CN210138450U

CN210138450U - Light aircraft

Info

Publication number: CN210138450U
Application number: CN201920368750.2U
Authority: CN
Inventors: 李兴文
Original assignee: SHANGHAI BENXING ELECTRONIC TECHNOLOGY Co Ltd
Current assignee: SHANGHAI BENXING ELECTRONIC TECHNOLOGY Co Ltd
Priority date: 2018-03-27
Filing date: 2019-03-22
Publication date: 2020-03-13
Anticipated expiration: 2029-03-22

Abstract

The utility model relates to a flying toy. A light aircraft comprises an aircraft shell, wherein a driving control system for driving propellers to rotate and controlling the rotation direction of the propellers is arranged in the shell, the driving control system is connected with the propellers, and the number of the propellers is three, namely a first propeller, a second propeller and a third propeller; the first propeller and the second propeller are symmetrically fixed on the left side and the right side of the shell, and rotating shafts of the first propeller and the second propeller are positioned in the horizontal direction; the third screw propeller is fixed below the shell, and a rotating shaft of the third screw propeller is positioned in the vertical direction. This patent is through the optimization to screw position and screw pivot direction, allows to provide the power that rises, descends through the third screw that is located the below, allows to provide the power that needs of rotation, march, retreat etc. through controlling the direction of rotation that is located the first screw of shell left side and is located the second screw on shell right side.

Description

Light aircraft

Technical Field

The utility model relates to a toy field, concretely relates to flight toy.

Background

An existing aircraft is provided with at least four propellers at four corners of the aircraft respectively, so that the four propellers drive the aircraft to fly up and down and change the flight direction, for example, an unmanned aerial vehicle of the Xinjiang company.

The design of four propellers is not beneficial to reducing the weight of the aircraft.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a light aircraft solves above technical problem.

The utility model provides a technical problem can adopt following technical scheme to realize:

a light aircraft comprises an aircraft shell, wherein a driving control system for driving propellers to rotate and controlling the rotation direction of the propellers is arranged in the shell, and the driving control system is connected with the propellers;

the first propeller and the second propeller are symmetrically fixed on the left side of the shell and the right side of the shell, and rotating shafts of the first propeller and the second propeller are positioned in the horizontal direction;

the third screw propeller is fixed below the shell, and a rotating shaft of the third screw propeller is positioned in the vertical direction.

This patent is through the optimization to screw position and screw pivot direction, allows to provide the power that rises, descends through the third screw that is located the below, allows to provide the power that needs of rotation, march, retreat etc. through controlling the direction of rotation that is located the first screw of shell left side and is located the second screw on shell right side. Therefore, the aircraft can also realize the use effects of up-down, front-back and rotation which can be realized by four propellers under the condition of three propellers. The structure is necessarily beneficial to reducing the weight of the aircraft and the volume of the aircraft due to the reduction of the number of the propellers.

The orientation of the first propeller may be the same as the orientation of the second propeller. When the driving control system controls the first propeller and the second propeller to rotate forwards, the aircraft moves forwards; when the driving control system controls the first propeller and the second propeller to rotate reversely, the aircraft moves backwards; when the driving control system controls the first propeller to forward drive and the second propeller to reversely rotate, the aircraft rotates forwards; when the driving control system controls the first propeller to reversely transmit and the second propeller to normally rotate, the aircraft reversely rotates.

The orientation of the first propeller may also be opposite to the orientation of the second propeller. When the driving control system controls the first propeller and the second propeller to rotate forwards, the aircraft rotates forwards; when the driving control system controls the first propeller and the second propeller to rotate reversely, the aircraft rotates reversely; when the driving control system controls the first propeller to forward drive and the second propeller to reverse, the aircraft moves forwards; when the driving control system controls the first propeller to reversely transmit and the second propeller to normally rotate, the aircraft moves backwards.

As a preferred scheme, the driving control system has two sets, namely a first control system and a second control system; the first control system is in driving connection with the first propeller and the second propeller;

the second control system is in driving connection with the third propeller. To control the movement of the aircraft in the horizontal direction and in the vertical direction separately.

The second control system comprises an infrared reflection type sensor system, a motor control mechanism and a motor, wherein the infrared reflection type sensor system is connected with the motor control mechanism, the motor control mechanism is connected with the motor, the motor is fixed below the shell, a rotating shaft of the motor is provided with a third propeller, and the rotating shaft of the motor is used as a rotating shaft of the third propeller; the infrared reflection type sensor system comprises an infrared light-emitting element and an infrared receiving element; two openings are arranged below the shell, and the infrared light-emitting element and the infrared receiving element extend out through the openings; the light emitting direction of the infrared light emitting element faces the outer side of the shell; the light receiving direction of the infrared receiving element is also toward the outside of the housing. When being close apart from ground or other objects, the infrared light that infrared light emitting component sent is received by infrared receiving element through ground or other object reflection to convert the signal of telecommunication into, motor control mechanism control motor rotates, thereby drives the screw and rotates, produces the lift. When the distance from the ground or the object is far, the infrared receiving element can not receive the reflected light reaching the threshold value and can not convert the reflected light into effective electric signals.

The first control system comprises a remote control signal receiving system, a motor control mechanism and two motors, wherein the remote control signal receiving system is connected with the motor control mechanism, the motor control mechanism is connected with the two motors, one motor is fixed on the left side of the shell, the other motor is fixed on the right side of the shell, rotating shafts of the two motors are respectively provided with a first propeller and a second propeller, and the rotating shafts of the two motors are respectively used as the rotating shaft of the first propeller and the rotating shaft of the second propeller; the shell is provided with a hole, the remote control signal receiving system comprises a remote control signal receiving element, and the remote control signal receiving element extends out of the hole; the first control system also comprises a remote control signal transmitting system matched with the remote control signal receiving system. The motor control mechanism analyzes the control parameters of the two motors according to the information received by the remote control signal receiving system, so that the two motors are controlled to rotate, the first propeller and the second propeller are further rotated, and the operations of left-turning, right-turning, advancing, backing and the like are realized.

In order to further reduce components and parts and reduce cost, the infrared receiving element is used as the remote control signal receiving element, and the remote control signal transmitting module adopts an infrared signal as a remote control transmitting module of a communication signal. After using the infrared signal as the communication signal, the remote control signal receiving system and the infrared reflective sensor system may share the infrared receiving element. The infrared reflection type sensor system further comprises an infrared communication module, and the infrared receiving element is connected with the infrared communication module. After the scheme is adopted, the two systems can share the infrared communication module. Of course, the motor control mechanism and the motor control mechanism can share the main control module.

As a preferred scheme, the left side and the right side of the shell are respectively connected with a barrel-shaped body with openings at two ends, a fixed seat for fixing a motor is arranged in the center of the barrel-shaped body, the motor is fixed on the fixed seat, and the fixed seat is connected with the barrel-shaped body through at least three support ribs. According to the design, on one hand, the positions of the fixed seat and the barrel body except for the support ribs are hollowed out, so that the material consumption can be reduced, and the total mass of the aircraft can be reduced; the other side of the barrel-shaped body has a certain radian due to the outer contour, and the direction of the aircraft can be changed by utilizing the radian when the aircraft lands on the ground, thereby playing a role in buffering.

The middle of the fixed seat is sunken, and the motor part is inserted into the sunken part. On one hand, the material consumption can be further reduced; in another aspect, a position of the motor may be further defined.

The first propeller and the second propeller are located in the barrel-shaped body. To reduce the probability of the propeller injuring the user.

The lower part of shell is equipped with the cover body that an opening is down, it has the air inlet to open on the lateral wall of the cover body, the third screw is located cover is internal. The cover body is also arranged to reduce the probability that the propeller hurts the user. The air inlet on the side wall can effectively ensure air inlet, reduce the airflow resistance at the third propeller and avoid overheating of the motor.

The air inlets are preferably equally spaced on the side walls of the housing. So that the cover body is symmetrical and the weight is relatively balanced.

In order to smooth the flight of the aircraft, a suspension mechanism for suspending the balloon is preferably provided above the housing. The user can make the aircraft keep below the balloon all the time and the opening of the aircraft faces downwards in the flying process by suspending the balloon, particularly the hydrogen balloon and the helium balloon above the suspension mechanism, so that the aircraft is prevented from turning in the vertical direction.

Drawings

FIG. 1 is a circuit diagram of a power supply module;

FIG. 2 is a circuit diagram of a master control module;

fig. 3 is a circuit diagram of an infrared communication module;

FIG. 4 is a circuit diagram of a motor drive module;

FIG. 5 is a circuit diagram of a motor drive module;

fig. 6 is a schematic structural view of a partial structure of one structure of the housing of the present invention;

FIG. 7 is a schematic view of the remainder of the housing of FIG. 6

Detailed Description

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific drawings.

A light aircraft comprises an aircraft shell, wherein a driving control system which drives propellers to rotate and controls the rotation direction of the propellers is arranged in the shell, the driving control system is connected with the propellers, and the propellers are three and are respectively a first propeller, a second propeller and a third propeller; the first propeller and the second propeller are symmetrically fixed on the left side and the right side of the shell, and rotating shafts of the first propeller and the second propeller are positioned in the horizontal direction; the third screw propeller is fixed below the shell, and a rotating shaft of the third screw propeller is positioned in the vertical direction. This patent is through the optimization to screw position and screw pivot direction, allows to provide the power that rises, descends through the third screw that is located the below, allows to provide the power that needs of rotation, march, retreat etc. through controlling the direction of rotation that is located the first screw of shell left side and is located the second screw on shell right side. Therefore, the aircraft can also realize the use effects of up-down, front-back and rotation which can be realized by four propellers under the condition of three propellers. The structure is necessarily beneficial to reducing the weight of the aircraft and the volume of the aircraft due to the reduction of the number of the propellers.

The orientation of the first propeller may be the same as the orientation of the second propeller. When the driving control system controls the first propeller and the second propeller to rotate forwards, the aircraft moves forwards; when the driving control system controls the first propeller and the second propeller to rotate reversely, the aircraft moves backwards; when the driving control system controls the first propeller to forward drive and the second propeller to reversely rotate, the aircraft rotates forwards; when the driving control system controls the first propeller to reversely transmit and the second propeller to normally rotate, the aircraft reversely rotates. The orientation of the first propeller may also be opposite to the orientation of the second propeller. When the driving control system controls the first propeller and the second propeller to rotate forwards, the aircraft rotates forwards; when the driving control system controls the first propeller and the second propeller to rotate reversely, the aircraft rotates reversely; when the driving control system controls the first propeller to forward drive and the second propeller to reverse, the aircraft moves forwards; when the driving control system controls the first propeller to reversely transmit and the second propeller to normally rotate, the aircraft moves backwards.

the second control system is in driving connection with the third propeller. To control the movement of the aircraft in the horizontal direction and in the vertical direction separately. The second control system comprises an infrared reflection type sensor system, a motor control mechanism and a motor, wherein the infrared reflection type sensor system is connected with the motor control mechanism, the motor control mechanism is connected with the motor, the motor is fixed below the shell, a rotating shaft of the motor is provided with a third propeller, and the rotating shaft of the motor is used as a rotating shaft of the third propeller; the infrared reflection type sensor system comprises an infrared light-emitting element and an infrared receiving element; two openings are arranged below the shell, and the infrared light-emitting element and the infrared receiving element extend out through the openings; the light emitting direction of the infrared light emitting element faces the outer side of the shell; the light receiving direction of the infrared receiving element is also toward the outside of the housing. When being close apart from ground or other objects, the infrared light that infrared light emitting component sent is received by infrared receiving element through ground or other object reflection to convert the signal of telecommunication into, motor control mechanism control motor rotates, thereby drives the screw and rotates, produces the lift. When the distance from the ground or the object is far, the infrared receiving element can not receive the reflected light reaching the threshold value and can not convert the reflected light into effective electric signals.

In order to further reduce components and parts and reduce cost, the infrared receiving element is used as a remote control signal receiving element, and the remote control signal transmitting module adopts an infrared signal as a remote control transmitting module of a communication signal. After using the infrared signal as the communication signal, the remote control signal receiving system and the infrared reflective sensor system may share the infrared receiving element. The infrared reflection type sensor system also comprises an infrared communication module, and the infrared receiving element is connected with the infrared communication module. After the scheme is adopted, the two systems can share the infrared communication module. Of course, the motor control mechanism and the motor control mechanism can share the main control module. The motor control mechanism also comprises a motor driving module, the signal input end of the motor driving module is connected with the main control module, and the signal output end of the motor driving module is connected with the motor; the motor control mechanism further comprises a motor driving module, the signal input end of the motor driving module is connected with the main control module, and the signal output end of the motor driving module is connected with the motor.

Referring to fig. 1, 2, 3, 4 and 5, fig. 1 is a circuit diagram of a power module, fig. 2 is a circuit diagram of a main control module, fig. 3 is a circuit diagram of an infrared communication module, fig. 4 is a circuit diagram of a motor driving module, and fig. 5 is a circuit diagram of a motor driving module. The power module in fig. 1 provides power to the energy consuming modules. The infrared communication module in fig. 3, the motor driving module in fig. 4, and the motor driving module in fig. 5 are all connected to the main control module in fig. 2. The model and parameters of each component are marked in the figure.

Referring to fig. 6, the left side and the right side of the housing 1 are respectively connected with a barrel-shaped body 2 with two open ends, a fixing seat 6 for fixing a motor is arranged in the center of the barrel-shaped body 2, the motor is fixed on the fixing seat 6, and the fixing seat 6 is connected with the barrel-shaped body 2 through at least three support ribs. According to the design, on one hand, the positions of the fixed seat 6 and the barrel-shaped body 2 except for the support ribs are hollowed out, so that the material consumption can be reduced, and the total mass of the aircraft can be reduced; the other side of the barrel-shaped body has a certain radian due to the outer contour, and the direction of the aircraft can be changed by utilizing the radian when the aircraft lands on the ground, thereby playing a role in buffering. The support ribs are preferably located adjacent one side of the barrel to reduce the material and volume of the barrel while ensuring that the propeller is located within the envelope of the barrel. The holder 6 may be located outside the barrel as in the configuration of figure 6.

The number of the support ribs is preferably three. So that the structure is firm and the deformation is reduced. The connecting part of the shell and the barrel body can be directly used as the component part of the barrel body, so that the material consumption can be further reduced, and the fixation is firmer. Part of the barrel may also be embedded within the housing. In order to make the structure of partial embedding more clear to those skilled in the art, taking fig. 6 as an example, the barrel is moved to the inner side of the shell during the design, and the part of the shell occupied by the barrel is abandoned.

The middle part of the fixed seat 6 is sunken, and the motor part is inserted into the sunken part. On one hand, the material consumption can be further reduced; in another aspect, the position of the motor may be further defined. The side wall of the recess is provided with a slot. The slotted design can further reduce the material consumption on one hand, and on the other hand, the power cord of the motor can be conveniently pulled out. The first propeller and the second propeller are positioned in the barrel-shaped body. To reduce the probability of the propeller injuring the user. A cover body 3 with a downward opening is arranged below the shell 1, an air inlet is formed in the side wall of the cover body, the third propeller is positioned in the cover body, and the position 5 in fig. 6 is an installation position of the third propeller. The cover body is also arranged to reduce the probability that the propeller hurts the user. The air inlet on the side wall can effectively ensure air inlet, reduce the airflow resistance at the third propeller and avoid overheating of the motor. The lower edge of the cover is preferably curved. So as to play a role of buffering by utilizing the radian of the cover body. The lower edge of fig. 6 is vertical, but is also possible. The air inlets are preferably equally spaced on the side walls of the housing. So that the cover body is symmetrical and the weight is relatively balanced.

In order to smooth the flight of the aircraft, a suspension means 8 for suspending the balloon is preferably provided above the housing 1. The user can make the aircraft keep below the balloon all the time and the opening of the aircraft faces downwards in the flying process by suspending the balloon, particularly the hydrogen balloon and the helium balloon above the suspension mechanism, so that the aircraft is prevented from turning in the vertical direction.

The hanging mechanism 8 preferably comprises two parallel strip-shaped bulges, and hollow parts are arranged below the bulges. The balloon can pass through the two hollowed-out parts firstly, then upwards bypasses the bulge positioned in front, is introduced from a gap between the two bulges, and passes through the hollowed-out part positioned below the bulge positioned in rear. Under the action of buoyancy, the balloon is pressed on the strip-shaped bulges. The fixing mode is green and environment-friendly, and is convenient to fix.

When the hydrogen balloon and the helium balloon are used, the hydrogen balloon and the helium balloon can provide certain buoyancy, so that the flying energy consumption is further saved. And the suspension effect can be conveniently manufactured as long as the buoyancy provided by the hydrogen balloon and the helium balloon is almost the same as the gravity of the aircraft, for example, the buoyancy provided by the hydrogen balloon and the helium balloon is more than 0.8 times of the gravity of the aircraft. In order to solve the problem that the aircraft cannot fall down when the buoyancy of the hydrogen balloon and the helium balloon is larger, a cavity is arranged in the shell, and an opening 7 is formed in the side wall of the shell of the cavity. The cavity may be filled with a weight by means of the port 7 to increase the weight of the aircraft. The counterweight is preferably steel balls.

In order to facilitate mounting and fixing of the power module, the motor control mechanism, and the like, it is preferable that the housing 1 is provided with a recess 4 as shown in fig. 6, and the power module, the motor control mechanism, and the like are fixed in the recess. At this time, the housing 1 further includes a cover for closing the opening, the cover is provided with an opening 9, and the infrared light emitting element and the infrared receiving element extend from the opening 9. The infrared light-emitting element and the infrared receiving element are both preferably positioned outside the rotating radius of the third propeller so as to avoid the interference of the third propeller on the infrared signal.

The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. A light aircraft comprises an aircraft shell, wherein a driving control system for driving propellers to rotate and controlling the rotation direction of the propellers is arranged in the shell, and the driving control system is connected with the propellers;

2. A lightweight aircraft according to claim 1, wherein: the first propeller is oriented in the same or opposite direction as the second propeller.

3. A lightweight aircraft according to claim 1, wherein: the driving control systems are provided with two sets, namely a first control system and a second control system; the first control system is in driving connection with the first propeller and the second propeller;

the second control system is in driving connection with the third propeller.

4. A lightweight aircraft according to claim 3, wherein: the second control system comprises an infrared reflection type sensor system, a motor control mechanism and a motor, wherein the infrared reflection type sensor system is connected with the motor control mechanism, the motor control mechanism is connected with the motor, the motor is fixed below the shell, a rotating shaft of the motor is provided with a third propeller, and the rotating shaft of the motor is used as a rotating shaft of the third propeller; the infrared reflection type sensor system comprises an infrared light-emitting element and an infrared receiving element; two openings are arranged below the shell, and the infrared light-emitting element and the infrared receiving element extend out through the openings; the light emitting direction of the infrared light emitting element faces the outer side of the shell; the light receiving direction of the infrared receiving element is also toward the outside of the housing.

5. A lightweight aircraft according to claim 4, wherein: the first control system comprises a remote control signal receiving system, a motor control mechanism and two motors, wherein the remote control signal receiving system is connected with the motor control mechanism, the motor control mechanism is connected with the two motors, one motor is fixed on the left side of the shell, the other motor is fixed on the right side of the shell, rotating shafts of the two motors are respectively provided with a first propeller and a second propeller, and the rotating shafts of the two motors are respectively used as the rotating shaft of the first propeller and the rotating shaft of the second propeller; the shell is provided with a hole, the remote control signal receiving system comprises a remote control signal receiving element, and the remote control signal receiving element extends out of the hole; the first control system also comprises a remote control signal transmitting system matched with the remote control signal receiving system.

6. A lightweight aircraft according to claim 5, wherein: the remote control signal transmitting module adopts an infrared signal as a communication signal;

the remote control signal receiving system also comprises an infrared communication module, and the infrared receiving element is connected with the infrared communication module.

7. A lightweight aircraft according to claim 1, 2, 3 or 4, wherein: the left side and the right side of the shell are respectively connected with a barrel-shaped body which is barrel-shaped and has two open ends, the center of the barrel-shaped body is provided with a fixed seat for fixing a motor, the motor is fixed on the fixed seat, and the fixed seat is connected with the barrel-shaped body through at least three support ribs;

the middle part of the fixed seat is sunken, and the motor part is inserted into the sunken part;

the first propeller and the second propeller are located in the barrel-shaped body.

8. A lightweight aircraft according to claim 7, wherein: the lower part of shell is equipped with the cover body that an opening is down, it has the air inlet to open on the lateral wall of the cover body, the third screw is located cover is internal.

9. A lightweight aircraft according to claim 1, 2, 3 or 4, wherein: and a suspension mechanism for suspending the balloon is arranged above the shell.

10. A lightweight aircraft according to claim 9, wherein: the shell is internally provided with a cavity, and the cavity is provided with an opening on the side wall of the shell.