Shelter for aviation charging

Abstract

The invention relates to the technical field of charging square cabins, in particular to an aviation charging square cabin which comprises a cabin body, a pressure sensing unit used for controlling opening and closing of a cabin door is arranged on the side wall of the cabin body, a sealing unit used for keeping sealing is arranged on the outer wall of the cabin body, and an air pressure adjusting unit used for balancing internal and external pressure is arranged on the outer wall of the cabin body. The pressure sensing unit comprises two fixing cylinders, the fixing cylinders are embedded in the outer wall of the cabin body, the two ends of the inner wall of each fixing cylinder are fixedly sleeved with clamping rings, a door plate of the cabin body is controlled through a ball and a trigger, and the situation that the cabin body is opened when the internal pressure of the cabin body is unbalanced due to misoperation is prevented; air pressure values borne by power generation equipment, electricity storage equipment and instruments in the cabin body can be effectively prevented from being rapidly changed, the equipment is prevented from being influenced and damaged by air pressure changes, automatic monitoring of air pressure difference and cabin door unlocking control are achieved through mechanical linkage closed-loop control logic, the function is equivalent to the function of judging a pressure threshold value, and the safety is improved. And manual operation errors are avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of charging cabins, in particular to a cabin for aviation charging. Background Art

[0002] The aviation charging cabin is essentially a comprehensive support system. Its main function is to provide convenient and efficient charging services for various aircraft, especially drones. In traditional aviation operations, aircraft, especially drones, often face the problem of insufficient endurance, which greatly limits their operating range and duration. The emergence of the aviation charging cabin effectively solves this problem. When the aircraft is low on power, it can quickly replenish its energy to ensure the continuous implementation of the mission.

[0003] For example, a pressure-balanced wireless charging station with publication number CN115750861A uses a piston to form a sealed breathing pressure regulating device and applies it to the telescopic mechanism of the wireless charging station to solve the problem of air pressure balance. However, there are a large number of electronic components inside the aviation charging cabin. The cabin needs to be kept sealed during transportation to prevent air pressure changes from damaging the electronic components. However, when the door of the aviation charging cabin is opened, the gases inside and outside will converge rapidly, which will cause the air pressure value inside the cabin to change rapidly. The rapid air pressure change will cause discharge and damage to the electronic components. The existing cabin pressure balancing device has the risk of opening the door when the internal and external pressures are unbalanced, which can easily lead to erroneous operations and damage to the equipment inside the cabin. Summary of the Invention

[0004] In response to the problems in the prior art, the present invention provides a square cabin for aviation charging.

[0005] The technical solution adopted by the present invention to solve the technical problem is: a cabin for aviation charging, comprising a cabin body, a pressure sensing unit for sensing the pressure difference between the inside and outside of the cabin and an execution unit for realizing cabin door control are provided on the side walls of the cabin body, an air pressure regulating unit for balancing the pressure inside and outside the cabin is provided on the outer wall of the cabin body, a sealing unit for maintaining the sealing of the cabin is provided on the outer wall of the cabin body, and a power generation assembly is fixedly connected to the inner wall of the cabin body; The pressure sensing unit includes two fixed cylinders, each of which is embedded in the outer wall of the cabin. A clamping ring is fixedly sleeved on both ends of the inner wall of the fixed cylinder. A ball is clamped inside the fixed cylinder. Two through holes are symmetrically formed on the outer wall of the fixed cylinder, and a trigger is embedded inside the through holes. The execution unit includes a wire fixedly connected to the trigger, a plurality of fixed boxes fixedly connected to the inner wall of the cabin, an electric cylinder embedded in the interior of the fixed box, a conical push rod fixedly connected to the output end of the electric cylinder, and an electrical connection between the electric cylinder and the power generation component.

[0006] Specifically, two ends of the wire are connected to the trigger and the electric cylinder respectively, and the trigger extends to the interior of the fixing cylinder.

[0007] Specifically, the surface of the sphere fits with the trigger, and the trigger is arranged at the center of the fixed cylinder.

[0008] Specifically, the air pressure regulating unit includes a cylinder, which is embedded in the outer wall of the cabin. A spherical groove is provided on the inner wall of the cylinder. A rotating ball is clamped inside the spherical groove. A balancing hole is provided at the center of the rotating ball. A rotating rod is fixedly connected to the surface of the rotating ball. A rotating hole is provided on the outer wall of the cylinder. The rotating rod is rotatably connected to the rotating hole, and a push rod is fixedly connected to the other end of the rotating rod.

[0009] Specifically, the rotating ball matches the spherical groove, and the balancing hole is arranged perpendicular to the rotating rod.

[0010] Specifically, the sealing unit includes a plurality of sockets opened on the surface of the cabin, an insertion rod is inserted into the inside of the socket, a clamping groove is opened on the surface of the insertion rod, the other end of the insertion rod is fixedly connected to a cover plate, two handles are symmetrically fixedly connected to one side wall of the cover plate, and two openings are opened on the outer wall of the cabin.

[0011] Specifically, the clamping groove matches the tapered push rod, the tapered push rod is inserted into the clamping groove, and the clamping groove is provided on the surface of one end of the tapered push rod inserted into the interior of the cabin.

[0012] Beneficial effects of the present invention: (1) The present invention provides a square cabin for aviation charging, which controls the cabin door panel by means of a ball and a trigger, thereby preventing the cabin door panel from being opened due to an operational error that causes an imbalance in the internal pressure of the cabin. This can effectively prevent the power generation equipment, power storage equipment and instruments in the cabin from experiencing rapid changes in the air pressure values, and prevent the equipment from being damaged by the air pressure changes. The closed-loop control logic of the mechanical linkage realizes automatic monitoring of the air pressure difference and door unlocking control, which is equivalent to having a pressure threshold judgment function, thereby avoiding manual operational errors.

[0013] (2) The present invention provides a square cabin for aviation charging, which connects the spaces at both ends of the cylinder through a balancing hole, so that the inner and outer ends of the cabin are connected, thereby allowing air to be input from the end with higher air pressure to the other end, thereby slowly balancing the air pressure inside the cabin with the external air pressure. This can avoid sudden changes in air pressure caused by a large difference between the internal and external air pressures of the cabin. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The present invention will be further described below with reference to the accompanying drawings and examples.

[0015] Figure 1 This is a schematic diagram of the appearance structure of an aviation charging cabin provided by the present invention; Figure 2 A schematic diagram of the cross-sectional structure of an aviation charging cabin provided by the present invention Figure 1 ; Figure 3 A schematic diagram of the cross-sectional structure of an aviation charging cabin provided by the present invention Figure 2 ; Figure 4 A schematic diagram of the cross-sectional structure of an aviation charging cabin provided by the present invention Figure 3 ; Figure 5 A schematic diagram of the cover structure of an aviation charging cabin provided by the present invention; Figure 6 A schematic diagram of the fixed cylinder structure of an aviation charging cabin provided by the present invention; Figure 7 This is a schematic diagram of the cylindrical structure of an aviation charging cabin provided by the present invention; Figure 8 This is a schematic diagram of the power generation component structure of an aviation charging cabin provided by the present invention.

[0016] In the figure: 1. Cabin; 2. Pressure sensing unit; 21. Fixing cylinder; 22. Retaining ring; 23. Ball; 24. Through hole; 25. Trigger; 3. Actuator; 31. Wire; 32. Fixing box; 33. Electric cylinder; 34. Conical push rod; 4. Air pressure regulating unit; 41. Cylinder; 42. Spherical groove; 43. Rotating ball; 44. Balancing hole; 45. Rotating rod; 46. Rotating hole; 47. Push rod; 5. Sealing unit; 51. Socket; 52. Rod; 53. Clamping groove; 54. Cover; 55. Handle; 56. Opening; 6. Power generation component. DETAILED DESCRIPTION

[0017] In order to make the technical means, creative features, objectives and effects achieved by the present invention easier to understand, the present invention is further described below in conjunction with specific implementation methods.

[0018] See also Figures 1 to 8 , the present invention provides the following technical solutions: Example 1: A shelter for aviation charging, comprising a shelter 1, with a pressure sensing unit 2 for sensing the pressure difference between the inside and outside of the shelter and an actuator 3 for controlling the cabin door provided on the side walls of the shelter 1; an air pressure regulating unit 4 for balancing the pressure inside and outside the shelter provided on the outer wall of the shelter 1; a sealing unit 5 for maintaining the seal of the shelter provided on the outer wall of the shelter 1; and a power generation assembly 6 fixedly connected to the inner wall of the shelter 1; The pressure sensing unit 2 includes two fixed cylinders 21, which are embedded in the outer wall of the cabin 1. A clamping ring 22 is fixedly sleeved on both ends of the inner wall of the fixed cylinder 21. A ball 23 is clamped inside the fixed cylinder 21. Two through holes 24 are symmetrically formed on the outer wall of the fixed cylinder 21, and a trigger 25 is embedded in the through holes 24. The execution unit 3 includes a wire 31 fixedly connected to the trigger 25, and a plurality of fixed boxes 32 are fixedly connected to the inner wall of the cabin 1. An electric cylinder 33 is embedded in the interior of the fixed box 32, and a conical push rod 34 is fixedly connected to the output end of the electric cylinder 33. The electric cylinder 33 is electrically connected to the power generation component 6.

[0019] The air pressure balance control system is composed of the pressure sensing unit 2, the execution unit 3, the air pressure regulating unit 4 and the sealing unit 5. The working process of the air pressure balance control system is as follows: Pressure monitoring stage: The pressure difference between the inside and outside of the cabin pushes the ball 23 to move. When the pressure difference is ≤0.05MPa, the ball 23 returns to the center of the fixed cylinder, triggering the trigger 25 to generate an electrical signal; Execution decision stage: an electrical signal is transmitted to the electric cylinder 33 via the wire 31, causing it to retract and unlock the hatch; Air pressure adjustment stage: If active air pressure balance is required, the operator rotates the rotating ball 43 through the push rod 47 to adjust the opening angle of the balance hole 44 according to the pressure difference. The greater the pressure difference, the greater the opening angle, forming a proportional control effect of manual intervention.

[0020] The two ends of the wire 31 are respectively connected to the trigger 25 and the electric cylinder 33. The trigger 25 extends to the inside of the fixed tube 21, and the signal received by the trigger 25 is transmitted through the wire 31. After receiving the signal, the electric cylinder 33 controls the output end to retract, and controls the fixing state of the hatch by controlling the extension and contraction state of the electric cylinder 33. The wire 31 is a weak signal wire. When the trigger 25 is triggered, the trigger 25 inputs a control signal to the wire 31, and the control signal is input into the electric cylinder 33 along the wire 31. The wire 31 is connected to the switching circuit of the electric cylinder 33, and the electric cylinder 33 is powered on and started by the control signal. The electric cylinder 33 is electrically connected to the power generation component 6, and the power provided by the power generation component 6 provides power for the electric cylinder 33.

[0021] The surface of the ball 23 fits with the trigger 25 , which is disposed at the center of the fixed cylinder 21 . The ball 23 contacts the trigger 25 , causing the trigger 25 to emit a control signal.

[0022] When in use, the air pressure inside and outside the cabin 1 will first squeeze the ball 23 to move, and the ball 23 will move to the side with lower air pressure. When the pressure inside and outside the cabin 1 is balanced, the ball 23 will return to the center of the fixed tube 21. At this time, the ball 23 contacts the trigger 25, and a retraction signal is sent to the electric cylinder 33 through the trigger 25 and the wire 31, causing the conical push rod 34 to retract. This can release the fixation of the door panel of the cabin 1, so that the cabin 1 can be opened. The door panel of the cabin 1 is controlled by the ball 23 and the trigger 25 to prevent it from being opened when the pressure inside the cabin 1 is unbalanced due to operational errors. It can effectively prevent the air pressure values of the power generation equipment, power storage equipment and instruments inside the cabin 1 from changing rapidly, and prevent the equipment from being damaged by air pressure changes. Through the closed-loop control logic of mechanical linkage, automatic monitoring of the air pressure difference and cabin door unlocking control are realized, which is equivalent to having a pressure threshold judgment function to avoid manual operation errors.

[0023] Embodiment 2: The technical solution of this embodiment that is different from that of embodiment 1 includes: the air pressure regulating unit 4 includes a cylinder 41, the cylinder 41 is embedded in the outer wall of the cabin 1, a spherical groove 42 is provided on the inner wall of the cylinder 41, a rotating ball 43 is clamped inside the spherical groove 42, a balancing hole 44 is provided at the center of the rotating ball 43, a rotating rod 45 is fixedly connected to the surface of the rotating ball 43, a rotating hole 46 is provided on the outer wall of the cylinder 41, the rotating rod 45 is rotatably connected to the rotating hole 46, and the other end of the rotating rod 45 is fixedly connected to a push rod 47.

[0024] The rotating ball 43 matches the spherical groove 42 , and the balancing hole 44 and the rotating rod 45 are arranged vertically, so that the balancing hole 44 can be completely hidden in the spherical groove 42 when the rotating ball 43 rotates.

[0025] When in use, first push the push rod 47 to drive the rotating rod 45 to rotate, and the rotating rod 45 drives the rotating ball 43 to rotate, and the rotating ball 43 drives the balancing hole 44 to move out of the spherical groove 42, so that the balancing hole 44 connects to the space at both ends of the cylinder 41, so that the inside and outside ends of the cabin 1 are connected, and then the end with higher air pressure inputs air to the other end, so that the air pressure inside the cabin 1 is slowly balanced with the external air pressure, so as to avoid sudden changes in air pressure caused by excessive difference between the internal and external air pressures of the cabin 1.

[0026] Embodiment 3: The technical solution of this embodiment that is different from that of embodiment 2 includes: the sealing unit 5 includes a plurality of sockets 51 opened on the surface of the cabin body 1, an insertion rod 52 is inserted into the inside of the socket 51, a clamping groove 53 is opened on the surface of the insertion rod 52, the other end of the insertion rod 52 is fixedly connected to a cover plate 54, two handles 55 are symmetrically fixedly connected to the side wall of one side of the cover plate 54, and two openings 56 are opened on the outer wall of the cabin body 1.

[0027] The clamping groove 53 matches the tapered push rod 34, and the tapered push rod 34 is inserted into the clamping groove 53. The clamping groove 53 is opened on the end surface of the tapered push rod 34 inserted into the interior of the cabin 1, and the insertion rod 52 is fixed by the tapered push rod 34 inserted into the clamping groove 53.

[0028] When in use, first pull out the tapered push rod 34 from the clamping groove 53 to release the fixation of the insertion rod 52. Then, the cover plate 54 can be pulled away from the opening 56 by the handle 55 to expose the equipment inside the cabin 1.

[0029] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the above-described embodiments. The above-described embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and modifications are intended to fall within the scope of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A cabin for aviation charging, comprising a cabin body (1), a pressure sensing unit (2) for sensing the pressure difference between the inside and outside of the cabin and an execution unit (3) for realizing cabin door control are provided on the side wall of the cabin body (1), an air pressure regulating unit (4) for balancing the pressure inside and outside the cabin is provided on the outer wall of the cabin body (1), a sealing unit (5) for maintaining the sealing of the cabin is provided on the outer wall of the cabin body (1), and a power generation assembly (6) is fixedly connected to the inner wall of the cabin body (1); Its characteristics are: The pressure sensing unit (2) comprises two fixed cylinders (21), the fixed cylinders (21) are embedded in the outer wall of the cabin (1), the inner walls of the fixed cylinders (21) are fixedly sleeved with clamping rings (22) at both ends, the interior of the fixed cylinders (21) is clamped with a ball (23), the outer wall of the fixed cylinders (21) is symmetrically provided with two through holes (24), and the interior of the through holes (24) is embedded with a trigger (25); The execution unit (3) includes a wire (31) fixedly connected to the trigger (25), a plurality of fixed boxes (32) fixedly connected to the inner wall of the cabin (1), an electric cylinder (33) embedded in the interior of the fixed box (32), a tapered push rod (34) fixedly connected to the output end of the electric cylinder (33), and an electrical connection between the electric cylinder (33) and the power generation assembly (6).

2. The aviation charging shelter according to claim 1, characterized in that: The two ends of the wire (31) are respectively connected to the trigger (25) and the electric cylinder (33), and the trigger (25) extends to the interior of the fixed cylinder (21).

3. The aviation charging shelter according to claim 1, characterized in that: The surface of the ball (23) fits in contact with the trigger (25), and the trigger (25) is arranged at the center of the fixed cylinder (21).

4. The aviation charging shelter according to claim 1, characterized in that: The air pressure regulating unit (4) includes a cylinder (41), which is embedded in the outer wall of the cabin (1), and a spherical groove (42) is provided on the inner wall of the cylinder (41). A rotating ball (43) is clamped inside the spherical groove (42), and a balancing hole (44) is provided at the center of the rotating ball (43). A rotating rod (45) is fixedly connected to the surface of the rotating ball (43), and a rotating hole (46) is provided on the outer wall of the cylinder (41). The rotating rod (45) is rotatably connected to the rotating hole (46), and the other end of the rotating rod (45) is fixedly connected to a push rod (47).

5. The aviation charging shelter according to claim 4, characterized in that: The rotating ball (43) matches the spherical groove (42), and the balancing hole (44) and the rotating rod (45) are arranged vertically.

6. The aviation charging shelter according to claim 1, characterized in that: The sealing unit (5) comprises a plurality of jacks (51) provided on the surface of the cabin (1), an insert rod (52) being inserted into the interior of the jacks (51), a clamping groove (53) being provided on the surface of the insert rod (52), the other end of the insert rod (52) being fixedly connected to a cover plate (54), two handles (55) being symmetrically fixedly connected to a side wall of one side of the cover plate (54), and two openings (56) being provided on the outer wall of the cabin (1).

7. The aviation charging shelter according to claim 6, characterized in that: The clamping groove (53) matches the tapered push rod (34), and the tapered push rod (34) is inserted into the clamping groove (53). The clamping groove (53) is formed on an end surface of the tapered push rod (34) inserted into the interior of the cabin (1).

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