CN104648678A - Method for acquiring ejection deplaning signal of ejection seat - Google Patents
Method for acquiring ejection deplaning signal of ejection seat Download PDFInfo
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- CN104648678A CN104648678A CN201310603514.1A CN201310603514A CN104648678A CN 104648678 A CN104648678 A CN 104648678A CN 201310603514 A CN201310603514 A CN 201310603514A CN 104648678 A CN104648678 A CN 104648678A
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Abstract
The invention belongs to the technical field of aviation protection and rescue, and in particular relates to a method for acquiring an ejection deplaning signal of an ejection seat. The method is that a first connecting module (1) is connected with the ejection seat (5); a second connecting module (2) which is matched and connected with the first connecting module (1) is arranged on a plane body. The method is characterized in that the second connecting module (2) is connected with a plane parameter system (3) and a chassis ground (4); when the seat is not ejected, the plane parameter system (3) records a ground signal input by the chassis ground (4); when the seat is ejected and deplaned and upwards move in a certain distance, the first connecting module (1) is separated from the second connecting module (2), the ground signal input by the chassis ground (4) is cut off, and the plane parameter system records an open-circuit signal which is the seat ejecting deplaning signal. With the adoption of the method, the ejection deplaning signal can be acquired during ejecting the seat and can be inputted into the plane parameter system to be recorded in the plane, and therefore, whether the seat is started to be ejected and deplaned in emergency can be known, and strong evidence is provided to determine the working condition of ejecting the seat and analyzing the flying accident.
Description
Technical field
The invention belongs to airway protection lifesaving technology field, particularly relate to a kind of ejection-seat ejection escape signal acquisition method.
Background technology
The ejection-seat that domestic active service fighter plane is equipped with scarcely possesses the function gathering the signal of disembarking that seat upwards launches, if in aviation accident, occur that aviator does not launch the situation of deliver from vault, then accurately cannot judge whether this situation is not upwards started caused by ejection escape by ejection-seat, therefore can cause very large puzzlement to accident analysis and system reliability checking.
Summary of the invention
The object of the invention is: gather ejection escape signal for ejection-seat, ejection-seat service condition to be judged and aircraft accident is analyzed significant.
Technical scheme of the present invention is:
A kind of ejection-seat ejection escape signal acquisition method, this method system used comprises the first link block 1, second link block 2, aircraft FDR system 3, casing ground 4 and ejection-seat 5, wherein, first link block 1 is connected with ejection-seat 5, airframe is arranged and is connected with aircraft FDR system 3, casing ground 4 with supporting the second link block 2, second link block 2 be connected of the first link block 1.
When seat does not normally launch work, what aircraft FDR system 3 recorded is the earth signal inputted from casing ground 4, when upward movement certain distance is disembarked in seat fire, first link block 1 is separated with the second link block 2, the earth signal of casing ground 4 input disconnects, FDR system record open circuit signaling, namely seat fire is disembarked signal.Interface relationship is shown in Fig. 1.
The invention has the beneficial effects as follows:
The present invention can gather ejection escape signal in ejection-seat working process, this signal can be inputed to FDR system aboard and carry out record, under can learning emergency condition, whether seat starts ejection escape, provides strong evidence to the judgement of ejection-seat service condition and aircraft accident analysis.
Accompanying drawing explanation
Fig. 1 is the annexation figure of system for use in carrying of the present invention;
Fig. 2 is the annexation figure of the embodiment of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail:
A kind of ejection-seat ejection escape signal acquisition method, this method system used comprises the first link block 1, second link block 2, aircraft FDR system 3, casing ground 4 and ejection-seat 5, wherein, first link block 1 is connected with ejection-seat 5, airframe is arranged and is connected with aircraft FDR system 3, casing ground 4 with supporting the second link block 2, second link block 2 be connected of the first link block 1.
When seat does not launch, what aircraft FDR system 3 recorded is the earth signal inputted from casing ground 4, when upward movement certain distance is disembarked in seat fire, first link block 1 is separated with the second link block 2, the earth signal of casing ground 4 input disconnects, FDR system records open circuit signaling, and namely seat fire is disembarked signal.
This ejection escape signal acquisition method is applied on aircraft ejection-seat, is reduction procedure, mitigation system weight, former ejection-seat 5 can be carried out Curve guide impeller.
First link block 1 adopts battery socket, and the second link block 2 adopts attaching plug.Machine power source enters ejection-seat 5 by the connection of battery socket and attaching plug.
The chair basin jacking system of ejection-seat 5 is connected with the attaching plug on aircraft by battery socket, and to power to seat, during emergency ejection, attaching plug is pulled out from battery socket by the cable wire be connected with cockpit floor by, thus disconnects machine power source.
As Fig. 2, battery socket on seat and the attaching plug on aircraft are all set to 4 cores, according to Fig. 2 mode of connection, earth's crust earth signal enters aircraft FDR system by the core F on the core A on attaching plug, the core E on battery socket, ejection-seat, battery socket, core B on attaching plug successively.
When seat fire is disembarked, battery socket is separated with attaching plug, and earth signal that FDR system recorded originally disconnects, and change open circuit signaling into, FDR system records this open circuit signaling, is seat fire and disembarks signal.
Claims (3)
1. an ejection-seat ejection escape signal acquisition method, this method system used comprises the first link block (1), the second link block (2), aircraft FDR system (3), casing ground (4) and ejection-seat (5), wherein, first link block (1) is connected with ejection-seat (5), airframe arranges second link block (2) that be connected supporting with the first link block (1), it is characterized in that, the second link block (2) is connected with aircraft FDR system (3), casing ground (4);
When seat does not launch, what aircraft FDR system (3) recorded is from casing ground (4) earth signal of inputting, when upward movement certain distance is disembarked in seat fire, first link block (1) is separated with the second link block (2), the earth signal that casing ground (4) inputs disconnects, FDR system records open circuit signaling, and namely seat fire is disembarked signal.
2. a kind of ejection-seat ejection escape signal acquisition method as claimed in claim 1, is characterized in that, the first link block (1) adopts battery socket, and the second link block (2) adopts attaching plug.
3. a kind of ejection-seat ejection escape signal acquisition method as claimed in claim 2, is characterized in that, machine power source enters ejection-seat (5) by the connection of battery socket and attaching plug.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310603514.1A CN104648678B (en) | 2013-11-22 | 2013-11-22 | Method for acquiring ejection deplaning signal of ejection seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310603514.1A CN104648678B (en) | 2013-11-22 | 2013-11-22 | Method for acquiring ejection deplaning signal of ejection seat |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104648678A true CN104648678A (en) | 2015-05-27 |
| CN104648678B CN104648678B (en) | 2017-02-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310603514.1A Active CN104648678B (en) | 2013-11-22 | 2013-11-22 | Method for acquiring ejection deplaning signal of ejection seat |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106680528A (en) * | 2016-12-14 | 2017-05-17 | 中国航空救生研究所 | Method of determining ejection speed of man-seat system |
| CN112238947A (en) * | 2020-10-26 | 2021-01-19 | 航宇救生装备有限公司 | Electronic instruction ejection system controlled by ejection mode switching |
| CN114291279A (en) * | 2021-12-31 | 2022-04-08 | 中国航空工业集团公司西安飞机设计研究所 | Life guarantee system-based warning system for avoiding pilot from mistakenly launching |
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| RU2266239C1 (en) * | 2004-06-28 | 2005-12-20 | Открытое акционерное общество "Научно-производственное предприятие "Звезда" | Ejection seat |
| US7667620B1 (en) * | 2007-02-02 | 2010-02-23 | Rockwell Collins, Inc. | Network enabled survival terminal |
| US20100308992A1 (en) * | 2009-01-29 | 2010-12-09 | King Saud University | Personal safety and locator device |
| CN202814225U (en) * | 2012-09-21 | 2013-03-20 | 航宇救生装备有限公司 | Signal transmitting system of ejection seat |
| CN203111514U (en) * | 2013-02-01 | 2013-08-07 | 中国航空工业集团公司西安飞机设计研究所 | Ejection seat ejection signal collection device |
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2013
- 2013-11-22 CN CN201310603514.1A patent/CN104648678B/en active Active
Patent Citations (5)
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| RU2266239C1 (en) * | 2004-06-28 | 2005-12-20 | Открытое акционерное общество "Научно-производственное предприятие "Звезда" | Ejection seat |
| US7667620B1 (en) * | 2007-02-02 | 2010-02-23 | Rockwell Collins, Inc. | Network enabled survival terminal |
| US20100308992A1 (en) * | 2009-01-29 | 2010-12-09 | King Saud University | Personal safety and locator device |
| CN202814225U (en) * | 2012-09-21 | 2013-03-20 | 航宇救生装备有限公司 | Signal transmitting system of ejection seat |
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Non-Patent Citations (1)
| Title |
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| 候晓蒙: "军用飞机的弹射座椅", 《现代军事》, 30 June 2002 (2002-06-30), pages 28 - 29 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106680528A (en) * | 2016-12-14 | 2017-05-17 | 中国航空救生研究所 | Method of determining ejection speed of man-seat system |
| CN106680528B (en) * | 2016-12-14 | 2019-08-13 | 中国航空救生研究所 | A method of judging human seat model ejection speed |
| CN112238947A (en) * | 2020-10-26 | 2021-01-19 | 航宇救生装备有限公司 | Electronic instruction ejection system controlled by ejection mode switching |
| CN112238947B (en) * | 2020-10-26 | 2023-10-13 | 航宇救生装备有限公司 | Electronic instruction ejection system for ejection mode switching control |
| CN114291279A (en) * | 2021-12-31 | 2022-04-08 | 中国航空工业集团公司西安飞机设计研究所 | Life guarantee system-based warning system for avoiding pilot from mistakenly launching |
| CN114291279B (en) * | 2021-12-31 | 2023-06-23 | 中国航空工业集团公司西安飞机设计研究所 | Warning system for avoiding pilot from being ejected by mistake based on life support system |
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| Publication number | Publication date |
|---|---|
| CN104648678B (en) | 2017-02-08 |
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