TWI480081B - Remote control aircraft - Google Patents

Description

Remote control aircraft

The present invention relates to a flying device, and more particularly to a remotely controllable unmanned aerial vehicle.

The design of traditional remote control aircraft is mostly based on entertainment. It focuses on the display of lighting or sound effects. The requirements of flight control for such remote control aircraft are usually only required to be able to fly, but the flight time and air-to-air capacity are not considered. In addition, such a remote-controlled aircraft sets the propeller at the head of the aircraft, so if it accidentally hits a person, it may cause personal injury. If it hits an obstacle, it may damage the propeller.

The design of another traditional remote-controlled aircraft is purely competitive, with a focus on flight speed and minimum radius of gyration. In order to pursue speed and control, this type of RC aircraft is optimized for the ratio of the wingspan to the average chord (the aspect ratio). The so-called chord refers to the length of the wing along the direction of the thrust line, and the span is the linear distance from the wing to the wing tip. However, the low aspect ratio means that a higher landing speed and a longer landing runway are required, so that it is suitable for operation in a wide outdoor field and cannot be operated in a space-limited room.

The above characteristics can also be seen from the flight behavior of birds. For example, the flight habit of the albatross is long-term soaring, so the aspect ratio of the wings is high; The mites belong to predatory animals and must pursue instantaneous high speed and flexible response, so their aspect ratio is low.

Competitive remote-controlled aircraft require lower aspect ratios in order to increase flight speed with limited power and power. In addition, this type of aircraft also mimics the historically famous racing engine GeeBee, which is placed on the nose of the aircraft so that the thrust line is in line with the axis of the fuselage.

Therefore, the conventional non-helicopter type remote control aircraft not only does not have the ability to stagnate, but also easily causes injury to the surrounding person or damage of the propeller itself once the impact occurs.

In view of the above, the present invention provides a remote control aircraft having a center of gravity and controlling its flight via a remote control device, which includes a two-square plate body, two wings, a propulsion module, a servo module and a control module. .

The two triangular plate system constitutes a fuselage of the remote control aircraft, and each of the triangular plates has a first side, a second side and a third side, wherein the first side is larger than the second side, and the second side is larger than the third side. Each of the triangular plates is connected to each other along the longest first side of the side and is defined by an angle to define an accommodation space. Each of the triangular plates has a first partial area that can be inverted with respect to the surface of each of the triangular plates, and at least a portion of the third side constitutes one of the edges of the first partial area.

The two wings have a quadrangular shape and each have a longest side and a shortest side, and each of the wings is connected to the second side of each of the triangular plates with its longest side, and the longest and shortest sides of each wing and the connected triangular plate body The third side meets at the same point. Each wing has one of the surfaces that can be flipped relative to each wing The second partial area, the shortest side constitutes one of the edges of the second partial area.

The propulsion module is fixed on the two triangular plate body, and is located between the intersection point of the first side and the second side and the center of gravity, and the thrust line does not pass through the accommodating space.

The servo module connects the first partial area and the second partial area respectively to control the flipping of the first partial area and the second partial area.

The control module is electrically connected to the propulsion module and the servo module, and the control module receives a remote control signal sent by the remote control device to control the propulsion module and the servo module.

In summary, the propulsion module of the present invention is located above the accommodating space formed by the two triangular plates, and is not located at the foremost end of the fuselage, thereby reducing the probability of injury or impulsion of the module when the impact occurs. In addition, the propulsion module is located between the intersection of the first side and the second side and the overall center of gravity of the remote control aircraft, and the thrust line does not pass through the axis of the fuselage, so that when the thrust is generated, a torque is generated to the fuselage. It has a tendency to form an elevation angle; and the airflow generated by the propulsion module causes the air flow velocity above the accommodating space and the two wings to be higher than the air velocity below, except that the lift is formed by the principle of the Bernoulli, and another body is generated for the fuselage. A torque causes the fuselage to have a tendency to form a depression angle. In this way, by adjusting the thrust of the thrust module to control the flight attitude of the remote control aircraft, the force of forward force, resistance, gravity and lift can be balanced to achieve the flight.

1‧‧‧Remote aircraft

11a, 11b‧‧‧ triangular plate

111‧‧‧ first side

112‧‧‧ second side

113‧‧‧ third side

115a, 115b‧‧‧ first partial area

119‧‧‧ accommodating space

13a, 13b‧‧‧ wing

135a, 135b‧‧‧ second partial area

15‧‧‧Promoting module

151‧‧‧propeller

152‧‧‧ bracket

152a‧‧‧ first end

152b‧‧‧ second end

171‧‧‧First servo

172‧‧‧Second servo

173‧‧‧Bridges

174‧‧‧first link

175‧‧‧second link

19‧‧‧Control module

21‧‧‧Fixed parts

23a‧‧‧ fold line

23b, 23c‧‧‧ cutting line

9‧‧‧Remote control

C1‧‧‧ center of gravity

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a perspective view of one embodiment of the present invention.

Figure 2 is an exploded view of one embodiment of the present invention.

Figure 3 is a top plan view of one embodiment of the present invention.

Figure 4 is a side elevational view of one embodiment of the invention.

Figure 5A is a schematic diagram of rudder actuation (I) of one embodiment of the present invention.

FIG. 5B is a schematic diagram of rudder actuation according to an embodiment of the present invention (2)

Figure 5C is an enlarged view of the rudder in Figure 5A.

Fig. 5D is an enlarged view of the rudder in Fig. 5B.

Fig. 6A is a schematic view (1) of the elevator actuation according to a specific embodiment of the present invention.

Figure 6B is a schematic diagram of the elevator actuation (2) of one embodiment of the present invention.

1 to 4 are respectively a perspective view, an exploded view, a top view and a side view of an embodiment of the present invention, and a remote control aircraft 1 having a center of gravity C1 is disclosed. The remote control aircraft 1 controls its flight via a remote control device 9, which comprises two triangular plates 11a and 11b, two wings 13a and 13b, a propulsion module 15, a servo module and a control module 19, which are described as follows. .

The two triangular plates 11a and 11b constitute a fuselage of the remote control aircraft 1. The two triangular plates 11a and 11b have a first side 111, a second side 112 and a third side 113, wherein the first side 111 is larger than the second side 112. The second side 112 is larger than the third side 113. The triangular plates 11a and 11b are connected to each other along the longest first side 111 and define an accommodating space 119 at an angle. The two triangular plates 11a and 11b respectively have one of the first partial regions 115a and 115b which are reversed with respect to the surface thereof, and at least a portion of the third side 113 constitutes one of the edges of the first partial regions 115a and 115b.

Referring to FIG. 5A and FIG. 5B, respectively, a rudder actuation diagram (1) and a schematic diagram (2) according to an embodiment of the present invention respectively disclose that the first partial regions 115a and 115b are leftward relative to the triangular plates 11a and 11b, respectively. Flip and flip to the right. The first partial regions 115a and 115b of the present embodiment can be used as the rudder of the remote control aircraft 1, and the flight direction of the remote control aircraft 1 is changed by flipping the surfaces of the triangular plates 11a and 11b, respectively.

Please refer to FIG. 5C and FIG. 5D again, which are enlarged view (1) and enlarged view (2) of the first partial region of FIGS. 5A and 5B, respectively. When the first partial regions 115a and 115b are controlled to be turned to the left with respect to the triangular plates 11a and 11b as shown in Fig. 5A, the remote control aircraft 1 can be turned to the left; when the first partial regions 115a and 115b are controlled as shown in Fig. 5B When the flaps 11A and 11b are turned to the right, the remote control aircraft 1 can be turned to the right.

The two wings 13a and 13b are quadrangular and each have a longest side 131 and a shortest side 132, and the two wings 13a and 13b respectively have their longest sides. 131 is connected to the second side 112 of the two triangular plates 11a and 11b, and the longest side 131 and the shortest side 132 of the two wings 13a and 13b respectively meet the third side 113 of the connected triangular plates 11a and 11b. . The two wings 13a and 13b respectively have second partial regions 135a and 135b which are flipped relative to their airfoil, and the shortest edges 132 of the two wings 13a and 13b respectively form one of the two second partial regions 135a and 135b.

As shown in FIGS. 1 and 2, the propulsion module 15 is fixed to the two triangular plates 11a and 11b, and is located between the intersection of the first side 111 and the second side 112 and the center of gravity C1. In addition, the thrust line of the propulsion module 15 does not pass through the accommodating space. That is to say, the thrust line does not pass through the axis of the fuselage, nor does it pass through the center of gravity C1 of the remote control aircraft 1.

In this embodiment, the propulsion module 15 includes a bracket 152 and a propeller 151. The bracket 152 has a first end 152a and a second end 152b. The first end 152a is fixed on the triangular plate bodies 11a and 11b and located in the accommodating space 119, and the second end 152b protrudes out of the accommodating space 119. The propeller 151 is coupled to the second end 152b such that the thrust line is higher than the airfoil of the two wings 13a and 13b.

In this embodiment, the servo module is disposed in the accommodating space 119, and includes a first servo 171, a second servo 172, a bridge 173, a first link 174, and two second links. 175. The two ends of the bridge member 173 are respectively bonded to the first partial regions 115a and 115b of the triangular plate bodies 11a and 11b with an adhesive, and the adhesive is not hardened (for example, silicone). The two ends of the first link 174 are respectively connected to the first servo 171 and the first partial region 115a of the triangular plate body 11a. When the first servo 171 is via the first link 174 When the first partial region 115a is pulled, the first partial region 115b can be synchronously pulled via the bridge member 173. Since the two ends of the bridge member 173 are fixed to the first partial regions 115a and 115b by using adhesive which is not hardened, the first The partial regions 115a and 115b can be smoothly flipped as shown in Figs. 5C and 5D.

As shown in FIG. 2, the two first partial regions 115a and 115b are defined by the fold line 23a and the cutting lines 23b and 23c on the two triangular plates 11a and 11b. The fold line 23a is located at the first side 111 and the second side 112. Between and parallel to the third side 113, the two cutting lines 23b and 23c extend from the two ends of the fold line 13a to the third side 113, respectively. The fold line can be further affixed with a flexible sheet (such as tape) for reinforcement.

Please refer to FIG. 6A and FIG. 6B respectively, which respectively illustrate an elevator actuation diagram (1) and an actuation diagram (2) according to an embodiment of the present invention, and the two ends of one of the second links 175 are respectively connected. The second servo 172 and the second partial region 135a are connected to the second servo 172 and the second partial region 135b, respectively. Therefore, the second servo 172 simultaneously pulls the two second partial regions 135a via the two second links 175 so that they can be flipped up at the same time as in FIGS. 6A and 6B. In the present embodiment, the two second links 175 are respectively connected to the second partial regions 135a and 135 of the wing adjacent to the longest side 131.

The second partial area 135a at the tail end of the wing is used as an elevator. When the remote control aircraft 1 wants to make a landing or deceleration, the second partial areas 135a and 135b can be turned up to increase the forward resistance and reduce Less lift.

The control module 19 is disposed in the accommodating space 119 and electrically connected to the propulsion module 15 and the servo module (the first servo 171 and the second servo 172). The control module 19 receives a remote control signal from the remote control device 9 and controls the operation of the propulsion module 15 and the servo modules (the first servo 171 and the second servo 172). In addition, in an implementation manner, the control module 19 is further electrically connected to a battery device (not shown) for supplying power required for the remote control aircraft 1 to fly, which can be set. In the accommodation space 119 of the remote control aircraft 1.

In this embodiment, the control module 19 further includes an electronic transmission (not shown) connected to the propeller 151 to control the rotation speed of the propeller 151 according to the remote control signal sent by the remote control device 9, thereby changing the thrust generated by the propeller 151.

In the present embodiment, the angle formed by the second side 112 of the triangular plates 11a and 11b is substantially in the range of 15° to 30°. If it is less than 15°, the fuselage formed by the triangular plates 11a and 11b is too narrow, which not only causes insufficient lift, but also adversely affects the flight stability (automatic returning ability) of the remote control aircraft 1, and is difficult to operate. If it is greater than 30°, the resistance experienced during flight is large, resulting in a decrease in endurance. When the angle formed by the second side 112 of the triangular plates 11a and 11b falls substantially in the range of 15° to 30°, the measured system can have the optimal setting of handling, stability and endurance.

The remote control aircraft 1 of the present embodiment further includes a plurality of fixing members 21 arranged at intervals, and the two ends of the fixing members 21 are respectively connected to the wing surfaces of the two wings 13a and 13b to improve the rigidity of the remote control aircraft as a whole. Such a When the remote control aircraft 1 is subjected to the torsion during flight, the overall structure is less prone to deformation, and the predictability of the flight path can be maintained. In this embodiment, three fixing members 21 are used, wherein one fixing member 21 is adjacently disposed at the second connecting end 152 of the propulsion module 15 to strengthen the rigidity of the torsion force; the other two fixing members 21 respectively It is placed at the longest part of the wingspan and adjacent to the second partial area 135a.

The propulsion module of the present invention is located above the accommodating space formed by the two triangular plates, and is not located at the foremost end of the entire remote control aircraft 1, thereby reducing the probability of injury or impulsion of the module when the impact occurs. In addition, the propulsion module is located between the intersection of the first side and the second side and the overall center of gravity of the remote control aircraft, and the thrust line does not pass through the axis of the fuselage, so that when the thrust is generated, a torque is generated to the fuselage. It has a tendency to form an elevation angle; and the airflow generated by the propulsion module causes the air flow velocity above the accommodating space and the two wings to be higher than the air velocity below, except that the lift is formed by the principle of the Bernoulli, and another body is generated for the fuselage. A torque causes the fuselage to have a tendency to form a depression angle. In this way, by adjusting the thrust of the thrust module to control the flight attitude of the remote control aircraft, the force of forward force, resistance, gravity and lift can be balanced to achieve the flight.

Although the technical content of the present invention has been disclosed in the above preferred embodiments, it is not intended to limit the present invention, and any modifications and refinements made by those skilled in the art without departing from the spirit of the present invention are encompassed by the present invention. The scope of protection of the present invention is therefore defined by the scope of the appended claims.

1‧‧‧Remote aircraft

11a, 11b‧‧‧ triangular plate

111‧‧‧ first side

112‧‧‧ second side

113‧‧‧ third side

115a, 115b‧‧‧ first partial area

119‧‧‧ accommodating space

13a, 13b‧‧‧ wing

135a, 135b‧‧‧ second partial area

15‧‧‧Promoting module

151‧‧‧propeller

152‧‧‧ bracket

152a‧‧‧ first end

152b‧‧‧ second end

172‧‧‧Second servo

173‧‧‧Bridges

175‧‧‧second link

21‧‧‧Fixed parts

9‧‧‧Remote control

C1‧‧‧ center of gravity

Claims (8)

A remote control aircraft having a center of gravity, the remote control aircraft controlling its flight via a remote control device, comprising: a triangular plate body, each of the triangular plate bodies having a first side, a second side and a third side, the first side being larger than The second side is larger than the third side, and each of the triangular plates is connected to each other along the first side and defines an accommodating space; each of the triangular plates has a corresponding triangular plate body The surface is inverted by a first partial area, at least a portion of the third side forming one of the edges of the first partial area; the two wings having a quadrilateral shape and each having a longest side and a shortest side Each of the wings is connected to the second side of each of the triangular plates with the longest side, and the longest side and the shortest side of each of the wings meet the third side of the connected triangular body In one point, each of the wings has a second partial area that is flipped relative to the surface of each of the wings, the shortest side forming one of the edges of the second partial area; a propulsion module fixed to the two triangular plates, and Located at the first Between the intersection point of the second side and the center of gravity, the thrust line of the propulsion module does not pass through the accommodating space; a servo module is disposed in the accommodating space and respectively connected to the first partial area and The second partial area is configured to control the inversion of the first partial area and the second partial area; and a control module is disposed in the receiving space, electrically connected to the propulsion module and the servo module, The control module receives a remote control signal sent by the remote control device to control the propulsion module and the servo module. The remote control aircraft of claim 1, wherein the propulsion module comprises: a bracket having a first end and a second end, the first end being fixed on the two triangular plates and located in the accommodating space; The second end protrudes from the accommodating space; and a propeller is connected to the second end such that the thrust line is higher than the airfoil of the two wings. The remote control aircraft of claim 2, wherein the control module further comprises an electronic transmission coupled to the propeller to control the thrust generated by the propeller according to the remote control signal. The remote control aircraft of claim 2, wherein the two second sides of the two triangular plates form an angle substantially in the range of 15° to 30°. The remote control aircraft of claim 2, wherein the servo module comprises: a first servo; a bridge member, the two ends are respectively connected to the first partial area of each of the triangular plates; a first link, two The ends are respectively connected to the first local area of the first servo machine and one of the triangular plate bodies; a second servo machine; and two second links, the two ends of each of the second links are respectively connected to the second The servo and the second partial area of the wing. The remote control aircraft of claim 5, wherein each of the second links is coupled to the second partial region adjacent to the longest side. The remote control aircraft of claim 1, further comprising: a plurality of fixing members spaced apart from each other, and the two ends of the fixing members are respectively Do not connect to the airfoil of the two wings. The remote control aircraft of claim 1, wherein each of the first partial regions is defined by a fold line and a second cut line, the fold line being located between the first side and the second side and parallel to the third side The two cutting lines extend from the two ends of the folding line to the third side.