CN104899400A - Design method of spring piece for repeatable holding-type locking device of magnetic levitation fly wheel - Google Patents
Design method of spring piece for repeatable holding-type locking device of magnetic levitation fly wheel Download PDFInfo
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Abstract
The invention discloses a design method of a spring piece for a repeatable holding-type locking device of a magnetic levitation fly wheel. The design method comprises the steps of utilizing multidisciplinary optimization software iSIGHT and finite element software ANSYS to perform spring piece optimization design, regarding comprehensive optimum of locking rigidity and locking damp of a locking device as an optimization target, using spring piece mass M, maximum bending stress Sigma max, unlocking force fu, locking state first-order resonant frequency F11 and unlocking state first-order resonant frequency Fu1 as constraint conditions, adopting a global comparison method for dispersion design variables, adopting a second-order derivable optimization algorithm for spring piece structure continuous design variables to perform spring piece structure optimization design. By means of the design method, the protecting performance of the locking device can be embodied, and the locking protection effect can be reasonable. The design method has the advantages of being high in accuracy, simple, feasible and the like, and the design concept of the design method can be used for design of various large-inertia magnetic levitation rotor locking devices.
Description
Technical field
The present invention relates to magnetically levitated flywheel can repeat to embrace design field, the particularly Large Spacecraft large inertia magnetically levitated flywheel of formula locking device shell fragment and the method for designing of large magnetic suspension control-moment gyro locking device shell fragment.
Background technology
Along with the development of spationautics, for meeting, the more and more higher requirement of appearance, orbit determination accuracy being determined to spacecraft, usually adopting counteraction flyback and bias momentum wheel to control satellite platform.Magnetically levitated flywheel is a kind of novel spacecraft attitude control system, compared with traditional mechanical flywheel, in control accuracy and serviceable life etc., has clear superiority.Owing to there is certain magnetic portable protective gaps between magnetically levitated flywheel stator and rotor, for preventing the transmitting powered phase mutual collision impact of flywheel stator and rotor from damaging, fly wheel system must adopt latch mechanism, carries out locking confining guard to it.
According to the position of locking device in magnetically levitated flywheel, locking device can be divided into internal locking device and outer locking device.According to locking/unblock number of times, locking device can be divided into disposable locking device and repeatable locking device.Before Spacecraft Launch, magnetically levitated flywheel must complete the test of various ground environment, needs often to lock it/unlock.In addition, when becoming rail work, for preventing the flywheel of free state to the interference of appearance control platform, also need to be locked; After entering the orbit, then flywheel rotor is unlocked.The repeatable locking device used at present mainly contains electromagnetic locking device, based on motor-conical surface locking closure locking device, based on motor-lever lock device and armful formula locking device.Electromagnetic locking device described in number of patent application 200810119968.0, positive/negative to superposing with permanent magnetic field by the electromagnetism magnetic field controlling electromagnet, what realize flywheel repeats locking/unblock.But locking tripping force is inversely proportional to unblock gap, and unblock gap can not adjust, and brings very big inconvenience to the assembling and setting of locking device.During work, generally on flywheel base, three to four electromagnetic locking devices are along the circumferential direction installed, when making perform locking and perform unblock, require higher to the synchronism of electromagnet action.In addition, if arbitrary electromagnetic locking device lost efficacy, magnetic bearing-supported flywheel system will be caused can not to perform locking and unlock, reduced the reliability of locking device.Described in number of patent application 201210338347.8 based on motor-conical surface locking closure locking device, by positive/negative turn of motor, drive conical surface locking closure to compress/unclamp flywheel rotor, what achieve flywheel repeats locking/unlock.Conical surface locking closure is positioned over stator core shaft radially inner side, reduces flywheel volume and weight, but the constraint area of the conical surface locking closure conical surface is less, and locking constraint rigidity is on the low side, to cause in vibration processes vibration displacement between large inertia magnetically levitated flywheel stator and rotor larger.Armful formula locking device described in number of patent application 200910093150.0, utilize shell fragment as extension mechanism, utilize wire rope as tightening system, by positive/negative turn of motor, order about tightening system extension mechanism is drawn in/unclamps, thus hold tightly/discharge flywheel rotor, what realize flywheel repeats locking/unblock.This locking device, compared with electromagnetic locking device, when locking device breaks down, adopts priming system to chop wire rope off and carries out compulsive unlocking to flywheel, add to perform and unlock reliability, and shell fragment stroke is adjustable, namely unlocks gap adjustable, there is assembling and setting advantage easily.With compared with motor-conical surface locking closure locking device, shell fragment and the flywheel rotor edge contact area of embracing formula locking device are comparatively large, add the rigidity of locking, thus can carry out confining guard to fly-wheel control rotor better.
Shell fragment is as repeating the critical component embracing formula locking device, and the impact of its mechanical property on fly wheel system is as follows: the releasing force under (1) locking state determines the unblock reliability of locking device; (2) locking motor power one timing, steel wire rope tension remains unchanged, and namely releasing force and coupling mechanism force sum are certain value, and the larger coupling mechanism force of releasing force is less, and reliable lock is lower; (3) excessive under locking state bending stress may cause shell fragment plastic yield; (4) under released state, shell fragment is in free state, and its released state first order resonance frequency is too low, can affect fly wheel system control moment precision; (5) under locking state, even if coupling mechanism force can retrain flywheel rotor, but too low locking rigidity can cause the vibration displacement between transmitting powered phase stator and rotor excessive, causes between stator and rotor and fierce collision and impact occur; (6) launch powered phase, flywheel rotor inertial force is comparatively large, and too low locking damping can not absorb flywheel rotor kinetic energy in time, forces vibration displacement to amplify further, also can cause fierce collision and the generation impacted.Therefore to lock the shell fragment that protected effect requires be the problem that needs solve with unlocking reliability, fly wheel system performance and flywheel how to design the locking that can meet whole locking device.
Summary of the invention
The technical problem to be solved in the present invention is to provide the method for designing that a kind of magnetically levitated flywheel can repeat to embrace formula locking device shell fragment, the magnetically levitated flywheel designing high rigidity high-damping whole, with repeating to embrace formula locking device, solves existing little inertia magnetically levitated flywheel the design of lockup equipment method with the minimum problem for optimization aim of quality.
For solving the problems of the technologies described above, the invention provides the method for designing that a kind of magnetically levitated flywheel can repeat to embrace formula locking device shell fragment, the method is comprehensive optimum for design object with locking damping with the locking rigidity that can repeat to embrace formula locking device shell fragment, comprises the following steps:
Step 1, setting discrete heat sources shell fragment number is n=i=4;
Step 2, sets the initial value of continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w;
Step 3, adopts FEM-software ANSYS as handling implement, utilizes the shell fragment number of setting and the initial value of shell fragment height h, shell fragment thickness t and shell fragment width w, sets up the model of following shell fragment correlation behavior respectively, be specially:
(1) set up the statics finite element model of shell fragment at locking state, this model APDL command stream is saved to locking statics file, calculates shell fragment mass M, maximum stress in bend σ
maxwith releasing force f
u, result of calculation is saved to locking statics destination file;
(2) set up the Dynamics Finite Element Model of shell fragment at locking state, this model APDL command stream is saved to locking power file, calculates shell fragment mass M, locking state first order resonance frequency F
l1, locking stiffness K and locking damping D, result of calculation is saved to locking power destination file;
(3) set up the Dynamics Finite Element Model of shell fragment at released state, this model APDL command stream is saved to and unlocks dynamics file, calculate shell fragment mass M and released state first order resonance frequency F
u1, result of calculation is saved to and unlocks kinetic results file;
Step 3, by described locking statics file, locking statics destination file, locking power file, locking power destination file, unlock dynamics file and unlock in kinetic results file importing multidisciplinary optimization software iSIGHT, and set the span of continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w, and setting bound variable shell fragment mass M, maximum stress in bend σ
max, releasing force f
u, locking state first order resonance frequency F
l1with released state first order resonance frequency F
u1restriction range;
Step 4, the optimized algorithm of multidisciplinary optimization software iSIGHT is utilized to calculate the direction of search and iteration step length, repeatedly text is locked statics file, locking power file and unlock dynamics file importing FEM-software ANSYS and statics and dynamics calculation are carried out to shell fragment, export locking statics destination file, the locking power destination file corresponding with each file simultaneously and unlock kinetic results file;
Step 5, judges whether optimizing process restrains;
Step 6, does not restrain if optimize, according to the direction of search and iteration step length, changes continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w, forward step 3 to;
Step 7, if optimize convergence, record shell fragment suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax;
Step 8, judges whether shell fragment number n=i is less than its maximal value 12;
Step 9, if when shell fragment number n=i is less than maximum shell fragment number 12, shell fragment number becomes n=i+1, and n=i+1 is substituted into step 2, enters cycle calculations;
Step 10, if when shell fragment number n=i is not less than maximum shell fragment number 12, more all shell fragment suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax, and obtain shell fragment universe optimum locking stiffness K
owith optimum locking damping D
o.
Beneficial effect of the present invention is: coordinate with multidisciplinary optimization software iSIGHT owing to utilizing FEM-software ANSYS, improve design efficiency, and with the high rigidity of locking device and high damping for design object, compared with the minimum method for designing for starting point of the existing quality with locking device, more be beneficial to the performance improving locking device, be especially more applicable for the design of large inertia magnetic levitation inertia actuator locking device.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme of the embodiment of the present invention, below the accompanying drawing used required in describing embodiment is briefly described, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the magnetically levitated flywheel locking device three-dimensional structure schematic diagram of embodiment of the present invention supplying method design;
Fig. 2 a is the shell fragment cut-open view of the magnetically levitated flywheel locking device of embodiment of the present invention supplying method design;
Fig. 2 b is the shell fragment sectional view of the magnetically levitated flywheel locking device of embodiment of the present invention supplying method design;
Fig. 2 c is the shell fragment three-dimensional structure schematic diagram of the magnetically levitated flywheel locking device of embodiment of the present invention supplying method design;
The method for designing process flow diagram that Fig. 3 provides for the embodiment of the present invention.
Embodiment
Be clearly and completely described the technical scheme in the embodiment of the present invention below, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on embodiments of the invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to protection scope of the present invention.
Magnetically levitated flywheel of the present invention can repeat the method for designing of embracing formula locking device shell fragment, the design magnetically levitated flywheel being starting point with high rigidity high-damping whole is with repeating to embrace formula locking device, overcome existing little inertia magnetically levitated flywheel the design of lockup equipment method with the minimum defect for optimization aim of quality, the method basic procedure is: utilize FEM-software ANSYS to set up the statics parameterized model of shell fragment at locking state respectively, the kinetic parameter model of locking state and the kinetic parameter model of released state, and three parameterized models are imported multidisciplinary optimization software iSIGHT, the span of continuous design variable and bound variable is set, optimized algorithm is utilized to calculate the direction of search and iteration step length, locking rigidity and the locking damping of the comprehensive optimum of shell fragment is obtained after multistep calculates.Specifically comprise the following steps:
Step 1, setting discrete heat sources shell fragment number is n=i=4;
Step 2, sets the initial value of continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w;
Step 3, adopts FEM-software ANSYS as handling implement, utilizes the shell fragment number of setting and the initial value of shell fragment height h, shell fragment thickness t and shell fragment width w, sets up the model of following shell fragment correlation behavior respectively, be specially:
(1) the statics finite element model of shell fragment at locking state is set up, this model APDL command stream is saved to locking statics file, this locking statics file can be the text of called after sl.txt, calculates shell fragment mass M, maximum stress in bend σ
maxwith releasing force f
u, result of calculation is saved to locking statics destination file, this locking statics destination file can be the text of called after response_sl.txt;
(2) Dynamics Finite Element Model of shell fragment at locking state is set up, this model APDL command stream is saved to locking power file, this locking power file can be the text of called after dl.txt, calculates shell fragment mass M, locking state first order resonance frequency F
l1, locking stiffness K and locking damping D, result of calculation is saved to locking power destination file, this locking power destination file can be the text of called after response_sl.txt;
(3) Dynamics Finite Element Model of shell fragment at released state is set up, this model APDL command stream is saved to and unlocks dynamics file, this unblock dynamics file can be the text of called after du.txt, calculates shell fragment mass M and released state first order resonance frequency F
u1, result of calculation be saved to and unlock kinetic results file, this unblock kinetic results file can be the text of called after response_du.txt;
Step 3, by described locking statics file, locking statics destination file, locking power file, locking power destination file, unlock dynamics file and unlock in kinetic results file importing multidisciplinary optimization software iSIGHT, and set the span of continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w, and setting bound variable shell fragment mass M, maximum stress in bend σ
max, releasing force f
u, locking state first order resonance frequency F
l1with released state first order resonance frequency F
u1restriction range;
Step 4, the optimized algorithm of multidisciplinary optimization software iSIGHT is utilized to calculate the direction of search and iteration step length, repeatedly text is locked statics file, locking power file and unlock dynamics file importing FEM-software ANSYS and statics and dynamics calculation are carried out to shell fragment, export locking statics destination file, the locking power destination file corresponding with each file simultaneously and unlock kinetic results file;
Step 5, judges whether optimizing process restrains;
Step 6, does not restrain if optimize, according to the direction of search and iteration step length, changes continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w, forward step 3 to;
Step 7, if optimize convergence, record shell fragment suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax;
Step 8, judges whether shell fragment number n=i is less than its maximal value 12;
Step 9, if when shell fragment number n=i is less than maximum shell fragment number 12, shell fragment number becomes n=i+1, and n=i+1 is substituted into step 2, enters cycle calculations;
Step 10, if when shell fragment number n=i is not less than maximum shell fragment number 12, more all shell fragment suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax, and obtain shell fragment universe optimum locking stiffness K
owith optimum locking damping D
o.
In said method, optimized algorithm is that second order can lead optimized algorithm, as adopted sequence double optimization algorithm or genetic algorithm etc.
In said method, shell fragment mass M is limited by magnetically levitated flywheel oeverall quality, and its restriction range is, M≤0.4Kg;
Maximum stress in bend σ
maxthe half of shell fragment material permissible stress [σ] should be less than or equal to;
Releasing force f
urelevant with shell fragment number i, its restriction range is, f
u=80/sin (2 π/n);
Locking state first order resonance frequency F
l1restriction range is, F
l1>=rocket launching maximum frequency of oscillation 2000Hz;
Released state first order resonance frequency F
u1restriction range is, F
u1>=1.5 times of magnetically levitated flywheel rotors the highest turn of frequency F
ω.
The principle of method for designing of the present invention is: utilize multidisciplinary optimization software iSIGHT to coordinate with FEM-software ANSYS and be optimized design to shell fragment, comprehensive optimum for optimization aim with the locking rigidity of locking device and locking damping, with shell fragment mass M, maximum stress in bend σ
max, releasing force f
u, locking state first order resonance frequency F
l1with released state first order resonance frequency F
u1for constraint condition, adopt universe relative method for discrete heat sources, adopt second order to lead optimized algorithm for the continuous design variable of elastic piece structure, Optimal Structure Designing is carried out to shell fragment.
Mathematical optimization models comprises design variable, feasible zone, bound variable, restriction range, objective function part.
Design variable: the structural parameters higher to the sensitivity of shell fragment bound variable are taken as design variable, specifically comprises shell fragment height h, shell fragment thickness t, shell fragment width w and shell fragment number n.It is as follows that design variable X is write as vector form,
X＝(h，t，w，n) (1)
Feasible zone: the span of design variable, as follows according to the span of requirement of engineering design variable X,
Bound variable: comprise shell fragment mass M, maximum stress in bend σ
max, releasing force f
u, locking state first order resonance frequency F
l1with released state first order resonance frequency F
u1.It is as follows that bound variable G is write as vector form,
G＝(M，σ
max，f
u，F
l1，F
u1) (3)
Bound variable scope: main from the viewpoint of statics and dynamics.(1) quality of space product is larger, and the rocket fuel of consumption is more, and launch cost is higher.Limit by magnetically levitated flywheel oeverall quality, require that shell fragment mass M is no more than 0.4kg.(2) under locking state, shell fragment is in case of bending, the bending stress that its inner existence is larger.For guaranteeing that locking device has higher reliability (safety coefficient is more than 2), require shell fragment maximum stress in bend σ
maxbe not more than the half of shell fragment material permissible stress [σ].(3) locking motor power one timing, under locking state, steel wire rope tension remains unchanged, and namely releasing force and coupling mechanism force sum are certain value, and the larger coupling mechanism force of releasing force is less, and reliable lock is lower.During for guaranteeing that shell fragment number is different, locking device has identical unblock reliability, requires releasing force f
uwith the corresponding relation of shell fragment number i be, f
u=80/sin (2 π/n).(4) launching powered phase, for avoiding rocket engine to evoke flywheel rotor resonance under locking state, thus evoking satellite platform vibration, require first order resonance frequency F under locking state
l1be not less than rocket launching maximum frequency of oscillation 2000Hz.(5) under released state, shell fragment is in free state, and its released state first order resonance frequency is too low, flywheel can be made to turn and frequently evoke shell fragment resonance, thus affect fly wheel system control moment precision.For guaranteeing that flywheel operating rotational speed range inner shrapnel, without resonance, (safety coefficient is more than 1.5) occurs, require released state first order resonance frequency F
u1be not less than the highest turn of 1.5 times of magnetically levitated flywheel rotors F frequently
ω.The mathematical notation of bound variable scope is as follows,
Objective function: write as functional form as follows for optimization aim so that the locking rigidity of locking device and locking damping are comprehensively optimum,
ε
KK+ε
DD＝maxf(h，t，w，n) (5)
Wherein K and D is locking rigidity and locking damping, ε
kand ε
drepresent the scale-up factor of locking stiffness K and locking damping D respectively.Discrete heat sources shell fragment number n=i=4 is set, and the kinetic parameter model of the statics parameterized model of the locking state of its correspondence, the kinetic parameter model of locking state and released state is imported multidisciplinary optimization software iSIGHT, and set the feasible zone of continuous design variable, restriction range and objective function, the optimized algorithm direction of search selecting second order to lead and iteration step length.After some step computings, obtain the suboptimum locking stiffness K under n=i=4
imaxwith suboptimum locking damping D
imax.In like manner, set gradually discrete heat sources shell fragment number n=i (i=5,6 ..., 12), and obtain corresponding suboptimum locking stiffness K respectively
imaxwith suboptimum locking damping D
imax.Finally more all suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax(i=4,5 ..., 12), obtain shell fragment universe optimum locking stiffness K
owith optimum locking damping D
o.
So far, this magnetically levitated flywheel can repeat embrace formula locking device shell fragment design complete.
Below in conjunction with specific embodiment, method for designing of the present invention is described further.
Design object of the present invention is the magnetically levitated flywheel shell fragment that can repeat to embrace formula locking device, and Fig. 1 is magnetically levitated flywheel locking device three-dimensional structure schematic diagram, and Fig. 2 a is shell fragment cut-open view, and Fig. 2 b is shell fragment sectional view, and Fig. 2 c is shell fragment three-dimensional structure schematic diagram.In Fig. 1,1 is flywheel stator core shaft, and 2 is flywheel rotor, and 3 is flywheel base, and 4 is priming system compulsive unlocking mechanism, and 5 is locking motor, and 6 is set nut, and 7 is leading screw, and 8 is wire rope, and 9 is shell fragment.
Method for designing of the present invention is with the locking rigidity of locking device and lock the comprehensive optimum of damping for optimization aim, and its design flow diagram as shown in Figure 3, specifically comprises the following steps:
(1) setting discrete heat sources shell fragment number is n=i=4;
(2) initial value of continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w is set;
(3) utilize FEM-software ANSYS to set up the statics finite element model of shell fragment at locking state, and preserve statical model APDL command stream text sl.txt, calculate and by shell fragment mass M, maximum stress in bend σ
maxwith releasing force f
u, export statics text response_sl.txt to;
(4) utilize FEM-software ANSYS to set up the Dynamics Finite Element Model of shell fragment at locking state, and preserve kinetic model APDL command stream text dl.txt, calculate and by shell fragment mass M, locking state first order resonance frequency F
l1, locking stiffness K and locking damping D, export dynamics text response_dl.txt to;
(5) utilize FEM-software ANSYS to set up the Dynamics Finite Element Model of shell fragment at released state, and preserve kinetic model APDL command stream text du.txt, calculate and by shell fragment mass M and released state first order resonance frequency F
u1, export dynamics text response_du.txt to;
(6) text sl.txt, response_sl.txt, dl.txt, response_dl.txt, du.txt and response_du.txt are imported in optimization integrated software, and set the span of continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w, set bound variable shell fragment mass M, maximum stress in bend σ simultaneously
max, releasing force f
u, locking state first order resonance frequency F
l1with released state first order resonance frequency F
u1restriction range;
(7) optimized algorithm is utilized to calculate the direction of search and iteration step length, and repeatedly text sl.txt, dl.txt and du.txt importing ANSYS software is carried out statics and dynamics calculation to shell fragment, export text response_sl.txt, response_dl.txt and response_du.txt of its correspondence simultaneously;
(8) judge whether optimizing process restrains;
(9) do not restrain if optimize, according to the direction of search and iteration step length, change continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w, and forward step (3) to;
(10) if optimize convergence, record shell fragment suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax;
(11) judge whether shell fragment number n=i is less than its maximal value 12;
(12) if when shell fragment number n=i is less than maximum shell fragment number 12, shell fragment number becomes n=i+1, and n=i+1 is substituted into step (2), enters cycle calculations;
(13) if when shell fragment number n=i is not less than maximum shell fragment number 12, more all shell fragment suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax, and obtain shell fragment universe optimum locking stiffness K
owith optimum locking damping D
o, namely complete the design of magnetically levitated flywheel locking device shell fragment.
Method for designing of the present invention also can be used for the design of all kinds of locking device of large inertia magnetic levitation inertia actuator, and meanwhile, the part be not described in detail in above-described embodiment all adopts relevant state of the art.
Method for designing of the present invention, with existing with compared with the minimum method for designing for target of quality, more can embody the protective value of locking device, make locking protected effect more reasonable, have the advantages such as accuracy is high, simple possible.
The above; be only the present invention's preferably embodiment, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (8)
1. magnetically levitated flywheel can repeat a method for designing of embracing formula locking device shell fragment, it is characterized in that, comprises the following steps:
Step 1, setting discrete heat sources shell fragment number is n=i=4;
Step 2, sets the initial value of continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w;
Step 3, adopts FEM-software ANSYS as handling implement, utilizes the shell fragment number of setting and the initial value of shell fragment height h, shell fragment thickness t and shell fragment width w, sets up the model of following shell fragment correlation behavior respectively, be specially:
(1) set up the statics finite element model of shell fragment at locking state, this model APDL command stream is saved to locking statics file, calculates shell fragment mass M, maximum stress in bend σ
maxwith releasing force f
u, result of calculation is saved to locking statics destination file;
(2) set up the Dynamics Finite Element Model of shell fragment at locking state, this model APDL command stream is saved to locking power file, calculates shell fragment mass M, locking state first order resonance frequency F
l1, locking stiffness K and locking damping D, result of calculation is saved to locking power destination file;
(3) set up the Dynamics Finite Element Model of shell fragment at released state, this model APDL command stream is saved to and unlocks dynamics file, calculate shell fragment mass M and released state first order resonance frequency F
u1, result of calculation is saved to and unlocks kinetic results file;
Step 3, by described locking statics file, locking statics destination file, locking power file, locking power destination file, unlock dynamics file and unlock in kinetic results file importing multidisciplinary optimization software iSIGHT, and set the span of continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w, and setting bound variable shell fragment mass M, maximum stress in bend σ
max, releasing force f
u, locking state first order resonance frequency F
l1with released state first order resonance frequency F
u1restriction range;
Step 4, the optimized algorithm of multidisciplinary optimization software iSIGHT is utilized to calculate the direction of search and iteration step length, repeatedly text is locked statics file, locking power file and unlock dynamics file importing FEM-software ANSYS and statics and dynamics calculation are carried out to shell fragment, export locking statics destination file, the locking power destination file corresponding with each file simultaneously and unlock kinetic results file;
Step 5, judges whether optimizing process restrains;
Step 6, does not restrain if optimize, according to the direction of search and iteration step length, changes continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w, forward step 3 to;
Step 7, if optimize convergence, record shell fragment suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax;
Step 8, judges whether shell fragment number n=i is less than its maximal value 12;
Step 9, if when shell fragment number n=i is less than maximum shell fragment number 12, shell fragment number becomes n=i+1, and n=i+1 is substituted into step 2, enters cycle calculations;
Step 10, if when shell fragment number n=i is not less than maximum shell fragment number 12, more all shell fragment suboptimum locking stiffness K
imaxwith suboptimum locking damping D
imax, and obtain shell fragment universe optimum locking stiffness K
owith optimum locking damping D
o.
2. magnetically levitated flywheel according to claim 1 can repeat the method for designing of embracing formula locking device shell fragment, and it is characterized in that, described optimized algorithm is that second order can lead optimized algorithm.
3. magnetically levitated flywheel according to claim 2 can repeat the method for designing of embracing formula locking device shell fragment, it is characterized in that, described second order can be led optimized algorithm and be adopted sequence double optimization algorithm or genetic algorithm.
4. magnetically levitated flywheel according to claim 1 can repeat the method for designing of embracing formula locking device shell fragment, and it is characterized in that, the restriction range of described shell fragment mass M is: M≤0.4Kg.
5. magnetically levitated flywheel according to claim 1 is with repeating the method for designing of embracing formula locking device, it is characterized in that, described maximum stress in bend σ
maxbe less than or equal to the half of shell fragment material permissible stress [σ].
6. magnetically levitated flywheel according to claim 1 can repeat the method for designing of embracing formula locking device shell fragment, it is characterized in that, described releasing force f
urestriction range be: f
u=80/sin (2 π/n).
7. magnetically levitated flywheel according to claim 1 can repeat the method for designing of embracing formula locking device shell fragment, it is characterized in that: described locking state first order resonance frequency F
l1restriction range be: F
l1>=rocket launching maximum frequency of oscillation 2000Hz.
8. magnetically levitated flywheel according to claim 1 can repeat the method for designing of embracing formula locking device shell fragment, it is characterized in that, described released state first order resonance frequency F
u1restriction range be: F
u1>=1.5 times of magnetically levitated flywheel rotors the highest turn of frequency F
ω.
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| CN106528969A (en) * | 2016-10-31 | 2017-03-22 | 努比亚技术有限公司 | Metal shrapnel simulation method and device |
| CN108875278A (en) * | 2018-07-26 | 2018-11-23 | 北京石油化工学院 | The design method of Lorentz force deflection magnetic bearing |
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Cited By (10)
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| CN106528969A (en) * | 2016-10-31 | 2017-03-22 | 努比亚技术有限公司 | Metal shrapnel simulation method and device |
| CN106528969B (en) * | 2016-10-31 | 2021-06-15 | 努比亚技术有限公司 | Metal elastic sheet simulation method and device |
| CN108875278A (en) * | 2018-07-26 | 2018-11-23 | 北京石油化工学院 | The design method of Lorentz force deflection magnetic bearing |
| CN108875278B (en) * | 2018-07-26 | 2022-06-17 | 北京石油化工学院 | Lorentz force deflection magnetic bearing design method |
| CN109918780A (en) * | 2019-03-06 | 2019-06-21 | 西安交通大学 | A kind of small retaining mechanism elastic element optimum design method towards high stability |
| CN109918780B (en) * | 2019-03-06 | 2020-11-10 | 西安交通大学 | High-stability-oriented optimal design method for elastic element of micro locking mechanism |
| CN113177341A (en) * | 2021-05-21 | 2021-07-27 | 南京工程学院 | Magnetic suspension flywheel motor multi-objective optimization design method based on kriging approximate model |
| CN113177341B (en) * | 2021-05-21 | 2023-08-22 | 南京工程学院 | Magnetic suspension flywheel motor multi-objective optimization design method based on kriging approximate model |
| CN113895654A (en) * | 2021-10-27 | 2022-01-07 | 北京航空航天大学宁波创新研究院 | Magnetic suspension inertia actuating mechanism locking device based on magnetostrictive shape memory structure |
| CN113895654B (en) * | 2021-10-27 | 2023-08-04 | 北京航空航天大学宁波创新研究院 | Magnetic suspension inertial actuating mechanism locking device based on magnetostriction shape memory structure |
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