CN108009315A - A kind of zero length lauuch device simulation analysis method - Google Patents
A kind of zero length lauuch device simulation analysis method Download PDFInfo
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Abstract
The present invention discloses a kind of zero length lauuch device simulation analysis method, including initially sets up the threedimensional model of each parts of unmanned plane emitter；According to the correlation between each parts of unmanned plane emitter, the topology controlment of each parts of unmanned plane emitter is completed, according to topological structure relation, creates constraints；All external loads are applied on simulation model；To unmanned plane, emission process solves on emitter, completes the foundation of unmanned plane launching simulation model；Emulated and export simulation result；Compared and analyzed with analog transmissions test data, judge the correctness of emulation mode.The present invention replaces actual loading test by simulation analysis, simulating analysis is relatively low to hardware requirement, realize that condition is relatively simple, it is reproducible and the cycle is short, it can virtually verify designing scheme, can also prediction experiment result exactly, also there is good visual effect at the same time, research fund can be reduced, shorten the lead time.
Description
Technical field
The present invention relates to simulation analysis field, and in particular to a kind of zero length lauuch device simulation analysis method, particularly one
The simulating analysis of kind unmanned plane safe separating on zero length lauuch device.
Background technology
Zero length lauuch device is important component in weapon system, transport fixation and transmitting for unmanned plane.Sending out
, it is necessary to verify the reasonability of the design parameters such as the angle of departure of emitter, blocking force, the posture that leaves the right or normal track in injection device development process,
And the security in emission process.Need to verify emitter items design objective by launch assist experiment in the past, so
And test there are difficulty is big, of high cost, the shortcomings that cycle is long.
The content of the invention
In view of the above situation of the prior art, the object of the present invention is to provide a kind of zero length lauuch device simulation analysis side
Method, for replacing actual loading test to verify emitter items design objective, realizes that condition is relatively simple, and the cycle is short, into
This is low.
The above-mentioned purpose of the present invention is realized using following technical solution：
A kind of zero length lauuch device simulation analysis method, the described method includes：Initially set up unmanned plane emitter each zero
The threedimensional model of component；According to the correlation between each parts of unmanned plane emitter, it is each to complete unmanned plane emitter
The topology controlment of parts, according to topological structure relation, creates constraints；All external loads are applied to emulation mould
In type；To unmanned plane, emission process solves on emitter, completes the foundation of unmanned plane launching simulation model；Imitated
It is true and export simulation result；Compared and analyzed with analog transmissions test data, judge the correctness of emulation mode.
Further, wherein the constraints includes fixed joint constraint, revolute pair constraint and contiguity constraint.
Further, wherein the correctness for judging emulation mode is carried out according to correlation coefficient process and curves degree.
Further, wherein simulation data result includes displacement, speed, acceleration, angle and the angle at unmanned plane barycenter
The time changing curve of speed.
Further, when the method may additionally include the threedimensional model for establishing each parts of emitter, to model into
The processing of row Rational Simplification.
The present invention by simulation analysis replaces actual loading test, and simulating analysis is relatively low to hardware requirement, realize condition compared with
To be simple, and the cycle is short, reproducible, can virtually verify designing scheme, moreover it is possible to which prediction experiment is as a result, at the same time also exactly
With good visual effect, research fund can be reduced, shortens the lead time.
Beneficial effect：
1) simulating analysis is relatively low to hardware requirement, realizes that condition is relatively simple, and the cycle is short, reproducible；
2) designing scheme can be virtually verified, moreover it is possible to which prediction experiment as a result, also have good visual effect at the same time exactly；
3) emitter items design objective can be verified instead of actual loading test；
4) research fund can be reduced, shortens the lead time, there is provided design efficiency.
Brief description of the drawings
Fig. 1 schematically illustrates zero length lauuch three-dimensional entity model；
Fig. 2 schematically illustrates the emitter simulation model established using the method for the present invention；
Fig. 3 is the curve that the unmanned plane angle that emulation and experiment obtain changes over time；
Fig. 4 is the curve that the unmanned plane angular speed that emulation and experiment obtain changes over time.
Specific implementation method
In order to be more clearly understood that the objects, technical solutions and advantages of the present invention, with reference to the accompanying drawings and embodiments, to this
Invention is further elaborated.
Zero length lauuch device is important component in weapon system, transport fixation and transmitting for unmanned plane.Sending out
, it is necessary to verify the reasonability of the design parameters such as the angle of departure of emitter, blocking force, the posture that leaves the right or normal track in injection device development process,
And the security in emission process.Need to verify emitter items design objective by launch assist experiment at present.Fig. 1
Schematically illustrate zero length lauuch three-dimensional entity model.As shown in the figure, in the physical model, adapter 1 fixes on the ground,
Base 2, which is bolted, to be fixed on adapter 1, and switching mechanism 4 is connected by axis pin with base 2, and guide rail 11 passes through bolt
It is connected on the rear branching holder of base 2, plug separating mechanism 8 and booster rocket docking mechanism 10 are connected to base by axis pin
On 2, booster rocket 9 is socketed on unmanned plane 6, and the front support axis 5 of unmanned plane 6 falls in 4 card slot of switching mechanism, rear support axis 7
Fall in guide rail 11, switching mechanism 4 and 11 fixed bearing of guide rail and constraint unmanned plane 6, switching mechanism 4 pass through shear pin 3 and bottom
Seat 2 is connected, and when unmanned plane 6 is launched, under the effect of booster rocket 9, switching mechanism 4 rotates, and shear pin 3 is cut, 6 edge of unmanned plane
Guide rail 11 travels forward.The shortcomings that actual loading test is big there are difficulty, of high cost, and the cycle is long.
Since simulating analysis is relatively low to hardware requirement, realize that condition is relatively simple, in embodiment, using emulation point
Analysis method replaces actual loading test.Operation principle is to initially set up emitter threedimensional model, is then introduced into Adams softwares,
According to the topological structure relation of emission system, constraints is added, all external loads are applied on simulation model, setting is asked
Device and derivation algorithm are solved, exports required simulation result, and is compared and analyzed with analog transmissions test data, according to correlation
Y-factor method Y and curves degree judge the correctness of emulation mode.
Specifically, zero length lauuch device simulation analysis method of the invention, comprises the following steps：
Step 1：Geometric Modeling.Using 3 d modeling software Catia, the threedimensional model of each parts of emitter is established,
And rational model simplification can be optionally carried out, above-mentioned model is opened in UG, carries out export operation, each part model is separately deposited
For x_t forms, the model of x_t forms is imported in Adams.
Step 2：Create constraint.According to the correlation between each parts of unmanned plane emitter, its topology knot is completed
Structure model, according to its topological structure relation, adapter is fixed on big ground, and base is connected with adapter, adds fixed joint
Constraint；It is rotation relation between base and switching mechanism, is rotation relation between switching mechanism inner link mechanism, addition rotates
Pair constraint；It can collide during relative motion between unmanned plane support shaft and guide rail, therefore create contiguity constraint.
Step 3：Apply load.Apply booster rocket thrust method, AKISPL functions are utilized in Adams, are loaded in nothing
Above man-machine, its call format is：AKISPL(time,0,SPLINE_CW,0)；Apply the thrust of sustainer, sustainer
Thrust is a definite value, and a concentrated force is added at nozzle center；Apply blocking force method, shear pin is arranged to
Fixed joint, is described using Simulation Control script sentence, carries out the analog simulation of blocking force, controls the descriptive statement to be：
SIMULATE/DYNAMIC, END=0.005, STEPS=10；DEACTIVATE/JOINT, ID=28.
Step 4：Solver is set.Scripting control file is established, controls the descriptive statement to be：SIMULATE/DYNAMIC,
END=0.005, STEPS=10；DEACTIVATE/JOINT, ID=28；SIMULATE/DYNAMIC, END=0.5, STEPS
=1000.Using Dynamic derivation algorithms, and GSTIFF rigidity digital integration method and S12 Integration Schemes are selected, error setting
For 1.0E-003, to unmanned plane, emission process carries out differential and algebraic equation solving on emitter, completes unmanned plane transmitting
The foundation of simulation model.
Step 5：Output emulation data.Emulated, after the completion of emulation, open Adams/PostProcessor post processings
Interface, exports the time changing curve of displacement, speed, acceleration, angle and the angular speed etc. at unmanned plane barycenter.
Step 6：Verification experimental verification.After simulation result output, for the correctness of simulation result, distance of zero mark is carried out in laboratory
Launcher analog transmissions are tested, and the flip angle and switching mechanism angular speed of switching mechanism are recorded by high-speed camera, will be tried
Test acquisition switching mechanism angle and angular velocity data with emulation data compare and analyze, draw analog transmissions test data and
The curve movement trend of emulation data matches, and according to correlation coefficient process, calculates the value for emulating data and test data
Both greater than 0.95, it was demonstrated that simulation result is rationally correct, as shown in Figures 3 and 4.
Although described above is the principle of the present invention and embodiment, under the above-mentioned guidance of the present invention,
Those skilled in the art can carry out various improvement and deformation on the basis of above-described embodiment, and these are improved or deformation falls
Within the scope of the present invention.It will be understood by those skilled in the art that above-mentioned specific description is intended merely to explain the present invention
Purpose, be not intended to limit the present invention.Protection scope of the present invention is limited by claim and its equivalent.
Claims (5)
1. a kind of zero length lauuch device simulation analysis method, including：
Initially set up the threedimensional model of each parts of unmanned plane emitter；
According to the correlation between each parts of unmanned plane emitter, the topology of completion each parts of unmanned plane emitter
Structural model, according to topological structure relation, creates constraints；
All external loads are applied on simulation model；
To unmanned plane, emission process solves on emitter, completes the foundation of unmanned plane launching simulation model；
Emulated and export simulation result；
Compared and analyzed with analog transmissions test data, judge the correctness of emulation mode.
2. in accordance with the method for claim 1, wherein the constraints includes fixed joint constraint, revolute pair constraint and contact
Constraint.
3. in accordance with the method for claim 1, wherein the correctness for judging emulation mode is according to correlation coefficient process and curve
What the goodness of fit carried out.
4. in accordance with the method for claim 1, wherein simulation data result include unmanned plane barycenter at displacement, speed, plus
The time changing curve of speed, angle and angular speed.
5. in accordance with the method for claim 1, be additionally included in the threedimensional model for establishing each parts of emitter, to model
Carry out the processing of Rational Simplification.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110990947A (en) * | 2019-11-19 | 2020-04-10 | 中国人民解放军总参谋部第六十研究所 | Multi-field coupling simulation analysis method for launching process of rocket-assisted unmanned aerial vehicle |
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