CN106249617B - Separation dummy emulation method is put in a kind of throwing - Google Patents
Separation dummy emulation method is put in a kind of throwing Download PDFInfo
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- CN106249617B CN106249617B CN201610780666.2A CN201610780666A CN106249617B CN 106249617 B CN106249617 B CN 106249617B CN 201610780666 A CN201610780666 A CN 201610780666A CN 106249617 B CN106249617 B CN 106249617B
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- separation
- separation assembly
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B17/00—Systems involving the use of models or simulators of said systems
- G05B17/02—Systems involving the use of models or simulators of said systems electric
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
- Geophysics And Detection Of Objects (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to aviation airborne equipment Virtual Simulation fields, and in particular to separation dummy emulation method is put in a kind of throwing.When aircraft accident occurs for aircraft, separation assembly puts separation from body upthrow automatically, avoid adverse circumstances when air crash, the load that separation assembly is born when reducing air crash, separation assembly may float on sea after falling into the sea, increase satellite positioning functions, realize quickly positioning and search, shortens the accident rescue time.Separation Virtual Simulation is put in present invention throwing, air path after putting separation safety for the throwing to separation assembly, disembark, the synthesis dynamic simulation for entering water floating stability, it needs to carry out safety analysis of disembarking to separation assembly after determining installation position, ensure that separation assembly can be popped up safely in installation position, has important directive significance to the development of product.
Description
Technical field
The invention belongs to aviation airborne equipment Virtual Simulation fields, and in particular to a kind of throw puts separation virtual emulation side
Method, air path after putting separation safety for the throwing to separation assembly, disembark, the comprehensive dynamic for entering water floating stability
Emulation.
Background technique
It develops when throwing that put the target of formula logger be aircraft normal flight, record flight, voice and video data etc., when winged
When aircraft accident occurs for machine, separation assembly puts separation from body upthrow automatically, avoids adverse circumstances when air crash, reduces and flies
The load that separation assembly is born when machine crashes, separation assembly may float on sea after falling into the sea, and increase satellite positioning functions, realize
Quickly positioning and search, shorten the accident rescue time.
Summary of the invention
The technical problems to be solved by the present invention are: providing a kind of throw puts separation dummy emulation method, formula record is put to throwing
Device is emulated throwing the comprehensive dynamic after putting, it is ensured that disembark safety and the fast searching after falling of separation assembly.
Separation dummy emulation method is put in throwing of the invention, comprising the following steps:
Step 1: original state simulation analysis
I.e. static throw puts separation simulation analysis, obtains static state by bang model to selected blasting bolt and flexible linear shaped charge
The initial velocity of separation assembly pop-up when putting is thrown, and displacement of the separation assembly in static separation is obtained to mark with test result
With speed dynamic response；
Step 2: dynamic, which is thrown, puts separation simulation analysis
It disembarks safety analysis, the result and flying speed obtained using step 1 is primary condition, in conjunction with air-flow pair
The influence of separation assembly athletic posture, the motion profile after aircraft is detached to separation assembly are simulated；
Step 3: airflight simulation analysis
Speed when in conjunction with the skyborne motion profile of pre-set flight condition simulation separation assembly and reaching stable state obtains and divides
From the maximum terrain clearance and height of drop of component and the relationship of speed；
Step 4: entering the analysis of water stability simulation
According to the overboard speed of separation assembly, obtains separation assembly and enter the posture after water floating stable and shock resistance energy of rupture
Power；
Step 5: floating stability simulation analysis
Separation assembly floats under posture, in conjunction with default sea conditions obtain the wobble amplitude of separation assembly, vibration frequency and
Athletic posture obtains floating stability of the separation assembly under different sea conditions.
By step 2 assessment, separation assembly throwing puts whether separation can collide with body under certain flying speed, selects
Select the suitable installation site of separation assembly.Athletic posture of the separation assembly in different sea conditions is obtained by step 5, is referred to
The design of artificial delivery product internal satellite transmitting locating module.
It is described it is static throw to put separation and refer to the separation assembly under stationary state is separated；Separation is put in the dynamic throwing is
Finger separates the separation assembly under simulated flight state.
Beneficial effects of the present invention: separation Virtual Simulation is put in present invention throwing, is put in formula logger development process in throwing,
Simulation throwing puts separation, airflight and pendant and bangs into the floating stability after water, needs to carry out separation assembly after determining installation position
It disembarks safety analysis, it is ensured that separation assembly can be popped up safely in installation position, have important guidance to the development of product
Meaning.
Specific embodiment
The invention will be described in further detail below.
Throwing is put formula logger and is made of separating mechanism, mounting rack, separation assembly, covering and flexible linear shaped charge etc..Static state, which is thrown, puts point
From principle it is as follows: the detonation of explosive inside separating mechanism pushes cutter to move upwards and ejects separation assembly, covering and installation
Flexible linear shaped charge between frame tears aircraft skin, and separation assembly is allowed to pop up.
It was found from separation assembly static state throws the simulation result and Experimental Comparison for putting separation: separation assembly moves in uphill process
Posture and test are very close, separation assembly lifting height and rotation angle and to test posture essentially identical, separation assembly by
Impact energy and test it is consistent, show that separation assembly pop-up moment is applied to the kinetic energy (speed and angular speed) on separation assembly
Pass Test condition can be used for the input primary condition of subsequent disembark safety analysis and airflight simulation analysis.Meanwhile it is right
Mark result also indicates that explosive volume is bonded with actual tests in simulation analysis.
It disembarks to throw in safety analysis model and puts installation site of the formula logger on certain amphitypy Aircraft Tools model, simulation flies
For machine under high-speed flight state, separation assembly is detached from the motion profile of airframe.Separation assembly and covering are disembarked motion profile
Figure assesses aircraft separation assembly throwing under certain flying speed and puts whether separation can collide with the horizontal tail wing.
After separation is put in separation assembly throwing, the motion profile that Analyze & separate component flies in the sky, simulation aircraft is in flat winged, machine
Head downwards, the dynamic responses relationship such as displacement, speed, terrain clearance of separation assembly under nose-high three state.
Separation assembly enters the motion process of water with certain speed and different overboard postures, obtains separation assembly and enters water floating
Posture and shock resistance damage capability after stabilization.
Separation assembly falls into the floating posture in three-level/seven grade sea conditions seawater with certain speed, obtains to throw and puts formula note
Record wobble amplitude, vibration frequency and the athletic posture of device.The wave of three-level and seven grades of sea situations be by wave generator generate wave and
The coefficient effect of stormy waves that wind speed generates can get under three-level wave and seven grades of wave effects based on the method that plate makes wave
The high simulation of stable wave.
Through above-mentioned simulation calculation, after separation test is put in throwing, simulation result matches with test result, after disembarking and aerial
Flight path matches with Rocket sled test result, and virtual emulation calculation method described herein really can intuitively simulate separation group
Part throws the synthesis dynamic process for putting separation.
Claims (4)
1. separation dummy emulation method is put in a kind of throwing, which is characterized in that method includes the following steps:
Step 1: original state simulation analysis
I.e. static throw puts separation simulation analysis, obtains static throw by bang model to selected blasting bolt and flexible linear shaped charge and puts
When separation assembly pop-up initial velocity, and displacement and speed of the separation assembly in static separation are obtained to mark with test result
Spend dynamic response；
Step 2: dynamic, which is thrown, puts separation simulation analysis
It disembarks safety analysis, the result obtained using step 1 and initial velocity is primary condition, in conjunction with air-flow to separation
The influence of component movement posture, the motion profile after aircraft is detached to separation assembly are simulated；
Step 3: airflight simulation analysis
Speed when in conjunction with the skyborne motion profile of pre-set flight condition simulation separation assembly and reaching stable state obtains separation group
The maximum terrain clearance and height of drop of part and the relationship of speed；
Step 4: entering the analysis of water stability simulation
According to the overboard speed of separation assembly, obtains separation assembly and enter posture and shock resistance damage capability after water floating stable；
Step 5: floating stability simulation analysis
Separation assembly floats under posture, and wobble amplitude, vibration frequency and the movement of separation assembly are obtained in conjunction with default sea conditions
Posture obtains floating stability of the separation assembly under different sea conditions.
2. separation dummy emulation method is put in throwing according to claim 1, it is characterised in that: assessed by step 2 certain
Separation assembly throwing puts whether separation can collide with body under initial velocity, selects the suitable installation site of separation assembly.
3. separation dummy emulation method is put in throwing according to claim 1, it is characterised in that: obtain separation group by step 5
Athletic posture of the part in different sea conditions instructs the design of separation assembly internal satellite transmitting locating module.
4. separation dummy emulation method is put in throwing according to any one of claim 1-3, it is characterised in that: the static throwing
Separation is put to refer to and separate the separation assembly under stationary state；The dynamic throwing is put separation and is referred to under simulated flight state
Separation assembly separated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610780666.2A CN106249617B (en) | 2016-08-30 | 2016-08-30 | Separation dummy emulation method is put in a kind of throwing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610780666.2A CN106249617B (en) | 2016-08-30 | 2016-08-30 | Separation dummy emulation method is put in a kind of throwing |
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| Publication Number | Publication Date |
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| CN106249617A CN106249617A (en) | 2016-12-21 |
| CN106249617B true CN106249617B (en) | 2019-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610780666.2A Active CN106249617B (en) | 2016-08-30 | 2016-08-30 | Separation dummy emulation method is put in a kind of throwing |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107891993B (en) * | 2017-08-30 | 2020-12-29 | 陕西千山航空电子有限责任公司 | Safety testing method for trigger logic of detonating device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0560495A (en) * | 1991-09-04 | 1993-03-09 | Mitsubishi Heavy Ind Ltd | Guidance control device for missile |
| KR20070045758A (en) * | 2005-10-28 | 2007-05-02 | 정철 | Water rocket launching set for learning |
| CN202362842U (en) * | 2011-12-14 | 2012-08-01 | 陕西千山航空电子有限责任公司 | Flight data and audio recorder |
| CN103065372A (en) * | 2012-12-07 | 2013-04-24 | 陕西千山航空电子有限责任公司 | Aviation recorder and automatic positioning method |
| CN105160084A (en) * | 2015-08-19 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Ejection escape simulation method |
-
2016
- 2016-08-30 CN CN201610780666.2A patent/CN106249617B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0560495A (en) * | 1991-09-04 | 1993-03-09 | Mitsubishi Heavy Ind Ltd | Guidance control device for missile |
| KR20070045758A (en) * | 2005-10-28 | 2007-05-02 | 정철 | Water rocket launching set for learning |
| CN202362842U (en) * | 2011-12-14 | 2012-08-01 | 陕西千山航空电子有限责任公司 | Flight data and audio recorder |
| CN103065372A (en) * | 2012-12-07 | 2013-04-24 | 陕西千山航空电子有限责任公司 | Aviation recorder and automatic positioning method |
| CN105160084A (en) * | 2015-08-19 | 2015-12-16 | 中国航空工业集团公司西安飞机设计研究所 | Ejection escape simulation method |
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| CN106249617A (en) | 2016-12-21 |
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