave pit is controlled through the angle from the center point of each concave ball to the intersection point of each concave ball and the fin and the surface of the fin.

5. The concave spherical surface heat sink for the collector of the space traveling wave tube according to claim 4, wherein: concave spherical pits on the front surface and the back surface of the fin are arranged in a staggered mode, and the number of the pits is multiple.

6. The concave spherical surface heat sink for the collector of the space traveling wave tube according to any one of claims 1 to 5, wherein: the concave spherical pits are hemispherical so as to fully improve the surface area of the radiator.

7. The concave spherical surface heat sink for the collector of the spatial traveling wave tube according to any one of claims 6, wherein: the radius of the concave sphere is 1.6 mm.

8. The concave spherical surface heat sink for the collector of the space traveling wave tube according to claim 1 or 7, wherein: the radiator is made of aluminum alloy.

Technical Field

The invention relates to the technical field of aerospace thermal control and vacuum electronics, in particular to a concave ball surface radiator for a collector of a space traveling wave tube.

Background

The space traveling wave tube is a satellite-borne key device, is mainly used for final-stage power amplification and is a core component in an amplifier system. The space traveling wave tube mainly comprises an electron gun, an energy transmission structure, a slow wave structure, a magnetic system and a collector. At present, the number of space traveling wave tubes required in a satellite gradually increases (10-20), and a collector is used as a device and a component for collecting energy released by the traveling wave tubes in the traveling wave tubes, so that the working stability and reliability of the collector directly influence the service life of the whole space traveling wave tube. At present, thermal failure caused by overhigh temperature of the collector of the space traveling wave tube is a troublesome problem, and the heat radiator added on the collector also obviously increases the overall load of the satellite.

The vacuum environment of the space traveling wave tube is quite severe, and neither the current forced convection heat dissipation method nor the current natural convection heat dissipation method can be applied to the space traveling wave tube under the vacuum condition. Therefore, radiation heat dissipation is the only way to dissipate heat for a space traveling wave tube. Waste heat of the collector in the space traveling wave tube can be transferred to the radiation radiator through heat conduction and then radiated, so that the temperature of the collector is effectively controlled, and the working reliability and stability of the space traveling wave tube are ensured.

The conventional collector radiating fin of the space traveling wave tube mainly structurally comprises a central metal cylinder and a plurality of radiating fins outside the metal cylinder. However, the conventional radiation heat sink not only has a limited surface heat dissipation area, but also has a general heat dissipation performance and its own weight, which is a burden for the light operation of the space traveling wave tube and even the entire satellite.

Chinese patent invention with publication number CN 101894723B discloses a collector radiator for a space traveling wave tube in 24/11/2010, in which a groove is formed in a metal fin of the radiator, so that the weight of the collector radiator for a space traveling wave tube is reduced, but the cooling effect of the radiator is slightly reduced from experimental data.

Disclosure of Invention

Aiming at the problems, the invention discloses a concave spherical surface radiator for a collector of a space traveling wave tube, and aims to design concave spherical array pit surfaces on the front surface and the back surface of a radiating fin so as to increase the radiating area, obviously improve the cooling effect and reduce the weight of the radiator.

The utility model provides a space travelling wave tube collector concave sphere surface radiator which characterized in that: the radiator comprises a metal sleeve positioned in the center of the radiator and a plurality of fins arranged around the metal sleeve, wherein concave spherical pits distributed in an array form are formed in the surfaces of the fins.

Preferably, the number of the fins is a plurality, and the fins surround the outer diameter surface of the metal sleeve at equal intervals.

Preferably, the thickness of the fin is 2mm, so as to ensure that the fin has sufficient heat conduction performance and mechanical property. The excessive thickness of the fins also causes the increase of the overall weight of the radiator, the increase of the thickness mainly affects the heat conductivity of the fins, but the increase of the thickness has little influence on the overall heat radiation performance after tests, so that the smaller thickness of the fins is adopted. The number of the fins of the radiator is 10 so as to achieve a better heat dissipation level, the fins are uniformly distributed outside the metal sleeve, and the angle interval is 36 degrees.

Preferably, concave spherical pits are distributed in an array mode on the front surface and the back surface of the fin, the size of each concave ball changes according to the radius of each concave ball, and the depth of each concave pit is controlled according to the angle from the center point of each concave ball to the intersection point of each concave ball and the fin and the surface of the fin.

Preferably, the concave spherical pits on the front and back surfaces of the fin are arranged in a staggered manner, and the number of the pits is multiple. The pits are distributed in a staggered mode so as to avoid the mechanical property of the fin from being greatly reduced due to the pits, and meanwhile, the pits at the same position are prevented from penetrating through the fin. The staggered distribution makes the heat conduction more uniform, ensuring a sufficient heat conduction area.

Preferably, the concave spherical pits are hemispherical to sufficiently increase the surface area of the heat sink.

Preferably, the concave spherical radius is 1.6mm, and an excessively large concave pit will result in a decrease in the penetration and heat conduction rate of the fin, while impairing the mechanical properties of the fin. Too small dimples increase manufacturing complexity and accuracy, while not being effective in reducing the weight of the fins with limited heat dissipation capabilities.

Preferably, the heat sink is made of a material having a light weight and a certain thermal conductivity, such as an aluminum alloy, but not limited to an aluminum alloy.

Has the advantages that:

(1) the concave spherical pit structure of the array is arranged on the surface of the fin of the collector radiator of the space traveling wave tube, so that the surface area of the radiator can be effectively increased, the radiation heat dissipation performance is enhanced, and the temperature of the collector is reduced;

(2) the concave staggered arrangement of the front surface and the back surface of the collector radiator of the space traveling wave tube can increase the surface area to the maximum extent and control the reduction of the mechanical property of the radiator;

(3) the pits arranged on the surface of the collector radiator of the space traveling wave tube can reduce the overall weight of the radiator, so that the aim of reducing the weight of the radiator is effectively fulfilled, the overall load of a satellite is reduced, and the stable operation of the satellite is promoted.

Drawings

FIG. 1 is a schematic view of a conventional collector heat sink structure of a spatial traveling wave tube;

FIG. 2 is a schematic diagram of a collector heat sink fin surface array dimple angle design in accordance with an embodiment of the present invention;

FIG. 3 is a schematic view of a front view of a collector heat sink fin according to one embodiment of the present invention;

FIG. 4 is a schematic view of a collector heat sink fin reverse structure according to one embodiment of the present invention;

fig. 5 is a schematic structural view of a heat sink according to embodiment 1 of the present invention;

fig. 6 is a schematic structural view of a heat sink according to embodiment 2 of the present invention;

fig. 7 is a schematic structural view of a heat sink according to embodiment 3 of the present invention;

fig. 8 is a schematic view of a heat sink structure according to embodiment 4 of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The invention discloses a concave spherical surface radiator for a collector of a space traveling wave tube, which comprises a plurality of fins and a metal sleeve positioned in the centers of the fins. The front surface and the back surface of the fin are provided with arrayed hemispherical pits, the pits greatly increase the surface area of the radiator for radiation, and simultaneously, the weight of the radiator is reduced. The invention can obviously enhance the radiation heat dissipation effect of the radiator, simultaneously reduce the weight of the radiator and the whole weight of the space traveling wave tube, thereby indirectly reducing the weight of the satellite and improving the operation reliability of the satellite. Meanwhile, the radiation heat dissipation structure can be applied to other components which need radiation heat dissipation, and the weight of the radiator can be reduced while the heat dissipation effect is improved by adopting the concave spherical surface for radiation heat dissipation.

Fig. 1 is a schematic structural diagram of a conventional collector heat sink for a space traveling wave tube. The main structure comprises a metal cylinder at the center and a plurality of radiating fins at the outer part. However, the conventional radiation heat sink not only has a limited surface heat dissipation area, but also has a general heat dissipation performance and its own weight, which is a burden for the light operation of the space traveling wave tube and even the entire satellite.

As shown in fig. 2, a schematic diagram of the pit angle design of the collector radiator fin surface array is shown. The thickness of the radiator fin is w, the diameter of the concave ball is d, theta is an included angle between the concave ball and the fin surface, the depth of the concave ball is changed according to the change of theta, namely the depth of a concave ball pit can be controlled by controlling the size of theta. When θ is 0, the dimple is hemispherical. When the pits are hemispherical, the surface area of the heat sink can be sufficiently increased, so that the surface area is maximized and the volume is minimized. The concave spherical radius is preferably 1.6mm, and an excessively large dimple will result in a decrease in the penetration and heat conduction rates of the fin, while impairing the mechanical properties of the fin. Too small dimples increase manufacturing complexity and accuracy, while not being effective in reducing the weight of the fins with limited heat dissipation capabilities.

Fig. 3 is a schematic diagram of a front structure of a collector radiator fin. l is the length of the fin, and the set length is 58 mm. h is the height of the fin and is set to 50 mm. a1 is the distance from the uppermost row of dimples on the front of the fin to the top of the fin, b1 is the distance from the left row of dimples on the front of the fin to the left of the fin, c is the longitudinal distance between the fins, and d is the transverse distance between the fins. The distance from the uppermost pit to the upper end and the distance from the lowermost pit to the lower end of the fin are the same, the distance from the left-most row pit to the right-left row pit to the left end and the right end of the fin are the same, and the distance between the pits is also a fixed value so as to ensure the uniformity of heat conduction.

As shown in fig. 4, a2 is the distance from the uppermost row on the reverse side of the fin to the tip of the fin, and b2 is the distance from the leftmost column on the reverse side of the fin to the left end of the fin. c and d are the same as those in FIG. 3 and are fixed numbers. The pit arrays on the back side and the pit arrays on the front side are uniformly distributed in a staggered mode, so that the mechanical property of the fin is prevented from being greatly reduced due to the pits, and meanwhile, the pits at the same position are prevented from penetrating through the fin. The staggered distribution makes the heat conduction more uniform, ensuring a sufficient heat conduction area.

The thickness of the fins is preferably 2mm to ensure that the fins have sufficient heat conduction performance and mechanical properties. The excessive thickness of the fins also causes the increase of the overall weight of the radiator, the increase of the thickness mainly affects the heat conductivity of the fins, but the increase of the thickness has little influence on the overall heat radiation performance after tests, so that the smaller thickness of the fins is adopted. The number of the fins of the heat radiator is preferably 10 to achieve a better heat dissipation level, and the fins are uniformly distributed outside the metal sleeve at the angle interval of 36 degrees.

Example 1: as shown in fig. 5, a metal sleeve is arranged in the center of the radiator, 10 fins are uniformly distributed on the outer side of the radiator, the front and back rows of the fins are 72 concave ball surfaces and 56 concave ball surfaces respectively, a concave pit is hemispherical, theta is 0 degree, the radius of the concave ball is 1.6mm, d is 3.2mm, a1 is 2.6mm, b1 is 3.4mm, a2 is 5.8mm, b2 is 6.6mm, c and d are 6.4mm, and the inner diameter and the outer diameter of the metal sleeve are 28mm and 32mm respectively.

Example 2: as shown in fig. 6, a metal sleeve is arranged in the center of the concave spherical surface heat sink of the collector of the space traveling wave tube, 10 fins are uniformly distributed on the outer side of the metal sleeve, the front and back rows of the fins are respectively provided with 42 concave spherical surfaces and 30 concave spherical surfaces, a concave pit is hemispherical, theta is 0 degree, the radius of the concave spherical surface is 2mm, d is 4mm, a1 and b1 are 5mm, a2 and b2 are 9mm, and c and d are 8 mm.

Example 3: as shown in fig. 7, a concave spherical surface heat sink for a collector of a space traveling wave tube, wherein a metal sleeve is arranged in the center, 10 fins are uniformly distributed on the outer side, the front and back rows of the fins are respectively 120 concave spherical surfaces and 99 concave spherical surfaces, a concave pit is hemispherical, θ is 0 °, the radius of a concave sphere is 1.2mm, d is 2.4mm, a1 is 3.4mm, b1 is 2.6mm, a2 is 5.8mm, b2 is 5mm, and c and d are 4.8 mm.

Example 4: as shown in fig. 8, θ is 30 ° and the remaining dimensional parameters are the same as those of example 1.

The heat dissipation performance of the conventional collector radiator of the space traveling wave tube and the heat dissipation performance of examples 1 to 4 will be compared. At present, the heating power of the collector of the space traveling wave tube with larger power can reach more than 100 w. An ANSYS FLUENT was used to simulate the vacuum environment of space, setting a background temperature of 3k of cold space. And loading a solar radiation model, only considering the influence of radiation, setting the vacuum degree to be 0pa, and respectively setting the emissivity and the absorptivity of the surface of the radiator to be 0.8 and 0.4. An internal heat source of 110w is applied in a metal sleeve of the heat radiator to simulate the heat generated by a collector of the space traveling wave tube. The radiator is made of aluminum alloy materials, so that certain heat conductivity is guaranteed, and the requirement of light weight is met. The heat source material is copper, and the contact thermal resistance between the heat source and the radiator is neglected to simplify the operation.

Various embodiments and current conventional finned heat sinks dissipate heat as shown in table 1. The conventional fin heat sink and collector temperatures were the highest and 12 ℃ higher than in concave spherical surface example 1, and the weight of the conventional fin heat sink was also the highest, reaching 0.2412 kg. The heat sink with the concave spherical radius of 1.6mm in the embodiment 1 achieves the similar heat dissipation effect with the heat sink with the concave spherical radius of 1.2mm in the embodiment 3, and the temperature of the heat sink and the collector is the lowest value. The radiator in embodiment 1 has a significant advantage in weight, which is 0.0108kg lighter than that in embodiment 3. The heat sink of example 2 having a concave spherical radius of 2mm has a disadvantage in heat dissipation surface area compared with examples 1 and 3, and thus the heat dissipation effect is not good. As can be seen from a comparison of example 1 with example 4, the different θ angles affect the surface area of the heat sink and thus indirectly affect the heat dissipation performance. The maximum temperature of the heat sink and collector is significantly higher than 0 deg. at a theta of 30 deg.. In summary, embodiment 1 has the best heat dissipation performance while satisfying the requirement of light weight. The concave spherical fins are superior to the existing traditional radiating fins in radiating performance, and have more advantages in light weight.

TABLE 1

The comparison of the embodiments shows that the concave spherical surface radiator adopted by the invention reduces the volume of the radiator by increasing the surface area of the radiator, so that the overall heat radiation performance of the radiator is improved, the overall weight of the radiator is reduced, conditions are created for the stable operation of the space traveling wave tube, and the overall load of the satellite in operation is reduced.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.