CN108446457A - A kind of satellite carrier system dynamics response analysis method and system - Google Patents
A kind of satellite carrier system dynamics response analysis method and system Download PDFInfo
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Abstract
The invention discloses a kind of satellite carrier system dynamics response analysis method and systems, wherein the method includes：Model analysis is carried out to holder according to the finite element modeling result of holder, and when holder modal analysis result meets design requirement, model analysis is carried out to carrier coupled system, obtains the frequency of carrier coupled system；And when the frequency of carrier coupled system meets setpoint frequency, model analysis is carried out to satellite, obtains the acceleration responsive value at carrier coupling body characteristic point；The acceleration responsive value of holder installation place is determined according to the acceleration responsive value at carrier coupling body characteristic point, and the pulling capacity of holder installation place is calculated；If the pulling capacity for the holder installation place being calculated is less than the embedded part pulling capacity, design is re-started until meeting the requirements.Satellite carrier system structure design is improved through the invention and dynamic analysis is horizontal.
Description
Technical field
The invention belongs to Dynamics analysis technology field more particularly to a kind of satellite carrier system dynamics response analysis sides
Method and system.
Background technology
With satellite main body structure power coupling may occur for widely used payload supporting structure in satellite engineering,
It is greatly enlarged in turn result in payload response.Payload holder and satellite main body structure are further thought of as an entirety
System (is known as carrier system).It, can since supporting structure has many advantages, such as that light weight, configuration are simple and plane occupied space is few
Satellite total quality is reduced, component difficulty of processing is reduced and is conducive to installation and the layout of instrument, therefore in Modern Satellite knot
Widely used rack-like structures are as payload or the installation pedestal of instrument and equipment in structure design.As posture crucial on star
Measuring part, the installation of sensor and direction have higher required precision.Sensor holder is mounted on the structure of satellite main body
It is the transition connecting structure between satellite main body and sensor on plate.To examine or check the mechanical property of holder, need to be carried out to holder must
The quiet, dynamics calculation wanted and analysis.
At present to the design of holder mostly using component-level payload supporting structure as research object, but work as payload branch
With after the installation of satellite main body structure, contour connection rigidity will change frame, cause the payload branch under whole starlike state
Frame structural dynamic characteristics differ larger with the structural dynamic characteristics under its component-level state.Therefore, effective for component-level
The rigidity Design that load support carries out not necessarily meets the payload stiffness of support requirement under whole starlike state, in some instances it may even be possible to can make
Payload response is further amplified.Satellite main body structure and sensor supporting structure are equivalent to a kind of single-degree-of-freedom by this patent
Spring system proposes a kind of satellite carrier system dynamics response analysis scheme.
Invention content
The technology of the present invention solves the problems, such as：Overcome the deficiencies of the prior art and provide a kind of satellite carrier system dynamics sound
Analysis method and system are answered, satellite carrier system structure design is improved and dynamic analysis is horizontal.
In order to solve the above-mentioned technical problem, the invention discloses a kind of satellite carrier system dynamics response analysis method,
Including：
Step 1, finite element modeling is carried out to holder, model analysis is carried out to holder according to modeling result, and in holder mould
When state analysis result meets design requirement, step 2 is executed；
Step 2, model analysis is carried out to carrier coupled system, obtains the frequency of carrier coupled system, and couple in carrier
When the frequency of system meets setpoint frequency, step 3 is executed；
Step 3, model analysis is carried out to satellite, obtains the acceleration responsive value at carrier coupling body characteristic point；
Step 4, the acceleration responsive of holder installation place is determined according to the acceleration responsive value at carrier coupling body characteristic point
Value, and the pulling capacity of holder installation place is calculated；
Step 5, judge whether the pulling capacity for the holder installation place being calculated meets embedded part pulling capacity；If being calculated
The pulling capacity of holder installation place is less than the embedded part pulling capacity, then returns to step 1, until design is met the requirements.
In above-mentioned satellite carrier system dynamics response analysis method, the step 1 specifically includes：
Finite element modeling is carried out to holder, assigns material properties, boundary constraint is clamped, obtains holder in physical coordinates system
Differential equation of motion in system is：
Wherein, [M] indicates that mass of system matrix, [K] indicate that stiffness matrix, { u } indicate the dynamic respond vector of system, { f
(t) } the excitation force vector of system is indicated；
{ f (t) }={ 0 } is enabled, formula (1) is solved, is obtained：
Wherein,Indicate the corresponding vibration shape feature vector of the i-th rank mode, wiIndicate the intrinsic frequency of the i-th rank mode, t tables
Show the time；
W is obtained according to formula (2) solutioni；
If wiNot less than setpoint frequency threshold value, it is determined that holder modal analysis result meets design requirement, executes step 2；
If wiLess than setpoint frequency threshold value, then holder is redesigned.
In above-mentioned satellite carrier system dynamics response analysis method, the frequency threshold is：100Hz.
In above-mentioned satellite carrier system dynamics response analysis method, which is characterized in that the step 2 specifically includes：
Model analysis is carried out to carrier coupled system, obtains the frequency of carrier coupled system；
If the frequency of carrier coupled system is not less than setpoint frequency, it is determined that the frequency of carrier coupled system meets setting frequency
Rate executes step 3；
If the frequency of carrier coupled system is less than setpoint frequency, carrier coupled system is redesigned.
In above-mentioned satellite carrier system dynamics response analysis method, the setpoint frequency is：40Hz.
In above-mentioned satellite carrier system dynamics response analysis method, as follows again to carrier coupled system
Design：
In the case where maintaining former carriage interface design constant, support height is reduced, to improve system frequency；
Carrier coupled system is reduced to single-degree-of-freedom spring model, carrier coupled system is obtained using theoretical analysis method
Frequency, then the model to meeting the requirements carry out numerical computations review, and until meeting the requirements, the modeling time is repeated to save.
In above-mentioned satellite carrier system dynamics response analysis method, the single-degree-of-freedom spring model is：
Wherein, f indicates that frequency, k indicate that stiffness factor, m indicate quality；
Determine that the front and back combination body frequency ratio of change support height is according to formula (3)：
Wherein, h indicates that assembly height of center of mass, subscript " 1 " indicate that the state before support height change, subscript " 2 " indicate
State after support height change.
Correspondingly, the invention also discloses a kind of satellite carrier system dynamics response analysis systems, including：
First analysis module carries out model analysis according to modeling result for carrying out finite element modeling to holder to holder,
And when holder modal analysis result meets design requirement, the second analysis module is executed；
Second analysis module, for the progress model analysis of carrier coupled system, obtaining the frequency of carrier coupled system, and
When the frequency of carrier coupled system meets setpoint frequency, third analysis module is executed；
Third analysis module obtains the acceleration at carrier coupling body characteristic point and rings for carrying out model analysis to satellite
It should be worth；
4th analysis module, for determining holder installation place according to the acceleration responsive value at carrier coupling body characteristic point
Acceleration responsive value, and the pulling capacity of holder installation place is calculated；
Whether the pulling capacity of the 5th analysis module, the holder installation place for judging to be calculated meets embedded part pulling capacity；
If the pulling capacity for the holder installation place being calculated is less than the embedded part pulling capacity, returns and execute the first analysis module, until
Design is met the requirements.
The present invention has the following advantages：
Satellite main body structure and sensor supporting structure are thought of as a total system by the present invention, propose a kind of Satellite
Frame system dynamics response analysis method and system, improve satellite carrier system structure design and dynamic analysis is horizontal, full
Foot design requirement, improves the accuracy of design efficiency and design result.In addition, passing through verification experimental verification, it has therefore proved that this hair
Bright feasibility and correctness can be applied to satellite holder and secondary structure design.
Description of the drawings
Fig. 1 is a kind of schematic diagram of satellite carrier coupled system in the embodiment of the present invention；
Fig. 2 is a kind of step flow chart of satellite carrier system dynamics response analysis method in the embodiment of the present invention；
Fig. 3 is carrier coupled system numerical analysis model schematic diagram a kind of in the embodiment of the present invention.
Specific implementation mode
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with attached drawing to disclosed by the invention
Embodiment is described in further detail.
At present to the design of holder mostly using component-level payload supporting structure as research object, but work as payload branch
With after the installation of satellite main body structure, contour connection rigidity will change frame, cause the payload branch under whole starlike state
Frame structural dynamic characteristics differ larger with the structural dynamic characteristics under its component-level state.Therefore, effective for component-level
The rigidity Design that load support carries out not necessarily meets the payload stiffness of support requirement under whole starlike state, in some instances it may even be possible to can make
Payload response is further amplified.Satellite main body structure and sensor supporting structure are thought of as an entirety system by the present invention
System, proposes a kind of satellite carrier system dynamics response analysis method and system, and by verification experimental verification prove this programme can
Row and correctness can be applied to satellite holder and secondary structure design.
Referring to Fig.1, a kind of schematic diagram of satellite carrier coupled system in the embodiment of the present invention is shown.Such as Fig. 1, the satellite
Carrier coupled system is mainly made of load, holder and deck board.With reference to Fig. 2, a kind of Satellite in the embodiment of the present invention is shown
The step flow chart of frame system dynamics response analysis method.In the present embodiment, the satellite carrier system dynamics response
Analysis method, including：
Step 1, finite element modeling is carried out to holder, model analysis is carried out to holder according to modeling result, and in holder mould
When state analysis result meets design requirement, step 2 is executed.
In the present embodiment, finite element modeling can be carried out to holder, assigns material properties, boundary constraint is clamped.Holder
For a continuous elastic linear structure, it is a single-degree-of-freedom undamped-free vibration system to do sliding-model control, in object
Reason coordinate system in differential equation of motion can be：
Wherein, [M] indicates that mass of system matrix, [K] indicate that stiffness matrix, { u } indicate the dynamic respond vector of system, { f
(t) } the excitation force vector of system is indicated.
{ f (t) }={ 0 } is enabled, for linear system, the form of formula (1) solution can be：
Wherein,Indicate the corresponding vibration shape feature vector of the i-th rank mode, wiIndicate the intrinsic frequency of the i-th rank mode, t tables
Show the time.
It can solve to obtain w according to formula (2)i；Wherein, if wiNot less than setpoint frequency threshold value, it is determined that holder model analysis knot
Fruit meets design requirement, executes step 2；If wiLess than setpoint frequency threshold value, then holder is redesigned.
Preferably, the frequency threshold can with but be not limited only to for：100Hz.
Step 2, model analysis is carried out to carrier coupled system, obtains the frequency of carrier coupled system, and couple in carrier
When the frequency of system meets setpoint frequency, step 3 is executed.
In the present embodiment, in the case where step 1 meets, model analysis can be carried out to carrier coupled system, obtains star
The frequency of frame coupled system.Wherein.If the frequency of carrier coupled system is not less than setpoint frequency, it is determined that carrier coupled system
Frequency meets setpoint frequency, executes step 3；If the frequency of carrier coupled system is less than setpoint frequency, to carrier coupled system
It redesigns.
Preferably, the setpoint frequency can with but be not limited only to for：40Hz.
Preferably, in the present embodiment, support height can be reduced in the case where maintaining former carriage interface design constant,
To improve system frequency；The modeling time is repeated to save, carrier coupled system can be reduced to single-degree-of-freedom spring model, is used
Theoretical analysis method obtains carrier coupled system frequency, then the model to meeting the requirements carries out numerical computations review, until meeting
It is required that.
In the present embodiment, it is public that single-degree-of-freedom spring intrinsic frequency theoretical calculation can be used in the single-degree-of-freedom spring model
Formula is specifically as follows：
Wherein, f indicates that frequency, k indicate that stiffness factor, m indicate quality.
Determine that the front and back combination body frequency ratio of change support height is according to formula (3)：
In the present embodiment, consider influence of the carrier coupling body height of center of mass to frequency, introduce height of center of mass h.Wherein,
Subscript " 1 " indicates that the state before support height change, subscript " 2 " indicate the state after support height change.
Step 3, model analysis is carried out to satellite, obtains the acceleration responsive value at carrier coupling body characteristic point.
Step 4, the acceleration responsive of holder installation place is determined according to the acceleration responsive value at carrier coupling body characteristic point
Value, and the pulling capacity of holder installation place is calculated.
Step 5, judge whether the pulling capacity for the holder installation place being calculated meets embedded part pulling capacity；If being calculated
The pulling capacity of holder installation place is less than the embedded part pulling capacity, then returns to step 1, until design is met the requirements.
On the basis of the above embodiments, it is illustrated with reference to a specific design example.
Such as Fig. 1, model analysis is carried out to the clamped state of holder shown in Fig. 1, it is 136Hz that intrinsic frequency, which is calculated,
(being more than 100Hz), meet support Design requirement.
Dynamic response numerical analysis is carried out to carrier coupled system using finite element method, obtains carrier coupled system
Frequency is 26Hz (being less than 40Hz), is unsatisfactory for requiring, needs to redesign holder, maintains former carriage interface design constant
In the case of, it reduces support height and can effectively improve system frequency；Carrier coupled system is reduced to single-degree-of-freedom spring-loaded floating die
Type will improve front and back quality and height of center of mass (17kg, 382mm；15.3kg, 232mm) and 26Hz (original state) substitution formulas
(4), combination frequency after can must improving：f2=1.74 × 26=45.1Hz；Calculated value is carried out using numerical analysis method
Review, carrier coupling body finite element model as shown in figure 3, use numerical calculations obtain carrier coupled system intrinsic frequency for
44H, Numerical results are consistent with theoretical analysis result, demonstrate the correctness of theoretical method.
Analyzing acceleration response is carried out to whole star finite element model, obtains the acceleration responsive at carrier coupling body characteristic point
Value, result of calculation are shown in Table 1；
| Position | X is to response (unit:g/Hz) | Y-direction responds (unit:g/Hz) | Z-direction responds (unit:g/Hz) |
| Stent root installation point | 0.8/22.0 | 6.8/22.0 | 6.1/56.0 |
| Cradle top center | 2.9/76.0 | 8.8/22.0 | 6.6/56.0 |
| Cradle top edge | 3.0/76.0 | 8.8/22.0 | 7.1/56.0 |
| Load center of mass point | 3.6/76.0 | 9.3/22.0 | 6.1/56.0 |
Table 1, Y-direction load acceleration responsive result and illustrate table
Such as table 1, result of calculation shows under the conditions of full magnitude cantilever tip response 8.8g, holder office at whole star single order dominant frequency
7g or so is responded at portion's frequency, response level reduces nearly 50% before opposite brackets reduce.
By acceleration responsive value shown in table 1, carrier coupling body embedded part load is calculated, analysis shows, maximum is drawn
After recessed processing, filler being carried out when pulling out load 371N, be less than the common M4 built-in fittings bearing capacity (700N) of deck board plate, and testing
Embedded part bearing power increase, therefore embedded part can meet bearing requirements, reduce the carrier coupling body after height and meet design requirement.
On the basis of the above embodiments, the invention also discloses a kind of satellite carrier system dynamics response analysis systems
System, including：First analysis module carries out model analysis according to modeling result for carrying out finite element modeling to holder to holder,
And when holder modal analysis result meets design requirement, the second analysis module is executed；Second analysis module, for carrier coupling
Collaboration system carries out model analysis, obtains the frequency of carrier coupled system, and meet setpoint frequency in the frequency of carrier coupled system
When, execute third analysis module；Third analysis module obtains carrier coupling body characteristic point for carrying out model analysis to satellite
The acceleration responsive value at place；4th analysis module, for determining branch according to the acceleration responsive value at carrier coupling body characteristic point
The acceleration responsive value of frame installation place, and the pulling capacity of holder installation place is calculated；5th analysis module is calculated for judging
Whether the pulling capacity of obtained holder installation place meets embedded part pulling capacity；If the pulling capacity for the holder installation place being calculated is less than
The embedded part pulling capacity then returns and executes the first analysis module, until design is met the requirements.
For system embodiments, since it is corresponding with embodiment of the method, so description is fairly simple, correlation
Place referring to embodiment of the method part explanation.
Each embodiment in this explanation is described in a progressive manner, the highlights of each of the examples are with its
The difference of his embodiment, the same or similar parts between the embodiments can be referred to each other.
The above, best specific implementation mode only of the invention, but scope of protection of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.
The content that description in the present invention is not described in detail belongs to the known technology of professional and technical personnel in the field.
Claims (8)
1. a kind of satellite carrier system dynamics response analysis method, which is characterized in that including：
Step 1, finite element modeling is carried out to holder, model analysis is carried out to holder according to modeling result, and in holder mode point
When analysis result meets design requirement, step 2 is executed；
Step 2, model analysis is carried out to carrier coupled system, obtains the frequency of carrier coupled system, and in carrier coupled system
Frequency when meeting setpoint frequency, execute step 3；
Step 3, model analysis is carried out to satellite, obtains the acceleration responsive value at carrier coupling body characteristic point；
Step 4, the acceleration responsive value of holder installation place is determined according to the acceleration responsive value at carrier coupling body characteristic point, and
The pulling capacity of holder installation place is calculated；
Step 5, judge whether the pulling capacity for the holder installation place being calculated meets embedded part pulling capacity；If the holder being calculated
The pulling capacity of installation place is less than the embedded part pulling capacity, then returns to step 1, until design is met the requirements.
2. satellite carrier system dynamics response analysis method according to claim 1, which is characterized in that the step 1,
It specifically includes：
Finite element modeling is carried out to holder, assigns material properties, boundary constraint is clamped, obtains holder in physical coordinate system
Differential equation of motion be：
Wherein, [M] indicates that mass of system matrix, [K] indicate that stiffness matrix, { u } indicate the dynamic respond vector of system, { f (t) }
The excitation force vector of expression system；
{ f (t) }={ 0 } is enabled, formula (1) is solved, is obtained：
Wherein,Indicate the corresponding vibration shape feature vector of the i-th rank mode, wiThe intrinsic frequency of the i-th rank mode is indicated, when t is indicated
Between；
W is obtained according to formula (2) solutioni；
If wiNot less than setpoint frequency threshold value, it is determined that holder modal analysis result meets design requirement, executes step 2；
If wiLess than setpoint frequency threshold value, then holder is redesigned.
3. satellite carrier system dynamics response analysis method according to claim 2, which is characterized in that the frequency threshold
Value is：100Hz.
4. satellite carrier system dynamics response analysis method according to claim 1, which is characterized in that the step 2,
It specifically includes：
Model analysis is carried out to carrier coupled system, obtains the frequency of carrier coupled system；
If the frequency of carrier coupled system is not less than setpoint frequency, it is determined that the frequency of carrier coupled system meets setpoint frequency,
Execute step 3；
If the frequency of carrier coupled system is less than setpoint frequency, carrier coupled system is redesigned.
5. satellite carrier system dynamics response analysis method according to claim 4, which is characterized in that the setting frequency
Rate is：40Hz.
6. satellite carrier system dynamics response analysis method according to claim 4, which is characterized in that by walking as follows
Suddenly carrier coupled system is redesigned：
In the case where maintaining former carriage interface design constant, support height is reduced, to improve system frequency；
Carrier coupled system is reduced to single-degree-of-freedom spring model, carrier coupled system frequency is obtained using theoretical analysis method
Rate, then the model to meeting the requirements carry out numerical computations review, and until meeting the requirements, the modeling time is repeated to save.
7. satellite carrier system dynamics response analysis method according to claim 6, which is characterized in that described single free
Spending spring model is：
Wherein, f indicates that frequency, k indicate that stiffness factor, m indicate quality；
Determine that the front and back combination body frequency ratio of change support height is according to formula (3)：
Wherein, h indicates that assembly height of center of mass, subscript " 1 " indicate that the state before support height change, subscript " 2 " indicate holder
State after height change.
8. a kind of satellite carrier system dynamics response analysis system, which is characterized in that including：
First analysis module, for carrying out finite element modeling to holder, according to modeling result to holder progress model analysis, and
When holder modal analysis result meets design requirement, the second analysis module is executed；
Second analysis module obtains the frequency of carrier coupled system, and in star for carrying out model analysis to carrier coupled system
When the frequency of frame coupled system meets setpoint frequency, third analysis module is executed；
Third analysis module obtains the acceleration responsive value at carrier coupling body characteristic point for carrying out model analysis to satellite；
4th analysis module, the acceleration for determining holder installation place according to the acceleration responsive value at carrier coupling body characteristic point
Response is spent, and the pulling capacity of holder installation place is calculated；
Whether the pulling capacity of the 5th analysis module, the holder installation place for judging to be calculated meets embedded part pulling capacity；If meter
The pulling capacity of obtained holder installation place is less than the embedded part pulling capacity, then returns and execute the first analysis module, until design
It meets the requirements.
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| CN112327665A (en) * | 2020-09-29 | 2021-02-05 | 北京空间飞行器总体设计部 | Satellite large-scale component rigidity control method based on half-power bandwidth in multi-satellite transmission |
| CN112525453A (en) * | 2020-11-30 | 2021-03-19 | 北京宇航系统工程研究所 | Structural parameter design method of damping type stand-alone support |
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| CN112525453A (en) * | 2020-11-30 | 2021-03-19 | 北京宇航系统工程研究所 | Structural parameter design method of damping type stand-alone support |
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