KR20190066398A - Tilt-prop air vehicle - Google Patents

Abstract

The tilt prop air body may include a body, wings extending in both directions of the body, a plurality of taps to be tilted with respect to the body, and a controller for controlling the tugs. A fixed-wick mode in which the power efficiency is improved by reducing or stopping the rotational speed of the rotor, and a rotor-blade mode in which all of the plurality of probes generate thrust.

Description

Tilted Prop Vehicle {TILT-PROP AIR VEHICLE}

The present invention relates to a tilt prop air craft comprising a plurality of blades and a plurality of props. It is a flight concept that can improve the flight performance by selectively driving the prop.

Flight bodies are typically aircraft, unmanned aircraft, helicopters, equipment and gliders.

Among these airplanes, unmanned aerial vehicles can be operated remotely using radio waves without a person. Thus, unmanned aerial vehicles can increase fuel efficiency and loading efficiency by reducing volume and weight, and can be used as a vehicle to carry out missions in dangerous areas instead of people.

In recent years, these unmanned aerial vehicles have been used for various purposes by various organizations such as global companies, IT companies, engineering universities, and the like due to the lower production costs and various applications due to the development of production technology.

Generally, multi - copter unmanned aerial vehicles mainly generate lift to take off the UAV by using a large number of props.

Such an unmanned aerial vehicle is disclosed in Korean Unexamined Patent Application Publication No. 2016-0014266 filed on July 29, 2014.

Another object according to an embodiment is to provide a tilt-prop projectile in which the tilt, the rotational speed, and the collective pitch of a plurality of probes can be individually controlled.

Another object of the present invention is to provide a tilt prop airbag that improves the power efficiency so as to extend the time of flight of the airbag.

Another object of the present invention is to provide a tilt prop airbag which can improve the attitude control performance of a flying object.

Another object of the present invention is to provide a tilt prop airbag capable of improving yaw control characteristics.

Another object of the present invention is to provide a tilt prop airbag which is capable of folding a stopped propeller so as to reduce the resistance of air at the time of flight cruise.

According to another aspect of the present invention, there is provided a tilt-prop flying body including a body, wings extending in both directions of the body, a plurality of tilts tilted with respect to the body, and a controller for controlling the tilts. The control unit may include a fixed-wick mode in which the power efficiency is improved by reducing or stopping the rotation speed of a part of the probes, and a rotor mode in which all of the plurality of probes generate thrust.

Also, a plurality of the treads of the tilt-prop air body according to an embodiment may include first taps and second taps, each of the first taps and the second taps being housed in the housing, The control unit may include a plurality of blades extending in a radial direction of the rotary shaft, wherein the control unit controls the pitch of the blades of the first prongs and the second prongs And the rotational speed of the other one of the first probes and the second probes is changed.

Also, in the fixed-wick mode of the tilt-prop pilot according to an exemplary embodiment, the control unit may stop the rotation of the other one of the first probes and the second probes.

Also, the control unit of the tilt-prop pilot according to an exemplary embodiment may control the rotation of the first prongs and the second rotors to stop in an angle range in which the blades are not in contact with the vanes.

In addition, in the fixed-wick mode of the tilter air vehicle according to one embodiment, the control unit may control the stationary blades of the first and second rotors to be turned in a direction parallel to the rotating shaft have.

Also, the wing of the tilt-prop pilot according to an embodiment may be formed of a front wing and a rear wing, and the plurality of the probes may include a first probe disposed on the front wing and a second probe disposed on the rear wing. Wherein the control unit is configured to tilt the first prongs and the second prongs such that a plurality of the first prongs and the second prongs are directed to the propulsion direction of the tilt prop air, The control unit may tilt the first prongs and the second prongs such that a plurality of the first prongs and the second prongs face the upper direction of the body.

In addition, in the rotor-blade mode of the tilt-prop pilot according to the embodiment, the control unit may control the pitch of each of the probes to control the posture of the tilt-prop pilot, the rotational speed of each of the probes, It is possible to control the rotational speed of a part of the plurality of the probes and to control the pitch of the other parts.

According to an embodiment of the present invention, the tilt, the rotational speed, and the collective pitch of a plurality of probes can be individually controlled.

In addition, according to the tilt-prop air vehicle according to one embodiment, the power efficiency can be improved so as to extend the flight time of the air vehicle.

In addition, according to the tilt-prop air vehicle according to the embodiment, the attitude control performance of the air vehicle can be improved.

Further, according to the tilt-prop air vehicle according to the embodiment, the yaw axis control characteristic can be improved.

In addition, according to the tilt prop air body according to the embodiment, the stopped propeller can be folded so as to reduce the air resistance at the time of flight cruise.

FIG. 1 shows a state in which a plurality of taps of a tilt-prop plane are tilted in the upward direction according to one embodiment.
FIG. 2 illustrates a state in which a plurality of props of a tilt-prop pilot are tilted in a propelling direction according to an embodiment of the present invention.
FIG. 3 shows a state in which a blade of a prop of a tilt-prop air vehicle according to an embodiment is pivoted toward the housing.
FIG. 4 shows a state in which a part of the blades of the plurality of props of the tilt-prop pilot is folded according to an embodiment of the present invention.
FIG. 5 illustrates the speed of a tilter air vehicle according to an embodiment and the change in demand force according to the driving of the rotor.

Hereinafter, embodiments will be described in detail with reference to exemplary drawings. It should be noted that, in adding reference numerals to the constituent elements of the drawings, the same constituent elements are denoted by the same reference symbols as possible even if they are shown in different drawings. In the following description of the embodiments, detailed description of known functions and configurations incorporated herein will be omitted when it may make the best of an understanding clear.

In describing the components of the embodiment, terms such as first, second, A, B, (a), and (b) may be used. These terms are intended to distinguish the constituent elements from other constituent elements, and the terms do not limit the nature, order or order of the constituent elements. When a component is described as being "connected", "coupled", or "connected" to another component, the component may be directly connected or connected to the other component, Quot; may be "connected," "coupled," or "connected. &Quot;

FIG. 1 illustrates a state in which a plurality of probes 130 of a tilt prop air unit 100 are tilted in an upward direction. FIG. 2 illustrates a state in which a plurality of probes 130 of a tilt- 130 are tilted in the propelling direction.

Referring to FIGS. 1 and 2, the tilt-prop air vehicle 100 according to one embodiment may include a body 110, a wing 120, a prop 130, and a control unit.

The body 110 may generally include a probe 130 and a battery that powers the control and a receiving member that receives commands to remotely steer the vehicle 100. The body 110 collects information A camera, a microphone, a radar, a position sensor, a gyro sensor, and the like, and may include a transmitting member for transmitting collected information remotely. Further, the body 110 may further include a receiving member capable of receiving an article for transportation.

The wings 120 may be disposed on both sides of the body 110. The wing 120 may be composed of a plurality of wings and more specifically includes a front wing 122 disposed relatively to the front of the body 110 and a rear wing 124 disposed relatively rearward of the body 110 . A rear flap 1222 may be provided behind the front flap 122 to control pitch posture of the flight body 100 and elevating the flight body 100. A rear flap 124 100 and a rear flap 1242 for pitch posture control.

The plurality of probes 130 may be provided and may be installed to be tilted with respect to the body 110. The plurality of props 130 may be installed apart from the body 110 and may be installed at both ends of the wings 120 as shown in FIGS.

For example, the plurality of props 130 may be installed perpendicularly to the longitudinal direction of the wings 120 at both ends of the wings 120 and may be tilted within a range perpendicular to the wings 120 have. That is, the wings 120 may be rotated about the longitudinal axis of the wings 120, and the rotational angles of the props 130 may be differently tilted.

FIG. 3 illustrates a state in which the blades 1326 and 1346 of the prop 130 of the tilt prop air body 100 according to the embodiment are pivoted toward the housing. FIG. 4 illustrates a state in which the tilt prop air body 100 (B) shows a state in which the blades 1326 and 1346 of some of the plurality of the props 130 of FIG.

4A shows a state in which the first probe 132 of the tilt-prep air vehicle 100 according to the embodiment is rotated and the second blade 1346 of the second prop 134 is folded, and FIG. 4B Shows a state in which the first bloat 1326 of the first probe 132 of the tilt-prep air vehicle 100 according to an embodiment is folded and the second prop 134 is rotated.

1 to 4B, the prop 130 according to one embodiment includes first prongs 132 disposed on the front vane 122 and second prongs 132 disposed on the rear vane 124 134).

Specifically, the first probes 132 may be disposed relatively forward with respect to the body 110, and the second probes 134 may be disposed relatively rearward with respect to the body 110.

The first prongs 132 may include a first housing 1322, a first rotating shaft 1324 and a plurality of first blades 1326 and the second prongs 134 may include a second housing 1342 ), A second rotating shaft 1344, and a plurality of second blades 1346. [

The blades 1326 and 1346 of the first and second props 132 and 134 are disposed in the radially extending configuration of the rotating shafts 1324 and 1346 and the blades 1326 and 1346 A joint element may be disposed between the rotating shafts 1324 and 1346.

The articulation causes the blades 1326 and 1346 to move in a direction parallel to the rotational shafts 1324 and 1346 or to change the collective pitch with respect to the rotational shafts 1324 and 1346, And may be attached to the outer surfaces of the housings 1322 and 1342.

Specifically, the control unit can vary the rotational speed, collective pitch, or shape of the props 132, 134 individually. The control unit controls the above factors to cause the air vehicle 100 to travel in the fixed-wing mode and the rotor-wing mode.

The fixed-wing mode of the control unit may reduce or stop the rotational speed of some of the props 132, 134 to improve power efficiency during cruise. Also, in the rotor blade mode of the control unit, all the propps 132 and 134 generate thrusts, thereby performing takeoff, landing, or high-speed travel of the air vehicle 100.

In the fixed-wing mode, the control unit can be tilted such that both the first and second probes 132 and 134 are directed in the direction of propulsion of the air vehicle body 100 or the leading edge of the airfoil 120. That is, the air vehicle 100 can generate lift through the wing 120 and generate thrust through the first and second prongs 132 and 134.

After the first and second prongs 132 and 134 are tilted toward the propulsion direction of the air vehicle 100, the control unit controls the first prongs 132 and one of the second prongs 134 It is possible to control the collective pitch of the blades 1326 or 1346 of the props 132 or 134 to be changed and at the same time to change the rotational speed of the other one of the first probes 132 and the second probes 134 .

More specifically, in the fixed wick mode, the control may reduce or stop the rotation speed of the props 132 or 134 of one of the first probes 132 and the second probes 134. One of the first and second props 132 and 134 stops at one of the props 132,134 so that the blade 1326 or 1346 can be pivoted toward the housing 1322 or 1342 have.

When the blades 1326 or 1346 are pivoted toward the housing, that is, when the blades 1326 or 1346 are folded in the direction of the housing 1322 or 1342, the probes 132 or 134, The rotation can be stopped at an angle such that the wings 1206 and 1326 or 1346 do not interfere with the wing 120. After the rotating shaft 1324 or 1344 of the props 132 or 134 is stopped, the blades 1326 or 1346 may be folded.

FIG. 5 illustrates the speed of a tilt-prop pilot according to an exemplary embodiment and a change in demand force according to drive of a prop.

Referring to FIG. 5, the first and second props 132 and 134 may be selectively collapsed, and the required power versus required speed may be reduced as the props 132 or 134 are collapsed.

For example, the bold solid line in FIG. 5 shows that the propps 132 and 134 of the air vehicle 100, which is composed of four props, that is, two first prop 132 and two second prop 134, 122 and the rear wing 124 in the longitudinal direction of the vehicle 100 toward the traveling direction of the flying body 100. [ That is, the bold solid line in FIG. 5 indicates a state in which all of the four props 132 and 134 are rotated to propel the air vehicle 100.

5 indicates that the blades 1326 of the first prop 132 are unfolded and the blades 1346 of the second prop 134 are in a folded state in accordance with the flying body 100 shown in Fig. And speed relationship.

The thin solid line in Figure 5 indicates that the blades 1346 of the second prong 134 are unfolded and the blades 1326 of the first prong 132 are folded in accordance with the flight 100 shown in Figure 4b Displays power and speed relationship.

5, the bold solid line (at the time of full prop drive) in FIG. 5 indicates that the air vehicle 100 according to the embodiment requires about 8.0 kW of power to maintain the speed of 160 km / h, 5 indicates that the engine 100 requires about 6.0 kW of power to maintain the speed of 160 km / h, and the thin solid line (when the first prop valve is driven) of FIG. Means that about 5.8 kW of power is needed to maintain a speed of 160 km / h.

That is, in the case of a flying object similar in shape to the air vehicle 100 shown in FIGS. 1 to 4, the required power versus specific speed is the lowest energy efficiency when rotating all four prop 132, 134, Efficiency is increased when one of the probes 132 or 134 is stopped and the other one of the probes 132 or 134 is rotated.

In the rotor blade mode, the control unit can control each of the probes 132 and 134 in a state in which all the probes 132 and 134 are rotated.

More specifically, the control unit may control the collective pitch of each of the probes 132 and 134 or may control the rotational speed of each of the probes 132 and 134 to control the attitude of the air vehicle 100. Not only can the control unit control the rotational speed and the collective pitch of the first probes 132 and the second probes 134 differently but also the collective pitch and rotational speed of each of the plurality of first probes 132 And the collective pitch and rotational speed of each of the plurality of second flaws 134 can be made different from each other.

For example, the rotor blade mode can control a plurality of probes 132 and 134 in four ways as shown in the following table.

COL RPM HYB1 HYB2 Col_Front 0 to 20 12 0 to 20 12 Col_Rear 0 to 20 12 12 0 to 20 RPM_Front 1800 1600-2000 1800 1600-2000 RPM_Rear 1800 1600-2000 1600-2000 1800 Tilt_Front 90 ~ 95 90 ~ 95 90 ~ 95 90 ~ 95 Tilt_Rear 85 to 90 85 to 90 85 to 90 85 to 90 Flap_ Front 30 30 30 30 Flap_Rear 30 30 30 30

Table 1 Example of the prop control method for rotor mode

As shown in Table 1, the rotor blade mode can be controlled by the collective pitch control method (COL), the rotational speed control method (RPM), and the hybrid control method (HYB1, HYB2) of the probes 132 and 134.

The collective pitch control method COL allows the control section to change the collective pitch of the first probes 132 and the second probes 134 and the first probes 132 and the second probes 132, The rotation speed of the motor 134 is fixed.

The rotation speed control method RPM is a method in which the control unit fixes the collective pitches of the first and second probes 132 and 134 and controls the rotation speed of the first and second probes 132 and 134 Is changed.

The first hybrid control system HYB1 is configured such that the control unit changes the collective pitch of the first probe 132 and fixes the collective pitch of the second probe 134 and fixes the rotational speed of the first probe 132, And the rotation speed of the prop 134 is changed.

In the second hybrid control system HYB2, the control unit fixes the collective pitch of the first probe 132, changes the collective pitch of the second probe 134, changes the rotational speed of the first probe 132, And the rotation speed of the two-prong 134 is fixed.

The rotor mode can perform posture control of the air vehicle 100 using the above-described control method.

1 to 4B, in order to improve the yaw control characteristic of the air vehicle in the rotor-blade mode, the control unit preferably controls the first (first) and second The prisms 132 can be tilted by 93 to 95 degrees and the second prongs 134 can be tilted by 87 to 95 degrees.

As described above, the tilt angle, the rotational speed, the collective pitch, and the like of the plurality of probes 130 can be individually controlled in the tilt-prop air vehicle 100 according to the embodiment, The posture performance can be improved and the yaw axis control characteristic can be improved. In addition, the rotation of some of the props 132 or 134 of the tilt prop air body 100 may be stopped to perform a flight with improved power efficiency, and the blades 1326 or 1346 of some of the frogs 132 or 134, It is possible to reduce the resistance of the air generated by the blades 1326 or 1346 that are stopped and stopped.

The air resistance of the tilting prop unit 100 is reduced and the power efficiency is improved, so that the flight time of the air unit 100 can be prolonged.

Although the present invention has been described in connection with what is presently considered to be practical exemplary embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, And various modifications and changes may be made thereto without departing from the scope of the present invention. Accordingly, the spirit of the present invention should not be construed as being limited to the embodiments described, and all of the equivalents or equivalents of the claims, as well as the following claims, belong to the scope of the present invention .

100: tilt prop air vehicle
110: Body
120: Wings
122: front wing
1222: front flap
124: rear wing
1242: rear flap
130: Prop
132: First prop
1322: first housing
1324: first rotating shaft
1326: First blade
134: second prop
1342: second housing
1344: Second rotary shaft
1346: Second blade

Claims (7)

Body;
A blade extending in both lateral directions of the body;
A plurality of tilts tilted with respect to the body; And
A control unit for controlling the prop;
Lt; / RTI >
Wherein,
A fixed wing mode in which power efficiency is improved by reducing or stopping the rotational speed of a part of the prop; And
A rotor blade mode in which all of the plurality of probes generate thrust;
And a tilt-prop plane.
The method according to claim 1,
Wherein the plurality of the probes includes first probes and second probes,
Each of said first probes and said second prongs,
housing;
A rotating shaft provided in the housing and rotated; And
A plurality of blades extending in a radial direction of the rotating shaft;
/ RTI >
In the fixed-wick mode, the control unit may change the pitch of the blades of one of the first probes and the second probes so that the rotation speed of the other one of the first probes and the second probes is changed Controlled, tilt-prop aircraft.
3. The method of claim 2,
In the fixed-wick mode, the control unit stops the rotation of the other one of the first probes and the second probes.
The method of claim 3,
Wherein the control unit controls the rotation of the first prongs and the other of the second prongs to stop in an angle range in which the blades do not contact the vane.
The method of claim 3,
Wherein in the fixed-wick mode, the control unit controls the other of the first probes and the second probes to be pivoted in a direction parallel to the rotating shaft.
The method according to claim 1,
Wherein the wings are formed of a front wing and a rear wing,
Wherein the plurality of probes includes a first probe disposed on the front wing and a second probe disposed on the rear wing,
In the fixed-wick mode, the control unit tilts the first prongs and the second prongs such that a plurality of the first prongs and the second prongs are directed to the propelling direction of the tilt-prop airavul
Wherein the control unit tilts the first prongs and the second prongs such that the plurality of first prongs and the second prongs are directed to the upper direction of the body.
The method according to claim 1,
In the rotor-blade mode, the control unit may control the pitch of each of the probes to control the posture of the tilt-prop air, control the rotational speed of each of the probes, or control the rotational speed of some of the plurality of probes And control the pitch of the other part, the tilt-propoid body.

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