CN105760613A - Load prediction method for pyrotechnic impact source of spacecraft - Google Patents
Load prediction method for pyrotechnic impact source of spacecraft Download PDFInfo
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Abstract
The invention discloses a load prediction method for a pyrotechnic impact source of a spacecraft. The details of explosive explosion, initiating explosive device rupture and explosive stress wave propagation in an initiating explosive device can be simulated; the coupling effect caused by initiating explosive device explosion in structure can be well processed, so that the vibration source characteristic is analyzed; effective extraction on a vibration source force function is a reasonable way for obtaining a pyrotechnic impact vibration source function. According to the method, a feasible way is provided for determination of the pyrotechnic impact source function of the spacecraft; and a foundation is laid for solving the problem of response prediction of the pyrotechnic impact of the spacecraft from engineering.
Description
Technical field
The invention belongs to spacecraft dynamics shock response technical field, be specifically related to a kind of spacecraft firer's impulse source load predicting method.
Background technology
Spacecraft firer's shock environment refers to that priming system on spacecraft detonates the impact loading produced response on main force support structure, and this response constitutes the ballistics environment of satellite borne equipment.Spacecraft firer's ballistics environment is one of mechanical environment the harshest of experience in Spacecraft Launch and operation on orbit process, instrument and equipment containing shock-sensitive components and parts can be caused fatal damage by material stress ripple and mesomerism response that priming system blast causes, thus causing the failure of space mission.
The quantitative description of firer's impulse source is the premise that analytical model for application method and numerical method carry out firer's shock environment indication, is the calculating input of shock response indication analytical model.Spacecraft firer's impact process comprises the physical phenomenon of complexity, its high frequency, instantaneous, peak value feature so that Explosive Shock Loading is difficult to measure；Coupling between High Temperature High Pressure load and priming system structure and complicated attachment structure that priming system blast produces makes Explosive Shock Loading be difficult to calculate.Therefore, the determination of firer's shock loading is always up a difficult problem in the indication of spacecraft firer's ballistics environment.Describing mode for firer's impulse source mainly has three kinds at present.First is from the view point of energy, manages the energy finding impulse source to discharge.The method energy similarity criterion according to Explosive separation impulse source, the ratio conversion of the gross energy that the shock response spectrum in all frequencies discharges by two different Fire load.Second is load using the near field shock response acceleration measured as shock loading.Acceleration loads the position generally structurally closing on priming system as far as possible and installs accelerometer, measures the acceleration responsive of near-field structure, in this, as load source.But acceleration responsive is applied as load, theoretically and unreasonable.Domestic current research shows, adopts near-field acceleration to load the calculating effect carrying out environment indication unsatisfactory.3rd is that force function loads.The impulsive force load produced in blast impulse structure around is the most direct load source.The power load that blast impulse produces cannot directly be measured, and a kind of method is anti-pushing manipulation, makes the tentative calculation needing to be repeatedly performed different parameters, different wave in this way, and repeatedly tentative calculation is still difficult to obtain real loading force function.Another kind of method is the process of the fluid and structural simulation process simulation priming system blasts such as application Hydrocodes, obtain firer's impulsive force function, but the coupling due to the complexity of spacecraft structure and explosive source and spacecraft structure, can priming system blast force function of effect on spacecraft structure pass through numerical computations and obtain approximate solution, and how to apply Hydrocodes and carry out the decomposition of spacecraft vibration source structure, effectively model and force function extraction etc. is all open question.
Summary of the invention
In view of this, it is an object of the invention to provide a kind of spacecraft firer's impulse source load predicting method, by the modeling of spacecraft firer's impulse source and analysis, solving the problem that in the indication of spacecraft firer's ballistics environment, shock loading cannot be determined.
A kind of spacecraft firer's impulse source load predicting method, the structure of described spacecraft includes vibration source system structure and spacecraft main structure, vibration source system structure includes priming system structure and attachment structure, described priming system structure is arranged in described spacecraft main structure by attachment structure, and object of study during priming system structural blast is the near-field structure in vibration source system structure and spacecraft main structure；Described method comprises the steps:
Step one, determine the parting surface of spacecraft: the progression n of described attachment structure represents, after priming system structural blast, wherein front x level separates from spacecraft main structure in company with priming system structural blast, remaining n-x level is retained in spacecraft main structure, then the interface between xth level and (x+1)th level is parting surface；Wherein the span of x is 1 to n；
Step 2, described vibration source system structure and near-field structure are carried out finite element modeling, particularly as follows:
S1, set up the FEM mesh of vibration source system structure and near-field structure；
S2, load according to load after the material character that shows of each structure and deformation extent, to each structure definition material constitutive model in vibration source system structure and near-field structure；
S3, material properties according to each structure in vibration source system structure and near-field structure, to structure definition unit algorithm；
S4, vibration source system structure and near-field structure FEM (finite element) model are defined the external applied load and boundary constraint that meet reality；
S5, the contact surface of each structure in vibration source system structure and near-field structure is defined Contact Algorithm；
The FEM (finite element) model that step 3, employing Hydrocodes program solution step 2 are set up, at described parting surface place extraction force function, it is achieved the indication to firer's impulse source load.
There is advantages that
The present invention can simulate the details that explosive charge in priming system, priming system fracture and Explosive stress wave are propagated, the coupling that priming system blast structurally causes can be processed well, thus analyzing vibration source characteristic, vibration source force function is effectively extracted, is obtain firer to impact the reasonable approach of vibration source function theoretically.The determination that the method is spacecraft firer's impulse source function proposes a kind of feasible approach, and the response indication problem impacted for solving spacecraft firer on engineering is laid a good foundation.
Accompanying drawing explanation
Fig. 1 is the system structure schematic diagram of the present invention；
The parting surface that Fig. 2 is the present invention chooses schematic diagram；
The point type that Fig. 3 is the present invention separates the division of firer's impulse source analytical model system；
" vibration source system near-field structure " integration computational geometry model that Fig. 4 (a) is the present invention；Fig. 4 (b)
Grid model for Fig. 4 (a)；
Fig. 5 is internal motion and the releasing process of the separation nut of the present invention；
Fig. 6 A～6C is the system parting surface force function curve chart of the present invention.
Detailed description of the invention
Develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
Firer impact the complexity of vibration source analysis include priming system blast analogue complexity and with two aspects of coupling of attachment structure.Priming system blast process comprises two links of response of explosive charge and metal material impact loading, instantaneous in priming system blast, explosive is in limited space (in metal bolts shell) and discharges big energy in the extremely short time, the high temperature produced, reaction under high pressure product extrudes rapidly surrounding medium (metal material), gas and detonation product that metal material is expanded rapidly stretch, material behavior changes, plastic zone it is stretched to rapidly from elastic region, even can enter the state of nearly fluid, therefore the simulation of priming system blast process is the solid coupled problem of a complicated non-linear flow.
Firer is impacted to the description of vibration source, being analyzed being inadequate to a priming system merely, priming system blast produces stress wave in near-field structure, and stress wave is propagated in the material, reflect at material interface, transmission, these mechanical behaviors all rely on the material of structure, shape and connected mode.That is: the mechanical behavior that firer impacts couples with attachment structure and near-field structure.The different designs of priming system, the material of attachment structure, shape and connected mode all will directly affect structural response and interstructural interaction.
A kind of spacecraft firer's impulse source modeling and the method for analysis, that is: Rational choice system parting surface on the basis that the separation process of spacecraft is analyzed, with " priming system attachment structure " for unitary construction " vibration source system " model, jointly set up integration together with " near-field structure " and calculate FEM (finite element) model (see Fig. 1), application Hydrocodes program carries out including the integrated numerical analysis of priming system blast and near field stress wave propagation, and at vibration source system and near-field structure joint face place extraction force function.
The key issue of application the method is vibration source system and the division of near-field structure and choosing of parting surface.This process needs the separation process of spacecraft is analyzed, and chooses real energy separation face, it may be assumed that while ensureing that spacecraft structure to be asked is complete as far as possible, chooses, in real structure parting surface, the interface that focused energy finally separates with spacecraft.Assuming that satellite main structure is spacecraft to be asked, n level attachment structure (such as Fig. 2) is there is from blasting bolt to satellite main structure, " attachment structure 1 ", " attachment structure 2 ", ... " attachment structure n ", in t, bolt separates with " attachment structure 1 ", the t+1 moment, " attachment structure 1 " and " attachment structure 2 separates ", ..., in the t+n moment, " attachment structure n " separates with satellite main structure.If the structure ignored below is all delivered to the energy of satellite main structure by any flash trapping stage face before choosing " attachment structure n " and satellite main structure as system parting surface.As chosen the t+i moment, " attachment structure i " and " attachment structure i+1 " are as system parting surface, then after the t+i moment, " attachment structure i+1 " ... " attachment structure n " also has energy and continue with in the middle of satellite main structure, then selecting such parting surface will be all inaccurate as the force function that system parting surface extracts.Therefore the parting surface that must choose t+n moment, " attachment structure n " and satellite main structure is system parting surface.Judging whether " attachment structure n " is included in the middle of satellite main structure, depend on whether separating between " attachment structure n " with satellite main structure in Explosive separation process, if do not separated, then " attachment structure n " belongs to satellite main structure.
In aforementioned expression, " near-field structure " is the first order minor structure or son assembling that in satellite main structure, distance vibration source is nearest.
Summing up, the application of the method must comply with following principle:
(1) system parting surface must be real structure parting surface；
(2) system parting surface must be separate the interface that last moment focused energy separates with spacecraft, is the parting surface of afterbody attachment structure and satellite main structure in general；
(3) solving of this process by Hydrocodes program, must be undertaken explicit finite-element accurately and solve.
In general, so modeling ensure that the vibration source force function extracted within the calculating time comprises complete surge waveform, and has clear and definite physical significance.
A kind of spacecraft firer's impulse source load predicting method that the present invention proposes to be embodied as step as follows:
Determine complete spacecraft structure to be asked.
Determine that namely complete spacecraft structure to be asked determines the object of study of problem, complete spacecraft structure to be asked includes the structure of spacecraft and includes vibration source system structure and spacecraft main structure, vibration source system structure includes priming system structure and attachment structure, described priming system structure is arranged in described spacecraft main structure by attachment structure, and object of study during priming system structural blast is the near-field structure in spacecraft main structure；Spacecraft main structure generally requires not separate between each assembling minor structure in Explosive separation process, is an entirety.
Dividing system, defines the scope of " vibration source system " and near-field structure, namely determines system parting surface.
System parting surface must be real structure parting surface；System parting surface must be separate the interface that last moment focused energy separates with spacecraft.The progression n of attachment structure represents, after priming system structural blast, before wherein, x level separates from spacecraft main structure in company with priming system structural blast, and remaining n-x level is retained in spacecraft main structure, then before, the interface between x level and (x+1)th level is parting surface；Wherein the span of x is 1 to n, and its concrete value is determined according to spacecraft practical situation, and x+1 level and above any one-level do not separate with main structure；It is likely to separate between x level and following any one-level two successive stages attachment structure.It is the parting surface of afterbody attachment structure and satellite main structure in general.Near-field structure is the first order structure that in spacecraft main structure, distance vibration source is nearest.
Carry out spacecraft and include the finite element modeling of vibration source system and near-field structure.
Finite element modeling is the discretization process to physical space, and this process has several concrete steps:
1, by including the vibration source system structure of blasting bolt internal structure, near-field structure carries out FEM meshing, due to the high frequency finite element analysis sensitivity to details, this FEM (finite element) model requires to comprise CONSTRUCTED SPECIFICATION, such as boss, groove, borehole etc., annexation to be consistent with actual as far as possible；
2, the deformation size of each structure after loading according to load, to each structure definition material constitutive model in vibration source system structure and near-field structure；For showing as the material of solid property in loading procedure, stress amplitude exceedes the need definition Elastic-plastic Constitutive of Materials Yield Limit, and stress amplitude is less than the definition elastic constitutive model of Materials Yield Limit；For showing as the material of fluid behaviour in loading procedure, need to defining fluid state equation, such as air, explosive, and some under high pressure show as the solid material of fluid behaviour.
3, the material properties according to each structure in vibration source system structure and near-field structure, the unit algorithm suitable to construction unit definition, explosive for air and priming system defines the euler algorithm being suitable for fluid, all the other solid structures are defined Lagrangian Arithmetic, between solid material and fluent material, describes effect each other with fluid-structure coupling computation；
4, vibration source system structure and near-field structure FEM (finite element) model are defined the external applied load and boundary constraint that meet reality, in order to describe the effect of bolt pretightening, structure boundary etc.；
5, the contact surface of each structure in vibration source system structure and near-field structure is defined Contact Algorithm, to there being collision each other, have definition sliding friction contact between the structure of relative sliding, be connected contact to having definition between bolted structure.
Finally, the FEM (finite element) model that Hydrocodes program solution step 2 is set up is adopted, at described parting surface place extraction force function, it is achieved the indication to firer's impulse source load.
The Hydrocodes program that this process can be write with oneself, it is also possible to solve with commercial Hydrocodes softwares such as LS-Dyna.This class method can extract the contact force function of structure interface.The contact force function of the system parting surface defined before extracting in result of calculation is the loading force function of firer's impulse source.
Embodiment one:
The complete spacecraft structure to be asked adopting point type satellite and the rocket isolating construction includes several parts such as reverse pushing-type Explosive separation nut, the delivery satellite support of side, satellite joint and spacecraft main structure.
Point type separation spacecraft structure is carried out system division (see Fig. 3) for the definition of vibration source system and near-field structure by the foundation present invention.In the Explosive separation process of point type isolating construction, along with the detonating of Explosive separation nut, unlock, the support of delivery side separates with satellite joint, and separation nut head comes off with mother space vehicle support, and the contact surface of satellite support and satellite joint is real energy separation face.Therefore the contact surface of prong frame Yu satellite joint is set as system parting surface, mother space vehicle support and Explosive separation nipple heads are divided into vibration source system as entirety, satellite joint is the first order minor structure that in satellite main structure, distance vibration source is nearest, therefore is modeled analyzing as near-field structure using satellite joint.
" vibration source system-near-field structure " Integrated Model is set up based on LS-DYNA.Geometric model comprises multiple links such as air, explosive, each internals of reverse pushing-type separation nut, bolt, satellite joint, rocket joint (mother space vehicle support).Satellite joint and rocket joint are reduced to the disk with actual condition of equivalent thickness, and set up local air model (see Fig. 4) in separation nut head zone.TRGRID software is adopted to set up full hexahedron FEM mesh, air and explosive unit adopt euler algorithm, all the other construction units all adopt Lagrangian Arithmetic, processed by fluid-structure coupling computation and interact between Eulerian mesh unit and Lagrangian mesh unit.Material model, satellite joint, rocket joint, owing to there is not moderate finite deformation, adopt linear elasticity Constitutive modeling；For it may happen that friction and the piston of moderate finite deformation, bolt adopt Elastic-plastic Constitutive to describe repeatedly；All the other structures are main based on rigid motion in separation nut explodes releasing process, and its stress-strain state is not the object of major concern, adopt body material Constitutive modeling for saving the calculating time.Air empty material expression, explosive material parameter and JWL state equation parameter adopt general T NT explosive parameter.
Reverse pushing-type separation nut internal explosion, motion, unblock and system parting surface separation overall process (see Fig. 5) finally by LS-DYNA solver calculating simulation, obtain the force function (see Fig. 6) in tri-directions of X, Y, Z on satellite and the rocket parting surface.
Above simulated example explanation, application " vibration source system near-field structure " integrated modelling and analysis method can carry out including the integrated numerical analysis of priming system blast and near field stress wave propagation, and extract, with near-field structure joint face place, the force function comprising complete waveform in vibration source system, thus lay the foundation for solving the problem that in the indication of spacecraft firer's ballistics environment, shock loading cannot be determined.
In sum, these are only presently preferred embodiments of the present invention, be not intended to limit protection scope of the present invention.All within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (1)
1. spacecraft firer's impulse source load predicting method, the structure of described spacecraft includes vibration source system structure and spacecraft main structure, vibration source system structure includes priming system structure and attachment structure, described priming system structure is arranged in described spacecraft main structure by attachment structure, and object of study during priming system structural blast is the near-field structure in vibration source system structure and spacecraft main structure；It is characterized in that, described method comprises the steps:
Step one, determine the parting surface of spacecraft: the progression n of described attachment structure represents, after priming system structural blast, wherein front x level separates from spacecraft main structure in company with priming system structural blast, remaining n-x level is retained in spacecraft main structure, then the interface between xth level and (x+1)th level is parting surface；Wherein the span of x is 1 to n；
Step 2, described vibration source system structure and near-field structure are carried out finite element modeling, particularly as follows:
S1, set up the FEM mesh of vibration source system structure and near-field structure；
S2, load according to load after the material character that shows of each structure and deformation extent, to each structure definition material constitutive model in vibration source system structure and near-field structure；
S3, material properties according to each structure in vibration source system structure and near-field structure, to structure definition unit algorithm；
S4, vibration source system structure and near-field structure FEM (finite element) model are defined the external applied load and boundary constraint that meet reality；
S5, the contact surface of each structure in vibration source system structure and near-field structure is defined Contact Algorithm；
The FEM (finite element) model that step 3, employing Hydrocodes program solution step 2 are set up, at described parting surface place extraction force function, it is achieved the indication to firer's impulse source load.
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| CN109002635A (en) * | 2018-08-02 | 2018-12-14 | 东南大学 | A kind of bolt connection considering connected nonlinearity |
| CN109211512A (en) * | 2018-09-03 | 2019-01-15 | 哈尔滨工业大学 | A kind of firer's shock environment analogue means |
| CN110083990A (en) * | 2019-05-28 | 2019-08-02 | 清华大学 | The mechanics shock-sensitive characteristic Simulation method of piezoresistive electrodes double layer capacitor |
| CN110160894A (en) * | 2018-04-16 | 2019-08-23 | 北京机电工程研究所 | Scragging system |
| CN110285176A (en) * | 2019-07-19 | 2019-09-27 | 厦门大学 | Firer based on anti-wavelength characteristic separates drop percussion mechanism and its preparation process |
| CN111666700A (en) * | 2020-05-12 | 2020-09-15 | 清华大学 | Laser excitation and fire impact equivalent method |
| CN114818144A (en) * | 2022-05-12 | 2022-07-29 | 清华大学 | Simulation calculation and analysis method for fire impact source |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110160894A (en) * | 2018-04-16 | 2019-08-23 | 北京机电工程研究所 | Scragging system |
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| CN110083990A (en) * | 2019-05-28 | 2019-08-02 | 清华大学 | The mechanics shock-sensitive characteristic Simulation method of piezoresistive electrodes double layer capacitor |
| CN110285176A (en) * | 2019-07-19 | 2019-09-27 | 厦门大学 | Firer based on anti-wavelength characteristic separates drop percussion mechanism and its preparation process |
| CN111666700A (en) * | 2020-05-12 | 2020-09-15 | 清华大学 | Laser excitation and fire impact equivalent method |
| CN114818144A (en) * | 2022-05-12 | 2022-07-29 | 清华大学 | Simulation calculation and analysis method for fire impact source |
| CN114818144B (en) * | 2022-05-12 | 2023-03-24 | 清华大学 | Simulation calculation and analysis method for fire impact source |
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