CN104359694A - Method for testing system-level trial run operation modes and operation deformation of liquid rockets - Google Patents
Method for testing system-level trial run operation modes and operation deformation of liquid rockets Download PDFInfo
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Abstract
The invention discloses a method for testing system-level trial run operation modes and operation deformation of liquid rockets. The method includes steps of determining measuring points; mounting sensors; constructing testing systems; debugging the testing systems; measuring data in trail run procedures; analyzing results and the like. The method has the advantages that kinetic characteristics of rocket body structures of the rockets in ignition states can be truly acquired, main low-frequency vibration characteristics of rocket bodies can be obtained by the aid of the few measuring points, and the multipurpose data are acquired and can be used for analyzing the operation modes, analyzing the operation deformation, formulating mechanical environments and the like.
Description
Technical field
The invention belongs to rocket dynamics attribute testing analysis field, be specifically related to the system-level trial run work mode of a kind of liquid rocket and working deformation test method.
Background technology
Last century early sixties, Thunder God series and god of unusual strength's series of fluids rocket start to occur the longitudinal autovibration of low frequency, and the kinetic instability that this liquid rocket chattering being called as " POGO " is mainly caused by the thrust oscillating phase interaction of rocket structure dynamics and liquid propelling system causes.We can observe this phenomenon in the frequency range of several hertz to 100 hertz, and this frequency range depends primarily on the size of liquid rocket.POGO vibration occurs rocket can cause the malfunctioning and structural failure of instrument on some arrow, the serious failure that even can cause aerial mission.In manned, POGO vibration may cause cosmonaut's physiological system to lack of proper care, and does not feel like oneself.Therefore, prevention and prohibition rocket body POGO vibration is extremely important and problem that is that merit attention.
First POGO vibration analysis should be carried out from two aspects, is the model analysis of rocket body structure on the one hand, mainly determines the Modal Characteristics that rocket body structure and propulsion system intercouple, as longitudinal vibration mode etc.Can ground modal test, structural finite element analysis and correlation analysis be passed through, obtain rocket body structure Modal Characteristics.Be the analysis of liquid-propellant rocket engine performance of propulsion system on the other hand, emphasis is the dynamics parameter determining storage tank pipe system, thrust chamber system etc., and this respect work mainly relies on the data analysis to ground experiment and flight test.After obtaining the analysis result of above two aspects, just the stability analysis of total system can be carried out.
In liquid rocket system-level (such as boosting total system, core one-level total system, core secondary total system) commissioning process, each epidemic situation comparison is close to Live Flying state.In order to the adaptability that proving trial state POGO designs, and POGO design verification is carried out on the basis of test figure, then need to carry out the Modal Experimental Analysis under rocket system level trial condition, obtain POGO by Modal Experimental Analysis and design the longitudinal mode parameter be concerned about.
In current test method, for obtaining the modal parameter of trial condition, generally after non-fueling or fueling, obtain modal parameter by the artificial excitation modal test that applies.Comparatively speaking, carry out Modal Parameter Identification by operational modal analysis in commissioning process then to have the following advantages: 1. because whole rocket body structure is complicated, especially when being in test bay state, artificial applying excitation energy is limited, under trial condition under rocket engine thrust closer to the force environment of Live Flying state.2. when whole rocket body be in test bay uses artificial apply excitation time, now test bay act as supporting role to rocket body, and in igniting commissioning process, test bay is drag interaction to rocket body, boundary condition is different, and the modal parameter under the boundary condition in commissioning process is more suitable for for analyzing to combination with the data in other commissioning process.3. after rocket firing, along with fuel consumption, can there is significant change in rocket body quality, now the dynamics of rocket body also can change, and can obtain the dynamics variation tendency along with fuel consumption rocket body by the operation mode identification carried out under trial condition.The test method that system-level test run under trial condition does not also have operation mode to be correlated with at present and research.
Summary of the invention
The object of the invention is to make up the deficiencies in the prior art, there is provided the system-level trial run work mode of a kind of new liquid rocket and working deformation measuring and analysis method, this test method overcomes and before test run, encourages the deficiency of carrying out existing for modal test by artificial applying at present; By the low-frequency vibration response in the system-level commissioning process of liquid rocket, operation mode and working deformation analytical approach is adopted to obtain modal parameter and working deformation.
To achieve these goals, technical scheme of the present invention is, the system-level trial run work mode of a kind of liquid rocket and working deformation test method, comprise the following steps:
Step 1, determines measuring point; Be fixed on the configuration state after test bay to liquid rocket core one-level total system to analyze, at the symmetrical two row measuring points of rocket body, these measuring point lengthwise positions lay respectively at bottom oxygen box top, inter-tank section top, inter-tank section bottom, combustion case and rocket body and test bay junction, are respectively measuring point, rocket body and test bay link position measuring point bottom fuel tank top measuring point, inter-tank section top measuring point, inter-tank section bottom measuring point, lower fuel tank; Inter-tank section top measuring point is also measuring point bottom upper fuel tank, and inter-tank section bottom measuring point is also lower fuel tank top measuring point;
Step 2, sensor installation on the measuring point that step 1 is determined;
Step 3, builds pilot system and debugging; Ensure that the coordinate direction of the sensor of all measuring points is consistent, and make a record preparation;
Step 3.1, pilot system is built; The sensor of all measuring points is connected to rear end by the cable of test bay measure in interior collector row of channels, and arranges acquisition parameter, sample frequency is set to 300Hz, low-pass filtering 100Hz; The passage of all measuring point sensors is in same collector, thus guarantees to have identical initial time in the final all data gathered;
Step 3.2, pilot system is debugged;
Step 4, measurement data in commissioning process; Listen password pre-cooling collector before test run, then personnel withdraw between measurement, and personnel withdraw rear beginning test run, after test run completes, close collector;
Step 5, interpretation of result; The data that all collectors gather are intercepted, makes all data all have identical initial time; Then carry out operational modal analysis and obtain working deformation analysis, concrete steps are as follows:
Step 5.1, sets up three-dimensional geometry wire-frame model according to the position coordinates of each Sensor on whole rocket coordinate system, uses Polymax method to obtain steady state picture;
Step 5.2, the steady state picture set up by step 5.1 is extracted possibility mode and obtains each rank modal parameter;
Step 5.3, uses mode decision criteria to carry out the checking of operational modal analysis result, thus obtains the rocket body lower mode in 100Hz.
In described step 2, sensor is ICP three-dimensional sensor;
In described step 2, be arranged on fuel tank top measuring point, the sensor of inter-tank section top measuring point uses the bonding sensor of low temperature glue or use screw-jointing method sensor installation; Sensor on other measuring points needs when installing, to mounting surface polishing paint removal, to be adhesively fixed.
Progress part of the present invention is as follows: 1. the dynamics truly obtaining rocket body structure under rocket firing state; 2., owing to being only concerned about the low-frequency vibration of liquid rocket entirety, therefore use less measuring point just can obtain the main low-frequency vibration feature of rocket body; 3. the data obtained can have multiple use, such as operational modal analysis, working deformation analysis, mechanical environment formulation etc.
Accompanying drawing explanation
Fig. 1 is measuring point distribution schematic diagram of the present invention.
Fig. 2 is pilot system schematic diagram of the present invention.
Fig. 3 is the three-dimensional geometry wire-frame model set up according to measuring point.
Fig. 4 obtains steady state picture for using Polymax method.
Fig. 5 is the MAC value figure that analytical calculation obtains.
In figure, 11-upper fuel tank, 12-inter-tank section, 13-lower fuel tank, 14-rear, 15-test bay, 16-upper fuel tank top measuring point, 17-inter-tank section top measuring point, 18-inter-tank section bottom measuring point, measuring point bottom 19-lower fuel tank, 110-rocket body and test bay link position measuring point, 21-sensor, 22-cable, 23-collector, between 24-measurement.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described further.
A kind of system-level trial run work mode of liquid rocket and working deformation test method, comprise the following steps:
Step 1, determines measuring point, be fixed on the configuration state after test bay to liquid rocket core one-level total system to analyze, this liquid rocket core one-level is from top to bottom by upper fuel tank 11, inter-tank section 12, lower fuel tank 13, rear 14 4 part forms, therefore, at the symmetrical two row measuring points of rocket body, these measuring point lengthwise positions lay respectively at oxygen box top, inter-tank section top, inter-tank section bottom, bottom combustion case and rocket body and test bay junction, as shown in Figure 1, be respectively fuel tank top measuring point 16, inter-tank section top measuring point 17, inter-tank section bottom measuring point 18, measuring point 19 bottom lower fuel tank, rocket body and test bay link position measuring point 110, inter-tank section top measuring point 17 is also measuring point bottom upper fuel tank, and inter-tank section bottom measuring point 18 is also lower fuel tank top measuring point,
Step 2, sensor installation 21 on the measuring point that step 1 is determined; Consider analysis frequency scope 0Hz-100Hz, sensor 21 used is ICP three-dimensional sensor; Be arranged on fuel tank top measuring point 16, the sensor 21 of inter-tank section top measuring point 17 uses the bonding sensor 21 of low temperature glue or use screw-jointing method sensor installation 21; Sensor 21 on other measuring points needs when installing, to mounting surface polishing paint removal, to be adhesively fixed, to ensure that in impact in commissioning process and vibration noise load, sensor 21 and rocket body combine all the time, do not produce fifth wheel.
Step 3, builds pilot system and debugging; Ensure that the coordinate direction of the sensor 21 of all measuring points is consistent, and make a record preparation;
Step 3.1, pilot system is built; By the sensor 21 of all measuring points by the cable 22 of test bay be connected to rear end measure between in collector 23 row of channels in 24, and arrange acquisition parameter, sample frequency is set to 300Hz, low-pass filtering 100Hz; The passage of all measuring point sensors 21 is in same collector 23, thus guarantees to have identical initial time in the final all data gathered, as shown in Figure 2;
Step 3.2, pilot system is debugged; After whole system has been built, by knocking rocket body surface, record each channel data thus debug system ensure whole system normal;
Step 4, measurement data in commissioning process; During test run, due to safety, between start-up period, personnel need 24 to withdraw between measurement; Therefore, listen password pre-cooling collector 23 before test run, then personnel to withdraw between measurement 24, and personnel withdraw rear beginning test run, close collector 23 after test run completes;
Step 5, interpretation of result; The data that all collectors 23 gather are intercepted, makes all data all have identical initial time; Then carry out operational modal analysis and obtain working deformation analysis, concrete steps are as follows:
Step 5.1, sets up three-dimensional geometry wire-frame model according to the position coordinates of each Sensor on whole rocket coordinate system, as shown in Figure 3, uses Polymax method to obtain steady state picture, as shown in Figure 4;
Step 5.2, the steady state picture set up by step 5.1 is extracted possibility mode and obtains each rank modal parameter, and the horizontal ordinate in Fig. 4 corresponding to vertical line is each rank model frequency of analysis.
Step 5.3, use MAC value to carry out the checking of operational modal analysis result, thus obtain the rocket body lower mode in 100Hz, the MAC value describing two vibration shapes of same physical mode should close to 1.As in Fig. 5, the MAC value namely for being obtained by step 5.1 and 5.2 analytical calculations.Can find out, the MAC value describing two of same single order mode vectorial is all 1.
Above embodiments of the invention are explained in detail, above-mentioned embodiment is only optimum embodiment of the present invention, but the present invention is not limited to above-described embodiment, in the ken that those of ordinary skill in the art possess, various change can also be made under the prerequisite not departing from present inventive concept.
Claims (3)
1. the system-level trial run work mode of liquid rocket and a working deformation test method, is characterized in that comprising the following steps:
Step 1, determines measuring point; Be fixed on the configuration state after test bay to liquid rocket core one-level total system to analyze, at the symmetrical two row measuring points of rocket body, these measuring point lengthwise positions lay respectively at bottom oxygen box top, inter-tank section top, inter-tank section bottom, combustion case and rocket body and test bay junction, are respectively measuring point (19), rocket body and test bay link position measuring point (110) bottom fuel tank top measuring point (16), inter-tank section top measuring point (17), inter-tank section bottom measuring point (18), lower fuel tank; Inter-tank section top measuring point (17) is also measuring point bottom upper fuel tank, and inter-tank section bottom measuring point (18) is also lower fuel tank top measuring point;
Step 2, sensor installation on the measuring point that step 1 is determined;
Step 3, builds pilot system and debugging; Ensure that the coordinate direction of the sensor (21) of all measuring points is consistent, and make a record preparation;
Step 3.1, pilot system is built; The sensor (21) of all measuring points is connected in collector (23) row of channels between the measurement of rear end in (24) by the cable (22) of test bay, and acquisition parameter is arranged, sample frequency is set to 300Hz, low-pass filtering 100Hz; The passage of all measuring point sensors (21) is in same collector (23), thus guarantees to have identical initial time in the final all data gathered;
Step 3.2, pilot system is debugged;
Step 4, measurement data in commissioning process; Listen password pre-cooling collector (23) before test run, then personnel withdraw (24) between measurement, and personnel withdraw rear beginning test run, close collector (23) after test run completes;
Step 5, interpretation of result; The data that all collectors (23) gather are intercepted, makes all data all have identical initial time; Then carry out operational modal analysis and obtain working deformation analysis, concrete steps are as follows:
Step 5.1, sets up three-dimensional geometry wire-frame model according to the position coordinates of each Sensor on whole rocket coordinate system, uses Polymax method to obtain steady state picture;
Step 5.2, the steady state picture set up by step 5.1 is extracted possibility mode and obtains each rank modal parameter;
Step 5.3, uses mode decision criteria to carry out the checking of operational modal analysis result, thus obtains the rocket body lower mode in 100Hz.
2. the system-level trial run work mode of a kind of liquid rocket as claimed in claim 1 and working deformation test method, is characterized in that sensor in step 2 (21) is for ICP three-dimensional sensor.
3. the system-level trial run work mode of a kind of liquid rocket as claimed in claim 1 and working deformation test method, is characterized in that being arranged in step 2 fuel tank top measuring point (16), the sensor (21) on inter-tank section top measuring point (17) uses the bonding sensor of low temperature glue (21) or use screw-jointing method sensor installation (21); Sensor (21) on other measuring points needs when installing, to mounting surface polishing paint removal, to be adhesively fixed.
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| CN106568582A (en) * | 2015-10-12 | 2017-04-19 | 华电宁夏灵武发电有限公司 | Air cooling island framework vibration monitoring method |
| CN106650045A (en) * | 2016-12-05 | 2017-05-10 | 大连理工大学 | Optimized design and strength analysis method of secondary box section structure |
| CN106777617A (en) * | 2016-12-05 | 2017-05-31 | 大连理工大学 | A kind of two grades of inter-tank section optimum structure design methods |
| CN107192522A (en) * | 2016-03-15 | 2017-09-22 | 北京强度环境研究所 | Major diameter strap-on vehicle Spatial Coupling mode exciting method for arranging |
| CN109911244A (en) * | 2018-11-12 | 2019-06-21 | 中航通飞研究院有限公司 | A kind of large aircraft ground roll-out Analysis of Vibration Characteristic method |
| CN110017992A (en) * | 2019-05-16 | 2019-07-16 | 九州云箭(北京)空间科技有限公司 | A kind of liquid rocket dynamical system test run method and its device |
| CN110542563A (en) * | 2019-08-28 | 2019-12-06 | 西安航天动力试验技术研究所 | Engine ground test POGO excitation method |
| CN110826020A (en) * | 2019-10-21 | 2020-02-21 | 西安航天动力研究所 | Method and system for rapidly analyzing hot test data of liquid rocket engine |
| CN112651078A (en) * | 2020-12-02 | 2021-04-13 | 西安航天动力技术研究所 | Rocket body structure state anomaly detection method based on symbolic dynamics |
| CN115200879A (en) * | 2022-09-19 | 2022-10-18 | 北京星河动力装备科技有限公司 | High-altitude flight test shutdown control method and system for liquid rocket engine |
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| CN106568582A (en) * | 2015-10-12 | 2017-04-19 | 华电宁夏灵武发电有限公司 | Air cooling island framework vibration monitoring method |
| CN107192522B (en) * | 2016-03-15 | 2020-02-21 | 北京强度环境研究所 | Large-diameter binding type carrier rocket space combination modal excitation arrangement method |
| CN107192522A (en) * | 2016-03-15 | 2017-09-22 | 北京强度环境研究所 | Major diameter strap-on vehicle Spatial Coupling mode exciting method for arranging |
| CN106053000B (en) * | 2016-07-15 | 2018-05-11 | 北京强度环境研究所 | A kind of guided missile and carrier rocket Modal Experimental Method |
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| CN106650045A (en) * | 2016-12-05 | 2017-05-10 | 大连理工大学 | Optimized design and strength analysis method of secondary box section structure |
| CN106777617B (en) * | 2016-12-05 | 2019-06-14 | 大连理工大学 | A kind of second level inter-tank section optimum structure design method |
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| CN110542563B (en) * | 2019-08-28 | 2020-12-11 | 西安航天动力试验技术研究所 | Engine ground test POGO excitation method |
| CN110542563A (en) * | 2019-08-28 | 2019-12-06 | 西安航天动力试验技术研究所 | Engine ground test POGO excitation method |
| CN110826020A (en) * | 2019-10-21 | 2020-02-21 | 西安航天动力研究所 | Method and system for rapidly analyzing hot test data of liquid rocket engine |
| CN110826020B (en) * | 2019-10-21 | 2023-06-23 | 西安航天动力研究所 | Rapid analysis method and system for thermal test run data of liquid rocket engine |
| CN112651078A (en) * | 2020-12-02 | 2021-04-13 | 西安航天动力技术研究所 | Rocket body structure state anomaly detection method based on symbolic dynamics |
| CN112651078B (en) * | 2020-12-02 | 2023-09-08 | 西安航天动力技术研究所 | Arrow body structure state abnormality detection method based on symbol dynamics |
| CN115200879A (en) * | 2022-09-19 | 2022-10-18 | 北京星河动力装备科技有限公司 | High-altitude flight test shutdown control method and system for liquid rocket engine |
| CN115200879B (en) * | 2022-09-19 | 2023-01-13 | 北京星河动力装备科技有限公司 | High-altitude flight test shutdown control method and system for liquid rocket engine |
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