A satellite-rocket separation device with adjustable size

Abstract

A satellite-rocket separation device with adjustable size includes: a base; an arm extending outward horizontally from the outer peripheral surface of the base, with a slide rail arranged along the arm; a plurality of movable platforms arranged horizontally and evenly around the arm, with a slider adapted to the slide rail, and a sliding connection with the arm is achieved through the adaptation of the slider of the slide rail; a support seat fixed to the upper surface of the movable platform by explosive bolts, and used for connecting the satellite. With the above structure, the distance between the movable platform and the base can be adjusted by sliding the slider and the slide rail, thereby adjusting the size of the satellite-rocket separation device to adapt to satellites of different sizes and improve the versatility of the satellite-rocket separation device.

Description

Technical Field

[0001] The present invention relates to the field of satellite launching technology, and in particular to a satellite-rocket separation device with adjustable size. Background Art

[0002] According to a report released by the U.S. Space Foundation, the global aerospace economy is about $330 billion, of which the commercial aerospace industry accounts for as much as 76%. Since 2015, when China opened up its policies to private capital in aerospace fields such as satellite manufacturing and satellite applications, domestic commercial aerospace companies have sprung up like mushrooms after rain. The aerospace industry, originally dominated by the government, is gradually moving towards the era of mass consumption and eventually towards ordinary people's homes. However, the development of my country's commercial aerospace field is still in its early stages. At present, Chinese private start-ups targeting the commercial aerospace market will launch small satellites for various purposes as their main task. Compared with the relatively mature commercial satellite companies in the United States, there is still a gap in technology. Due to funding considerations, my country's commercial aerospace private enterprises usually try to shorten the development cycle in satellite development and manufacturing, so there is a lot of room for growth in terms of satellite performance improvement and technological innovation. In the process of satellite development, the use of mature inherited platform design, modular design, and universal design can greatly improve the cost reduction and efficiency improvement effect of satellite development, which is also the direction that commercial satellite companies need to pay attention to.

[0003] The satellite-rocket connection and separation device is a mechanism with connection, unlocking and separation functions. During the flight, the separation connection device completes the unlocking and separation actions in a prescribed sequence to separate the satellite from the rocket. For the connection and separation devices of micro-satellites, there are mainly point-type connection and separation, box-shaped fixed constraint ejection separation, and belt separation. Figure 1 This is a structural diagram of the point-type connection and separation device, in which the satellite is mainly connected and fixed to the separated body through explosive bolts, unlocking bolts, and separation nuts. Figure 2 This is a schematic diagram of the satellite-rocket separation process of the box-shaped fixed constraint ejection separation device (also known as POD). POD is generally used for the separation of Pinacube satellites. A cylindrical spring is installed at one end of the POD, and a rotatable end cover with a torsion spring at the root. After the cover is released by the upper release device, it rotates open under the action of the torsion spring, and the satellite slides out along the linear guide under the action of the cylindrical spring of the energy storage element. Figure 3 It is a belt-separation type separation device. Its main function is to form a positive pressure along the axial direction of the satellite through the clamp under the condition of applying a certain pre-tightening force, so as to ensure the reliable connection between the satellite and the carrier rocket. This process is to load the pre-tightening force of the separation belt; when the satellite and the rocket are separated, the shell of the explosive bolt connecting the separation belt breaks, and the pre-tightening force of the separation belt is released. At the same time, under the action of components such as the tension spring, the separation belt is retracted on the carrier docking section, thereby completing the separation of the satellite and the rocket.

[0004] At present, with the development of commercial aerospace, the demand for microsatellites is increasing, and the interfaces between satellites and launch vehicles are quite different. This puts high demands on the development cycle and cost of separation and connection devices. However, traditional connection and separation devices need to be designed according to the different sizes of satellites. Products of different sizes have poor flexibility and are a waste of the design cycle. Therefore, it is of great significance to develop a satellite-rocket separation and unlocking device with adjustable size. By designing a product, it can adapt to the needs of satellites of different sizes, enhance the versatility of the design, and play a very large role in reducing costs and increasing efficiency, especially for commercial aerospace companies. Summary of the invention

[0005] In view of this, the main purpose of the present invention is to provide a satellite-rocket separation device with adjustable size so as to adapt to satellites of different sizes and improve the versatility of the satellite-rocket separation device.

[0006] The satellite-rocket separation device with adjustable size provided by the present invention belongs to a point-type connection and separation device, comprising: a base; a support arm, which is horizontally extended outward from the outer peripheral surface of the base, and a slide rail is arranged along the support arm; a plurality of movable platforms, which are horizontally and evenly distributed around the support arm, and have sliders adapted to the slide rails, and a sliding connection with the support arm is achieved through the adaptation of the slide rail sliders; a support seat, which is fixed to the upper surface of the movable platform by explosive bolts and is used to connect the satellite.

[0007] By adopting the above structure, the distance between the movable platform and the base can be adjusted through the sliding connection between the slider and the slide rail, thereby adjusting the size of the satellite-rocket separation device to adapt to satellites of different sizes, thereby improving the versatility of the satellite-rocket separation device.

[0008] Preferably, each two adjacent movable platforms further include a first connecting arm and a second connecting arm extending horizontally toward each other; a connecting rod is extended from one of the two connecting arms, and a connecting hole is provided at a corresponding position of the connecting rod of the other; wherein the connecting rod moves in the connecting hole to movably connect the two adjacent movable platforms.

[0009] By adopting the above structure, through the movable connection between the connecting rod and the connecting hole, the movable platform can change the distance with the base to change the size of the satellite-rocket separation device, thereby improving the firmness and stability of the satellite-rocket separation device.

[0010] Preferably, each of the movable platforms further comprises a third connecting arm which is arranged horizontally, and the sliding block is arranged on the third connecting arm; the third connecting arm is provided with a rack which extends to the top of the base horizontally along the direction of the sliding rail; the upper surface of the base is provided with first gears which are respectively meshed with the racks, and each first gear is simultaneously meshed with the second gear.

[0011] With the above structure, when the distance between a movable platform and the base is changed, the transmission of the rack and the gear can drive other movable platforms to move the same distance, thereby ensuring that the movable platform and the support seat on it are always located at the vertex of the equilateral polygon, so that the connection between satellites is more secure and the force is more even.

[0012] Preferably, the racks are arranged vertically staggered or in parallel above the base.

[0013] By adopting the above structure, the racks can be prevented from influencing each other when they move above the base, thereby increasing the range of motion of the movable platform, thereby increasing the size change range of the satellite-rocket separation device, and increasing the scope of application of the satellite-rocket separation device.

[0014] Preferably, in the present invention, the second gear is an inner ring gear.

[0015] Preferably, the base is provided with a support ring, the inner ring gear is sleeved in the support ring and is movably connected to the support ring via balls; and each first gear is arranged in the inner ring gear and meshes with the inner ring gear.

[0016] By adopting the above structure, a specific structure of the inner ring gear is provided.

[0017] Preferably, the support arm is provided with an elliptical through-hole-shaped limiting hole along the slide rail; and the third connecting arm is provided with a limiting bolt movable in and along the limiting hole at a position corresponding to the limiting hole.

[0018] By adopting the above structure, the cooperation between the limiting bolt and the limiting hole can prevent the third connecting arm from separating from the support arm, thereby improving the stability of the satellite-rocket separation device when adjusting the size.

[0019] Preferably, the cross section of the support arm is I-shaped, and the slide rail is arranged in the middle position of the upper surface of the support arm; and the number of the limiting holes is two and is arranged on both sides of the slide rail.

[0020] By adopting the above structure, the two limit holes and the limit bolts arranged on both sides of the slide rail can make the satellite-rocket separation device more stable when changing its size.

[0021] Preferably, the slide rail is a trapezoidal through groove extending along the upper surface of the support arm.

[0022] By adopting the above structure, a specific structure of the slide rail is provided.

[0023] Preferably, the slider has a bottom disposed along the third connecting arm; and the limit bolts are located at both sides of the slider end.

[0024] With the above structure, when the limit bolt is located at the end of the limit hole, it ensures that the end of the slider is still located in the slide rail, which can prevent the slider from detaching from the slide rail and improve the stability of the satellite-rocket separation device when the size is changed. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a structural schematic diagram of a point-type connection separation device;

[0026] Figure 2 It is a schematic diagram of the satellite-rocket separation process of the box-shaped fixed restraint ejection separation device;

[0027] Figure 3 It is a schematic diagram of the structure of the tape separation type separation device;

[0028] Figure 4 This is a schematic diagram of the structure of the satellite-rocket separation device of this application;

[0029] Figure 5 for Figure 4 Schematic diagram of the structure after the upper cover is opened;

[0030] Figure 6 for Figure 5 Schematic diagram of the moving mechanism in the away state;

[0031] Figure 7 for Figure 5 A schematic diagram of the structure of the fixing mechanism;

[0032] Figure 8 for Figure 6 Schematic diagram of the structure of the activity mechanism.

[0033] Description of Reference Numerals

[0034] Fixing mechanism 1; base 11; support ring 12; inner ring gear 13; gear 14; support arm 15; slide rail 151; limiting hole 152; upper cover 16; movable mechanism 2; movable platform 21; first connecting arm 22; connecting rod 221; second connecting arm 23; connecting hole 231; third connecting arm 24; slider 241; rack 242; limiting bolt 243; support seat 25; explosive bolt 26. DETAILED DESCRIPTION

[0035] Below, the specific structure of the adjustable-size satellite-rocket separation device of the present application is described in detail with reference to the drawings.

[0036] Figure 4 This is a schematic diagram of the structure of the satellite-rocket separation device of this application; Figure 5 for Figure 4 A schematic diagram of the structure after the upper cover 16 is opened; Figure 6 for Figure 5 Schematic diagram of the moving mechanism 2 being away from the state. Figure 1, Figure 2 , Figure 3 As shown, the satellite-rocket separation device of the present application includes a fixed mechanism 1 located in the middle and four movable mechanisms 2 arranged around the fixed mechanism 1 and movably connected to the fixed mechanism 1. The movable mechanism 2 can be scaled and changed in size through the movable connection with the fixed mechanism 1 to adapt to satellites of different sizes.

[0037] Figure 7 for Figure 5 The structural diagram of the fixing mechanism 1 is shown in FIG. Figure 5 , Figure 6 , Figure 7 As shown, the fixing mechanism 1 comprises: a base 11 which is generally circular and has a certain thickness. A support ring 12 is fixedly arranged on the upper surface of the base 11, and the outer diameter of the support ring 12 is the same as that of the base 11, so that the outer surfaces of the base 11 and the support ring 12 overlap. An inner ring gear 13 is sleeved inside the support ring 12, and the teeth of the inner ring gear 13 are located on the inner surface of the inner ring gear 13 and arranged toward the axis. The size of the inner ring gear 13 is adapted to the support ring 12, and the upper surface of the inner ring gear 13 is flush with the upper surface of the support ring 12. The outer surface of the inner ring gear 13 and the inner surface of the support ring 12 are movably connected by spherical balls (the structure between the inner ring gear 13 and the support ring 12 is the same as that of the ball bearing), so that the inner ring gear 13 can rotate freely in the support ring 12. Four smaller gears 14 are evenly arranged in the inner ring gear 13 at the top of the base 11, and the gears 14 are meshed with the inner ring gear 13. The gear 14 has a large tooth width, so that the gear 14 is higher than the upper surface of the inner ring gear 13. The outer peripheral surface of the base 11 is provided with four outwardly extending arms 15, which are arranged in a cross shape, and there is a 90° angle between two adjacent arms 15. The arm 15 is a component with an I-shaped cross section. A trapezoidal through-groove-shaped slide rail 151 is arranged along the arm 15 in the middle position of the upper surface of the upper horizontal plate of the arm 15, and elliptical limiting holes 152 are arranged along the side walls on both sides of the slide rail 151. A circular shell-shaped upper cover 16 is also provided on the upper part of the support ring 12. The upper cover 16 is adapted to the base 11 and the support ring 12, and is fixedly connected to the outer bottom of the base 11 by bolts, forming a closed internal space with the support ring 12 and the base 11. The outer peripheral surface of the upper cover 16 has an opening for the rack 242 to pass through at a relative position to the rack 242 described below.

[0038] Figure 8 for Figure 6 The schematic diagram of the structure of the movable mechanism 2. Figure 6 , Figure 8As shown, the movable mechanism 2 includes a movable platform 21 which is in the shape of a square block as a whole. The movable platform 21 has a first connecting arm 22, a second connecting arm 23 and a third connecting arm 24 extending horizontally. The cross-sections of the first connecting arm 22, the second connecting arm 23 and the third connecting arm 24 are trapezoidal. The first connecting arm 22 and the second connecting arm 23 have the same length and are arranged at 90°. The third connecting arm 24 is located between the first connecting arm 22 and the second connecting arm 23 and is arranged at a 45° angle to the first connecting arm 22 and the second connecting arm 23. A connecting rod 221 extends horizontally from the middle position of the end of the first connecting arm 22, and a connecting hole 231 is arranged at the middle position of the end of the second connecting arm 23. The third connecting arm 24 is higher than the first connecting arm 22 and the second connecting arm 23, and one end of the third connecting arm 24 is fixedly connected to the upper surface of the movable platform 21 by bolts. A sliding block 241 with a trapezoidal cross-section is arranged along the third connecting arm 24 at the middle position of the lower surface of the third connecting arm 24. The sliding block 241 is adapted to the above-mentioned slide rail 151 and can be movably connected to the slide rail 151. A rack 242 extends horizontally from the upper part of the other end of the third connecting arm 24, and the teeth of the rack 242 face the side of the second connecting arm 23. A downwardly extending limiting bolt 243 is provided at both sides of the slider 241 at the other end of the third connecting arm 24, and the limiting hole 152 is movably connected to the limiting bolt 243. A support seat 25 is provided at the middle position of the upper surface of the movable platform 21, and the support seat 25 is in the shape of an inverted truncated cone, and is fixedly connected to the movable platform 21 through an explosive bolt 26 provided at the axial position.

[0039] After installation, four movable mechanisms 2 are arranged around the fixed mechanism 1 in a square arrangement. The four movable mechanisms 2 are movably connected with the slide rails 151 on the four arms 15 of the fixed mechanism 1 through the slider 241, and the slider 241 is prevented from being separated from the slide rail 151 by the limit bolt 243. Four racks 242 extend from the upper side of the support ring 12 and mesh with a gear 14 on the base 11 respectively, wherein the two opposite racks 242 are located at the same height, and when the two racks 242 are close, the backs of the racks 242 (the side opposite to the teeth) are in contact; two adjacent racks 242 are located at different heights, and when the two racks 242 are close, they can pass each other. When a movable mechanism 2 moves inward or outward along the slide rail 151, the rack 242 drives the gear 14 to rotate, the gear 14 drives the inner ring gear 13 to rotate, and the inner ring gear 13 drives the other three gears 14 to rotate, thereby driving the other three movable mechanisms 2 to move in the same direction, so that the distance between the four support seats 25 can be changed, and at the same time, the four support seats 25 are ensured to be arranged in a square. When in use, the position of the movable mechanism 2 can be adjusted according to the size of the satellite, thereby adjusting the distance between the support seats 25, so that the satellite-rocket separation device can adapt to the size of the satellite and facilitate the connection between the satellite and the rocket.

[0040] Furthermore, the inner ring gear 13 can be replaced by a gear disposed between the four gears 14 and meshed with the four gears 14 respectively. When one of the four gears 14 disposed around rotates, the other three gears 14 can be driven to rotate in the same direction through the transmission of the intermediate gear. Furthermore, when a movable mechanism 2 moves inward or outward along the slide rail 151, the other three movable mechanisms 2 move in the same direction under the transmission between the gears 14, thereby changing the distance between the four support seats 25 and ensuring that the four support seats 25 are arranged in a square.

[0041] Furthermore, the number of the movable mechanisms 2 arranged around the fixing mechanism 1 can also be 3, 5 or more, and the multiple fixing mechanisms 1 form an equilateral polygon and are located at the vertex positions. Accordingly, it is necessary to change the number of gears 14 and support arms 15 and the angle between the first connecting arm 22 and the second connecting arm 23, so that the first connecting arm 22 and the second connecting arm 23 are located at the edge position of the polygon formed by the fixing mechanism 1, and the third connecting arm 24 is located at the midline position of the angle formed by the first connecting arm 22 and the second connecting arm 23.

[0042] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A satellite-rocket separation device with adjustable size, characterized in that: include: A base, wherein a support ring is provided on the base; The support arm is horizontally extended outward from the outer peripheral surface of the base, and a slide rail is arranged along the support arm; A plurality of movable platforms are horizontally and evenly distributed around the support arm, and are provided with sliders adapted to the slide rails, and a sliding connection with the support arm is achieved through the adaptation of the slide rail sliders; each of the two adjacent movable platforms also includes a first connecting arm and a second connecting arm that extend horizontally toward each other; one of the two connecting arms extends a connecting rod, and the other is provided with a connecting hole at a corresponding position of the connecting rod; wherein the connecting rod moves in the connecting hole to movably connect the two adjacent movable platforms; each of the movable platforms also includes a third connecting arm that is horizontally arranged, and the slider is arranged on the third connecting arm; the third connecting arm is horizontally provided with a rack extending to the top of the base along the direction of the slide rail; the upper surface of the base is provided with first gears that mesh with the racks respectively, and the first gears mesh with the second gears at the same time, and the second gears are inner ring gears; the inner ring gears are sleeved in a support ring and movably connected to the support ring through balls; the first gears are arranged in the inner ring gear and mesh with the inner ring gear; The support base is fixed to the upper surface of the movable platform by explosive bolts and is used to connect the satellite.

2. The size-adjustable satellite-rocket separation device according to claim 1, characterized in that: The racks are arranged above the base in an up-and-down staggered or parallel manner.

3. The size-adjustable satellite-rocket separation device according to claim 1, characterized in that: An elliptical through-hole-shaped limiting hole is arranged along the slide rail on the support arm; a limiting bolt which can move in and along the limiting hole is arranged at a position corresponding to the third connecting arm and the limiting hole.

4. The size-adjustable satellite-rocket separation device according to claim 3, characterized in that: The cross section of the support arm is in an I-shape, and the slide rail is arranged in the middle position of the upper surface of the support arm; and the limiting holes are two arranged on both sides of the slide rail.

5. The size-adjustable satellite-rocket separation device according to claim 4, characterized in that: The slide rail is a trapezoidal through groove extending along the upper surface of the support arm.

6. The size-adjustable satellite-rocket separation device according to claim 5, characterized in that: The bottom of the sliding block is arranged along the third connecting arm; and the limiting bolt is located at the connecting position between the rack and the third connecting arm.

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