CN111666700B - Laser excitation and fire impact equivalent method - Google Patents
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Abstract
The invention provides a laser excitation and fire impact equivalent method, and belongs to the field of ground simulation tests of spacecraft fire impact environments. Firstly, establishing a finite element model of a fire impact source; extracting an excitation function of the initiating explosive shock by using a finite element model; and constructing a single-plate force function debugging finite element model, loading an initiating explosive shock excitation function, simplifying the complex oscillation initiating explosive shock excitation function into a triangular pulse force function according to response equivalence, and finally carrying out proofreading equivalence on the pulse width and the amplitude of the triangular pulse force function and the laser shock excitation function. The invention can fully consider the complex coupling field in the initiating explosive device impact process, establish the equivalent criterion between laser excitation and initiating explosive device impact from the angle of an impact source, provide guidance for accurately simulating initiating explosive device impact by adopting laser excitation, and further provide test guarantee for the development of aerospace models in China.
Description
Technical Field
The invention relates to the field of ground simulation tests of spacecraft fire impact environments, in particular to a laser excitation and fire impact equivalent method.
Background
The impulse response of the initiating explosive device of the spacecraft (such as a satellite) is the transient impulse response acting on the structure caused by the detonation of the initiating explosive device in the working processes of satellite and rocket separation, component assembly expansion and the like, and has the characteristics of transient state, high frequency and high magnitude. The mechanical environment of the fire impact of the spacecraft is one of the most harsh mechanical environments experienced by the spacecraft in the whole life cycle, and the fire impact can cause fatal damage to precise electronic equipment containing crystal oscillators, brittle materials and the like on the spacecraft and even possibly cause early termination of a space mission.
In order to improve the working performance and reliability of the spacecraft, an initiating explosive impact ground simulation experiment is usually required to be carried out to check the service performance and the fire-resisting explosive impact capability of sensitive equipment on the spacecraft and reduce the influence of initiating explosive impact. A laser excitation type fire impact simulation experiment method is developed at present, and has an important effect on improving the fire impact simulation precision. However, in the conventional laser excitation type firer impact simulation, the impact response is controlled only in a trial and error mode, so that the manual experience is excessively relied on, and the randomness is strong. Therefore, it is necessary to establish an equivalent method of laser excitation and initiating explosive shock for guiding the selection of laser parameters required for simulating the initiating explosive shock environment, so as to realize accurate simulation of the initiating explosive shock environment.
Disclosure of Invention
The invention aims to fill the blank of the prior art and provides a laser excitation and fire impact equivalent method. The invention can fully consider the complex coupling field in the initiating explosive device impact process, establish the equivalent criterion between laser excitation and initiating explosive device impact from the angle of an impact source, provide guidance for accurately simulating initiating explosive device impact by adopting laser excitation, and further provide test guarantee for the development of aerospace models in China.
The invention provides a laser excitation and fire impact equivalent method which is characterized by comprising the following steps:
1) establishing a finite element model of the initiating explosive impact source; the finite element model includes: the method comprises the following steps that (1) a corresponding model of an initiating explosive device impact source adopted by an actual aircraft and a corresponding model of a connecting structure of the initiating explosive device impact source and the aircraft are adopted;
2) extracting a fire impact excitation function by using the finite element model established in the step 1);
3) randomly constructing a force function debugging finite element model; the force function debugging finite element model is of a rectangular plate structure, the rectangular plate structure is simulated by adopting a shell unit, and the rectangular plate structure comprises a central force function acting area and a response contrast area;
4) loading the firer impact excitation function extracted in the step 2) into the central force function action area of the force function debugging finite element model in the step 3), performing display dynamics calculation, extracting acceleration impact response at any node i in the response comparison area, and calculating an impact response spectrum SRS at the node i ；
5) According to the impact response spectrum equivalence, the fire impact excitation function is equivalent to a corresponding triangular pulse force function; the method comprises the following specific steps:
5-1) selecting any node i from a response comparison area of the force function debugging finite element model;
5-2) selecting an initial triangular pulse force function, wherein the triangular pulse force function is an isosceles triangle function and comprises two parameters of pulse width and amplitude; wherein, the initial pulse width is the maximum value of the pulse width in the waveform of the initiating explosive shock excitation function;
recording the initial pulse width as T1, and recording the minimum value of the pulse width in the waveform of the initiating explosive shock excitation function as T2;
5-3) taking T1 as the pulse width of the triangular pulse force function, and calculating the amplitude A1 corresponding to T1 by using the formula (1) as follows:
wherein F is an impact force function, lower corner marks Ori and Tri respectively represent a fire impact excitation function and a triangular pulse force function, and t 1 -t 0 Time interval of the initiating-shock excitation function, t 2 -t 0 Is a triangular pulse force function pulse width;
5-4) loading a triangular pulse force function with the pulse width of T1 and the amplitude of A1 to a central force function action area, extracting the acceleration impact response at the node i of the response contrast area selected in the step 5-1), and calculating an updated impact response spectrum at the node;
5-5) calculating the deviation between the impact response spectrum at the node i and the updated impact response spectrum at the node obtained in the step 5-4), and marking the deviation as sigma _ 1;
the calculation method of the deviation comprises the following steps:
where σ is the offset, SRS equi For the updated impulse response spectrum at node i,
represents SRS equi The amplitude of the impulse response spectrum at frequency f,
as SRS i Amplitude of the impulse response spectrum at frequency f, NThe total number of the selected frequency points;
5-6) taking T2 as the pulse width of the triangular pulse force function, and calculating the amplitude corresponding to T2 by using the formula (1) and recording as A2;
5-7) loading a triangular pulse force function with the pulse width of T2 and the amplitude of A2 to a central force function action area, extracting the acceleration impact response at the node i of the response contrast area selected in the step 5-1), and calculating an updated impact response spectrum at the node;
5-8) calculating the deviation between the impact response spectrum at the node i and the updated impact response spectrum at the node obtained in the step 5-7) by using the formula (2), and marking the deviation as sigma _ 2;
5-9) comparing the magnitudes of σ _1 and σ _2 and deciding:
if σ _1 is smaller than σ _2, T1 remains unchanged, and the pulse width mean value T3 of T1 and T2 is (T1+ T2)/2 as new T2, and the process proceeds to step 5-10);
if σ _1 is larger than σ _2, T2 remains unchanged, and the pulse width average value T3 of T1 and T2 is (T1+ T2)/2 as new T1, and the process proceeds to step 5-11);
if σ _1 is equal to σ _2, the pulse width mean value T3 of T1 and T2 is (T1+ T2)/2 as the final pulse width of the triangular pulse force function, the amplitude a3 corresponding to T3 is calculated by using the formula (1) as the final amplitude of the triangular pulse force function, the triangular pulse force function is adjusted, the adjusted triangular pulse force function is the equivalent function of the fire impact excitation function, and the process proceeds to step 6);
5-10) repeating the steps (5-6) to (5-9) until the sigma _1 is equal to the sigma _2, taking the mean value of the pulse widths T3 of T1 and T2 as (T1+ T2)/2 as the final pulse width of the triangular pulse force function, calculating the amplitude a3 corresponding to T3 by using the formula (1) as the final amplitude of the triangular pulse force function, finishing the adjustment of the triangular pulse force function, wherein the adjusted triangular pulse force function is the equivalent function of the initiating explosive shock excitation function, and entering the step 6);
5-11) repeating the steps 5-3) to 5-5) to obtain updated sigma _1, then repeating the step (5-9), until the sigma _1 is equal to the sigma _2, taking the mean value T3 of the pulse widths of T1 and T2 as (T1+ T2)/2 as the final pulse width of the triangular pulse force function, calculating the amplitude a3 corresponding to T3 as the final amplitude of the triangular pulse force function by using the formula (1), finishing the adjustment of the triangular pulse force function, wherein the adjusted triangular pulse force function is the equivalent function of the firer impact excitation function, and entering the step 6);
6) the pulse width of the triangular pulse force function is 3 times of that of the laser, and the laser pulse width is 1/3 of T3;
according to the following formula:
wherein P is laser impact peak pressure, rho proportionality coefficient, Z is acoustic impedance, I 0 Is the laser power density;
a3 was taken as P in formula (3), and the laser power density I was calculated 0 And finishing the equivalence.
The invention has the characteristics and beneficial effects that:
aiming at the defect that the existing laser excitation type initiating explosive device impact simulation experiment method lacks relevant theories and standard guidance, starting from an impact source, the invention establishes the quantitative equivalent relation between initiating explosive device parameters and laser parameters (single pulse energy, pulse width and the like) by adopting a finite element simulation mode, overcomes the defect that an initiating explosive device impact function is difficult to carry out experimental measurement, and can guide the selection of laser excitation parameters when initiating explosive device impact environment simulation experiment is carried out, thereby effectively reducing the cost and time cost brought by continuous trial and error in the simulation experiment process. The invention can be used in ground identification experiments of various types and multiple separation structures of missiles, rockets, spacecrafts and the like in the fields of military affairs and aerospace in China, and provides guarantee for the operation safety of aircrafts.
Drawings
FIG. 1 is an overall flow diagram of the process of the present invention;
FIG. 2 is a schematic diagram of a finite element model in an embodiment of the present invention;
FIG. 3 is a graph of force functions extracted using the model of FIG. 2;
FIG. 4 is a schematic diagram of a force function debugging finite element model according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of the force function equivalent triangular pulse function of FIG. 3;
FIG. 6 is a graph of the comparison result of the impulse response spectrum under the loading of the initiating explosive impulse function and the equivalent triangular impulse function.
Detailed Description
The invention provides a laser excitation and fire impact equivalent method, which is further described in detail by combining the drawings and specific embodiments. It should be apparent that the described embodiments are only some of the embodiments of the present invention, and not all of them. All other embodiments, which can be derived by a person skilled in the art from the described embodiments of the invention without inventive step, are within the scope of protection of the invention.
Unless defined otherwise, technical or scientific terms used herein shall have the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs.
The invention provides a laser excitation and fire impact equivalent method, the whole flow is shown as figure 1, the method comprises the following steps:
1) establishing a finite element model of the initiating explosive impact source;
establishing a finite element model of a fire impact source by using ANSYS/autodyn software based on Hydrocodes; the finite element model comprises a corresponding model of an initiating explosive device impact source adopted by an actual aircraft and a corresponding model of a connecting structure of the initiating explosive device impact source and the aircraft;
in this embodiment, the finite element model structure is shown in fig. 2; fig. 2 is a schematic diagram of a satellite-rocket joint of a spacecraft, which is used for mounting a firer impact source and transmitting impact to a satellite, wherein 1 is a load (for simulating the satellite), 2 is a connecting part, 3 is a support plate, and 4 is a separation nut;
the connecting part is used for simulating an interface between a satellite and a carrier rocket (namely a connecting structure between a firer impact source and an aircraft), and two ends of the connecting part are respectively connected with the support plate and a load.
The bracket plate is a part of the carrier rocket and is used for screwing the separation nut so as to facilitate modeling;
the finite element model further comprises a separation nut, the separation nut is connected with the support plate in a joint mode, and the separation nut is used for simulating a fire impact source. For the modeling of the split nut reference can be made to the paper: X.X.Wang, Z.Y.Q, J.F.Ding, F.L.Chu, Finite element modification and pyroshock response analysis of segmentation, AEROSP.SCI.TECHNOL.68(2017) 380-.
2) Extracting a fire impact excitation function by using the finite element model established in the step 1);
in this embodiment, the internal force of the star-arrow connection unit with the cross section shown in fig. 3 is extracted in Autodyn, and the resultant force in the Z direction (interface normal direction) is obtained as the function of the firer impact excitation.
3) Constructing a force function debugging finite element model;
and randomly constructing a force function debugging finite element model. The force function debugging finite element model is of a rectangular plate structure (modeling is carried out by adopting Ansys/Autodyn software, the rectangular plate is of a thin plate structure, the length and the width are more than or equal to ten times of the thickness, and the size of the rectangular plate adopted in the embodiment is 700mm multiplied by 500mm multiplied by 2 mm); simulating the rectangular plate structure by adopting a shell unit; the rectangular plate structure includes a central force function affected zone and a responsive contrast zone. (the force function debugging finite element model of this embodiment is shown in fig. 4, the central force function action area is located at the geometric center of the plate, and is a circular area with a radius of 2-10 mm, the response contrast area is an area of the rectangular plate except for the central force function action area, and the central force function action area used in this embodiment has a radius of 2 mm);
4) loading the firer impact excitation function extracted in the step 2) into the central force function action area of the force function debugging finite element model in the step 3), performing display dynamics calculation, extracting acceleration impact response at any node i in the response comparison area, and calculating an impact response spectrum SRS at the node i 。
5) According to the impact response spectrum equivalence, the complex oscillation firer impact excitation function is equivalent to a corresponding triangular pulse force function; the method comprises the following specific steps:
5-1) selecting any node i from a response comparison area of the force function debugging finite element model;
5-2) selecting an initial triangular pulse force function, wherein the triangular pulse force function is an isosceles triangle function and comprises two parameters of pulse width and amplitude. The initial pulse width is the maximum value of the pulse width in the waveform of the initiating explosive shock excitation function, and is set to 230us in the embodiment.
Recording the initial pulse width as T1, and recording the minimum value of the pulse width in the waveform of the initiating explosive shock excitation function as T2;
5-3) taking T1 as the pulse width of the triangular pulse force function, calculating the amplitude A1 corresponding to T1 by using the formula (1) according to the integral equality of the force function to time, wherein the expression is as follows:
wherein F is an impact force function, lower corner marks Ori and Tri respectively represent a fire impact excitation function and a triangular pulse force function, and t 1 -t 0 Time interval of the initiating-shock excitation function, t 2 -t 0 Is a triangular pulse force function pulse width;
when T1 is the initial pulse width, a1 is the initial amplitude, and the initial amplitude is set to 0.5 in this embodiment.
5-4) loading a triangular pulse force function with the pulse width of T1 and the amplitude of A1 to a central force function action area, extracting the acceleration impact response at the node i of the response contrast area selected in the step 5-1), and calculating an updated impact response spectrum at the node;
5-5) calculating the deviation of the impact response spectrum at the node i and the updated impact response spectrum at the node corresponding to the pulse width T1 and the amplitude A1, and marking as sigma _ 1;
the deviation calculation method comprises the following steps:
where σ is the offset, SRS equi For the updated impulse response spectrum at node i,
and
are respectively SRS equi And SRS i The amplitude of the impulse response spectrum at frequency f, N, is the total number of selected frequency points (in this embodiment f, 1/6 octaves are used to set the frequency interval).
5-6) taking T2 as the pulse width of the triangular pulse force function, and calculating the amplitude corresponding to T2 by using the formula (1) and recording as A2;
5-7) loading a triangular pulse force function with the pulse width of T2 and the amplitude of A2 to a central force function action area, extracting the acceleration impact response at the node i of the response contrast area selected in the step 5-1), and calculating an updated impact response spectrum at the node;
5-8) calculating the deviation of the impact response spectrum at the node i and the updated impact response spectrum corresponding to the pulse width T2 and the amplitude A2 by using the formula (2) and recording as sigma _ 2;
5-9) comparing the magnitudes of σ _1 and σ _2 and deciding:
if σ _1 is smaller than σ _2, T1 remains unchanged, and the pulse width mean value T3 of T1 and T2 is (T1+ T2)/2 as new T2, and the process proceeds to step 5-10);
if σ _1 is larger than σ _2, T2 remains unchanged, and the pulse width average value T3 of T1 and T2 is (T1+ T2)/2 as new T1, and the process proceeds to step 5-11);
if σ _1 is equal to σ _2, the pulse width mean value T3 of T1 and T2 is (T1+ T2)/2 as the final pulse width of the triangular pulse force function, the amplitude a3 corresponding to T3 is calculated by using the formula (1) as the final amplitude of the triangular pulse force function, the triangular pulse force function is adjusted, the adjusted triangular pulse force function is the equivalent function of the fire impact excitation function, and the process proceeds to step 6);
5-10) repeating the steps (5-6) to (5-9) until σ _1 is equal to σ _2, then, taking the mean value T3 of the pulse widths of T1 and T2 as (T1+ T2)/2 as the final pulse width of the triangular pulse force function, calculating the amplitude a3 corresponding to T3 as the final amplitude of the triangular pulse force function by using the formula (1), finishing the adjustment of the triangular pulse force function, wherein the adjusted triangular pulse force function is the equivalent function of the initiating explosive shock excitation function, and entering step 6);
5-11) repeating the steps 5-3) to 5-5) to obtain an updated sigma _1, then repeating the step (5-9) until the sigma _1 is equal to the sigma _2, taking the mean value of the pulse widths T3 of T1 and T2 as (T1+ T2)/2 as the final pulse width of the triangular pulse force function, calculating the amplitude a3 corresponding to T3 by using the formula (1) as the final amplitude of the triangular pulse force function, finishing the adjustment of the triangular pulse force function, wherein the adjusted triangular pulse force function is the equivalent function of the initiating impulse excitation function, and entering the step 6);
the invention adjusts the pulse width and the amplitude of the triangular pulse force function until the deviation sigma is stable and unchanged, then the triangular pulse force function is adjusted, and the adjusted triangular pulse force function is the equivalent function of the initiating explosive shock excitation function.
As shown in fig. 5, the equivalent triangular pulse force function finally obtained in this embodiment is obtained, and the equivalent triangular pulse force function and the fire impact force function are respectively substituted into the force function debugging finite element model, the response at any node 3741 in the response comparison area is extracted, and the impact response spectrum is calculated, and the comparison condition is shown in fig. 6, which shows that the two functions have better consistency.
6) The pulse width according to the triangular pulse force function is 3 times of the laser pulse width, and the laser pulse width is 1/3 of T3;
the amplitude of the triangular pulse force function is based on a laser shock semi-empirical formula:
wherein P is the laser shock peak pressure, rho proportionality coefficient (constant), Z is acoustic impedance (acoustic impedance of material, obtained by table lookup according to specific material), I is 0 Is the laser power density; a3 was taken as P in formula (3), and the laser power density I was calculated 0 And (5) completing the equivalence.
Claims (1)
1. A laser excitation and fire impact equivalent method is characterized by comprising the following steps:
1) establishing a finite element model of the initiating explosive impact source; the finite element model includes: the method comprises the following steps that a corresponding model of an initiating explosive device impact source adopted by an actual aircraft and a corresponding model of a connecting structure of the initiating explosive device impact source and the aircraft are obtained;
2) extracting a fire impact excitation function by using the finite element model established in the step 1);
3) randomly constructing a force function debugging finite element model; the force function debugging finite element model is of a rectangular plate structure, the rectangular plate structure is simulated by adopting a shell unit, and the rectangular plate structure comprises a central force function acting area and a response contrast area;
4) loading the firer impact excitation function extracted in the step 2) into the central force function action area of the force function debugging finite element model in the step 3), performing display dynamics calculation, extracting acceleration impact response at any node i in the response comparison area, and calculating an impact response spectrum SRS at the node i ；
5) According to the impact response spectrum equivalence, the initiating explosive impact excitation function is equivalent to a corresponding triangular pulse force function; the method comprises the following specific steps:
5-1) selecting any node i from a response comparison area of a force function debugging finite element model;
5-2) selecting an initial triangular pulse force function, wherein the triangular pulse force function is an isosceles triangle function and comprises two parameters of pulse width and amplitude; the initial pulse width is the maximum value of the pulse width in the waveform of the initiating explosive shock excitation function;
recording the initial pulse width as T1, and recording the minimum value of the pulse width in the waveform of the initiating explosive shock excitation function as T2;
5-3) taking the T1 as the pulse width of the triangular pulse force function, calculating the amplitude A1 corresponding to the T1 by using the formula (1) as follows:
wherein F is an impact force function, lower corner marks Ori and Tri respectively represent an initiating explosive impact excitation function and a triangular pulse force function, and t 1 -t 0 Time interval of the initiating-shock excitation function, t 2 -t 0 Is a triangular pulse force function pulse width;
5-4) loading a triangular pulse force function with the pulse width of T1 and the amplitude of A1 to a central force function action area, extracting the acceleration impact response at the node i of the response contrast area selected in the step 5-1), and calculating an updated impact response spectrum at the node;
5-5) calculating the deviation between the impact response spectrum at the node i and the updated impact response spectrum at the node obtained in the step 5-4), and recording the deviation as sigma _ 1;
the calculation method of the deviation comprises the following steps:
where σ is the offset, SRS equi For the updated impulse response spectrum at node i,
represents SRS equi The amplitude of the impulse response spectrum at frequency f,
as SRS i The amplitude of the impulse response spectrum at the frequency f, N being the total number of the selected frequency points;
5-6) taking T2 as the pulse width of the triangular pulse force function, and calculating the amplitude corresponding to T2 by using the formula (1) and recording as A2;
5-7) loading a triangular pulse force function with the pulse width of T2 and the amplitude of A2 to a central force function action area, extracting the acceleration impact response at the node i of the response contrast area selected in the step 5-1), and calculating an updated impact response spectrum at the node;
5-8) calculating the deviation between the impact response spectrum at the node i and the updated impact response spectrum at the node obtained in the step 5-7) by using the formula (2), and marking the deviation as sigma _ 2;
5-9) comparing the magnitudes of σ _1 and σ _2 and deciding:
if σ _1 is smaller than σ _2, T1 remains unchanged, and the pulse width mean value T3 of T1 and T2 is (T1+ T2)/2 as new T2, and the process proceeds to step 5-10);
if σ _1 is larger than σ _2, T2 remains unchanged, and the pulse width average value T3 of T1 and T2 is (T1+ T2)/2 as new T1, and the process proceeds to step 5-11);
if σ _1 is equal to σ _2, the mean value T3 of the pulse widths of T1 and T2 is (T1+ T2)/2 as the final pulse width of the triangular pulse force function, the amplitude a3 corresponding to T3 is calculated by using the formula (1) as the final amplitude of the triangular pulse force function, the triangular pulse force function is adjusted, the adjusted triangular pulse force function is the equivalent function of the fire impact excitation function, and the process goes to step 6);
5-10) repeating the steps (5-6) to (5-9) until σ _1 is equal to σ _2, then, taking the mean value T3 of the pulse widths of T1 and T2 as (T1+ T2)/2 as the final pulse width of the triangular pulse force function, calculating the amplitude a3 corresponding to T3 as the final amplitude of the triangular pulse force function by using the formula (1), finishing the adjustment of the triangular pulse force function, wherein the adjusted triangular pulse force function is the equivalent function of the initiating explosive shock excitation function, and entering step 6);
5-11) repeating the steps 5-3) to 5-5) to obtain updated sigma _1, then repeating the step (5-9), until the sigma _1 is equal to the sigma _2, taking the mean value T3 of the pulse widths of T1 and T2 as (T1+ T2)/2 as the final pulse width of the triangular pulse force function, calculating the amplitude a3 corresponding to T3 as the final amplitude of the triangular pulse force function by using the formula (1), finishing the adjustment of the triangular pulse force function, wherein the adjusted triangular pulse force function is the equivalent function of the firer impact excitation function, and entering the step 6);
6) the pulse width of the triangular pulse force function is 3 times of that of the laser, and the laser pulse width is 1/3 of T3;
according to the following formula:
wherein P is the laser impact peak pressure, rho proportionality coefficient, Z is acoustic impedance, I 0 Is the laser power density;
a3 was taken as P in formula (3), and the laser power density I was calculated 0 And finishing the equivalence.
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