CN202372981U - Dynamic model modification device applicable to spacecrafts - Google Patents
Dynamic model modification device applicable to spacecrafts Download PDFInfo
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- CN202372981U CN202372981U CN 201120417355 CN201120417355U CN202372981U CN 202372981 U CN202372981 U CN 202372981U CN 201120417355 CN201120417355 CN 201120417355 CN 201120417355 U CN201120417355 U CN 201120417355U CN 202372981 U CN202372981 U CN 202372981U
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Abstract
The utility model belongs to the technical field of modification of dynamic models, particularly relates to a dynamic model modification device applicable to spacecrafts, and solves the problem that in the prior art, the modification efficiency of dynamic models of spacecrafts is very low, and the effect is poor. The dynamic model modification device applicable to spacecrafts comprises a model and data collecting module, a relativity computation module, a sensitivity computation module and a model modification module; the model and data collecting module is connected with the relativity computation module, the sensitivity computation module and the model modification module respectively; and the relativity computation module is connected with the sensitivity computation module. The device provided by the utility model adopts a relativity computation module, the sensitivity computation module and the model modification module, so that the purpose of modifying a dynamic model of a spacecraft quickly, efficiently and accurately can be achieved, designers can be released from simple and repeated work, and the work efficiency is improved. The device provided by the utility model can be further applied to modification of dynamic characteristic models of rockets and to optimization of structural rigidity of rockets or spacecrafts.
Description
Technical field
The utility model belongs to kinetic model correction technique field, is specifically related to a kind of kinetic model correcting device that is applicable to spacecraft.
Background technology
Therefore the out-of-shape of spacecraft, the intersegmental annexation complicacy of portion can not be simplified to discrete space beam model with reference to existing rocket, need set up detailed space plate shell model, and intersegmental power transmission route of simulation part and coupling stiffness.When the correction of spacecraft dynamic dynamics model, parameter to be revised is more, and rule of thumb is difficult to confirm the parameter responsive to the frequency and the vibration shape etc., so hand form block correction workload is big, and is difficult to obtain desirable effect.
To be the designer make amendment according to mass property such as engineering experience, manual thickness to each section of structure, diameter, elasticity modulus of materials, moment of inertia or rigidity data in existing rocket dynamic dynamics model correction work.And the parameter of the each adjustment of record and the variation tendency of result of calculation, finally revise out the rocket model that satisfies optimization aim or ground test result.Because often rely on engineering experience or free hand modification, therefore, prior art is to extremely low, the poor effect of kinetic model correction efficient of spacecraft.
Summary of the invention
The purpose of the utility model is to solve that prior art is extremely low to the kinetic model correction efficient of spacecraft, the problem of poor effect, and a kind of kinetic model correcting device that is applicable to spacecraft is provided.
The utility model is achieved in that
A kind of kinetic model correcting device that is applicable to spacecraft comprises model and data acquisition module, correlation calculations module, sensitivity calculations module and model correcting module; Model is connected with correlation calculations module, sensitivity calculations module and model correcting module respectively with data acquisition module; The correlation calculations module also is connected with the sensitivity calculations module.
Aforesaid sensitivity calculations module comprises the optimization aim acquisition module and treats the corrected parameter acquisition module; Optimization aim acquisition module and model are with data acquisition module, correlation calculations module and treat that the corrected parameter acquisition module is connected; Treat that the corrected parameter acquisition module also is connected with the model correcting module.
Aforesaid model and data acquisition module, correlation calculations module, sensitivity calculations module and model correcting module all adopt prior art to pass through industrial computer, multi-purpose computer or Intelligent treatment chip and realize.
The beneficial effect of the utility model is:
The device of the utility model adopts correlation calculations module, sensitivity calculations module and model correcting module; Quick, efficient, accurately correction have been realized to the kinetic model correction of spacecraft; Designer's substance of conforming to the principle of simplicity is freed in working again, improved work efficiency.The device of the utility model is also applicable to the rigidity of structure optimization of dynamic dynamics model correction, rocket or the spacecraft of rocket.
Description of drawings
Fig. 1 is a kind of structure principle chart that is applicable to the kinetic model correcting device of spacecraft of the utility model;
Fig. 2 is the structure principle chart of Fig. 1 medium sensitivity computing module.
Embodiment
Below in conjunction with accompanying drawing and embodiment a kind of kinetic model correcting device of spacecraft that is applicable to of the utility model is introduced:
As shown in Figure 1, a kind of kinetic model correcting device that is applicable to spacecraft comprises model and data acquisition module, correlation calculations module, sensitivity calculations module and model correcting module.
Model is connected with correlation calculations module, sensitivity calculations module and model correcting module respectively with data acquisition module; It gathers spacecraft dynamic dynamics model and spacecraft dynamic response test data to be revised; And spacecraft dynamic dynamics model that collects and spacecraft dynamic response test data sent to correlation calculations module and sensitivity calculations module, spacecraft dynamic dynamics model to be revised is sent to the model correcting module.The test figure here is that real space aircraft product is carried out the modal test data that ground experiment obtains; Comprise frequency, the vibration shape and damping data, spacecraft dynamic dynamics model to be revised is based on the quality of real space aircraft product and the finite element theory model that Stiffness Distribution adopts prior art to obtain.Spacecraft dynamic characteristic finite element model that collection is to be revised and spacecraft dynamic response test data can adopt existing techniques in realizing.
The correlation calculations module also is connected with the sensitivity calculations module; It carries out correlation calculations according to spacecraft dynamic dynamics model and spacecraft dynamic response test data that the first step obtains; And judge the close degree of finite element model and test figure, and then determine whether need carry out the model correction according to correlativity calculation result.If need to revise, then further confirm the order corresponding relation of spacecraft dynamic response test data and spacecraft dynamic dynamics model mode, then above-mentioned corresponding relation is sent to the sensitivity calculations module.
In the present embodiment, the correlation calculations module adopts correlation criterion to carry out correlation calculations.The correlation criterion here comprises frequency and vibration shape correlativity, mode degree of confidence (MAC), mode scale factor (MSF) and mode orthogonality (EVO).The general mode degree of confidence that adopts is carried out correlation calculations.Adopt correlation criterion to carry out correlation calculations and can adopt existing techniques in realizing.The correlation calculations module is carried out correlation calculations and is obtained mode degree of confidence (MAC), if when MAC＜0.8, need carry out the model correction; Otherwise model meets the demands, and need not carry out the model correction.The mode corresponding relation of confirming spacecraft dynamic response test data and spacecraft dynamic dynamics model can adopt existing techniques in realizing.The mode here is meant frequency, the vibration shape and the damping of each order of spacecraft dynamic dynamics model to be revised.
The sensitivity calculations module also is connected with the model correcting module.As shown in Figure 2, the sensitivity calculations module comprises the optimization aim acquisition module and treats the corrected parameter acquisition module.Optimization aim acquisition module and model are with data acquisition module, correlation calculations module and treat that the corrected parameter acquisition module is connected; Its is according to spacecraft dynamic dynamics model to be revised and the spacecraft dynamic response test data of coming self model and data acquisition module, from the corresponding relation of the spacecraft dynamic response test data of correlation calculations module and spacecraft dynamic dynamics model mode order to be revised; Confirm the optimization aim of the mode of spacecraft dynamic dynamics model to be revised, and the optimization aim of the mode of the spacecraft dynamic dynamics model to be revised that will obtain sends to and treats the corrected parameter acquisition module.The optimization aim here comprises frequency, the vibration shape and quality, and this optimization aim can be corresponding to above-mentioned order spacecraft dynamic response test data, also can be the desired value of storing in advance, confirms according to actual needs.Treat that the corrected parameter acquisition module also is connected with the model correcting module; The variable gradient that it treats corrected parameter according to the optimization aim calculation optimization target of the mode of the spacecraft dynamic dynamics model to be revised that receives obtains the sensitivity data; And with the descending ordering of sensitivity data, wherein preceding 20% data corresponding parameters conduct treats that corrected parameter sends to the model correcting module then.The corrected parameter of treating here comprises architecture quality characteristic, static(al) displacement, natural frequency, the vibration shape and frequency response function etc.The sensitivity calculations module will be to be revised the spacecraft dynamic dynamics model mode optimization aim and spacecraft dynamic dynamics model to be revised treat that corrected parameter sends to the model correcting module and is connected.The sensitivity calculations here can adopt existing techniques in realizing.
The model correcting module is according to the optimization aim of the mode of the spacecraft dynamic dynamics model to be revised that receives, spacecraft dynamic dynamics model to be revised and treat corrected parameter; Treat the spacecraft dynamic dynamics model of correction and revise, obtain the finite element model of new spacecraft.
In the present embodiment; The model correcting module is adjusted the corrected parameter of treating of spacecraft dynamic dynamics model to be revised; The FEM modal analysis and modal and the optimization aim of spacecraft dynamic dynamics model to be revised are complementary; Both relative deviations are revised during less than pre-set threshold and are finished, and obtain the finite element model of new spacecraft.Threshold value is generally got 5%-10%.The adjustment here is meant to increase and reduces parameter value that the amplitude of general adjustment is positive and negative 10%.
Model and data acquisition module, correlation calculations module, sensitivity calculations module and model correcting module all adopt prior art to pass through industrial computer, multi-purpose computer or Intelligent treatment chip and realize.
The device of the utility model adopts correlation calculations module, sensitivity calculations module and model correcting module; Quick, efficient, accurately correction have been realized to the kinetic model correction of spacecraft; Designer's substance of conforming to the principle of simplicity is freed in working again, improved work efficiency.The device of the utility model is also applicable to the rigidity of structure optimization of dynamic dynamics model correction, rocket or the spacecraft of rocket.
Claims (3)
1. a kinetic model correcting device that is applicable to spacecraft is characterized in that: comprise model and data acquisition module, correlation calculations module, sensitivity calculations module and model correcting module; Model is connected with correlation calculations module, sensitivity calculations module and model correcting module respectively with data acquisition module; The correlation calculations module also is connected with the sensitivity calculations module.
2. a kind of kinetic model correcting device that is applicable to spacecraft according to claim 1 is characterized in that: described sensitivity calculations module comprises the optimization aim acquisition module and treats the corrected parameter acquisition module; Optimization aim acquisition module and model are with data acquisition module, correlation calculations module and treat that the corrected parameter acquisition module is connected; Treat that the corrected parameter acquisition module also is connected with the model correcting module.
3. a kind of kinetic model correcting device that is applicable to spacecraft according to claim 1 and 2 is characterized in that: described model and data acquisition module, correlation calculations module, sensitivity calculations module and model correcting module all adopt prior art to pass through industrial computer, multi-purpose computer or Intelligent treatment chip and realize.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120417355 CN202372981U (en) | 2011-10-27 | 2011-10-27 | Dynamic model modification device applicable to spacecrafts |
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| Application Number | Priority Date | Filing Date | Title |
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| CN 201120417355 CN202372981U (en) | 2011-10-27 | 2011-10-27 | Dynamic model modification device applicable to spacecrafts |
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| CN202372981U true CN202372981U (en) | 2012-08-08 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103593518A (en) * | 2013-10-31 | 2014-02-19 | 中国运载火箭技术研究院 | Aircraft model modification system based on modal test data |
| CN105912772A (en) * | 2016-04-08 | 2016-08-31 | 北京宇航系统工程研究所 | Model correction method integrated with frequency, vibration modes and frequency response functions |
| CN106682353A (en) * | 2017-01-11 | 2017-05-17 | 南京航空航天大学 | Locomotive multi-body structure dynamic model correction method |
| CN109489690A (en) * | 2018-11-23 | 2019-03-19 | 北京宇航系统工程研究所 | A kind of boost motor navigator fix calculation method reentered suitable for high dynamic rolling |
-
2011
- 2011-10-27 CN CN 201120417355 patent/CN202372981U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103593518A (en) * | 2013-10-31 | 2014-02-19 | 中国运载火箭技术研究院 | Aircraft model modification system based on modal test data |
| CN103593518B (en) * | 2013-10-31 | 2016-06-01 | 中国运载火箭技术研究院 | A kind of aircraft Modifying model system based on mode testing data |
| CN105912772A (en) * | 2016-04-08 | 2016-08-31 | 北京宇航系统工程研究所 | Model correction method integrated with frequency, vibration modes and frequency response functions |
| CN105912772B (en) * | 2016-04-08 | 2019-04-09 | 北京宇航系统工程研究所 | A kind of model modification method integrating frequency, the vibration shape and frequency response function |
| CN106682353A (en) * | 2017-01-11 | 2017-05-17 | 南京航空航天大学 | Locomotive multi-body structure dynamic model correction method |
| CN109489690A (en) * | 2018-11-23 | 2019-03-19 | 北京宇航系统工程研究所 | A kind of boost motor navigator fix calculation method reentered suitable for high dynamic rolling |
| CN109489690B (en) * | 2018-11-23 | 2020-10-23 | 北京宇航系统工程研究所 | Booster navigation positioning resolving method suitable for high dynamic rolling reentry |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120808 |