CN106428624A - Dynamic jettisoning and separation test method - Google Patents
Dynamic jettisoning and separation test method Download PDFInfo
- Publication number
- CN106428624A CN106428624A CN201610782219.0A CN201610782219A CN106428624A CN 106428624 A CN106428624 A CN 106428624A CN 201610782219 A CN201610782219 A CN 201610782219A CN 106428624 A CN106428624 A CN 106428624A
- Authority
- CN
- China
- Prior art keywords
- recorder
- throwing
- jettisoning
- test
- dynamic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention belongs to the technical field of aviation airborne electronic equipment, and particularly relates to a dynamic jettisoning and separation test method. According to the dynamic jettisoning and separation test method disclosed by the invention, a power device and a deceleration device are adopted to simulate the speed of an aircraft during an air crash; when the condition of jettisoning a jettisoning recorder is met, the jettisoning recorder is jettisoned out of the aircraft, the process of separation of the jettisoning recorder from simulation tools is recorded and tested by a test system, and the deceleration process in the air, aerial attitude, landing process and other data of the jettisoning recorder required for the test are tested and monitored. According to the dynamic jettisoning and separation test method disclosed by the invention, the design efficiency of the jettisoning recorder is effectively improved, and the service life of the jettisoning recorder is effectively prolonged.
Description
Technical field
The invention belongs to airborne technical field of electronic equipment is and in particular to a kind of dynamic throwing puts exclusion assay.
Background technology
Developing rapidly with aircraft industry, the event such as air crash also occurs more, and the survival rate for recorder proposes
High requirement, fixed recorder does not at sea have floating capacity, and recorder exists searches difficulty, and the cycle of salvaging is long, cost
High problem.Therefore, aircraft is badly in need of installing the throwing that can survive by different way additional and putting recorder.Shown according to foreign data,
Install throw put recorder generation 108 air crash accidents in, successful recovery record device data have 101, success rate is
94%.If each airplane all installs throwing puts recorder, the crash probability of survival of recorder will improve a lot.When accident is sent out
When raw, throw to put recorder and automatically can throw to put with aircraft and separate, it is landed by Air slowdown by the construction profile of uniqueness itself
Or float on the water surface.
Dynamic throwing is put exclusion assay and is simulated aircraft crash condition, throws and put disembark process and crashing of recorder and survive
One comprehensive verification test.By studying and implementing this test, achievable throwing put recorder throw put separate, Air slowdown falls
Ground, the compbined test checking of data test.
Content of the invention
The technical problem to be solved is：A kind of dynamic throwing is provided to put exclusion assay, simulation throwing is put and separated
Dynamic response after separating with aircraft for the device, provides reference frame for throwing the design putting separator.
Exclusion assay is put in the dynamic throwing of the present invention, realize throwing put recorder throw put separate, Air slowdown land, data
The compbined test of test, recorder is put in throwing and is fixed in simulation frock, this simulation frock is arranged on operation by rack construction
On track, and it is connected with power set, test system provides, by power set, the speed meeting when simulated aircraft crashes, and works as mould
When the plan frock speed of service reaches test setting index, test system transmission throwing discharge signal puts recorder internal circuit blocks to throwing
Come to realize throwing put recorder with simulation frock separate, and by test system record throw put recorder with simulation frock separate
Process, throwing put the test desired data of the skyborne moderating process of recorder, attitude and the process that lands.
Further, deceleration device is additionally provided with running track.
The invention has the beneficial effects as follows：Exclusion assay is put in dynamic throwing using the present invention, effectively increases throwing and puts note
The design efficiency of record device and service life.
Brief description
Fig. 1 is that dynamic throwing puts separation test system composition schematic diagram；
Fig. 2 is that dynamic throwing puts separation test process schematic diagram.
1st, throw and put recorder；2nd, simulate frock；3rd, rack construction；4th, power set；5th, deceleration device；6th, test system
Specific embodiment
Because aircraft has an accident in high-speed flight, recorder is put in throwing to be needed to depart from body, and dynamic throwing puts exclusion assay
When simulated aircraft crashes, can achieve throw put recorder throw put separate, Air slowdown lands, the checking of the compbined test of data test.
A kind of dynamic throwing puts exclusion assay, realize throwing put recorder throw put separate, Air slowdown lands, data test
Compbined test, by throwing put recorder 1 be fixed on simulation frock 2 on, this simulation frock 2 is arranged on operation by rack construction 3
On track, and it is connected with power set 4, test system 6 passes through power set 4 provides the speed meeting when simulated aircraft crashes,
When simulation frock 2 speed of service reaches test and sets index, test system 6 transmission throwing discharge signal is put inside recorder 1 to throwing
Circuit module come to realize throwing put recorder 1 with simulation frock 2 separate, and by test system 6 record throwing put recorder 1 and mould
Intend the separation process of frock 2, throw the test desired data putting the skyborne moderating process of recorder 1, attitude and the process that lands.?
Deceleration device 5 is additionally provided with running track.
When the core technology point that separation test is put in dynamic throwing mainly uses power set, the accident of deceleration device simulated aircraft
Speed, when recorder is thrown and put condition throwing put with recorder carry out throwing and put disembarking when meeting throwing and putting, with the test of test system record
Throw put recorder and the simulation separation process of frock, test, monitor throwing put recorder in the air moderating process, aerial statue and
The test desired data such as ground process.
Claims (2)
1. a kind of dynamic throwing puts exclusion assay, realize throwing put recorder throw put separate, Air slowdown lands, data test
Compbined test it is characterised in that：Recorder (1) is put in throwing be fixed in simulation frock (2), this simulation frock (2) passes through frame
Structure (3) is arranged in running track, and is connected with power set (4), and test system (6) passes through power set (4) to be provided completely
Speed when sufficient simulated aircraft crashes, when simulation frock (2) speed of service reaches test and sets index, test system (6) passes
Send throwing discharge signal to throwing put recorder (1) internal circuit blocks to realize throwing put recorder (1) with simulate frock (2) separate,
And put recorder (1) and the separation process simulating frock (2), throw and put recorder (1) in the air by test system (6) record throwing
Moderating process, attitude and the process that lands test desired data.
2. dynamic throwing according to claim 1 put exclusion assay it is characterised in that：Running track is additionally provided with
Deceleration device (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610782219.0A CN106428624A (en) | 2016-08-30 | 2016-08-30 | Dynamic jettisoning and separation test method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610782219.0A CN106428624A (en) | 2016-08-30 | 2016-08-30 | Dynamic jettisoning and separation test method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106428624A true CN106428624A (en) | 2017-02-22 |
Family
ID=58091865
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610782219.0A Pending CN106428624A (en) | 2016-08-30 | 2016-08-30 | Dynamic jettisoning and separation test method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106428624A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264802A (en) * | 2017-06-27 | 2017-10-20 | 北京电子工程总体研究所 | A kind of unmanned plane fire extinguisher bomb glass penetration test system and test method |
| CN107572006A (en) * | 2017-09-13 | 2018-01-12 | 陕西千山航空电子有限责任公司 | A kind of helicopter puts logger exclusion assay with throwing |
| CN112660399A (en) * | 2020-12-11 | 2021-04-16 | 陕西千山航空电子有限责任公司 | Automatic throwing control device and method for flight recorder |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060103853A1 (en) * | 2004-11-12 | 2006-05-18 | The Boeing Company | Optical projection system |
| CN202471109U (en) * | 2012-02-29 | 2012-10-03 | 深圳市丰泰瑞达实业有限公司 | Ejection accelerator |
| CN203832760U (en) * | 2014-04-25 | 2014-09-17 | 北京中量安测科技有限公司 | Catapulting system for small size unmanned aerial vehicle |
| CN105799948A (en) * | 2016-03-18 | 2016-07-27 | 北京理工大学 | Catapult of flywheel-type high-speed unmanned aerial vehicle |
-
2016
- 2016-08-30 CN CN201610782219.0A patent/CN106428624A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060103853A1 (en) * | 2004-11-12 | 2006-05-18 | The Boeing Company | Optical projection system |
| CN202471109U (en) * | 2012-02-29 | 2012-10-03 | 深圳市丰泰瑞达实业有限公司 | Ejection accelerator |
| CN203832760U (en) * | 2014-04-25 | 2014-09-17 | 北京中量安测科技有限公司 | Catapulting system for small size unmanned aerial vehicle |
| CN105799948A (en) * | 2016-03-18 | 2016-07-27 | 北京理工大学 | Catapult of flywheel-type high-speed unmanned aerial vehicle |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264802A (en) * | 2017-06-27 | 2017-10-20 | 北京电子工程总体研究所 | A kind of unmanned plane fire extinguisher bomb glass penetration test system and test method |
| CN107572006A (en) * | 2017-09-13 | 2018-01-12 | 陕西千山航空电子有限责任公司 | A kind of helicopter puts logger exclusion assay with throwing |
| CN112660399A (en) * | 2020-12-11 | 2021-04-16 | 陕西千山航空电子有限责任公司 | Automatic throwing control device and method for flight recorder |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8880283B2 (en) | Deployable flight recorder | |
| CN104344882B (en) | A kind of aircraft shaking detection system and method | |
| CN106428624A (en) | Dynamic jettisoning and separation test method | |
| CN106240811A (en) | Unmanned plane safety device and unmanned plane safety protecting method | |
| CN111498113B (en) | Jettisoning type flight recorder system and control method | |
| CN101298974A (en) | Active recycling control method of air-to-air missile experiment missile | |
| CN103224031A (en) | Landing device of fixed-wing aircraft | |
| CN104915715A (en) | Multi-method combination avionics system fault diagnosis method | |
| CN205098484U (en) | Aircraft launches system of fleing | |
| CN105000173A (en) | Ground protection system and method for airplane brake | |
| CN111186553B (en) | Recycling test method for aerostat carrying planetary sampling returning capsule | |
| CN108438236A (en) | A kind of aerial falling proof device of unmanned plane | |
| CN106218867A (en) | Flexible bionic landing system and application thereof | |
| AU2018357860B2 (en) | Distributed aircraft recorder system | |
| CN110979695A (en) | Automatic parachute throwing condition interpretation method for parachuting recovery unmanned aerial vehicle | |
| CN104648678B (en) | Method for acquiring ejection deplaning signal of ejection seat | |
| CN206020053U (en) | Virtual train access device | |
| CN104943866A (en) | Airborne training launching device | |
| CN104875895B (en) | A kind of depopulated helicopter parachute landing system airborne ejection parachute-deploying test device and method | |
| CN106882362A (en) | A kind of undercarriage that can be flown and its working method | |
| CN107572006A (en) | A kind of helicopter puts logger exclusion assay with throwing | |
| CN216636838U (en) | Airborne equipment protection device and unmanned aerial vehicle | |
| CN106249617B (en) | Separation dummy emulation method is put in a kind of throwing | |
| CN106898187A (en) | A kind of rotor wing unmanned aerial vehicle landing training platform that takes off | |
| CN2581330Y (en) | Land spare device for aircraft landing gear |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170222 |
|
| WD01 | Invention patent application deemed withdrawn after publication |