Cabin of a heavy-load helicopter

Abstract

The invention discloses a cabin of a heavy-load helicopter, and relates to the technical field of helicopters. The cabin mechanism comprises a helicopter cabin, wherein one end of the helicopter cabin is connected to a nose, an upper surface of the helicopter cabin is connected to a propeller, both sides of the helicopter cabin are fixedly connected to slide rails, two slide rails are slidably connected to switch doors inside, and two switch doors are fixedly connected to fixing bars on one side away from each other. The cabin of the heavy-load helicopter is provided with a stable center of gravity unit. When uneven cargo is placed on an upper chassis in the helicopter cabin, the center of gravity of the cabin of the heavy-load helicopter is deflected. By self-adjusting its own inclination angle according to the load amount, the center of gravity of the cabin is conveniently adjusted, so that the center of gravity of the cabin is always in the center, and the phenomenon that the flight of the helicopter is unstable due to the deflection of the center of gravity of the cabin is reduced, thereby ensuring the stability of the aircraft during flight.

Description

Technical Field

[0001] The invention relates to the technical field of helicopters, in particular to a cabin of a heavy-load helicopter. Background Art

[0002] Heavy-load helicopters are helicopters designed to carry and transport heavier cargo or personnel than ordinary helicopters. They usually have a larger take-off weight, load capacity and stronger structural design. Heavy-load helicopters can be used for military transport, large cargo transportation, search and rescue, and disaster response missions.

[0003] When a heavy-loaded helicopter transports cargo, the load coefficient of the chassis increases due to the heavier load in the cabin. The uneven distribution of the cargo causes uneven force on the chassis, making it easy for the center of gravity to shift, affecting the normal flight of the helicopter.

[0004] Combining the above problems, we will find that it is difficult to avoid the above problems at the same time when using the existing heavy-load helicopter cabins on the market, and even if they can be solved, they need to be solved with the cooperation of external tools, which makes it impossible to achieve the desired effect. Therefore, we propose a heavy-load helicopter cabin. Summary of the invention

[0005] The object of the present invention is to provide a cabin of a heavy-load helicopter to solve the problems raised in the above background technology.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] The present invention provides a cabin of a heavy-load helicopter, comprising a cabin mechanism, wherein the cabin mechanism comprises a helicopter cabin, one end of the helicopter cabin is connected to a nose, a propeller is arranged on the top of the helicopter cabin, both sides of the helicopter cabin are fixedly connected to slide rails, the interiors of the two slide rails are slidably connected to switch doors, the sides of the two switch doors away from each other are fixedly connected to fixing bars, the sides of the two fixing bars away from each other are fixedly connected to pulling plates, and a stabilizing mechanism is arranged inside the helicopter cabin;

[0008] The stabilizing mechanism comprises a stabilizing center of gravity unit, the stabilizing center of gravity unit is located inside the helicopter cabin, and the stabilizing center of gravity unit is used to adjust the center of gravity of the helicopter cabin;

[0009] The stabilizing mechanism further comprises an adjusting guide unit, which is located around the stabilizing center of gravity unit. The stabilizing center of gravity unit and the adjusting guide unit are used in conjunction with each other, and the adjusting guide unit is used to limit the moving track and shaking amplitude of the adjusting chassis;

[0010] A buffer mechanism is provided inside the stable center of gravity unit. The buffer mechanism is used in conjunction with the stabilizing mechanism and is used to provide buffering between the two chassis.

[0011] Preferably, the stable center of gravity unit comprises a lower chassis, the bottom surface of the lower chassis is fixedly connected to the inner bottom wall of the helicopter cabin, the upper surface of the lower chassis is fixedly connected to a support rod, an upper chassis is arranged on the top of the lower chassis, the bottom surface of the upper chassis is fixedly connected to a hinge ball, the hinge ball is rotatably connected to the inside of the support rod, the bottom surface of the upper chassis is fixedly connected to a plurality of connecting ropes, the bottom ends of the plurality of connecting ropes are fixedly connected to lead balls, and the upper surface of the lower chassis is respectively fixedly connected to four batteries and a PLC controller;

[0012] The PLC controller is electrically connected to one of the batteries, and the upper surface of the lower chassis is respectively fixedly connected with a first electric telescopic rod, a second electric telescopic rod, a third electric telescopic rod and a fourth electric telescopic rod, and the telescopic ends of the first electric telescopic rod, the second electric telescopic rod, the third electric telescopic rod and the fourth electric telescopic rod are all fixedly connected with a push rod, and the top end of each push rod is rotatably hinged with a pressure sensor;

[0013] The first electric telescopic rod, the second electric telescopic rod, the third electric telescopic rod and the fourth electric telescopic rod are electrically connected to four pressure sensors through a PLC controller, respectively; the sensing end of each pressure sensor is fixedly connected to a push plug plate, the upper surface of each push plug plate is provided with a slot, the bottom surface of the upper chassis is fixedly connected to four plug blocks, the first electric telescopic rod, the second electric telescopic rod, the third electric telescopic rod and the fourth electric telescopic rod are electrically connected to the four push plug plates, respectively, and the four batteries are electrically connected to the four plug blocks, respectively.

[0014] Preferably, a water storage cavity is opened inside the upper chassis, a water supply pipe is fixedly connected to the upper surface of the upper chassis, the water supply pipe is connected to the water storage cavity, and a switch valve is fixedly connected to the top end of the water supply pipe.

[0015] Preferably, four supporting legs are fixedly connected to the bottom surface of the helicopter cabin, and a supporting plate is fixedly connected to the bottom end of each supporting leg.

[0016] Preferably, the adjustment guide unit includes an upper limit frame and a lower limit frame that are correspondingly arranged, the outer surfaces of the upper limit frame and the outer surfaces of the lower limit frame are fixedly connected to the inner wall of the helicopter cabin, the bottom surface of the upper limit frame and the upper surface of the lower limit frame are commonly fixedly connected with four first limit blocks, and the side surfaces of the four first limit blocks that are close to each other are each provided with a first limit groove, the front and back surfaces of the upper chassis are fixedly connected with two first guide blocks, and the four first guide blocks are respectively slidably connected to the inside of the four first limit grooves.

[0017] Preferably, the bottom surface of the upper limit frame and the upper surface of the lower limit frame are fixedly connected with four second limit blocks, and the side surfaces of the four second limit blocks close to each other are each provided with a second limit groove, and the two side surfaces of the upper chassis are fixedly connected with two second guide blocks, and the four second guide blocks are respectively slidably connected to the inside of the four second limit grooves.

[0018] Preferably, a limit spring is sleeved on the outer surface of each pushing plug plate, and the bottom ends of the four limit springs are respectively fixedly connected to the upper surface of the first electric telescopic rod, the upper surface of the second electric telescopic rod, the upper surface of the third electric telescopic rod and the upper surface of the fourth electric telescopic rod, and the top end of each limit spring is fixedly connected to the bottom surface of the upper chassis.

[0019] Preferably, the outer surface of each of the limit springs is sleeved with two stabilizing rings, wherein the upper surfaces of four of the stabilizing rings are fixedly connected to the bottom surface of the upper chassis, and the bottom surfaces of the other four stabilizing rings are respectively fixedly connected to the upper surface of the first electric telescopic rod, the upper surface of the second electric telescopic rod, the upper surface of the third electric telescopic rod and the upper surface of the fourth electric telescopic rod.

[0020] Preferably, the buffer mechanism includes a plurality of evenly distributed buffer bases, the bottom surfaces of several of the buffer bases are fixedly connected to the upper surface of the lower chassis, the interiors of several of the buffer bases are slidably connected with buffer rods, the top ends of several of the buffer rods are fixedly connected to the bottom surface of the upper chassis, the bottom ends of several of the buffer rods are fixedly connected with sliding plates, the interiors of several of the buffer bases are provided with hydraulic oil chambers, several of the hydraulic oil chambers are half-filled with buffer hydraulic oil, the inner walls of several of the hydraulic oil chambers are fixedly connected with sleeves, and several of the sliding plates are slidably connected to the interiors of several sleeves, respectively.

[0021] Preferably, the outer surfaces of the plurality of buffer bases are sleeved with compression springs, and the top ends and bottom ends of the plurality of compression springs are fixedly connected to the bottom surface of the upper chassis and the upper surface of the lower chassis respectively.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. The present invention provides a stabilizing center of gravity unit. When uneven cargo is placed on the upper chassis in the helicopter cabin, the center of gravity of the cabin of the heavy-loaded helicopter will be deflected. By self-adjusting its own inclination angle according to the load amount, the center of gravity of the helicopter cabin can be conveniently adjusted, so that the center of gravity of the helicopter cabin is always in the center, reducing the phenomenon of unstable flight of the helicopter due to the deflection of the center of gravity of the helicopter cabin, thereby ensuring the stability of the aircraft during flight.

[0024] 2. The present invention provides an adjustment guide unit. Since the center of gravity of the cabin of the heavy-loaded helicopter is adjusted by utilizing an adjustment mechanism, the upper chassis will move and shake. The movement trajectory and shaking amplitude of the upper chassis can be limited by the limit adjustment guide structure, thereby minimizing the movement amplitude of the load chassis and reducing the impact on the flight of the aircraft, thereby further improving the flight stability of the aircraft.

[0025] 3. The present invention can cooperate with the use of a stabilizing center of gravity unit and an adjusting guide unit by setting a buffer mechanism, utilizes a sliding plate to slide in a sleeve of a hydraulic oil chamber, squeezes the buffered hydraulic oil through the sliding plate, and buffers the impact force applied by the buffer sliding plate to the buffer base, thereby buffering the impact force between the lower chassis and the upper chassis, ensuring a stable connection between the two chassis and minimizing the vibration effect, reducing the instability of the helicopter due to the deviation of the center of gravity of the helicopter cabin, and further ensuring the stability of the aircraft during flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0027] Figure 2 It is a cross-sectional structural schematic diagram of a helicopter cabin of the present invention;

[0028] Figure 3 It is a structural schematic diagram of the opening and closing door of the present invention;

[0029] Figure 4 It is a structural schematic diagram of the upper chassis of the present invention;

[0030] Figure 5 It is a schematic diagram of the cross-sectional structure of the upper chassis of the present invention;

[0031] Figure 6 It is a structural schematic diagram of the battery of the present invention;

[0032] Figure 7 It is a bottom view structural schematic diagram of the upper chassis of the present invention;

[0033] Figure 8 It is a structural schematic diagram of a first electric telescopic rod of the present invention;

[0034] Fig. 9It is a schematic cross-sectional structural diagram of the buffer base of the present invention;

[0035] Fig.10 It is a partial cross-sectional structural schematic diagram of the upper chassis of the present invention.

[0036] In the figure: 1. Cabin mechanism; 11. Helicopter cabin; 12. Propeller; 13. Nose; 14. Support leg; 15. Support plate; 16. Slide rail; 17. Open / close door; 18. Pull plate; 19. Fixing bar; 2. Stabilizing mechanism; 21. Stable center of gravity unit; 2101. Lower chassis; 2102. Support rod; 2103. Upper chassis; 2104. Articulated ball; 2105. Water pipe; 2106. Open / close valve; 2107. Connecting rope; 2108. Lead ball; 2109. Battery; 2110. PLC controller; 2111. First electric telescopic rod; 2112. Push rod; 2113. Pressure sensor; 2114. Push plate; 2115. Slot; 211 6. Insert block; 2117. Water storage chamber; 2118. Second electric telescopic rod; 2119. Third electric telescopic rod; 2120. Fourth electric telescopic rod; 22. Adjustment guide unit; 2201. Upper limit frame; 2202. Lower limit frame; 2203. First limit block; 2204. First limit groove; 2205. Second limit block; 2206. Second limit groove; 2207. First guide block; 2208. Second guide block; 2209. Limit spring; 2210. Stabilizing ring; 3. Buffer mechanism; 301. Compression spring; 302. Buffer base; 303. Buffer rod; 304. Hydraulic oil chamber; 305. Sleeve; 306. Sliding disk; 307. Buffer hydraulic oil. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] Embodiment 1

[0039] like Figure 1-10As shown, an embodiment of the present invention provides a cabin of a heavy-load helicopter, including a cabin mechanism 1, wherein the cabin mechanism 1 includes a helicopter cabin 11, one end of the helicopter cabin 11 is connected to a head 13, a propeller 12 is arranged on the top of the helicopter cabin 11, both sides of the helicopter cabin 11 are fixedly connected to slide rails 16, the insides of the two slide rails 16 are slidably connected to switch doors 17, the sides of the two switch doors 17 away from each other are fixedly connected to fixing bars 19, the sides of the two fixing bars 19 away from each other are fixedly connected to pull plates 18, and the inside of the helicopter cabin 11 is provided with a stabilizing mechanism 2;

[0040] Four support legs 14 are fixedly connected to the bottom surface of the helicopter cabin 11, and two support plates 15 are fixedly connected to the bottom ends of the four support legs 14, respectively. The support structure composed of the four support legs 14 and the support plates 15 can support the helicopter cabin 11 on the horizontal ground, thereby assisting the use of heavy-load helicopters;

[0041] The stabilizing mechanism 2 comprises a stabilizing center of gravity unit 21 . The stabilizing center of gravity unit 21 is located inside the helicopter cabin 11 . The stabilizing center of gravity unit 21 is used to adjust the center of gravity of the helicopter cabin 11 .

[0042] As a further limitation of the stabilizing mechanism 2 of the present invention, the stabilizing center of gravity unit 21 includes a lower chassis 2101, the bottom surface of the lower chassis 2101 is fixedly connected to the inner bottom wall of the helicopter cabin 11, the upper surface of the lower chassis 2101 is fixedly connected to a support rod 2102, an upper chassis 2103 is arranged on the top of the lower chassis 2101, the bottom surface of the upper chassis 2103 is fixedly connected to a hinge ball 2104, the hinge ball 2104 is rotatably connected to the inside of the support rod 2102, the bottom surface of the upper chassis 2103 is fixedly connected to a plurality of connecting ropes 2107, the bottom ends of the plurality of connecting ropes 2107 are fixedly connected to a lead ball 2108, and the upper surface of the lower chassis 2101 is respectively fixedly connected to four batteries 2109 and a PLC controller 2110;

[0043] The PLC controller 2110 is electrically connected to one of the batteries 2109. The upper surface of the lower chassis 2101 is respectively fixedly connected with a first electric telescopic rod 2111, a second electric telescopic rod 2118, a third electric telescopic rod 2119 and a fourth electric telescopic rod 2120. The telescopic ends of the first electric telescopic rod 2111, the second electric telescopic rod 2118, the third electric telescopic rod 2119 and the fourth electric telescopic rod 2120 are all fixedly connected with a top rod 2112. The top of each top rod 2112 is hinged with a pressure sensor 2113. The first electric telescopic rod 2111, the second electric telescopic rod 2118, the third electric telescopic rod 2119 and the fourth electric telescopic rod 2120 are respectively electrically connected to four pressure sensors 2113 through the PLC controller 2110, and they are connected one by one through wires.

[0044] The sensing end of each pressure sensor 2113 is fixedly connected to a push plug plate 2114, and a slot 2115 is provided on the upper surface of each push plug plate 2114. Four plug blocks 2116 are fixedly connected to the bottom surface of the upper chassis 2103. The first electric telescopic rod 2111, the second electric telescopic rod 2118, the third electric telescopic rod 2119 and the fourth electric telescopic rod 2120 are electrically connected to the four push plug plates 2114 respectively; the four storage batteries 2109 are electrically connected to the four plug blocks 2116 respectively;

[0045] By setting the center of gravity stabilizing unit 21, when uneven cargo is placed on the upper chassis 2103 in the helicopter cabin 11, the center of gravity of the cabin of the heavy-load helicopter will be deflected. By being able to self-adjust its own inclination angle according to the load amount on the upper chassis 2103, the center of gravity of the helicopter cabin 11 can be conveniently adjusted, so that the center of gravity of the helicopter cabin 11 is always in the center, reducing the phenomenon of unstable flight of the helicopter due to the deflection of the center of gravity of the helicopter cabin 11, thereby ensuring the stability of the aircraft during flight;

[0046] A water storage chamber 2117 is provided inside the upper chassis 2103, and a water supply pipe 2105 is fixedly connected to the upper surface of the upper chassis 2103. The water supply pipe 2105 is connected to the water storage chamber 2117, and a switch valve 2106 is fixedly connected to the top of the water supply pipe 2105. By manually connecting the external water pipe with the water supply pipe 2105 and opening the switch valve 2106, external water can be conveniently filled into the water storage chamber 2117 provided inside the upper chassis 2103. By tilting the upper chassis 2103, the water in the water storage chamber 2117 can flow to compensate for the weight of the heavy objects on the upper chassis 2103, thereby facilitating the adjustment of the center of gravity of the cabin of the heavy-loaded helicopter.

[0047] The specific implementation of this embodiment is as follows:

[0048] When the helicopter cabin 11 is needed to transport cargo stably, firstly, the four batteries 2109 are fully charged manually, so that the electrical equipment in the stable center of gravity unit 21 can be powered conveniently, and the external water pipe is manually connected to the water supply pipe 2105, and the switch valve 2106 is manually opened to fill the water storage chamber 2117 opened in the upper chassis 2103 with half of water, so as to facilitate the adjustment of the center of gravity of the cabin of the heavy-load helicopter;

[0049] Therefore, the weight counterweight and the center of gravity adjustment method of the cabin of the heavy-load helicopter in the embodiment of the present application are relatively special. Since water is automatically obtained and the flow control is convenient, it is very convenient to use it to adjust the center of gravity.

[0050] Then, the cargo is manually carried to the upper chassis 2103 in the helicopter cabin 11, so that the center of gravity of the cabin of the heavy-load helicopter is shifted. Since the upper chassis 2103 is connected to the lower chassis 2101 fixed to the bottom wall of the helicopter cabin 11 through the support rod 2102 and the hinge ball 2104, it is convenient to rotate in the support rod 2102 through the hinge ball 2104, so that the upper chassis 2103 is slightly tilted; the plug block 2116 fixed to the lower side of the upper chassis 2103 is stuck in the slot 2115 opened on the push plug plate 2114, so that the first electric telescopic rod 2111, the second electric telescopic rod 2118, and the third electric telescopic rod 2119 at this position can be pushed. The telescopic rod 2119 or the fourth electric telescopic rod 2120 is connected to the battery 2109 and energized, which causes the pressure sensor 2113 fixed under the inclined side push plug plate 2114 to display a value, and the program set by the PLC controller 2110 for the four electric telescopic rods can cause one of the first electric telescopic rod 2111, the second electric telescopic rod 2118, the third electric telescopic rod 2119 or the fourth electric telescopic rod 2120 corresponding to the pressure sensor 2113 displaying the value to start moving, thereby using the electric telescopic rod to push the downwardly inclined side of the upper chassis 2103 to rise, and push the upper chassis 2103 to rise to its horizontal position;

[0051] Since the four pushing plug plates 2114 do not contact the bottom surface of the upper chassis 2103 when the upper chassis 2103 is in a horizontal state, the electric telescopic rod continues to be used to push the corresponding position of the upper chassis 2103 up until the other electric telescopic rods display values, and due to the inclination of the upper chassis 2103, the water in the water storage chamber 2117 will flow to the inclined lower side of the upper chassis 2103, and the lead ball 2108 connected to the connecting rope 2107 will also move to the inclined lower side of the upper chassis 2103, so as to better compensate for the position with light gravity. At this time, the four electric telescopic rods are controlled by the PLC controller 2110 to act simultaneously; the pushing plug plates 2114 are pushed to contact the upper chassis 2103 by the four electric telescopic rods, and the values ​​of the pressure sensors 2113 arranged on the four electric telescopic rods can be made equal by utilizing the extension and retraction of the four electric telescopic rods. Since the four electric telescopic rods are evenly arranged at the bottom of the helicopter cabin 11, the center of gravity of the upper chassis 2103 and the heavy objects on its upper surface are completely centered; combined with Figure 5 and Fig.10 A partition is provided in the water storage chamber 2117, and a plurality of grids are provided in the partition. When the upper chassis 2103 is tilted, the partition will move due to gravity, and the water in the water storage chamber 2117 will be located in the grids of the partition, making the water body more stable, thereby reducing the shaking of the water body inside the water storage chamber 2117; at this time, the center of gravity of the helicopter cabin 11 also tends to the center position, reducing the phenomenon of unstable flight of the helicopter due to the deviation of the center of gravity of the helicopter cabin 11, thereby ensuring the stability of the aircraft during flight.

[0052] The above technical solution describes a system for stabilizing the center of gravity when transporting cargo by helicopter, and its technical effects can be summarized as follows: by manually moving cargo in the helicopter cabin, the center of gravity in the helicopter cabin can be easily adjusted to accommodate cargo of different weights and volumes. And by filling the water storage chamber 2117 with water to adjust the center of gravity, a simple and effective method is provided to change the weight distribution of the helicopter.

[0053] At the same time, the center of gravity is adjusted by using an electric telescopic rod system: four electric telescopic rods are fixed between the upper chassis 2103 and the lower chassis 2101 and connected to the battery 2109, and the upper chassis can be lifted and tilted by electric control to adjust the center of gravity. Tilt compensation mechanism: when the upper chassis 2103 tilts, the water in the water storage chamber 2117 and the lead ball 2108 of the connecting rope 2107 will move to the lower side of the tilt, automatically compensating for the gravity change caused by the center of gravity shift.

[0054] The pressure between the push plate 2114 and the upper chassis 2103 is monitored by the pressure sensor 2113. The PLC controller 2110 accurately controls the movement of the four electric telescopic rods according to the value of the pressure sensor 2113 until the values ​​of the four pressure sensors 2113 tend to be equal, ensuring that the center of gravity of the upper chassis 2103 and the heavy objects on its surface are adjusted to the center position.

[0055] In summary, this technical solution can stabilize the center of gravity of the helicopter cabin at the center position through a series of methods combining automation and manual operation, reducing the flight instability caused by the center of gravity offset. The entire center of gravity adjustment process can be achieved through manual operation and automated control systems, simplifying the operation process. The above technical solution can effectively solve the center of gravity stability problem during helicopter transportation, and improve transportation efficiency and flight safety.

[0056] Embodiment 2

[0057] like Figure 1-6 As shown, the present invention provides a technical solution: a cabin of a heavy-load helicopter. The present invention makes corresponding improvements to the technical problems mentioned in the background technology.

[0058] As a further limitation of the stabilizing mechanism 2 of the present invention, the stabilizing mechanism 2 further includes an adjusting guide unit 22, which is located around the stabilizing center of gravity unit 21, and the stabilizing center of gravity unit 21 is used in conjunction with the adjusting guide unit 22, and the adjusting guide unit 22 is used to limit the movement and shaking of the upper chassis 2103;

[0059] The adjusting guide unit 22 comprises an upper limit frame 2201 and a lower limit frame 2202 which are respectively arranged. The outer surfaces of the upper limit frame 2201 and the lower limit frame 2202 are fixedly connected to the inner wall of the helicopter cabin 11. The bottom surface of the upper limit frame 2201 and the upper surface of the lower limit frame 2202 are fixedly connected with four first limit blocks 2203. The side surfaces of the four first limit blocks 2203 which are close to each other are all provided with first limit grooves 2204. The front and back surfaces of the upper chassis 2103 are fixedly connected with two first guide blocks 2207. The four first guide blocks 2207 are respectively slidably connected to the insides of the four first limit grooves 2204.

[0060] By setting the adjustment guide unit 22, the upper chassis 2103 can adjust its own tilt angle according to the load amount on the upper chassis 2103, and the center of gravity of the cabin of the heavy-load helicopter can be adjusted, which will cause the upper chassis 2103 to move and shake. The movement trajectory and shaking amplitude of the upper chassis 2103 can be limited by the limit adjustment guide structure, so as to minimize the movement amplitude of the upper chassis 2103 and reduce the impact on the flight of the aircraft, thereby further improving the flight stability of the aircraft.

[0061] like Figure 4-8 As shown, the bottom surface of the upper limit frame 2201 and the upper surface of the lower limit frame 2202 are fixedly connected with four second limit blocks 2205, and the side surfaces of the four second limit blocks 2205 close to each other are all provided with second limit grooves 2206, and the two side surfaces of the upper chassis 2103 are fixedly connected with two second guide blocks 2208, and the four second guide blocks 2208 are respectively slidably connected to the inside of the four second limit grooves 2206. By using the second guide blocks 2208 to slide in the second limit grooves 2206 opened on one side of the second limit blocks 2205, the movement trajectory and shaking amplitude of the upper chassis 2103 can be further limited, thereby further improving the flight stability of the aircraft;

[0062] The outer surface of each push plug plate 2114 is sleeved with a limit spring 2209, and the bottom ends of the four limit springs 2209 are respectively fixedly connected to the upper surface of the first electric telescopic rod 2111, the upper surface of the second electric telescopic rod 2118, the upper surface of the third electric telescopic rod 2119 and the upper surface of the fourth electric telescopic rod 2120, and the top end of each limit spring 2209 is fixedly connected to the bottom surface of the upper chassis 2103; by arranging the limit springs 2209 between the first electric telescopic rod 2111, the second electric telescopic rod 2118, the third electric telescopic rod 2119 and the fourth electric telescopic rod 2120 and the upper chassis 2103, the elastic force inside the limit springs 2209 can be used to prevent the push plug plate 2114 from contacting the bottom surface of the upper chassis 2103, and by adjusting the guiding effect of the guide unit 22, it is convenient to use the stable center of gravity unit 21 to adjust the center of gravity of the cabin of the heavy-load helicopter;

[0063] like Figure 8-10 As shown, the outer surface of each limit spring 2209 is sleeved with two stabilizing rings 2210, wherein the upper surfaces of four stabilizing rings 2210 are fixedly connected to the bottom surface of the upper chassis 2103, and the bottom surfaces of the other four stabilizing rings 2210 are respectively fixedly connected to the upper surface of the first electric telescopic rod 2111, the upper surface of the second electric telescopic rod 2118, the upper surface of the third electric telescopic rod 2119, and the upper surface of the fourth electric telescopic rod 2120;

[0064] Analysis of the above structural design shows that: through the two stabilizing rings 2210 sleeved on the outer surface of the limit spring 2209, since the top of the limit spring 2209 is connected to the upper chassis 2103, the bottom of the limit spring 2209 is fixed to the upper surface of the first electric telescopic rod 2111, the upper surface of the second electric telescopic rod 2118, the upper surface of the third electric telescopic rod 2119, or the upper surface of the fourth electric telescopic rod 2120. The two stabilizing rings 2210 are respectively fixed to the upper chassis 2103 and the upper surface of the first electric telescopic rod 2111, the upper surface of the second electric telescopic rod 2118, the upper surface of the third electric telescopic rod 2119, or the upper surface of the fourth electric telescopic rod 2120, so that they can be stably sleeved on the outer surface of the limit spring 2209. The limit spring 2209 is extended and retracted along the telescopic end of the first electric telescopic rod 2111, the telescopic end of the second electric telescopic rod 2118, the telescopic end of the third electric telescopic rod 2119 or the telescopic end of the fourth electric telescopic rod 2120. In this way, the limit spring 2209 is stably contracted by the stabilizing ring 2210, so that the limit spring 2209 is stably arranged between the first electric telescopic rod 2111, the second electric telescopic rod 2118, the third electric telescopic rod 2119 and the fourth electric telescopic rod 2120 and the upper chassis 2103, thereby improving the telescopic stability of the limit spring 2209.

[0065] The specific implementation of this embodiment is as follows: when the center of gravity of the helicopter cabin 11 is adjusted, the upper chassis 2103 can be easily moved and tilted by rotating the hinge ball 2104 in the support rod 2102, and when the upper chassis 2103 moves and tilts, the first guide block 2207 and the second guide block 2208 on both sides of the upper chassis 2103 slide in the first limit groove 2204 on one side of the first limit block 2203 and the second limit groove 2206 on one side of the second limit block 2205, respectively, to improve the movement and tilt stability of the upper chassis 2103, and the upper chassis 2103 surface and the bottom surface of the upper chassis 2103 are arranged The upper limit frame 2201 and the lower limit frame 2202 can limit the up and down inclination of the upper chassis 2103 to avoid the problem that the cargo on the surface of the upper chassis 2103 moves and dumps due to the inclination angle being too large; at the same time, the limit springs 2209 fixed on the four electric telescopic rods can guide the movement of the push plate 2114, thereby facilitating the control of the adjustment of the cabin center of gravity of the heavy-loaded helicopter using the stable center of gravity unit 21, and the movement trajectory and shaking amplitude of the upper chassis 2103 can be limited through the limit adjustment guide structure, the movement amplitude of the load chassis is minimized, and the impact on the flight of the aircraft is reduced, thereby further improving the flight stability of the aircraft.

[0066] Embodiment 3

[0067] like Figure 1-10As shown, the present invention provides a technical solution: a cabin of a heavy-load helicopter. The present invention makes corresponding improvements to the technical problems mentioned in the background technology.

[0068] As a further limitation of the stabilizing mechanism 2 of the present invention, a buffer mechanism 3 is provided inside the stabilizing center of gravity unit 21. The buffer mechanism 3 is used in conjunction with the stabilizing mechanism 2. The buffer mechanism 3 is used to buffer between the lower chassis 2101 and the upper chassis 2103.

[0069] The buffer mechanism 3 includes a plurality of evenly distributed buffer bases 302, the bottom surfaces of the plurality of buffer bases 302 are fixedly connected to the upper surface of the lower chassis 2101, the interiors of the plurality of buffer bases 302 are slidably connected with buffer rods 303, the top ends of the plurality of buffer rods 303 are fixedly connected to the bottom surface of the upper chassis 2103, the bottom ends of the plurality of buffer rods 303 are fixedly connected with sliding plates 306, the interiors of the plurality of buffer bases 302 are provided with hydraulic oil chambers 304, the plurality of hydraulic oil chambers 304 are half-filled with buffer hydraulic oil 307, the inner walls of the plurality of hydraulic oil chambers 304 are fixedly connected with sleeves 305, and the plurality of sliding plates 306 are slidably connected to the interiors of the plurality of sleeves 305, respectively.

[0070] By setting the buffer mechanism 3, it is possible to cooperate with the use of the stabilizing center of gravity unit 21 and the adjusting guide unit 22, and utilize the sliding plate 306 to slide in the sleeve 305 of the hydraulic oil chamber 304, and squeeze the buffer hydraulic oil 307 through the sliding plate 306, and the buffer sliding plate 306 slides in the buffer base 302, so as to buffer the impact force between the lower chassis 2101 and the upper chassis 2103, ensure the stable connection between the two chassis and reduce the vibration effect to a minimum, reduce the instability of the helicopter due to the deviation of the center of gravity of the helicopter cabin 11, and further ensure the stability of the aircraft during flight; the above-mentioned buffer mechanism 3 has There are various forms of shock absorbing modules. Since the lower chassis 2101 and the upper chassis 2103 are softly connected by the rotation of the hinge ball 2104 in the support rod 2102, the upper chassis 2103 can rotate spherically along the hinge ball 2104 in the support rod 2102. By utilizing the buffer mechanism 3 fixed between the lower chassis 2101 and the upper chassis 2103, a buffer can be formed between the lower chassis 2101 and the upper chassis 2103 through hydraulic buffering and spring buffering, so that the inclination angle of the upper chassis 2103 can be stably adjusted, the center of gravity of the aircraft can be stably adjusted, and the flight stability of the aircraft can be enhanced.

[0071] The outer surfaces of several buffer bases 302 are all sleeved with compression springs 301, and the top and bottom ends of several compression springs 301 are respectively fixedly connected to the bottom surface of the upper chassis 2103 and the upper surface of the lower chassis 2101. By utilizing the compression springs 301 fixed between the upper chassis 2103 and the lower chassis 2101, in cooperation with the buffer structure of the buffer mechanism 3, the buffering effect of the buffer mechanism 3 can be improved.

[0072] The specific implementation of this embodiment is as follows:

[0073] While the center of gravity of the helicopter cabin 11 is adjusted, the upper chassis 2103 and the lower chassis 2101 are connected together only by the hinge ball 2104 and the support rod 2102, which will make the connection between the upper chassis 2103 and the lower chassis 2101 unstable. By fixing the compression spring 301 between the upper chassis 2103 and the lower chassis 2101, the cooperation between the buffer base 302 and the buffer rod 303 can buffer the impact force between the upper chassis 2103 and the lower chassis 2101; the buffer rod 303 is used to slide with the sliding plate 306 in the sleeve 305 fixed in the buffer base 302; since the sleeve 305 is fixed to the inner wall of the hydraulic oil chamber 304 opened in the buffer base 302, and the hydraulic oil chamber 304 is half filled with buffer hydraulic oil 307, the buffer hydraulic oil 307 in the hydraulic oil chamber 304 can be squeezed by the sliding plate 306, so that the buffer hydraulic oil 307 flows along the sleeve 305 in the hydraulic oil chamber 304. At the same time, the surface tension of the buffer hydraulic oil 307 can be used to buffer the impact force of the sliding plate 306, thereby buffering the impact force between the upper chassis 2103 and the lower chassis 2101, thereby ensuring a stable connection between the two chassis and reducing the vibration effect to a minimum;

[0074] Therefore, the mechanical action of the buffering performed by the components of the above-mentioned buffer rod 303, sliding plate 306, buffer base 302, sleeve 305 and other structures can further reduce the instability of the helicopter due to the deviation of the center of gravity of the helicopter cabin 11, and further ensure the stability of the aircraft during flight.

[0075] In summary, the cabin of the heavy-load helicopter provided by the present invention ensures a stable connection between the two chassis and minimizes the vibration effect, reduces the instability of the helicopter due to the deviation of the center of gravity of the helicopter cabin, further ensures the stability of the aircraft during flight, and is particularly suitable for use in conjunction with heavy-load aircraft models.

[0076] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0077] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A cabin of a heavy-load helicopter, comprising a cabin structure (1), characterized in that: The cabin mechanism (1) comprises a helicopter cabin (11), one end of the helicopter cabin (11) is connected to a head (13), a propeller (12) is arranged on the top of the helicopter cabin (11), both sides of the helicopter cabin (11) are fixedly connected to slide rails (16), the insides of the two slide rails (16) are slidably connected to switch doors (17), the sides of the two switch doors (17) away from each other are fixedly connected to fixing strips (19), the sides of the two fixing strips (19) away from each other are fixedly connected to pull plates (18), and the inside of the helicopter cabin (11) is provided with a stabilizing mechanism (2); The stabilizing mechanism (2) comprises a stabilizing center of gravity unit (21), the stabilizing center of gravity unit (21) being located inside the helicopter cabin (11), and the stabilizing center of gravity unit (21) being used to adjust the center of gravity of the helicopter cabin (11); The stabilizing mechanism (2) further comprises an adjusting guide unit (22), wherein the adjusting guide unit (22) is located around the stabilizing center of gravity unit (21), the stabilizing center of gravity unit (21) and the adjusting guide unit (22) are used in conjunction with each other, and the adjusting guide unit (22) is used to limit the movement trajectory and shaking amplitude of the adjusting chassis; A buffer mechanism (3) is provided inside the stable gravity center unit (21), and the buffer mechanism (3) is used in conjunction with the stable mechanism (2), and the buffer mechanism (3) is used to buffer between the two chassis; The stable center of gravity unit (21) comprises a lower chassis (2101), the bottom surface of the lower chassis (2101) is fixedly connected to the inner bottom wall of the helicopter cabin (11), the upper surface of the lower chassis (2101) is fixedly connected to a support rod (2102), an upper chassis (2103) is arranged on the top of the lower chassis (2101), the bottom surface of the upper chassis (2103) is fixedly connected to a hinge ball (2104), and the hinge ball (2104) is rotatably connected to the inside of the support rod (2102); The bottom surface of the upper chassis (2103) is fixedly connected to a plurality of connection ropes (2107), the bottom ends of the plurality of connection ropes (2107) are fixedly connected to lead balls (2108), and the upper surface of the lower chassis (2101) is respectively fixedly connected to four storage batteries (2109) and a PLC controller (2110); The PLC controller (2110) is electrically connected to one of the batteries (2109); the upper surface of the lower chassis (2101) is respectively fixedly connected with a first electric telescopic rod (2111), a second electric telescopic rod (2118), a third electric telescopic rod (2119) and a fourth electric telescopic rod (2120); the telescopic ends of the first electric telescopic rod (2111), the second electric telescopic rod (2118), the third electric telescopic rod (2119) and the fourth electric telescopic rod (2120) are all fixedly connected with a push rod (2112); the top end of each push rod (2112) is rotatably hinged with a pressure sensor (2113); the first electric telescopic rod (2111), the second electric telescopic rod (2118), the third electric telescopic rod (2119) and the fourth electric telescopic rod (2120) are respectively electrically connected to the four pressure sensors (2113) through the PLC controller (2110); The sensing end of each of the pressure sensors (2113) is fixedly connected to a push plug plate (2114), the upper surface of each of the push plug plates (2114) is provided with a slot (2115), the bottom surface of the upper chassis (2103) is fixedly connected to four plug blocks (2116), the first electric telescopic rod (2111), the second electric telescopic rod (2118), the third electric telescopic rod (2119) and the fourth electric telescopic rod (2120) are electrically connected to the four push plug plates (2114) respectively, and the four storage batteries (2109) are electrically connected to the four plug blocks (2116) respectively; A water storage chamber (2117) is provided inside the upper chassis (2103), a water supply pipe (2105) is fixedly connected to the upper surface of the upper chassis (2103), the water supply pipe (2105) is connected to the water storage chamber (2117), and a switch valve (2106) is fixedly connected to the top of the water supply pipe (2105).

2. The cabin of a heavy-load helicopter according to claim 1, characterized in that: Four support legs (14) are fixedly connected to the bottom surface of the helicopter cabin (11), and a support plate (15) is fixedly connected to the bottom end of each support leg (14).

3. The cabin of a heavy-load helicopter according to claim 1, characterized in that: The adjustment guide unit (22) comprises an upper limit frame (2201) and a lower limit frame (2202) which are arranged correspondingly, and the outer surface of the upper limit frame (2201) and the outer surface of the lower limit frame (2202) are both fixedly connected to the inner wall of the helicopter cabin (11); The bottom surface of the upper limit frame (2201) and the upper surface of the lower limit frame (2202) are fixedly connected with four first limit blocks (2203), and the side surfaces of the four first limit blocks (2203) close to each other are each provided with a first limit groove (2204). The front and back surfaces of the upper chassis (2103) are fixedly connected with two first guide blocks (2207), and the four first guide blocks (2207) are respectively slidably connected to the inside of the four first limit grooves (2204).

4. The cabin of a heavy-load helicopter according to claim 3, characterized in that: The bottom surface of the upper limit frame (2201) and the upper surface of the lower limit frame (2202) are fixedly connected with four second limit blocks (2205), and the side surfaces of the four second limit blocks (2205) close to each other are each provided with a second limit groove (2206). The two side surfaces of the upper chassis (2103) are fixedly connected with two second guide blocks (2208), and the four second guide blocks (2208) are respectively slidably connected to the inside of the four second limit grooves (2206).

5. The cabin of a heavy-load helicopter according to claim 1, characterized in that: The outer surface of each pushing plug plate (2114) is sleeved with a limit spring (2209), and the bottom ends of the four limit springs (2209) are respectively fixedly connected to the upper surface of the first electric telescopic rod (2111), the upper surface of the second electric telescopic rod (2118), the upper surface of the third electric telescopic rod (2119) and the upper surface of the fourth electric telescopic rod (2120), and the top end of each limit spring (2209) is fixedly connected to the bottom surface of the upper chassis (2103).

6. The cabin of a heavy-load helicopter according to claim 5, characterized in that: The outer surface of each limit spring (2209) is sleeved with two stabilizing rings (2210), wherein the upper surfaces of four of the stabilizing rings (2210) are fixedly connected to the bottom surface of the upper chassis (2103), and the bottom surfaces of the other four stabilizing rings (2210) are respectively fixedly connected to the upper surface of the first electric telescopic rod (2111), the upper surface of the second electric telescopic rod (2118), the upper surface of the third electric telescopic rod (2119), and the upper surface of the fourth electric telescopic rod (2120).

7. The cabin of a heavy-load helicopter according to claim 1, characterized in that: The buffer mechanism (3) comprises a plurality of evenly distributed buffer bases (302), and the bottom surfaces of the plurality of buffer bases (302) are fixedly connected to the upper surface of the lower chassis (2101); A plurality of the buffer bases (302) are slidably connected to buffer rods (303) inside, and the top ends of the plurality of the buffer rods (303) are fixedly connected to the bottom surface of the upper chassis (2103); the bottom ends of the plurality of the buffer rods (303) are fixedly connected to sliding plates (306); and a plurality of the buffer bases (302) are provided with hydraulic oil chambers (304) inside. The plurality of hydraulic oil chambers (304) are half-filled with buffer hydraulic oil (307), the inner walls of the plurality of hydraulic oil chambers (304) are fixedly connected with sleeves (305), and the plurality of sliding plates (306) are respectively slidably connected to the interiors of the plurality of sleeves (305).

8. The cabin of a heavy-load helicopter according to claim 7, characterized in that: The outer surfaces of the plurality of buffer bases (302) are sleeved with compression springs (301), and the top and bottom ends of the plurality of compression springs (301) are fixedly connected to the bottom surface of the upper chassis (2103) and the upper surface of the lower chassis (2101), respectively.

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