CN113221243B - 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
- Publication number
- CN113221243B CN113221243B CN202110516273.1A CN202110516273A CN113221243B CN 113221243 B CN113221243 B CN 113221243B CN 202110516273 A CN202110516273 A CN 202110516273A CN 113221243 B CN113221243 B CN 113221243B
- Authority
- CN
- China
- Prior art keywords
- control surface
- folded
- unfolding
- load
- explosive
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Geometry (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mathematical Physics (AREA)
- Computing Systems (AREA)
- Algebra (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computational Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
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 an arbitrary 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 as much as possible when the airborne guided munition is hung, 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 maneuverability 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 chinese patent application publication No. CN106156444A, an aircraft aerodynamic load processing method and an aircraft strength calculation method 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 meets the requirements of the design on 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 full-elastic pneumatic appearance design, and whether the unfolding state of the foldable rudder correctly determines the success or failure of guided missile flight. With the increasing flying speed of the airplane, the aerodynamic load born by the airborne weapon at the moment of launching is more complex, 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 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;
and 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;
and 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 substeps:
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: the pneumatic pressure load is equivalent to the equivalent load borne by the folding control surface, and the equivalent load comprises the equivalent pressure load of the folding control surface and hinge moment.
Preferably, the step S2 includes the following substeps:
step S2.1: taking an unfolding angle time history curve pre-designed for 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 substeps:
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 explosive explosion at different initial cavity volumes.
Preferably, the step S4 includes the following substeps:
step S4.1: selecting different configurations, rigidity and initial orientations of the damping lugs through a folding control surface unfolding angular speed time history design curve after the action of the explosive load;
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 substeps:
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:
a 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;
a module M2: calculating the aerodynamic equivalent load of the aircraft in the unfolding process of the folding control surface in the actual flight process by using fluid dynamics and finite element software;
a 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;
a module M4: the initial configuration and the initial orientation of the damping lug plates are selected and arranged;
a 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 comprises 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 for 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: and establishing a simple model design by any Euler Lagrange method to study the effect of explosive explosion at 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 rapidness, 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 unfolding of the aircraft folding 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 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 folding rudder comprises the following steps:
step S1: and calculating the aerodynamic equivalent load of the aircraft at the initial unfolding moment of the folding 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.
And step S3: and describing high-temperature and high-pressure gas generated after the explosive 6 is exploded by adopting a JWL state equation, and simulating fluid-solid coupling interaction in real time by using any Euler Lagrange method.
Specifically, parameters in a JWL explosive 6 state equation are determined by developing a performance test of the explosive 6 in the closed container 3, so that data support is provided for simulating and calculating a high-temperature and high-pressure gas product 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 the explosive 6 is exploded and simulate the propagation to the surroundings. The chemical energy released after explosion of explosive 6 is described by using the Jones-Wilkens-Lee (JWL) equation of state in ABAQUS, and the model form is as follows:
wherein, A, B, R 1 ，R 2 ω is the model constant, ρ 0 Is the initial density of explosive 6, rho is the density of detonation product of explosive 6, E m The 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 make the pressure time course curve in the simulation calculation model consistent with the model test curve. The model parameters are then recorded and entered as subsequent calculations and fixed.
And step S4: the damping lugs 4 are arranged in an initial configuration and an initial orientation.
Specifically, different damping lug pieces 4 are selected in configuration, rigidity and initial orientation through a design curve of the unfolding angular speed time process of the folded control surface 1 under the action of the explosive load, different damping rigidity is adjusted, so that the retardation load borne by the folded control surface in the unfolding process is designed, and the folded control surface 1 is locked after being unfolded in place through the damping lug pieces 4.
According to the ear deformation time history confirmed by the folding rudder unfolding angular velocity time history pre-reached in the design, ABAQUS/explicit is adopted to calculate the deformation process of the ear and the support reaction generated in the deformation process under the condition of an external strong displacement boundary. And adjusting the lug plate configuration according to the equivalent of explosive 6 selected subsequently and the pressure peak value of the cavity to change the retardant load, so that the retardant load of the damping lug plate 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 course and a container internal pressure time course received by a piston connecting rod 5 in a closed container 3 after an explosive 6 explodes 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 early-stage calculated pneumatic load, a damping load and an angular velocity time course required by unfolding of a folding control surface 1, 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, and therefore a folding rudder unfolding angular velocity time course 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 developed. 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, carrying out full system simulation calculation, introducing the control surface aerodynamic load and the damping lug 4 retardation load in the previous design step, then adjusting the equivalent weight of the initial explosive 6 and the size of the initial sealed cavity according to the calculation result of the simple model, and achieving the purpose of designing the specific expansion angular velocity 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 has described specific embodiments of the present invention. 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 (8)
1. A simulation calculation method for transient synchronous unfolding of an aircraft folding rudder is characterized by comprising the following steps:
step S1: calculating the aerodynamic 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 aerodynamic load of the aircraft in the folding control surface unfolding process in the actual flight process by applying fluid dynamics and finite element software;
and 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 an arbitrary Euler Lagrange method;
and step S4: the initial configuration and the initial orientation of the damping lug plates are selected and arranged;
step S5: selecting the volume of the initial closed container of the folded rudder and the equivalent weight of explosive based on the calculation result of the simple model;
the step S4 includes the following substeps:
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;
the step S5 includes the following substeps:
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, the retarding load and the angular speed time history required by unfolding of the folded control surface which are calculated in the early stage;
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.
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 substeps:
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 aerodynamic load distribution of the folded control surface at the initial unfolding moment by adopting fluid dynamics software;
step S1.3: and the pneumatic load is equivalent to the equivalent load borne by the folding control surface, including the equivalent pressure load and the hinge moment of the folding control surface.
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 substeps:
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 folding rudder according to claim 1 is characterized in that: the step S3 includes the following substeps:
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 by any Euler Lagrange method to design and study the explosive effect of different initial cavity volumes.
5. A simulation computing system for transient synchronous unfolding of an aircraft folded rudder is characterized in that: the system comprises the following modules:
a module M1: calculating aerodynamic load of the aircraft at the initial moment of unfolding the folded control surface in the actual flight process by using fluid mechanics software and finite element software;
a module M2: calculating aerodynamic load of the aircraft in the folding control surface unfolding process in the actual flight process by applying fluid dynamics and finite element software;
a 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 an arbitrary Euler Lagrange method;
a module M4: the initial configuration and the initial orientation of the damping lug plates are selected and arranged;
a module M5: 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;
the module M4 comprises the following sub-modules:
module M4.1: 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;
module M4.2: adjusting different damping rigidity so as to design a retardation load suffered by the folded rudder in the unfolding process;
module M4.3: the foldable control surface is locked after being unfolded in place through the damping lug;
the module M5 comprises the following sub-modules:
module M5.1: according to the state equation established by experimental verification and the loading time history and the pressure time history in the container of the piston connecting rod in the closed container after the explosion of the explosive under the simple model,
module M5.2: selecting the volume of an initial closed container and the equivalent weight of explosive according to the pneumatic load and the retarding load calculated in the early stage and the angular velocity time history required by unfolding of the folded control surface;
module M5.3: 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.
6. The simulation computing system for transient synchronous deployment of aircraft folded rudders as claimed in claim 5, wherein: the module M1 comprises 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 aerodynamic load distribution of the folded control surface at the initial unfolding moment by adopting fluid dynamics software;
module M1.3: the pneumatic load is equivalent to the equivalent load borne by the folding control surface, including the equivalent pressure load and the hinge moment of the folding control surface.
7. The simulation computing system for transient synchronous unfolding of the aircraft folded rudder according to claim 5, wherein: the module M2 comprises the following sub-modules:
module M2.1: taking an unfolding angle time history curve pre-designed for 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.
8. The simulation computing system for transient synchronous deployment of aircraft folded rudders as claimed in claim 5, wherein: the module M3 comprises 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 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110516273.1A CN113221243B (en) | 2021-05-12 | 2021-05-12 | Simulation calculation method and system for transient synchronous unfolding of aircraft folded rudder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110516273.1A CN113221243B (en) | 2021-05-12 | 2021-05-12 | Simulation calculation method and system for transient synchronous unfolding of aircraft folded rudder |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113221243A CN113221243A (en) | 2021-08-06 |
| CN113221243B true CN113221243B (en) | 2023-01-20 |
Family
ID=77095007
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110516273.1A Active CN113221243B (en) | 2021-05-12 | 2021-05-12 | Simulation calculation method and system for transient synchronous unfolding of aircraft folded rudder |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113221243B (en) |
Families Citing this family (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 |
| CN114861481A (en) * | 2022-03-30 | 2022-08-05 | 西北核技术研究所 | Calculation method for any-configuration explosion source ground motion steady-state effect |
| CN114818144B (en) * | 2022-05-12 | 2023-03-24 | 清华大学 | Simulation calculation and analysis method for fire impact source |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104133933A (en) * | 2014-05-29 | 2014-11-05 | 温州职业技术学院 | Pneumatic elastic mechanical characteristic analytical method of hypersonic speed aircraft in thermal environment |
| CN108760228A (en) * | 2018-06-08 | 2018-11-06 | 中国航天空气动力技术研究院 | A kind of rudder face dynamic force measurement device and test method folded during rudder is unfolded |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2596038C2 (en) * | 2015-01-23 | 2016-08-27 | Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" (Госкорпорация "Росатом") | Device for determining aerodynamic loads acting upon tail model |
| CN110793405B (en) * | 2019-09-16 | 2021-10-15 | 上海航天控制技术研究所 | Self-adaptive control method for preventing instantaneous impact of unfolding of folding rudder of electric steering engine |
| CN112747894B (en) * | 2020-12-29 | 2022-12-06 | 中国航天空气动力技术研究院 | Processing method for measuring aerodynamic moment data in folding rudder unfolding process |
-
2021
- 2021-05-12 CN CN202110516273.1A patent/CN113221243B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104133933A (en) * | 2014-05-29 | 2014-11-05 | 温州职业技术学院 | Pneumatic elastic mechanical characteristic analytical method of hypersonic speed aircraft in thermal environment |
| CN108760228A (en) * | 2018-06-08 | 2018-11-06 | 中国航天空气动力技术研究院 | A kind of rudder face dynamic force measurement device and test method folded during rudder is unfolded |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113221243A (en) | 2021-08-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113221243B (en) | Simulation calculation method and system for transient synchronous unfolding of aircraft folded rudder | |
| CN110610065B (en) | Aircraft multi-body separation CFD simulation method and system based on hybrid dynamic grid technology | |
| Moore | Approximate methods for weapon aerodynamics | |
| de Celis et al. | Guidance and control for high dynamic rotating artillery rockets | |
| Klock et al. | Aerothermoelastic simulation of air-breathing hypersonic vehicles | |
| Runduo et al. | Multi-objective optimization of the aerodynamic shape of a long-range guided rocket | |
| Scheuermann et al. | Aerodynamic characterization of a microspoiler system for supersonic finned projectiles | |
| Witeof et al. | Fluid-thermal-structural interaction effects in preliminary design of high speed vehicles | |
| Ernst et al. | Development of a trajectory-centric CFD-RBD framework for advanced multidisciplinary/multiphysics simulation | |
| Bryson et al. | Modeling and flight dynamics of a projectile with nonlinear, roll-dependent aerodynamics | |
| McQuellin et al. | Investigating endo-atmospheric separation of a hypersonic flyer-sustainer using wind tunnel based free-flight | |
| Verberne et al. | Dynamics of precision-guided projectile launch: fluid–structure interaction | |
| Fresconi et al. | Flight performance of a small diameter munition with a rotating wing actuator | |
| Heimbs et al. | A numerical method for blast shock wave analysis of missile launch from aircraft | |
| Jimenez Mena et al. | Rocket engine digital twin–modeling and simulation benefits | |
| Atallah et al. | Modeling and simulation for free fall bomb dynamics in windy environment | |
| Wang et al. | Numerical investigation on muzzle flow characteristics for small combustion chamber with embedded propelled body | |
| Huang et al. | Numerical investigations on the sabots discard process of an APFSDS at different angles of attack | |
| Dali et al. | Increasing the Range of Contemporary Artillery Projectiles | |
| Ernst et al. | Coupling Computational Fluid Dynamics with 6DOF Rigid Body Dynamics for Unsteady, Accelerated Flow Simulations | |
| Kozak et al. | Effects of aircraft aeroelastic deformations on external store separation dynamics | |
| De Celis et al. | A simplified computational method for two-body high spinning rate vehicles | |
| Anh et al. | Development of a framework for ballistic simulation | |
| Korolev et al. | Simulation of the spatial motion of projectile in the presence of mass and shape asymmetry | |
| Cox et al. | Launch Vehicle Structural Analysis (LVSA): A Multifidelity, Multidisciplinary Environment for Design and Analysis of Rocket-Powered Vehicles |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |