CN113221243A - Simulation calculation method and system for transient synchronous unfolding of aircraft folded rudder - Google Patents
Simulation calculation method and system for transient synchronous unfolding of aircraft folded rudder Download PDFInfo
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Abstract
The invention provides a simulation calculation method and a simulation calculation system for transient synchronous unfolding of aircraft folded rudders, which comprise the following steps: calculating the aerodynamic equivalent load of the aircraft at the initial unfolding moment of the folded control surface in the actual flight process by using fluid mechanics software and finite element software; calculating the aerodynamic equivalent load of the aircraft in the folding control surface unfolding process in the actual flight process by applying fluid dynamics and finite element software; describing high-temperature and high-pressure gas generated after the explosive is exploded by adopting a state equation, and simulating fluid-solid coupling interaction in real time by using any Euler Lagrange method; the initial configuration and the initial orientation of the damping lug plates are selected and arranged; and selecting the volume of the initial closed container of the folded rudder and the equivalent weight of the explosive based on the calculation result of the simple model. According to the invention, high-temperature and high-pressure gas generated by explosive explosion is used as an expansion energy source, and a simple model verification test and a fluid-solid coupling calculation method are adopted, so that the design efficiency is effectively improved, and the repeated iteration in the design process is reduced.
Description
Technical Field
The invention relates to a design calculation method in the aerospace field, in particular to a simulation calculation method and a simulation calculation system for transient synchronous unfolding of an aircraft folded rudder.
Background
With the continuous innovation and development of aviation technology and guided munitions, airborne guided munitions are required to reduce the occupied airborne space when the airborne guided munition is hung as much as possible, and especially under the requirement of improving stealth performance of military aircrafts, the airborne guided munition is generally required to adopt an embedded hanging mode. On the other hand, guided munitions often require large aerodynamic control surfaces to achieve higher control maneuvers to achieve sufficient aerodynamic control torque. The folding technology of the control surface becomes a key technology for solving the contradiction between the control surface of the guided weapon and the mounting space of the carrier.
In the chinese patent application publication No. CN106156444A, a method for processing aerodynamic loads of an aircraft and a method for calculating the strength of the aircraft are disclosed. The aircraft aerodynamic load processing method comprises the following steps: step 1: constructing a finite element model of a structure to be analyzed, and acquiring unit information; step 2: applying pneumatic load to the finite element model, acquiring pneumatic load information, and interpolating the pneumatic load information into the node information by an interpolation method according to the pneumatic load information so as to obtain node load information; and step 3: and (3) replacing the node numbers of all the units in the unit information with the pneumatic load values corresponding to all the nodes in the node load information, so as to obtain the pneumatic load information, and substituting the pneumatic load information into the finite element model in the step (1). The pneumatic load processing method provided by the invention has strong applicability, can be applied to structural members with complex shapes and under the condition of sparse pneumatic load nodes, and can obtain a better calculation result.
The traditional rudder surface folding mode for small-sized missiles and box-type launching guidance weapons adopts a torsion spring structure, the rudder needs to be restrained by the launching tube wall after being folded, and the rudder is separated from restraint and automatically unfolded after being launched, and the unfolding mode needs the tube wall and cannot be applied to airborne guidance weapons without the launching tube. The guided weapon used in service is mostly folded transversely, and under the conditions that the diameter of a projectile body of the guided weapon is small and the extension length of a control surface is large, the requirement on the outer envelope space of a carrier of the small-diameter type projectile body is difficult to meet after the control surface is transversely folded. In addition, since guided munitions generally have multiple control surfaces at the same time, the conventionally used control surface folding often provides an independent folding and unfolding mechanism for each control surface. After launching, the control surface is quickly unfolded to a designed position and locked under the action of the unfolding mechanism. When the foldable rudder is unfolded, the foldable rudder needs to meet the requirements of designed unfolding time, unfolding angle, unfolding synchronism and the like, after the foldable rudder is unfolded in place, the foldable rudder can be reliably locked and accords with the design of a full-elastic pneumatic appearance, and whether the unfolding state of the foldable rudder is correct or not determines the success or failure of guided missile flight. With the increasing flying speed of the airplane, the aerodynamic load born by an airborne weapon at the moment of launching is more complicated, and the aerodynamic load acting on the control surface becomes a key factor influencing whether the folded rudder can be normally unfolded, so that the aerodynamic load of the control surface is an important index for structural design and part type selection, and the determination of the aerodynamic load in the unfolding process of the folded rudder has important significance for the design of the folded rudder.
The requirements for the unfolding synchronism and the instantaneity of the folded rudder in a high-mach flight state are more severe. Therefore, the traditional mechanical folding technology cannot meet the requirements of synchronous and instantaneous design technology of the folding rudder under complex environment.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a simulation calculation method and a simulation calculation system for transient synchronous unfolding of an aircraft folded rudder.
The invention provides a simulation calculation method for transient synchronous unfolding of an aircraft folded rudder, which comprises the following steps:
step S1: calculating the aerodynamic equivalent load of the aircraft at the initial moment of unfolding the folded control surface in the actual flight process by using the fluid mechanics software XFOLW and finite element software;
step S2: calculating the aerodynamic equivalent load of the aircraft in the folding control surface unfolding process in the actual flight process by applying fluid dynamics and finite element software;
step S3: describing high-temperature and high-pressure gas generated after the explosive is exploded by adopting a state equation, and simulating the fluid-solid coupling interaction in real time by using any Eulerian Lagrange method;
step S4: the initial configuration and the initial orientation of the damping lug plates are selected and arranged;
step S5: and selecting the volume of the initial closed container of the folded rudder and the equivalent weight of the explosive based on the calculation result of the simple model.
Preferably, the step S1 includes the following sub-steps:
step S1.1: establishing a three-dimensional configuration of a real folding control surface and an actual flying speed and attitude;
step S1.2: calculating and obtaining the pneumatic pressure load distribution of the folded control surface at the initial unfolding moment by adopting fluid dynamics software;
step S1.3: and the pneumatic pressure load is equivalent to the equivalent load borne by the folding control surface, including the equivalent pressure load of the folding control surface and the hinge moment.
Preferably, the step S2 includes the following sub-steps:
step S2.1: taking an unfolding angle time history curve pre-designed by the folding control surface as calculation input;
step S2.2: calculating the aerodynamic load of the folded control surface in the unfolding process by adopting fluid dynamics software;
step S2.3: and equating the calculated aerodynamic load to the equivalent load borne by the folding control surface, wherein the equivalent load comprises equivalent pressure load of the folding control surface and hinge moment.
Preferably, the step S3 includes the following sub-steps:
step S3.1: developing a test for testing the explosive performance of the closed container to determine parameters in an explosive state equation and providing data support for simulating and calculating a high-temperature and high-pressure gas product generated after the explosive is detonated;
step S3.2: a simple model is established by any Euler Lagrange method to design and study the effect of explosive after explosion in different initial cavity volumes.
Preferably, the step S4 includes the following sub-steps:
step S4.1: selecting different configurations, rigidity and initial orientations of damping lugs through a folding control surface unfolding angular velocity time history design curve after the action of explosive loads;
step S4.2: adjusting different damping stiffness so as to design a retardation load borne by the folded rudder in the unfolding process;
step S4.3: the foldable control surface is locked after being unfolded in place through the damping lug.
Preferably, the step S5 includes the following sub-steps:
step S5.1: according to the state equation established by experimental verification and the load time history and the pressure time history in the container which are born by the piston connecting rod in the closed container after the explosive is exploded under the simple model,
step S5.2: selecting the volume of an initial closed container and the equivalent weight of explosive according to the pneumatic load and the damping load calculated in the early stage and the angular velocity time history required by unfolding of the folded control surface;
step S5.3: and iteratively correcting the volume of the initial closed container and the equivalent weight of the explosive according to the calculation simulation result so as to achieve the design curve of the angular speed and the time history of the unfolding of the folding rudder required by the design.
The invention provides a simulation computing system for transient synchronous unfolding of an aircraft folded rudder, which comprises the following modules:
module M1: calculating the aerodynamic equivalent load of the aircraft at the initial moment of unfolding the folded control surface in the actual flight process by using the fluid mechanics software XFOLW and finite element software;
module M2: calculating the aerodynamic equivalent load of the aircraft in the folding control surface unfolding process in the actual flight process by applying fluid dynamics and finite element software;
module M3: describing high-temperature and high-pressure gas generated after the explosive is exploded by adopting a state equation, and simulating the fluid-solid coupling interaction in real time by using any Eulerian Lagrange method;
module M4: the initial configuration and the initial orientation of the damping lug plates are selected and arranged;
module M5: and selecting the volume of the initial closed container of the folded rudder and the equivalent weight of the explosive based on the calculation result of the simple model.
Preferably, the module M1 includes the following sub-modules:
module M1.1: establishing a three-dimensional configuration of a real folding control surface and an actual flying speed and attitude;
module M1.2: calculating and obtaining the pneumatic pressure load distribution of the folded control surface at the initial unfolding moment by adopting fluid dynamics software;
module M1.3: and the pneumatic pressure load is equivalent to the equivalent load borne by the folding control surface, including the equivalent pressure load of the folding control surface and the hinge moment.
Preferably, the module M2 includes the following sub-modules:
module M2.1: taking an unfolding angle time history curve pre-designed by the folding control surface as calculation input;
module M2.2: calculating the aerodynamic load of the folded control surface in the unfolding process by adopting fluid dynamics software;
module M2.3: and equating the calculated aerodynamic load to the equivalent load borne by the folding control surface, wherein the equivalent load comprises equivalent pressure load of the folding control surface and hinge moment.
Preferably, the module M3 includes the following sub-modules:
module M3.1: developing a test for testing the explosive performance of the closed container to determine parameters in an explosive state equation and providing data support for simulating and calculating a high-temperature and high-pressure gas product generated after the explosive is detonated;
module M3.2: a simple model is established by any Euler Lagrange method to design and study the effect of explosive after explosion in different initial cavity volumes.
Compared with the prior art, the invention has the following beneficial effects:
1. the method considers the non-uniform aerodynamic load on the air control surface in the actual flying process, and realizes the accurate application of the three-dimensional non-uniform aerodynamic load on the control surface;
2. the method realizes the accurate application of the explosive load on the basis of simple test verification, and greatly improves the accuracy of the calculation result;
3. according to the method, explosive explosion is simultaneously initiated to serve as a control surface unfolding energy source, so that the rapidity, the synchronism and the controllability of unfolding of the folded control surface in a high Mach complex environment are realized;
4. the pressure of the closed container is accurately controllable in the control surface unfolding process by adopting the strong coupling of the high-temperature and high-pressure gas after explosion and the solid.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic diagram of an aircraft folded rudder system in a simulation calculation method for transient synchronous unfolding of aircraft folded rudders according to an embodiment of the present application;
FIG. 2 is a schematic diagram illustrating explosive installation in a simulation calculation method for transient synchronous unfolding of aircraft folded rudders according to an embodiment of the present application;
fig. 3 is a time history curve of the deployment angle of the folded rudder in the simulation calculation method for transient synchronous deployment of the aircraft folded rudder according to the embodiment of the present application;
fig. 4 is a time history curve of the explosion pressure applied to the piston disc in the simulation calculation method for transient synchronous deployment of the aircraft folded rudder according to the embodiment of the present application.
Description of reference numerals: 1. folding the control surface; 2. a piston disc; 3. a closed container; 4. a damping lug; 5. a piston connecting rod; 6. an explosive; 7. and (5) fixing the control surface.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
In order to solve the technical problem that the folded rudder of a high-Mach embedded aircraft is transiently unfolded and requires synchronization, the invention discloses a design idea that high-temperature and high-pressure gas generated by simultaneous explosion of explosives 6 is used as unfolding energy, and by referring to fig. 1 and fig. 2, a simple model verification test and a fluid-solid coupling calculation method are adopted, so that the design idea is accurately guided, the design efficiency is effectively improved, and the repeated iteration in the design process is reduced.
A simulation calculation method for transient synchronous unfolding of an aircraft folded rudder comprises the following steps:
step S1: and calculating the aerodynamic equivalent load of the aircraft at the initial unfolding moment of the folded control surface 1 in the actual flight process by using the fluid mechanics software XFOLW and the finite element software ABAQUS.
Specifically, by establishing a three-dimensional configuration and an actual flying speed and attitude of the real folded control surface 1, aerodynamic pressure load distribution of the folded control surface 1 at the initial unfolding moment is calculated by adopting a fluid dynamics software XFLOW, and then the aerodynamic pressure load is equivalent to an equivalent load of the folded control surface 1, including an equivalent pressure load and a hinge moment of the folded control surface 1.
Step S2: and calculating the aerodynamic equivalent load of the aircraft in the unfolding process of the folding control surface 1 in the actual flight process by applying the fluid dynamics XFW and the finite element software ABAQUS.
Specifically, according to a pre-designed unfolding angle time history curve of the folded control surface 1 as a calculation input, referring to fig. 3, a fluid dynamics software XFLOW is used for calculating an aerodynamic load on the folded control surface 1 in the unfolding process, and then the calculated aerodynamic load is equivalent to an equivalent load on the folded control surface 1, including an equivalent pressure load and a hinge moment of the folded control surface 1.
According to the aircraft flight attitude at the initial unfolding moment of the folding rudder surface 1 and the initial folding configuration of the folding rudder, which are obtained in advance through design, the XFLOW fluid dynamics software and the ABAQUS finite element software are adopted to calculate the aerodynamic pressure load on the rudder surface at the initial unfolding moment of the folding rudder in a coupling mode, the aerodynamic pressure load is equivalent to the control surface pressure center position and serves as the pressure load and the hinge moment of the rudder surface, meanwhile, the equivalent load on the rudder surface in the unfolding process is obtained through the angular speed time history coupling calculation designed in the unfolding process of the rudder surface, and therefore the equivalent load serves as the input of subsequent key calculation design parameters.
Step S3: JWL state equation is adopted to describe the high-temperature high-pressure gas generated after the explosive 6 explodes, and the fluid-solid coupling interaction is simulated in real time through any Euler Lagrange method.
Specifically, parameters in the JWL explosive 6 state equation are determined by developing an explosive 6 performance test of the closed container 3, so that data support is provided for simulating and calculating high-temperature and high-pressure gas products generated after the explosive 6 is detonated. Then, a simple model design is established by any Euler Lagrange method (CEL) to study the effect of the explosive 6 with different initial cavity volumes after explosion.
JWL equation of state is used to describe the high temperature and high pressure gas generated after explosive 6 explodes and simulate the propagation of the gas to the surroundings. The chemical energy released after the explosive 6 is exploded is described by using a Jones-Wilkens-Lee (JWL) state equation in ABAQUS, and the model form is as follows:
wherein, A, B, R1，R2ω is the model constant, ρ0Is the initial density of explosive 6, and rho is the detonation of explosive 6Product Density, EmThe specific internal energy is the energy contained in the unit mass explosive 6.
In the design calculation, other seven characteristic parameters in the model are selected according to the detonation velocity of the explosive 6 which is accurately measured in the test, then the detonation pressure measurement of the explosive 6 in the standard fixed wall cavity is carried out, the detonation energy product of the explosive 6 is determined by measuring the fixed pressure time course curve of the wall surface at a certain distance and an azimuth angle, and then the parameters in the JWL state equation are adjusted to ensure that the pressure time course curve in the simulation calculation model is consistent with the model test curve. The model parameters are then recorded and entered as subsequent calculations and fixed.
Step S4: the damping lug 4 is arranged in an initial configuration and an initial orientation selection.
Specifically, different damping lug 4 configurations, rigidity and initial orientations are selected through a design curve of the unfolding angular speed time course of the folded control surface 1 under the action of the explosive load, different damping rigidities are adjusted to design a retardation load borne in the unfolding process of the folded control, and the folded control surface 1 is locked after being unfolded in place through the damping lugs 4.
According to the ear deformation time course confirmed by the folding rudder unfolding angular velocity time course which is pre-reached in the design, ABAQUS/explicit is adopted to calculate the deformation process of the ear and the support reaction force generated in the deformation process under the condition of the external strong displacement boundary. And adjusting the lug structure according to the equivalent of explosive 6 selected subsequently and the pressure peak value of the cavity to change the retardation load, so that the retardation load of the damping lug 4 is smaller than the thrust load generated by explosion of the explosive 6 in the unfolding process of the real folded rudder.
Step S5: and selecting the volume of the initial closed container 3 of the folded rudder and 6 equivalent of explosive based on the calculation result of the simple model.
Specifically, according to a JWL state equation established by experimental verification and a load time history and a container internal pressure time history of a piston connecting rod 5 in a closed container 3 after an explosive 6 is exploded under a simple model, referring to fig. 4, the volume of the initial closed container 3 and the equivalent weight of the explosive 6 are selected according to an earlier-calculated pneumatic load, a damping load and an angular velocity time history required by unfolding of a folding control surface 1, and the volume of the initial closed container 3 and the equivalent weight of the explosive 6 are iteratively corrected according to a calculation simulation result, so that a folding rudder unfolding angular velocity time history design curve required by design is achieved.
According to the JWL state equation parameters determined in the early stage, the process of applying work to the solid structure after the explosive 6 explodes under the condition of a simple model is firstly carried out. The pressure of the cavities is focused, the material structure of the cavities and the material structure of the piston disc 2 are checked for the problem of high rigidity by calculating the volumes of the initially different cavities, and therefore materials meeting the design requirement of high rigidity under the specific size limitation condition are selected. On the basis of simple model calculation, full system simulation calculation is carried out, the control surface aerodynamic load and the damping lug 4 retardation load in the previous design step are introduced, then the initial explosive 6 equivalent and the initial sealed cavity size are adjusted according to the simple model calculation result, and the purpose of designing the specific expansion angular velocity is achieved through a small amount of iterative calculation.
Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, units provided by the present invention as pure computer readable program code, the system and its various devices, modules, units provided by the present invention can be fully implemented by logically programming method steps in such a manner as to implement the same functions in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A simulation calculation method for transient synchronous unfolding of an aircraft folded rudder is characterized by comprising the following steps:
step S1: calculating the aerodynamic equivalent load of the aircraft at the initial unfolding moment of the folded control surface in the actual flight process by using fluid mechanics software and finite element software;
step S2: calculating the aerodynamic equivalent load of the aircraft in the folding control surface unfolding process in the actual flight process by applying fluid dynamics and finite element software;
step S3: describing high-temperature and high-pressure gas generated after the explosive is exploded by adopting a state equation, and simulating fluid-solid coupling interaction in real time by using any Euler Lagrange method;
step S4: the initial configuration and the initial orientation of the damping lug plates are selected and arranged;
step S5: and selecting the volume of the initial closed container of the folded rudder and the equivalent weight of the explosive based on the calculation result of the simple model.
2. The simulation calculation method for the transient synchronous unfolding of the aircraft folded rudder according to claim 1, wherein the simulation calculation method comprises the following steps: the step S1 includes the following sub-steps:
step S1.1: establishing a three-dimensional configuration of a real folding control surface and an actual flying speed and attitude;
step S1.2: calculating and obtaining the pneumatic pressure load distribution of the folded control surface at the initial unfolding moment by adopting fluid dynamics software;
step S1.3: and the pneumatic pressure load is equivalent to the equivalent load borne by the folding control surface, including the equivalent pressure load of the folding control surface and the hinge moment.
3. The simulation calculation method for the transient synchronous unfolding of the aircraft folded rudder according to claim 1, wherein the simulation calculation method comprises the following steps: the step S2 includes the following sub-steps:
step S2.1: taking an unfolding angle time history curve pre-designed by the folding control surface as calculation input;
step S2.2: calculating the aerodynamic load of the folded control surface in the unfolding process by adopting fluid dynamics software;
step S2.3: and equating the calculated aerodynamic load to the equivalent load borne by the folded control surface, wherein the equivalent load comprises the equivalent pressure load of the folded control surface and the hinge moment.
4. The simulation calculation method for the transient synchronous unfolding of the aircraft folded rudder according to claim 1, wherein the simulation calculation method comprises the following steps: the step S3 includes the following sub-steps:
step S3.1: developing a test for testing the explosive performance of the closed container to determine parameters in an explosive state equation and providing data support for simulating and calculating a high-temperature and high-pressure gas product generated after the explosive is detonated;
step S3.2: and establishing a simple model design by any Euler Lagrange method to study the effect of the explosive with different initial cavity volumes after explosion.
5. The simulation calculation method for the transient synchronous unfolding of the aircraft folded rudder according to claim 1, wherein the simulation calculation method comprises the following steps: the step S4 includes the following sub-steps:
step S4.1: selecting different damping lug configurations, rigidities and initial orientations through a folded control surface unfolding angular velocity time history design curve after the action of explosive loads;
step S4.2: adjusting different damping stiffness so as to design a retardation load borne by the folded rudder in the unfolding process;
step S4.3: the foldable control surface is locked after being unfolded in place through the damping lug.
6. The simulation calculation method for the transient synchronous unfolding of the aircraft folded rudder according to claim 1, wherein the simulation calculation method comprises the following steps: the step S5 includes the following sub-steps:
step S5.1: according to the state equation established by experimental verification and the load time history and the pressure time history in the container which are born by the piston connecting rod in the closed container after the explosive is exploded under the simple model,
step S5.2: selecting the volume of an initial closed container and the equivalent weight of explosive according to the pneumatic load and the damping load calculated in the early stage and the angular velocity time history required by unfolding of the folded control surface;
step S5.3: and iteratively correcting the volume of the initial closed container and the equivalent weight of the explosive according to the calculation simulation result, thereby achieving the folded rudder deployment angular velocity time history design curve required by design.
7. A simulation computing system for transient synchronous unfolding of an aircraft folded rudder is characterized in that: the system comprises the following modules:
module M1: calculating the aerodynamic equivalent load of the aircraft at the initial unfolding moment of the folded control surface in the actual flight process by using fluid mechanics software and finite element software;
module M2: calculating the aerodynamic equivalent load of the aircraft in the folding control surface unfolding process in the actual flight process by applying fluid dynamics and finite element software;
module M3: describing high-temperature and high-pressure gas generated after the explosive is exploded by adopting a state equation, and simulating fluid-solid coupling interaction in real time by using any Euler Lagrange method;
module M4: the initial configuration and the initial orientation of the damping lug plates are selected and arranged;
module M5: and selecting the volume of the initial closed container of the folded rudder and the equivalent weight of the explosive based on the calculation result of the simple model.
8. The system according to claim 7, wherein the system comprises: the module M1 includes the following sub-modules:
module M1.1: establishing a three-dimensional configuration of a real folding control surface and an actual flying speed and attitude;
module M1.2: calculating and obtaining the pneumatic pressure load distribution of the folded control surface at the initial unfolding moment by adopting fluid dynamics software;
module M1.3: and the pneumatic pressure load is equivalent to the equivalent load borne by the folding control surface, including the equivalent pressure load of the folding control surface and the hinge moment.
9. The system according to claim 7, wherein the system comprises: the module M2 includes the following sub-modules:
module M2.1: taking an unfolding angle time history curve pre-designed by the folding control surface as calculation input;
module M2.2: calculating the aerodynamic load of the folded control surface in the unfolding process by adopting fluid dynamics software;
module M2.3: and equating the calculated aerodynamic load to the equivalent load borne by the folded control surface, wherein the equivalent load comprises the equivalent pressure load of the folded control surface and the hinge moment.
10. The system according to claim 7, wherein the system comprises: the module M3 includes the following sub-modules:
module M3.1: developing a test for testing the explosive performance of the closed container to determine parameters in an explosive state equation and providing data support for simulating and calculating a high-temperature and high-pressure gas product generated after the explosive is detonated;
module M3.2: and establishing a simple model design by any Euler Lagrange method to study the effect of the explosive with different initial cavity volumes after explosion.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113865546A (en) * | 2021-10-29 | 2021-12-31 | 上海机电工程研究所 | Folding rudder angle measuring device and folding rudder |
| CN114322675A (en) * | 2021-11-30 | 2022-04-12 | 上海机电工程研究所 | Deformable ejector rod and foldable control surface structure in foldable rudder of guided missile and guided missile |
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| CN114322675A (en) * | 2021-11-30 | 2022-04-12 | 上海机电工程研究所 | Deformable ejector rod and foldable control surface structure in foldable rudder of guided missile and guided missile |
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| CN114818144A (en) * | 2022-05-12 | 2022-07-29 | 清华大学 | Simulation calculation and analysis method for fire impact source |
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