Helicopter external load gravity center dynamic adjustment balancing structure

Abstract

The utility model relates to a helicopter external load gravity center dynamic adjustment balancing structure which comprises a helicopter mounting plate, a dismounting structure and a balancing assembly, a sliding block at the bottom of a first moving guide rail drives a first empty box to move, and a sliding block at the bottom of a second moving guide rail drives a second empty box to move. Water in the water tank is guided into the first empty box through the first pump body, water in the water tank is guided into the second empty box through the second pump body, the water amount in the first empty box and the water amount in the second empty box are monitored through the corresponding ultrasonic flow meters, and the positions of the first empty box and the positions of the second empty box are adjusted according to use requirements. The weight of the first empty box and the second empty box is adjusted according to use requirements, gravity center dynamic adjusting and balancing work is completed, the flight gravity center is kept stable, safety is improved, the balance weight position is adjusted by using water as an adjusting medium and moving a guide rail, the burden of the whole aircraft body is reduced, production is simple, production cost and maintenance cost are low, practicability is good, and overhaul and replacement are convenient.

Description

Technical Field

[0001] This utility model relates to the field of helicopter technology, and in particular to a dynamic adjustment and trim structure for the external load center of gravity of a helicopter. Background Technology

[0002] As one of the most distinctive creations of 20th-century aviation technology, the helicopter has greatly expanded the application range of aircraft. A typical dual-use product, helicopters can be widely used in transportation, patrol, tourism, rescue, and many other fields. Dynamic adjustment of the helicopter's center of gravity is a key technology for ensuring flight stability. Its core lies in offsetting the torque imbalance caused by the shift in the center of gravity by adjusting the position of external loads or system parameters in real time.

[0003] A search revealed a helicopter transmission mechanism and helicopter with publication number CN220809811U, relating to the technical field of transmission structures. It includes a belt drive assembly connected to the helicopter's power system, comprising a drive pulley; a first drive shaft and a second drive shaft respectively connected to the two ends of the drive pulley, the first and second drive shafts driving in opposite directions under the drive of the drive pulley; and at least two reduction gears respectively connected to the ends of the first and second drive shafts away from the belt drive assembly, each reduction gear including a rotor shaft that drives the helicopter rotor to rotate. This invention achieves torque cancellation on both sides, and by setting a certain distance between the reduction gears on the front and rear sides, it increases the overall center of gravity adjustment range of the helicopter.

[0004] The device in the disclosed patent cannot dynamically adjust the position of the external load to perform balance work according to the usage requirements, which has low practicality. In addition, the device has high production cost, high maintenance cost, and troublesome inspection and replacement. Utility Model Content

[0005] In response to the technical problems in existing patents, such as the inability of the device to dynamically adjust the center of gravity and balance according to usage requirements, resulting in low practicality, high production and maintenance costs, and cumbersome repair and replacement, this utility model provides a dynamic adjustment and balance structure for the center of gravity of helicopter external loads.

[0006] The technical solution adopted in this utility model is: a dynamic adjustment and trim structure for the external load center of gravity of a helicopter, comprising:

[0007] Helicopter mounting plate;

[0008] A disassembly / assembly structure is installed at the bottom of the helicopter mounting plate;

[0009] A balancing component is installed at the bottom of the disassembly structure and is used to dynamically adjust the center of gravity for balancing according to usage requirements.

[0010] The balancing assembly includes a balancing plate installed at the bottom of the disassembly structure, a water tank installed at the bottom middle of the balancing plate, a front balancing structure installed at the front end of the balancing plate, and a rear balancing structure installed at the rear end of the balancing plate.

[0011] Furthermore, the front balancing structure includes a first movable guide rail installed at the bottom of the front end of the balancing plate, a first empty box installed at the bottom of the slider of the first movable guide rail, and a first pump body installed on one side of the first empty box. The two ends of the first pump body are respectively connected to the first empty box through pipes and to the water tank through hoses.

[0012] Furthermore, the rear balancing structure includes a second movable guide rail installed at the bottom of the rear end of the balancing plate, a second empty box installed at the bottom of the slider of the second movable guide rail, and a second pump body installed on one side of the second empty box. The two ends of the second pump body are respectively connected to the second empty box through pipes and to the water tank through hoses.

[0013] Furthermore, both the first empty box and the second empty box are equipped with ultrasonic flow meters.

[0014] Furthermore, the disassembly and assembly structure includes disassembly and assembly components mounted on the top of the mounting plate and a positioning plate fixedly welded to the bottom of the helicopter mounting plate.

[0015] Furthermore, the assembly / disassembly component includes a vertical plate fixedly welded to the top of the mounting plate, a cylinder bolted to one side of the vertical plate, an adjusting plate mounted on the cylinder output shaft, and a positioning pin fixedly welded to one side of the adjusting plate. The positioning plate has positioning holes, and the positioning pin cooperates with the positioning plate.

[0016] The beneficial effects of this utility model are:

[0017] The first empty tank is moved by a slider at the bottom of the first moving guide rail, and the second empty tank is moved by a slider at the bottom of the second moving guide rail. Water from the first water tank is pumped into the first empty tank, and water from the second water tank is pumped into the second empty tank. The water volume in the first and second empty tanks is monitored by corresponding ultrasonic flow meters. The positions and weights of the first and second empty tanks are adjusted according to usage requirements to complete the dynamic adjustment and balancing of the center of gravity, maintain flight center of gravity stability, and improve safety. Using water as an adjustment medium and moving guide rails to adjust the counterweight position reduces the overall load on the aircraft, helps save energy, is simple to produce, has low production and maintenance costs, is practical, and is easy to inspect and replace. Attached Figure Description

[0018] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0019] Figure 2 This is a three-dimensional structural diagram of the present invention viewed from below;

[0020] Figure 3 This is a three-dimensional structural diagram of the disassembly and assembly structure and the helicopter mounting plate in this utility model.

[0021] The diagram is marked as follows:

[0022] 1. Helicopter mounting plate; 2. Disassembly and assembly structure; 201. Disassembly and assembly parts; 202. Positioning plate;

[0023] 3. Balancing assembly; 301. Balancing plate; 302. Water tank; 303. Front balancing structure; 3031. First moving guide rail; 3032. First empty tank; 3033. First pump body; 304. Rear balancing structure; 3041. Second moving guide rail; 3042. Second empty tank; 3043. Second pump body;

[0024] 4. Hose; 5. Vertical plate; 6. Cylinder; 7. Adjusting plate; 8. Positioning post; 9. Positioning hole. Detailed Implementation

[0025] In the description of this utility model, it should be noted that the terms "front", "up", "down", "left", "right", "vertical", "horizontal", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0026] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0027] The following is in conjunction with the appendix Figure 1-3 The present invention will be further described below.

[0028] To address the problems existing in the background art, this application proposes the following technical solution:

[0029] The helicopter external load center of gravity dynamic adjustment trim structure includes: helicopter mounting plate 1, disassembly and assembly structure 2, and trim assembly 3;

[0030] The disassembly / assembly structure 2 is installed at the bottom of the helicopter mounting plate 1;

[0031] The disassembly and assembly structure 2 includes a disassembly and assembly component 201 installed on the top of the mounting plate 301 and a positioning plate 202 fixedly welded to the bottom of the helicopter mounting plate 1.

[0032] The assembly / disassembly component 201 includes a vertical plate 5 fixedly welded to the top of the mounting plate 301, a cylinder 6 bolted to one side of the vertical plate 5, an adjusting plate 7 mounted on the output shaft of the cylinder 6, and a positioning pin 8 fixedly welded to one side of the adjusting plate 7. The positioning plate 202 has a positioning hole 9, and the positioning pin 8 cooperates with the positioning plate 202.

[0033] like Figure 1-3 As shown, the balancing component 3 is installed at the bottom of the disassembly structure 2. The balancing component 3 is used to dynamically adjust the center of gravity for balancing work according to usage requirements.

[0034] The balancing assembly 3 includes a balancing plate 301 installed at the bottom of the disassembly structure 2, a water tank 302 installed at the bottom middle of the balancing plate 301, a front balancing structure 303 installed at the front end of the balancing plate 301, and a rear balancing structure 304 installed at the rear end of the balancing plate 301.

[0035] Furthermore, the front trim structure 303 includes a first movable guide rail 3031 installed at the bottom of the front end of the trim plate 301, a first empty box 3032 installed at the bottom of the slider of the first movable guide rail 3031, and a first pump body 3033 installed on one side of the first empty box 3032. The two ends of the first pump body 3033 are respectively connected to the first empty box 3032 through pipes and connected to the water tank 302 through hoses 4.

[0036] Furthermore, the rear balancing structure 304 includes a second moving guide rail 3041 installed at the bottom of the rear end of the balancing plate 301, a second empty box 3042 installed at the bottom of the slider of the second moving guide rail 3041, and a second pump body 3043 installed on one side of the second empty box 3042. The two ends of the second pump body 3043 are respectively connected to the second empty box 3042 through pipes and connected to the water tank 302 through hoses 4.

[0037] Furthermore, both the first empty box 3032 and the second empty box 3042 are equipped with ultrasonic flow meters.

[0038] Working principle: During use, the cylinder 6 drives the adjusting plate 7 to move, and the adjusting plate 7 drives the positioning column 8 to move, thereby controlling the relative position of the positioning column 8 and the positioning hole 9, and thus controlling the relative position of the helicopter mounting plate 1 and the trim plate 301, which facilitates the maintenance and replacement of the trim assembly 3.

[0039] During the balancing process, the first empty tank 3032 is moved by the slider at the bottom of the first moving guide rail 3031, and the second empty tank 3042 is moved by the slider at the bottom of the second moving guide rail 3041. Water from the water tank 302 is pumped into the first empty tank 3032 by the first pump body 3033, and water from the water tank 302 is pumped into the second empty tank 3042 by the second pump body 3043. The water volume in the first empty tank 3032 and the second empty tank 3042 is monitored by corresponding ultrasonic flow meters. The positions and weights of the first empty tank 3032 and the second empty tank 3042 are adjusted according to usage requirements to complete the dynamic adjustment and balancing of the center of gravity, maintain the stability of the flight center of gravity, improve safety, reduce the overall load on the aircraft by using water as the adjustment medium and the moving guide rails to adjust the position of the counterweight, which helps to save energy. The process is simple to produce, has low production and maintenance costs, is practical, and is easy to inspect and replace.

[0040] All standard parts used in this utility model can be purchased from the market, and irregular parts can be customized according to the description and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts and equipment adopt conventional models in the prior art. In addition, the circuit connection adopts conventional connection methods in the prior art, which will not be described in detail here. The contents not described in detail in this specification belong to the prior art known to those skilled in the art.

[0041] Although embodiments of the present invention have been shown and described, the scope of the present invention will be defined by the appended claims and their equivalents for those skilled in the art.

Claims

1. A dynamic adjustment trim structure for the center of gravity of an external load of a helicopter, characterized in that, The utility model relates to a kind of dynamic adjustment center of gravity of helicopter installation plate (1);Disassembling structure (2) is equipped in the bottom of the helicopter installation plate (1);Trim assembly (3) is equipped in the bottom of the disassembling structure (2), and trim assembly (3) is used for dynamic adjustment center of gravity according to demand and is used for trimming work;The trim assembly (3) includes the trim plate (301) equipped in the bottom of the disassembling structure (2), the water tank (302) equipped in the bottom of the middle end of the trim plate (301), the front trim structure (303) equipped in the front end of the trim plate (301) and the rear trim structure (304) equipped in the rear end of the trim plate (301). The front trim structure (303) includes the first mobile guide rail (3031) equipped in the bottom of the front end of the trim plate (301), the first empty tank (3032) equipped in the bottom of the slider of the first mobile guide rail (3031) and the first pump body (3033) equipped in one side of the first empty tank (3032), and the first pump body (3033) is communicated with the first empty tank (3032) through pipeline and communicated with the water tank (302) through hose (4) respectively at both ends. The rear trim structure (304) includes the second mobile guide rail (3041) equipped in the bottom of the rear end of the trim plate (301), the second empty tank (3042) equipped in the bottom of the slider of the second mobile guide rail (3041) and the second pump body (3043) equipped in one side of the second empty tank (3042), and the second pump body (3043) is communicated with the second empty tank (3042) through pipeline and communicated with the water tank (302) through hose (4) respectively at both ends. The first empty tank (3032) and the second empty tank (3042) are equipped with ultrasonic flowmeter inside. The disassembling structure (2) includes the disassembling piece (201) equipped in the top of the trim plate (301) and the positioning plate (202) fixedly welded in the bottom of the helicopter installation plate (1).

2. The dynamic trim structure for the center of gravity of an external load of a helicopter according to claim 1, characterized in that, The disassembling piece (201) includes the vertical plate (5) fixedly welded in the top of the trim plate (301), the air cylinder (6) installed in one side of the vertical plate (5) through bolt, the adjusting plate (7) equipped on the output shaft of the air cylinder (6) and the positioning column (8) fixedly welded in one side of the adjusting plate (7), and the positioning hole (9) is formed in the positioning plate (202), and the positioning column (8) is matched with the positioning plate (202).

3. The dynamic trim structure for a center of gravity of an external load of a helicopter according to claim 2, characterized by, ​ 4. The dynamic trim structure for a center of gravity of an external load of a helicopter according to claim 3, characterized by ​ 5. The dynamic trim structure for a center of gravity of an external load of a helicopter according to Claim 1, characterized by ​ 6. The dynamic trim structure for a helicopter external load center of gravity according to claim 5, wherein ​

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