A thin film spacecraft

Abstract

The application discloses a thin film spacecraft, which comprises communication electronic equipment, a star body, a cylinder, a longitudinal telescopic mechanism, at least one thin film antenna structure and a folding structure. The star body is provided with an opening on one side. The cylinder is located at the opening and connected with the star body. 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 is connected with the communication electronic equipment to drive the communication electronic equipment to contract into the star body or extend out of the cylinder. The thin film antenna structure is connected with the communication electronic equipment, the longitudinal telescopic mechanism and the cylinder respectively to be telescoped with the longitudinal telescopic mechanism. The folding structure is arranged on the longitudinal telescopic mechanism and located on the side of the communication electronic equipment away from the star body. The longitudinal telescopic mechanism is contracted into the star body, the thin film antenna structure is folded along the length direction, and is coiled between the folding structure and the cylinder to reduce the space occupied by the folded thin film antenna structure on the star body.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, and more specifically to a thin-film spacecraft. Background Technology

[0002] Spacecraft, also known as space vehicles or space shuttles, operate in space according to the laws of celestial mechanics.

[0003] However, existing spacecraft consist of a separate star and a deployment mechanism. The deployment mechanism is equipped with a thin-film antenna structure, and the surface of the star is connected to the deployment mechanism. Since the star does not have a storage function, the thin-film antenna structure in the folded state occupies a large placement space when launched with the satellite, which is not conducive to satellite carrying.

[0004] Therefore, existing technologies still need to be improved and enhanced. Summary of the Invention

[0005] In view of the shortcomings of the prior art, the purpose of the present invention is to provide a thin-film spacecraft that aims to solve the technical problem that the thin-film antenna structure occupies too much placement space when launched with a satellite.

[0006] The technical solution adopted by this invention to solve the technical problem is as follows:

[0007] A thin-film spacecraft includes communication electronic equipment and further includes:

[0008] A celestial body, wherein an opening is provided on one side;

[0009] A cylindrical body is located at the opening and connected to the celestial body, with the central hole of the cylindrical body communicating with the opening;

[0010] A longitudinal telescopic mechanism, one end of which is connected to the body of the satellite and the other end of which is connected to the communication electronic device, so as to drive the communication electronic device to retract into the body of the satellite or extend out of the cylinder;

[0011] At least one thin-film antenna structure is connected to the communication electronic device, the longitudinal telescopic mechanism, and the cylindrical body respectively, so as to extend and retract with the longitudinal telescopic mechanism;

[0012] An enclosing structure is provided on the longitudinal telescopic mechanism and located on the side of the communication electronic device away from the satellite. When the communication electronic device is located inside the satellite, the enclosing structure can be sleeved on the outside of the cylinder and confine the thin-film antenna structure between itself and the cylinder.

[0013] As a further improved technical solution, the longitudinal telescopic mechanism includes:

[0014] A longitudinal extension arm, one end of which is fixedly connected to the body of the satellite, and the other end of which is fixedly connected to the top of the communication electronic device;

[0015] A support column, one end of which is fixedly connected to the bottom of the communication electronic device, and the other end of which is connected to the enclosure structure.

[0016] As a further improved technical solution, the longitudinal extension arm includes:

[0017] The gas source is fixedly connected to the body of the star;

[0018] The first sleeve, the top end of the first sleeve is fixedly connected to the gas source;

[0019] The second sleeve has one end slidably connected inside the first sleeve;

[0020] The third sleeve has one end slidably connected to the inside of the second sleeve, and the other end fixedly connected to the communication electronic device;

[0021] The gas supply pipe has one end connected to the gas source and the other end passing through the first sleeve, the second sleeve, and the third sleeve before being connected to the communication electronic device. The gas source supplies compressed gas to the gas supply pipe, causing the third sleeve and the second sleeve to extend in sequence, which in turn causes the gas supply pipe to extend.

[0022] As a further improvement, the thin-film spacecraft also includes:

[0023] At least one pod rod is connected to one end of the thin-film antenna structure, and one end of the pod rod is connected to the cylindrical body, while the other end is located between the enclosing structure and the cylindrical body.

[0024] As a further improved technical solution, the enclosing structure includes:

[0025] A retaining frame is located at the end of the support column away from the communication electronic device, and a pressing and unlocking structure is sleeved on the outer side of the retaining frame;

[0026] Several shaft end baffles are arranged in pairs at the top and bottom of the enclosing cylinder frame.

[0027] Several limiting pivots are connected between corresponding two shaft end baffles.

[0028] As a further improved technical solution, the clamping and unlocking structure includes:

[0029] Several mounting bases are evenly distributed around the outer side of the enclosing tube frame;

[0030] Several metal sleeves are disposed on the mounting base;

[0031] Two limiting blocks are symmetrically arranged on both sides of the cylinder and fixedly connected to the bottom end of the star. The limiting blocks are located between two metal sleeves.

[0032] Two unlocking units are symmetrically arranged on both sides of the cylinder and fixedly connected to the bottom of the star. The unlocking unit is located between two metal sleeves and is arranged separately from the limiting block.

[0033] The binding rope passes through several metal sleeves, two limiting blocks, and two unlocking units before being connected end to end.

[0034] As a further improved technical solution, the unlocking unit is provided with a thermal fuse for melting the binding rope, and the two opposite sides of the unlocking unit are provided with connecting cylinders so that after the thermal fuse melts the binding rope, the binding rope remains in the connecting cylinder, so as to prevent the binding rope from swinging up and down after melting.

[0035] As a further improved technical solution, the enclosing structure also includes:

[0036] A damper is located at the bottom end of the enclosing tube frame and connected to the end of the support column away from the communication electronic device.

[0037] As a further improved technical solution, the damper includes:

[0038] The housing is fixedly connected to the bottom end of the enclosing cylinder frame;

[0039] An inner core is disposed inside the housing, the inner core is rotatably connected to the housing, and the inner core is fixedly connected to the end of the support column away from the communication electronic device;

[0040] A viscous fluid is disposed between the housing and the inner core to provide a reverse damping force on the rotation of the housing.

[0041] As a further improved technical solution, the thin-film antenna structure includes:

[0042] A thin film substrate, one end of which is connected to the pod stalk and the other end of which is connected to the bottom of the communication electronic device;

[0043] Several antenna elements are arranged at intervals on the thin film substrate along the length direction of the thin film substrate.

[0044] Compared with the prior art, the beneficial effects of the present invention are:

[0045] This application provides a thin-film spacecraft, which integrates the spacecraft with a longitudinal telescopic mechanism by setting a longitudinal telescopic mechanism inside the spacecraft. A part of the longitudinal telescopic mechanism is retracted into the spacecraft, causing the thin-film antenna structure to fold and retract along the length direction. The thin-film antenna structure is then coiled and retracted between the enclosing structure and the cylindrical body, thereby reducing the space occupied by the retracted thin-film antenna structure on the spacecraft. Attached Figure Description

[0046] Figure 1 A schematic diagram of the structure of a thin-film spacecraft in its deployed state;

[0047] Figure 2 for Figure 1 The main view;

[0048] Figure 3 This is a partial schematic diagram of a thin-film antenna structure;

[0049] Figure 4 A partial cross-sectional view of the thin-film spacecraft in its folded-up state;

[0050] Figure 5 This is a schematic diagram of the lateral unfolding mechanism in its unfolded state.

[0051] Figure 6 A schematic diagram showing the connection between the enclosing structure and the clamping / unlocking structure;

[0052] Figure 7 This is a schematic diagram of the damper's structure;

[0053] Figure 8 This is a schematic diagram of the longitudinal limiting frame.

[0054] The numbers in the diagram represent: 1. Star body; 2. Lateral unfolding mechanism; 201. Pod stem; 202. Enclosing structure; 2021. Enclosing cylinder frame; 2022. Limiting pivot; 2023. Shaft end baffle; 203. Cylinder body; 204. Positioning structure; 2041. Longitudinal limiting frame; 2042. Positioning frame; 205. Pressing and unlocking structure; 2051. Limiting block; 2052. Binding rope; 2053. Metal sleeve; 2054. Unlocking slip. 2055, Mounting base; 206, Damper; 2061, Inner core; 2062, Housing; 2063, Viscous fluid; 3, Longitudinal telescopic mechanism; 301, Longitudinal extension arm; 3011, First sleeve; 3012, Second sleeve; 3013, Third sleeve; 3014, Gas pipe; 3015, Gas source; 302, Support column; 4, Thin film antenna structure; 401, Thin film substrate; 402, Antenna vibrator; 5, Communication electronic equipment. Detailed Implementation

[0055] To make the objectives, technical solutions, and effects of this invention clearer and more explicit, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0056] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0057] It should also be noted that the same or similar reference numerals in the accompanying drawings of the embodiments of the present invention correspond to the same or similar components; in the description of the present invention, it should be understood that if terms such as "upper," "lower," "left," "right," etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, they are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the terms used to describe positional relationships in the accompanying drawings are only for illustrative purposes and should not be construed as limiting the present patent. For those skilled in the art, the specific meaning of the above terms can be understood according to the specific circumstances.

[0058] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0059] Example 1

[0060] like Figure 1 and Figure 2 As shown, where, Figure 1 A schematic diagram of the structure of a thin-film spacecraft in its deployed state; Figure 2 for Figure 1The front view. Specifically, this embodiment provides a thin-film spacecraft, including a communication electronic device 5, a satellite 1, a cylindrical body 203, a longitudinal telescopic mechanism 3, at least one thin-film antenna structure 4, and an enclosure structure 202. The satellite 1 has an opening on its bottom side, and the cylindrical body 203 is located at the bottom of the opening and fixedly connected to the bottom of the satellite 1. The central hole of the cylindrical body 203 communicates with the opening. The longitudinal telescopic mechanism 3 is disposed inside the satellite 1, with one end fixedly connected to the top of the satellite 1 and the other end fixedly connected to the communication electronic device 5, so as to drive the communication electronic device 5 to retract into the satellite 1 or extend out of the cylindrical body 203.

[0061] like Figure 4 As shown, Figure 4 This is a partial cross-sectional view of the thin-film spacecraft in its retracted state. Specifically, the longitudinal telescopic mechanism 3 includes a longitudinal extension arm 301 and a support column 302. The top end of the longitudinal extension arm 301 is fixedly connected to the top end of the satellite 1, and the bottom end is fixedly connected to the top end of the communication electronic device 5; the top end of the support column 302 is fixedly connected to the bottom end of the communication electronic device 5. When the longitudinal extension arm 301 is extended, the communication electronic device 5 moves downward and passes through the opening and the cylinder 203 in sequence, causing the thin-film antenna structure 4 to unfold.

[0062] The longitudinal extension arm 301 includes an air source 3015, a first sleeve 3011, a second sleeve 3012, a third sleeve 3013, and an air supply pipe 3014. The air source 3015 is fixedly connected to the top end of the satellite 1. Specifically, the air source 3015 is a cylinder; however, it can also be other driving devices as used in the prior art. The top end of the first sleeve 3011 is fixedly connected to the air source 3015. One end of the second sleeve 3012 is slidably connected inside the first sleeve 3011. One end of the third sleeve 3013 is slidably connected inside the second sleeve 3012, and the other end is fixedly connected to the communication electronic device 5. The communication electronic device 5 can be a computer, a radar, or any communication device in the prior art, provided that the actual needs are met. One end of the gas supply pipe 3014 is connected to the gas source 3015, and the other end passes through the first sleeve 3011, the second sleeve 3012, and the third sleeve 3013 before being connected to the communication electronic device 5. The gas source 3015 supplies compressed gas to the gas supply pipe 3014, causing the third sleeve 3013 and the second sleeve 3012 to extend sequentially, which in turn causes the gas supply pipe 3014 to extend, thereby causing the communication electronic device 5 to descend and extend outside the cylinder 203.

[0063] The first sleeve 3011 has a first limiting part at the bottom of its inner wall and the second sleeve 3012 has a second limiting part at the top of its outer wall. The second limiting part abuts against the first limiting part to prevent the second sleeve 3012 from coming off the first sleeve 3011.

[0064] The second sleeve 3012 has a third limiting part at the bottom of its inner wall and the third sleeve 3013 has a fourth limiting part at the top of its outer wall. The fourth limiting part abuts against the third limiting part to prevent the third sleeve 3013 from coming off the second sleeve 3012.

[0065] It should be noted that 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, depending on actual needs, the third sleeve 3013 can be removed, or a fourth sleeve can be added to the third sleeve 3013, with the outer diameter of the fourth sleeve being smaller than the inner diameter of the third sleeve 3013, and so on.

[0066] like Figure 5 As shown, Figure 5 This is a schematic diagram of the lateral unfolding mechanism in its unfolded state. Specifically, the enclosing structure 202, the cylinder 203, and the four pod-shaped rods 201 constitute the... Figure 5 The lateral unfolding mechanism 2 shown has a central hole in the middle of the cylinder 203. The support column 302 passes through the cylinder 203 and is connected to the enclosing structure 202. The communication electronic device 5 can pass through the opening and the cylinder 203 as the support column 302 moves. The top of the cylinder 203 is fixedly connected to the bottom of the star 1. One end of the pod stalk 201 is connected to the cylinder 203, and the other end is located between the enclosing structure 202 and the cylinder 203. It can be ejected from the gap between the enclosing structure 202 and the cylinder 203 under the action of elastic potential energy.

[0067] Specifically, the pod stem 201 can store elastic potential energy. In the unfolded state, the pod stem 201 is straight and has a pod-shaped cross-section. It should be noted that the pod shape can be simply understood as a double "Ω" shaped closed cross-section. This shape has good load-bearing stiffness. If the cross-section is flattened, the bending stiffness will be greatly reduced, allowing the pod stem 201 to easily curl and coil between the wrapping structure 202 and the cylinder 203 to achieve the folding of the pod stem 201. When the pod stem 201 pops out from the gap between the wrapping structure 202 and the cylinder 203, the flattened cross-section will gradually and automatically spring back to the original pod shape, and the pod stem 201 will straighten and unfold.

[0068] The function of the enclosing structure 202 is to enclose and retract the pod rod 201 and the thin film antenna structure 4 after they are enclosed. It can also restrict the pod rod 201 from unfolding synchronously along the gaps in the four directions of the enclosing structure 202 during the unfolding process of the thin film antenna structure 4.

[0069] Specifically, the enclosing structure 202 includes an enclosing frame 2021, several shaft end baffles 2023, and several limiting pivots 2022. The enclosing frame 2021 is located at the bottom of the star 1 and is connected to the end of the support column 302 away from the communication electronic device 5. Each pair of shaft end baffles 2023 is correspondingly arranged at the top and bottom of the enclosing frame 2021. The limiting pivots 2022 are located between the corresponding two shaft end baffles 2023 and are connected to the shaft end baffles 2023. They are evenly distributed around the outside of the enclosing frame 2021 to limit the pop-out of the pod rod 201.

[0070] As a further preferred embodiment, the number of shaft end baffles 2023 is eight, and the number of limiting rotating shafts 2022 is four, with the four limiting rotating shafts 2022 evenly distributed around the outer side of the wrapping cylinder frame 2021.

[0071] The enclosing cylindrical frame 2021 is provided with a positioning structure 204, which includes a positioning frame 2042 and a longitudinal limiting frame 2041. The bottom end of the positioning frame 2042 is detachably connected to the enclosing cylindrical frame 2021, for example, by bolts; or a boss is provided at the bottom end of the enclosing cylindrical frame 2021, and the positioning frame 2042 engages with the boss. Regardless of the connection method used, this embodiment is not limited. The longitudinal limiting frame 2041 is disposed on the positioning frame 2042, and the cylindrical body 203 is sleeved on the outside of the longitudinal limiting frame 2041 and fixed by bolts to improve the stability of the connection between the cylindrical body 203 and the longitudinal limiting frame 2041.

[0072] It should be noted that the positioning frame 2042 assists in the retraction of the pod rod 201 and the thin-film antenna structure 4, allowing them to smoothly wrap around the surface of the cylindrical body 203. The positioning frame 2042 is connected to the end of the support column 302 furthest from the communication electronic device 5.

[0073] like Figure 8 As shown, Figure 8 This is a schematic diagram of the longitudinal limiting frame. Specifically, the longitudinal limiting frame 2041 is composed of four structural frames, and the four structural frames have identical structures.

[0074] The longitudinal limiting frame 2041 serves to reserve space for the extension and retraction of the longitudinal telescopic mechanism 3. The cylinder 203 is for winding the pod stem 201. The gap in the middle allows the longitudinal extension arm 301 to pass smoothly and prevents it from being misaligned in the central space, which would prevent it from extending properly. This also saves material and reduces weight. When the longitudinal extension arm 301 extends, the wrapping cylinder frame 2021 causes the positioning frame 2042 to disengage from the cylinder 203.

[0075] like Figure 6 As shown, Figure 6 This is a schematic diagram of the connection between the enclosing structure and the clamping / unlocking structure. Specifically, a clamping / unlocking structure 205 is arranged around the outer side of the enclosing cylindrical frame 2021 to apply an inward clamping force to the enclosing cylindrical frame 2021. The clamping / unlocking structure 205 is fixedly connected to the bottom end of the star body 1. After the clamping / unlocking structure 205 is unlocked, the enclosing cylindrical frame 2021 is released.

[0076] Specifically, the clamping and unlocking structure 205 includes several mounting seats 2055, several metal sleeves 2053, two limiting blocks 2051, two unlocking units 2054, and binding ropes 2052. The mounting seats 2055 are evenly distributed around the outer side of the wrapping tube frame 2021. The wrapping tube frame 2021 has a gap between every two mounting seats 2055 for the pod stem 201 to pop out. The metal sleeves 2053 are embedded in the mounting seats 2055 to prevent the metal sleeves 2053 from shifting. The surface of the 2053 is provided with a slot, which is arranged along the length of the metal sleeve 2053; two limiting blocks 2051 are symmetrically arranged on both sides of the cylinder 203 and fixedly connected to the bottom end of the star 1, and the limiting blocks 2051 are located between the two metal sleeves 2053; two unlocking units 2054 are symmetrically arranged on both sides of the cylinder 203 and fixedly connected to the bottom end of the star 1, and the unlocking units 2054 are located between the two metal sleeves 2053 and are arranged separately from the limiting blocks 2051. In short, the line connecting the two limiting blocks 2051 and the line connecting the two unlocking units 2054 are arranged in a cross shape; the binding rope 2052 passes through several metal sleeves 2053, the two limiting blocks 2051 and the two unlocking units 2054 and is connected end to end. One side of the binding rope 2052 is in contact with the bottom wall of the slot, so that the binding rope 2052 is tensioned on the outside of the wrapping tube frame 2021.

[0077] The unlocking unit 2054 is equipped with a thermal fuse for melting the binding rope 2052. When the unlocking unit 2054 is unlocked, the thermal fuse heats up and melts the binding rope 2052, thereby releasing the clamping force. This embodiment is designed with two heating and cutting points to ensure the necessity of melting the binding rope 2052.

[0078] The unlocking unit 2054 has connecting cylinders on opposite sides. After the thermal fuse melts the binding rope 2052, the binding rope 2052 remains within the connecting cylinder. Simultaneously, the limiting block 2051 prevents the melted binding rope 2052 from moving up and down. All exposed parts of the binding rope 2052 are equipped with knots to prevent it from shifting left and right and slipping out after melting. When the longitudinal telescopic mechanism 3 extends, the support column 302 drives the wrapping cylinder frame 2021 downwards, and the melted binding rope 2052 moves downwards along with the wrapping cylinder frame 2021.

[0079] A damper 206 is provided at the bottom end of the enclosing tube frame 2021. For example... Figure 7 As shown, Figure 7 This is a schematic diagram of the damper's structure. Specifically, the damper 206 includes a housing 2062, an inner core 2061, and a viscous fluid 2063. The housing 2062 is fixedly connected to the bottom end of the enclosing cylinder frame 2021. The inner core 2061 is disposed within the housing 2062 and is rotatably connected to the housing 2062. The inner core 2061 is also fixedly connected to the bottom end of the support column 302 to restrict the rotational freedom of the support column 302. The viscous fluid 2063 fills the space between the housing 2062 and the inner core 2061, providing a reverse damping force against the rotation of the housing 2062. Specifically, the viscous fluid 2063 is silicone oil; however, depending on the specific requirements, it can be any viscous fluid from the prior art, and is not limited in this embodiment.

[0080] It should be noted that when the unlocking unit 2054 is unlocked, the thermal fuse melts the binding rope 2052, and the pod rod 201 pops out from the gap between the cylinder 203 and the wrapping frame 2021 under the action of elastic potential energy. Driven by the pod rod 201, the wrapping frame 2021 rotates to a certain extent, and the housing 2062 also rotates slightly. Due to the presence of the viscous liquid 2063, the viscous liquid 2063 generates a damping force opposite to the rotation direction of the housing 2062. The damper 206 controls the unfolding speed of the pod rod 201 and the thin film antenna structure 4 according to the internal and external damping torques.

[0081] like Figure 3 As shown, Figure 3 This is a partial schematic diagram of the thin-film antenna structure. Specifically, the thin-film antenna structure 4 includes four thin-film substrates 401 and several antenna elements 402. The top two points of the thin-film substrates 401 are connected to the two ends of the pod stem 201, and the bottom end is connected to the communication electronic device 5. The several antenna elements 402 are arranged at intervals along the length of the thin-film substrates 401. After the thin-film substrates 401 are bent and folded, they cooperate with the antenna elements 402 to form a strip structure.

[0082] Specifically, the working principle of the thin-film spacecraft provided in this embodiment is as follows:

[0083] When the thin-film antenna structure 4 is in the process of retracting, the longitudinal extension arm 301 and the communication electronic device 5 retract into the satellite body 1, and drive the thin-film antenna structure 4 to fold upward. After the thin-film antenna structure 4 is folded and retracted along the length direction, the strip structure formed by the shrinkage of the thin-film antenna structure 4 is located on the upper part of the pod rod 201. Then, the pod rod 201 drives the thin-film antenna structure 4 to curl and coil in the gap between the cylinder 203 and the wrapping cylinder frame 2021, reducing the space occupied by the retracted thin-film antenna structure 4 on the satellite body 1.

[0084] When the thin-film antenna structure 4 is in the process of extension, the thermal fuse melts the binding rope 2052. Under the action of elastic potential energy, the pod rod 201 pops out from the gap between the cylinder 203 and the wrapping frame 2021. The pod rod 201 drives the wrapping frame 2021 to rotate slightly. The damper 206 generates a damping torque opposite to the rotation direction of the wrapping frame 2021 to control the extension speed of the pod rod 201 and the thin-film antenna structure 4, thereby enabling the four pod rods 201 to extend synchronously along the gaps in the four directions of the wrapping frame 2021. The gas source 3015 delivers compressed gas to the gas supply pipe 3014, causing the third sleeve 3013 and the second sleeve 3012 to move and extend in sequence, and driving the gas supply pipe 3014 to extend, thereby extending the longitudinal extension arm 301 out of the cylinder 203, and driving the thin-film antenna structure 4 to extend longitudinally.

[0085] Specifically, the beneficial effects of the thin-film spacecraft provided in this embodiment include at least the following:

[0086] (1) One end of the longitudinal extension arm 301 is connected to the top of the star 1, and drives the communication electronic equipment 5, the support column 302 and the enclosure structure 202 to unfold and retract along the longitudinal direction, realizing the integrated connection between the longitudinal extension arm 301 and the star 1. The pod rod 201 drives the thin film antenna structure 4 to retract into the gap between the cylinder 203 and the enclosure frame 2021. The retraction rate is high, which greatly reduces the space occupied by the retracted thin film antenna structure 4 on the star 1.

[0087] (2) The enclosing structure 202 limits the folded pod rod 201 and the thin film antenna structure 4, reducing the range of motion and enhancing the stability of the pod rod 201 and the thin film antenna structure 4 when launched with the spacecraft under the compressed state.

[0088] (3) The enclosure structure 202 adopts a lightweight structural design, which is lightweight and saves materials, reducing the launch cost of the spacecraft;

[0089] (4) The setting of the pressing and unlocking structure 205 enables the pod rod 201 and the thin film antenna structure 4 to be reliably retracted; after unlocking, the pod rod 201 and the thin film antenna structure 4 can be reliably deployed, which has high reliability.

[0090] This application provides a thin-film spacecraft, including a communication electronic device 5, a satellite 1, a cylindrical body 203, a longitudinal telescopic mechanism 3, at least one thin-film antenna structure 4, and an enclosure structure 202. The satellite 1 has an opening on one side; the cylindrical body 203 is located at the opening and connected to the satellite 1, with a central hole in the cylindrical body 203 communicating with the opening; one end of the longitudinal telescopic mechanism 3 is connected to the inside of the satellite 1, and the other end is connected to the communication electronic device 5, so as to drive the communication electronic device 5 to retract into the satellite 1 or extend into the satellite 1. The thin-film antenna structure 4 is connected to the communication electronic device 5, the longitudinal telescopic mechanism 3, and the cylinder 203 respectively, so as to extend and retract with the longitudinal telescopic mechanism 3. The enclosing structure 202 is disposed on the longitudinal telescopic mechanism 3 and is located on the side of the communication electronic device 5 away from the satellite 1. When the communication electronic device 5 is located inside the satellite 1, the enclosing structure 202 can be sleeved on the outside of the cylinder 203, and the thin-film antenna structure 4 is confined between the enclosing structure 202 and the cylinder 203. This application provides a longitudinal telescopic mechanism 3 inside the satellite 1, so that the satellite 1 and the longitudinal telescopic mechanism 3 are integrated. A part of the longitudinal telescopic mechanism 3 is retracted into the satellite 1, which drives the thin-film antenna structure 4 to fold and retract along the length direction, and then coils and retracts the thin-film antenna structure 4 between the enclosing structure 202 and the cylinder 203, so as to reduce the space occupied by the retracted thin-film antenna structure 4 on the satellite 1.

[0091] Other embodiments of the invention will readily occur to those skilled in the art upon consideration of the specification and practice of the solutions disclosed herein. This invention is intended to cover any variations, uses, or adaptations of the invention that follow the general principles of the invention and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of the invention are indicated by the claims.

Claims

1. A thin-film spacecraft, comprising communication electronic equipment, characterized in that, Also includes: A celestial body, wherein an opening is provided on one side; A cylindrical body is located at the opening and connected to the celestial body, with the central hole of the cylindrical body communicating with the opening; A longitudinal telescopic mechanism, one end of which is connected to the body of the satellite and the other end of which is connected to the communication electronic device, so as to drive the communication electronic device to retract into the body of the satellite or extend out of the cylinder; At least one thin-film antenna structure is connected to the communication electronic device, the longitudinal telescopic mechanism, and the cylindrical body respectively, so as to extend and retract with the longitudinal telescopic mechanism; An enclosing structure is provided on the longitudinal telescopic mechanism and located on the side of the communication electronic device away from the satellite. When the communication electronic device is located inside the satellite, the enclosing structure can be sleeved on the outside of the cylinder and the thin film antenna structure is confined between the enclosing structure and the cylinder. The longitudinal telescopic mechanism includes: A longitudinal extension arm, one end of which is fixedly connected to the body of the satellite, and the other end of which is fixedly connected to the top of the communication electronic device; A support column, one end of which is fixedly connected to the bottom end of the communication electronic device, and the other end of which is connected to the enclosure structure; The longitudinal extension arm includes: The gas source is fixedly connected to the body of the star; The first sleeve, the top end of the first sleeve is fixedly connected to the gas source; The second sleeve has one end slidably connected inside the first sleeve; The third sleeve has one end slidably connected to the inside of the second sleeve, and the other end fixedly connected to the communication electronic device; The gas supply pipe has one end connected to the gas source and the other end passing through the first sleeve, the second sleeve, and the third sleeve before being connected to the communication electronic device. The gas source supplies compressed gas to the gas supply pipe, causing the third sleeve and the second sleeve to extend in sequence, which in turn causes the gas supply pipe to extend.

2. The thin-film spacecraft according to claim 1, characterized in that, The thin-film spacecraft also includes: At least one pod rod is connected to one end of the thin-film antenna structure, and one end of the pod rod is connected to the cylindrical body, while the other end is located between the enclosing structure and the cylindrical body.

3. The thin-film spacecraft according to claim 2, characterized in that, The enclosing structure includes: A retaining frame is located at the end of the support column away from the communication electronic device, and a pressing and unlocking structure is sleeved on the outer side of the retaining frame; Several shaft end baffles are arranged in pairs at the top and bottom of the enclosing cylinder frame. Several limiting pivots are connected between corresponding two shaft end baffles.

4. The thin-film spacecraft according to claim 3, characterized in that, The clamping and unlocking structure includes: Several mounting bases are evenly distributed around the outer side of the enclosing tube frame; Several metal sleeves are disposed on the mounting base; Two limiting blocks are symmetrically arranged on both sides of the cylinder and fixedly connected to the bottom end of the star. The limiting blocks are located between two metal sleeves. Two unlocking units are symmetrically arranged on both sides of the cylinder and fixedly connected to the bottom of the star. The unlocking unit is located between two metal sleeves and is arranged separately from the limiting block. The binding rope passes through several metal sleeves, two limiting blocks, and two unlocking units before being connected end to end.

5. The thin-film spacecraft according to claim 4, characterized in that, The unlocking unit is equipped with a thermal fuse for melting the binding rope. The unlocking unit has connecting cylinders on opposite sides, so that after the thermal fuse melts the binding rope, the binding rope remains in the connecting cylinder to prevent the bound rope from swinging up and down after melting.

6. The thin-film spacecraft according to claim 3, characterized in that, The enclosing structure also includes: A damper is located at the bottom end of the enclosing tube frame and connected to the end of the support column away from the communication electronic device.

7. The thin-film spacecraft according to claim 6, characterized in that, The damper includes: The housing is fixedly connected to the bottom end of the enclosing cylinder frame; An inner core is disposed inside the housing, the inner core is rotatably connected to the housing, and the inner core is fixedly connected to the end of the support column away from the communication electronic device; A viscous fluid is disposed between the housing and the inner core to provide a reverse damping force on the rotation of the inner core.

8. The thin-film spacecraft according to claim 2, characterized in that, The thin-film antenna structure includes: A thin film substrate, one end of which is connected to the pod stalk and the other end of which is connected to the bottom of the communication electronic device; Several antenna elements are arranged at intervals on the thin film substrate along the length direction of the thin film substrate.

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