CN108009315B - Simulation analysis method for zero-length transmitting device - Google Patents
Simulation analysis method for zero-length transmitting device Download PDFInfo
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Abstract
The invention discloses a simulation analysis method of a zero-length launching device, which comprises the steps of firstly establishing a three-dimensional model of each part of an unmanned aerial vehicle launching device; according to the mutual relation among all parts of the unmanned aerial vehicle launching device, completing a topological structure model of all parts of the unmanned aerial vehicle launching device, and creating constraint conditions according to the topological structure relation; applying all external loads to the simulation model; solving the launching process of the unmanned aerial vehicle on the launching device to complete the establishment of the unmanned aerial vehicle launching simulation model; carrying out simulation and outputting a simulation result; and comparing and analyzing the simulation data with the simulated emission test data to judge the correctness of the simulation method. The simulation analysis method replaces a physical test, has low requirement on hardware, simple realization condition, short period and good repeatability, can virtually verify the design scheme, can accurately predict the test result, has good visual effect, can reduce the development cost and shorten the development period.
Description
Technical Field
The invention relates to the field of simulation analysis, in particular to a simulation analysis method for a zero-length transmitting device, and particularly relates to a simulation analysis method for safe separation of an unmanned aerial vehicle on the zero-length transmitting device.
Background
The zero-length launching device is an important component in a weapon system and is used for transportation fixing and launching of the unmanned aerial vehicle. In the process of developing the launching device, the reasonability of design parameters such as a launching angle, locking force, off-orbit attitude and the like of the launching device and the safety in the launching process need to be verified. In the past, all design indexes of a launching device need to be verified through a boosting launching test, but the test has the defects of high difficulty, high cost and long period.
Disclosure of Invention
In view of the above-mentioned situation in the prior art, an object of the present invention is to provide a simulation analysis method for a zero-length transmitting device, which is used to replace a physical test to verify various design indexes of the transmitting device, and has the advantages of simple implementation conditions, short period and low cost.
The above object of the present invention is achieved by the following technical solutions:
a method of simulation analysis of a zero-length transmitting device, the method comprising: firstly, establishing a three-dimensional model of each part of an unmanned aerial vehicle launching device; according to the mutual relation among all parts of the unmanned aerial vehicle launching device, completing a topological structure model of all parts of the unmanned aerial vehicle launching device, and creating constraint conditions according to the topological structure relation; applying all external loads to the simulation model; solving the launching process of the unmanned aerial vehicle on the launching device to complete the establishment of the unmanned aerial vehicle launching simulation model; carrying out simulation and outputting a simulation result; and comparing and analyzing the simulation data with the simulated emission test data to judge the correctness of the simulation method.
Further wherein the constraints include fixed pair constraints, revolute pair constraints and contact constraints.
Further, the correctness of the simulation method is judged according to a correlation coefficient method and curve goodness of fit.
Further, the simulation output result comprises time variation curves of displacement, speed, acceleration, angle and angular speed at the center of mass of the unmanned aerial vehicle.
Furthermore, the method can also comprise the step of reasonably simplifying the model when the three-dimensional model of each part of the transmitting device is established.
The simulation analysis method replaces a physical test, has low requirement on hardware, simple realization condition, short period and good repeatability, can virtually verify the design scheme, can accurately predict the test result, has good visual effect, can reduce the development cost and shorten the development period.
Has the advantages that:
1) the simulation analysis method has lower requirements on hardware, simpler implementation conditions, short period and good repeatability;
2) the design scheme can be virtually verified, the test result can be accurately predicted, and meanwhile, a good visual effect is achieved;
3) the design indexes of the transmitting device can be verified by replacing a physical test;
4) can reduce the development cost, shorten the development period and improve the design efficiency.
Drawings
FIG. 1 schematically illustrates a zero-length emission three-dimensional solid model;
FIG. 2 schematically illustrates a simulation model of a transmitting device created using the method of the present invention;
FIG. 3 is a plot of unmanned aerial vehicle angle versus time obtained from simulation and testing;
fig. 4 is a graph of the angular velocity of the drone as a function of time, obtained by simulation and experiment.
Detailed description of the invention
For a clearer understanding of the objects, technical solutions and advantages of the present invention, the present invention will be described in further detail below with reference to the accompanying drawings and embodiments.
The zero-length launching device is an important component in a weapon system and is used for transportation fixing and launching of the unmanned aerial vehicle. In the process of developing the launching device, the reasonability of design parameters such as a launching angle, locking force, off-orbit attitude and the like of the launching device and the safety in the launching process need to be verified. At present, various design indexes of the launching device need to be verified through a boosting launching test. Fig. 1 schematically shows a zero-length emission three-dimensional solid model. As shown in the figure, among the solid model, adapter 1 is fixed subaerial, base 2 is fixed on adapter 1 through bolted connection, tilting mechanism 4 is connected with base 2 through the round pin axle, guide rail 11 passes through bolted connection on base 2's back supporting seat, electric plug separating mechanism 8 and boosting rocket docking mechanism 10 pass through round pin hub connection on base 2, boosting rocket 9 cup joints on unmanned aerial vehicle 6, unmanned aerial vehicle 6's preceding supporting shaft 5 falls in tilting mechanism 4 draw-in groove, back supporting shaft 7 falls in guide rail 11, tilting mechanism 4 and guide rail 11 fixed bearing and restraint unmanned aerial vehicle 6, tilting mechanism 4 links firmly through shear pin 3 and base 2, when unmanned aerial vehicle 6 launches, under the effect of boosting rocket 9, tilting mechanism 4 rotates, cut shear pin 3, unmanned aerial vehicle 6 moves along guide rail 11 forward. The material object test has the defects of high difficulty, high cost and long period.
In the embodiment, the simulation analysis method is adopted to replace a physical test because the simulation analysis method has lower requirements on hardware and simpler implementation conditions. The working principle is that a three-dimensional model of the launching device is established firstly, then the launching device is led into Adams software, constraint conditions are added according to the topological structure relation of a launching system, all external loads are applied to a simulation model, a solver and a solving algorithm are set, a required simulation result is output and is compared and analyzed with simulated launching test data, and the correctness of the simulation method is judged according to a correlation coefficient method and curve goodness of fit.
Specifically, the simulation analysis method for the zero-length transmitting device comprises the following steps:
the method comprises the following steps: and (4) geometric modeling. And establishing a three-dimensional model of each part of the transmitting device by using three-dimensional modeling software Catia, carrying out reasonable model simplification according to conditions, opening the model in UG, carrying out export operation, storing each part model in an x _ t format, and importing the model in the x _ t format into Adams.
Step two: a constraint is created. According to the mutual relation among all parts of the unmanned aerial vehicle launching device, a topological structure model of the unmanned aerial vehicle launching device is completed, according to the topological structure relation, the adapter is fixed on the ground, the base is fixedly connected with the adapter, and fixed pair constraints are added; the base and the turnover mechanism are in a rotating relationship, the link mechanisms in the turnover mechanism are in a rotating relationship, and a revolute pair constraint is added; collisions can occur during relative motion between the drone support shaft and the guide rail, thus creating contact constraints.
Step three: a load is applied. The method for applying the thrust of the boosting rocket is characterized in that an AKISPL function is used in Adams and loaded on an unmanned aerial vehicle, and the calling format is as follows: AKISPL (time,0, SPLINE _ CW, 0); applying the thrust of a main engine, wherein the thrust of the main engine is a fixed value, and applying a concentrated force at the center of a tail nozzle of the engine; the method for applying the locking force comprises the steps of setting a shear pin as a fixed pair, describing by using a simulation control script statement, and carrying out simulation on the locking force, wherein the control description statement is as follows: SIMULATE/DYNAMIC, END 0.005, STEPS 10; DEACTIVATE/join, ID 28.
Step four: and setting a solver. Establishing a script control file, wherein a control description statement is as follows: SIMULATE/DYNAMIC, END 0.005, STEPS 10; DEACTIVATE/join, ID 28; simple/DYNAMICs, END 0.5, and stages 1000. And (3) adopting a Dynamic solving algorithm, selecting a GSTIFF rigid digital integral method and an S12 integral format, setting the error as 1.0E-003, and carrying out differential and algebraic equation solving on the launching process of the unmanned aerial vehicle on the launching device to complete the establishment of the unmanned aerial vehicle launching simulation model.
Step five: and outputting the simulation data. And (4) carrying out simulation, after the simulation is finished, opening an Adams/Postprocessor post-processing interface, and outputting time variation curves of displacement, speed, acceleration, angle, angular speed and the like at the center of mass of the unmanned aerial vehicle.
Step six: and (5) testing and verifying. After the simulation result is output, in order to ensure the correctness of the simulation result, a zero-length launching stand simulation launching test is carried out in a laboratory, the turnover angle and the angular speed of the turnover mechanism are recorded by a high-speed camera, the data of the angle and the angular speed of the turnover mechanism obtained by the test are compared and analyzed with the simulation data, the trend of the motion curve of the simulation launching test data is matched with that of the simulation data, and the values of the simulation data and the test data are calculated to be more than 0.95 according to a correlation coefficient method, so that the simulation result is proved to be reasonable and correct, as shown in fig. 3 and 4.
While the principles and specific embodiments of this invention have been described above, those skilled in the art, having the benefit of the teachings herein, will appreciate numerous modifications and variations from the described embodiments, which fall within the scope of the invention. It will be appreciated by persons skilled in the art that the foregoing detailed description is provided for the purpose of illustrating the invention and is not to be construed as limiting the invention. The scope of the invention is defined by the claims and their equivalents.
Claims (2)
1. A simulation analysis method for a zero-length transmitting device comprises the following steps:
firstly, establishing a three-dimensional model of each part of an unmanned aerial vehicle launching device, comprising the following steps: establishing a three-dimensional model of each part of the transmitting device by using three-dimensional modeling software Catia, storing each part model as an x _ t format, and importing the model in the x _ t format into Adams;
according to the mutual relation among all parts of the unmanned aerial vehicle launching device, completing a topological structure model of all parts of the unmanned aerial vehicle launching device, and according to the topological structure relation, creating constraint conditions, wherein the constraint conditions comprise fixed pair constraints of a base and a transfer base; revolute pair constraints are arranged between the base and the turnover mechanism and between the connecting rod mechanisms in the turnover mechanism; contact constraint between the unmanned aerial vehicle support shaft and the guide rail;
applying all external loads on the simulation model, including applying boosting rocket thrust, and loading the external loads on the unmanned aerial vehicle by using an AKISPL function in Adams; applying the thrust of a main engine, wherein the thrust of the main engine is a fixed value, and applying a concentrated force at the center of a tail nozzle of the engine; applying locking force, setting the shear pin as a fixed pair, and performing simulation on the locking force by using the statement description of a simulation control script;
solving the launching process of the unmanned aerial vehicle on the launching device to complete the establishment of the unmanned aerial vehicle launching simulation model, wherein the establishment of the unmanned aerial vehicle launching simulation model comprises establishing a script control file, adopting a Dynamic solving algorithm, selecting a GSTIFF rigid digital integration method and an S12 integration format, setting the error to be 1.0E-003, and performing differential and algebraic equation solution on the launching process of the unmanned aerial vehicle on the launching device to complete the establishment of the unmanned aerial vehicle launching simulation model;
carrying out simulation and outputting a simulation result, wherein the simulation result comprises the time variation curves of displacement, speed, acceleration, angle and angular speed at the mass center of the unmanned aerial vehicle;
and comparing and analyzing the data with the simulated launch test data to judge the correctness of the simulation method, wherein the method comprises the steps of recording the turnover angle and the angular speed of the turnover mechanism by a high-speed camera, comparing and analyzing the turnover mechanism angle and angular speed data obtained by the test with the simulation data to obtain the coincidence of the motion curve trends of the simulated launch test data and the simulation data, and calculating the values of the simulation data and the test data according to a correlation coefficient method.
2. The method of claim 1, further comprising processing the model to make it reasonably simple when building a three-dimensional model of the components of the transmitting device.
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