KR0129614B1 - A reduction device of the initial acceleration for an aircraft - Google Patents
A reduction device of the initial acceleration for an aircraftInfo
- Publication number
- KR0129614B1 KR0129614B1 KR1019940036641A KR19940036641A KR0129614B1 KR 0129614 B1 KR0129614 B1 KR 0129614B1 KR 1019940036641 A KR1019940036641 A KR 1019940036641A KR 19940036641 A KR19940036641 A KR 19940036641A KR 0129614 B1 KR0129614 B1 KR 0129614B1
- Authority
- KR
- South Korea
- Prior art keywords
- vehicle
- flow control
- power cylinder
- initial
- drain line
- Prior art date
Links
- 230000001133 acceleration Effects 0.000 title claims abstract description 16
- 238000013016 damping Methods 0.000 claims abstract description 15
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 3
- 229910001873 dinitrogen Inorganic materials 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 230000007257 malfunction Effects 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B13/00—Details of servomotor systems ; Valves for servomotor systems
- F15B13/02—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors
- F15B13/04—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with a single servomotor
- F15B13/0401—Valve members; Fluid interconnections therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
- F15B15/08—Characterised by the construction of the motor unit
- F15B15/14—Characterised by the construction of the motor unit of the straight-cylinder type
- F15B15/1423—Component parts; Constructional details
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B2211/00—Circuits for servomotor systems
- F15B2211/70—Output members, e.g. hydraulic motors or cylinders or control therefor
- F15B2211/705—Output members, e.g. hydraulic motors or cylinders or control therefor characterised by the type of output members or actuators
- F15B2211/7051—Linear output members
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/023—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means
- F16F15/027—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means comprising control arrangements
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
Description
제1도는 종래 기술에 의한 무인비행체 발사장치의 회로도로서 초기 가속도 감쇄장치가 없는 무인항공기 발사장치이다.1 is a circuit diagram of a prior art unmanned aerial vehicle launch apparatus, which is an unmanned aerial vehicle launch apparatus without an initial acceleration damping apparatus.
제2도는 본 발명의 실시예에 의한 무인비행체의 회로도로서 파워실린더 헤드블록에 초기 유량제어장치를 부착한 무인항공기 발사장치이다.2 is a circuit diagram of an unmanned aerial vehicle according to an embodiment of the present invention, which is an unmanned aerial vehicle launch apparatus having an initial flow rate control device attached to a power cylinder head block.
본 발명은 무인항공기 발사대에서 비행체의 발사초기에 과도한 가속에 의해 발생되는 진동을 감쇄시켜 비행체의 발사시 비행체 구조 및 탑재된 전자장비에 무리하게 전달되는 충격적인 진동을 효과적으로 감쇄시킬 수 있도록 하는 비행체의 초기가속도 감쇄장치에 관한 것이다.The present invention is the initial of the aircraft to attenuate the vibration caused by excessive acceleration at the early launch of the aircraft in the unmanned aerial vehicle launch platform to effectively attenuate the shock vibration transmitted to the structure and mounted electronic equipment when the aircraft is launched An acceleration damping device.
종래의 무인항공이 발사장치는 제1도에 도시된 바와 같이 발사장치 주 구조물(10)과 구조물(10)상에서 전후 이동이 가능하게 설치되는 운반차(12)와 운반차(12)에 이탈 가능하게 탑재되는 비행체(도시생략)와 운반차(12)를 구조물(10)상에 록킹시키는 록킹장치(14), 그리고 운반차(12)를 정지시키는 운반차 정지장치(도시생략)와, 운반차(12)의 전면과 연결된 견인용 와이어 로프(16)가 가속장치(18)와 연결되고 이 가속장치(18)의 일측이 견인용 파워실린더(20)와 연결되며, 이 파워 실린더(20)의 헤드에는 드레인라인(21)이 설치되고, 오일충진용 유압 펌프(22)와 오일충진용 밸브(24)를 통해 작동유압이 공급되며, 파워 실린더(20)의 양측에는 질소가스 어큐뮬레이터(26)가 설치되어 구성된다.The conventional unmanned aerial vehicle launch device is detachable from the transport vehicle 12 and the transport vehicle 12 which are installed to be moved back and forth on the launch device main structure 10 and the structure 10, as shown in FIG. The vehicle 14 (not shown) and the locking device 14 which locks the transport vehicle 12 on the structure 10, The transport vehicle stop device (not shown) which stops the transport vehicle 12, and a transport vehicle Towing wire rope 16 connected to the front of the (12) is connected to the accelerator 18, one side of the accelerator 18 is connected to the traction power cylinder 20, the power cylinder (20) The head is provided with a drain line 21, the hydraulic pressure is supplied through the oil filling hydraulic pump 22 and the oil filling valve 24, and nitrogen gas accumulator 26 is provided on both sides of the power cylinder 20. Installed and configured.
상기와 같이 구성된 종래의 무인항공기 발사장치에 의하면 비행체를 탑재한 운반차(12)가 록킹장치(14)에 의해 록킹된 상태이고, 도 파워실린더(20)는 가속장치(18)를 통하여 와이어 로프(16)로 연결된 운반차(12)에 계속해서 견인을 가하고 있는 상태에 있다. 즉, 비행체의 발사대기 상태에서 파워실린더(20)의 피스톤 로드부에 작용하는 유압에 의해 견인력이 발생되어 가속장치(18)와 운반차(12) 사이에 연결된 와이어 로프(16)는 약 20mm가 늘어나게 되어 발사시 순간적으로 록킹장치(14)를 해제시키면 와이어 로프(16)는 스프링현상에 의한 탄성에너지 및 견인력에 의하여 운반차(12)는 순간적인 가속력이 20g이상 발생되게 된다. 이때 파워실린더(20)의 헤드부에 드레인라인(21)만 설치되어 있기 때문에 초기에 발생되는 과도한 가속도를 감쇄시킬 수 없어 비행체의 구조 및 비행체에 탑재된 전자장비에 무리한 힘이 전달되어 비행체의 파손 및 전자장비에 오동작의 원인을 제공하게 된다.According to the conventional unmanned aerial vehicle launch apparatus configured as described above, the vehicle 12 on which the vehicle is mounted is locked by the locking device 14, and the power cylinder 20 is connected to the wire rope through the accelerator 18. Traction is continuously applied to the transport vehicle 12 connected by (16). That is, the traction force is generated by the hydraulic pressure acting on the piston rod of the power cylinder 20 in the standby state of the vehicle, the wire rope 16 connected between the accelerator 18 and the vehicle 12 is about 20 mm When the momentary release of the locking device 14 at launch, the wire rope 16 is generated by the momentary acceleration force of 20g or more due to the elastic energy and the traction force of the spring phenomenon. At this time, since only the drain line 21 is installed in the head of the power cylinder 20, excessive acceleration generated at the initial stage cannot be attenuated, and excessive force is transmitted to the structure of the aircraft and the electronic equipment mounted on the aircraft, resulting in damage to the aircraft. And provide the cause of malfunction to the electronic equipment.
본 발명의 상기와 같은 종래 기술의 문제점을 해결하기 위해 창안된 것으로, 그 목적은 무인항공기를 발사대에서 발사기 발사초기에 발생되는 과도한 가속도를 제어하여 비행체 구조물의 파손 및 전자장비의 오동작을 방지할 수 있도록 하는 비행체의 초기가속도 감쇄장치를 제공하는 데 있다.In order to solve the problems of the prior art as described above of the present invention, the object is to control the excessive acceleration generated during the initial launch of the launcher from the unmanned aerial vehicle to prevent damage to the aircraft structure and malfunction of the electronic equipment An early acceleration damping device for a vehicle is provided.
상기의 목적을 실현하기 위한 본 발명은 파워실린더의 드레인유량을 제어하는 헤드블록과, 초기의 오일유출을 막아주는 유량조절 바와, 상기 유량조절 바의 속도를 제어하는 유량 조절밸브와, 상기 유량조절바를 제어하는 댐핑실린더와, 댐핑실린더의 초기화를 위한 제어용 솔레노이드밸브, 파이롯트 체크밸브, 유량조절밸브로 구성한 것이다.The present invention for realizing the above object is a head block for controlling the drain flow rate of the power cylinder, a flow control bar for preventing the initial oil outflow, a flow control valve for controlling the speed of the flow control bar, and the flow control It consists of a damping cylinder for controlling the bar, a solenoid valve for controlling the damping cylinder, a pilot check valve, and a flow control valve.
이하, 본 발명의 바람직한 실시예를 첨부된 도면에 의해 상세히 설명하면 다음과 같다.Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.
제2도는 본 발명의 실시예에 의한 무인비행체의 회로도로서 파워실린더 헤드블록에 초기 유량제어장치를 부착한 무인항공기 발사장치를 도시한 것으로, 본 발명의 설명에서 종래와 동일 또는 동등한 부분은 같은 도면부호로 표기하여 설명한다.2 is a circuit diagram of an unmanned aerial vehicle according to an exemplary embodiment of the present invention, which shows an unmanned aerial vehicle launch apparatus having an initial flow control device attached to a power cylinder head block. It describes by making a code | symbol.
도시된 바와 같이 발사장치 주 구조물(10)과 구조물(10)상에서 전후 이동이 가능하게 설치되는 운반차(12)와 운반차(12)에 이탈가능하게 탑재되는 비행체(도시생략)와 운반차(12)를 구조물(10)상에 록킹시키는 록킹장치(14), 그리고 운반차(12)를 정지시키는 운반차 정치장치(도시생략)와, 운반차(12)의 전면과 연결된 견인용 와이어 로프(16)가 가속장치(18)와 연결되고 이 가속장치(18)의 일측이 견인용 파워실린더(20)와 연결되며, 이 파워실린더(20)의 헤드에는 드레인라인(21)이 설치되고, 오일층진용 유압펌프(22)와 오일층진용 밸브(24)를 통해 작동유압이 공급되며, 파워실린더(20)의 양측에는 질소가스 어큐뮬레이터(26)가 설치된 발사장치에 있어서, 파워실린더(20)의 드레인유량을 제어하기 위해 헤드블록(28)에 테이퍼 홀(28a)을 형성하고, 이 헤드블록(28)의 홀(28a)에 초기 오일유출을 막아주는 유량조절 바(30)가 상기 테이퍼 홀(28a)과 대응되는 테이퍼를 갖도록 형성하고, 상기 유량조절 바(30)의 속도를 제어하는 유량조절밸브(32)를 형성하고, 이 유량조절밸브(32)와 연결되어 유량조절 바(30)를 제어하는 댐핑실린더(34)를 형성하고, 이 댐핑실린더(34)를 초기화시키기 위해 제어용 솔레노이드밸브(36), 파이롯트 체크밸브(38)및 유량조절밸브(40)를 구성한 것이다.As shown, a vehicle (not shown) and a vehicle (not shown) detachably mounted to the vehicle 12 and the vehicle 12 that are installed to be movable back and forth on the main structure 10 and the structure 10 of the launch device ( Locking device 14 for locking the 12 on the structure 10, and the carrier stationary device (not shown) for stopping the transport vehicle 12, and a wire rope for towing connected to the front surface of the transport vehicle 12 ( 16 is connected to the accelerator 18, one side of the accelerator 18 is connected to the traction power cylinder 20, the drain line 21 is installed on the head of the power cylinder 20, oil The hydraulic pressure is supplied through the laminar hydraulic pump 22 and the oil laminar valve 24, and both sides of the power cylinder 20 are provided with a nitrogen gas accumulator 26 on the side of the power cylinder 20. A tapered hole 28a is formed in the head block 28 to control the drain flow rate, and the hole 28a of the head block 28 is formed. The flow rate control bar 30 to prevent the initial oil outflow is formed to have a taper corresponding to the taper hole 28a, and to form a flow rate control valve 32 for controlling the speed of the flow rate control bar 30, It is connected to the flow regulating valve 32 to form a damping cylinder 34 for controlling the flow regulating bar 30, the control solenoid valve 36, the pilot check valve 38 to initialize the damping cylinder 34 ) And the flow control valve 40.
상기와 같이 구성된 본 발명에 의하면 비행체를 발사 대기상태에서 비행체의 발사를 위해 운반차 록킹 장치(14)를 해제시키면 와이어 로프(16)에 저장된 탄성에너지가 견인력에 부과되어 과도한 가속도가 발생되는데, 이때 파워실린더(20)의 헤드블록(28)에 가공된 드레인 라인(21)용 홀(28a)을 테이퍼로 하고 그 테이퍼부에 대응하는 유량조절 바(30)에 의하여 드레인라인(21)은 막혀 있어 과도하게 후진하는 피스톤 로드(23)의 속도가 제어된다.이후 파워실린더(20)의 로드(23) 측으로 가해지는 유압에 의해 헤드블록(28)측의 오일을 가압하여 드레인라인(21)을 차단하고 있던 유량조절 바(30)를 밀어내게 되며, 이때 유량조절 바(30)의 밀리는 속도는 댐핑실린더(34)와 연결된 유량 조절밸브(32)에 의해 제어되면서 드레인라인(21)이 열리기 시작한다. 이후, 드레인라인(21)이 완전히 열리면 피스톤 전면에 작용하는 유압에 의해 규정된 속도로 파워실린더(20)는 운반차(12)를 가속시켜 이륙속도에 이르게 된다. 상기와 같이 유량조절 바(30)는 발사초기의 와이어 로프(16) 탄성에너지가 소멸되는 시점에 맞추어 드레인라인(21)을 완전히 개방시키는 역할을 하게 되어 결국 발사초기에 막혀 있던 드레인라인(21)이 파워실린더 피스톤의 충격적인 밀림현상을 방지하여 발사초기에 발생되는 초기가속도에 따른 비행체의 진동을 감쇄시키는 결과를 얻게 되는 것이다.According to the present invention configured as described above, when the vehicle locking device 14 is released for the launch of the vehicle in the standby state of launching the vehicle, elastic energy stored in the wire rope 16 is applied to the traction force, and excessive acceleration occurs. The hole 28a for the drain line 21 machined in the head block 28 of the power cylinder 20 is tapered, and the drain line 21 is blocked by the flow control bar 30 corresponding to the tapered portion. The speed of the piston rod 23 which is excessively reversed is controlled. Thereafter, the oil on the head block 28 side is pressurized by the hydraulic pressure applied to the rod 23 side of the power cylinder 20 to block the drain line 21. When the flow control bar 30 is pushed out, the pushing speed of the flow control bar 30 is controlled by the flow control valve 32 connected to the damping cylinder 34 and the drain line 21 starts to open. . Thereafter, when the drain line 21 is completely opened, the power cylinder 20 accelerates the transport vehicle 12 at the speed defined by the hydraulic pressure acting on the piston front to reach the take-off speed. As described above, the flow control bar 30 plays a role of completely opening the drain line 21 at the time when the wire rope 16 elastic energy of the initial launch is dissipated, so that the drain line 21 was blocked at the initial launch. The shock cylinder of the power cylinder piston is prevented to achieve the result of attenuating the vibration of the vehicle according to the initial acceleration generated at the initial launch.
상기와 같이 비행체의 발사가 완료되면 초기화(Reset)를 위해 제어용 솔레노이드밸브(36)가 작동되어 댐핑실린더(34)에 오일이 공급되면서 유량조절 바(30)를 전진시켜 헤드블록(28)의 홀(28a)을 막아 드레인라인(21)을 블록킹시킨다. 이와 같이 드레인라인(21)의 블록킹이 완료되면 댐핑실린더(34)에는 더이상 오일이 공급되지 않고, 이때부터 발사를 시행할 때까지 파이롯트 체크밸브(38)에 의하여 블록킹되어 유량조절 바(30)는 파워실린더(20) 헤드측의 유압에 의해서만 작동된다.When the launching of the vehicle is completed as described above, the control solenoid valve 36 is operated to reset, and the oil is supplied to the damping cylinder 34 to move the flow control bar 30 to advance the hole of the head block 28. The drain line 21 is blocked by blocking the 28a. When the blocking of the drain line 21 is completed as described above, the damping cylinder 34 is no longer supplied with oil. From this time, the flow check bar 30 is blocked by the pilot check valve 38 until firing is performed. Power cylinder 20 is operated only by the hydraulic pressure on the head side.
이상에서 설명한 바와 같이 본 발명의 비행체의 초기가속도 감쇄장치에 의하여 초기가속도에 의한 비행체의 구조 및 전자장비의 오동작을 방지할 수 있어 비행안전 및 비행체 내구성향상과 운반차의 내구성향상 등의 효과를 얻을 수 있다.As described above, it is possible to prevent malfunction of the structure and electronic equipment by the initial acceleration by the initial acceleration damping device of the aircraft of the present invention, and thus the effects of flight safety, aircraft durability, and durability of the vehicle can be obtained. Can be.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR1019940036641A KR0129614B1 (en) | 1994-12-24 | 1994-12-24 | A reduction device of the initial acceleration for an aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR1019940036641A KR0129614B1 (en) | 1994-12-24 | 1994-12-24 | A reduction device of the initial acceleration for an aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| KR960022161A KR960022161A (en) | 1996-07-18 |
| KR0129614B1 true KR0129614B1 (en) | 1998-04-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| KR1019940036641A KR0129614B1 (en) | 1994-12-24 | 1994-12-24 | A reduction device of the initial acceleration for an aircraft |
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| Country | Link |
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| KR (1) | KR0129614B1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103661972A (en) * | 2013-11-12 | 2014-03-26 | 南京航空航天大学 | Plane traction rod with hydraulic buffer type overload protection function |
-
1994
- 1994-12-24 KR KR1019940036641A patent/KR0129614B1/en not_active IP Right Cessation
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103661972A (en) * | 2013-11-12 | 2014-03-26 | 南京航空航天大学 | Plane traction rod with hydraulic buffer type overload protection function |
| CN103661972B (en) * | 2013-11-12 | 2015-10-28 | 南京航空航天大学 | Plane traction rod with hydraulic buffer type overload protection function |
Also Published As
| Publication number | Publication date |
|---|---|
| KR960022161A (en) | 1996-07-18 |
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