CN104899400B - The repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel - Google Patents
The repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel Download PDFInfo
- Publication number
- CN104899400B CN104899400B CN201510355363.1A CN201510355363A CN104899400B CN 104899400 B CN104899400 B CN 104899400B CN 201510355363 A CN201510355363 A CN 201510355363A CN 104899400 B CN104899400 B CN 104899400B
- Authority
- CN
- China
- Prior art keywords
- shell fragment
- locking
- file
- locking device
- magnetically levitated
- 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
Abstract
The invention discloses a kind of repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel, including：Coordinated using multidisciplinary optimization software iSIGHT and FEM-software ANSYS and design is optimized to shell fragment, it is optimal for optimization aim with the locking rigidity of locking device and locking damping synthesis, with shell fragment mass M, maximum stress in bend σmax, releasing force fu, locking state first order resonance frequency Fl1With released state first order resonance frequency Fu1For constraints, universe comparison method is used for discrete heat sources, optimized algorithm can be led using second order for elastic piece structure continuous design variable, Optimal Structure Designing is carried out to shell fragment.This method can more embody the protective value of locking device, make locking protecting effect more reasonable, have the advantages that degree of accuracy height, simple possible, and its design philosophy can be used for the design of all kinds of large inertia magnetic suspension rotor locking devices.
Description
Technical field
The present invention relates to the repeatable design field for embracing formula locking device shell fragment of magnetically levitated flywheel, particularly large-scale space flight
The design method of device large inertia magnetically levitated flywheel and large magnetic suspension control-moment gyro locking device shell fragment.
Background technology
With the development of space technology, to meet to determine spacecraft the higher and higher requirement of appearance, orbit determination accuracy, generally use
Counteraction flyback and bias momentum wheel control satellite platform.Magnetically levitated flywheel is a kind of new spacecraft attitude control system, with
Tradition machinery flywheel is compared, and is had a clear superiority in control accuracy and service life etc..Due to magnetically levitated flywheel stator and rotor
Between certain magnetic portable protective gaps be present, for prevent launch the mutual collision impact of powered phase flywheel stator and rotor damage, fly wheel system
Retaining mechanism must be used, locking confining guard is carried out to it.
According to position of the locking device in magnetically levitated flywheel, locking device can be divided into internal locking device and outer locking dress
Put.According to locking/unblock number, locking device can be divided into disposable locking device and repeatable locking device.Spacecraft Launch
Before, magnetically levitated flywheel must complete various ground environment experiments, need often it lock/unlock.In addition, become rail work
When, to prevent interference of the flywheel of free state to attitude control platform, also need to be locked；After entering the orbit, then flywheel rotor is carried out
Unblock.At present used in repeatable locking device mainly have electromagnetic locking device, based on motor-conical surface locking closure locking device,
Based on motor-lever lock device and embrace formula locking device.Electromagnetic locking dress described in number of patent application 200810119968.0
Put, by controlling the electromagnetism magnetic field of electromagnet positive/negative to being superimposed with permanent magnetic field, realize repetition locking/unblock of flywheel.But lock
Tight startup power is inversely proportional with unblock gap, and unblock gap can not be adjusted, and very big inconvenience is brought to the assembling and setting of locking device.
During work, three to four electromagnetic locking devices are along the circumferential direction installed typically on flywheel base so that perform locking and perform
During unblock, higher is required to the synchronism of electromagnet action.In addition, if any electromagnetic locking device fails, magnetcisuspension may result in
Suspension flywheel system can not perform locking and unblock, reduce the reliability of locking device.Number of patent application 201210338347.8
It is described based on motor-conical surface locking closure locking device, by positive/negative turn of motor, driving conical surface locking closure compresses/unclamped flywheel and turns
Son, realize repetition locking/unblock of flywheel.Conical surface locking closure is positioned over stator core shaft radially inner side, reduce flywheel volume and
Weight, but the constraint area of the conical surface locking closure conical surface is smaller, and locking constraint rigidity is relatively low, causes large inertia magnetic suspension in vibration processes
Vibration displacement is larger between flywheel stator and rotor.Formula locking device is embraced described in number of patent application 200910093150.0, utilizes shell fragment
As mechanism is upheld, by the use of steel wire rope as tightening system, by positive/negative turn of motor, drive tightening system to uphold mechanism and receive
Hold together/unclamp, so as to hold tightly/discharge flywheel rotor, realize repetition locking/unblock of flywheel.The locking device fills with electromagnetic locking
Put and compare, when locking device breaks down, steel wire rope is chopped off using priming system compulsive unlocking is carried out to flywheel, add execution
Reliability is unlocked, and shell fragment stroke is adjustable, i.e. unblock gap is adjustable, has the advantages of assembling and setting facilitates.With based on motor-cone
Face locking closure locking device is compared, and the shell fragment and flywheel rotor EDGE CONTACT area of armful formula locking device are larger, add locking
Rigidity, so as to preferably carry out confining guard to fly-wheel control rotor.
Shell fragment is as follows as the repeatable critical component for embracing formula locking device, influence of its mechanical property to fly wheel system：
(1) releasing force under locking state determines the unblock reliability of locking device；(2) timing of locking motor power one, steel wire rope
Tension force keeps constant, i.e., releasing force and coupling mechanism force sum are certain value, and the bigger coupling mechanism force of releasing force is smaller, and reliable lock is got over
It is low；(3) bending stress excessive under locking state may cause shell fragment to be plastically deformed；(4) under released state, shell fragment is in freely
State, its released state first order resonance frequency is too low, can influence fly wheel system control moment precision；(5) under locking state, even if
Coupling mechanism force can constrain flywheel rotor, but too low locking rigidity can cause to launch the vibration displacement mistake between powered phase stator and rotor
Greatly, cause fierce collision and impact occurs between stator and rotor；(6) powered phase is launched, flywheel rotor inertia force is larger, too low
Locking damping can not absorb flywheel rotor kinetic energy in time, force vibration displacement further to amplify, also result in fierce collision with
The generation of impact.Therefore how to design can meet the locking of whole locking device and unblock reliability, fly wheel system performance and
The shell fragment of flywheel locking protecting effect requirement is to need to solve the problems, such as.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of repeatable armful of formula locking device shell fragment of magnetically levitated flywheel
Design method, the magnetically levitated flywheel that can design high rigidity high-damping embrace formula locking device with repeatable, solve existing small inertia
The problem of magnetically levitated flywheel the design of lockup equipment method minimum with quality optimization aim.
In order to solve the above technical problems, the present invention provides a kind of repeatable armful of formula locking device shell fragment of magnetically levitated flywheel
Design method, this method are comprehensive optimal for design mesh with the repeatable locking rigidity for embracing formula locking device shell fragment and locking damping
Mark, comprises the following steps：
Step 1, discrete heat sources shell fragment number is set as n=i=4；
Step 2, continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w initial value are set；
Step 3, using FEM-software ANSYS as handling implement, using the shell fragment number and shell fragment height h of setting,
Shell fragment thickness t and shell fragment width w initial value, the model of following shell fragment correlation behavior is established respectively, be specially：
(1) statics FEM model of the shell fragment in locking state is established, model APDL command streams are preserved to locking
Statics file, calculate shell fragment mass M, maximum stress in bend σmaxWith releasing force fu, result of calculation is preserved to locking static(al)
Learn destination file；
(2) Dynamics Finite Element Model of the shell fragment in locking state is established, model APDL command streams are preserved to locking
Dynamics file, calculate shell fragment mass M, locking state first order resonance frequency Fl1, locking stiffness K and locking damping D, will calculate
As a result preserve to locking power destination file；
(3) Dynamics Finite Element Model of the shell fragment in released state is established, model APDL command streams are preserved to unblock
Dynamics file, calculate shell fragment mass M and released state first order resonance frequency Fu1, result of calculation is preserved to unblock dynamics
Destination file；
Step 3, by the locking statics file, locking statics destination file, locking power file, locking power
Learn destination file, unblock dynamics file and unblock kinetic results file to import in multidisciplinary optimization software iSIGHT, and set
Fixed continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w span, and setting bound variable shell fragment matter
Measure M, maximum stress in bend σmax, releasing force fu, locking state first order resonance frequency Fl1With released state first order resonance frequency Fu1's
Restriction range；
Step 4, the direction of search and iteration step length are calculated using multidisciplinary optimization software iSIGHT optimized algorithm, repeatedly will
Text locking statics file, locking power file and unblock dynamics file import FEM-software ANSYS to bullet
Piece carries out statics and dynamics calculation, while exports locking statics destination file corresponding with each file, locking power
Destination file and unblock kinetic results file；
Step 5, judge whether optimization process restrains；
Step 6, if optimization does not restrain, 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, goes to step 3；
Step 7, if optimization convergence, record shell fragment suboptimum locking stiffness KimaxDamping D is locked with suboptimumimax；
Step 8, judge whether shell fragment number n=i is less than its maximum 12；
Step 9, if shell fragment number n=i is less than maximum shell fragment number 12, shell fragment number is changed into n=i+1, and by n=i+
1 substitutes into step 2, into cycle calculations；
Step 10, if shell fragment number n=i is not less than maximum shell fragment number 12, the locking of more all shell fragment suboptimums is firm
Spend KimaxDamping D is locked with suboptimumimax, and obtain the optimal locking stiffness K of shell fragment universeoWith optimal locking damping Do。
Beneficial effects of the present invention are：Due to being coordinated using FEM-software ANSYS and multidisciplinary optimization software iSIGHT,
Design efficiency is improved, and using the high rigidity of locking device and high-damping as design object, with existing with locking device
The design method of the minimum starting point of quality is compared, and is more favorable for improving the performance of locking device, is especially more applicable for big
The design of inertia magnetic suspension inertia actuator locking device.
Brief description of the drawings
In order to illustrate the technical solution of the embodiments of the present invention more clearly, required use in being described below to embodiment
Accompanying drawing be briefly described, it should be apparent that, drawings in the following description are only some embodiments of the present invention, for this
For the those of ordinary skill in field, on the premise of not paying creative work, other can also be obtained according to these accompanying drawings
Accompanying drawing.
Fig. 1 provides the magnetically levitated flywheel locking device three dimensional structure diagram of method design for the embodiment of the present invention；
Fig. 2 a provide the shell fragment sectional view of the magnetically levitated flywheel locking device of method design for the embodiment of the present invention；
Fig. 2 b provide the shell fragment sectional view of the magnetically levitated flywheel locking device of method design for the embodiment of the present invention；
Fig. 2 c provide the shell fragment three-dimensional structure signal of the magnetically levitated flywheel locking device of method design for the embodiment of the present invention
Figure；
Fig. 3 is design method flow chart provided in an embodiment of the present invention.
Embodiment
The technical scheme in the embodiment of the present invention is clearly and completely described below, it is clear that described embodiment
Only part of the embodiment of the present invention, rather than whole embodiments.Based on embodiments of the invention, ordinary skill
The every other embodiment that personnel are obtained under the premise of creative work is not made, belongs to protection scope of the present invention.
The repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel of the present invention, using high rigidity high-damping as
The design magnetically levitated flywheel of starting point embraces formula locking device with repeatable, overcomes existing small inertia magnetically levitated flywheel locking device to set
The defects of meter method minimum with quality optimization aim, this method basic procedure is：Established respectively using FEM-software ANSYS
Statics parameterized model, the kinetic parameter model of locking state and the dynamics of released state of the shell fragment in locking state
Parameterized model, and three parameterized models are imported into multidisciplinary optimization software iSIGHT, continuous design variable and constraint are set
The span of variable, the direction of search and iteration step length are calculated using optimized algorithm, the synthesis of shell fragment is obtained after multistep calculates
Optimal locking rigidity and locking damps.Specifically include following steps：
Step 1, discrete heat sources shell fragment number is set as n=i=4；
Step 2, continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w initial value are set；
Step 3, using FEM-software ANSYS as handling implement, using the shell fragment number and shell fragment height h of setting,
Shell fragment thickness t and shell fragment width w initial value, the model of following shell fragment correlation behavior is established respectively, be specially：
(1) statics FEM model of the shell fragment in locking state is established, model APDL command streams are preserved to locking
Statics file, the locking statics file can be the text for being named as sl.txt, calculate shell fragment mass M, maximum
Bending stress σmaxWith releasing force fu, result of calculation is preserved to locking statics destination file, the locking statics destination file
It can be the text for being named as response_sl.txt；
(2) Dynamics Finite Element Model of the shell fragment in locking state is established, model APDL command streams are preserved to locking
Dynamics file, the locking power file can be the texts for being named as dl.txt, calculate shell fragment mass M, locking
State first order resonance frequency Fl1, locking stiffness K and locking damping D, result of calculation is preserved to locking power destination file, this
Locking power destination file can be the text for being named as response_sl.txt；
(3) Dynamics Finite Element Model of the shell fragment in released state is established, model APDL command streams are preserved to unblock
Dynamics file, the unblock dynamics file can be the text for being named as du.txt, calculate shell fragment mass M and unblock
State first order resonance frequency Fu1, result of calculation is preserved to unblock kinetic results file, the unblock kinetic results file can
To be the text for being named as response_du.txt；
Step 3, by the locking statics file, locking statics destination file, locking power file, locking power
Learn destination file, unblock dynamics file and unblock kinetic results file to import in multidisciplinary optimization software iSIGHT, and set
Fixed continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w span, and setting bound variable shell fragment matter
Measure M, maximum stress in bend σmax, releasing force fu, locking state first order resonance frequency Fl1With released state first order resonance frequency Fu1's
Restriction range；
Step 4, the direction of search and iteration step length are calculated using multidisciplinary optimization software iSIGHT optimized algorithm, repeatedly will
Text locking statics file, locking power file and unblock dynamics file import FEM-software ANSYS to bullet
Piece carries out statics and dynamics calculation, while exports locking statics destination file corresponding with each file, locking power
Destination file and unblock kinetic results file；
Step 5, judge whether optimization process restrains；
Step 6, if optimization does not restrain, 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, goes to step 3；
Step 7, if optimization convergence, record shell fragment suboptimum locking stiffness KimaxDamping D is locked with suboptimumimax；
Step 8, judge whether shell fragment number n=i is less than its maximum 12；
Step 9, if shell fragment number n=i is less than maximum shell fragment number 12, shell fragment number is changed into n=i+1, and by n=i+
1 substitutes into step 2, into cycle calculations；
Step 10, if shell fragment number n=i is not less than maximum shell fragment number 12, the locking of more all shell fragment suboptimums is firm
Spend KimaxDamping D is locked with suboptimumimax, and obtain the optimal locking stiffness K of shell fragment universeoWith optimal locking damping Do。
In the above method, optimized algorithm is that second order can lead optimized algorithm, can such as use sequence double optimization algorithm or heredity
Algorithm etc..
In the above 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 σmaxIt should be less than the half equal to shell fragment material allowable stress [σ]；
Releasing force fuRelevant with shell fragment number i, its restriction range is fu=80/sin (2 π/n)；
Locking state first order resonance frequency Fl1Restriction range is Fl1>=rocket launching maximum frequency of oscillation 2000Hz；
Released state first order resonance frequency Fu1Restriction range is Fu1>=1.5 times of magnetically levitated flywheel rotor highests turn frequency Fω。
The principle of design method of the present invention is：Coordinated using multidisciplinary optimization software iSIGHT and FEM-software ANSYS
Design is optimized to shell fragment, it is optimal for optimization aim with the locking rigidity of locking device and locking damping synthesis, with shell fragment matter
Measure M, maximum stress in bend σmax, releasing force fu, locking state first order resonance frequency Fl1With released state first order resonance frequency Fu1For
Constraints, universe comparison method is used for discrete heat sources, can be led using second order for the continuous design variable of elastic piece structure
Optimized algorithm, Optimal Structure Designing is carried out to shell fragment.
Mathematical optimization models include design variable, feasible zone, bound variable, restriction range, object function part.
Design variable：Design variable is taken as to shell fragment bound variable structural parameters in higher sensitivity, specifically includes bullet
Piece 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, it is as follows according to requirement of engineering design variable X span,
Bound variable：Including shell fragment mass M, maximum stress in bend σmax, releasing force fu, locking state first order resonance frequency
Fl1With released state first order resonance frequency Fu1.It is as follows that bound variable G is write as vector form,
G=(M, σmax, fu, Fl1, Fu1) (3)
Bound variable scope：Mainly from the aspect of statics and dynamics.(1) quality of space product is bigger, consumption
Rocket fuel is more, and launch cost is higher.Limited by magnetically levitated flywheel oeverall quality, it is desirable to which shell fragment mass M is no more than 0.4kg.
(2) under locking state, shell fragment is in case of bending, larger bending stress inside it be present.For ensure locking device have compared with
High reliability (safety coefficient is more than 2), it is desirable to shell fragment maximum stress in bend σmaxNo more than shell fragment material allowable stress [σ]
Half.(3) timing of locking motor power one, steel wire rope tension keeps constant under locking state, i.e., releasing force and coupling mechanism force it
With for certain value, the bigger coupling mechanism force of releasing force is smaller, and reliable lock is lower.During to ensure shell fragment number difference, locking device
Reliability is unlocked with identical, it is desirable to releasing force fuCorresponding relation with shell fragment number i is fu=80/sin (2 π/n).(4)
Launch powered phase, to avoid rocket engine from evoking the flywheel rotor resonance under locking state, so as to evoke satellite platform vibration,
It is required that first order resonance frequency F under locking statel1Not less than rocket launching maximum frequency of oscillation 2000Hz.(5) under released state, bullet
Piece is in free state, and its released state first order resonance frequency is too low, and flywheel can be made to turn frequency and evoke shell fragment resonance, so as to influence to fly
Wheel system control moment precision.To ensure that without resonance (safety coefficient is more than 1.5) occur for flywheel operating rotational speed range inner shrapnel,
It is required that released state first order resonance frequency Fu1Not less than 1.5 times magnetically levitated flywheel rotor highests turn frequency Fω.Bound variable scope
Mathematical notation is as follows,
Object function：It is optimal for optimization aim with the locking rigidity of locking device and locking damping synthesis, write as function shape
Formula is as follows,
εKK+εDD=maxf (h, t, w, n) (5)
Wherein K and D damps for locking rigidity and locking, εKAnd εDLocking stiffness K and locking damping D ratio are represented respectively
Coefficient.Set discrete heat sources shell fragment number n=i=4, and by the statics parameterized model of its corresponding locking state,
The kinetic parameter model of locking state and the kinetic parameter model of released state import multidisciplinary optimization software
ISIGHT, and feasible zone, restriction range and the object function of continuous design variable are set, the optimized algorithm for selecting second order to lead
The direction of search and iteration step length.After some step computings, the suboptimum locking stiffness K under n=i=4 is obtainedimaxLock and hinder with suboptimum
Buddhist nun Dimax.Similarly, discrete heat sources shell fragment number n=i (i=5,6 ..., 12) is set gradually, and is respectively obtained corresponding time
Excellent locking stiffness KimaxDamping D is locked with suboptimumimax.Finally more all suboptimum locking stiffness KsimaxLock and damp with suboptimum
Dimax(i=4,5 ..., 12), obtain the optimal locking stiffness K of shell fragment universeoWith optimal locking damping Do。
So far, the repeatable shell fragment design for embracing formula locking device of the magnetically levitated flywheel finishes.
The design method of the present invention is described further with reference to specific embodiment.
The design object of the present invention is flown for magnetically levitated flywheel with the repeatable shell fragment for embracing formula locking device, Fig. 1 for magnetic suspension
Locking device three dimensional structure diagram is taken turns, Fig. 2 a are shell fragment sectional view, and Fig. 2 b are shell fragment sectional view, and Fig. 2 c are shell fragment three-dimensional structure
Schematic diagram.1 is flywheel stator core shaft in Fig. 1, and 2 be flywheel rotor, and 3 be flywheel base, and 4 be priming system compulsive unlocking mechanism, and 5 are
Locking motor, 6 be locking nut, and 7 be leading screw, and 8 be steel wire rope, and 9 be shell fragment.
Design method of the present invention is optimal for optimization aim with the locking rigidity of locking device and locking damping synthesis, and it is designed
Flow chart is as shown in figure 3, specifically include following steps：
(1) discrete heat sources shell fragment number is set as n=i=4；
(2) continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w initial value are set；
(3) statics FEM model of the shell fragment in locking state is established using FEM-software ANSYS, and preserves static(al)
Model APDL command stream text sl.txt are learned, are calculated and by shell fragment mass M, maximum stress in bend σmaxWith releasing force fu, it is defeated
Go out to statics text response_sl.txt；
(4) Dynamics Finite Element Model of the shell fragment in locking state is established using FEM-software ANSYS, and preserves power
Model APDL command stream text dl.txt are learned, are calculated and by shell fragment mass M, locking state first order resonance frequency Fl1, locking
Stiffness K and locking damping D, are exported to dynamics text response_dl.txt；
(5) Dynamics Finite Element Model of the shell fragment in released state is established using FEM-software ANSYS, and preserves power
Model APDL command stream text du.txt are learned, are calculated and by shell fragment mass M and released state first order resonance frequency Fu1, output
To dynamics text response_du.txt；
(6) by text sl.txt, response_sl.txt, dl.txt, response_dl.txt, du.txt and
Response_du.txt is imported in optimization integrated software, and sets continuous design variable shell fragment height h, shell fragment thickness t and shell fragment
Width w span, concurrently set bound variable shell fragment mass M, maximum stress in bend σmax, releasing force fu, locking state one
Rank resonant frequency Fl1With released state first order resonance frequency Fu1Restriction range；
(7) direction of search and iteration step length are calculated using optimized algorithm, and repeatedly by text sl.txt, dl.txt and
Du.txt imports ANSYS softwares and carries out statics and dynamics calculation to shell fragment, while exports its corresponding text
Response_sl.txt, response_dl.txt and response_du.txt；
(8) judge whether optimization process restrains；
(9) if optimization does not restrain, according to the direction of search and iteration step length, continuous design variable shell fragment height h, shell fragment are changed
Thickness t and shell fragment width w, and go to step (3)；
(10) if optimization convergence, record shell fragment suboptimum locking stiffness KimaxDamping D is locked with suboptimumimax；
(11) judge whether shell fragment number n=i is less than its maximum 12；
(12) if shell fragment number n=i is less than maximum shell fragment number 12, shell fragment number is changed into n=i+1, and by n=i+1
Step (2) is substituted into, into cycle calculations；
(13) if shell fragment number n=i is not less than maximum shell fragment number 12, more all shell fragment suboptimums locking rigidity
KimaxDamping D is locked with suboptimumimax, and obtain the optimal locking stiffness K of shell fragment universeoWith optimal locking damping Do, that is, complete magnetcisuspension
The design of suspension flywheel locking device shell fragment.
The design method of the present invention can also be used for design of the large inertia magnetic suspension inertia actuator with all kinds of locking devices,
Meanwhile the part not being described in detail in above-described embodiment is using related state of the art.
The present invention design method, with it is existing with the design method of the minimum target of quality compared with, can more embody locking
The protective value of device, make locking protecting effect more reasonable, there is degree of accuracy height, simple possible.
The foregoing is only a preferred embodiment of the present invention, but protection scope of the present invention be not limited thereto,
Any one skilled in the art is in the technical scope of present disclosure, the change or replacement that can readily occur in,
It should all be included within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of claims
Enclose and be defined.
Claims (8)
1. the repeatable design method for embracing formula locking device shell fragment of a kind of magnetically levitated flywheel, it is characterised in that including following step
Suddenly：
Step 1, discrete heat sources shell fragment number is set as n=i=4, and wherein n is shell fragment number, and i is following in shell fragment circulation
Ring variable；
Step 2, continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w initial value are set；
Step 3, the shell fragment number and shell fragment height h, shell fragment of setting are utilized as handling implement using FEM-software ANSYS
Thickness t and shell fragment width w initial value, the model of following shell fragment correlation behavior is established respectively, be specially：
(1) statics FEM model of the shell fragment in locking state is established, model APDL command streams are preserved to locking static(al)
File is learned, calculates shell fragment mass M, maximum stress in bend σmaxWith releasing force fu, result of calculation is preserved to locking statics knot
Fruit file；
(2) Dynamics Finite Element Model of the shell fragment in locking state is established, model APDL command streams are preserved to locking power
File is learned, calculates shell fragment mass M, locking state first order resonance frequency Fl1, locking stiffness K and locking damping D, by result of calculation
Preserve to locking power destination file；
(3) Dynamics Finite Element Model of the shell fragment in released state is established, model APDL command streams are preserved to unblock power
File is learned, calculates shell fragment mass M and released state first order resonance frequency Fu1, result of calculation is preserved to unblock kinetic results
File；
Step 3, the locking statics file, locking statics destination file, locking power file, locking power are tied
Fruit file, unblock dynamics file and unblock kinetic results file are imported in multidisciplinary optimization software iSIGHT, and the company of setting
Continuous design variable shell fragment height h, shell fragment thickness t and shell fragment width w span, and setting bound variable shell fragment mass M,
Maximum stress in bend σmax, releasing force fu, locking state first order resonance frequency Fl1With released state first order resonance frequency Fu1Constraint
Scope；
Step 4, the direction of search and iteration step length are calculated using multidisciplinary optimization software iSIGHT optimized algorithm, repeatedly by text
File locking statics file, locking power file and unblock dynamics file import FEM-software ANSYS and shell fragment are entered
Row statics and dynamics calculation, while export locking statics destination file corresponding with each file, locking power result
File and unblock kinetic results file；
Step 5, judge whether optimization process restrains；
Step 6, if optimization does not restrain, according to the direction of search and iteration step length, continuous design variable shell fragment height h, shell fragment are changed
Thickness t and shell fragment width w, goes to step 3；
Step 7, if optimization convergence, record shell fragment suboptimum locking stiffness KimaxDamping D is locked with suboptimumimax；
Step 8, judge whether shell fragment number n=i is less than its maximum 12；
Step 9, if shell fragment number n=i is less than maximum shell fragment number 12, shell fragment number is changed into n=i+1, and by n=i+1 generations
Enter step 2, into cycle calculations；
Step 10, if shell fragment number n=i is not less than maximum shell fragment number 12, more all shell fragment suboptimums locking stiffness Kimax
Damping D is locked with suboptimumimax, and obtain the optimal locking stiffness K of shell fragment universeoWith optimal locking damping Do。
2. the repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel according to claim 1, its feature
It is, the optimized algorithm is that second order can lead optimized algorithm.
3. the repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel according to claim 2, its feature
It is, the second order can lead optimized algorithm and use sequence double optimization algorithm or genetic algorithm.
4. the repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel according to claim 1, its feature
It is, the restriction range of the shell fragment mass M is：M≤0.4Kg.
5. the repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel according to claim 1, its feature
It is, the maximum stress in bend σmaxLess than or equal to the half of shell fragment material allowable stress [σ], wherein the shell fragment material that [σ] is represented
Expect that allowable stress is shell fragment material maximum stress value allowed to bear.
6. the repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel according to claim 1, its feature
It is, the releasing force fuConstraints be：fu=80/sin (2 π/n).
7. the repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel according to claim 1, its feature
It is：The locking state first order resonance frequency Fl1Restriction range be：Fl1>=rocket launching maximum frequency of oscillation 2000Hz.
8. the repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel according to claim 1, its feature
It is, the released state first order resonance frequency Fu1Restriction range be：Fu1>=1.5 times of magnetically levitated flywheel rotor highests turn frequency
Fω。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510355363.1A CN104899400B (en) | 2015-06-24 | 2015-06-24 | The repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510355363.1A CN104899400B (en) | 2015-06-24 | 2015-06-24 | The repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104899400A CN104899400A (en) | 2015-09-09 |
| CN104899400B true CN104899400B (en) | 2018-02-23 |
Family
ID=54032062
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510355363.1A Active CN104899400B (en) | 2015-06-24 | 2015-06-24 | The repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104899400B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106528969B (en) * | 2016-10-31 | 2021-06-15 | 努比亚技术有限公司 | Metal elastic sheet simulation method and device |
| CN108875278B (en) * | 2018-07-26 | 2022-06-17 | 北京石油化工学院 | Lorentz force deflection magnetic bearing design method |
| 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 |
| 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 |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5031587A (en) * | 1989-03-22 | 1991-07-16 | Briggs & Stratton Corporation | Internal combustion engine with integral stator and regulator |
| CN101693472A (en) * | 2009-09-25 | 2010-04-14 | 北京航空航天大学 | Repeatable locking device for magnetically suspended flywheel |
| CN101792024A (en) * | 2010-03-03 | 2010-08-04 | 北京航空航天大学 | Lever-type repeatable locking device for magnetically suspended flywheel |
| CN104309821A (en) * | 2014-09-29 | 2015-01-28 | 北京石油化工学院 | Repeatable maglev flywheel locking device |
-
2015
- 2015-06-24 CN CN201510355363.1A patent/CN104899400B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5031587A (en) * | 1989-03-22 | 1991-07-16 | Briggs & Stratton Corporation | Internal combustion engine with integral stator and regulator |
| CN101693472A (en) * | 2009-09-25 | 2010-04-14 | 北京航空航天大学 | Repeatable locking device for magnetically suspended flywheel |
| CN101792024A (en) * | 2010-03-03 | 2010-08-04 | 北京航空航天大学 | Lever-type repeatable locking device for magnetically suspended flywheel |
| CN104309821A (en) * | 2014-09-29 | 2015-01-28 | 北京石油化工学院 | Repeatable maglev flywheel locking device |
Non-Patent Citations (1)
| Title |
|---|
| 磁悬浮飞轮用可重复电磁锁紧装置的设计与试验;刘强等;《机械工程学报》;20120430;第48卷(第8期);第12-20页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104899400A (en) | 2015-09-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104899400B (en) | The repeatable design method for embracing formula locking device shell fragment of magnetically levitated flywheel | |
| CN104267732B (en) | Flexible satellite high stability attitude control method based on frequency-domain analysis | |
| Bachmann et al. | Passive damping of composite blades using embedded piezoelectric modules or shape memory alloy wires: a comparative study | |
| CN104973268B (en) | High-frequency micro-vibration isolation device of spacecraft control moment gyroscope | |
| CN104899399B (en) | The design method of repeatable electromagnetic locking device electromagnet | |
| Zeng et al. | Micro-amplitude vibration suppression of a bistable nonlinear energy sink constructed by a buckling beam | |
| Geng et al. | Dynamic design of a magnetic-enhanced nonlinear energy sink | |
| CN106886152A (en) | A kind of magnetic suspension rotor odd harmonic electric current suppressing method based on second order odd repetitive controller | |
| Karmakar et al. | Failure analysis of laminated composite pretwisted rotating plates | |
| Zhang et al. | Combined resonance of graphene platelets reinforced metal foams cylindrical shells with spinning motion under nonlinear forced vibration | |
| Wang et al. | Improving the gravity-rotation-excited vibration energy harvesting in offset configurations | |
| Ye et al. | Design and optimization of repeatable locking/unlocking device for magnetically suspended control moment gyro | |
| Försching | Aeroelastic stability of cascades in turbomachinery | |
| Yu et al. | A new hysteretic model for magnetorheological elastomer base isolator and parameter identification based on modified artificial fish swarm algorithm | |
| Yang et al. | Longitudinal aerodynamic performance of the apollo entry capsule near transonic speeds | |
| CN105468046B (en) | The many branched power local vibration control methods of ship basic propulsion system | |
| Jensen et al. | Numerical simulation of gyroscopic effects in Ansys | |
| Xiao et al. | Study on vibration of marine diesel-electric hybrid propulsion system | |
| Kim et al. | Actuator design and flight testing of an active microspoiler-equipped projectile | |
| Rogers et al. | Cantilever beam design for projectile internal moving mass systems | |
| Cassenti | A contained antiproton catalyzed pulse nuclear propulsion system | |
| CN107066653A (en) | A kind of aeroelastic analysis method for considering engine dynamics | |
| CN109188900A (en) | Spacecraft compliant member caused by a kind of external disturbance vibrates passive suppressing method | |
| Zhao et al. | Research on the reliability model of the water-entry process of air-launched vehicle under the simulation environment of numerical wave tank | |
| Barad et al. | Influence of chiral lattice on modal characteristics of structures |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |