Launching box mechanism

Abstract

The utility model belongs to the technical field of launching equipment, and provides a launching box mechanism. The device comprises a cylinder body, a control unit and an end cover, the cylinder body is provided with a through cavity used for containing an aircraft, the outer side wall of the cylinder body is provided with a containing cavity, and the containing cavity is provided with a communication opening communicated with the through cavity; the control unit is arranged in the containing cavity and at least comprises a cable, and the cable penetrates through the communication opening and is electrically connected with the aircraft. The end covers are connected to the two ends of the through cavity. According to the utility model, the operation risk of the aircraft is reduced, and the launching preparation period of the aircraft is shortened.

Description

Technical Field

[0001] This utility model relates to the field of launching equipment technology, and in particular to a launching box mechanism. Background Technology

[0002] The launch container and the control system are the two core systems in the launch process of an aircraft. The launch container is the physical carrier and launch platform of the aircraft, while the control system is the "brain" of the aircraft launch. The two work together to ensure that the aircraft can safely and accurately complete the launch mission in complex environments.

[0003] In existing technology, the aircraft is installed inside the launch container and is separate from the control system. When it is necessary to launch the aircraft, the control system cable is manually inserted into the interface that matches the aircraft to complete the electrical connection between the aircraft and the control system, so that the control system can control the launch of the aircraft.

[0004] Transmission systems typically involve high-voltage equipment. Improper manual cable connection (such as failure to properly disconnect power or insufficient insulation) can lead to electric shock, causing serious personal injury or even death. Furthermore, accidental activation of the transmit button or incorrect wiring during manual connection may trigger unexpected transmission procedures, resulting in equipment damage or transmission failure. Moreover, manual connection makes it difficult to ensure a tight contact between the cable and the interface, potentially increasing contact resistance, causing overheating, and long-term operation may burn out the interface or cause a fire.

[0005] Therefore, a new solution is needed to address the aforementioned technical problems. Utility Model Content

[0006] In view of the shortcomings of the prior art described above, the purpose of this utility model is to provide a launch box mechanism to solve the problem of operational risks caused by manually connecting the launch system and the aircraft during the pre-launch phase of the aircraft.

[0007] To achieve the above and other related objectives, this utility model provides a launch box mechanism, specifically configured as follows: it includes a cylindrical body, a control unit, and an end cap, wherein the cylindrical body is provided with a through cavity for placing an aircraft, and an accommodating cavity is provided on the outer side wall of the cylindrical body, the accommodating cavity having a communication port communicating with the through cavity; the control unit is disposed within the accommodating cavity and includes at least a cable, the cable passing through the communication port and being electrically connected to the aircraft; the end cap is connected to both ends of the through cavity.

[0008] Optionally, the launch box mechanism further includes a cable protection assembly disposed inside the cylinder for protecting the cables during the launch of the aircraft.

[0009] Optionally, the cable protection assembly includes at least a first cover plate rotatably connected to the communication port, with a gap between the first cover plate and the communication port, through which the cable extends out of the receiving cavity and is electrically connected to the aircraft; and the communication port is opened along the launch direction of the aircraft, and the communication port can be opened or closed when the first cover plate is rotated.

[0010] Optionally, the cable protection assembly further includes an elastic rotating member, which is connected to both the communication port and the first cover plate, and drives the first cover plate to rotate.

[0011] Optionally, the cable protection assembly further includes a connector connected to the bottom plate of the through cavity, a mounting shaft connected to the connector, an elastic element connected to the mounting shaft, and a second cover plate. The second cover plate is located below the connection point between the cable and the aircraft and is perpendicular to the bottom plate of the through cavity under the action of the elastic element. When the cable detaches from the aircraft, the second cover plate rotates in the opposite direction to the launch of the aircraft along the axis of the mounting shaft under the action of an external force to cover the joint of the cable.

[0012] Optionally, the connecting seat is located on one side of the communication port along the launch direction of the aircraft, and the connecting seat is configured as a hollow structure. The hollow structure is open on the side facing the communication port and on the top away from the bottom plate of the through cavity. When the second cover plate rotates along the axis of the mounting shaft in the opposite direction of the launch of the aircraft under the action of external force, the top of the connecting seat is covered by the second cover plate, and the joint is located in the receiving cavity formed by the connecting seat and the second cover plate.

[0013] Optionally, the accommodating cavity is configured to be recessed from the outer wall of the cylinder into the interior of the through cavity, and the accommodating cavity includes a first chamber and a second chamber that are connected to each other. The first chamber is used to place the main body of the control unit, and the second chamber is used to place the cable.

[0014] Optionally, the cylinder is provided with a plurality of viewing windows in its circumference, and the interior of the cylinder is connected to the outside through the viewing windows.

[0015] Optionally, the through cavity is provided with a limiting seat and a limiting pin for fixing the aircraft. The limiting seat is provided with a limiting groove, and the tail end of the aircraft abuts in the limiting groove. The two opposite side walls of the cylinder are provided with clearance holes for the limiting pin to be inserted into and pulled out of the through cavity. The aircraft is provided with a pin hole that cooperates with the limiting pin. The limiting pin passes through the clearance hole and the pin hole to fix the aircraft in the through cavity.

[0016] Optionally, multiple guide rails are provided on the inner wall of the through cavity to guide the sliding of the aircraft within the through cavity; and / or, multiple hoisting assemblies are connected to the top of the cylinder, the hoisting assembly including at least a lifting ring.

[0017] As described above, the launch box mechanism of this utility model has the following beneficial effects:

[0018] By setting a receiving cavity on the cylinder, in which a control unit is placed, and the receiving cavity is provided with a connecting port that communicates with the through cavity of the cylinder, during the process of installing the aircraft in the cylinder, the cable of the control unit enters the through cavity through the connecting port and connects to the aircraft, so that the control unit and the aircraft are electrically connected. This achieves the purpose of electrically connecting the control unit and the aircraft in advance, avoiding the need to manually electrically connect the control unit and the aircraft during the aircraft's pre-launch phase, which helps to reduce the operational risks of the aircraft and shortens the launch preparation cycle of the aircraft. Attached Figure Description

[0019] Figure 1 The diagram shown is a structural schematic of the launch box mechanism according to an embodiment of the present utility model.

[0020] Figure 2 The diagram shown is a structural schematic of the open launch box mechanism according to an embodiment of the present utility model.

[0021] Figure 3 The diagram shown is a partial structural schematic of the cylinder according to an embodiment of the present utility model.

[0022] Figure 4 The diagram shown is a cross-sectional view of the launch box mechanism according to an embodiment of the present utility model;

[0023] Figure 5 Displayed as Figure 4 A schematic diagram of the structure of part A in the middle;

[0024] Figure 6 The diagram shown is a partial structural schematic of the cable protection assembly according to an embodiment of the present invention;

[0025] Figure 7 The diagram shown is a structural schematic of the limiting seat according to an embodiment of the present invention.

[0026] Explanation of reference numerals in the attached figures

[0027] 1-Cylinder body; 11-Through cavity; 12-Connecting port; 13-U-shaped main body; 131-Bottom plate; 14-Top cover; 15-First chamber; 16-Second chamber; 17-Leaving hole; 18-Viewing window; 19-Guide rail;

[0028] 2-End cap;

[0029] 3-Reinforcing components;

[0030] 4-First cover plate; 41-Elastic rotating component;

[0031] 5-Connecting seat; 51-Mounting shaft; 52-Elastic element; 53-Second cover plate; 54-Limiting shaft;

[0032] 6-Limit seat; 61-Limit groove;

[0033] 7-Limit pin;

[0034] 8-panel;

[0035] 9-Hanging rings. Detailed Implementation

[0036] The following specific examples illustrate the implementation of this utility model. Those skilled in the art can easily understand other advantages and effects of this utility model from the content disclosed in this specification. This utility model can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this utility model.

[0037] It should be noted that the illustrations provided in this embodiment are only schematic representations of the basic concept of this utility model. Therefore, the illustrations only show components relevant to this utility model and are not drawn according to the actual number, shape, and size of the components in implementation. In actual implementation, the shape, quantity, and proportion of each component can be arbitrarily changed, and the component layout may be more complex. The structures, proportions, and sizes shown in the accompanying drawings are only for illustrative purposes to aid those skilled in the art and are not intended to limit the implementation conditions of this utility model. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to size, without affecting the effects and objectives of this utility model, should still fall within the scope of the technical content disclosed in this utility model. Furthermore, terms such as "upper," "lower," "left," "right," "middle," and "one" used in this specification are only for clarity of description and are not intended to limit the scope of implementation of this utility model. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of implementation of this utility model.

[0038] like Figure 1 and Figure 2As shown, some embodiments of this application provide a launch box mechanism, including a cylindrical body 1, a control unit, and end caps 2. The cylindrical body 1 has a through cavity 11, and the end caps 2 are installed at both ends of the open portion of the through cavity 11 to close it. The aircraft is installed inside the through cavity 11, and the end caps 2 provide dust and water protection for the aircraft. A receiving cavity is provided on the outer wall of the cylindrical body 1, and the control unit is installed inside this receiving cavity. This receiving cavity has a connecting port 12 that communicates with the through cavity 11. The control unit includes at least a cable, which enters the through cavity 11 through the connecting port 12 and connects to the aircraft, enabling an electrical connection between the control unit and the aircraft. This allows for pre-connection of the control unit and the aircraft, avoiding manual electrical connection during the pre-launch phase, reducing operational risks, and shortening the launch preparation cycle.

[0039] For example, the end cap 2 is set as a fragile cap. Before the aircraft is launched, the end cap 2 serves to prevent dust and water. During the launch process, the aircraft breaks the end cap 2 under the action of the booster to complete the launch.

[0040] like Figure 1 and Figure 3 As shown, in one example, the cylinder 1 can be assembled from a U-shaped body 13 and a top cover 14 mounted on the U-shaped body 13. The cylinder 1 is made of composite material, which helps to avoid electromagnetic interference generated inside the cylinder 1 that could cause positioning errors in the control unit. Furthermore, the inner wall of the cylinder 1 is coated with a fire-retardant coating, which helps to improve the service life of the cylinder 1.

[0041] A reinforcing member 3 is installed on the circumferential sidewall of the cylinder 1 to improve the structural strength of the cylinder 1. Multiple reinforcing members 3 may be provided and spaced apart on the circumferential sidewall of the cylinder 1.

[0042] like Figure 2 As shown, in one example, the accommodating cavity is configured as a recessed structure extending from the outer wall of the cylinder 1 into the interior of the through cavity 11. The accommodating cavity can be made into a sealed chamber by mounting the panel 8. This configuration makes the external structure of the cylinder 1 regular and facilitates storage. Furthermore, the accommodating cavity includes a first chamber 15 and a second chamber 16 that are connected. The first chamber 15 is used to house the main body of the control unit, and the second chamber 16 is used to house the cable. The arrangement of the second chamber 16 also helps to reduce electromagnetic interference from the cable.

[0043] In some embodiments, the cables located within the through cavity 11 are at risk of being burned by the flames ejected from the tail of the aircraft during launch. Therefore, a cable protection assembly is provided inside the cylinder 1 to protect the cables, thereby enabling the cables to be reused and helping to save on aircraft launch costs.

[0044] like Figure 2 , Figure 4 and Figure 5 As shown, in one example, the cable protection assembly includes at least a first cover plate 4. A gap is provided between the first cover plate 4 and the communication port 12 of the accommodating cavity. The cable located in the accommodating cavity extends out of the accommodating cavity through this gap to complete the electrical connection with the aircraft. The first cover plate 4 is rotatably connected to the communication port 12 of the accommodating cavity, and the communication port 12 of the accommodating cavity is opened along the launch direction of the aircraft. When the first cover plate 4 is rotated, the communication port 12 of the accommodating cavity can be opened or closed.

[0045] During the launch process, the cable is initially pulled towards the launch direction by the aircraft. During this process, the first cover plate 4 rotates to open the connection port 12 of the accommodating cavity, which helps reduce wear on the cable. After the cable detaches from the aircraft, the first cover plate 4 rotates to close the connection port 12 of the accommodating cavity, preventing the flames ejected from the tail of the aircraft from entering the accommodating cavity and protecting the cable. It should be noted that the initial state of the first cover plate 4 is with the connection port 12 of the accommodating cavity closed.

[0046] In one example, an elastic rotating member 41 is installed at the connection port 12 of the accommodating cavity, and a first cover plate 4 is mounted on the elastic rotating member 41. When the cable is pulled by the aircraft, the elastic rotating member 41, under the action of the cable, drives the first cover plate 4 to open the connection port 12 of the accommodating cavity; when the cable is detached from the aircraft, the elastic rotating member 41, under the action of its own restoring force, drives the first cover plate 4 to close the connection port 12 of the accommodating cavity.

[0047] For example, the elastic rotating element 41 includes, but is not limited to, a hinge with a torsion spring.

[0048] like Figure 6 As shown, in some embodiments, the cable protection assembly further includes a connector 5, a mounting shaft 51, an elastic element 52, and a second cover plate 53. The connector 5 is mounted on the base plate 131 of the through cavity 11, the mounting shaft 51 is mounted on the connector 5, and the elastic element 52 and the second cover plate 53 are both mounted on the mounting shaft 51. The second cover plate 53 is located below the connection point between the cable and the aircraft, and initially, under the action of the elastic element 52, the second cover plate 53 is perpendicular to the base plate 131 of the through cavity 11. When the cable detaches from the aircraft, the second cover plate 53 rotates relative to the axis of the mounting shaft 51 in the opposite direction of the aircraft's launch under the force of the aircraft's jet flame, thus covering the cable joint and protecting it. This allows the cable to be reused multiple times, improving its service life and reducing the launch cost of the aircraft.

[0049] In one example, the connector 5 is located on the side of the cavity connection 12 along the launch direction of the aircraft and is configured as a hollow structure. This hollow structure is open on the side facing the cavity connection 12 and on its top away from the bottom plate 131 of the through cavity 11. When the second cover plate 53 rotates relative to the axis of the mounting shaft 51 in the opposite direction of the aircraft launch under the force of the aircraft's jet flame, the top of the connector 5 is covered by the second cover plate 53. At this time, the cable connector is located within the cavity formed by the hollow structure of the connector 5 and the second cover plate 53, thereby preventing the cable connector from being burned by the flames ejected from the tail of the aircraft.

[0050] For example, the elastic element 52 may include, but is not limited to, a torsion spring.

[0051] In one example, in order to restrict the direction of rotation of the second cover plate 53, the connecting seat 5 is also equipped with a limiting shaft 54.

[0052] For example, a certain distance is provided between the connecting port 12 of the accommodating cavity and the connecting seat 5. The cable located between this distance is completely exposed in the through cavity 11. Fireproof cotton can be wrapped around this section of cable to protect the cable.

[0053] like Figure 2 and Figure 7 As shown, in some embodiments, to secure the aircraft within the through cavity 11 of the cylindrical body 1, a limiting seat 6 and a limiting pin 7 are provided within the through cavity 11 of the cylindrical body 1. The limiting seat 6 is mounted on the base plate 131 of the through cavity 11 and has a limiting groove 61. The tail end of the aircraft abuts against the limiting groove 61 to limit the tail end of the aircraft. Both opposite side walls of the cylindrical body 1 are provided with clearance holes 17, which can be two opposite side walls in the width direction of the cylindrical body 1. The limiting pin 7 is inserted into or removed from the through cavity 11 through the clearance holes 17, and the aircraft has a pin hole that mates with the limiting pin 7. When the limiting pin 7 is inserted into the pin hole on the aircraft through the clearance hole 17, the aircraft is completely secured within the through cavity 11; when the limiting pin 7 is removed from the pin hole on the aircraft through the clearance hole 17, the aircraft is released and subsequent launch operations can be performed. It should be noted that the pin hole can be located in the middle of the aircraft or near the front of the aircraft.

[0054] In some embodiments, the cylindrical body 1 is provided with a plurality of viewing windows 18 in the circumferential direction. The number and position of the viewing windows 18 can be adaptively adjusted according to the position to be observed. The situation inside the through cavity 11 can be observed through the viewing windows 18, such as the connection between the cable connector and the aircraft, the fixation of the aircraft inside the through cavity 11, etc.

[0055] Furthermore, the interior of the cylinder 1 is connected to the outside world through a viewing window 18, so that the viewing window 18 can relieve pressure on the through cavity 11 during the launch of the aircraft, which is beneficial to improving the service life of the cylinder 1.

[0056] In some embodiments, a plurality of guide rails 19 are provided on the inner sidewall of the through cavity 11 of the cylinder 1, thereby guiding the aircraft to slide inside the cylinder 1, and the guide rails 19 also play a role in improving the structural strength of the cylinder 1.

[0057] In some embodiments, the top of the cylinder 1 is connected to a plurality of lifting assemblies, which include at least a lifting ring 9. The lifting ring 9 enables automatic transfer of the launch box, which helps to reduce the transfer stress of the launch box.

[0058] In summary, the launch box mechanism provided by this utility model, by setting a receiving cavity on the cylindrical body, in which a control unit is placed, and the receiving cavity is provided with a connecting port that communicates with the through cavity of the cylindrical body, during the process of installing the aircraft in the cylindrical body, the cable of the control unit enters the through cavity through the connecting port and connects to the aircraft, so that the control unit and the aircraft are electrically connected, thereby achieving the purpose of electrically connecting the control unit and the aircraft in advance, avoiding manual electrical connection of the control unit and the aircraft during the aircraft's pre-launch stage, which helps to reduce the operational risks of the aircraft and shortens the launch preparation cycle of the aircraft.

[0059] The above embodiments are merely illustrative of the principles and effects of this utility model and are not intended to limit the scope of this utility model. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this utility model. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this utility model should still be covered by the claims of this utility model.

Claims

1. A launching box mechanism, characterized by, The application relates to a launching box mechanism for launching a flying vehicle. The launching box mechanism comprises a barrel provided with a through cavity for placing the flying vehicle, and a containing cavity is arranged on the outer wall of the barrel, the containing cavity is provided with a communication port communicated with the through cavity; A control unit is arranged in the containing cavity and comprises at least a cable line, the cable line passes through the communication port and is electrically connected with the flying vehicle; End covers are connected at both ends of the through cavity.

2. The launching box mechanism of claim 1, wherein: The launching box mechanism further comprises a cable protection assembly arranged in the barrel for protecting the cable line during launching of the flying vehicle.

3. The launching box mechanism of claim 2, wherein: The cable protection assembly comprises at least a first cover plate rotatably connected at the communication port, a gap is arranged between the first cover plate and the communication port, the cable line passes through the gap and is electrically connected with the flying vehicle, the communication port is opened along the launching direction of the flying vehicle, and the first cover plate can open or close the communication port when rotating.

4. The launching box mechanism of claim 3, wherein: The cable protection assembly further comprises an elastic rotating member, the elastic rotating member is connected with the communication port and the first cover plate and drives the first cover plate to rotate.

5. The launching box mechanism of claim 3, wherein: The cable protection assembly further comprises a connecting seat connected on the bottom plate of the through cavity, a mounting shaft connected on the connecting seat, and an elastic member and a second cover plate connected on the mounting shaft, the second cover plate is arranged below the connection position of the cable line and the flying vehicle and is perpendicularly arranged on the bottom plate of the through cavity under the action of the elastic member, and the second cover plate rotates along the axis of the mounting shaft in the direction opposite to the launching direction of the flying vehicle under the action of external force to cover the joint of the cable line when the cable line is separated from the flying vehicle.

6. The launching box mechanism of claim 5, wherein: The connecting seat is arranged on one side of the communication port along the launching direction of the flying vehicle, the connecting seat is arranged as a hollow structure, the side of the hollow structure facing the communication port and the top of the hollow structure away from the bottom plate of the through cavity are both arranged as open structures, the top of the connecting seat is covered by the second cover plate when the second cover plate rotates along the axis of the mounting shaft in the direction opposite to the launching direction of the flying vehicle under the action of external force, and the joint is arranged in the receiving cavity formed by the connecting seat and the second cover plate.

7. The launching box mechanism of any of claims 1-6, wherein: The containing cavity is arranged as a structure recessed from the outer wall of the barrel to the inside of the through cavity, and the containing cavity comprises a first chamber and a second chamber communicated with each other, the first chamber is used for placing the main body of the control unit, and the second chamber is used for placing the cable line.

8. The launching box mechanism of any one of claims 1-6, wherein: A plurality of visual windows are arranged on the circumference of the barrel, and the inside of the barrel is communicated with the outside through the visual windows.

9. The launching box mechanism of claim 8, wherein: Limiting seats and limiting pins for fixing the flying vehicle are arranged in the through cavity, limiting grooves are arranged on the limiting seats, and the tail end of the flying vehicle abuts against the limiting grooves; the limiting pins are arranged in the limiting grooves and the pin holes to fix the flying vehicle in the through cavity.

10. The launching box mechanism of claim 9, wherein: The inner side wall of the through cavity is provided with a plurality of guide rails to guide the sliding of the aircraft in the through cavity; and / or the top of the cylinder body is connected with a plurality of hoisting assemblies, and the hoisting assemblies at least include lifting rings.

Images