Flight structure for remote control aircraft

Abstract

The utility model discloses a flight structure for a remote control aircraft, which comprises a gearbox, a power assembly, an upper paddle and a lower paddle, and the upper paddle and the lower paddle are driven by the power assembly to rotate along opposite directions; an upper balance rod and a lower balance rod are symmetrically arranged at the upper end of the upper paddle and the upper end of the lower paddle respectively, balance iron is symmetrically installed at the two ends of the lower balance rod, and the outer edge of the upper paddle and the outer edge of the lower paddle are each sleeved with a protective ring wrapping the periphery of the upper paddle and the periphery of the lower paddle. According to the utility model, the balance rod is arranged on the paddle and rotates along with the rotation of the paddle, can be similar to a single-degree-of-freedom gyroscope relative to the fuselage, has the fixed axis property and the precession property, plays a certain role in wind resistance, can prevent the instantaneous large-amplitude displacement of the remote control aircraft, and ensures the flight stability; and secondly, the edges of the blades are sleeved with the protection rings, when misoperation occurs, the protection rings make contact with the human body firstly, the fan blades can be prevented from hurting people, and safety is higher.

Description

Technical Field

[0001] The utility model belongs to the technical field of remote-controlled aircraft, in particular to a flying structure used for remote-controlled aircraft. Background Art

[0002] A remote-controlled aircraft is an aircraft that can be controlled from a distance. With the development of technology, remote-controlled aircraft have entered ordinary families, with entertainment as the main purpose; some enthusiasts also modify them to achieve more entertainment (such as aerial photography, load carrying, etc.). Among them, coaxial twin-propeller remote-controlled aircraft have better aerodynamics and lower energy consumption, and are therefore very popular.

[0003] Currently, when remote-controlled aircraft encounter strong winds, updrafts, downdrafts and other severe weather during flight, they are easily pulled and swayed by the air currents, making it difficult for them to control their own stability, and they are prone to deflection or even overturning and crashing. Secondly, the current propeller blades are the main lift components, and their edges are relatively sharp and their own rotation speed is relatively fast. There is a risk of cuts or scratches when in use, and therefore the growing usage needs of users cannot be met. Utility Model Content

[0004] In order to overcome the shortcomings of the prior art, the utility model aims to provide a flying structure for a remote-controlled aircraft.

[0005] The technical solution adopted by the utility model is as follows: a flight structure for a remote-controlled aircraft, comprising a gearbox, a power assembly, an upper blade and a lower blade, wherein the upper blade and the lower blade are driven to rotate in opposite directions by the power assembly; an upper balance rod and a lower balance rod are symmetrically provided at the upper ends of the upper blade and the lower blade, respectively; balance irons are symmetrically installed at both ends of the lower balance rod; and protective rings covering the outer edges of the upper blade and the lower blade are both provided.

[0006] In a preferred embodiment, the outer edges of the upper blade and the lower blade are both protruded to form a positioning pin shaft, and the protective ring is provided with a sleeve adapted to be inserted into the positioning pin shaft.

[0007] In a preferred embodiment, the power assembly includes a motor, an outer transmission shaft, an inner transmission shaft and a gear set transmission-connected to the motor, the gear set is accommodated inside the gearbox, and the gearbox has a motor slot for accommodating the motor.

[0008] In a preferred embodiment, the gear set includes an upper double gear, a lower double gear, a first transmission gear and a second transmission gear. The output end of the motor is connected to the upper double gear. The large gear and the small gear of the upper double gear are respectively meshed with the first transmission gear and the small gear of the lower double gear. The large gear of the lower double gear is meshed with the second transmission gear. The lower double gear is rotatably arranged inside the gearbox through a rotating shaft.

[0009] In a preferred embodiment, the outer transmission shaft is provided with a through hole for the inner transmission shaft to pass through. The first transmission gear and the second transmission gear are respectively installed on the outer transmission shaft and the inner transmission shaft. The bottoms of the outer transmission shaft and the inner transmission shaft are both rotatably arranged inside the gearbox. The upper ends of the outer transmission shaft and the inner transmission shaft are both connected with hollow connectors.

[0010] In a preferred embodiment, both between the upper paddle and the upper balance bar and between the lower paddle and the lower balance bar are connected together by two connecting buckles. Positioning bumps adapted to be buckled with the connecting buckles are provided at both middle ends of the upper balance bar, the upper paddle, the lower paddle and the lower balance bar.

[0011] In a preferred embodiment, the two ends of the connector are provided with limiting bumps. Limiting grooves adapted to allow the limiting bumps to be inserted are formed in the bottom walls of the upper balance bar, the lower balance bar, the lower paddle and the upper paddle. Blade clips are connected to the bottom ends of the lower paddle and the upper paddle for fixing the lower paddle and the upper paddle on the connector.

[0012] In summary, due to the adoption of the above technical solutions, the beneficial effects of the present utility model are as follows:

[0013] 1. In the present utility model, balance bars are provided on the paddles of the remote control aircraft. The balance bars can rotate together with the paddles. It can be similar to a single-degree-of-freedom gyroscope relative to the aircraft, having fixity of axis and precession, playing a certain role in wind resistance. At the same time, balance weights are additionally added on the lower balance bar. The cooperation of the lower balance bar and the balance weights plays an auxiliary balancing role, which can ensure the flight stability of the remote control aircraft, thereby improving the user's operation effect.

[0014] 2. In the present utility model, a protective ring is sleeved on the edge of the paddle. When a misoperation occurs, the protective ring will come into contact with the human body first, which can prevent the paddle from hurting people and is safer. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is a three-dimensional structural diagram of the whole of the present utility model;

[0016] Figure 2 is an exploded three-dimensional structural diagram of the whole of the present utility model;

[0017] Figure 3 This is an exploded three-dimensional structural schematic diagram of the connection part between the lower propeller blade and the lower balance bar in the present utility model;

[0018] Figure 4 This is an exploded three-dimensional structural schematic diagram of the connection part between the motor and the gear set in the present utility model.

[0019] Markings in the figure: 1 - motor, 2 - gearbox, 3 - protective ring, 31 - bushing, 4 - lower propeller blade, 5 - upper propeller blade, 6 - upper balance bar, 7 - connecting buckle, 8 - outer transmission shaft, 9 - inner transmission shaft, 10 - lower balance bar, 11 - propeller blade clamp, 12 - connecting head, 13 - gear set, 131 - upper double gear, 132 - lower double gear, 133 - second transmission gear, 134 - first transmission gear, 14 - balance weight, 15 - positioning bump, 16 - positioning pin shaft. Detailed implementation manners

[0020] In order to make the purpose, technical solutions and advantages of the present utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present utility model and are not used to limit the present utility model.

[0021] A flight structure for a remote control aircraft, referring to Figures 1-4 , includes a gearbox 2, a power assembly, an upper propeller blade 5 and a lower propeller blade 4. The upper propeller blade 5 and the lower propeller blade 4 are driven by the power assembly to rotate in opposite directions; upper balance bars 6 and lower balance bars 10 are symmetrically arranged at the upper ends of the upper propeller blade 5 and the lower propeller blade 4 respectively. By equipping the upper propeller blade 5 and the lower propeller blade 4 with the upper balance bars 6 and the lower balance bars 10 respectively, the balance bar part rotates together with the propeller blade part, which can be similar to a single-degree-of-freedom gyroscope relative to the fuselage, having fixed-axis property and precession property, playing a certain role in wind resistance, preventing large displacements of the unmanned aerial vehicle instantaneously, and ensuring flight stability.

[0022] Among them, balance weights 14 are symmetrically installed at both ends of the lower balance bar 10. By adding the balance weights 14, the overall weight can be additionally increased, which can play an auxiliary balancing role and make the flight more stable.

[0023] Among them, the entire flight mechanism is installed above the fuselage of a remote control aircraft (not shown in the figure) and is electrically connected to the main control board built in the remote control aircraft.

[0024] Furthermore, protective rings 3 covering the outer peripheries of the upper propeller blade 5 and the lower propeller blade 4 are sleeved on the outer edges of the upper propeller blade 5 and the lower propeller blade 4 respectively. By sleeving the protective rings 3 on the edges of the propeller blades, when there is an accidental operation, the protective rings 3 will come into contact with the human body first, which can prevent the propeller blades from hurting people, making it safer. At the same time, when contacting with a collision object, it can also protect the propeller blades.

[0025] Furthermore, the outer edges of the upper blade 5 and the lower blade 4 are both protruding with a positioning pin 16, and the protective ring 3 is provided with a sleeve 31 adapted to be inserted into the positioning pin 16, wherein the protective ring 3 is preferably made of plastic material. When the protective ring 3 is damaged, the sleeve 31 can be directly pulled out from the positioning pin 16 by utilizing the elasticity of the plastic itself, and the protective ring 3 can be replaced.

[0026] Furthermore, the power assembly includes a motor 1, an outer transmission shaft 8, an inner transmission shaft 9 and a gear set 13 connected to the motor 1 in transmission. The gear set 13 is accommodated in the interior of the gearbox 2. The gearbox 2 has a motor slot for accommodating the motor 1. The gear set 13 includes an upper double gear 131, a lower double gear 132, a first transmission gear 134 and a second transmission gear 133. The output end of the motor 1 is connected to the upper double gear 131. The large gear and the small gear of the upper double gear 131 are respectively meshed with the first transmission gear 134 and the small gear of the lower double gear 132. The large gear of the lower double gear 132 is meshed with the second transmission gear 133. The lower double gear 132 is rotated inside the gearbox 2 through a rotating shaft. The outer transmission shaft 8 is penetrated by a through hole that allows the inner transmission shaft 9 to pass through. The first transmission gear 1 34 and the second transmission gear 133 are respectively installed on the outer transmission shaft 8 and the inner transmission shaft 9. The bottoms of the outer transmission shaft 8 and the inner transmission shaft 9 are both rotated inside the gearbox 2. The upper ends of the outer transmission shaft 8 and the inner transmission shaft 9 are connected with a hollow connector 12. When the motor 1 is working, the upper double gear 131 can be driven to rotate. Since the upper double gear 131 is meshed with the lower double gear 132, the lower double gear 132 and the first transmission gear 134 and the second transmission gear 133 respectively meshed with the upper double gear 131 and the lower double gear 132 can be driven to rotate in opposite directions, thereby driving the upper blade 5 and the lower blade 4 installed on the outer transmission shaft 8 and the inner transmission shaft 9 to rotate in opposite directions, so as to provide lift for the gearbox 2 and the remote-controlled aircraft fuselage to meet the flight requirements of the remote-controlled aircraft.

[0027] Of course, it is known that when the horizontal rotation direction of the upper blade 5 is adjusted, the remote-controlled aircraft can also be adjusted to move in another direction accordingly, thereby completing the turning operation.

[0028] Furthermore, limiting protrusions are provided at both ends of the connecting head 12, and limiting grooves adapted to accommodate the limiting protrusions are provided on the bottom walls of the upper balance rod 6, the lower balance rod 10, the lower blade 4 and the upper blade 5. The bottom ends of the lower blade 4 and the upper blade 5 are connected with blade clamps 11 for fixing the lower blade 4 and the upper blade 5 to the connecting head 12, wherein the connecting head 12 can be fixed to the bottom of the lower blade 4 and the upper blade 5 by screws or clamping. The limiting protrusions of the connecting head 12 can also assist in limiting the installation position of the upper balance rod 6 and the lower balance rod 10 to ensure the accuracy of the installation and the stability after subsequent use.

[0029] Further, both between the upper blade 5 and the upper balance bar 6 and between the lower blade 4 and the lower balance bar 10 are connected together by two connecting buckles 7. Positioning convex points 15 adapted to be buckled with the connecting buckles 7 are provided at both middle ends of the upper balance bar 6, the upper blade 5, the lower blade 4 and the lower balance bar 10. Through the connecting buckles 7, the balance bar part and the blade part can be combined into a whole. When the remote control aircraft wants to move in a certain direction, since the balance bar and the blade are connected by a connecting rod, while the blade changes its own rotation direction, the direction of the balance bar will also be changed. While ensuring flight stability, it will not affect the steering operation of the remote control aircraft.

[0030] The above are only the preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A flying structure for a remote-controlled aircraft, characterized in that: It includes a gearbox, a power assembly, an upper blade and a lower blade, wherein the upper blade and the lower blade are driven to rotate in opposite directions by the power assembly; an upper balance rod and a lower balance rod are symmetrically provided at the upper ends of the upper blade and the lower blade, respectively, and balance irons are symmetrically installed at both ends of the lower balance rod; the outer edges of the upper blade and the lower blade are both provided with protective rings covering the periphery of the two.

2. A flying structure for a remote-controlled aircraft as claimed in claim 1, characterized in that: The outer edges of the upper blade and the lower blade are both protruded to form a positioning pin shaft, and the protective ring is provided with a shaft sleeve adapted to be inserted into the positioning pin shaft.

3. A flying structure for a remote-controlled aircraft as claimed in claim 1, characterized in that: The power assembly includes a motor, an outer transmission shaft, an inner transmission shaft and a gear set transmission-connected to the motor. The gear set is accommodated inside the gearbox, and the gearbox has a motor slot for accommodating the motor.

4. A flying structure for a remote-controlled aircraft as claimed in claim 3, characterized in that: The gear set includes an upper double gear, a lower double gear, a first transmission gear and a second transmission gear. The output end of the motor is connected to the upper double gear. The large gear and the small gear of the upper double gear are respectively meshed with the first transmission gear and the small gear of the lower double gear. The large gear of the lower double gear is meshed with the second transmission gear. The lower double gear is rotated inside the gearbox through a rotating shaft.

5. A flying structure for a remote-controlled aircraft as claimed in claim 4, characterized in that: The outer transmission shaft is penetrated by a through hole for the inner transmission shaft to pass through, the first transmission gear and the second transmission gear are respectively mounted on the outer transmission shaft and the inner transmission shaft, the bottoms of the outer transmission shaft and the inner transmission shaft are both rotated inside the gearbox, and the upper ends of the outer transmission shaft and the inner transmission shaft are connected with hollow connectors.

6. A flying structure for a remote-controlled aircraft as claimed in claim 5, characterized in that: The upper blade and the upper balance pole, as well as the lower blade and the lower balance pole, are connected together by two chain buckles, and both ends of the middle of the upper balance pole, the upper blade, the lower blade and the lower balance pole are provided with positioning protrusions that fit and buckle with the chain buckles.

7. A flying structure for a remote-controlled aircraft as claimed in claim 6, characterized in that: Limiting protrusions are provided at both ends of the connecting head, and limiting grooves adapted to meet the requirements of the limiting protrusions are provided on the upper balance rod, the lower balance rod, the lower blade and the bottom wall of the upper blade. The bottom ends of the lower blade and the upper blade are connected with blade clamps for fixing the lower blade and the upper blade on the connecting head.

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