Remote control four-axis aircraft

Abstract

The utility model discloses a remote control four-axis aircraft, relates to the technical field of unmanned rotorcrafts, and aims to provide a remote control four-axis aircraft which can play a role in buffering and damping and can prevent the aircraft from being impacted and damaged when the aircraft lands, the technical key point is that the remote control four-axis aircraft comprises an aircraft body, and a battery compartment and an indicator light are arranged on the side surface of the aircraft body; cantilever crane components are arranged at four corners of the fuselage, brushless motors are arranged at the front ends of the cantilever crane components, rotors are arranged on the brushless motors, a damping component is arranged below the fuselage, and a damping component is arranged in the damping component. The device has the technical effects that by arranging the damping component, when the machine body falls, the upper bracket and the lower bracket are influenced by the gravity of the machine body and are rotationally folded, and meanwhile, the coil spring positioned between the upper bracket and the lower bracket can resist and absorb impact by utilizing the elasticity of the coil spring, so that the problem that the machine body is impacted and damaged in the falling process is avoided, and the safety of the device is guaranteed; and the buffering effect is achieved.

Description

TECHNICAL FIELD

[0001] The utility model relates to rotor unmanned plane technical field, concretely is a kind of remote control four-axis aircraft. BACKGROUND

[0002] Four-axis aircraft is a kind of multicopter, it is composed of four rotors, the attitude and flight direction of aircraft are controlled by changing the rotating speed of four rotors, due to its outstanding stability, it is widely concerned in market, commonly used in high-altitude aerial photography, logistics distribution, agricultural plant protection, surveying and mapping, education and scientific research and other fields, when it lands, it is mainly to reduce the speed of rotor to reduce lift, but when aircraft approaches ground, the airflow interference is particularly serious, some adverse conditions make aircraft difficult to stabilize falling, need to keep safe height from ground, close rotor and use gravity to fall directly, but such way is easy to cause aircraft to be impacted greatly, cause internal component to be easily damaged. SUMMARY

[0003] In view of the deficiency of prior art, the utility model provides a remote control four-axis aircraft, which can buffer and shock-absorb when the aircraft lands, and avoid impact damage of the aircraft.

[0004] To achieve the above object, the utility model provides the following technical scheme: a remote control four-axis aircraft, including fuselage, the side of fuselage is equipped with battery compartment and pilot lamp, the four corners of fuselage are equipped with armrest component, the front end of armrest component is equipped with brushless motor, the brushless motor is equipped with rotor, the lower part of fuselage is equipped with damping component, the damping component is equipped with damping component in.

[0005] The damping component includes an upper support arranged below the fuselage, an upper support bracket hingedly connected to the lower part of the upper support, a lower support bracket hingedly connected to the lower part of the upper support bracket, and a lower support arranged below the lower support bracket, and a coil spring connected to the hinged parts of the upper support bracket and the lower support bracket.

[0006] Preferably, the damping component includes a damping assembly arranged below the fuselage, the other end of the damping assembly is connected to the lower support, and the side of the damping assembly is provided with a sensing assembly below the upper support.

[0007] Preferably, the damping assembly includes a fixed plate arranged below the fuselage, the side of the fixed plate is provided with a DC motor, the output end of the DC motor is provided with a winding wheel, the side of the winding wheel is wound with a steel cable, and the other end of the steel cable passes through the sensing assembly and is connected to the lower support.

[0008] Preferably, the sensing assembly includes a pressure sensor arranged below the upper support and electrically connected to the DC motor, a connecting plate is slidingly fitted to the lower part of the pressure sensor, and a pulley is hingedly connected to the connecting plate and abuts against the steel cable.

[0009] Preferably, the lower support is provided with a nylon pad below, which is used for avoiding the abrasion of the lower support.

[0010] Preferably, the arm support component comprises a fixing frame arranged on the fuselage, a pin shaft is hingedly arranged at the front end of the fixing frame, and a connecting arm supporting the brushless motor is arranged on the pin shaft.

[0011] Preferably, a locking component is slidingly arranged on the connecting arm, and a clamping groove connected with the locking component is arranged on the fixing frame.

[0012] Preferably, the locking component comprises a connecting rod sleeved on the connecting arm, push rods are arranged on the two sides of the connecting rod, a clamping plate matched with the clamping groove is arranged at the center of the connecting rod, and springs connected with the connecting arm are arranged on the back surface of the clamping plate.

[0013] Compared with the prior art, the remote control four-axle aircraft has the following beneficial effects:

[0014] 1. The shock absorbing component is composed of the upper support and the lower support which are hingedly arranged, and a coil spring is arranged between the upper support and the lower support, when the fuselage falls, the fuselage moves downward under the influence of gravity, at this time, the upper support and the lower support rotate and fold under the influence of the gravity of the fuselage, and the coil spring between the upper support and the lower support resists and absorbs the impact by using the elasticity of the coil spring, so that the impact on the fuselage gradually decreases to a bearable range, the problem of impact damage of the fuselage during the falling process is avoided, the safety of the equipment is ensured, and the buffering effect is realized.

[0015] 2. The damping assembly and the sensing assembly are arranged, when the upper support and the lower support fold, the distance between the upper support and the lower support becomes smaller, at this time, the steel cable connected with the lower support becomes loose, the sensing assembly matched with the steel cable senses the change, and then the direct current motor is controlled to work, so that the direct current motor winds the steel cable by using the winding wheel, when the impact force of the fuselage is equal to the elastic force of the coil spring, the coil spring gradually resets and pushes the upper support and the lower support to unfold, at this time, the distance between the upper support and the lower support expands, the steel cable is pulled tight, and the steel cable in the winding wheel is released, the winding wheel drives the direct current motor to rotate reversely by using the connection with the direct current motor, the direct current motor limits the slow release of the steel cable by using the electromagnetic resistance, the problem that the coil spring rebounds quickly to cause the fuselage to jump up is prevented, and the damping effect is realized. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is a three-dimensional schematic view of the utility model;

[0017] Figure 2 It is a three-dimensional schematic view of the shock absorbing component of the utility model;

[0018] Figure 3 It is a three-dimensional schematic view of the damping component of the utility model;

[0019] Figure 4 It is the three-dimensional schematic view of the arm support component of the utility model;

[0020] Figure 5 It is the three-dimensional schematic view of the locking component of the utility model.

[0021] In the figure: 1, fuselage; 2, battery compartment; 3, damping component; 301, upper support; 302, upper support; 303, coil spring; 304, lower support; 305, lower support; 4, damping component; 401, damping assembly; 4011, fixed plate; 4012, DC motor; 4013, winding wheel; 4014, steel cable; 402, sensing assembly; 4021, connecting plate; 4022, pressure sensor; 4023, pulley; 5, indicator light; 6, locking component; 601, connecting rod; 602, push rod; 603, clamping plate; 604, spring; 7, arm support component; 701, fixed frame; 702, pin shaft; 703, clamping groove; 704, connecting arm; 8, rotor; 9, brushless motor; 10, nylon pad. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.

[0023] Please refer to Figures 1-5 A remote control four-axis aircraft, including fuselage 1, the side of fuselage 1 is equipped with battery compartment 2 and indicator light 5, the four corners of fuselage 1 are equipped with arm support component 7, the front end of arm support component 7 is equipped with brushless motor 9, brushless motor 9 is equipped with rotor 8, the lower part of fuselage 1 is equipped with damping component 3, damping component 3 is equipped with damping component 4;

[0024] Damping component 3 includes upper support 301 under fuselage 1, upper support 301 is hingedly connected with upper support 302, upper support 302 is hingedly connected with lower support 304, lower support 304 is hingedly connected with lower support 305, the hinge part of upper support 302 and lower support 304 is connected with coil spring 303;

[0025] The utility model discloses a shock absorbing component 3 is provided with, and the shock absorbing component 3 is composed of the upper support 302 and lower support 304 of mutual hinging, and is equipped with the coil spring 303 between the two, when the fuselage 1 falls, is affected by gravity, the fuselage 1 moves down, the upper support 302 and lower support 304 of this time are affected by the gravity of the fuselage 1, and rotate folding, and the coil spring 303 between the two, will utilize the elasticity of itself and resist and absorb impact, make the impact that the fuselage 1 receives gradually drop to the range that can bear, avoid the problem that the fuselage 1 falls in the process and appears impact damage, guarantee the safety of equipment, realize the effect of buffering.

[0026] The damping component 4 includes a damping assembly 401 disposed below the fuselage 1, the other end of the damping assembly 401 is connected with a lower support 305, the side of the damping assembly 401 is provided with a sensing assembly 402 located below an upper support 301, the damping assembly 401 includes a fixed plate 4011 disposed below the fuselage 1, the side of the fixed plate 4011 is provided with a DC motor 4012, the output end of the DC motor 4012 is provided with a winding wheel 4013, the side of the winding wheel 4013 is wound with a steel cable 4014, the other end of the steel cable 4014 passes through the sensing assembly 402 and is connected with the lower support 305;

[0027] By setting the damping assembly 401 and the sensing assembly 402, when the upper support 302 and the lower support 304 are folded, the distance between the upper support 301 and the lower support 305 will become smaller, at this time, the steel cable 4014 connected with the lower support 305 will become loose, and the sensing assembly 402 matched with the steel cable 4014 will sense the change, thereby controlling the DC motor 4012 to work, so that the DC motor 4012 winds the steel cable 4014 by the winding wheel 4013, when the impact force of the fuselage 1 and the elastic force of the coil spring 303 are balanced, the coil spring 303 will gradually reset and push the upper support 302 and the lower support 304 to unfold, at this time, the distance between the upper support 301 and the lower support 305 is expanded, the steel cable 4014 is tightened, and at the same time, the steel cable 4014 in the winding wheel 4013 is released, the winding wheel 4013 drives the reverse rotation by being connected with the DC motor 4012, the DC motor 4012 limits the slow release of the steel cable 4014 by electromagnetic resistance, preventing the fuselage 1 from jumping up due to the rapid rebound of the coil spring 303, realizing the damping effect, and the reverse rotation of the DC motor 4012 can realize the power generation effect.

[0028] The sensing assembly 402 includes a pressure sensor 4022 disposed below the upper support 301 and electrically connected with the DC motor 4012, a connecting plate 4021 is slidingly fitted below the pressure sensor 4022, a pulley 4023 abutting the steel cable 4014 is hinged in the connecting plate 4021;

[0029] Through the setting of the pressure sensor 4022 and the pulley 4023, the pulley 4023 can change the direction of the steel cable 4014 and make the steel cable 4014 slide smoothly, and after the steel cable 4014 changes the direction, the pulley 4023 can transmit the pressure to the pressure sensor 4022 through the connecting plate 4021, so that the pressure sensor 4022 can detect the state of the steel cable 4014, and the purpose of timely feedback is realized.

[0030] The lower support 305 is provided with a nylon pad 10, which is used to avoid wear of the lower support 305;

[0031] By setting the nylon pad 10, the nylon pad 10 has the characteristics of wear resistance and impact resistance, which can avoid the problem of friction damage caused by the direct contact of the lower support 305 with the ground, and the nylon pad 10 is connected with the lower support 305, so that it can be conveniently replaced after being damaged.

[0032] The arm support part 7 includes a fixed frame 701 provided on the fuselage 1, a pin shaft 702 hinged at the front end of the fixed frame 701, and a connecting arm 704 supporting a brushless motor 9 provided on the pin shaft 702;

[0033] By setting the fixed frame 701 and the connecting arm 704, the fixed frame 701 is hinged with the connecting arm 704 through the pin shaft 702, so that the connecting arm 704 can be rotated and folded, which is convenient for the aircraft to be stored and transported when not in use.

[0034] The connecting arm 704 is slidably provided with a locking part 6, and the fixed frame 701 is provided with a clamping groove 703 connected with the locking part 6, the locking part 6 includes a connecting rod 601 sleeved on the connecting arm 704, push rods 602 are arranged on both sides of the connecting rod 601, a clamping plate 603 is arranged at the center of the connecting rod 601 and connected with the clamping groove 703, and springs 604 are arranged on the back surface of the clamping plate 603 and connected with the connecting arm 704;

[0035] By setting the clamping groove 703 and the clamping plate 603, when the connecting arm 704 is unfolded, the clamping plate 603 is inserted into the clamping groove 703 under the pushing of the spring 604, so that the connecting arm 704 is locked with the fixed frame 701, preventing accidental folding of the connecting arm 704 during use, and ensuring the safety and stability of the aircraft during work.

[0036] Working principle: when the fuselage 1 falls, the upper support 302 is extruded through the upper support 301, so that the upper support 302 is folded with the lower support 304, and the coil spring 303 between the two is compressed and wound, so that the fuselage 1 gradually falls, achieving the purpose of absorbing impact force, and the pressure sensor 4022 detects that the steel cable 4014 connected with the lower support 305 is relaxed, and then the steel cable 4014 is wound by the DC motor 4012 and the winding wheel 4013.

[0037] When the impact force of the fuselage 1 is equal to the elastic force of the coil spring 303, the coil spring 303 will gradually drive the upper support 302 and the lower support 304 to unfold, at this time, the steel cable 4014 connected with the lower support 305 will be pulled tight, and the steel cable 4014 will be released by the winding wheel 4013, the winding wheel 4013 drives the direct current motor 4012 to rotate reversely, the direct current motor 4012 utilizes electromagnetic resistance to make the steel cable 4014 be released slowly, realizes the damping effect, prevents the fuselage 1 from being bounced up by the elastic force of the coil spring 303, and meanwhile, the reverse rotation of the direct current motor 4012 can also realize the power generation effect.

[0038] The above are only specific embodiments of the present application, but the technical features of the present application are not limited to this. Any simple change, equivalent replacement or modification made on the basis of the present application to solve the basically same technical problem and realize the basically same technical effect is all covered in the protection scope of the present application.

Claims

1. A remote-controlled quadcopter comprising a fuselage (1), characterized in that: The side of the fuselage (1) is provided with a battery compartment (2) and an indicator light (5), the four corners of the fuselage (1) are provided with an arm support component (7), the front end of the arm support component (7) is provided with a brushless motor (9), the brushless motor (9) is provided with a rotor (8), and the lower side of the fuselage (1) is provided with a damping component (3), and the damping component (3) is provided with a damping component (4). The damping component (3) comprises an upper support (301) arranged below the fuselage (1), an upper support (302) hingedly connected below the upper support (301), a lower support (304) hingedly connected below the upper support (302), and a lower support (305) hingedly connected below the lower support (304). The hinge parts of the upper support (302) and the lower support (304) are connected with a coil spring (303).

2. The remote controlled quadcopter of claim 1, wherein: The damping component (4) comprises a damping assembly (401) arranged below the fuselage (1), the other end of the damping assembly (401) is connected with the lower support (305), and the side of the damping assembly (401) is provided with a sensing assembly (402) below the upper support (301).

3. A remote controlled quadcopter according to claim 2, characterized in that: The damping assembly (401) comprises a fixed plate (4011) arranged below the fuselage (1), the side of the fixed plate (4011) is provided with a DC motor (4012), the output end of the DC motor (4012) is provided with a winding wheel (4013), the side of the winding wheel (4013) is wound with a steel cable (4014), and the other end of the steel cable (4014) passes through the sensing assembly (402) and is connected with the lower support (305).

4. The remote controlled quadcopter of claim 3, wherein: The sensing assembly (402) comprises a pressure sensor (4022) arranged below the upper support (301) and electrically connected with the DC motor (4012), the lower side of the pressure sensor (4022) is slidably connected with a connecting plate (4021), and the connecting plate (4021) is hingedly connected with a pulley (4023) abutting the steel cable (4014).

5. The remote controlled quadcopter of claim 1, wherein: The lower side of the lower support (305) is provided with a nylon pad (10), and the nylon pad (10) is used to avoid abrasion of the lower support (305).

6. The remote controlled quadcopter of claim 1, wherein: The arm support component (7) comprises a fixed frame (701) arranged on the fuselage (1), a pin shaft (702) hingedly connected to the front end of the fixed frame (701), and a connecting arm (704) supporting the brushless motor (9) arranged on the pin shaft (702).

7. The remote controlled quadcopter of claim 6, wherein: The connecting arm (704) is slidably provided with a locking component (6), and the fixed frame (701) is provided with a clamping groove (703) connected with the locking component (6).

8. The remote controlled quadcopter of claim 7, wherein: The locking component (6) comprises a connecting rod (601) sleeved on the connecting arm (704), push rods (602) arranged on both sides of the connecting rod (601), a clamping plate (603) arranged at the center of the connecting rod (601) and matched with the clamping groove (703), and springs (604) arranged on the back of the clamping plate (603) and connected with the connecting arm (704).

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