CN113378292B - Method for obtaining slope and deviation of rocket modal shape through cabin test - Google Patents
Method for obtaining slope and deviation of rocket modal shape through cabin test Download PDFInfo
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Abstract
The invention relates to a method for acquiring a rocket modal shape slope and deviation thereof through a cabin test, belongs to the technical field of rocket dynamics characteristic simulation and test, and mainly relates to a carrier rocket modal shape slope test and simulation calculation method. The invention superimposes the deviation of the cabin test and the simulation calculation result and the deviation of the local installation position, namely the deviation can be given in percentage form as the deviation of the vibration mode slope standard value. And the method of cabin test is adopted to conduct optimization of the mounting position of the inertial device, and the inertial device position selection is not needed through a full rocket mode test.
Description
Technical Field
The invention relates to a method for acquiring a rocket modal shape slope and deviation thereof through a cabin test, belongs to the technical field of rocket dynamics characteristic simulation and test, and mainly relates to a carrier rocket modal shape slope test and simulation calculation method.
Background
In the rocket test, the vibration mode slope response of the position of the inertial device in the bending mode needs to be measured so as to be optimal for the installation position, and along with the improvement of the design level, the dynamic characteristic data of the rocket can be obtained by adopting a substructure test, so that the local vibration mode slope test is also carried out by adopting a substructure or cabin level test. The invention adopts a cabin test method to obtain the slope of the mode shape of the rocket and the deviation thereof.
Disclosure of Invention
The technical solution of the invention is as follows: the method for acquiring the slope and the deviation of the rocket mode shape by the cabin test is provided, and the slope and the deviation of the rocket mode shape are acquired by the cabin test.
The technical scheme of the invention is as follows:
A method for obtaining a rocket mode shape slope and deviation thereof through a cabin segment test, the method comprising the steps of:
step one, obtaining a vibration mode slope test result a of an inertial device installation cabin;
The method for acquiring the vibration mode slope test result of the inertial device installation cabin section comprises the following steps: carrying out a modal test on the inertial device installation cabin to obtain modal frequency and vibration mode of the inertial device installation cabin and vibration mode slope test results of a plurality of preselected installation positions of the inertial device;
The preselected installation position of the inertial device is not required to be within the range of 0.2D from the upper boundary and the lower boundary (D is the diameter of an installation cabin section of the inertial device), and for a cabin section with h/D being more than 1.5 (h is the height of the cabin section), a modal test in three states of free two ends, free top end of a bottom end fixing support and cover plate constraint is required to be carried out;
the method comprises the steps that a free state test of the top end of a bottom support is carried out at the two ends, the free state test of the top end of the bottom support is carried out at the two ends, the modal frequency and the vibration mode are required to be measured, a state test of the top end of the bottom support and the cover plate is required to be carried out, meanwhile, the mass of the cover plate can be adjusted, and a vibration mode slope test result a of an inertial device installation cabin under various states is obtained;
For the cabin section with h/D smaller than 1, a mode test with free ends and free top end support is required, wherein the mode frequency and the vibration mode are required to be measured in the free state test of the two ends, the mode frequency, the vibration mode and the vibration mode slope are required to be measured in the free state test of the top end support, and the measurement result of the respiratory mode slope of the central symmetry shape of the free state of the top end support is a;
for the cabin section with h/D between 1 and 1.5, the test can be carried out according to the state of less than 1 or more than 1 and the result is obtained;
step two, obtaining a simulation result b of the vibration mode slope of the inertial device installation cabin;
The simulation result acquisition method of the vibration mode slope of the inertial device installation cabin section comprises the following steps: firstly, carrying out fine modeling on an inertial device installation cabin section, wherein the fine modeling means that a skin of the cabin section is modeled by a shell unit, a stringer and a ring frame are modeled by a beam unit, and instrument equipment is modeled by a mass unit and is connected with nodes of the skin and the stringer by multi-point constraint; secondly, carrying out modal calculation on the conditions that the h/D is smaller than 1 and larger than 1.5, 1 and 1.5 according to the modal test state in the first step, correcting the cabin section model according to the frequency and the vibration mode measurement result of the modal test in the first step, correcting the rigidities of the skin and the stringers, wherein the deviation between the model modal frequency calculation result and the test result after correction is within 20% in the first 3 steps, and finally calculating according to the cabin section vibration mode slope measurement test state to obtain a simulation result b of the cabin section vibration mode slope;
Thirdly, obtaining a first partial deviation m= (a-b)/b of the vibration mode slope of 100% according to the cabin vibration mode slope test result a and the simulation result b obtained in the first step and the second step;
Fourthly, replacing the cabin section of the inertial device in the whole rocket model with the corrected cabin section refined model in the second step, and obtaining a vibration mode slope distribution diagram of the cabin section under a whole rocket first-order bending mode through simulation calculation, wherein a simulation calculation result of a preselected position of the inertial device is marked as c, a range of longitudinal distance of not less than 0.5m and circumferential angle of not less than 5 degrees is selected for evaluating the change of vibration mode slope, the average value of the vibration mode slope in the range is marked as p, the maximum value of the vibration mode slope is q, the minimum value is r, and the vibration mode slope deviation n=Max (q-p, p-r)/p is 100% caused by the local installation position of the inertial device;
Fifthly, the slope deviation k= ± (m+n) of the vibration mode of the preselected installation position of the inertial device, wherein the slope of the vibration mode of the preselected position is c obtained in the fourth step, the attitude control stability evaluation is carried out on c and k, the installation position which can meet the design requirement of the attitude control stability and is used as a proper inertial device is selected from a plurality of preselected installation positions, the slope result of the vibration mode of the final selected position is used as the slope result of the vibration mode of the actual installation position, and the slope deviation of the vibration mode of the final selected position is used as the slope deviation of the vibration mode of the actual installation position;
and sixthly, taking the determined vibration mode slope c and vibration mode slope deviation k of the actual installation position as design input of attitude control stability evaluation to carry out attitude control stability design of the whole rocket.
Advantageous effects
(1) The invention carries out fine modeling on the mounting cabin section of the inertial device, and adopts the forms of beams, shells and the like to simulate the rigidity of the skin and the stringers;
(2) The accuracy of the model is verified through experiments: carrying out mode tests in three states of constraint of a cover plate at one end and the other end, free at the other end and free at the two ends of the cabin section with the height and diameter ratio being greater than 1.5 respectively, correcting a refined model through mode results in the three test states, obtaining deviation between a vibration mode slope cabin section test result and a simulation calculation result through a first-order bending mode vibration mode slope measurement result of constraint of the cover plate at the other end and the one end, and giving the deviation in a percentage form;
(3) In the cabin test, the vibration mode slope measuring point is not required to be selected in the range of 0.2D from the upper boundary and the lower boundary (D is the diameter of the cabin), the first-order bending mode response can be adjusted by adjusting the mass of the cover plate, and the measurement of various results is carried out;
(4) The invention carries out the mode test of one end supporting the other end freely and two ends freely for the cabin section with the height and diameter ratio smaller than 1, corrects the refined model by the test, obtains the deviation of the test result and the simulation calculation result of the vibration mode slope cabin section by the measurement result of the central symmetry shape breathing mode vibration mode slope of the free state of one end supporting the other end, and gives out in percentage form;
(5) The invention can test the cabin section with the height and diameter ratio between 1 and 1.5 in a state less than 1 or in a state more than 1.5 to obtain the deviation between the test result of the vibration mode slope cabin section and the simulation calculation result, and the deviation is given in percentage form;
(6) The invention can test the cabin section with the height and diameter ratio between 1 and 1.5 in a state of less than 1 or in a state of more than 1.5;
(7) According to the invention, through a corrected refined model, a distribution diagram of local vibration mode slope of a cabin section under a full rocket mode is obtained through simulation calculation, a simulation calculation result of the local vibration mode slope is a standard value of the vibration mode slope, a change range of the vibration mode slope is estimated according to a range that the longitudinal distance of the cabin section is not less than 0.5m and the circumferential angle is not less than 5 degrees, and the change range is used as vibration mode slope deviation caused by the local installation position of an inertial device and is given in a percentage form;
(8) The invention superimposes the deviation of the cabin test and the simulation calculation result and the deviation of the local installation position, namely the deviation can be given in percentage form as the deviation of the vibration mode slope standard value. And the method of cabin test is adopted to conduct optimization of the mounting position of the inertial device, and the inertial device position selection is not needed through a full rocket mode test.
Drawings
FIG. 1 is a schematic illustration of a respiratory modality of a centrosymmetric shape;
Fig. 2 is a graph showing the local mode slope distribution of the cabin in the full rocket mode.
Detailed Description
The invention is further described below with reference to the drawings and examples.
A method for obtaining a rocket mode shape slope and deviation thereof through a cabin segment test, the method comprising the steps of:
(1) Firstly, carrying out fine modeling on an inertial device installation cabin section, and adopting forms such as beams, shells and the like to simulate the rigidity of skins and stringers;
(2) The accuracy of the model was then verified by trial: carrying out mode tests in three states of constraint of a cover plate at one end and the other end, free at the other end and free at the two ends of the cabin section with the height and diameter ratio larger than 1.5 respectively, correcting a refined model through mode results in the three test states, obtaining deviation between a vibration mode slope cabin section test result and a simulation calculation result through a first-order bending mode vibration mode slope measurement result of constraint of the cover plate at the other end of one section and the other end of the other section, and giving the deviation in percentage form;
(3) In the cabin test, the vibration mode slope measuring point is not selected in the range of 0.2D from the upper boundary and the lower boundary (D is the cabin diameter), the first-order bending mode response can be adjusted by adjusting the mass of the cover plate, and the measurement of various results is carried out;
(4) Carrying out mode tests of free ends at one end and free ends at the other end respectively on cabin sections with the height and diameter ratio smaller than 1, correcting a refined model through the tests, obtaining deviation between a vibration mode slope cabin section test result and a simulation calculation result through a central symmetry shape respiration mode vibration mode slope measurement result of the free state at the other end of the one end, and giving the deviation in percentage form; a schematic diagram of a centrally symmetric shape of the breathing mode is shown in fig. 1;
(5) For the cabin section with the height and diameter ratio between 1 and 1.5, the test can be carried out in a state of less than 1, or in a state of more than 1.5, so that the deviation between the test result of the vibration mode slope cabin section and the simulation calculation result is obtained, and the deviation is given in a percentage form;
(6) For the cabin section with the height and diameter ratio between 1 and 1.5, the test can be performed in a state of less than 1, or in a state of more than 1.5;
(7) Then, through the corrected refined model, a distribution diagram of local vibration mode slope of the cabin section under a full rocket mode is obtained through simulation calculation, the simulation calculation result of the local vibration mode slope is a standard value of the vibration mode slope, the change range of the vibration mode slope is estimated according to the range that the longitudinal distance of the cabin section is not less than 0.5m and the circumferential angle is not less than 5 degrees, and the change range is used as the vibration mode slope deviation caused by the local installation position of an inertial device and is given in a percentage form;
(8) And finally, superposing the deviation of the cabin test and the simulation calculation result and the deviation of the local installation position, and giving the deviation in percentage form as the deviation of the vibration mode slope standard value.
Examples
A method for obtaining a rocket mode shape slope and deviation thereof through a cabin segment test, the method comprising the steps of:
The method comprises the steps that firstly, a rate gyroscope of a rocket is arranged on an interstage section, preselected four installation positions are arranged on quadrant lines at positions 4.5m away from the lower end face, h/D of the interstage section is calculated to be 1.8, mode tests of three states including free ends, free ends of bottom-end supports and top ends of the bottom-end supports and cover plate constraint are conducted on the interstage section, and first-order bending mode vibration mode slope measurement results of four positions of the bottom-end supports and top ends and the cover plate constraint state are respectively-0.143, -0.145, -0.271 and-0.266;
Modeling a rocket stage section, and correcting the model through a modal frequency test result in the first step to ensure that the deviation of the first 3 steps is within 20%, and calculating the first-order bending modal shape slope of four positions according to the constraint state of adding a cover plate at the top end of the bottom end, wherein the result is-0.1;
Thirdly, according to the results of the first two steps, the deviation of the first part of the vibration mode slopes of the four preselected installation positions of the inertial device is 43%, 45%, 171% and 166%;
fourthly, replacing an inter-stage section in the whole rocket model with the cabin section refined model corrected in the second step, and obtaining a vibration mode slope distribution diagram of the cabin section in a first-order bending mode of the whole rocket through simulation calculation, wherein simulation calculation results of preselected positions of four inertial devices are-0.0411, the change of vibration mode slope around the preselected positions is-0.033 to-0.044, the mean value is-0.04, and the vibration mode slope deviation caused by the local installation positions of the inertial devices is 20%;
Fifthly, the slope deviation of the vibration modes of preselected installation positions of four inertial devices in the interstage section is +/-63 percent, +/-65 percent, +/-191 percent and +/-186 percent respectively, the slope of the first-order bending vibration mode of the preselected positions is-0.0411, the 1 st and 2 nd positions of the rate gyro installation positions are finally determined through attitude control stability evaluation, the result of the slope of the first-order bending vibration mode is-0.0411, and the deviation is +/-63 percent and +/-65 percent;
and sixthly, carrying out attitude control stability design of the whole arrow by taking the determined first-order bending vibration mode slope result-0.0411 and deviation +/-63 percent and +/-65 percent as the input of final attitude control stability evaluation.
Claims (5)
1. A method for obtaining a rocket mode shape slope and deviation thereof through a cabin segment test, the method comprising the steps of:
step one, obtaining a vibration mode slope test result a of an inertial device installation cabin;
The method for acquiring the vibration mode slope test result of the inertial device installation cabin section comprises the following steps: carrying out a modal test on the inertial device installation cabin to obtain a modal frequency and a vibration mode of the inertial device installation cabin and a vibration mode slope test result a of a plurality of preselected installation positions of the inertial device;
In the first step, acquiring a vibration mode slope test result a of an inertial device installation cabin, wherein the preselected installation position of the inertial device is not required to be in a range of 0.2D from the upper boundary and the lower boundary, and D is the diameter of the inertial device installation cabin;
the deviation of the model modal frequency calculation result and the test result after correction is within 20% in the first 3 rd order;
in a vibration mode slope test result a of an inertial device installation cabin section, for a cabin section with h/D larger than 1.5, h is the height of the cabin section, and a mode test in three states of free two ends, free top end of a bottom fixing support, and top end of the bottom fixing support and cover plate constraint is required to be carried out;
In a vibration mode slope test result a of an inertial device installation cabin section, for a cabin section with h/D smaller than 1, a mode test with free ends and free top ends of a bottom support is required, wherein the mode frequency and the vibration mode are required to be measured in a free state test of the two ends, the mode frequency, the vibration mode and the vibration mode slope are required to be measured in a free state test of the bottom support and the top ends, and a measurement result of the vibration mode slope of a central symmetry shape breathing mode in the free state of the bottom support and the top ends is a;
In the first step, a vibration mode slope test result a of an inertial device installation cabin section is obtained, and the cabin section with h/D between 1 and 1.5 is tested according to the state smaller than 1 or larger than 1.5 to obtain a result;
in the second step, in the simulation result b of the vibration mode slope of the inertial device installation cabin, carrying out mode calculation on the conditions that h/D is smaller than 1 and larger than 1.5 and 1 and 1.5 according to the mode test state in the first step;
step two, obtaining a simulation result b of the vibration mode slope of the inertial device installation cabin;
The simulation result acquisition method of the vibration mode slope of the inertial device installation cabin section comprises the following steps:
(1) Carrying out fine modeling on an inertial device installation cabin section, carrying out shell unit modeling on a skin of the cabin section, beam unit modeling on a stringer and a ring frame during fine modeling, carrying out mass unit modeling on instrument equipment, and connecting with nodes of the skin and the stringer by using multi-point constraint;
(2) Carrying out modal calculation according to the modal test state in the first step, correcting the cabin model according to the frequency and the vibration mode measurement result of the modal test in the first step, correcting the rigidities of the skin and the stringers, wherein the mode frequency calculation result and the test result of the corrected model are within a set range, and finally calculating according to the cabin vibration mode slope measurement test state to obtain a simulation result b of the cabin vibration mode slope;
Thirdly, obtaining a first partial deviation m= (a-b)/b of the vibration mode slope of 100% according to the cabin vibration mode slope test result a and the simulation result b obtained in the first step and the second step;
And fourthly, replacing the cabin section of the inertial device in the full arrow model with the corrected cabin section refined model in the second step, and obtaining a vibration mode slope distribution diagram of the cabin section under the full arrow first-order bending mode through simulation calculation, wherein the simulation calculation result of the preselected position of the inertial device is marked as c, the longitudinal distance around the preselected position is selected to be not smaller than a set value, the circumferential angle is not smaller than the set angle to evaluate the change of the vibration mode slope, the average value of the vibration mode slope in the range is marked as p, the maximum value of the vibration mode slope is q, the minimum value is r, the vibration mode slope deviation n=Max (q-p, p-r)/p is 100% caused by the local installation position of the inertial device, and the vibration mode slope deviation k= (+/-) (m+n) of the preselected installation position of the inertial device.
2. A method of acquiring a rocket mode shape slope and deviations thereof through a segment test as claimed in claim 1, wherein:
The free state test of the top end of the bottom support is required to measure the modal frequency and the vibration mode, the state test of the top end of the bottom support and the cover plate is required to measure the modal frequency, the vibration mode and the vibration mode slope, and meanwhile, the mass of the cover plate can be adjusted, so that the vibration mode slope test result a of the inertial device installation cabin under various states is obtained.
3. A method of acquiring a rocket mode shape slope and deviations thereof through a segment test as claimed in claim 1, wherein:
C and k are subjected to attitude control stability evaluation, a proper inertia device installation position which can meet the attitude control stability design requirement is selected from a plurality of preselected installation positions, the vibration mode slope result of the final selected position is used as the vibration mode slope result of the actual installation position, and the vibration mode slope deviation of the final selected position is used as the vibration mode slope deviation of the actual installation position.
4. A method of obtaining a rocket mode shape slope and deviations thereof through a segment test as claimed in claim 3, wherein:
And taking the determined vibration mode slope c and vibration mode slope deviation k of the actual installation position as design inputs of attitude control stability evaluation to carry out attitude control stability design of the whole rocket.
5. A method of acquiring a rocket mode shape slope and deviations thereof through a segment test as claimed in claim 1, wherein:
and thirdly, selecting a range of not less than 0.5m of longitudinal distance around the preselected position and not less than 5 degrees of circumferential angle to evaluate the change of the vibration mode slope.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012130237A1 (en) * | 2011-03-30 | 2012-10-04 | Rune Brincker | Method for improving determination of mode shapes for a mechanical structure and applications hereof |
| CN103455645A (en) * | 2012-05-31 | 2013-12-18 | 北京宇航系统工程研究所 | Overall-modal extraction method |
| CN110907208A (en) * | 2019-11-26 | 2020-03-24 | 蓝箭航天空间科技股份有限公司 | Modal test method of carrier rocket |
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- 2021-05-13 CN CN202110524490.5A patent/CN113378292B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012130237A1 (en) * | 2011-03-30 | 2012-10-04 | Rune Brincker | Method for improving determination of mode shapes for a mechanical structure and applications hereof |
| CN103455645A (en) * | 2012-05-31 | 2013-12-18 | 北京宇航系统工程研究所 | Overall-modal extraction method |
| CN110907208A (en) * | 2019-11-26 | 2020-03-24 | 蓝箭航天空间科技股份有限公司 | Modal test method of carrier rocket |
Non-Patent Citations (2)
| Title |
|---|
| 火箭模态振型斜率预示方法研究;祁峰;杨树涛;秦旭东;容易;张智;;导弹与航天运载技术(04);摘要及正文第1-4节 * |
| 运载火箭振型斜率测量系统研制;焦舰;黄慧章;张明举;邵添羿;刘汉辰;;导航与控制(02);全文 * |
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