CN104648686A - Ejection escape early-warning system - Google Patents
Ejection escape early-warning system Download PDFInfo
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- CN104648686A CN104648686A CN201310606961.2A CN201310606961A CN104648686A CN 104648686 A CN104648686 A CN 104648686A CN 201310606961 A CN201310606961 A CN 201310606961A CN 104648686 A CN104648686 A CN 104648686A
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- excess time
- ejection
- early warning
- rest time
- warning
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Abstract
The invention belongs to the technical field of ejection escape of fighters, and in particular relates to an ejection escape early-warning system. The system is characterized in that a data acquiring circuit is used for acquiring flight parameters from a fighter inertial navigation platform and an atmospheric data machine and continuously inputs into an early-warning computer; the early-warning computer is used for processing the acquired data and calculating the rest time that the ejection is to be carried out under the current distance and the rest time variation rate; a display system is used for directly displaying the rest time to a pilot; a warning system warns when the rest time is close to a warning value and alarms when the rest time variation rate is close to the warning value. With the adoption of the ejection escape early-warning system, the rest time for ejection is reminded to the pilot when the fighter is to suffer from an accident, and the pilot is warned when the rest time and the rest time variation rate are close to the warning value, so that the pilot can quickly determine and handle with the time limit, and as a result, the delay of ejection due to human factors can be avoided, and the ejection escape success rate can be increased.
Description
Technical field
The invention belongs to fighter plane Aircrew Escape Technology field, particularly relate to a fighter plane ejection survival forewarn system.
Background technology
Ejection escape device is when aeroplane accident, ensures that aviator can ejection escape rapidly, the important equipment of being rescued safely.But along with the appearance of third and fourth fighter plane, height, the speed and motor-driven performance of fighter plane are greatly improved, and this safe ejection for aviator adds difficulty in generation.
Existing foundation of launching is mainly aircraft Distal promoter and stall warning, needs to be carried out judging rear decision according to above-mentioned alarm and aircraft existing condition by aviator when launching.Its shortcoming is, cannot estimate the time disposing aircraft.Often therefore delay favourable opportunity of launching, cause insufficient height and cause the accident.There is no at present effective measures can reduce human element incur loss through delay cause launch unsuccessful rate.
Summary of the invention
The object of the invention is:
A kind of fighter plane ejection survival forewarn system is provided, can calculates in real time and show the excess time that must launch, and excess time or excess time rate of change carry out alarm close to during warning value.
Technical scheme of the present invention is:
A kind of ejection survival forewarn system, is characterized in that, comprising: data acquisition circuit, early warning computing machine, display system and alarm system.Data acquisition circuit input end is connected with aircraft INS Platform and atmosphere data machine; Data acquisition circuit mouth is connected with early warning computer input end; Early warning fanout connects display system and alarm system respectively.
Wherein, data acquisition circuit Real-time Collection comes from the flight parameter in aircraft INS Platform and atmosphere data machine, and successively inputs early warning computing machine; The data of collection process by early warning computing machine, calculate excess time that now distance must launch and excess time rate of change; Excess time is intuitively shown to aviator by display system; Alarm system 4 carries out alarm in excess time close to during warning value; Alarm system excess time rate of change carry out alarm close to during warning value.
The invention has the beneficial effects as follows:
The present invention is when fighter plane is about to have an accident, remind the excess time that aviator must launch, and excess time and excess time rate of change close to alarm during warning value, aviator is helped to judge fast to dispose the time limit, avoid incuring loss through delay because of human element launching opportunity, thus improve ejection survival success ratio.
Accompanying drawing explanation
Fig. 1 is functional block diagram of the present invention.
Fig. 2 be calculate in the present invention excess time and excess time rate of change diagram of circuit.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail:
Ejection survival forewarn system of the present invention is the ancillary system of fighter plane ejection escape device, sees Fig. 1, is made up of data acquisition circuit 1, early warning computing machine 2, display system 3 and alarm system 4.Data acquisition circuit 1 Real-time Collection comes from the flight parameter in aircraft INS Platform 5 and atmosphere data machine 6, and successively inputs early warning computing machine 2; The data of collection process by early warning computing machine 2, calculate excess time that now distance must launch and excess time rate of change; Excess time is intuitively shown to aviator by display system 3; Alarm system 4 carries out alarm in excess time close to during warning value; Alarm system 4 excess time rate of change carry out alarm close to during warning value.
Early warning calculation flow chart excess time of the present invention, is shown in Fig. 2.The human seat model parameter of the flight parameter collected and initial setting up processes by early warning computing machine, if calculate the required minimum safe altitude of now airplane catapult in real time; Early warning computing machine calculates vertical direction speed according to flight parameter, extracts corrected altitude; The corrected altitude of minimum safe altitude with now aircraft vertical direction speed and plane distance ground contrasts by early warning computing machine, calculates the excess time that now distance must be launched.To carrying out differential calculation rate of change excess time excess time.
Display system of the present invention and alarm system.Display system is arranged on Flight Instrument plate; Excess time is shown with digital display in second by display system, and scope is 00 second ~ 99 seconds, is shown as 99 seconds when the excess time that forewarn system calculates is more than or equal to 99 seconds, shows in real time when being less than 99 seconds; When excess time is greater than 45 seconds, digital display shows that font color is green to alarm system second, alert status display " safety " printed words; Alarm system is in excess time within the scope of 15 seconds ~ 45 seconds, and second, digital display showed that font color is orange, alert status display " attention " printed words; Alarm system digital body color in the second when excess time is less than 15 seconds is for red, and alert status display " warning " printed words also glimmer; Alarm system is when excess time, rate of change was greater than 5, and alert status display " reducing too fast " printed words also glimmer.
Claims (2)
1. an ejection survival forewarn system, is characterized in that, native system comprises: data acquisition circuit, early warning computing machine, display system and alarm system.Data acquisition circuit input end is connected with aircraft INS Platform and atmosphere data machine; Data acquisition circuit mouth is connected with early warning computer input end; Early warning fanout connects display system and alarm system respectively.
Wherein, data acquisition circuit Real-time Collection comes from the flight parameter in aircraft INS Platform and atmosphere data machine, and successively inputs early warning computing machine; The data of collection process by early warning computing machine, calculate excess time that now distance must launch and excess time rate of change; Excess time is intuitively shown to aviator by display system; Alarm system carries out alarm in excess time close to during warning value; Alarm system excess time rate of change carry out alarm close to during warning value.
2. a kind of ejection survival forewarn system as claimed in claim 1, it is characterized in that, calculate excess time that now distance must launch and excess time rate of change method as follows: the human seat model parameter of the flight parameter collected and initial setting up processes by alarm computing machine, if calculate the required minimum safe altitude of now airplane catapult in real time; Early warning computing machine calculates vertical direction speed according to flight parameter, extracts corrected altitude; The corrected altitude of minimum safe altitude with now aircraft vertical direction speed and plane distance ground contrasts by early warning computing machine, calculates the excess time that now distance must be launched, to carrying out differential calculation rate of change excess time excess time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310606961.2A CN104648686A (en) | 2013-11-22 | 2013-11-22 | Ejection escape early-warning system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310606961.2A CN104648686A (en) | 2013-11-22 | 2013-11-22 | Ejection escape early-warning system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104648686A true CN104648686A (en) | 2015-05-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310606961.2A Pending CN104648686A (en) | 2013-11-22 | 2013-11-22 | Ejection escape early-warning system |
Country Status (1)
| Country | Link |
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| CN (1) | CN104648686A (en) |
Cited By (2)
| 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 |
| CN110780610B (en) * | 2019-10-30 | 2022-10-18 | 航宇救生装备有限公司 | Method for fusing and processing health management signals of ejection lifesaving system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6525674B1 (en) * | 2001-08-08 | 2003-02-25 | Rockwell Collins, Inc. | Conditional hazard alerting display |
| US20110148665A1 (en) * | 2009-12-23 | 2011-06-23 | Airbus Operations (Sas) | Method And A Device For Detecting Lack Of Reaction From The Crew Of An Aircraft To An Alarm Related To A Path |
| CN102481980A (en) * | 2009-07-27 | 2012-05-30 | 贝尔直升机泰克斯特龙公司 | Aircraft occupant protection system |
-
2013
- 2013-11-22 CN CN201310606961.2A patent/CN104648686A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6525674B1 (en) * | 2001-08-08 | 2003-02-25 | Rockwell Collins, Inc. | Conditional hazard alerting display |
| CN102481980A (en) * | 2009-07-27 | 2012-05-30 | 贝尔直升机泰克斯特龙公司 | Aircraft occupant protection system |
| US20110148665A1 (en) * | 2009-12-23 | 2011-06-23 | Airbus Operations (Sas) | Method And A Device For Detecting Lack Of Reaction From The Crew Of An Aircraft To An Alarm Related To A Path |
Non-Patent Citations (2)
| Title |
|---|
| 周方: "提高低空不利姿态下弹射救生成功率的措施", 《航空科学技术》 * |
| 曾智悦: "空管系统中告警技术的应用研究", 《中国优秀博硕士学位论文全文数据库 (硕士) 信息科技辑》 * |
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 |
| 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 |
| CN110780610B (en) * | 2019-10-30 | 2022-10-18 | 航宇救生装备有限公司 | Method for fusing and processing health management signals of ejection lifesaving system |
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Application publication date: 20150527 |
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| RJ01 | Rejection of invention patent application after publication |