Satellite-rocket separation signal triggering mechanism

Abstract

The utility model relates to a satellite and rocket separation signal triggering mechanism which comprises an ejector pin and a nut. The ejector pin has a certain length, one end is a signal triggering end, and the other end is a first connecting end; the nut is provided with a first connecting structure which is connected with the first connecting end. An elastic element is further arranged on the ejector pin body in a sleeved mode, and the elastic element is in sliding fit with the ejector pin body. The ejector pin, the nut and the elastic element are combined to obtain a combined part; a mounting position is arranged near a signal switch of the satellite, and when the assembly is assembled to the mounting position, the signal triggering end faces the signal switch; the ejector pin has a stroke of linear movement on the installation position so as to control the signal switch to be turned on and turned off. The satellite antenna is installed externally and is convenient to maintain and repair, and other parts of the satellite do not need to be disassembled.

Description

Technical Field

[0001] This utility model relates to the field of aerospace equipment technology, and in particular to a star-rocket separation signal triggering mechanism. Background Technology

[0002] After the satellite separates from the rocket, it receives the triggered separation signal and proceeds with subsequent tasks according to a pre-set program. Depending on the separation mechanism used, the triggering mechanism for the separation signal can take various forms. However, for relatively small CubeSats, which typically use a Separation Deployer (POD) for separation, the installation location for the separation signal triggering mechanism is usually limited. Traditional installation methods require installation from inside the satellite, and the assembly process must consider at which step the separation signal triggering mechanism needs to be installed. Furthermore, the maintenance or replacement of the separation signal triggering mechanism presents certain challenges. Utility Model Content

[0003] Therefore, it is necessary to provide a star-rocket separation signal triggering mechanism that is easy to install and maintain, addressing the aforementioned technical problems.

[0004] A star-rocket separation signal triggering mechanism includes: a pin and a nut; the pin has a certain length, one end of which is a signal triggering end and the other end is a first connecting end; the nut has a first connecting structure, which is connected to the first connecting end; an elastic element is also sleeved on the body of the pin, and the elastic element and the body of the pin are slidably engaged.

[0005] The ejector pin, the nut, and the elastic element are combined to obtain an assembly;

[0006] A mounting position is provided near the satellite's signal switch. When the assembly is assembled into the mounting position, the signal trigger end faces the signal switch. The pin has a linear travel on the mounting position to control the opening and closing of the signal switch.

[0007] In one embodiment, the first connecting end of the ejector pin and the first connecting structure of the nut are threaded connection, snap-fit ​​connection, or adhesive connection.

[0008] In one embodiment, a limiting member is also provided on the ejector pin; the limiting member is arranged circumferentially along the ejector pin body and is located on the side close to the first connecting end.

[0009] In one embodiment, a plug is also included; the plug has a first through hole through it, and the nut passes through the first through hole and is clearance-fitted with the first through hole.

[0010] In one embodiment, the plug is provided with a second connecting end, and the mounting position is provided with a second connecting structure. When the assembly is assembled onto the mounting position, the second connecting end is connected to the second connecting structure.

[0011] In one embodiment, the nut has a cap edge on the side near the ejector pin, the height of which is greater than the diameter of the first through hole, in order to restrict the movement of the plug.

[0012] In one embodiment, the second connecting end of the plug and the second connecting structure on the mounting position are connected by a threaded connection, a snap-fit ​​connection, or an adhesive connection.

[0013] In one embodiment, the mounting position is further provided with a pin through hole and a receiving cavity; the pin through hole is located on the side near the signal switch, and the receiving cavity is located between the pin through hole and the second connecting structure;

[0014] When the assembly is assembled to the mounting position, the elastic element and the ejector pin body are placed in the receiving cavity, and the signal trigger end passes through the ejector pin through hole and faces the signal switch; the ejector pin body and the ejector pin through hole are clearance fit.

[0015] In one embodiment, the signal triggering end has a tapered structure.

[0016] In one embodiment, the elastic element is a spring.

[0017] Compared with existing technologies, the star-rocket separation signal triggering mechanism provided by this utility model has the following advantages:

[0018] 1. The assembly process is simplified by pre-assembling the pin, nut, and elastic element into a modular assembly before installing it onto the mounting position near the satellite switch. External installation reduces the need for complex operations inside the satellite, facilitating maintenance and repair without disassembling other parts of the satellite.

[0019] 2. The linear movement of the signal trigger end of the ejector pin controls the opening and closing of the signal switch, ensuring the accuracy and reliability of signal triggering and avoiding signal triggering failure or false triggering caused by complex movements.

[0020] 3. Pre-assembled components can be applied to satellites of different sizes and types to meet the needs of various satellite-rocket separation scenarios. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of a star-rocket separation signal triggering mechanism in one embodiment, where the elastic element is in its natural state.

[0023] Figure 2 This is a schematic diagram of the star-rocket separation signal triggering mechanism in one embodiment, where the elastic element is in a pre-tightened state.

[0024] Figure 3 An exploded view of an assembly in one embodiment;

[0025] Figure 4 for Figure 3 AA section view in the middle;

[0026] Figure 5 This is a schematic diagram of the assembled structure of the components in one embodiment;

[0027] Figure 6 for Figure 5 BB cross-section diagram in the middle;

[0028] Figure 7 This is a schematic diagram of the mounting position structure in one embodiment;

[0029] Figure 8 This is a schematic diagram showing the installation location of the satellite-rocket separation signal triggering mechanism on the satellite in one embodiment.

[0030] Figure 9 This is a schematic diagram of a satellite ejecting from the separation deployer hatch in one embodiment.

[0031] Figure label:

[0032] The satellite-rocket separation signal triggering mechanism includes: 10, pin 1, body 11, signal triggering end 12, first connecting end 13, limiting member 14, nut 2, first connecting structure 21, cap edge 22, elastic element 3, plug 4, first through hole 41, second connecting end 42, mounting position 5, pin through hole 51, receiving cavity 52, second connecting structure 53, satellite 6, slide rail 61, signal switch 7, separation deployer 8, hatch 81, and spring connecting plate 82.

[0033] The purpose, features, and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0034] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0035] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in this utility model embodiment are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0036] Furthermore, in this utility model, the use of terms such as "first," "second," etc., is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this utility model, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0037] In this utility model, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal connection of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0038] Furthermore, the detachable connection described in this utility model includes, but is not limited to, snap-fit ​​connections, threaded connections, pin connections, magnetic connections, plug-in connections, etc., which can be selected flexibly according to the situation. The specific detachable connection methods shown in the following embodiments are one of the feasible methods and are not intended to be the only limitation.

[0039] The embodiments of this utility model will now be described in detail with reference to the accompanying drawings.

[0040] Example 1

[0041] like Figures 1 to 9As shown, the satellite-rocket separation signal triggering mechanism 10 provided in this embodiment includes: a pin 1 and a nut 2; the pin 1 has a certain length, one end of which is a signal triggering end 12, and the other end is a first connecting end 13; the nut 2 has a first connecting structure 21, which is connected to the first connecting end 13; an elastic element 3 is also sleeved on the body 11 of the pin 1, and the elastic element 3 is slidably engaged with the body 11 of the pin 1; the pin 1, the nut 2, and the elastic element 3 are combined to obtain an assembly. A mounting position 5 is provided near the signal switch 7 of the satellite 6. When the assembly is assembled to the mounting position 5, the signal triggering end 12 faces the signal switch 7; the pin 1 has a linear travel stroke on the mounting position 5 to control the opening and closing of the signal switch 7.

[0042] Specifically, the surface of the ejector pin 1 is smooth, thereby reducing friction and facilitating the movement of the body 11 of the ejector pin 1. The cross-section of the ejector pin 1 is circular, but it can also be designed as a polygon or rectangle, depending on the requirements. The front end of the ejector pin 1 is a signal trigger end 12. The side of the signal trigger end 12 closest to the body 11 has the same shape as the body 11, and its outward extension gradually narrows to form a conical structure. The conical structure design can reduce the movement resistance and provide effective cushioning when pressing the signal switch 7.

[0043] The rear end of the ejector pin 1 is the first connecting end 13. The first connecting end 13 and the first connecting structure 21 of the nut 2 are connected by a thread, a snap-fit, or an adhesive. For example, when the first connecting end 13 and the first connecting structure 21 are connected by a thread, the first connecting end 13 has a partial length and its surface is designed to be threaded. Correspondingly, the first connecting structure 21 of the nut 2 is a threaded hole that matches the first connecting end 13, so as to facilitate the connection and fixation of the first connecting end 13 and the first connecting structure 21. When the first connecting end 13 and the first connecting structure 21 are connected by a snap-fit, the first connecting end 13 and the first connecting structure 21 are respectively designed as an elastic hook and a groove. The elastic hook is compressed and undergoes elastic deformation during insertion. When the elastic hook reaches the groove position, the elastic hook recovers its deformation and snaps into the groove, thereby realizing the snap-fit ​​connection and fixation of the first connecting end 13 and the first connecting structure 21. When the first connecting end 13 and the first connecting structure 21 are bonded together, a special high-strength adhesive can be applied to the surface of the first connecting end 13 and / or the first connecting structure 21. After the two come into contact and adhere, the first connecting end 13 and the first connecting structure 21 are firmly bonded together through the curing effect of the adhesive, forming a stable connection structure. Alternatively, the rear end face of the body 11 can be directly regarded as the first connecting end 13, and the side of the nut 2 that contacts the first connecting end 13 can be regarded as the first connecting structure 21, and then the connection can be fixed by adhesive bonding. Among the above connection methods, threaded connection and snap-fit ​​connection are convenient for quick installation and disassembly, while adhesive connection can ensure the sealing and integrity of the connection part and reduce the connection gap. The specific connection method can be selected according to the requirements.

[0044] A limiting member 14 is also provided on the ejector pin 1; the limiting member 14 is arranged circumferentially along the body 11 of the ejector pin 1 and is located on the side close to the first connecting end 13. The body 11, the first connecting end 13, the first connecting structure 21 and the limiting member 14 are arranged coaxially; and in cross-section, the diameter of the limiting member 14 is larger than that of the body 11, the first connecting end 13 and the first connecting structure 21; its main function is to limit the amount of displacement of the connecting part towards the body 11 when the first connecting end 13 is connected to the first connecting structure 21, thereby effectively preventing the connecting part from getting too close to the body 11, ensuring the stability and reliability of the connecting part, and avoiding structural failure or performance degradation caused by over-connection.

[0045] The length of nut 2 is greater than the length of plug 4, specifically designed according to the length of ejector pin 1. The combined length is designed to allow for linear movement on mounting position 5, facilitating smooth control of the opening and closing of signal switch 7. The surface of nut 2 is smooth to facilitate movement within the first through hole 41 of plug 4. Nut 2 has a cap edge 22 on the side near ejector pin 1, the height of which is greater than the diameter of the first through hole 41, limiting the rightward displacement of plug 4. Nut 2 has a cavity, with a first connecting structure 21 on the right side of the cavity. This cavity mainly accommodates part of body 11, elastic element 3, and limiting member 14. In this embodiment, since a threaded connection is shown, the first connecting structure 21 is a threaded hole adapted to the first connecting end 13, and this threaded hole is a through design. If it is a snap-fit ​​connection or adhesive connection, the first connecting structure 21 is designed accordingly, which will not be elaborated here.

[0046] The elastic element 3 is a structure that can deform under external force and return to its original shape after the external force is removed. It can be a part made of elastic material such as a spring or a sheet spring. In this embodiment, a spring is preferred. The elastic element 3 is sleeved on the body 11 of the ejector pin 1 and can slide on the body 11. The diameter of the elastic element 3 is smaller than that of the limiting member 14. When the elastic element 3 is pre-tightened, the limiting member 14 can restrict the axial displacement of the elastic element 3, thereby preventing the elastic element 3 from leaving the preset position during the force application process.

[0047] The assembly also includes a plug 4, which has a first through hole 41 through which a nut 2 passes and is clearance-fitted. A second connecting end 42 is also provided on the plug 4. Correspondingly, a second connecting structure 53 is provided on the mounting position 5. When the assembly is assembled onto the mounting position 5, the second connecting end 42 is connected and fixed to the second connecting structure 53. The connection and fixing method is threaded connection, snap-fit ​​connection, or adhesive connection. Specifically, when the second connecting end 42 and the second connecting structure 53 are threadedly connected, the surface of the second connecting end 42 is designed with a threaded structure; correspondingly, the second connecting structure 53 is designed with a threaded hole adapted to the second connecting end 42 to facilitate the threaded connection between the second connecting end 42 and the second connecting structure 53. When the second connecting end 42 and the second connecting structure 53 are connected by a snap-fit, the second connecting end 42 and the second connecting structure 53 are designed as an elastic hook and a slot, respectively. The elastic hook undergoes elastic deformation under compression during insertion. When the elastic hook reaches the slot position, it recovers its deformation and engages with the slot, thus achieving a snap-fit ​​connection and fixation between the second connecting end 42 and the second connecting structure 53. When the second connecting end 42 and the second connecting structure 53 are connected by an adhesive, a special high-strength adhesive can be applied to the surface of the second connecting end 42 and / or the second connecting structure 53. After the two come into contact and adhere, the adhesive cures, firmly bonding the second connecting end 42 and the second connecting structure 53 together to form a stable connection structure. Among the above connection methods, threaded connections and snap-fit ​​connections facilitate quick installation and disassembly, while adhesive connections ensure the sealing and integrity of the connection parts and reduce connection gaps. The specific connection method can be selected according to requirements.

[0048] Mounting position 5 is mainly used to install the assembly formed by the pin 1, nut 2, elastic element 3 and plug 4. It is preferably set near the signal switch 7. In this embodiment, mounting position 5 is set on the slide rail 61 of satellite 6, and located at the front end and / or rear end of the slide rail. The number of mounting positions is more than one, and the specific number is determined according to the requirements. Specifically, mounting position 5 includes a pin through hole 51, a receiving cavity 52 and a second connecting structure 53. The pin through hole 51, the receiving cavity 52 and the second connecting structure 53 are all through holes that are opened through the slide rail 61, but the hole diameters are different. Among them, the pin through hole 51 is set on the side near the signal switch 7, and its inner diameter is preferably large enough to accommodate the body 11 of the pin 1 to pass through, and it is clearance fit with the body 11 of the pin 1. The receiving cavity 52 is located between the pin through hole 51 and the second connecting structure 53. It is mainly used to accommodate the body 11 after the elastic element 3 is sleeved. Its inner diameter is determined according to the height of the limiting member 14 and its length is determined according to the elastic element 3 in its natural state. The inner diameter of the second connecting structure 53 is adapted to the outer diameter of the plug 4. When the assembly is assembled to the mounting position 5, the elastic element 3 and the body 11 of the ejector pin 1 are placed in the receiving cavity 52. ​​The signal trigger end 12 of the ejector pin 1 passes through the ejector pin through hole 51 and faces the signal switch 7. When the elastic element 3 is in the natural state, it abuts against the signal switch 7. When the elastic element 3 is in the pre-tightened state, it presses the signal switch 7.

[0049] like Figure 8 As shown, when the star-rocket separation signal triggering mechanism 10 is installed on the slide rail 61, the elastic element 3 is in its natural state, and the right end of the nut 2 protrudes outward.

[0050] During operation, the ejector pin 1, nut 2, elastic element 3 and plug 4 are first pre-assembled to form a combination. The combination is installed on the slide rail 61 from the outside and does not need to be installed from the inside of the satellite body. Therefore, no special consideration is needed in the final assembly process.

[0051] The satellite is then installed in the separation and deployment unit 8. The hatch 81 of the separation and deployment unit 8 is closed. The closed hatch 81 and the spring connecting plate 82 in the separation and deployment unit 8 apply force to the nuts 2 at both ends of the slide rail 61. Since the nuts 2 and the plug 4, and the body 11 of the ejector pin 1 and the ejector pin through hole 51 are all clearance fit, the force causes the signal trigger end 12 to move toward the signal switch 7, and the elastic element 3 is gradually compressed, such as... Figure 2 As shown, when the elastic element 3 is in a pre-tightened state, the signal trigger end 12 of the ejector pin 1 presses the signal switch, at which point the signal switch 7 is closed. This design of pressing the signal switch 7 can avoid the possibility of accidental activation due to vibration or impact during satellite launch, ensuring that it is only triggered when the satellite separates from the launch vehicle, thus improving the safety of the system.

[0052] Once the rocket reaches its designated position, the hatch 81 of the separation and deployment unit 8 opens, and satellite 6 is ejected from the separation and deployment unit 8, as follows: Figure 2 As shown, the elastic element 3 changes from a pre-tightened state to a relaxed state, thereby driving the body 11 of the ejector pin 1 and the nut 2 to move away from the signal switch 7. The signal switch 7 then opens, enabling the satellite to perform subsequent operations according to the preset program. This invention simplifies the assembly process, reducing the need for complex operations inside the satellite through external installation, facilitating maintenance and repair without disassembling other parts of the satellite. The pre-assembled components can be applied to satellites of different sizes and types, meeting the needs of various satellite-rocket separation scenarios, and are particularly suitable for smaller CubeSats.

[0053] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0054] The embodiments described above are merely illustrative of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the appended claims.

Claims

1. A satellite-rocket separation signal trigger mechanism, characterized by, The utility model relates to a signal trigger device for satellite, which comprises: a plunger and a nut; the plunger has a length, one end of which is a signal trigger end and the other end is a first connecting end; the nut has a first connecting structure, which is connected with the first connecting end; an elastic element is sleeved on the plunger body and is slidably connected with the plunger body; the plunger, the nut and the elastic element are combined to obtain an assembly; an installation site is arranged near a signal switch of a satellite, and when the assembly is assembled to the installation site, the signal trigger end faces the signal switch; the plunger has a linear movement stroke on the installation site to control the opening and closing of the signal switch.

2. The satellite-launch vehicle separation signal triggering mechanism according to claim 1, characterized in that, The first connecting end of the plunger and the first connecting structure of the nut are threadedly connected, buckled or adhesively connected.

3. The satellite-launch vehicle separation signal triggering mechanism according to claim 1, characterized in that, A limiting piece is arranged on the plunger; the limiting piece is arranged annularly along the plunger body and is located on the side close to the first connecting end.

4. The satellite-to-rocket separation signal triggering mechanism according to any one of claims 1 to 3, characterized in that, A plug is further included; a first through hole is formed through the plug, and the nut passes through the first through hole and is gap-connected with the first through hole.

5. The satellite-launch vehicle separation signal triggering mechanism according to claim 4, characterized in that, A second connecting end is arranged on the plug, and a second connecting structure is arranged on the installation site; when the assembly is assembled to the installation site, the second connecting end is connected with the second connecting structure.

6. The satellite-launch vehicle separation signal triggering mechanism according to claim 5, characterized in that, A brim is arranged on the nut close to the plunger, and the height of the brim is greater than the diameter of the first through hole to limit the movement of the plug.

7. The satellite-to-rocket separation signal triggering mechanism according to claim 5 or 6, characterized in that, The second connecting end on the plug and the second connecting structure on the installation site are threadedly connected, buckled or adhesively connected.

8. The satellite-launch vehicle separation signal triggering mechanism according to any one of claims 1 to 3, characterized in that, A plunger through hole and a receiving cavity are further arranged on the installation site; the plunger through hole is arranged on the side close to the signal switch, and the receiving cavity is located between the plunger through hole and the second connecting structure; when the assembly is assembled to the installation site, the elastic element and the plunger body are arranged in the receiving cavity, the signal trigger end passes through the plunger through hole and faces the signal switch, and the plunger body is gap-connected with the plunger through hole.

9. The satellite-to-rocket separation signal triggering mechanism according to any one of claims 1 to 3, characterized in that, The signal trigger end is a conical structure.

10. The satellite-to-rocket separation signal triggering mechanism according to any one of claims 1 to 3, characterized in that, The elastic element is a spring.

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