KR100832067B1 - Stability augmentation unit and tilt rotor aircraft having the same - Google Patents

Abstract

A stability augmentation unit and a tilt rotor aircraft having the same are provided to return an instable flight state into a stable flight state by driving a moment wheel in case of a change of a flight posture. A tilt rotor aircraft(100) includes a body(110), a pair of fixed wing units, a pair of rotary blade units(130), and a stability augmentation unit. The body is loaded with a pilot seat and various kinds of equipment. A surface of the body is designed in a streamline shape to reduce resistance of air. The fixed wing units are formed on both sides of the body and provide a lift to float the tilt rotor aircraft. The rotary blade units are formed on both sides of the body to provide a thrust corresponding to a drag of the tilt rotor aircraft. The stability augmentation unit includes a momentum wheel(140). The momentum wheel is vertically mounted at a Y-axis of the tilt rotor aircraft to increase stability of a pitch axis of the tilt rotor aircraft.

Description

STABILITY AUGMENTATION UNIT AND TILT ROTOR AIRCRAFT HAVING THE SAME}

1 is a side view showing a tilt rotor aircraft equipped with a stability enhancing unit of the present invention.

Figure 2 is a front view showing a tilt rotor aircraft equipped with a stability enhancing unit of the present invention.

Figure 3 is a perspective view showing a momentum wheel of the stability enhancing unit of the present invention.

4 is a conceptual view illustrating the operation of the stability enhancing unit of the present invention.

<Explanation of symbols for the main parts of the drawings>

100: Tilt rotor aircraft 110: Body

120: fixed wing unit 130: rotary wing unit

140 ： Momentum wheel 142 ： Cover part

144 ： Main body 146 ： Circuit

The present invention relates to a stability enhancer unit and a tilt rotor aircraft including the same, and in more detail, a stability enhancer unit capable of realizing flight stability by quickly responding to a disturbance when the aircraft changes its attitude during flight and includes the same. It relates to a tilt rotor aircraft.

Tilt-rotor aircraft refers to aircraft that are mounted at both ends of the main wing and large porters up and down to take off and land vertically like helicopters, and to the front to fly like propeller aircraft. After taking off vertically, the tilted rotor was named because it tilts forward in order to fly horizontally in order to fly horizontally. Tiltrotor aircraft are capable of short takeoff and landing as well as normal takeoff and landing, as well as vertical takeoff and landing.

The tilt rotor aircraft has both a rotor blade mode exhibiting characteristics similar to a helicopter during takeoff and landing, and a fixed wing mode exhibiting fixed wing aircraft characteristics for performing a mission. In addition, the tilt rotor aircraft has a transition mode for switching between the two modes. Unlike the general aircraft, the transition mode is a special flight area that only the tilt rotor has, and much research is being conducted. The transition mode is a flight mode in which a transition from the rotor blade mode to the fixed wing mode or the reverse transition from the fixed wing mode to the rotor blade mode is performed by changing the nacelle. Such a transition and reverse transition flight mode is the most sensitive and complicated flight area in the controller design of the tilt rotor aircraft. In particular, since the tilt angle changes, the aircraft pitch angle changes, causing a problem that the posture becomes unstable, and the nose is severely changed due to disturbance during the transition flight, thereby enabling unstable flight. In order to solve the problem that the aircraft pitch attitude becomes unstable due to a change in tilting angle or disturbance, the attitude control device should be considered accordingly.

The present invention solves the above problems, an object of the present invention is a tilt enhancer unit that can maintain the stability of the flight when the tilt rotor is converted to the transition mode and the transition in flight and a tilt rotor aircraft comprising the same In providing.

It is another object of the present invention to provide a stability enhancing unit capable of maintaining a stable flight attitude even when disturbance or gusts occur during flight, and a tilt rotor aircraft including the same.

According to a preferred embodiment of the present invention for achieving the above object of the present invention, the stability enhancing unit mounted to the vehicle for the flight stability of the present invention includes a momentum wheel and sensor unit.

The momentum wheel is mounted on one side of the vehicle, and the sensor unit detects the movement of the vehicle and transmits the sensing signal to the momentum wheel to drive the same. The stability augmentation unit detects the sensor unit and transmits a detection signal to the momentum wheel when the flight state becomes unstable due to posture change or disturbance of the aircraft, and the momentum wheel is unstable. By generating a moment that can reduce the flight state can be made to allow the aircraft to fly stably. Such a vehicle is a tilt rotor aircraft, but is not limited thereto.

The air vehicle may include a fixed wing unit and a rotary wing unit, and the sensor unit may operate the momentum wheel according to the flight mode to be converted when the mutual flight mode is converted between the fixed wing unit and the rotary wing unit to ensure flight stability. Can be maintained.

In addition, the tilt rotor aircraft of the present invention includes a body, a fixed wing unit, a rotary wing unit and a stability enhancing unit. The body is formed streamlined against drag. The fixed blade unit and the rotary blade unit is formed on both sides or the rear of the body to provide the lifting force to raise the body in the air and the thrust to move forward or backward. The safety enhancement unit includes a sensor unit for detecting the flight mode conversion and disturbance, a transmission unit for transmitting a signal of the sensor unit, and a momentum wheel connected to one side of the transmission unit and driving in response to the flight mode conversion and disturbance. .

The moment wheel may include a main body portion having an open upper portion, a cover portion for opening and closing an upper portion of the main body portion, a circuit portion stored inside the main body portion to sense a signal of the transmission portion, and a wheel portion rotating at a predetermined angular speed by the circuit portion. The tilt rotor may be returned to a normal flight state from an unstable flight state generated by the flight mode conversion and disturbance by the moment generated due to the rotation of the wheel unit.

The flight mode refers to a transition flight mode for converting from the rotary wing unit mode to the adjustment wing unit mode and a reverse transition flight mode for converting from the fixed wing unit mode to the rotation wing unit mode.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, but the present invention is not limited or limited by the embodiments.

1 is a side view showing a tilt rotor aircraft equipped with a stability enhancing unit of the present invention, Figure 2 is a front view showing a tilt rotor aircraft equipped with a stability enhancing unit of the present invention, Figure 3 is a stability enhancing unit of the present invention A perspective view of a momentum wheel.

As shown therein, the tilt rotor aircraft 100 includes a body 110, a fixed wing unit 120, a rotary wing unit 130 and a stability enhancing unit.

The body 110 is a place where each part of the tilt rotor aircraft 100 is coupled, it can be equipped with a cockpit and other equipment. The surface of the body 110 is designed in a streamlined form to minimize the resistance of the air, the cockpit arrangement can be divided into a front and rear double seats installed in the front and rear daughter in the model and left and right double seats mounted to the left and right. The body 110 may be mainly made of aluminum alloy, glass fiber or the like to strengthen the internal strength, light weight, and also minimize the resistance of the air. In addition, the skeleton structure of the body 110 can be strengthened by harmonizing the truss and monocoque structure. A landing unit (not shown) may be formed below the body 110 to safely land the tilt rotor aircraft 100.

The fixed wing unit 120 is formed on both sides of the body 110 to provide a lift so that the tilt rotor aircraft 100 can be supported in response to gravity. The rotary blade unit 130 is formed on both sides of the body 110, and has a rotary blade connected to the engine and the engine, respectively, to provide a thrust corresponding to the drag force of the tilt rotor aircraft 100.

The stability augmentation unit includes a sensor unit (not shown), a transmission unit (not shown) and a momentum wheel 140, the tilt rotor aircraft 100 converts the flight mode, or the disturbance to the tilt rotor aircraft 100 It can maintain flight stability when it occurs.

The sensor unit detects when the tilt rotor aircraft 100 deviates from the normal movement due to the conversion of the flight mode or the occurrence of disturbance, and generates a detection signal, and the transmitter transmits the detection signal to the momentum wheel 140. And transmits the momentum wheel 140.

The momentum wheel 140 is mounted such that the plane of the momentum wheel 140 is perpendicular to the y axis to increase stability of the pitch axis of the tilt rotor aircraft 100. Provide moments to maintain normal flight conditions.

In addition, even when the tilt rotor aircraft 100 is unstable with respect to the yaw axis or the roll axis, the momentum wheel 140 may correct the instability.

The momentum wheel 140 includes a main body portion 144 having an open upper portion, a cover portion 142 covering the main body portion 144, a circuit portion 146 stored in the main body portion 144, and the circuit portion 146. It includes a wheel part (not shown) that rotates by). The circuit unit 146 may receive the detection signal of the transmission unit, and the wheel unit (not shown) may rotate by the circuit unit 146.

The mechanism to maintain the flight stability of the tilt rotor aircraft 100 by the momentum wheel 140. 4 is shown.

4 is a conceptual view illustrating the operation of the stability enhancing unit of the present invention.

As shown in the drawing, the wheel part of the momentum wheel rotating at a constant angular velocity rotates at an angular acceleration in proportion to the pitch angular velocity of the tilt rotor. Create a moment that can be. If this is expressed as an equation, Equation 1 is obtained.

 to be.

은 불안정한 피치자세를 잡기 위한 모멘트이고, I 는 모멘텀 휠의 관성모멘트이고,

는 모멘텀 휠의 각가속도이다. 그리고, q 는 항공기의 피치각속도이며, -K는 q에 따른 보정변수이다.remind

Is the moment for catching the unstable pitch, I is the moment of inertia of the momentum wheel,

Is the angular acceleration of the momentum wheel. And, q is the pitch angular velocity of the aircraft, -K is a correction variable according to q.

)의 반대방향으로 작용하여 감쇠비에 영향을 미친다. 또한, 상기 항공기의 피치각속도(q)가 q에서 q + △q만큼 변할 때 상기 모멘텀 휠의 각가속도(

)가

에서

+ △

가 변화하여 불안정한 비행상태를 안정적인 비행상태로 변화시키기 위한 모멘트를 제공한다. 이와 같이, 불필요한 항공기의 운동을 감지하고, 그 운동에 저항하도록 조종면이 움직이도록 피드백하여 항공기의 단주기 동특성 모드를 개선할 수 있다.As in Equation 1, the aircraft angular velocity q is the angular acceleration velocity of the momentum wheel

It works in the opposite direction of), affecting the damping ratio. Further, when the pitch angular velocity q of the aircraft varies from q to q + Δq, the angular acceleration of the momentum wheel (

)end

in

+ △

Is changed to provide a moment to change from an unstable flight to a stable flight. As such, it is possible to improve the short-period dynamic mode of the aircraft by detecting unnecessary movement of the aircraft and feeding back the steering surface to resist the movement.

Therefore, according to the present invention, when the tilt rotor aircraft converts the attitude, by detecting this to drive the momentum wheel, there is an effect that can return to the unstable flight state at the time of attitude change to the normal flight state.

In addition, if the tilt rotor is out of the normal flight mode due to the occurrence of disturbance during flight, it is possible to increase the short period damping by changing the rotational angular velocity of the wheel of the momentum wheel for the unstable flight mode, thereby ensuring robustness against disturbance. It can be effective.

As described above, although described with reference to the preferred embodiment of the present invention, those skilled in the art various modifications and variations of the present invention without departing from the spirit and scope of the invention described in the claims below I can understand that you can.

Claims (7)

In the stability enhancing unit mounted on the aircraft for flight stability, A momentum wheel mounted on one side of the vehicle; And A sensor unit which detects a movement of the vehicle and transmits and drives a detection signal to the momentum wheel; Including, but when the flight is unstable flight due to posture change or the occurrence of disturbance to the aircraft, the sensor unit detects this and transmits a detection signal to the momentum wheel, the momentum wheel is unstable flight Generates moments that can be reduced to promote flight stability of the vehicle, The momentum wheel may be rotated at a predetermined angular speed by a body part having an open top, a cover part which opens and closes an upper part of the body part, a circuit part stored in the body part and detecting a detection signal from the sensor part, and the circuit part. Stability enhancing unit characterized in that it comprises a wheel portion. The method of claim 1, The vehicle is a stability enhancing unit, characterized in that the tilt rotor aircraft. The method of claim 1, The aircraft has a fixed wing unit and a rotary wing unit, wherein the sensor unit when the mutual flight mode conversion between the fixed wing unit and the rotary wing unit, the momentum wheel according to the flight mode is converted stability Reinforcement unit. Body; Rotating blade unit and fixed wing unit provided on the left and right sides of the body; And A stability enhancing unit mounted on one side of the body; Includes, the stability enhancing unit to promote flight stability when the conversion and disturbance of the flight mode, The stability enhancing unit, the sensor unit for detecting the flight mode conversion and disturbance, a transmission unit for transmitting the signal of the sensor, and a momentum wheel connected to one side of the transmission unit to drive in response to the flight mode conversion and disturbance Equipped, The momentum wheel may include a main body part having an open upper portion, a cover part for opening and closing an upper part of the main body part, a circuit part stored in the main body part to sense a signal of the transmission part, and a wheel part rotating at a predetermined angular speed by the circuit part. And a tilt rotor that is capable of returning to a normal flight state from an unstable flight state generated by the flight mode conversion and disturbance due to a moment generated due to the rotation of the wheel unit. delete delete The method of claim 4, wherein The flight mode is A transition mode for switching from the rotary blade unit mode to the fixed blade unit mode; And A reverse transition mode for converting the fixed blade unit mode into the rotary blade unit mode; Tilt rotor aircraft comprising a.

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