CN117022672A

CN117022672A - Thin film spacecraft

Info

Publication number: CN117022672A
Application number: CN202311203919.6A
Authority: CN
Inventors: 彭福军; 毛科力
Original assignee: Shenzhen Graduate School Harbin Institute of Technology
Current assignee: Shenzhen Graduate School Harbin Institute of Technology
Priority date: 2023-09-15
Filing date: 2023-09-15
Publication date: 2023-11-10

Abstract

The application discloses a thin-film spacecraft, which comprises communication electronic equipment, a star, a barrel, a longitudinal telescopic mechanism, at least one thin-film antenna structure and a wrapping structure, wherein an opening is formed in one side of the star; the cylinder is positioned at the opening and connected with the star body, and the central hole of the cylinder is communicated with the opening; one end of the longitudinal telescopic mechanism is connected in the star body, and the other end of the longitudinal telescopic mechanism is connected with the communication electronic equipment so as to drive the communication electronic equipment to shrink into the star body or extend out of the cylinder body; the film antenna structure is respectively connected with the communication electronic equipment, the longitudinal telescopic mechanism and the cylinder body so as to extend and retract along with the longitudinal telescopic mechanism; the folding structure is arranged on the longitudinal telescopic mechanism and is positioned at one side of the communication electronic equipment far away from the star. According to the application, a part of the longitudinal telescopic mechanism is contracted into the star body, so that the film antenna structure is driven to fold and fold along the length direction and then coiled and folded between the folding structure and the cylinder body, and the space occupied by the folded film antenna structure on the star body is reduced.

Description

Thin film spacecraft

Technical Field

The application relates to the technical field of spacecrafts, in particular to a thin-film spacecraft.

Background

The spacecraft is also called a spacecraft and a space vehicle and operates in space according to the law of astronomical mechanics.

However, the existing spacecraft is composed of an independent star body and a unfolding mechanism, the unfolding mechanism is provided with a film antenna structure, and the surface of the star body is connected with the unfolding mechanism.

In view of this, the prior art is still to be improved and enhanced.

Disclosure of Invention

In view of the above-mentioned shortcomings of the prior art, the present application aims to provide a thin film spacecraft, which aims to solve the technical problem that the thin film antenna structure occupies too much space when transmitting along with a satellite.

The technical scheme adopted for solving the technical problems is as follows:

a thin film spacecraft, comprising communication electronics, further comprising:

a star, wherein one side of the star is provided with an opening;

the cylinder is positioned at the opening and connected with the star, and the central hole of the cylinder is communicated with the opening;

one end of the longitudinal telescopic mechanism is connected with the star body, and the other end of the longitudinal telescopic mechanism is connected with the communication electronic equipment so as to drive the communication electronic equipment to shrink into the star body or stretch out of the cylinder body;

at least one film antenna structure connected with the communication electronic equipment, the longitudinal telescopic mechanism and the cylinder respectively so as to be telescopic along with the longitudinal telescopic mechanism;

the wrapping structure is arranged on the longitudinal telescopic mechanism and is positioned on one side, far away from the star, of the communication electronic equipment, and when the communication electronic equipment is positioned in the star, the wrapping structure can be sleeved outside the cylinder and limits the film antenna structure between the film antenna structure and the cylinder.

As a further improvement, the longitudinal telescopic mechanism includes:

one end of the longitudinal extending arm is fixedly connected with the star body, and the other end of the longitudinal extending arm is fixedly connected with the top end of the communication electronic equipment;

and one end of the support column is fixedly connected with the bottom end of the communication electronic equipment, and the other end of the support column is connected with the wrapping structure.

As a further improvement, the longitudinally extending arm includes:

the air source is fixedly connected in the star body;

the top end of the first sleeve is fixedly connected with the air source;

one end of the second sleeve is connected in the first sleeve in a sliding way;

one end of the third sleeve is connected in the second sleeve in a sliding way, and the other end of the third sleeve is fixedly connected with the communication electronic equipment;

the gas transmission pipe, the one end of gas transmission pipe with the air supply is connected, the other end pass first sleeve second sleeve and behind the third sleeve with communication electronic equipment is connected, the air supply to the gas transmission pipe carries compressed gas, makes the third sleeve the second sleeve moves in proper order and extends, and drives the gas transmission pipe extends.

As a further improved technical solution, the thin film spacecraft further comprises:

and the pod rod is connected with one end of the film antenna structure, one end of the pod rod is connected with the cylinder body, and the other end of the pod rod is limited between the wrapping structure and the cylinder body.

As a further improvement, the wrapping structure includes:

the packing cylinder frame is arranged at one end, far away from the communication electronic equipment, of the support column, and a compressing and unlocking structure is sleeved on the outer side of the packing cylinder frame;

the shaft end baffles are correspondingly arranged at the top end and the bottom end of the gathering cylinder frame;

the limiting rotating shafts are connected between the two corresponding shaft end baffles.

As a further improved technical scheme, the compressing and unlocking structure comprises:

the mounting seats are circumferentially and uniformly distributed on the outer side of the gathering cylinder frame;

the metal sleeves are arranged on the mounting seat;

the two limiting blocks are symmetrically arranged on two sides of the cylinder body and fixedly connected with the bottom end of the star body, and the limiting blocks are positioned between the two metal sleeves;

the unlocking units are symmetrically arranged on two sides of the cylinder body and fixedly connected with the bottom end of the star body, and the unlocking units are positioned between the two metal sleeves and are separated from the limiting block;

the binding ropes pass through the metal sleeves, the two limiting blocks and the two unlocking units and are connected end to end.

As a further improvement technical scheme, be equipped with in the unblock unit and be used for fusing the thermal fuse of bundle rope, the unblock unit is equipped with the connecting cylinder in opposite both sides for after the thermal fuse fuses the bundle rope, the bundle rope still keeps in the connecting cylinder, in order to prevent after the fuse link rope and fly up and down.

As a further improvement technical scheme, the packing structure further includes:

and the damper is arranged at the bottom end of the folding cylinder frame and is connected with one end of the support column far away from the communication electronic equipment.

As a further improvement, the damper includes:

the shell is fixedly connected to the bottom end of the folding cylinder frame;

the inner core is arranged in the shell, is rotationally connected with the shell, and is fixedly connected with one end, far away from the communication electronic equipment, of the support column;

and the viscous liquid is arranged between the shell and the inner core and is used for providing reverse damping force for the rotation of the shell.

As a further improvement, the film antenna structure includes:

one end of the thin film substrate is connected with the pod rod, and the other end of the thin film substrate is connected with the bottom end of the communication electronic equipment;

and the antenna vibrators are arranged on the film substrate at intervals along the length direction of the film substrate.

Compared with the prior art, the application has the beneficial effects that:

the application provides a thin film spacecraft, which is characterized in that a longitudinal telescopic mechanism is arranged in a star body, so that the star body and the longitudinal telescopic mechanism are integrally connected, a part of the longitudinal telescopic mechanism is contracted into the star body, a thin film antenna structure is driven to fold and fold along the length direction, and the thin film antenna structure is coiled and folded between a folding structure and a cylinder body, so that the space occupied by the folded thin film antenna structure on the star body is reduced.

Drawings

FIG. 1 is a schematic structural view of a thin film spacecraft in an unfolded state;

FIG. 2 is a front view of FIG. 1;

FIG. 3 is a partial schematic view of a thin film antenna structure;

FIG. 4 is a partial cutaway view of a thin film spacecraft in a collapsed state;

FIG. 5 is a schematic view of the lateral deployment mechanism in a deployed state;

FIG. 6 is a schematic view of a connection between a tucking feature and a compression release feature;

FIG. 7 is a schematic structural view of a damper;

fig. 8 is a schematic structural view of the longitudinal stopper.

The numerical labels in the figures are represented as: 1. a star; 2. a lateral deployment mechanism; 201. pod stems; 202. a wrapping structure; 2021. a cylinder frame is folded; 2022. a limiting rotating shaft; 2023. a shaft end baffle; 203. a cylinder; 204. a positioning structure; 2041. a longitudinal limit frame; 2042. a positioning frame; 205. compressing the unlocking structure; 2051. a limiting block; 2052. bundling ropes; 2053. a metal sleeve; 2054. an unlocking unit; 2055. a mounting base; 206. a damper; 2061. an inner core; 2062. a housing; 2063. a viscous fluid; 3. a longitudinal telescopic mechanism; 301. a longitudinally extending arm; 3011. a first sleeve; 3012. a second sleeve; 3013. a third sleeve; 3014. a gas pipe; 3015. a gas source; 302. a support column; 4. a thin film antenna structure; 401. a thin film substrate; 402. an antenna element; 5. communication electronic equipment.

Detailed Description

In order to make the objects, technical solutions and effects of the present application clearer and more specific, the present application will be described in further detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the application.

It will be understood that when an element is referred to as being "mounted" or "disposed" on another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.

It should also be noted that in the drawings of the embodiments of the present application, the same or similar reference numerals correspond to the same or similar components; in the description of the present application, it should be understood that, if there is an azimuth or positional relationship indicated by terms such as "upper", "lower", "left", "right", etc., based on the azimuth or positional relationship shown in the drawings, it is only for convenience of describing the present application and simplifying the description, but it is not indicated or implied that the apparatus or element referred to must have a specific azimuth, be constructed and operated in a specific azimuth, and thus, terms describing the positional relationship in the drawings are merely for exemplary illustration and are not to be construed as limitations of the present patent, and specific meanings of the terms described above may be understood by those skilled in the art according to specific circumstances.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.

Example 1

As shown in fig. 1 and 2, fig. 1 is a schematic structural view of a thin film spacecraft in an unfolded state; fig. 2 is a front view of fig. 1. Specifically, this embodiment provides a thin film spacecraft, including communication electronic equipment 5, star 1, barrel 203, vertical telescopic machanism 3, at least one thin film antenna structure 4 and package structure 202, wherein, the bottom side of star 1 is provided with the opening, barrel 203 is located the open-ended bottom, and with the bottom of star 1 is fixed connection, the centre bore of barrel 203 with the opening is linked together, vertical telescopic machanism 3 sets up in the star 1, just the one end of vertical telescopic machanism 3 with the top of star 1 is fixed connection, the other end with communication electronic equipment 5 is fixed connection, in order to drive communication electronic equipment 5 shrink to in the star 1, or stretch out outside the barrel 203.

As shown in fig. 4, fig. 4 is a partial cutaway view of the thin film spacecraft in a collapsed state. Specifically, the longitudinal telescopic mechanism 3 includes a longitudinal extending arm 301 and a supporting column 302, the top end of the longitudinal extending arm 301 is fixedly connected with the top end of the star 1, and the bottom end is fixedly connected with the top end of the communication electronic device 5; the top end of the support column 302 is fixedly connected with the bottom end of the communication electronic device 5. When the longitudinally extending arms 301 are deployed, the communications electronic device 5 moves downwardly and sequentially through the opening and the barrel 203, causing the film antenna structure 4 to deploy.

The longitudinal stretching arm 301 includes an air source 3015, a first sleeve 3011, a second sleeve 3012, a third sleeve 3013, and an air pipe 3014, where the air source 3015 is fixedly connected to the top end of the star 1, and the air source 3015 is specifically a cylinder, which of course, should be understood that other driving devices in the prior art are also possible; the top end of the first sleeve 3011 is fixedly connected with the air source 3015; one end of the second sleeve 3012 is slidingly connected in the first sleeve 3011; one end of the third sleeve 3013 is slidably connected in the second sleeve 3012, and the other end is fixedly connected with the communication electronic device 5, where the communication electronic device 5 may be a computer, a radar, or any communication device in the prior art under the condition of meeting the actual needs; one end of the air pipe 3014 is connected with the air source 3015, the other end of the air pipe 3014 passes through the first sleeve 3011, the second sleeve 3012 and the third sleeve 3013 and then is connected with the communication electronic device 5, and the air source 3015 conveys compressed air to the air pipe 3014, so that the third sleeve 3013 and the second sleeve 3012 sequentially move and stretch, and the air pipe 3014 is driven to stretch, so that the communication electronic device 5 descends and stretches out of the cylinder 203.

The inner wall bottom of first sleeve 3011 is provided with first spacing portion, the outer wall top of second sleeve 3012 is provided with second spacing portion, second spacing portion with first spacing portion offsets, prevents that second sleeve 3012 breaks away from first sleeve 3011.

The inner wall bottom of second sleeve 3012 is provided with the third spacing portion, the outer wall top of third sleeve 3013 is provided with the fourth spacing portion, the fourth spacing portion with the third spacing portion offsets, prevents that third sleeve 3013 breaks away from second sleeve 3012.

The inner diameter of the first sleeve 3011 is larger than the outer diameter of the second sleeve 3012, and the inner diameter of the second sleeve 3012 is larger than the outer diameter of the third sleeve 3013. Of course, it should be understood that the third sleeve 3013 may be removed as needed, or a fourth sleeve may be added on the basis of the third sleeve 3013, where the outer diameter of the fourth sleeve is smaller than the inner diameter of the third sleeve 3013, and so on.

As shown in fig. 5, fig. 5 is a schematic structural view of the lateral deployment mechanism in the deployed state. Specifically, the folding structure 202, the cylinder 203, and four pod rods 201 form a transverse unfolding mechanism 2 shown in fig. 5, a central hole is provided in the middle of the cylinder 203, the support column 302 passes through the cylinder 203 and then is connected with the folding structure 202, the communication electronic device 5 can pass through the opening and the cylinder 203 along with the driving of the support column 302, and the top end of the cylinder 203 is fixedly connected with the bottom end of the star 1; one end of the pod rod 201 is connected with the cylinder 203, and the other end is located between the folding structure 202 and the cylinder 203, and can be ejected from a gap between the folding structure 202 and the cylinder 203 under the action of elastic potential energy.

Specifically, the pod rod 201 is capable of storing elastic potential energy, in the unfolded state, the pod rod 201 is straightened, and the cross section is pod-shaped, and it should be noted that the pod-shaped can be simply understood as a double-omega-shaped closed cross section, and the pod-shaped has better bearing rigidity, if the cross section is flattened, the bending rigidity is greatly weakened, so that the pod rod 201 can be easily curled and coiled between the wrapping structure 202 and the cylinder 203, so as to achieve the gathering of the pod rod 201; when the pod rod 201 is ejected from the gap between the tucking feature 202 and the barrel 203, the flattened cross-section will gradually spring back automatically to the original pod shape, and the pod rod 201 will straighten out and expand.

The folding structure 202 is used for folding the pod rod 201 and the film antenna structure 4 after folding, and can limit the pod rod 201 to be unfolded synchronously along the gaps of four directions of the folding structure 202 in the unfolding process of the film antenna structure 4.

Specifically, the wrapping structure 202 includes a wrapping cylinder frame 2021, a plurality of shaft end baffles 2023, and a plurality of limiting rotating shafts 2022, where the wrapping cylinder frame 2021 is located at the bottom end of the star 1 and is connected to one end of the support column 302 away from the communication electronic device 5; every two shaft end baffles 2023 are correspondingly arranged at the top end and the bottom end of the folding cylinder frame 2021; the limiting rotating shaft 2022 is located between the two corresponding shaft end baffles 2023, and is connected to the shaft end baffles 2023, and is circumferentially and uniformly distributed on the outer side of the folding cylinder frame 2021, so as to limit the ejection of the pod rod 201.

As a further preferable solution of this embodiment, the number of the shaft end baffles 2023 is eight, the number of the limiting rotating shafts 2022 is four, and the four limiting rotating shafts 2022 are circumferentially and uniformly distributed on the outer side of the folding cylinder frame 2021.

The positioning structure 204 is disposed in the folding cylinder frame 2021, the positioning structure 204 includes a positioning frame 2042 and a longitudinal limiting frame 2041, and the bottom end of the positioning frame 2042 is detachably connected with the folding cylinder frame 2021, for example: is fixedly connected through bolts; or a boss is provided at the bottom end of the cylinder 2021, and the positioning frame 2042 is engaged with the boss, which is not limited in this embodiment no matter what connection method is adopted. The longitudinal limiting frame 2041 is disposed on the positioning frame 2042, and the cylinder 203 is sleeved on the outer side of the longitudinal limiting frame 2041 and is fixed by bolts, so as to improve the connection stability of the cylinder 203 and the longitudinal limiting frame 2041.

It should be noted that the positioning frame 2042 is used to assist the pod rod 201 and the film antenna structure 4 to be folded so as to be smoothly wound on the surface of the cylinder 203. The positioning frame 2042 is connected to an end of the support column 302 remote from the communication electronic device 5.

As shown in fig. 8, fig. 8 is a schematic structural view of the longitudinal limiting frame. Specifically, the longitudinal limiting frame 2041 is formed by combining four structural frames, and the structures of the four structural frames are completely identical.

The longitudinal limiting frame 2041 is used for reserving a space for the expansion and contraction of the longitudinal expansion mechanism 3, the cylinder 203 is used for winding the pod rod 201, a gap in the middle is used for enabling the longitudinal expansion arm 301 to smoothly pass through, dislocation of the longitudinal expansion arm 301 in a central space is prevented, the longitudinal expansion arm 301 cannot normally expand, meanwhile, materials can be saved, and weight is reduced. When the longitudinal extension arm 301 extends, the folding cylinder frame 2021 drives the positioning frame 2042 to disengage from the cylinder 203.

As shown in fig. 6, fig. 6 is a schematic structural diagram of the connection between the folding structure and the pressing and unlocking structure. Specifically, the compressing and unlocking structure 205 is circumferentially disposed on the outer side of the folding cylinder frame 2021, so as to apply an inward compressing force to the folding cylinder frame 2021, the compressing and unlocking structure 205 is fixedly connected with the bottom end of the star 1, and the compressing and unlocking structure 205 releases the folding cylinder frame 2021 after unlocking.

Specifically, the compressing and unlocking structure 205 includes a plurality of mounting seats 2055, a plurality of metal sleeves 2053, two limiting blocks 2051, two unlocking units 2054 and a bundling rope 2052, wherein the plurality of mounting seats 2055 are circumferentially and uniformly distributed on the outer side of the folding cylinder frame 2021, and a gap for ejecting the pod rod 201 is reserved between every two mounting seats 2055 of the folding cylinder frame 2021; the metal sleeve 2053 is embedded in the mounting seat 2055 to prevent the metal sleeve 2053 from moving, and the surface of the metal sleeve 2053 is provided with clamping grooves which are distributed along the length direction of the metal sleeve 2053; two limiting blocks 2051 are symmetrically arranged on two sides of the cylinder 203 and fixedly connected with the bottom end of the star 1, and the limiting blocks 2051 are positioned between two metal sleeves 2053; the two unlocking units 2054 are symmetrically arranged at two sides of the cylinder 203 and fixedly connected with the bottom end of the star 1, and the unlocking units 2054 are positioned between the two metal sleeves 2053 and are separated from the limiting block 2051. In short, the connection line between the two limiting blocks 2051 and the connection line between the two unlocking units 2054 are arranged in a crisscross manner; the binding rope 2052 is connected end to end after passing through a plurality of metal sleeves 2053, two limiting blocks 2051 and two unlocking units 2054, and one side of the binding rope 2052 is attached to the bottom wall of the clamping groove, so that the binding rope 2052 is tensioned on the outer side of the folding cylinder frame 2021.

The unlocking unit 2054 is internally provided with a thermal fuse for fusing the binding rope 2052, when the unlocking unit 2054 is unlocked, the thermal fuse heats and fuses the binding rope 2052, so that the pressing force is released, two heating and cutting working points are designed in the embodiment, and the working necessity of fusing the binding rope 2052 is guaranteed.

The unlocking unit 2054 is provided with connecting cylinders on two opposite sides, and after the thermal fuse blows the binding rope 2052, the binding rope 2052 is still kept in the connecting cylinders, and meanwhile, under the action of the limiting block 2051, the broken binding rope 2052 is prevented from drifting up and down, and all parts of the binding rope 2052 exposed to the outside are provided with knots so as to prevent the broken binding rope 2052 from drifting left and right and sliding out. When the longitudinal telescopic mechanism 3 is extended, the support column 302 drives the folding cylinder frame 2021 to move downwards, and the melted binding rope 2052 moves downwards along with the folding cylinder frame 2021.

A damper 206 is provided at the bottom end of the packing cylinder 2021. As shown in fig. 7, fig. 7 is a schematic structural view of the damper. Specifically, the damper 206 includes an organic housing 2062, an inner core 2061, and a viscous liquid 2063; the shell 2062 is fixedly connected to the bottom end of the gathering cylinder frame 2021; the inner core 2061 is disposed in the casing 2062, the inner core 2061 is rotatably connected to the casing 2062, and the inner core 2061 is fixedly connected to the bottom end of the support column 302 to limit the rotational freedom of the support column 302; the viscous liquid 2063 is filled between the housing 2062 and the inner core 2061 for providing a reverse damping force to the rotation of the housing 2062. The viscous liquid 2063 is specifically silicone oil, and may be any viscous liquid in the prior art, and is not limited in this embodiment, if the actual needs are satisfied.

It should be noted that, when the unlocking unit 2054 is unlocked, the thermal fuse melts the binding rope 2052, the pod rod 201 is ejected from the gap between the cylinder 203 and the folding cylinder 2021 under the action of elastic potential energy, the folding cylinder 2021 is driven by the pod rod 201 to rotate to a certain extent, the housing 2062 also rotates slightly, and due to the existence of the viscous liquid 2063, the viscous liquid 2063 generates a damping force opposite to the rotation direction of the housing 2062, and the damper 206 controls the unfolding speed of the pod rod 201 and the film antenna structure 4 according to the internal and external damping moment.

As shown in fig. 3, fig. 3 is a partial schematic view of a thin film antenna structure. Specifically, the film antenna structure 4 includes four film substrates 401 and a plurality of antenna elements 402, two points at the top end of the film substrate 401 are connected with the pod rod 201 end to end, and the bottom end is connected with the communication electronic device 5; the plurality of antenna elements 402 are arranged on the film substrate 401 at intervals along the length direction of the film substrate 401, and after the film substrate 401 is bent and folded, the film substrate 401 is matched with the antenna elements 402 to form a strip structure.

Specifically, the working principle of the thin-film spacecraft provided by the embodiment is as follows:

when the film antenna structure 4 is in the folding process, the longitudinal stretching arm 301 and the communication electronic device 5 are folded into the star 1, and drive the film antenna structure 4 to fold upwards, and after the film antenna structure 4 is folded along the length direction, the strip structure formed by shrinkage of the film antenna structure 4 is positioned at the upper part of the pod rod 201; afterwards, the pod rod 201 drives the film antenna structure 4 to be curled and coiled in the gap between the cylinder 203 and the folding cylinder frame 2021, so that the space occupied by the folded film antenna structure 4 on the star 1 is reduced.

When the film antenna structure 4 is in the stretching process, the thermal fuse fuses the binding rope 2052, the pod rods 201 pop up from the gap between the cylinder 203 and the folding cylinder 2021 under the action of elastic potential energy, the pod rods 201 drive the folding cylinder 2021 to rotate in a small amplitude, and the damper 206 generates a damping moment opposite to the rotating direction of the folding cylinder 2021 so as to control the stretching speed of the pod rods 201 and the film antenna structure 4, and further enable the four pod rods 201 to be stretched synchronously along the gaps of the folding cylinder 2021 in four directions; the air source 3015 sends compressed air to the air pipe 3014, so that the third sleeve 3013 and the second sleeve 3012 move and stretch in sequence, and drive the air pipe 3014 to stretch, so that the longitudinal stretching arm 301 stretches, stretches out of the cylinder 203, and drives the film antenna structure 4 to stretch along the longitudinal direction.

Specifically, the thin-film spacecraft provided in this embodiment has the beneficial effects that at least:

(1) One end of the longitudinal extension arm 301 is connected with the top end of the star 1, and drives the communication electronic equipment 5, the support column 302 and the folding structure 202 to be unfolded and folded longitudinally, so that the integrated connection of the longitudinal extension arm 301 and the star 1 is realized, the pod rod 201 drives the film antenna structure 4 to be folded into a gap between the cylinder 203 and the folding cylinder frame 2021, the folding rate is higher, and the space occupied by the folded film antenna structure 4 on the star 1 is greatly reduced;

(2) The folding structure 202 limits the folded pod rod 201 and the film antenna structure 4, so that the activity amplitude is reduced, and the stability of the pod rod 201 and the film antenna structure 4 in a compressed state along with the emission of a spacecraft is enhanced;

(3) The packing structure 202 adopts a light structural design, so that the weight is light, the materials are saved, and the emission cost of the spacecraft is reduced;

(4) The pod rod 201 and the film antenna structure 4 can be reliably folded by the arrangement of the pressing and unlocking structure 205; after unlocking, the pod rod 201 and the film antenna structure 4 can be reliably unfolded, and the reliability is high.

The application provides a thin-film spacecraft, which comprises communication electronic equipment 5, a star 1, a cylinder 203, a longitudinal telescopic mechanism 3, at least one thin-film antenna structure 4 and a wrapping structure 202, wherein an opening is formed in one side of the star 1; the cylinder 203 is positioned at the opening and connected with the star 1, and the central hole of the cylinder 203 is communicated with the opening; one end of the longitudinal telescopic mechanism 3 is connected in the star 1, and the other end is connected with the communication electronic equipment 5 so as to drive the communication electronic equipment 5 to shrink into the star 1 or stretch out of the cylinder 203; the film antenna structure 4 is respectively connected with the communication electronic device 5, the longitudinal telescopic mechanism 3 and the cylinder 203 so as to be telescopic along with the longitudinal telescopic mechanism 3; the wrapping structure 202 is disposed on the longitudinal telescopic mechanism 3 and is located at a side of the communication electronic device 5 away from the star 1, when the communication electronic device 5 is located in the star 1, the wrapping structure 202 may be sleeved outside the cylinder 203, and the film antenna structure 4 may be limited between the wrapping structure 202 and the cylinder 203. According to the application, the star 1 is integrally connected with the longitudinal telescopic mechanism 3 by arranging the longitudinal telescopic mechanism 3 in the star 1, a part of the longitudinal telescopic mechanism 3 is contracted into the star 1, the film antenna structure 4 is driven to fold and fold along the length direction, and the film antenna structure 4 is coiled and folded between the folding structure 202 and the cylinder 203, so that the space occupied by the folded film antenna structure 4 on the star 1 is reduced.

Other embodiments of the application will be apparent to those skilled in the art from consideration of the specification and practice of the disclosed embodiments. This application is intended to cover any variations, uses, or adaptations of the application following, in general, the principles of the application and including such departures from the present disclosure as come within known or customary practice within the art to which the application pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the application being indicated by the following claims.

Claims

1. A thin film spacecraft comprising communication electronics, characterized in that it further comprises:

a star, wherein one side of the star is provided with an opening;

2. The thin film spacecraft of claim 1, wherein said longitudinal telescoping mechanism comprises:

3. The thin film spacecraft of claim 2, wherein said longitudinally extending arms comprise:

the air source is fixedly connected in the star body;

the top end of the first sleeve is fixedly connected with the air source;

one end of the second sleeve is connected in the first sleeve in a sliding way;

4. The thin film spacecraft of claim 2, further comprising:

5. The thin film spacecraft of claim 4, wherein said containment structure comprises:

6. The thin film spacecraft of claim 5, wherein said compression unlocking structure comprises:

the metal sleeves are arranged on the mounting seat;

7. The thin-film spacecraft of claim 6, wherein a thermal fuse for fusing the strapping lines is disposed in the unlocking unit, and connecting cylinders are disposed at opposite sides of the unlocking unit, and the strapping lines are still maintained in the connecting cylinders after the thermal fuse fuses the strapping lines, so as to prevent the strapping lines from drifting up and down after fusing.

8. The thin film spacecraft of claim 5, wherein said containment structure further comprises:

9. The thin film spacecraft of claim 8, wherein said damper comprises:

the shell is fixedly connected to the bottom end of the folding cylinder frame;

10. The thin film spacecraft of claim 4, wherein said thin film antenna structure comprises: