CN102789526B - Analog calculating method for landing buffering process of equipment air drop - Google Patents
Analog calculating method for landing buffering process of equipment air drop Download PDFInfo
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Abstract
The invention relates to the technical field of simulation evaluation of an air drop technology, in particular to an analog calculating method for the landing buffering process of the equipment air drop. The analog calculating method comprises the following three implementing steps of: establishing a finite element model of an equipment-airbag system by a computer; carrying out analog calculation on the landing buffering process of the equipment air drop on the basis of a nonlinear finite element; and generating an analog result of the landing buffering process of the equipment air drop. The analog calculating method implements the simulation on the landing buffering process of the equipment air drop on the basis of a nonlinear finite element method and also acquires a simulation calculation method for the airbag buffering characteristic of the equipment-airbag system and the equipment impact response characteristic, provides an effective measure for the demonstration, design and development work of air drop equipment, and solves the problems of high risk, high cost and long period of the equipment air drop test.
Description
Technical field
The present invention relates to air-drop technology Simulation Evaluation technical field, refer in particular to a kind of simulation method equipping airborn landing buffering course.
Background technology
If directly contacted to earth when landing after being equipped in parachuting, moment impact overload will damage the physical construction of equipment and the instrument and equipment of inside.Therefore need to absorb a part of impact energy by energy absorbing device.Widely used energy absorbing device mainly contains compressible material, braking rocket and air bag buffer system.Air bag buffer system is compared other energy absorbing device and is had that structure is simple, easy to use, good buffer effect and low cost and other advantages.Air bag buffer system, mainly through the buffering of air bag, absorbs most of impact energy when landing, and alleviates the impact being equipped in and landing suffered by moment.Due to the multiple advantages of air bag buffer system, be widely used in the field that traffic, space flight and air-drop etc. exist greater impact, air bag buffer system becomes one of important component part of equipment aerial delivery system gradually in recent years.
Started to the research of landing cushion gasbag abroad the latter stage fifties.The early stage aerothermodynami that mainly utilizes is theoretical, set up the analytical calculation model of buffer air bag, studied the damping characteristics of air bag by research air bag by the change of internal gas parameter in compression process, the NASA that the ESGAR of the U.S. etc. delivered in nineteen sixty reports in " Analytical Study of Soft Landings on Gas-Filled Bags " literary composition shape and structure, dimensional parameters, opening pressure and the exhaust port area etc. of adopting and discussing air bag in this way and requires the relation between index and the relation that influences each other between each parameter.Along with the development of computing technique, non-linear finite element method is widely adopted in air bag specificity analysis, be published in " Investigation Of The Application Of Airbag Technology To Provide A Soft Landing Capability For Military Heavy Airdrop " literary composition of AIAA in calendar year 2001, the Taylor of the U.S. adopts the air-drop air bag damping characteristics of explicit finite element to brave carriage to carry out simulation analysis and Experimental Comparison, demonstrates the validity of finite element method.
The domestic research to buffer air bag starts from the latter stage nineties.In " Cushioning Characteristics of Air Bag for RPV Recovery research " literary composition that " Nanjing Aero-Space University's journal " the 4th phase in 1999 delivers, the dagger-axe heir of Nanjing Aero-Space University really waits and is studied the air bag damping characteristics of unmanned aircraft parachute descent-air bag recovery system, with single air bag for object, analyze the principal element affecting shock-absorbing capacity, research shows that mass volume ratio and exhaust port area are the principal elements determining buffering effect.In " air bag cushions the experimental study of dummy vehicle landing characteristics " literary composition that " experimental technique and testing machine " the 1st phase in 2003 delivers, the people such as the Wan Zhimin of Harbin Institute of Technology adopt the method for experimental study to test the impact of pressure on damping characteristics in closed airbag feature, the landing characteristics of the dummy vehicle of experimental test two kinds equipment air bag buffer systems, studies fundamental characteristics in Landing Buffer process of the aircraft that draws and affects the factor of landing stability.In " emulation of cargo airdrop system air bag buffering course " literary composition that " Journal of System Simulation " the 14th phase in 2007 delivers, Wang Yawei, Yang Chunxin etc. of BJ University of Aeronautics & Astronautics establish cargo airdrop system air bag simulation model of airbag cushion process based on thermodynamics method, consider the change of exhaust port area in the actual buffering course of work, effectively simulate the actual working characteristics of this type buffer air bag.
From domestic and international research conditions, the experimental test of physical prototyping is mainly adopted, based on methods such as thermodynamic (al) analytical analysis and nonlinear finite element method with assessment to the design and analysis of buffer air bag.The method of the experimental test of physical prototyping the most directly and truly can reflect the characteristic of buffer air bag, but generally the experimental test difficulty of physical prototyping is comparatively large, poor repeatability, cost are high, the cycle is long, security is low and some extreme operating condition cannot realize by testing.Based on thermodynamic (al) analytic method be by research air bag studied the buffer action of air bag by the change of internal gas parameter in compression process, the method is easier, computational accuracy can meet general requirement of engineering, there is good engineer applied, but accurately cannot calculate air bag distortion, vertical landing operating mode can only be analyzed.Nonlinear finite element method is on the basis of thermodynamics method, by to airbag wall grid division, calculate the distortion of not air bag in the same time, thus accurately calculate any time air bag distortion in landing mission and be out of shape gas parameter change and damping characteristics in the capsule that causes, the method calculates accurately, can air bag damping characteristics under the various landing operating mode of analog computation, the air bag damping characteristics particularly under extreme operating condition.But because nonlinear finite element method modeling is complicated, in existing research, generally adopt the experimental test of physical prototyping and study equipment air-drop based on the method for thermodynamic (al) analytical analysis, nonlinear finite element method lacks practical application in equipment landing buffering course dynamic simulation calculates.
Therefore, the present invention for research object, proposes a kind of simulation method adopting the equipment airborn landing buffering course of nonlinear finite element method with equipment-gas-bag system, for air-drop equipment demonstration, design and development work significant.
Summary of the invention
The object of the invention is to the simulation method that equipment airborn landing buffering course is provided for the deficiencies in the prior art, this simulation method achieves the simulation to equipment airborn landing buffering course based on nonlinear finite element method, obtain the air bag damping characteristics of equipment-gas-bag system and the emulated computation method of equipment shock response characteristic simultaneously, for the demonstration of air-drop equipment, design and development work provide effective means, solve the excessive risk of equipment airdrop test, high cost and macrocyclic problem.
For achieving the above object, a kind of simulation method equipping airborn landing buffering course of the present invention, comprise: the first step, set up the finite element model of equipment-gas-bag system by computing machine, the finite element model of described equipment-gas-bag system comprises equipment finite element model, air bag finite element model and equips and the contact model of air bag;
Second step, based on the analog computation of the equipment airborn landing buffering course of nonlinear finite element, the implementation step of described analog computation is as follows: 1) solve with progressive failure and calculate equipment finite element model, 2) control volume mothod is adopted to resolve air bag finite element model, 3) contact model of equipment and air bag is resolved, at equipment with the contact model of air bag, the bottom of equipment is defined as interarea, the upper surface of air bag is defined as from face, by from the power of face node with to calculate the additional mass of interarea node from face node and obtain the speed of interarea node and the acceleration of interarea node, equipment calculates the average rigid body displacement based on unit with the contact of air bag, be connected from the barycenter of face node with the unit of interarea, power and inertia transfer to interarea node by from face node, each node of interarea corresponding unit is reassigned to from the square of face node, point face contact between the different piece of each air bag module and between adjacent each air bag module adopts penalty function method to solve, each face of air bag is interarea is also from face, each time step first checks respectively whether penetrate interarea from face node, if do not penetrate interarea, then this is left intact from face node, if penetrate interarea, then at this from face node and penetrated between interarea and introduce a normal direction contact force, the size of this normal direction contact force and penetration depth, interarea rigidity is directly proportional,
3rd step: the analog result of equipment airborn landing buffering course generates, and is obtained and equip the analog result of airborn landing buffering course by calculating, described analog result comprises air bag damping characteristics and equipment shock response characteristic.
Wherein, Johnson-Cook strength of materials model is adopted to be described the material constitutive model of equipment in described equipment finite element model, described Johnson-Cook strength of materials model is an ideal elastic-plastic strength model that can reflect strain hardening, strain rate hardening effect and temperature softening effect, and its expression formula is as follows:
In formula,
for flow stress;
for yield stress;
for hardening Plastic parameter;
for rate of strain coefficient;
for hardenability value;
for plastic strain;
for rate of strain;
for reference rate of strain;
for kelvin degree;
for temperature of fusion;
for initial temperature;
for humidity index.
Wherein, the contact model of described equipment and air bag adopts consolidation style, fricton-tight each other, and the contact relation between the different piece of each air bag module and between adjacent each air bag module adopts some face contact to describe.
Wherein, the precision of described analog result is verified by adopting the test figure of typical condition, and the simulation then carrying out the equipment airborn landing buffering course of various different operating mode on this basis goes forward side by side luggage for structural strength assessment and air bag structure optimization matched design.
Beneficial effect of the present invention: 1) the present invention adopts emulation technology to establish equipment-gas-bag system model, comparatively accurately reflect the dynamic response characteristic of equipment airborn landing buffering course, on the basis of verification experimental verification, alternate test the research of equipping airborn landing buffering course be can carry out, the excessive risk of equipment airdrop test, high cost and long period problem solved;
2) present invention achieves the simulation to equipment airborn landing buffering course based on nonlinear finite element method, obtain the air bag damping characteristics of equipment-gas-bag system and the emulated computation method of equipment shock response characteristic, for the demonstration of air-drop equipment, design and development work provide effective means simultaneously.
Accompanying drawing explanation
Fig. 1 is process flow diagram of the present invention.
Fig. 2 is weight mass and the multi-point constraint simulation drawing of large parts in assembling model of the present invention.
Fig. 3 is the contact relation schematic diagram of equipment-gas-bag system of the present invention.
Fig. 4 is the analog result figure of equipment airborn landing buffering course of the present invention.
Fig. 5 is the Comparative result figure of test of the present invention and simulation.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in detail.
As shown in Figures 1 to 5, a kind of simulation method equipping airborn landing buffering course of the present invention, described simulation method comprises the finite element model by computing machine foundation equipment-gas-bag system, the analog computation based on the equipment airborn landing buffering course of nonlinear finite element and equips the analog result generation three large implementation steps of airborn landing buffering course.Wherein,
The first step, sets up the finite element model of equipment-gas-bag system by computing machine, and the finite element model of described equipment-gas-bag system comprises equipment finite element model, air bag finite element model and equips and the contact model of air bag.Utilize HyperWorks software in Hypermesh module, build equipment finite element model and air bag finite element model, and the contact model with air bag is equipped in definition on this basis.
Wherein, Johnson-Cook strength of materials model is adopted to be described the material constitutive model of equipment in described equipment finite element model, described Johnson-Cook strength of materials model is an ideal elastic-plastic strength model that can reflect strain hardening, strain rate hardening effect and temperature softening effect, and its expression formula is as follows:
In formula,
for flow stress;
for yield stress;
for hardening Plastic parameter;
for rate of strain coefficient;
for hardenability value;
for plastic strain;
for rate of strain;
for reference rate of strain;
for kelvin degree;
for temperature of fusion;
for initial temperature;
for humidity index.
As shown in Figure 2, the described HyperWorks of utilization software builds equipment finite element model and the construction method of air bag finite element model is in Hypermesh module:
Set up the three-dimensional entity model of equipment according to design drawing and actual, measured dimension, adopt different unit to carry out stress and strain model for the version of different parts or system in equipment.Large parts in equipment model utilize weight mass and multi-point constraint simulation, model includes 110677 unit and 115294 nodes, in the present embodiment, equipment configuration material mainly adopts the aluminium alloy that quality is light, intensity is high, plasticity is good, and its physical characteristics parameter is as shown in table 1.
Table 1 equipment configuration physical characteristics of materials parameter
| Density (g/mm 3) | Elastic modulus (MPa) | Poisson ratio | Yield strength (Mpa) | Tensile strength (Mpa) |
| 2.7×10 -3 | 72000 | 0.35 | 265 | 410 |
Buffer air bag adopts shell unit grid division, is made up of 78754 unit and 77286 nodes.
As shown in Figure 3, equipment and gas-bag system upper surface are completely fixed, and namely the force and moment of all directions can stably transmit.Therefore, equipment adopts consolidation style with the contact model of air bag, fricton-tight each other.The change of air bag shape in the course of the work and position is very complicated, because in Landing Buffer process, air bag can produce compression deformation, between the different piece of therefore each air bag module and can contact relation be produced between adjacent each air bag module, in order to determine the changes shape that buffer air bag is last, some face contact is adopted to describe this part contact relation.
Second step, based on the analog computation of the equipment airborn landing buffering course of nonlinear finite element, the implementation step of described analog computation is as follows:
1) calculating equipment finite element model is solved with progressive failure, described progressive failure is different from implicit integration algorithm, progressive failure is without the need to setting up stiffness matrix and inversion operation, but adopt central difference method explicit solution finite element equation, and by single-point Gauss integration and lumped mass, improve solving speed, there is the advantage of saving computing time and storage space and being easy to process problem.In Explicit Finite Element Analysis, adopt lumped mass matrix to solve collision movement equation and directly obtain acceleration, then speed is obtained to time integral, then integration once obtains displacement.Here adopt the explicit form of central difference to carry out time integral, the explicit form of central difference is:
2) adopt control volume mothod to resolve air bag finite element model, first suppose: 1. equip the buffer action only considering air bag in airborn landing process, ignore aerodynamic drag; 2. ignore the air leakage of airbag wall, in capsule, air is mainly discharged from vent port; 3. in air bag, interior pressure is more or less the same everywhere, and its air pressure inside is uniform; 4. because Landing Buffer process time is extremely short, have little time the exchange carrying out heat with the external world, think that buffering course is adiabatic process, in capsule, gas is ideal gas.
In the calculating of finite element, in air bag, gas volume can be calculated by following formula:
Wherein,
for unit
's
the mean value of coordinate;
for unit normal and
direction cosine between direction;
for unit
surface area.
Air bag is regarded as the control volume constantly expanded, the rate of change controlling volume internal gas quality is determined by the gas mass flow of inlet and outlet air bag.
In formula,
for gas mass flow variable quantity in air bag;
for entering the gas mass flow of air bag;
for discharging the gas mass flow of air bag.
In actual condition, before Landing Buffer process, buffer air bag is full of completely, and its gas replenishment process does not affect landing buffering course, therefore only needs the gas mass flow considering to discharge air bag.The gas mass flow of discharging air bag calculates by following formula:
In formula,
for coefficient of flow;
for ventilation aperture area;
for gaseous tension in air bag;
for gas law constant;
for gas temperature in air bag;
for external pressure;
for the specific heat ratio of gas in air bag.
3) contact model of equipment and air bag is resolved, at equipment with the contact model of air bag, the bottom of equipment is defined as interarea, the upper surface of air bag is defined as from face, by from the power of face node with to calculate the additional mass of interarea node from face node and obtain the speed of interarea node and the acceleration of interarea node, equipment calculates the average rigid body displacement based on unit with the contact of air bag, be connected from the barycenter of face node with the unit of interarea, power and inertia transfer to interarea node by from face node, each node of interarea corresponding unit is reassigned to from the square of face node.
Point face contact between the different piece of each air bag module and between adjacent each air bag module adopts penalty function method to solve, each face of air bag is interarea is also from face, each time step first checks respectively whether penetrate interarea from face node, if do not penetrate interarea, then this is left intact from face node, if penetrate interarea, then at this from face node and penetrated between interarea and introduce a normal direction contact force, the size of this normal direction contact force is directly proportional to penetration depth, interarea rigidity.
In formula,
for from the normal direction contact force between face node and contact node;
for penetration depth;
for interarea rigidity;
for contact point place interarea
outer normal unit vector.
The contact certainly that this normal direction contact force is produced by the contact between each air bag module and air bag self-deformation produces, and for interarea unit is to the acting force from face node, this force direction is perpendicular to interarea unit.Its physical significance is equivalent to from face node and penetrated between interarea and place a normal direction spring, to limit from node penetrating interarea.
3rd step: the analog result of equipment airborn landing buffering course generates, by calculating the analog result obtaining equipment airborn landing buffering course, described analog result comprises air bag damping characteristics and equipment shock response characteristic.
As shown in Figure 5, the precision of described analog result is verified by adopting the test figure of typical condition (landing operating mode), comparing result shows that the coherence of changing trend of the impact acceleration curve of test point is better and error is few, the precision of institute's established model is higher, can meet engineering analysis demand and for next step simulation analysis.Simulate the equipment airborn landing buffering course of various different operating mode on this basis, equipment configuration strength assessment, the design of air bag Optimized Matching etc. can be carried out, thus shorten development and design time and funds.
Above content is only preferred embodiment of the present invention, and for those of ordinary skill in the art, according to thought of the present invention, all will change in specific embodiments and applications, this description should not be construed as limitation of the present invention.
Claims (4)
1. equip a simulation method for airborn landing buffering course, it is characterized in that: the step of described analogy method comprises:
The first step, sets up the finite element model of equipment-gas-bag system by computing machine, the finite element model of described equipment-gas-bag system comprises the contact model of equipment finite element model, air bag finite element model, equipment and air bag;
Second step, based on the analog computation of the equipment airborn landing buffering course of nonlinear finite element, the implementation step of described analog computation is as follows: 1) solve with progressive failure and calculate equipment finite element model, 2) control volume mothod is adopted to resolve air bag finite element model, 3) contact model of equipment and air bag is resolved, at equipment with the contact model of air bag, the bottom of equipment is defined as interarea, the upper surface of air bag is defined as from face, by from the power of face node with to calculate the additional mass of interarea node from face node and obtain the speed of interarea node and the acceleration of interarea node, equipment calculates the average rigid body displacement based on unit with the contact of air bag, be connected from the barycenter of face node with the unit of interarea, power and inertia transfer to interarea node by from face node, each node of interarea corresponding unit is reassigned to from the square of face node, point face contact between the different piece of each air bag module and between adjacent each air bag module adopts penalty function method to solve, each face of air bag is interarea is also from face, each time step first checks respectively whether penetrate interarea from face node, if do not penetrate interarea, then this is left intact from face node, if penetrate interarea, then at this from face node and penetrated between interarea and introduce a normal direction contact force, the size of this normal direction contact force and penetration depth, interarea rigidity is directly proportional,
Adopt control volume mothod to resolve air bag finite element model, first suppose: 1. equip the buffer action only considering air bag in airborn landing process, ignore aerodynamic drag; 2. ignore the air leakage of airbag wall, in capsule, air is discharged from vent port; 3. inside air bag air pressure is even; 4. Landing Buffer process is adiabatic process, and in capsule, gas is ideal gas;
In the calculating of finite element, in air bag, gas volume can be calculated by following formula:
Wherein,
for unit
's
the mean value of coordinate;
for unit normal and
direction cosine between direction;
for unit
surface area;
Air bag is regarded as the control volume constantly expanded, the rate of change controlling volume internal gas quality is determined by the gas mass flow of inlet and outlet air bag;
In formula,
for gas mass flow variable quantity in air bag;
for entering the gas mass flow of air bag;
for discharging the gas mass flow of air bag;
In actual condition, before Landing Buffer process, buffer air bag is full of completely, and its gas replenishment process does not affect landing buffering course, and the gas mass flow of discharging air bag calculates by following formula:
In formula,
for coefficient of flow;
for ventilation aperture area;
for gaseous tension in air bag;
for gas law constant;
for gas temperature in air bag;
for external pressure;
for the specific heat ratio of gas in air bag;
3rd step: the analog result of equipment airborn landing buffering course generates, by calculating the analog result obtaining equipment airborn landing buffering course, described analog result comprises air bag damping characteristics and equipment shock response characteristic.
2. the simulation method of equipment airborn landing buffering course according to claim 1, it is characterized in that: in described equipment finite element model, adopt Johnson-Cook strength of materials model to be described the material constitutive model of equipment, described Johnson-Cook strength of materials model is an ideal elastic-plastic strength model that can reflect strain hardening, strain rate hardening effect and temperature softening effect, and its expression formula is as follows:
In formula,
for flow stress;
for yield stress;
for hardening Plastic parameter;
for rate of strain coefficient;
for hardenability value;
for plastic strain;
for rate of strain;
for reference rate of strain;
for kelvin degree;
for temperature of fusion;
for initial temperature;
for humidity index.
3. the simulation method of equipment airborn landing buffering course according to claim 1, it is characterized in that: the contact model of described equipment and air bag adopts consolidation style, fricton-tight each other, the contact relation between the different piece of each air bag module and between adjacent each air bag module adopts some face contact to describe.
4. the simulation method of equipment airborn landing buffering course according to claim 1, it is characterized in that: the precision of described analog result is verified by adopting the test figure of typical condition, the simulation then carrying out the equipment airborn landing buffering course of various different operating mode on this basis goes forward side by side luggage for structural strength assessment and air bag structure optimization matched design.
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| CN103469918B (en) * | 2013-09-18 | 2015-11-18 | 南京大学 | The fire-resistant Optimization Design of the two-way compartment floor of metro depot steel concrete |
| CN104166771B (en) * | 2014-08-26 | 2017-07-18 | 中国人民解放军装甲兵工程学院 | Airborn landing analogue simulation and evaluation method under complex environment |
| CN106777573B (en) * | 2016-11-30 | 2020-04-28 | 江西洪都航空工业集团有限责任公司 | Simulation method for landing range of aircraft air-drop emptying auxiliary fuel tank |
| CN106768547B (en) * | 2016-12-09 | 2019-08-23 | 中国航空工业集团公司西安飞机设计研究所 | A method of calculating enlargement device idler wheel contact force |
| CN111076887B (en) * | 2019-12-09 | 2021-07-13 | 北京空间机电研究所 | Method for acquiring additional mass in parachute opening process in air-drop test |
| CN113033031B (en) * | 2019-12-25 | 2024-05-10 | 海鹰航空通用装备有限责任公司 | Simulation device and method for landing process of aircraft with buffer air bags |
| CN113155393B (en) * | 2021-03-03 | 2023-03-28 | 中国人民解放军95795部队 | Air-drop buffering air bag test device |
| CN112926215B (en) * | 2021-03-16 | 2023-04-07 | 中国人民解放军95795部队 | Uncertain analysis method for buffer landing process of air-drop cargo platform |
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