KR20030017148A - Rocket Onboard Safety Device for 2nd or 3rd Stage Ignition - Google Patents

Rocket Onboard Safety Device for 2nd or 3rd Stage Ignition Download PDF

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KR20030017148A
KR20030017148A KR1020010051305A KR20010051305A KR20030017148A KR 20030017148 A KR20030017148 A KR 20030017148A KR 1020010051305 A KR1020010051305 A KR 1020010051305A KR 20010051305 A KR20010051305 A KR 20010051305A KR 20030017148 A KR20030017148 A KR 20030017148A
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South Korea
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connector
ignition
stage
rocket
separation
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KR1020010051305A
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Korean (ko)
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KR100417005B1 (en
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이재득
이수진
이상래
김성완
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한국항공우주연구원
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Health & Medical Sciences (AREA)
  • Health & Medical Sciences (AREA)
  • Emergency Medicine (AREA)
  • Critical Care (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Details Of Connecting Devices For Male And Female Coupling (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)

Abstract

PURPOSE: An ignition safety device is provided to simplify the configuration of the device by eliminating the necessity of using a stage separation detection sensor and related hardware and software. CONSTITUTION: An ignition safety device comprises a stage separation connector(3) connected through two pins; a connector separation line(5) connected to the stage separation connector, which permits a plug(1) of the stage separation connector to be taken out when the stage separation is performed; a connector separation line fixing line(6) for fixing the connector separation line to an end of a rocket; a ground connected to the plug of the stage separation connector; an ignition box connected to a socket(2) of the stage separation connector; an ignition command output from an inertial navigation system and input to an input terminal of the ignition box; and a sequence controller for controlling the ignition command.

Description

로켓 탑재용 2단 또는 3단 추진기관 점화 안전 장치{Rocket Onboard Safety Device for 2nd or 3rd Stage Ignition}Rocket Onboard Safety Device for 2nd or 3rd Stage Ignition}

로켓 및 인공위성 발사체의 단 분리 후 점화되는 추진기관인 2단 또는 3단 추진기관 점화 안전 장치에 관한 것으로, 대부분의 다단 로켓이나 인공위성 발사체의 경우 1단은 지상의 점화장치에 의해 점화되어 비행을 시작하고 1단 연소가 종료되면 1단을 분리시키고 몇 초 동안의 시간 지연을 가진 후 탑재용 시퀀스 제어기(Sequence Controller)의 제어에 의한 점화 명령으로 2단 점화, 2단 연소가 종료되면 2단 분리 후 3단 추진기관을 점화하여 페이로드를 원하는 궤도에 올리게 된다.The present invention relates to a two-stage or three-stage propulsion engine ignition safety device, which is a propulsion engine that is ignited after stage separation of rockets and satellite projectiles. After the first stage combustion ends, separate the first stage and have a time delay for a few seconds.After the second stage ignition by the ignition command by the control of the onboard sequence controller, after the second stage combustion ends, separate the second stage.3 However, the propulsion engine is ignited and the payload is put on the desired track.

이때 2단 또는 3단 점화는 2단 또는 3단이 분리된 후에 시작되어야 하는데 그 이유는 단 분리가 되지 않은 상태에서 2단 또는 3단이 점화되면 추진기관의 노즐 부분이 막혀 있어서 추진기관 연소시 나오는 고압고온의 화염에 의해서 폭발하거나 추력방향이 틀어져 엉뚱한 방향으로 날아갈 수 있기 때문에 안전에 심각한 영향을 줄 수 있다.At this time, the 2nd or 3rd stage ignition should be started after the 2nd or 3rd stage is separated. If the 2nd or 3rd stage is ignited without the stage separation, the nozzle part of the propulsion engine is clogged. The high pressure and high temperature flames may explode or cause the thrust to be distorted and fly in the wrong direction, which may seriously affect safety.

통상적으로 2단 또는 3단 분리 및 점화는 탑재용 컴퓨터에 미리 시간을 프로그래밍하여 정해진 시간이 되면 무조건 이벤트를 수행하도록 하는 방법과 특정한 센서를 단 분리면에 설치하여 단 분리 여부를 확인한 후 특정시간이 되었을 때 점화를 수행하도록 하는 방법으로 분류할 수 있다.Normally, two-stage or three-stage separation and ignition are programmed to program the time in advance on the mounting computer so that the event can be performed unconditionally, and a specific sensor is installed on the stage separation surface to check whether the stage is disconnected. Can be classified in such a way as to allow ignition when performed.

후자의 방식은 전자의 방식에 비해 별도의 단 분리 확인용 센서와 이 신호를 처리할 수 있는 처리장치 등이 있어야 하는 단점이 있으나 주어진 시간이 되면 무조건 점화를 시키는 전자에 비해 훨씬 발사 안정성이 보장된다.The latter method has a disadvantage of having a separate stage separation sensor and a processing device capable of processing this signal, but the firing stability is much higher than that of the ignition unconditionally at a given time. .

우주 개발 선진국에서는 수많은 발사 시험과 실패 경험으로 많은 기술이 축적되어 신뢰도 높은 방식을 채택하고 있을 것으로 추정되나 로켓 관련 기술은 타국으로 기술이전을 극히 제한하고 있기 때문에 잘 알 수가 없다.It is estimated that a number of technologies have been accumulated and adopted in a highly reliable manner in the space-developed countries with many launch tests and failure experiences, but the rocket-related technologies are extremely unknown because they restrict the transfer of technology to other countries.

다만 추정으로는 변위계(Displacement) 센서와 같은 별도의 센서를 단 분리면에 부착하여 이 센서의 출력값을 기준으로 단 분리 여부를 확인하고 2단 또는 3단을 점화시키는 방식을 채용하고 있을 것으로 생각된다.However, it is assumed that a separate sensor such as a displacement sensor is attached to the stage separation surface to check whether the stage is separated based on the output value of the sensor, and to ignite two or three stages. .

이 경우 별도의 센서를 단 분리면에 부착하기 위한 공간과 이 센서에 필요한 바이어스 전원, 이 신호를 처리하는 하드웨어 및 소프트웨어 등이 추가되어야 하므로 소자의 고장 등에 의한 문제점이 고려된다.In this case, a space for attaching a separate sensor to a single separation surface, a bias power required for the sensor, hardware and software for processing the signal, and the like must be added, so that problems due to device failure are considered.

본 발명은 단 분리가 되면서 커넥터가 분리되는 푸쉬풀(Push Pull)형 커넥터인 기존의 단 분리용 커넥터에 있는 2개의 핀을 이용하여 한쪽으로는 로켓전원의 접지(Ground)에 연결시켜 단 분리가 되지 않으면 점화 명령이 들어와도 2단 또는 3단이 점화되지 않도록 하는 점화 안전 장치를 고안함으로써 별도의 센서와 이와 관련된 하드웨어 및 소프트웨어가 필요없는 2단 또는 3단 점화 안전 장치를 구현하는 것이다.The present invention is connected to the ground of the rocket power on one side by using two pins in the existing pull-out connector that is a push pull type connector in which the connector is separated while the stage is separated. If not, devise an ignition safety device that will not ignite the second or third stage even if an ignition command is received, thus implementing a two- or three-stage ignition safety device that does not require a separate sensor and its associated hardware and software.

이러한 본 발명은 구성이 아주 단순하여 기존의 단 분리용 커넥터에서 2개 의 핀을 할당받아 도 1 에서와 같이 연결하고 단 분리용 커넥터의 플러그는 접지(Ground)와 연결하고 단 분리용 커넥터의 소켓은 2단 점화 또는 3단 점화 장치 (I. G. Box) 입력단에 연결시켜줌으로써 이루어진다.The present invention is very simple in configuration so that two pins are allocated from the existing end separation connector and are connected as shown in FIG. 1, and the plug of the end separation connector is connected to the ground and the socket of the end separation connector is connected. This is accomplished by connecting to a two stage ignition or three stage ignition (IG Box) input.

도 1 은 본 발명의 단 분리용 커넥터의 장착도1 is a mounting view of the connector for disconnection of the present invention

도 2 는 본 발명의 점화 안전 장치 회로도2 is a circuit diagram of an ignition safety device of the present invention.

[도면의 주요부분에 대한 부호의 설명][Explanation of symbols on the main parts of the drawings]

1 : 단 분리용 커넥터 플러그2 : 단 분리용 커넥터 소켓1: Connector plug for disconnection 2: Connector socket for disconnection

3 : 단 분리용 커넥터4 : 로켓의 단 분리면3: end separation connector 4: end separation surface of rocket

5 : 커넥터 분리용 선6 : 커넥터 분리용 선의 고정선5: Connector disconnection line 6: Connector disconnection line

7 : 케이블8 : 접지7 Cable 8: Ground

9 : 점화 장치10 : 점화명령9 ignition device 10 ignition command

11 : 시퀀스 제어기12 : 저항11: sequence controller 12: resistance

본 발명은 단 분리가 되면서 커넥터가 분리되는 푸쉬풀형 커넥터인 기존의 단 분리용 커넥터에 있어서,The present invention provides a conventional pull-out connector that is a push-pull connector in which the connector is separated while being disconnected.

2개의 핀을 이용하여 연결된 단 분리용 커넥터(3)와,Disconnecting connector (3) connected using two pins,

상기 단 분리용 커넥터(3)에 연결되어 단 분리가 이루어지면 커넥터의 플러그(1)를 빠지게 하는 커넥터 분리용 선(5)과,A connector disconnecting wire 5 connected to the connector for disconnecting the connector 3 to disconnect the plug 1 of the connector when the terminal is disconnected;

상기 커넥터 분리용 선(5)을 로켓단에 고정시키는 커넥터 분리용 선의 고정선(6)과,A fixing line 6 of a connector separating line for fixing the connector separating line 5 to the rocket end,

상기 단 분리용 커넥터(3)의 플러그(1)에 연결된 접지(8)와,A ground 8 connected to the plug 1 of the connector 3 for disconnecting ends;

상기 단 분리용 커넥터(3)의 소켓(2)에 연결된 점화 장치(9)와,An ignition device 9 connected to the socket 2 of the connector for disconnecting stage 3,

상기 점화 장치(9)의 입력단에 입력되는 관성항법장치의 점화명령(10)과,An ignition command 10 of the inertial navigation device inputted to an input terminal of the ignition device 9,

상기 관성항법장치의 점화명령(10)을 제어하는 시퀀스 제어기(11)로 이루어진다.The sequence controller 11 controls the ignition command 10 of the inertial navigation apparatus.

도 1 에서와 같이 로켓 단 분리면(4)에 2개의 핀을 이용하여 단 분리용 커넥터(3)의 플러그(1)와 소켓(2)이 연결된 상태인 단 분리용 커넥터(3)가 장착되어 있는데 로켓의 단 분리가 이루어지면 단 분리 커넥터(3)에 붙어 있는 커넥터 분리용 선(Lanyard)(5)에 의해서 단 분리용 커넥터의 플러그(1)가 빠지게 된다.As shown in FIG. 1, a stage separation connector 3 is mounted with a plug 1 and a socket 2 of the stage separation connector 3 connected to each other using two pins on the rocket stage separation surface 4. If the stage separation of the rocket is made by the connector separation line (Lanyard) 5 attached to the stage separation connector (3), the plug (1) of the stage separation connector is pulled out.

또한, 도 2 에서 보면 단 분리가 원활히 이루어지면 단 분리용 커넥터(3)의플러그가 빠지면서 점화 장치(9)의 입력단에 연결된 접지(8)와 분리되어 시퀀스 제어기(11)의 제어에 의한 관성항법장치의 점화 명령(10)을 받아 2단 또는 3단 추진기관이 점화 가능한 상태가 되나, 외부의 원인(전자파 등)이나 내부의 비행 시퀀스 제어기의 고장 등 여러 가지 요인에 의해 단 분리가 이루어지지 않으면 단 분리 커넥터(3)의 플러그(1)가 빠지지 않고 점화 장치(9)의 입력단에는 항상 접지(8)가 연결되어 있어서 관성항법장치로부터 점화 명령(10)이 와도 점화장치(9)가 이 명령을받아들이지 않음을 볼 수 있다.In addition, as shown in FIG. 2, when the stage separation is smoothly performed, the plug of the stage separation connector 3 is pulled out and is separated from the ground 8 connected to the input terminal of the ignition device 9, thereby controlling the inertial navigation by the control of the sequence controller 11. If the two-stage or three-stage propulsion engine is enabled to receive the ignition command (10) of the device, but the stage is not separated by various factors such as external causes (electromagnetic waves, etc.) or failure of the internal flight sequence controller, The plug (1) of the stage disconnect connector (3) does not come out, and the ground (8) is always connected to the input terminal of the ignition device (9), so that even if the ignition command (10) comes from the inertial navigation system, the ignition device (9) receives this command. You can see that it does not accept.

이러한 기능은 로켓을 총 조립한 후 시험과정 2단 및 3단의 점화 안전 장치인 SAD의 Redundancy로서도 활용이 가능하여 발사 준비시 안전성을 높이는데도 큰 도움이 된다.This function can be used as the redundancy of SAD, which is a two- and three-stage ignition safety device after the total assembly of the rockets, which greatly helps to increase safety when preparing for launch.

본 발명은 별도의 단 분리 확인용 센서와 이에 따른 별도의 하드웨어 및 소프트웨어가 필요없으면서도 기능적인 면으로 볼 때 훨씬 안전한(별도의 장치가 필요없기 때문에 소자가 고장날 확률이 낮음) 단 분리용 커넥터를 이용한 로켓 2단 및 3단 점화 안정 장치에 관한 것으로서, 이와 유사한 기능이 필요한 각종 지상 장비에도 유용하게 응용이 가능할 것으로 기대된다.According to the present invention, a separate end disconnecting sensor and a separate hardware and software are not required, and the functional side is much safer in terms of functionality (the device is unlikely to break down because there is no need for a separate device). The present invention relates to a two- and three-stage ignition stabilizer used, and is expected to be usefully applied to various ground equipments requiring similar functions.

Claims (2)

단 분리가 되면서 커넥터가 분리되는 푸쉬풀형 커넥터인 기존의 단 분리용 커넥터에 있어서,In the existing stage separation connector, which is a push-pull connector in which the stage is separated and the connector is separated, 2개의 핀을 활용하여 연결된 단 분리용 커넥터(3)와,Disconnecting connector (3) connected using two pins, 상기 단 분리용 커넥터(3)에 연결되어 단 분리가 이루어지면 커넥터의 플러그(1)를 빠지게 하는 커넥터 분리용 선(5)과,A connector disconnecting wire 5 connected to the connector for disconnecting the connector 3 to disconnect the plug 1 of the connector when the terminal is disconnected; 상기 커넥터 분리용 선(5)을 로켓단에 고정시키는 커넥터 분리용 선의 고정선(6)과,A fixing line 6 of a connector separating line for fixing the connector separating line 5 to the rocket end, 상기 단 분리용 커넥터(3)의 플러그(1)에 연결된 접지(8)와,A ground 8 connected to the plug 1 of the connector 3 for disconnecting ends; 상기 단 분리용 커넥터(3)의 소켓(2)에 연결된 점화 장치(9)와,An ignition device 9 connected to the socket 2 of the connector for disconnecting stage 3, 상기 점화 장치(9)의 입력단에 입력되는 관성항법장치의 점화명령(10)과,An ignition command 10 of the inertial navigation device inputted to an input terminal of the ignition device 9, 상기 관성항법장치의 점화명령(10)을 제어하는 시퀀스 제어기(11)로 구성됨을 특징으로 하는 로켓 탑재용 추진기관 점화 안전 장치.The rocket mounting propulsion engine ignition safety device, characterized in that consisting of a sequence controller for controlling the ignition command (10) of the inertial navigation device. 제 1 항에 있어서, 단 분리용 커넥터(3)는 단 분리면(4)에 2개의 핀을 이용하여 단 분리용 커넥터(3)의 플러그(1)와 소켓(2)이 연결된 것을 특징으로 하는 로켓 탑재용 추진기관 점화 안전 장치.The terminal separating connector (3) is characterized in that the plug (1) and the socket (2) of the separating connector (3) are connected to each other by using two pins on the separating surface (4). Rocket mounted propulsion engine ignition safety device.
KR10-2001-0051305A 2001-08-24 2001-08-24 Rocket Onboard Safety Device for 2nd or 3rd Stage Ignition KR100417005B1 (en)

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US10113847B2 (en) 2016-08-23 2018-10-30 Agency For Defense Development Arm-fire device and method of igniting propulsion system using the same

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KR20000018642U (en) * 1999-03-25 2000-10-25 김영환 Device for disconnecting in satellite
KR20000061523A (en) * 1999-03-26 2000-10-25 김영환 Separation system using air
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10113847B2 (en) 2016-08-23 2018-10-30 Agency For Defense Development Arm-fire device and method of igniting propulsion system using the same

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