KR100553378B1 - Front rudder of aircraft - Google Patents

Front rudder of aircraft Download PDF

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Publication number
KR100553378B1
KR100553378B1 KR1020040101148A KR20040101148A KR100553378B1 KR 100553378 B1 KR100553378 B1 KR 100553378B1 KR 1020040101148 A KR1020040101148 A KR 1020040101148A KR 20040101148 A KR20040101148 A KR 20040101148A KR 100553378 B1 KR100553378 B1 KR 100553378B1
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KR
South Korea
Prior art keywords
aircraft
rudder
front wheel
landing device
wheel landing
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KR1020040101148A
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Korean (ko)
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성기정
권태희
안석민
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한국항공우주연구원
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Steering Devices For Bicycles And Motorcycles (AREA)

Abstract

본 발명은 항공기용 전방 방향타에 관한 것으로서, 특히 항공기용 방향타에 있어서, 상기 방향타는, 유선형의 날개 단면 형상으로 내부가 빈 형태로 형성되고, 앞바퀴가 좌우로 조향 가능하도록 설치된 항공기의 고정식 앞바퀴 착륙장치에 결합 가능하도록 상면에 고정식 앞바퀴 착륙장치가 관통되는 원형 홀이 형성되고, 저면에 앞바퀴와의 간섭을 피하도록 사각형 홀이 형성되어 항공기 전방에 위치한 고정식 앞바퀴 착륙장치에 설치되는 것을 특징으로 한다.BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a front rudder for aircraft, and in particular, for a rudder for aircraft, the rudder is formed in a hollow shape with a streamlined wing cross-section, and the fixed front wheel landing device of the aircraft installed so that the front wheel can be steered from side to side. A circular hole through which the fixed front wheel landing device penetrates is formed on the upper surface to be coupled to the upper surface, and a rectangular hole is formed on the bottom surface to prevent interference with the front wheel and is installed on the fixed front wheel landing device located in front of the aircraft.

상기와 같은 본 발명에 따르면 방향타를 무게 중심보다 앞쪽인 고정식 앞바퀴 착륙장치에 설치하고, 앞바퀴의 조향각과 동일한 회전 각도로 회전되도록 설치함으로써 동일한 방향타의 표면적으로 상대적으로 높은 조정력을 제공하고, 조정 계통을 단순화시킴으로써 항공기의 신뢰성을 향상시키고, 조종 계통의 부품수를 줄여 항공기의 무게를 줄임으로써 항공기의 성능을 향상시킬 수 있다.According to the present invention as described above by installing the rudder in the fixed front wheel landing device that is ahead of the center of gravity, installed to rotate at the same rotation angle as the steering angle of the front wheel to provide a relatively high adjustment of the surface area of the same rudder, and adjust the adjustment system Simplification can improve the reliability of the aircraft and reduce the weight of the aircraft by reducing the number of parts in the control system, thereby improving the performance of the aircraft.

항공기, 방향타, 앞바퀴 착륙장치, 수직꼬리날개, 작동발판Aircraft, Rudder, Front Wheel Landing Gear

Description

항공기용 전방 방향타{Front rudder of aircraft}Front rudder of aircraft

도 1은 본 발명에 따른 항공기용 전방 방향타의 구성을 나타낸 사시도,1 is a perspective view showing the configuration of a front rudder for an aircraft according to the present invention;

도 2는 도 1의 저면도,2 is a bottom view of FIG. 1;

도 3은 본 발명에 따른 항공기용 전방 방향타의 측단면도,3 is a side cross-sectional view of a front rudder for an aircraft according to the present invention;

도 4는 본 발명에 따른 항공기용 전방 방향타가 항공기에 부착된 모습을 나타낸 사시도,4 is a perspective view showing a state in which the front rudder for the aircraft according to the present invention is attached to the aircraft,

도 5는 본 발명에 따른 항공기용 전방 방향타가 항공기에 부착된 상태에서의 단면도.5 is a cross-sectional view of a front rudder for an aircraft according to the present invention attached to an aircraft;

<도면의 주요 부분에 관한 부호의 설명><Explanation of symbols on main parts of the drawings>

10 : 항공기 11 : 고정식 앞바퀴 착륙장치10: aircraft 11: fixed front wheel landing gear

13 : 버팀대 15 : 앞바퀴13: prop 15: front wheel

19 : 원형 플랜지 100 : 방향타19: circular flange 100: rudder

110 : 원형 홀 120 : 사각형 홀110: round hole 120: square hole

130 : 플랜지 결합부재 131 : 홀130: flange coupling member 131: hole

133 : 볼트홀133: bolt hole

본 발명은 항공기용 전방 방향타에 관한 것으로서, 상세하게는 방향타를 고정식 앞바퀴 착륙장치에서 앞바퀴의 조향각과 동일한 회전 각도로 회전되도록 설치함으로써 항공기의 성능을 향상시키도록 하는 항공기용 전방 방향타에 관한 것이다.The present invention relates to a front rudder for an aircraft, and more particularly, to a front rudder for an aircraft to improve the performance of the aircraft by installing the rudder to be rotated at the same rotation angle as the steering angle of the front wheel in the fixed front wheel landing device.

현재까지 개발된 항공기들은 수직꼬리날개와 방향타를 항공기의 후미나 후미의 역할을 하는 부분에 장착하여 가로방향 안정성과 조정성을 도모하였다.The aircrafts developed so far have been equipped with vertical tails and rudders on the aircraft's rear and rear parts to achieve lateral stability and control.

방향타란 항공기의 수직꼬리날개에 설치되어 항공기의 기수를 좌측 또는 우측으로 방향 전환시켜 주는 것으로, 조정사가 작동 발판을 이용하여 제어하게 되어 있다.Rudder is installed on the vertical wing of the aircraft to change the aircraft's nose to the left or right, the coordinator is to control by using the operation scaffold.

그러나, 이러한 방향타는 수직꼬리날개에 장착되기 때문에 항공기의 무게 중심 뒤쪽에서 가로 안전성과 조정성을 확보하였다. 이로 인하여 방향타 조정을 위한 장치들이 조정석의 작동 발판으로부터 방향타까지 연결되어야 하는 데, 연결 과정에 들어가는 부품들이 많아 항공기 중량의 한 부분을 이루고, 연결이 길어질수록 연결 부품들이 증가되고, 구조가 복잡해져 신뢰성에 문제가 발생한다.However, these rudders are mounted on the vertical tail wing, ensuring transverse safety and adjustability behind the aircraft's center of gravity. Due to this, the devices for rudder adjustment must be connected from the operating step of the cockpit to the rudder, and there are many parts involved in the connection process, making up a part of the weight of the aircraft. A problem arises.

따라서, 본 발명은 상기와 같은 문제점을 해결하기 위한 것으로, 방향타를 무게 중심보다 앞쪽인 고정식 앞바퀴 착륙장치의 버팀대에 설치하고, 앞바퀴의 조향각과 동일한 회전 각도로 회전되도록 설치함으로써 동일한 방향타의 표면적으로 상대적으로 높은 조정력을 제공하고, 조정 계통을 단순화시킴으로써 항공기의 신뢰 성을 향상시키고, 조종 계통의 부품수를 줄여 항공기의 무게를 줄임으로써 항공기의 성능을 향상시키도록 하는 데 그 목적이 있다.Accordingly, the present invention is to solve the above problems, the rudder is installed in the brace of the fixed front wheel landing device that is ahead of the center of gravity, and installed so as to rotate at the same rotation angle as the steering angle of the front wheel relative to the surface area of the same rudder The aim is to improve aircraft performance by providing high coordination, simplifying the coordination system and improving aircraft reliability and reducing aircraft weight by reducing the number of components in the control system.

또한, 본 발명은 방향타가 전방에 있을 경우 항공기의 안정성이 낮아지게 되므로 항공기 후방의 수직꼬리날개에 의해 안정성을 도모하는 데 그 목적이 있다.In addition, the present invention is intended to achieve stability by the vertical tail of the rear of the aircraft since the stability of the aircraft is lowered when the rudder is in the front.

상기와 같은 목적을 달성하기 위한 본 발명의 특징은, 항공기용 방향타에 있어서, 상기 방향타는, 유선형의 날개 단면 형상으로 내부가 빈 형태로 형성되고, 앞바퀴의 회전이 가능하도록 설치된 항공기의 고정식 앞바퀴 착륙장치의 버팀대에 결합 가능하도록 상면에 버팀대가 관통되는 원형 홀이 형성되고, 저면에 앞바퀴와의 간섭을 피하도록 사각형 홀이 형성되는 것을 특징으로 한다.A feature of the present invention for achieving the above object is, in the rudder for aircraft, the rudder is formed in a hollow shape in a streamlined wing cross-sectional shape, the fixed front wheel landing of the aircraft installed to enable the rotation of the front wheels. A circular hole through which the brace penetrates is formed on the upper surface to be coupled to the brace of the device, and a rectangular hole is formed on the bottom to avoid interference with the front wheel.

여기에서, 상기 고정식 앞바퀴 착륙장치의 버팀대는 회전부에 원형 플랜지가 결합된다.Here, the brace of the fixed front wheel landing device is coupled to a circular flange to the rotating portion.

여기에서 또한, 상기 방향타는 상기 버팀대의 회전부와 동일하게 회전되도록 내측면에 상기 원형 플랜지와 결합되는 플랜지 결합부재가 일체로 형성된다.Here, the rudder is integrally formed with a flange engaging member coupled to the circular flange on the inner side so as to rotate in the same way as the rotation of the brace.

이하, 본 발명에 따른 항공기용 전방 방향타의 구성을 첨부된 도면을 참조하여 상세하게 설명하면 다음과 같다.Hereinafter, the configuration of the front rudder for an aircraft according to the present invention will be described in detail with reference to the accompanying drawings.

도 1은 본 발명에 따른 항공기용 전방 방향타의 구성을 나타낸 사시도이고, 도 2는 도 1의 저면도이며, 도 3은 본 발명에 따른 항공기용 전방 방향타의 측단면도이며, 도 4는 본 발명에 따른 항공기용 전방 방향타가 항공기에 부착된 모습을 나타낸 사시도이며, 도 5는 본 발명에 따른 항공기용 전방 방향타가 항공기에 부착 된 상태에서의 단면도이다.1 is a perspective view showing the configuration of an aircraft front rudder according to the present invention, Figure 2 is a bottom view of Figure 1, Figure 3 is a side cross-sectional view of the aircraft front rudder according to the invention, Figure 4 is According to the present invention, the front rudder is a perspective view showing the state attached to the aircraft, and FIG.

도 1 내지 도 5를 참조하면, 본 발명에 따른 항공기용 전방 방향타(100)는, 유선형의 날개 단면 형상으로 내부가 빈 형태로 형성되고, 앞바퀴(15)가 좌우로 조향 가능하도록 설치된 항공기(10)의 고정식 앞바퀴 착륙장치(11)의 버팀대(13)에 결합 가능하도록 상면에 버팀대(13)가 관통되는 원형 홀(110)이 형성되고, 저면에 앞바퀴(15)의 조향에 간섭을 주지 않도록 사각형 홀(120)이 형성된다.1 to 5, the aircraft front rudder 100 according to the present invention has a streamlined wing cross-sectional shape, the inside of which is formed in an empty shape, and the front wheel 15 is installed so that the front wheel 15 can be steered left and right. A circular hole 110 through which the brace 13 penetrates is formed on the upper surface of the fixed front wheel landing device 11 so as to be coupled to the brace 13 of the fixed front wheel landing device 11, and a square so as not to interfere with the steering of the front wheel 15 on the bottom surface thereof. The hole 120 is formed.

또한, 방향타(100)는 버팀대(13)와 동일하게 회전되도록 내면에 버팀대(13)에 결합된 원형 플랜지(19)와 결합되는 판형태의 플랜지 결합부재(130)가 더 형성된다. 여기에서, 플랜지 결합부재(130)는 버팀대(13)가 관통되는 홀(131)을 구비하며, 홀(131) 주변에 원형 플랜지(19)의 볼트홀(19-1)과 볼트(20)로 결합 가능한 볼트홀(133)이 형성된다. 여기에서 또한, 플랜지 결합부재(130)는 버팀대(13)와, 앞바퀴(15)와의 간섭이 없도록 버팀대(13)의 형상에 맞추어 어떠한 형태로 변형이 가능하다.In addition, the rudder 100 is further formed with a plate-shaped flange coupling member 130 coupled to the circular flange 19 coupled to the brace 13 on the inner surface so as to rotate in the same way as the brace 13. Here, the flange coupling member 130 has a hole 131 through which the brace 13 passes, and the bolt hole 19-1 and the bolt 20 of the circular flange 19 around the hole 131. Combinable bolt holes 133 are formed. Here, the flange coupling member 130 may be deformed in any form to match the shape of the prop 13 so that there is no interference with the prop 13 and the front wheel 15.

이하, 본 발명에 따른 항공기용 전방 방향타의 동작 및 작용을 첨부된 도면을 참조하여 상세하게 설명하면 다음과 같다.Hereinafter, the operation and action of the front rudder for an aircraft according to the present invention will be described in detail with reference to the accompanying drawings.

먼저, 본 발명에 따른 항공기용 전방 방향타(100)는 항공기(10)의 고정식 앞바퀴 착륙장치(11)의 버팀대(13)에서 회전되도록 설치되는 데, 이때, 고정식 앞바퀴 착륙장치(11)의 버팀대(13)에 삽입한 상태에서, 버팀대(13)에 결합된 원형 플랜지(19)와 플랜지 결합부재(130)를 볼트(20)로 결합시킨다.First, the aircraft front rudder 100 according to the present invention is installed to rotate in the brace 13 of the fixed front wheel landing device 11 of the aircraft 10, at this time, the brace of the fixed front wheel landing device 11 In the state inserted into 13, the circular flange 19 and the flange coupling member 130 coupled to the brace 13 is coupled to the bolt (20).

또한, 방향타(100)는 앞바퀴(15)와 동일한 각도로 고정된다.In addition, the rudder 100 is fixed at the same angle as the front wheel 15.

이렇게 결합된 방향타(100)는 조종실의 작동발판(도시 생략)에 의해 작동되는 앞바퀴 착륙장치(11)의 조향에 따라 좌우로 회전 동작을 한다.The combined rudder 100 rotates left and right in accordance with the steering of the front wheel landing device 11 that is operated by the operating step (not shown) of the cockpit.

방향타(100)는 작동 발판이 중립일 때 동체의 길이 방향과 평행하게 정렬되고, 조종사가 항공기(10)를 좌/우 회전하기 위해서 앞바퀴(15)를 조향하면 방향타(100)도 앞바퀴(15)의 조향각과 동일한 방향 및 각도로 회전하게 된다. 이때 방향타(100)에서 발생하는 양력으로 비행중인 항공기(10)의 기수는 좌/우측으로 회전하게 된다.The rudder 100 is aligned parallel to the longitudinal direction of the fuselage when the operating foot is neutral, and when the pilot steers the front wheel 15 to rotate the aircraft 10 left / right, the rudder 100 is also the front wheel 15. It will rotate in the same direction and angle as the steering angle of. At this time, the nose of the aircraft 10 in flight with the lifting force generated in the rudder 100 is rotated to the left / right.

따라서, 항공기의 무게 중심보다 전방에 위치하는 조종면의 효과에 의해 가로 방향 조종력을 극대화시킬 수 있다.Therefore, it is possible to maximize the lateral control force by the effect of the control surface located ahead of the center of gravity of the aircraft.

상기와 같이 구성되는 본 발명인 항공기용 전방 방향타에 따르면, 방향타를 무게 중심보다 앞쪽인 고정식 앞바퀴 착륙장치의 버팀대에 설치하고, 앞바퀴의 조향각과 동일한 회전 각도로 회전되도록 설치함으로써 동일한 방향타의 표면적으로 상대적으로 높은 조정력을 제공하고, 조정 계통을 단순화시킴으로써 항공기의 신뢰성을 향상시키고, 조종 계통의 부품수를 줄여 항공기의 무게를 줄임으로써 항공기의 성능을 향상시킬 수 있다.According to the present invention the front rudder configured as described above, by installing the rudder in the brace of the fixed front wheel landing device that is ahead of the center of gravity, and installed to rotate at the same rotation angle as the steering angle of the front wheel relative to the surface area of the same rudder By providing high coordination, simplifying the coordination system, the aircraft's reliability can be improved, and the aircraft's performance can be improved by reducing the weight of the aircraft by reducing the number of parts in the control system.

또한, 본 발명은 고정식뿐만 아니라 인입식(Retractable) 착륙장치에도 적용가능한데, 이 경우에 파바퀴 착륙장치의 인입을 위한 구동장치를 제외할 수 있는 장점도 있다.In addition, the present invention can be applied to a retractable landing device as well as a fixed type, in which case there is an advantage in that the drive device for retracting the wheel landing device can be excluded.

Claims (3)

항공기용 방향타에 있어서,In rudder for aircraft, 상기 방향타는,The rudder, 유선형의 날개 단면 형상으로 내부가 빈 형태로 형성되고, 앞바퀴가 좌우로 조향 가능하도록 설치된 항공기의 고정식 앞바퀴 착륙장치의 버팀대에 결합 가능하도록 상면에 버팀대가 관통되는 원형 홀이 형성되고, 저면에 앞바퀴와의 간섭을 피하도록 사각형 홀이 형성되는 것을 특징으로 하는 항공기용 전방 방향타.It has a streamlined cross-section of the wing and is formed in an empty form, and a circular hole is formed on the upper surface so that the front wheel can be coupled to the prop of the fixed front wheel landing device of the aircraft installed so that the front wheel can be steered from side to side. The front rudder for the aircraft, characterized in that the rectangular hole is formed to avoid interference. 제 1 항에 있어서,The method of claim 1, 상기 고정식 앞바퀴 착륙장치의 버팀대는,The brace of the fixed front wheel landing device, 회전부에 원형 플랜지가 결합되는 것을 특징으로 하는 항공기용 전방 방향타.The front rudder for the aircraft, characterized in that the circular flange is coupled to the rotating portion. 제 2 항에 있어서,The method of claim 2, 상기 방향타는,The rudder, 상기 버팀대의 회전부와 동일하게 회전되도록 내측면에 상기 원형 플랜지와 결합되는 플랜지 결합부재가 일체로 형성되는 것을 특징으로 하는 항공기용 전방 방향타.The front rudder of the aircraft, characterized in that the flange engaging member coupled to the circular flange is integrally formed on the inner surface so as to rotate in the same way as the rotation of the brace.
KR1020040101148A 2004-12-03 2004-12-03 Front rudder of aircraft KR100553378B1 (en)

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Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH01285490A (en) * 1988-05-13 1989-11-16 Mitsubishi Heavy Ind Ltd Air control face used as wheel well door

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH01285490A (en) * 1988-05-13 1989-11-16 Mitsubishi Heavy Ind Ltd Air control face used as wheel well door

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