CN212501116U

CN212501116U - Electronic investigation satellite capable of on-orbit release

Info

Publication number: CN212501116U
Application number: CN202020652358.3U
Authority: CN
Inventors: 杨峰; 任维佳; 杜志贵; 寇义民
Original assignee: Changsha Tianyi Space Technology Research Institute Co Ltd
Current assignee: Changsha Tianyi Space Technology Research Institute Co Ltd
Priority date: 2020-04-26
Filing date: 2020-04-26
Publication date: 2021-02-09
Anticipated expiration: 2030-04-26

Abstract

The utility model relates to an electronic investigation satellite that can carry out on-orbit release includes at least: a satellite body (1) which can be cylindrical; a receiving plate (2) that can be connected to the satellite body (1) by a vibration damping portion (3); -an on-rail release (4) which can be arranged on the receiving plate (2), the on-rail release (4) comprising at least a receiving compartment (401) in the shape of a hollow cube and at least one firing channel (402) arranged on the receiving compartment (401), wherein: the accommodating bin (401) is arranged on the bearing plate (2) in a rotatable mode.

Description

Electronic investigation satellite capable of on-orbit release

Technical Field

The utility model belongs to the technical field of the satellite, especially, relate to an electronic investigation satellite that can carry out the release in orbit.

Background

The traditional satellite generally adopts a rocket to launch into a preset orbit, and realizes the separation of a satellite and the rocket in a mode of belt unlocking or explosive bolt unlocking, and the 2 satellite release modes have complicated design and high cost. The in-orbit deployment mode of the micro-nano satellite generally comprises 3 modes, wherein the micro-nano satellite is connected with a carrier rocket and is directly released after entering an orbit, the micro-nano satellite is attached to a large satellite in a mother-child satellite mode, the micro-nano satellite is released in the orbit operation process of the large satellite, and the micro-nano satellite is released from a space station. Compared with a large satellite, the micro-nano satellite generally operates in orbit by adopting a multi-satellite networking mode, and the launching cost of the carrier rocket can be saved by one-time in-orbit multi-satellite release. In the prior art, a plurality of devices suitable for in-orbit release of a micro/nano satellite exist.

For example, patent document CN106516172B discloses an apparatus for in-orbit release of a micro/nano satellite, which includes: the device comprises a satellite storage box, a flexible unlocking device and a release spring; the flexible unlocking device comprises a fixed block and a flexible locking rope, the fixed block is arranged at the upper end of the satellite storage box, the flexible locking rope penetrates through one end of the satellite storage box and is fixedly connected with the fixed block, and the other end of the flexible locking rope abuts against the inner lower bottom surface of the satellite storage box to prevent the satellite from popping out; the release spring is arranged on the side surface of the satellite, and the satellite is placed in the satellite storage box. The invention can carry a plurality of micro-nano satellites and realize multi-satellite release at one time; the flexible unlocking device has small mechanical impact and is safe and reliable; the structure is simple, the installation is easy, the adaptability is strong, and the device can be installed in carrying, satellites and space stations.

In the prior art, the orientation of the satellite storage box cannot be adjusted conveniently. Therefore, the electronic investigation satellite can adjust the transmitting direction of the micro-nano satellite.

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".

To the deficiency of the prior art, the utility model provides an electronic investigation satellite that can carry out the on-orbit release includes at least: a satellite body that can be cylindrical; a receiving plate connectable to the satellite body through a vibration damping portion; an on-rail release portion capable of being disposed on the receiving plate, the on-rail release portion at least including a housing bin in a hollow cube shape and at least one launching channel disposed on the housing bin, wherein: the accommodating bin is arranged on the bearing plate in a self-rotating mode.

According to a preferred embodiment, at least one rotating shaft is arranged on the end surface of the accommodating bin, which is in contact with the bearing plate, at least one fixing hole is arranged on the bearing plate, and the accommodating bin is rotatably connected to the bearing plate in a manner that the rotating shaft is nested in the fixing hole.

According to a preferred embodiment, the end face is provided with at least one annular meshing rack, and the receiving plate is provided with at least one meshing gear capable of rotating, wherein: the engaging rack is abuttingly contactable to the engaging gear with the rotating shaft nested in the fixing hole.

According to a preferred embodiment, the in-orbit release part further comprises at least one base for placing a micro-nano satellite, which is arranged in the accommodating bin, wherein: the base with all be provided with the extending direction and the extending direction of launching the substantially parallel guide way of passageway in the passageway, be provided with on the micro nano satellite and can slide the nested slider in the guide way.

According to a preferred embodiment, the in-orbit release part further comprises a fixing rod and an elastic body, wherein the fixing rod and the elastic body are arranged in the accommodating bin, one end of the elastic body can be connected to the fixing rod, the other end of the elastic body can be connected to the micro-nano satellite, and the extending direction of the elastic body can be approximately parallel to the extending direction of the launching channel.

According to a preferred embodiment, the storage container is rotatable about the axis of rotation of the meshing gear, with the meshing gear rotating about its own central axis.

According to a preferred embodiment, the damping portion comprises at least a first damping body and a second damping body nestably arranged in the first damping body to define at least a first fixing point and a second fixing 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 convex portions and the concave portions may be alternately arranged with each other in a direction along a line connecting the first fixing point and the second fixing point.

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.

The utility model also provides a jettison device convenient to change transmission direction, jettison device includes at least: a receiving plate connectable to the satellite body through a vibration damping portion; the rail release part at least comprises a containing bin in a hollow cube shape and at least one launching channel arranged on the containing bin, and the containing bin is arranged on the bearing plate in a self-rotating mode.

The utility model has the advantages of: in the prior art, the orientation of the transmitting channel of the micro-nano satellite can be completed only by adjusting the orientation through the satellite body, the required time and the cost are higher, the orientation of the transmitting channel can be adjusted through the rotation of the meshing gear, and therefore the transmitting direction of the micro-nano satellite can be adjusted conveniently under the condition that the orientation of the satellite body is not changed.

Drawings

Fig. 1 is a schematic diagram of the overall structure of a preferred electronic detection satellite of the present invention;

FIG. 2 is a schematic structural view of a preferred in-orbit release of the present invention;

fig. 3 is a schematic view of a preferred arrangement of the meshing rack of the present invention; and

fig. 4 is a schematic structural view of a preferred vibration damping portion of the present invention.

List of reference numerals

1: the satellite body 2: the bearing plate 3: vibration damping part

4: on-rail release portion 5: end surface 6: rotating shaft

7: fixing hole 8: the meshing rack 9: meshing gear

10: micro-nano satellite 11: guide groove 12: sliding block

13: first fixing point 14: second fixing point 15: outer convex part

16: the concave portion 301: first vibration damping body 302: second vibration damping body

401: the housing bin 402: emission channel 403: base seat

404: fixing rod 405: elastic body

Detailed Description

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

Example 1

As shown in fig. 1 to 4, an electronic investigation satellite capable of performing on-orbit release at least includes: the satellite comprises a satellite body 1, a bearing plate 2, a vibration damping part 3 and an on-orbit release part 4. The satellite body 1 may be cylindrical. The receiving plate 2 can be connected to the satellite body 1 through the vibration damping portion 3. The rail release portion 4 can be provided on the receiving plate 2. The in-orbit release part 4 can store a plurality of micro/nano satellites 10, and the micro/nano satellites 10 can be released in an in-orbit manner through ejection. Vibration generated in the in-orbit release process of the micro/nano satellite can be partially absorbed by the vibration damping part 3, so that the influence of the vibration on the satellite body 1 can be reduced.

Preferably, as shown in fig. 1 and 2, the on-rail release part 4 at least comprises a housing bin 401 in the shape of a hollow cube and at least one launching channel 402 arranged on the housing bin 401. The storage bin 401 is provided on the receiving plate 2 so as to be rotatable. Specifically, at least one rotating shaft 6 is provided on an end surface 5 of the accommodating chamber 401, which is in contact with the receiving plate 2. The bearing plate 2 is provided with at least one fixing hole 7. The receiving bin 401 is rotatably connected to the receiving plate 2 in such a manner that the rotating shaft 6 is nested in the fixing hole 7. Preferably, a rolling bearing can be further disposed in the fixing hole 7, and the rotating shaft 6 can be nested in the rolling bearing to enable the accommodating chamber 401 to rotate. At least one annular meshing rack 8 is arranged on the end surface 5. The receiving plate 2 is provided with at least one meshing gear 9 capable of rotating. With the rotary shaft 6 nested in the fixing hole 7, the meshing rack 8 can be brought into abutting contact with the meshing gear 9. In the case where the meshing gear 9 rotates about its own central axis, the housing 401 can rotate on its own axis about the rotation shaft 6. Preferably, a driving motor and a power supply for supplying power to the driving motor can be further arranged in the bearing plate 2, or the driving motor can be electrically connected to the satellite body 1 to realize power supply thereof. The drive motor can be connected to the meshing gear 9, thereby providing a driving force for rotation of the meshing gear 9. In the prior art, the orientation of the transmitting channel of the micro-nano satellite can be completed only by adjusting the orientation through the satellite body 1, the required time and the cost are higher, the orientation of the transmitting channel can be adjusted through the rotation of the meshing gear 9, and therefore the transmitting direction of the micro-nano satellite can be adjusted conveniently under the condition that the orientation of the satellite body 1 is not changed.

Preferably, referring again to fig. 1 and 2, the in-orbit release part 4 further includes at least one base 403 for placing the micro-nano satellite 10, which is disposed in the accommodating bin 401. The base 403 and the launching channel 402 are each provided therein with a guide groove 11 extending in a direction substantially parallel to the extending direction of the launching channel 402. The micro-nano satellite 10 is provided with a slide block 12 which can be nested in the guide groove 11 in a sliding manner. The sliding block 12 can slide along the guide groove 11, and the accuracy of the micro-nano satellite in the transmitting direction can be further improved. It can be understood that an electromagnetic locking technology in the prior art can be adopted, that is, an electromagnet is arranged in the guide groove 11, and the electromagnet can adsorb the sliding block 12 when being electrified, so that the micro-nano satellite can be parked in the accommodating bin 401. When the electromagnet is powered off, the micro-nano satellite can be ejected out of the accommodating bin 401. The electromagnet can be powered by the satellite body or by an independent power supply arranged in the bearing plate.

Preferably, referring again to fig. 1 and 2, the on-rail releasing part 4 further includes a fixing rod 404 and an elastic body 405 provided in the accommodating compartment 401. The elastomer 405 may be a compression spring. One end of the elastic body 405 can be connected to the fixing rod 404. The other end of the elastic body 405 can be connected to the micro/nano satellite 10. The extension direction of the elastic body 405 can be substantially parallel to the extension direction of the firing channel 402. When the micro-nano satellite is placed in the accommodating bin, the elastic body 405 can be in a compressed state, and then after the slider 12 is free from movement limitation, the micro-nano satellite can be ejected out of the accommodating bin 401 based on elastic potential energy of the elastic body.

Preferably, as shown in fig. 4, the vibration damping portion 3 includes at least a first vibration damping body 301 and a second vibration damping body 302. The second damping body 302 can be arranged nested in the first damping body 301 to define at least a first fastening point 13 and a second fastening point 14. The second vibration damping body 302 can rotate about a line connecting the first fixed point 13 and the second fixed point 14 as a rotation axis. The first damping body 301 and the second damping body 302 each comprise at least a number of male portions 15 and a number of female portions 16. The male protrusions 15 and the female protrusions 16 can be arranged alternately with each other in a direction along a line connecting the first fixing point 13 and the second fixing point 14. With the first and second damping

bodies

301, 302 substantially parallel to one another, the outer protrusion 15 of the second damping body 302 can be nested in the outer protrusion 15 of the first damping body 301, wherein the shape of both the outer protrusion 15 and the inner recess 16 can be defined by a U-shape. In use, the first damping body 301 and the second damping body 302 can be perpendicular to each other and cross. When in transport or storage, the second vibration damping body 302 can be rotated such that the second vibration damping body 302 is substantially parallel to the first vibration damping body 301, at which point the second vibration damping body 302 is completely nested in the first vibration damping body 301, so that the transport space or storage space required for the vibration damping portion 3 can be reduced. Preferably, as shown in fig. 4, the vibration damping portion further includes a first flange connected to the first fixing point, and a second flange connected to the second fixing point. The first flange and the second flange can facilitate the connection and fixation of the vibration damping part and, for example, a satellite body. Threaded holes can be formed in the first fixing point and the second fixing point, T-shaped holes can be formed in the first flange plate and the second flange plate, and then the first flange plate and the first fixing point are connected through T-shaped bolts, and the second flange plate and the second fixing point are connected through T-shaped bolts.

For ease of understanding, the working principle of the electronic reconnaissance satellite of the present application is explained.

When the electronic detection satellite runs in a designated orbit and needs to emit the micro-nano satellite, firstly, the satellite body can control the driving motor to work so as to enable the meshing gear 9 to rotate, and then the orientation of the emission channel 402 can be changed, and after the emission channel is adjusted to the set orientation, the satellite body 1 is in contact with the movement limitation of the sliding block 12, so that the micro-nano satellite can be ejected out of the accommodating bin 401 based on the elastic potential energy of the elastic body 405.

Example 2

As shown in fig. 1 to 3, the present application also provides an ejector device for facilitating the change of the launching direction, which comprises at least a receiving plate 2 and an on-rail release part 4. The receiving plate 2 can be connected to the satellite body 1 through the vibration damping portion 3. The on-rail release 4 comprises at least a receiving compartment 401 in the form of a hollow cube and at least one firing channel 402 arranged on the receiving compartment 401. The storage bin 401 is provided on the receiving plate 2 so as to be rotatable. In the prior art, the orientation of the transmitting channel of the micro-nano satellite can be completed only by adjusting the orientation through the satellite body 1, the required time and the cost are higher, the orientation of the transmitting channel can be adjusted through the rotation of the meshing gear 9, and therefore the transmitting direction of the micro-nano satellite can be adjusted conveniently under the condition that the orientation of the satellite body 1 is not changed.

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

1. An electronic investigation satellite capable of on-orbit release, comprising at least:

a satellite body (1) which can be cylindrical;

a receiving plate (2) that can be connected to the satellite body (1) by a vibration damping portion (3);

a rail release part (4) which can be arranged on the bearing plate (2),

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

the on-orbit release part (4) at least comprises a containing cabin (401) in a hollow cube shape and at least one launching channel (402) arranged on the containing cabin (401), wherein:

the accommodating bin (401) is arranged on the bearing plate (2) in a rotatable mode.

2. The electronic investigation satellite according to claim 1, characterized in that an end face (5) of the receiving bin (401) contacting the receiving plate (2) is provided with at least one rotating shaft (6), the receiving plate (2) is provided with at least one fixing hole (7), and the receiving bin (401) is rotatably connected to the receiving plate (2) in such a manner that the rotating shaft (6) is nested in the fixing hole (7).

3. Electronic investigation satellite according to claim 2, characterized in that the end face (5) is provided with at least one annular meshing rack (8), and the receiving plate (2) is provided with at least one meshing gear (9) capable of rotating, wherein:

the meshing rack (8) is abuttingly contactable to the meshing gear (9) with the rotary shaft (6) nested in the fixing hole (7).

4. Electronic investigation satellite according to claim 3, characterized in that the in-orbit release (4) further comprises at least one base (403) for placing micro-nano satellites (10) arranged in the housing compartment (401), wherein:

guide grooves (11) with the extending directions approximately parallel to the extending direction of the transmitting channel (402) are formed in the base (403) and the transmitting channel (402), and a sliding block (12) capable of being nested in the guide grooves (11) in a sliding mode is arranged on the micro-nano satellite (10).

5. The electronic investigation satellite of claim 4, wherein the in-orbit release part (4) further comprises a fixing rod (404) and an elastic body (405) arranged in the accommodating bin (401), one end of the elastic body (405) can be connected to the fixing rod (404), the other end of the elastic body (405) can be connected to the micro-nano satellite (10), wherein the extending direction of the elastic body (405) can be approximately parallel to the extending direction of the launching channel (402).

6. The electronic investigation satellite according to claim 5, characterized in that the housing bin (401) is capable of rotating on its own axis of rotation about the axis of rotation (6) in the event that the meshing gear wheel (9) rotates about its own axis of rotation.

7. Electronic investigation satellite according to claim 6, wherein the damping portion (3) comprises at least a first damping body (301) and a second damping body (302), the second damping body (302) being nestably arranged in the first damping body (301) to define at least a first fixing point (13) and a second fixing point (14), wherein: the second vibration damping body (302) is capable of rotating around a line connecting the first fixed point (13) and the second fixed point (14) as a rotation axis.

8. Electronic investigation satellite according to claim 7, wherein the first and second damping bodies (301, 302) each comprise at least a number of male portions (15) and a number of female portions (16), wherein:

the male protrusions (15) and the female protrusions (16) can be arranged alternately with each other in a direction along a line connecting the first fixing point (13) and the second fixing point (14).

9. Electronic investigation satellite according to claim 8, characterized in that with the first and second damping bodies (301, 302) substantially parallel to each other, the male portion (15) of the second damping body (302) can be nested in the male portion (15) of the first damping body (301), wherein the shape of both the male portion (15) and the female portion (16) can be defined by a U-shape.