CN210078843U

CN210078843U - Four-axis remote control aircraft

Info

Publication number: CN210078843U
Application number: CN201920891037.6U
Authority: CN
Inventors: 黄伟光
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-06-14
Filing date: 2019-06-14
Publication date: 2020-02-18
Anticipated expiration: 2029-06-14

Abstract

The utility model discloses a four-axis remote control aircraft, including aircraft body and remote controller, the top of aircraft body is provided with the infrared gesture response mechanism that is used for responding to user's gesture signal, and the remote controller includes main control mechanism and vice control mechanism, and main control mechanism includes first wearing mechanism and installs in the main control unit of first wearing mechanism top, and vice control mechanism includes that the second wears the mechanism and installs in the finger button of second wearing mechanism. The utility model relates to a rationally, simple structure, the appearance is pleasing to the eye, fashion, and the remote controller is wearable structure, and is small, easily carries, sets up perception user gesture signal's infrared gesture response mechanism, consequently starts, switches the operational mode or closes the stop operation to the aircraft body, and easy operation has improved user's experience greatly and has felt, and the function is many, can many-sided satisfying consumer's demand, does benefit to extensive popularization.

Description

Four-axis remote control aircraft

Technical Field

The utility model belongs to the technical field of the toy, concretely relates to four-axis remote control aircraft.

Background

At present, general remote control toy can only realize the front and back, up-and-down motion of toy through the remote controller usually, can't be through realizing better interactive, and the remote controller is bulky simultaneously, operates inconveniently.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a four-axis remote control aircraft to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a four-axis remote control aircraft, includes aircraft body and remote controller, its structural feature lies in: an infrared gesture sensing mechanism used for sensing a gesture signal of a user is arranged above the airplane body and comprises an infrared gesture signal transmitter and an infrared gesture signal receiver, wherein the infrared gesture signal transmitter transmits a gesture sensing signal, the infrared gesture signal receiver receives a reflected signal of the gesture of the user, the infrared gesture sensing mechanism feeds the detected gesture signal of the user back to a first control circuit arranged in the airplane body, the first control circuit controls the start, operation mode switching or shutdown stop of the airplane body, the remote controller comprises a main control mechanism and a secondary control mechanism, the main control mechanism comprises a first wearing mechanism and a main controller arranged above the first wearing mechanism, a second control circuit is arranged in the main controller, the secondary control mechanism comprises a second wearing mechanism and finger keys arranged on the second wearing mechanism, the main controller is connected with the finger keys through wires, and the second control circuit controls the finger keys to start, switch the operation mode or stop when the machine is turned off.

Preferably, the aircraft body comprises a main body and four rotor wing mechanisms symmetrically arranged on the periphery of the main body, wherein a power switch is arranged above the main body, and a first battery is arranged in the main body.

Preferably, the rotor mechanism comprises an annular protective frame connected with the main body, fan blades arranged inside the annular protective frame and a positive and negative motor used for driving the fan blades, wherein a first gear is fixed at the bottom of the fan blades, and a second gear meshed with the first gear is arranged at the output end of the positive and negative motor.

Preferably, the bottom of the main body is provided with an infrared transmitting and receiving detection mechanism for detecting obstacles below and around the aircraft body, and the infrared transmitting and receiving detection mechanism comprises an infrared transmitting end and an infrared receiving end.

Preferably, the infrared transmitting and receiving detection mechanism comprises a plurality of infrared transmitting ends and more than one corresponding infrared receiving end, and the infrared transmitting ends point to the lower side and the side of the airplane body.

Preferably, the infrared emission ends are five, one of the infrared emission ends is directed to the right lower side, and the other four infrared emission ends are respectively arranged between two adjacent annular protective frames and are directed to the right side or obliquely lower side of the airplane body.

Preferably, the infrared receiving end is one and is a common infrared receiving end of all the infrared transmitting ends on the lower side of the airplane body.

Preferably, the first wearing mechanism comprises a wrist strap, wherein two ends of the wrist strap are respectively provided with a positioning column and a positioning hole, and an opening is formed in the position of the wrist strap corresponding to the thumb.

Preferably, the main controller is provided with a main control switch and an electric quantity indicating lamp, and the main controller is internally provided with a second battery.

Preferably, the second wearing mechanism is in a belt shape, and two ends of the second wearing mechanism are detachably connected through the primary and secondary pastes.

Compared with the prior art, the utility model relates to a rationally, simple structure, the appearance is pleasing to the eye, fashion, and the remote controller is wearable structure, and is small, easily carries, sets up perception user gesture signal's infrared gesture response mechanism, consequently starts, switches the operational mode or closes the stop operation to the aircraft body, and easy operation has improved user's experience greatly and has felt, and the function is many, can many-sided satisfying consumer's demand, does benefit to extensive popularization.

Drawings

Fig. 1 is a perspective view of the aircraft body of the present invention;

fig. 2 is a schematic view of the internal structure of the aircraft body of the present invention;

fig. 3 is a bottom view of the aircraft body of the present invention;

fig. 4 is a partial structural schematic view of the rotor mechanism of the present invention;

fig. 5 is a perspective view of the controller of the present invention;

fig. 6 is a schematic structural diagram of the main control mechanism of the present invention;

FIG. 7 is a schematic structural view of the auxiliary control mechanism of the present invention;

fig. 8 is a schematic block circuit diagram of the present invention;

in the figure: 1-infrared gesture signal transmitter, 2-infrared gesture signal receiver, 3-main controller, 4-finger button, 5-wire, 6-main body, 7-first battery, 8-annular protective frame, 9-fan blade, 10-positive and negative motor, 11-first gear, 12-second gear, 13-infrared transmitting end, 14-infrared receiving end, 15-wrist strap, 16-positioning column, 17-positioning hole, 18-opening, 19-main control switch, 20-electric quantity indicator light, 21-second wearing mechanism and 22-power switch.

Detailed Description

The invention is further explained with reference to the drawings, without limiting the scope of protection of the invention.

In the description of the present invention, it should be noted that the terms "upper", "lower", "left", "right", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

Referring to fig. 1-8, the utility model provides a technical scheme, a four-axis remote control aircraft, including an aircraft body and a remote controller, the aircraft body is provided with an infrared gesture sensing mechanism for sensing a user gesture signal above, the infrared gesture sensing mechanism includes an infrared gesture signal transmitter 1 and an infrared gesture signal receiver 2, wherein the infrared gesture signal transmitter 1 transmits a gesture sensing signal, the infrared gesture signal receiver 2 receives a reflection signal of a user gesture, and the infrared gesture sensing mechanism feeds back a detected user gesture signal to a first control circuit built in the aircraft body, the first control circuit controls the start, switching operation mode or shutdown stop of the aircraft body, the remote controller includes a main control mechanism and a secondary control mechanism, the main control mechanism includes a first wearing mechanism and a main controller 3 installed above the first wearing mechanism, and a second control circuit is arranged in the main controller 3, the auxiliary control mechanism comprises a second wearing mechanism 21 and a finger key 4 installed on the second wearing mechanism 21, wherein the main controller 3 is connected with the finger key 4 through an electric wire 5, and the second control circuit controls the finger key 4 to start, switch the operation mode or stop when the machine is turned off.

In this embodiment, the aircraft body includes a main body 6 and four rotor mechanisms symmetrically disposed on the periphery of the main body 6, wherein a power switch 22 is disposed above the main body 6, and a first battery 7 is disposed in the main body 6.

In this embodiment, the rotor mechanism includes an annular protective frame 8 connected to the main body 6, a fan blade 9 mounted inside the annular protective frame 8, and a forward and backward motor 10 for driving the fan blade 9, wherein a first gear 11 is fixed at the bottom of the fan blade 9, and a second gear 12 meshed with the first gear 11 is disposed at an output end of the forward and backward motor 10.

In this embodiment, an infrared transmitting/receiving detection mechanism for detecting obstacles below and around the aircraft body is installed at the bottom of the main body 6, and the infrared transmitting/receiving detection mechanism includes an infrared transmitting end 13 and an infrared receiving end 14.

In this embodiment, the infrared transmitting/receiving detection mechanism includes a plurality of infrared transmitting terminals 13 and one or more corresponding infrared receiving terminals 14, and the infrared transmitting terminals 13 point to the lower side and the side of the aircraft body.

In the present embodiment, there are five infrared emission ends 13, one of which is directed directly downward, and the other four of which are respectively disposed between two adjacent annular protection frames 8 and are directed directly or obliquely downward from the aircraft body.

In the present embodiment, the infrared receiving end 14 is a common infrared receiving end 14 of all the infrared emitting ends 13 on the lower side of the aircraft body.

In the present embodiment, the first wearing mechanism includes a wrist strap 15, wherein two ends of the wrist strap 15 are respectively provided with a positioning post 16 and a positioning hole 17, and an opening 18 is provided at a position of the wrist strap 15 corresponding to the thumb.

In this embodiment, the main controller 3 is provided with a main control switch 19 and an electric quantity indicator light 20, and the main controller 19 is provided with a second battery (not shown).

In this embodiment, the second wearing mechanism 21 is in a belt shape, and two ends of the second wearing mechanism 21 are detachably connected through the snap-fit patch.

The working principle is as follows: as shown in fig. 8, the start, the operation mode switching or the shutdown stop of the finger button 4 is controlled by the second control circuit through different pressing modes of the finger button 4, the user sends a gesture signal, the gesture signal of the user is received by the infrared gesture signal receiver 2 and fed back to the first control circuit, the first control circuit can recognize the gesture signal by recognizing the frequency, the duration and the times of the reflected signal, and the first control circuit controls the start, the operation mode switching or the shutdown stop of the aircraft body according to the recognized reflected signal. The infrared transmitting end 13 can detect the flying height of the airplane body and the distance between surrounding obstacles and the airplane body, when the airplane body flies above a certain height in the operation process of the airplane body, the transmitting and receiving detection mechanism cannot detect a reflected signal of the infrared transmitting end 13, and the first control circuit confirms that the flying height of the airplane body exceeds a preset range, so that the lifting force of the airplane body is controlled to fall, and the airplane body descends; when the infrared transmitting and receiving detection mechanism detects the reflected signal of the infrared transmitting end 13, the first control circuit confirms that the aircraft body has descended to the preset height, so as to control the forward and reverse motors 10 to make corresponding actions and lift, and thus the basic cycle is performed so that the aircraft body is maintained within a flight height range which can be controlled by a user. When an obstacle is arranged below or on one side of the airplane body, the infrared transmitting and receiving detection mechanism feeds back obstacle information to the first control circuit, and the first control circuit controls the positive and negative motors 10 to act, so that the airplane body and the obstacle or the ground below the airplane body are maintained within a certain flight height range, and the airplane body avoids moving or rotating towards the other direction far away from the obstacle below the airplane body.

The main control switch 19: starting up the machine by short pressing for the first time; resetting by short pressing for the second time; the short press in flight is slow landing; the long press for 1 second is the scram, and the long press for 3 seconds is the shutdown.

Finger key 4: the first short press takeoff is 1.2 meters; the short press in flight is a rolling function; rapidly pressing three times in flight to enter an infrared obstacle avoidance mode; the long press is a switch to (throttle and steering) function.

The operation mode is as follows: the right thumb passes through the opening 18, the wrist strap is adjusted to the appropriate length, the main control mechanism is fixed on the wrist through the positioning column 16 and the positioning hole 17, the auxiliary control mechanism is sleeved on the index finger through the second wearing mechanism 21, and the finger key 4 is pressed through the thumb to perform control operation.

The airplane body is started by pressing the power switch 22, the flying remote controller is started by pressing the main control switch 19, the airplane body is butted with the remote controller, and the airplane body takes off to 1.2 meters by pressing the finger key 4.

When the airplane body flies, the long press of the finger presses the key 4, when the fist is raised, the airplane body rises, and when the fist is lowered, the airplane body descends; when the airplane body flies, the finger buttons 4 are loosened, the airplane body retreats when the fist is raised, and the airplane body advances when the fist is pressed down; during the aircraft body flight, unclamp finger button 4, the aircraft body flies to the left side when fist left bank, and the aircraft body flies to the right side when fist right bank.

The utility model relates to a rationally, simple structure, the appearance is pleasing to the eye, fashion, and the remote controller is wearable structure, and is small, easily carries, sets up perception user gesture signal's infrared gesture response mechanism, consequently starts, switches the operational mode or closes the stop operation to the aircraft body, and easy operation has improved user's experience greatly and has felt, and the function is many, can many-sided satisfying consumer's demand, does benefit to extensive popularization.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein, and any reference signs in the claims are not intended to be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims

1. The utility model provides a four-axis remote control aircraft, includes aircraft body and remote controller, its characterized in that: the remote controller comprises a main control mechanism and a secondary control mechanism, the main control mechanism comprises a first wearing mechanism and a main controller arranged above the first wearing mechanism, the secondary control mechanism comprises a second wearing mechanism and finger keys arranged on the second wearing mechanism, the main controller is connected with the finger keys through wires, and the second control circuit controls the finger keys to start, switch the operation mode or stop when the machine is turned off.

2. A quadcopter according to claim 1, characterised in that: the aircraft body include main part and symmetry and set up four rotor mechanisms in the main part periphery, wherein the top of main part is equipped with switch, and is equipped with first battery in the main part.

3. A quadcopter according to claim 2, characterised in that: the rotor wing mechanism include the annular that is connected with the main part protect the frame, install at the inside flabellum of annular fender frame and be used for driving the positive and negative motor of flabellum, wherein the bottom of flabellum is fixed with first gear, and positive and negative motor's output be equipped with first gear engagement's second gear.

4. A quadcopter according to claim 1, characterised in that: the bottom of main part install the infrared emission who is used for detecting aircraft body below and barrier on every side and receive detection mechanism, and infrared emission receives detection mechanism and includes infrared emission end and infrared receiving terminal.

5. The quadcopter according to claim 4, characterized in that: the infrared transmitting and receiving detection mechanism comprises a plurality of infrared transmitting ends and more than one corresponding infrared receiving end, and the infrared transmitting ends point to the lower part and the side of the airplane body.

6. A quadcopter according to claim 4 or 5, characterized in that: the infrared emission ends are five, one of the infrared emission ends points to the right lower side, and the other four infrared emission ends are respectively arranged between two adjacent annular protective frames and point to the right side or the oblique lower side of the airplane body.

7. The quadcopter according to claim 4, characterized in that: the infrared receiving end is a common infrared receiving end of all infrared transmitting ends on the lower side of the airplane body.

8. A quadcopter according to claim 1, characterised in that: first wearing mechanism include the wrist strap, wherein the both ends of wrist strap are equipped with reference column and locating hole respectively, and the wrist strap is equipped with the opening with the corresponding position of thumb.

9. A quadcopter according to claim 1, characterised in that: the main control unit on be equipped with master switch and electric quantity pilot lamp, and main control unit inside is equipped with the second battery.

10. A quadcopter according to claim 1, characterised in that: the second wearing mechanism be the banding, and the both ends of second wearing mechanism are passed through primary and secondary and are pasted and can dismantle the connection.