CN110957558B - Antenna support and spacecraft - Google Patents
Antenna support and spacecraft Download PDFInfo
- Publication number
- CN110957558B CN110957558B CN201911167175.0A CN201911167175A CN110957558B CN 110957558 B CN110957558 B CN 110957558B CN 201911167175 A CN201911167175 A CN 201911167175A CN 110957558 B CN110957558 B CN 110957558B
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- Prior art keywords
- antenna
- frame body
- spacecraft
- compartment
- viscous fluid
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/1242—Rigid masts specially adapted for supporting an aerial
-
- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/023—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Details Of Aerials (AREA)
Abstract
The invention provides an antenna support and a spacecraft, wherein the antenna support comprises: the frame body at least partially penetrates through each compartment, and viscous fluid is filled in the compartments. The antenna bracket provided by the invention is based on the principle of tuned liquid damping, and the bracket, the compartment and the viscous fluid form a damping buffer device. In the launching stage of the spacecraft, the vibration and the impact of the spacecraft are transmitted to the bottom end of the frame body, so that viscous fluid in the separation chamber shakes, the moving side pressure is generated on the frame body, and the acceleration response of the top end of the frame body is reduced; meanwhile, the vibration of the viscous fluid can effectively absorb and consume the vibration energy of the support so as to achieve the effect of damping and buffering, reduce the acceleration response of the antenna load in the launching section of the spacecraft and improve the adaptability and reliability of the antenna load and the support body.
Description
Technical Field
The invention relates to the technical field of space equipment, in particular to an antenna bracket and a spacecraft.
Background
The low-orbit broadband communication satellite communication load generally has the load of a reflector antenna of a working system of mechanical scanning. In order to avoid rotation interference, antenna loads such as an antenna load and a servo rotating shaft need to be fixedly connected with the star body through a mounting bracket, and the rotating shaft is supported to a position with a certain height away from the star body. The mounting bracket plays a role in bearing mechanical loads such as vibration and impact of antenna loads on the transmitting section.
The mounting bracket is generally formed by an aluminum alloy thick plate through a precision machine, the bottom of the mounting bracket is provided with a mounting interface with the star body, and the upper part of the mounting bracket is provided with a mounting interface with the antenna load.
In the prior art, the antenna load mounting bracket is simple in structure. However, due to the height of the mounting bracket, the vibration shock actually experienced by the antenna load may be amplified.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art or the related art.
In view of the above, an object of the present invention is to provide an antenna support.
Another object of the present invention is to provide a spacecraft having the antenna mount described above.
In order to achieve the above object, a first aspect of the present invention provides an antenna stand, including: the frame body at least partially penetrates through each compartment, and viscous fluid is filled in the compartments.
At least one sealed compartment is arranged between the top end and the bottom end, and viscous fluid is filled in the compartment.
In this scheme, the top and the antenna load of support body are connected, and the bottom and the spacecraft of support body are connected, are equipped with at least one compartment between top and the bottom, and the support body passes and has filled the viscous fluid in compartment and the compartment, and like this, based on harmonious liquid damping's principle, support, compartment and have constituted damping buffer with the viscous fluid.
In the launching stage of the spacecraft, the vibration and the impact of the spacecraft are transmitted to the bottom end of the frame body, so that viscous fluid in the separation chamber shakes, the moving side pressure is generated on the frame body, and the acceleration response of the top end of the frame body is reduced; meanwhile, the vibration of the viscous fluid can effectively absorb and consume the vibration energy of the support so as to achieve the effect of damping and buffering, reduce the acceleration response of the antenna load in the launching section of the spacecraft, further reduce the vibration impact on the antenna load and improve the adaptability and reliability of the antenna load and the support body.
In the above technical solution, preferably, the frame body is formed by a plurality of rod bodies which are mutually crossed and connected, and the rod bodies penetrate through the compartment and are fixedly connected with the compartment.
In any of the above technical solutions, preferably, the material of the rod body is an aluminum alloy.
In any of the above technical solutions, preferably, the frame body has a pyramid lattice structure.
In any of the above technical solutions, preferably, the method further includes: and the skin is wrapped on the outer side of the frame body.
In any of the above technical solutions, preferably, the compartment includes: the bin body is fixedly connected with the frame body and is provided with an opening; the sealing plug is detachably arranged in the opening, and after viscous fluid flows into the bin body through the opening, the sealing plug can be embedded into the opening and seal the opening.
In any of the above embodiments, preferably, the viscous fluid is silicone oil.
In any of the above technical solutions, preferably, the frame body is located entirely within the compartment at a position where the frame body penetrates the compartment.
In any of the above technical solutions, preferably, the compartment is located at one end of the top of the frame body.
In a second aspect of the present invention, a spacecraft is provided, including: a spacecraft body, an antenna load and an antenna mount in any of the technical solutions of the first aspect; one end of the support body of the antenna support is fixedly connected with the spacecraft body, and the other end of the support body is fixedly connected with the antenna load.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
FIG. 1 is a side view of an antenna mount according to one embodiment of the invention;
FIG. 2 is a side view of an antenna mount according to one embodiment of the invention;
fig. 3 is a partially enlarged view of a portion a in fig. 2.
Wherein, the correspondence between the reference numbers and the component names in fig. 1 to 3 is:
the device comprises a frame body 10, a rod body 11, a compartment 20, a compartment body 21, a sealing plug 22, a skin 30, an antenna load 40 and viscous fluid 50.
Detailed Description
So that the manner in which the above recited objects, features and advantages of the present invention can be understood in detail, a more particular description of the invention, briefly summarized above, may be had by reference to the embodiments thereof which are illustrated in the appended drawings. It should be noted that the embodiments and features of the embodiments of the present application may be combined with each other without conflict.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those specifically described herein, and therefore the scope of the present invention is not limited by the specific embodiments disclosed below.
Some embodiments according to the invention are described below with reference to fig. 1 to 3.
As shown in fig. 1 to 3, an embodiment of a first aspect of the present invention provides an antenna mount, user spacecraft, comprising: the antenna comprises a frame body 10, wherein the top end of the frame body 10 is provided with an interface connected with an antenna load 40, the bottom end of the frame body 10 is provided with an interface connected with a spacecraft, at least one sealed compartment 20 is arranged between the top end and the bottom end, a viscous fluid 50 is filled in the compartment 20, and at least part of the frame body 10 penetrates through each compartment 20.
In the scheme, the top end of the frame body 10 is connected with the antenna load 40, the bottom end of the frame body 10 is connected with the spacecraft, at least one compartment 20 is arranged between the top end and the bottom end, the frame body 10 penetrates through the compartment 20, and the compartment 20 is filled with the viscous fluid 50, so that the support, the compartment 20 and the viscous fluid 50 form the damping and buffering device based on the principle of tuned liquid damping.
In the launching stage of the spacecraft, the vibration and the impact of the spacecraft are transmitted to the bottom end of the frame body 10, so that the viscous fluid 50 in the separation chamber 20 shakes, the dynamic side pressure is generated on the frame body 10, and the acceleration response of the top end of the frame body 10 is reduced; meanwhile, the vibration of the viscous fluid 50 can effectively absorb and consume the vibration energy of the support so as to achieve the effect of shock absorption and buffering, reduce the acceleration response of the antenna load 40 in the launching section of the spacecraft, further reduce the vibration impact on the antenna load 40, and improve the adaptability and reliability of the antenna load 40 and the support body 10.
In the above embodiment, preferably, the frame body 10 is composed of a plurality of rod bodies 11 which are crossed and connected with each other, and the rod bodies 11 pass through the compartment 20 and are fixedly connected with the compartment 20.
In this scheme, support body 10 is for having the hollow framework of a plurality of interconnect's the body of rod 11, can reduce the weight of support when making the intensity of support up to standard, and then reduce the whole weight of spacecraft.
In any of the above embodiments, preferably, the material of the rod body 11 is an aluminum alloy.
In this scheme, the material of the body of rod 11 is the aluminum alloy, and aluminum alloy strength is high light in weight, can reduce the holistic weight of spacecraft.
In any of the above embodiments, the frame 10 preferably has a pyramid lattice structure.
In this scheme, support body 10 is pyramid type lattice structure, and the energy-absorbing effect and the shock resistance of support body 10 are better.
In the pyramid lattice structure in this embodiment, on the front view plane, the tower body includes the horizontal rod body and the oblique rod body that intersects each other, and the oblique rod body and the vertical plane all form an included angle of 45 °. The three rods intersect at one point.
On the right sight face, the body all includes the horizontal body of rod and the slope body of rod of intercrossing, and the slope body of rod all is 45 contained angles with vertical face. The three rods intersect at one point.
In any of the above embodiments, preferably, the method further includes: and the skin 30 is wrapped on the outer side of the frame body 10.
Wherein preferably the skin 30 is formed for 3D printing additive manufacturing.
In any of the above embodiments, preferably, the compartment 20 comprises: the bin body 21 is fixedly connected with the frame body 10, and an opening is formed in the bin body 21; the sealing plug 22 is detachably arranged in the opening, and after the viscous fluid 50 flows into the bin body 21 through the opening, the sealing plug 22 can be embedded into the opening to seal the opening.
In any of the above embodiments, preferably, the viscous fluid 50 is silicone oil.
In the scheme, the viscous fluid 50 is silicon oil, the low-temperature performance of the silicon oil is good, and good physical properties (especially viscous properties) can be kept at low temperature, so that the silicon oil still can have good damping and buffering effects when the spacecraft is raised to a higher height in the launching stage of the spacecraft.
In any of the above embodiments, the shelves are preferably located entirely within the compartment 20 where they extend through the compartment 20.
In this scheme, on the cross section that runs through compartment 20, support body 10 all is located compartment 20, and like this, the vibration transmission of support body 10 bottom is all transmitted through compartment 20 to the in-process on support body 10 top, and compartment 20's buffering effect is better.
Preferably, as shown in fig. 1 to 3, the number of the compartments 20 is three, and the compartments 20 are sequentially arranged in the height direction of the bracket, so that the vibration transmitted from the bottom end to the top end of the frame body 10 can be greatly reduced through the shock absorption and buffering of the plurality of compartments 20, and the vibration impact received by the antenna load 40 is further reduced.
In any of the above embodiments, preferably, the compartment 20 is located at one end of the top of the frame 10.
In this scheme, compartment 20 is located the half section at support body 10 top, and compartment 20 is close to the top of support body 10 promptly, and the half section amplitude of vibration that support body 10 is close to the top is bigger, and viscous fluid's oscillation is more obvious, and the energy-absorbing effect is better, and then makes compartment 20's shock attenuation cushioning effect better.
Embodiments of a second aspect of the invention provide a spacecraft comprising: a spacecraft body, an antenna load 40 and an antenna mount in any embodiment of the first aspect; the bottom end of the frame body 10 of the antenna support is fixedly connected with the spacecraft body, and the top end of the frame body 10 is fixedly connected with the antenna load 40.
The spacecraft provided by the scheme has all the beneficial effects of the technical scheme due to the antenna support in any technical scheme of the first aspect, and the description is omitted here.
The spacecraft comprises a space shuttle and a satellite.
Specifically, when the spacecraft is a satellite, the spacecraft body is a star, the bottom end of the antenna support is fixed to the star, and the top end of the antenna support is fixed to the antenna load 40.
In the satellite launching section, the vibration and impact of the rocket body are transmitted to the bottom end of the antenna bracket, so that the viscous fluid 50 in the compartment shakes, the moving side pressure is generated on the frame body 10, and the acceleration response of the top end of the frame body 10 is reduced; while the oscillation of the viscous fluid 50 can effectively absorb and dissipate the vibration energy of the housing 10. Thereby achieving the purpose of shock absorption and buffering.
After the satellite enters the orbit, the large vibration and shock disappear, and the viscous fluid 50 is in a free state. The frame 10 serves as a base for rigidity in the operation of the antenna load 40.
The technical scheme of the invention is explained in detail by combining the attached drawings, and the antenna bracket provided by the invention is based on the principle of tuned liquid damping, and the bracket, the compartment and the viscous fluid form a damping and buffering device. In the launching stage of the spacecraft, the vibration and the impact of the spacecraft are transmitted to the bottom end of the frame body, so that viscous fluid in the separation chamber shakes, the moving side pressure is generated on the frame body, and the acceleration response of the top end of the frame body is reduced; meanwhile, the vibration of the viscous fluid can effectively absorb and consume the vibration energy of the support so as to achieve the effect of damping and buffering, reduce the acceleration response of the antenna load in the launching section of the spacecraft and improve the adaptability and reliability of the antenna load and the support body.
In the present invention, the terms "first", "second", and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; the term "plurality" means two or more unless expressly limited otherwise. The terms "mounted," "connected," "fixed," and the like are to be construed broadly, and for example, "connected" may be a fixed connection, a removable connection, or an integral connection; "coupled" may be direct or indirect through an intermediary. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "left", "right", "front", "rear", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the referred device or unit must have a specific direction, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
In the description herein, the description of the terms "one embodiment," "some embodiments," "specific embodiments," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. 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.
Claims (9)
1. An antenna stand, comprising:
a frame body (10);
at least one sealed compartment (20), said frame (10) passing at least partially through each of said compartments (20) and said compartments (20) being filled with a viscous fluid (50);
the frame body (10) comprises a plurality of intercrossing and connected rod bodies (11), and the rod bodies (11) penetrate through the separation bins (20) and are fixedly connected with the separation bins (20).
2. The antenna stand of claim 1,
the rod body (11) is made of aluminum alloy.
3. The antenna stand of claim 1,
the frame body (10) is of a pyramid lattice structure.
4. The antenna stand of claim 1, further comprising:
and the skin (30) is wrapped on the outer side of the frame body (10).
5. An antenna stand according to any of claims 1 to 4, characterized in that the compartment (20) comprises:
the bin body (21) is fixedly connected with the frame body (10), and an opening is formed in the bin body (21);
the sealing plug (22) is detachably arranged in the opening, and after viscous fluid (50) flows into the bin body (21) through the opening, the sealing plug (22) can be embedded into the opening and seal the opening.
6. The antenna stand according to any one of claims 1 to 4,
the viscous fluid (50) is silicone oil.
7. The antenna stand according to any one of claims 1 to 4,
the frame body (10) is completely positioned in the separation bin (20) at the position where the frame body penetrates through the separation bin (20).
8. The antenna stand according to any one of claims 1 to 4,
the compartment (20) is positioned at one end of the top of the frame body (10).
9. A spacecraft, comprising:
-a spacecraft body, an antenna load (40) and an antenna mount according to any one of claims 1 to 8;
one end of a frame body (10) of the antenna support is fixedly connected with the spacecraft body, and the other end of the frame body (10) is fixedly connected with the antenna load (40).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911167175.0A CN110957558B (en) | 2019-11-25 | 2019-11-25 | Antenna support and spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911167175.0A CN110957558B (en) | 2019-11-25 | 2019-11-25 | Antenna support and spacecraft |
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| CN110957558A CN110957558A (en) | 2020-04-03 |
| CN110957558B true CN110957558B (en) | 2021-06-15 |
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| CN110957558A (en) | 2020-04-03 |
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