CN212515012U - Synthetic aperture radar satellite for enhancing vibration reduction - Google Patents

Abstract

The utility model relates to a synthetic aperture radar satellite of reinforcing damping includes at least: a satellite body (1) which can be cylindrical; a support plate (2) on which a power supply part (3) is arranged; -a damping mechanism (4) which can be arranged between the satellite body (1) and the bearing plate (2), the damping mechanism (4) comprising at least a first damping body (4a) and a second damping body (4b), the second damping body (4b) being nestably arranged in the first damping body (4a) so as to define at least a first fixing point (5) and a second fixing point (6), wherein: the second vibration damping body (4b) is capable of rotating about a line connecting the first fixed point (5) and the second fixed point (6) as a rotation axis.

Description

Synthetic aperture radar satellite for enhancing vibration reduction

Technical Field

The utility model belongs to the technical field of the satellite, especially, relate to a synthetic aperture radar satellite of reinforcing damping.

Background

With the development of remote sensing satellite technology, the imaging precision of loads such as ground optical imaging cameras, ground mapping cameras and mapping radars is higher and higher, and the loads are more sensitive to micro-vibration interference. And various movable parts of the satellite inevitably generate vibration interference when in operation in orbit. For example, a Control Moment Gyro (CMG) is a posture control member commonly used for satellites, and inevitably generates vibration disturbance during high-speed rotation. The in-orbit micro-vibration of the satellite is transmitted to the camera through the satellite structure, which causes the degradation of the imaging quality. In the prior art, there are many vibration isolation devices with different functions.

For example, patent document No. CN105276076B discloses a novel high-precision hybrid vibration isolation device, which includes a mounting plate, a middle partition plate, a bottom plate, an air spring, and a magnetorheological damper, wherein the mounting plate is connected to the middle partition plate through the magnetorheological damper, the middle partition plate is fixedly connected to the air spring through a bolt, and the bottom plate is fixedly connected to the air spring. The magnetorheological dampers are used for isolating low-frequency vibration signals from the ground, and the 4 groups of magnetorheological dampers have vibration isolation capability in six-degree-of-freedom directions in view of the fact that ground signal sources can be transmitted in multi-dimensional directions. The air spring and the magneto-rheological damper are reasonably connected with the middle partition plate, so that high-precision active and passive mixed vibration isolation capability can be realized.

In the prior art, the manufacturing cost of the vibration damper is high, and meanwhile, the vibration damper has more accessory parts, and the connection between the parts is complex, so that the assembly and the transportation of the vibration damper are not facilitated. Therefore, the present application aims to provide a vibration damping member and a radar satellite equipped with the same, which have a simple assembly structure and can reduce the occupied space.

Furthermore, on the one hand, due to the differences in understanding to the person skilled in the art; on the other hand, since the inventor studied a lot of documents and patents when making the present invention, but the space did not list all details and contents in detail, however, this is by no means the present invention does not possess these prior art features, but on the contrary the present invention has possessed all features of the prior art, and the applicant reserves the right to increase the related prior art in the background art.

Disclosure of Invention

The word "module" as used herein describes any type of hardware, software, or combination of hardware and software that is capable of performing the functions associated with the "module".

Not enough to prior art, the utility model provides a synthetic aperture radar satellite of reinforcing damping includes at least: a satellite body that can be cylindrical; a support plate on which a power supply part is arranged; a damping mechanism positionable between the satellite body and the support plate, the damping mechanism including at least a first damping body and a second damping body nestably positionable within the first damping body to define at least a first fixed point and a second fixed point, wherein: the second vibration damping body is capable of rotating about a line connecting the first fixed point and the second fixed point as a rotation axis.

According to a preferred embodiment, the first damping body and the second damping body each comprise at least a number of male portions and a number of female portions, wherein: the male protrusions and the female protrusions may be alternately arranged with each other in the first direction.

According to a preferred embodiment, the male part of the second damping body can be nested in the male part of the first damping body, with the first and second damping bodies being substantially parallel to one another, wherein the shape of both the male and female parts can be defined by a U-shape.

According to a preferred embodiment, the first end of the first damping body can be brought into abutting contact with the second end of the second damping body to define said first fixing point, and the third end of the first damping body can be brought into abutting contact with the fourth end of the second damping body to define said second fixing point.

According to a preferred embodiment, the first end is provided with a first flange, and the third end is provided with a second flange.

According to a preferred embodiment, the power supply comprises at least a base body, around which a first end of the base body and/or a second end of the base body can be wound, with the power supply being arranged on the support plate so as to define at least one third fixing point, wherein: the shape of the base can be defined by a circle with the first end in abutting contact with the second end.

According to a preferred embodiment, a fixed shaft is arranged on the third fixed point, and a first rotating rod and a second rotating rod are rotatably arranged on the fixed shaft, wherein: the first rotary lever is connectable to the first end and the second rotary lever is connectable to the second end, wherein the first end is abuttingly contactable to the second end in a case where the first rotary lever is rotated in a second direction and the second rotary lever is rotated in a third direction; the second direction is opposite to the third direction.

According to a preferred embodiment, the first rotary lever can be provided on one end of the fixed shaft and the second rotary lever can be provided on the other end of the fixed shaft, wherein: a first coil spring is arranged between the first rotating rod and the fixed shaft, and a second coil spring is arranged between the second rotating rod and the fixed shaft.

According to a preferred embodiment, the fixing shaft is provided with fixing holes on both ends, the fixing holes are provided with rolling bearings, and the first rotating rod or the second rotating rod can be nested in the rolling bearings, wherein: the first rotating lever can stop rotating in a case where the locking portion is in abutting contact with the first rotating lever, or the second rotating lever can stop rotating in a case where the locking portion is in abutting contact with the second rotating lever.

The utility model also provides a damping part, including damping mechanism at least, damping mechanism includes first damping body and the second damping body at least, the second damping body can nest set up in order to inject first fixed point and second fixed point at least in the first damping body, wherein: the second vibration damping body is capable of rotating about a line connecting the first fixed point and the second fixed point as a rotation axis.

The utility model has the advantages of: when using, first damping body can be the cross with the second damping body and is described, when installing and depositing, the second damping body can rotate, and then nests completely in first damping body so that first damping body and second damping body can be roughly parallel, thereby can reduce the shared storage space of damping mechanism.

Drawings

Fig. 1 is a schematic structural diagram of a preferred damping mechanism of the present invention;

fig. 2 is a schematic diagram of the overall structure of a preferred synthetic aperture radar satellite of the present invention;

FIG. 3 is a schematic structural view of a preferred power supply unit of the present invention;

fig. 4 is a schematic view of the arrangement of the first coil spring or the second coil spring according to the present invention;

FIG. 5 is a schematic view of the preferred power supply portion of the present invention, shown in a shape that is not fully folded;

FIG. 6 is a schematic view showing the shape of a power supply unit according to a preferred embodiment of the present invention after being developed; and

fig. 7 is a schematic structural view of a preferred locking portion of the present invention.

List of reference numerals

1: the satellite body 2: a bearing plate 3: power supply unit

4: the vibration damping mechanism 5: first fixing point 6: second fixing point

7: outer convex portion 8: the concave portion 9: first end

10: second end 11: third end 12: fourth terminal

13: first flange 14: second flange 15: third fixing point

16: first end portion 17: second end portion 18: first rotating rod

19: second rotating lever 20: fixed shaft 21: first coil spring

22: second coil spring 23: fixing hole 24: rolling bearing

25: locking part

3 a: base 4 a: first vibration damping body 4 b: second vibration damping body

25 a: locking block 25 b: the slider 25 c: electromagnet

25 d: elastomer 25 e: sliding groove

Detailed Description

The following detailed description is made with reference to the accompanying drawings.

Example 1

As shown in fig. 1 to 7, the present application provides a synthetic aperture radar satellite with enhanced vibration damping, including at least a satellite body 1, a support plate 2, a power supply unit 3, and a vibration damping mechanism 4. The satellite body 1 may be cylindrical. The support plate 2 is provided with a power supply portion 3. The power supply unit 3 can be electrically connected to the satellite body 1, and can supply power to the satellite body 1. The vibration damping mechanism 4 can be provided between the satellite body 1 and the support plate 2. During the vibration generated by the power supply unit 3 performing an operation such as deployment, a part of the vibration can be absorbed by the vibration reduction mechanism 4, thereby reducing the influence of the vibration on the satellite body 1.

Preferably, as shown in fig. 1, the damping mechanism 4 includes at least a first damping body 4a and a second damping body 4 b. The second damping body 4b can be arranged nested in the first damping body 4a to define at least a first fixing point 5 and a second fixing point 6. The second vibration damping body 4b can rotate about a line connecting the first fixed point 5 and the second fixed point 6 as a rotation axis. Specifically, as shown in fig. 1, each of the first vibration damping body 4a and the second vibration damping body 4b includes at least a plurality of convex portions 7 and a plurality of concave portions 8. In the first direction, the male protrusions 7 and the female protrusions 8 can be alternately arranged with each other. The first direction may be a vertical direction. The alternate arrangement means that: an outer convex part 7 is arranged between two adjacent inner concave parts 8. Alternatively, one concave portion 8 is provided between two adjacent convex portions 7. When the first damper body 4a and the second damper body 4b are substantially parallel to each other, the outward protruding portion 7 of the second damper body 4b can be fitted into the outward protruding portion 7 of the first damper body 4 a. The shape of both the male part 7 and the female part can be defined by a U-shape. When the vibration damping mechanism is used, the first vibration damping body 4a and the second vibration damping body 4b can be in a cross shape, when the vibration damping mechanism is installed and stored, the second vibration damping body 4b can rotate, and then is completely nested in the first vibration damping body 4b, so that the first vibration damping body and the second vibration damping body can be approximately parallel, and the storage space occupied by the vibration damping mechanism can be reduced.

Preferably, again with reference to fig. 1, the first end 9 of the first damping body 4a can be in abutting contact to the second end 10 of the second damping body 4b to define the first fixing point 5. The third end 11 of the first damping body 4a can be brought into abutting contact with the fourth end 11 of the second damping body 4b to define the second fastening point 6. The first end 9 is provided with a first flange 13. The third end 11 is provided with a second flange 14. For example, threaded holes may be provided in the first fixing points 5 and the second fixing points 6, T-shaped holes may be provided in the first flange 13 and the second flange 14, and the first flange or the second flange may be fixed by T-shaped bolts. Meanwhile, as shown in fig. 2, the vibration damping mechanism can be connected to the satellite body 1 via the first flange 13. The vibration damping mechanism can be connected to the power supply portion 3 via the second flange 14.

Preferably, as shown in fig. 2 and 3, the power supply portion 3 includes at least a base body 3 a. In case the power supply part 3 is arranged on the support plate 2 to define at least one third fixing point 15, the first end 16 of the base body 3a and/or the second end 17 of the base body 3a can be wound around the third fixing point 15. The shape of the base body 3a can be defined by a circle with the first end 16 in abutting contact with the second end 17. The base body 3a may be made of a shape memory alloy, and its shape can be defined by a thin plate shape, thereby enabling the base body 3a to be folded or bent. It is understood that the substrate 3a may be provided with a sheet-like organic solar cell, which is formed by using an organic material having a photosensitive property as a semiconductor material to form a film in a large area, so that the power supply portion can convert solar energy into electric energy. Specifically, as shown in fig. 3, 5 and 6, the third fixing point 15 is provided with a fixing shaft 20. The fixed shaft 20 is rotatably provided with a first rotating rod 18 and a second rotating rod 19. A first rotary lever 18 can be connected to the first end 16. A second rotary lever 19 can be connected to the second end 17. In the case where the first rotating lever 18 is rotated in the second direction and the second rotating lever 19 is rotated in the third direction, the first end 16 can be in abutting contact to the second end 17. The second direction is opposite to the third direction. For example, as shown in fig. 5, the second direction may be a counterclockwise direction. The third direction may be a clockwise direction. The base body 3a can be unfolded or folded like a folding fan, thereby enabling the space it occupies during the satellite launch. And since the power supply portion is circular after being developed, it can provide a larger light receiving surface than a power supply portion having a square shape. It will be appreciated that a plurality of support frames may also be provided between the first and second rotary bars 18, 19. The support armature can be connected to the base body 3a to provide support for the base body 3a, and the support armature can rotate about a fixed axis. The support frame is similar to a fan rib in a folding fan.

Preferably, as shown in fig. 3 and 4, the first rotating lever 18 can be disposed on one end of the fixed shaft 20, and the second rotating lever 19 can be disposed on the other end of the fixed shaft 20. A first coil spring 21 is disposed between the first rotating lever 18 and the fixed shaft 20 to provide power required for the rotation of the first rotating lever 18. A second coil spring 22 is disposed between the second rotating lever 19 and the fixed shaft 20 to provide power required for the rotation of the second rotating lever 19.

Preferably, as shown in fig. 3 and 7, fixing holes 23 are provided on both end portions of the fixing shaft 20. A rolling bearing 24 is provided in the fixing hole 23. The first rotary lever 18 or the second rotary lever 19 can be arranged nested in the rolling bearing 24. By providing a rolling bearing, the first or second rotary lever can be made to rotate relative to the stationary shaft 20.

Preferably, the synthetic aperture radar further includes a locking part 25 provided in the fixed shaft 20. With the locking portion 25 in abutting contact to the first rotating lever 18, the first rotating lever 18 can stop rotating. Alternatively, in the case where the locking portion 25 is in abutting contact to the second rotating lever 19, the second rotating lever 19 can stop rotating. Specifically, as shown in fig. 7, the locking portion 14 includes at least a locking piece 25a, a slider 25b, an electromagnet 25c, an elastic body 25d, and a slide groove 25 e. In a case where one end of the elastic body 25d is connected to the slider 25b, the locking piece 25a can be provided on the other end of the elastic body 25 d. The elastic body 25d may be a spring. The sliding groove 25e is provided in the fixed shaft 20. The slider 25b is slidably disposed in a sliding groove 25e, wherein the sliding groove 25e can extend in a direction substantially perpendicular to the axial direction of the fixed shaft 20. The locking block 25a can be connected to the slider 25 b. With the electromagnet 25c and the slider 25b attracted to each other, the lock block 25a can be brought into abutting contact with the first rotating lever or the second rotating lever. Specifically, the working principle of the locking part is as follows: when electro-magnet 25c circular telegram, it can adsorb slider 25b, and then makes slider 25b move left, and at this moment, elastomer 25d is in compression state for latch segment 25a can lean on with first rotary rod or second rotary rod and contact based on the elastic potential energy of elastomer 25d, and then restricts the rotation of first rotary rod or second rotary rod. When the electromagnet 25c is powered off, the sliding block 25b moves rightward based on the elastic potential energy of the elastic body, so that the locking block 25a is separated from the first rotating rod or the second rotating rod, and the first rotating rod or the second rotating rod can rotate under the action of the elastic potential energy stored in the first coil spring or the second coil spring.

For ease of understanding, the principles of operation of the synthetic aperture radar satellites of the present application are explained.

The first damping body 4a and the second damping body 4b can be substantially parallel to each other when on the ground to reduce the space they need to occupy during transport. During installation, the second damping body 4b can be rotated such that the second damping body 4b can cross the first damping body 4 a. The vibration damping mechanism can be connected to the satellite body 1 by means of bolts and the first flange 13. The power supply part can be connected to the vibration damping mechanism through the bolt and the second flange plate, and vibration generated by the power supply part in the unfolding process can be partially absorbed by the vibration damping mechanism, so that the aim of vibration isolation can be fulfilled. When the satellite launches and enters a designated orbit through on-orbit release, for example, the electromagnet can be powered off in a manual control mode such as remote control, or a timing breaker can be arranged in a circuit of the electromagnet, and when the set time is reached, the electromagnet is powered off automatically, so that the solar cell array is triggered to be unfolded. The circuit of the electromagnet can be formed by connecting the electromagnet, the timing breaker and the power supply in series.

Example 2

As shown in fig. 1, the present application provides a vibration damping member including at least a vibration damping mechanism 4. The damping mechanism 4 includes at least a first damping body 4a and a second damping body 4 b. The second damping body 4b can be arranged nested in the first damping body 4a to define at least a first fixing point 5 and a second fixing point 6. The second vibration damping body 4b can rotate about a line connecting the first fixed point 5 and the second fixed point 6 as a rotation axis. When the vibration damping device is used, the first vibration damping body 4a and the second vibration damping body 4b can be in a cross shape, when the vibration damping device is installed and stored, the second vibration damping body 4b can rotate, and then the first vibration damping body and the second vibration damping body can be completely nested in the first vibration damping body 4b to be approximately parallel, so that the storage space occupied by the vibration damping components can be reduced.

It should be noted that the above-mentioned embodiments are exemplary, and those skilled in the art can devise various solutions in light of the present disclosure, which are also within the scope of the present disclosure and fall within the scope of the present disclosure. It should be understood by those skilled in the art that the present specification and drawings are illustrative only and are not limiting upon the claims. The scope of the invention is defined by the claims and their equivalents.

Claims (9)

1. A synthetic aperture radar satellite with enhanced vibration reduction, comprising at least:

a satellite body (1) which can be cylindrical;

a support plate (2) on which a power supply part (3) is arranged;

a vibration reduction mechanism (4) which can be provided between the satellite body (1) and the support plate (2),

it is characterized in that the preparation method is characterized in that,

the damping mechanism (4) comprises at least a first damping body (4a) and a second damping body (4b), the second damping body (4b) being nestably arranged in the first damping body (4a) to define at least a first fixing point (5) and a second fixing point (6), wherein: the second vibration damping body (4b) is capable of rotating about a line connecting the first fixed point (5) and the second fixed point (6) as a rotation axis.

2. The synthetic aperture radar satellite according to claim 1, wherein the first damping body (4a) and the second damping body (4b) each comprise at least a number of male parts (7) and a number of female parts (8), wherein:

the male protrusions (7) and the female protrusions (8) can be arranged alternately with each other in the first direction.

3. The synthetic aperture radar satellite according to claim 2, characterized in that with the first and second damping bodies (4a, 4b) substantially parallel to each other, the male part (7) of the second damping body (4b) can be nested in the male part (7) of the first damping body (4a), wherein the shape of both the male part (7) and the female part (8) can be defined by a U-shape.

4. Synthetic aperture radar satellite according to claim 3, wherein a first end (9) of the first damping body (4a) is abuttable to a second end (10) of the second damping body (4b) to define said first fixation point (5), and a third end (11) of the first damping body (4a) is abuttable to a fourth end (12) of the second damping body (4b) to define said second fixation point (6).

5. Synthetic aperture radar satellite according to claim 4, wherein said first end (9) is provided with a first flange (13) and said third end (11) is provided with a second flange (14).

6. Synthetic aperture radar satellite according to claim 5, characterized in that the power supply (3) comprises at least a base body (3a), around which third fixing point (15) the first end (16) of the base body (3a) and/or the second end (17) of the base body (3a) can be wound, in case the power supply (3) is arranged on the support plate (2) to define at least one third fixing point (15), wherein:

the shape of the base body (3a) can be defined by a circle with the first end (16) in abutting contact with the second end (17).

7. The synthetic aperture radar satellite according to claim 6, wherein a stationary shaft (20) is arranged on the third stationary point (15), and wherein a first rotating shaft (18) and a second rotating shaft (19) are rotatably arranged on the stationary shaft (20), wherein:

the first rotary lever (18) being connectable to the first end (16), the second rotary lever (19) being connectable to the second end (17), wherein the first end (16) is abuttingly contactable to the second end (17) in the case of a rotation of the first rotary lever (18) in a second direction and a rotation of the second rotary lever (19) in a third direction;

the second direction is opposite to the third direction.

8. The synthetic aperture radar satellite according to claim 7, wherein the first rotary rod (18) is arrangeable on one end of a stationary shaft (20) and the second rotary rod (19) is arrangeable on the other end of the stationary shaft (20), wherein:

a first coil spring (21) is arranged between the first rotating rod (18) and the fixed shaft (20), and a second coil spring (22) is arranged between the second rotating rod (19) and the fixed shaft (20).

9. The synthetic aperture radar satellite according to claim 8, wherein a fixed shaft (20) is provided with a fixed hole (23) on both ends, a rolling bearing (24) is provided in the fixed hole (23), and the first rotating rod (18) or the second rotating rod (19) is nestably provided in the rolling bearing (24), wherein:

the synthetic aperture radar further comprises a locking portion (25) disposed in the fixed shaft (20), wherein the first rotary rod (18) can stop rotating when the locking portion (25) is in contact with the first rotary rod (18), or the second rotary rod (19) can stop rotating when the locking portion (25) is in contact with the second rotary rod (19).

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