CN101498616A - Strain feedback-based load input method in whole-satellite experiment - Google Patents
Strain feedback-based load input method in whole-satellite experiment Download PDFInfo
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- CN101498616A CN101498616A CNA2009100782648A CN200910078264A CN101498616A CN 101498616 A CN101498616 A CN 101498616A CN A2009100782648 A CNA2009100782648 A CN A2009100782648A CN 200910078264 A CN200910078264 A CN 200910078264A CN 101498616 A CN101498616 A CN 101498616A
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Abstract
The invention relates to a load input method based on strain feedback in a whole-satellite test, comprising the following steps: (1) the maximum value Nmax of support reaction of a binding surface of a satellite and a carry binding surface is ascertained; (2) the proportion relation of strain Epsilon generated between the satellite and the carry binding surface and binding surface support reaction N is ascertained; (3) according to the results of the steps (1) and (2), threshold value Epsilonmax of the strain Epsilon during the whole-satellite vibration test is ascertained; (4) during the whole-satellite vibration test, the load is input according to the change condition of the strain Epsilon generated between the satellite and the carry binding surface; and when the load is input, the strain Epsilon between the satellite and the carry binding surface, which is generated by the load input is ensured to be smaller than the threshold value Epsilonmax. The invention does not need complicated computation modules and emulation calculation and has simple operation and high load input precision.
Description
Technical field
Based on the recessed method of the input curve of load of strain feedback, be applicable to the whole star vibration test of all satellites when the present invention relates to the whole star vibration test of a kind of satellite.
Background technology
The whole star vibration test of satellite is a requisite checking project in the satellite development activity.Usually, the object of the whole star vibration test of satellite can be flight star (positive sample star), also can be structure star (first sample star).During test, satellite is placed and is connected on the shaking table, control system by shaking table is imported the Load Control signal according to the testing requirements of satellite to shaking table, and shaking table applies oscillating load for the satellite that is connected on the shaking table according to the frequency spectrum of input Load Control signal.
The frequency spectrum of shaking table input Load Control signal is by the testing requirements regulation of satellite.The testing requirements of satellite comes from the environmental baseline of carrier rocket in the emission powered phase again.The frequency spectrum of environmental baseline regulation is generally straight line in the amplitude on the spectrogram in certain frequency range, but this frequency spectrum differs sometimes and accurately gives expression to the actual conditions of carrier rocket in the emission powered phase surely, but on indivedual frequency ranges or frequency, certain deviation is arranged, make satellite in test on indivedual frequency ranges or frequency, overloading easily, bring unnecessary damage to satellite.Therefore, the frequency spectrum to the environmental baseline regulation carries out the recessed problem that often will run in the whole star vibration test of satellite that becomes on indivedual frequency ranges or frequency.
At present, the recessed method of input load commonly used when satellite is put in order the star vibration test has two kinds, a kind of is that to be according to the load-up condition of determining certain good on-board equipment that threshold value feeds back recessed, specific implementation method is on the satellite structure installed surface of this equipment vibration transducer to be installed, being no more than the load-up condition threshold value of determining this good on-board equipment with the response of this sensor is criterion, input load to this satellite is carried out FEEDBACK CONTROL, make satellite input load on some frequency range, carry out recessed, the vibration environment of this equipment exceeds former imposing a condition when avoiding whole-satellite experiment occurring, makes this apparatus overload.But this method also has its weak point, promptly when carrying out satellite input load according to the vibration environment of certain on-board equipment when recessed, will cause the border incoming quality level of the whole star of satellite to reduce, will cause the underload of on the recessed frequency range of load other all on-board equipments like this.
Another recessed method is, compare according to the result of satellite-delivery coupling analysis and the environmental baseline on satellite-delivery interface, just can carry out recessedly before the vibration test to the input load of satellite on some frequency range, usually the result of star-delivery coupling analysis is in the environmental baseline that is less than on most of frequency ranges on satellite-delivery interface.This kind method is because directly relevant with the simulation capacity of satellite-delivery model of coupling, when the local of analytical model or certain key point appearance and actual conditions do not meet, will make satellite import that load is recessed to have a very big uncertainty.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, the load input method that feeds back based on strain in the whole star vibration test that provide simple to operate, test accuracy is high.
Technical solution of the present invention is: based on the load input method of strain feedback, step is as follows in the whole-satellite experiment:
(1) determines satellite and the interface support reaction maximal value N of delivery between the interface
Max
(2) determine the strain stress that produces between satellite under the different situations and the delivery interface and the proportionate relationship of interface support reaction N;
The threshold value ε of strain stress when (3) determining the test of satellite body vibration according to the result of step (1) and step (2)
Max
(4) in satellite body vibration when test, apply input load according to the situation of change of the strain stress that produces between satellite and the delivery interface, guarantees the satellite that is caused by input load during input load and deliver strain stress between the interface less than threshold value ε
Max
Determine interface support reaction maximal value N in the described step (1)
MaxMethod be: the support reaction N that calculates satellite that the disalignment act on satellite barycenter place causes to quasi-static loads and delivery interface respectively
1, and different normal direction quasi-static loads satellite that causes and the support reaction N that delivers interface
2, then choose the maximal value of the maximal value of both sums, i.e. N as interface support reaction N
Max=MAX (N
1+ N
2).
Satellite that the described axial quasi-static loads that acts on satellite barycenter place causes and the support reaction N that delivers interface
1Computing formula be:
N
1＝Mg(kP
1-P
0)/2πR
Wherein M is the satellite gross mass, and g is the gravity acceleration constant, and R is satellite and the radius that delivers interface, P
1Be axial load factor coefficient, P
0For satellite from heavy load, k is a safety coefficient, the span of k is 1.25～1.5.
Satellite that the described normal direction quasi-static loads that acts on satellite barycenter place causes and the support reaction N that delivers interface
2Computing formula be:
N
2＝k?MHg?P
2/πR
2
Wherein M is the satellite gross mass, and g is the gravity acceleration constant, and R is satellite and the radius that delivers interface, P
2Be the normal g-load coefficient, the satellite height of center of mass of H for counting by interface, k is a safety coefficient, the span of k is 1.25～1.5.
The method of determining the proportionate relationship of strain stress and interface support reaction N in the described step (2) is: adopt vibration test under particular frequency static(al) or power, fixed frequency frequently is not more than 0.5 times of satellite natural vibration frequency, amount of acceleration fraction a, the 2.0a of input load and 4.0a are three grades during vibration test under particular frequency, at least carry out three tests for each acceleration magnitude, satellite and the strain value ε that delivers interface
a, ε
2.0aAnd ε
4.0aGet the mean value that test records data; Simultaneously by formula N
a=agM/2 π R or N
a=agMH/ π R
2Calculate satellite and the support reaction N that delivers interface when input load acceleration magnitude is a
a, in like manner obtain satellite and the support reaction N that delivers interface when input load acceleration magnitude is 2.0a, 4.0a
2.0a, N
4.0aThereby, proportionate relationship ε/N=ε of acquisition strain stress and interface support reaction N
a/ N
a=ε
2.0a/ N
2.0a=ε
4.0a/ N
4.0a, M is the satellite gross mass in the formula, and g is the gravity acceleration constant, and R is satellite and the radius that delivers interface, the satellite height of center of mass of H for being counted by interface.
The threshold value ε of strain stress when the satellite body vibration is tested in the described step (3)
MaxComputing method be: ε
Max=AN
Max, N wherein
MaxBe the interface support reaction maximal value between the satellite that calculates in the step (1) and the delivery interface, A is the satellite that calculates in the step (2) and deliver the strain stress that produces between the interface and the proportionate relationship of interface support reaction N.
The present invention's advantage compared with prior art is:
1, the inventive method is according to acting on the axial of satellite barycenter place, normal direction and horizontal quasi-static loads, calculate the maximum support reaction that this load produces at satellite-delivery interface, then near interface, paste foil gauge, pass through vibration test under particular frequency then, record the proportionate relationship of the strain value of satellite-delivery interface and corresponding satellite-delivery interface support reaction, calculate the threshold value that input load is carried out strain control, test by one to twice preview, enter official test at last, the input curve of load of realizing the strain feedback is recessed, all come from on-the-spot whole-satellite experiment actual measurement through the raw data of calculating the interface strain control threshold value institute foundation that obtains in the said process, there are not complicated computation model and simulation calculation, do not have analytical model and the incongruent situation of actual tests object, so method is simple, error is little, the precision height;
2, dynamically importing load in the inventive method is according to carrying out real-time FEEDBACK CONTROL through calculating the satellite and the delivery interface strain control threshold value that obtain at the recessed of some frequency range, avoided the test forefathers dynamically to import the recessed frequency range of load and the inaccurate situation that corresponding amplitude may be brought thereof, further improved measuring accuracy for regulation;
3, dynamically import recessed be actually whole star vibration input load recessed of load in the inventive method, therefore do not have the underload problem of on-board equipment load that the recessed frequency range of load occurs of importing in some frequency range.
Description of drawings
Fig. 1 is the theory diagram of the inventive method;
When calculating the interface support reaction for the present invention, Fig. 2 concerns synoptic diagram.
Embodiment
As shown in Figure 1, be the FB(flow block) of load input method of the present invention, its concrete steps are as follows:
The first step calculates the support reaction N that this load produces at satellite-delivery interface according to the axial quasi-static loads that acts on satellite barycenter place
1
Because acting on the axial quasi-static loads at satellite barycenter place is uniformly at the support reaction of satellite-delivery interface generation in theory, so at this axial quasi-static loads MgP with satellite barycenter place
1On average to whole interface (frame), obtain:
N
1＝MgP
1/2πR
Consider the safety coefficient of satellite, can obtain in the deadweight and the design on ground:
N
1＝Mg(kP
1-P
0)/2πR
In fact, be uniformly because act on the axial quasi-static loads at satellite barycenter place in theory at the support reaction of satellite-delivery interface generation, so N
1Be the average support reaction that produces on the interface.
Wherein: M-satellite gross mass (weight)
G-acceleration of gravity constant is got 9.8m/s
2
Interface frame, mating frame radius on R-satellite-delivery interface is pressed star-delivery nominal interface selection of dimension
P
1-axial load factor coefficient (can from the delivery handbook, find)
P
0The satellite of=1.0 hypothesis 1.0g is from heavy load
N
1-satellite-delivery interface support reaction of causing by the axial load at satellite barycenter place
The safety coefficient of k-design, relevant with the degree of ripeness of satellite and delivery, generally get 1.25 (satellite and delivery all belong to matured product) or 1.5 (satellite or delivery wherein any one for newly developing product).
Second step calculated the maximum support reaction N that this load produces at satellite-delivery interface place according to the horizontal or normal direction quasi-static loads that acts on satellite barycenter place
2
Because according to mechanics principle, act on the horizontal or normal direction quasi-static loads at satellite barycenter place, the maximum point of the support reaction that produces on satellite-delivery interface is positioned at the two ends on this direction, as shown in Figure 2, so have according to dynamic balance:
Act on the moment of flexure of the support reaction generation that distributes on the moment of flexure=interface on the interface, that is:
So N
2=MHg P
2/ π R
2,
In fact, N
2Be the maximum support reaction that produces on the interface.
Consider the safety coefficient of design, can obtain:
N
2＝k?MHg?P
2/πR
2
Wherein: M-satellite quality (weight)
G-acceleration of gravity constant 9.8m/s
2
Interface frame, mating frame radius on R-satellite-delivery interface is pressed star-delivery nominal interface selection of dimension
P
2-horizontal or normal g-load coefficient (can from the delivery handbook, find)
H-satellite height of center of mass (counting) from star-delivery interface
N
2-by satellite barycenter place laterally or the maximum support reaction at satellite-delivery interface place of causing of normal load
The safety coefficient of k-design, relevant with the degree of ripeness of satellite and delivery, generally get 1.25 (ripe) or 1.5 (developments newly).
The 3rd step was calculated maximum total support reaction.
Because act on the quasi-static loads at satellite barycenter place various working is arranged, thus should calculate maximum total support reaction by the first step and second support reaction that goes on foot the satellite-delivery interface under each operating mode that calculates, that is:
N＝N
1+N
2
Get the maximal value N of N then
Max=Max (N) is total support reaction.
Near the 4th maximum support reaction place that the step is positioned at interface laterally and the normal direction quasi-static loads produces (totally 4 positions, laterally and respectively 2 of normal direction, the maximum point of the support reaction that produces on corresponding respectively satellite-delivery interface) the stickup foil gauge.By vibration test under particular frequency, record the strain value ε of satellite-delivery interface
a(the input load that corresponding acceleration magnitude is a) and corresponding satellite-delivery interface support reaction N
aProportionate relationship.Should be taken into account different application demands and the various situations that may run into during test, test respectively at each demand and situation, to obtain the proportionate relationship under the various conditions.
Fixed frequency values frequently should be low as far as possible, the highest must not be greater than 0.5 times of whole star natural vibration frequency.The input load magnitude of vibration test under particular frequency is generally decided three grades, a, 2.0a and 4.0a.Each test is carried out three times at least, and each strain value is got the mean value ε that three tests record
a, ε
2.0aAnd ε
4.0a
When axial vibration is tested, observe the linear trend of the strain value of all four foil gauges with load change, the strain value of that foil gauge that line taking trend is best carries out next step calculating.
When horizontal or normal vibration test, to observe along the linear trend of the strain value of testing two foil gauges on the direction with load change, the strain value of that foil gauge that line taking trend is best carries out next step calculating.
Satellite-delivery interface support reaction by the following two formulas input load that to calculate corresponding acceleration magnitude be a is:
N
a=agM/2 π R, or N
a=agMH/ π R
2(definition of each parameter is ditto described in the formula)
Thereby obtain ε
a/ N
aNumerical value.In theory, for linear system, ε
a/ N
aNumerical value should with ε
2.0a/ N
2.0a, ε
4.0a/ N
4.0aThe numerical value unanimity, also should be consistent with the numerical value of ε/N under any time, if find that through experiment numerical value is inconsistent, then should adjust the position of foil gauge, make ε
a/ N
aNumerical value and ε
2.0a/ N
2.0a, ε
4.0a/ N
4.0aThe numerical value unanimity.
The threshold value ε of strain stress when the 5th step was determined the test of satellite body vibration
Max
ε
Max=ε
AN
Max/ N
A, N wherein
MaxBe the maximum interface support reaction between satellite and the delivery interface, N
AInterface support reaction when being A between satellite and the delivery interface for input load acceleration magnitude, ε
AFor with N
ACorresponding strain.ε
A/ N
AAlso be the proportionate relationship that obtains in the 4th step.ε
MaxValue be exactly the threshold value that will carry out strain control.
The 6th step, usually strain signal belonged to more weak signal on the test transmission channel, was easy to disturbedly, or was applied other noises.Therefore, before official test, get ε
Max0.25 times as the preview of the recessed control of strain control threshold value, get identify load 0.25 times as the load incoming quality level.This test carries out twice, observes the noise that whether exists in the control channel, guarantees the cleaning of FEEDBACK CONTROL passage, makes test safer.
The 7th step official test begins, and requires to load according to load input, and the strain value of FEEDBACK CONTROL foil gauge makes strain value≤ε
MaxValue, just satellite structure is no more than design load.
The content that is not described in detail in the instructions of the present invention belongs to those skilled in the art's known technology.
Claims (6)
1, the load input method that feeds back based on strain in the whole-satellite experiment is characterized in that step is as follows:
(1) determines satellite and the interface support reaction maximal value N of delivery between the interface
Max
(2) determine the strain stress that produces between satellite under the different situations and the delivery interface and the proportionate relationship of interface support reaction N;
The threshold value ε of strain stress when (3) determining the test of satellite body vibration according to the result of step (1) and step (2)
Max
(4) in satellite body vibration when test, apply input load according to the situation of change of the strain stress that produces between satellite and the delivery interface, guarantees the satellite that is caused by input load during input load and deliver strain stress between the interface less than threshold value ε
Max
2, the load input method that feeds back based on strain in the whole-satellite experiment according to claim 1 is characterized in that: determine interface support reaction maximal value N in the described step (1)
MaxMethod be: the support reaction N that calculates satellite that the disalignment act on satellite barycenter place causes to quasi-static loads and delivery interface respectively
1, and different normal direction quasi-static loads satellite that causes and the support reaction N that delivers interface
2, then choose the maximal value of the maximal value of both sums, i.e. N as interface support reaction N
Max=MAX (N
1+ N
2).
3, the load input method that feeds back based on strain in the whole-satellite experiment according to claim 2 is characterized in that: satellite that the described axial quasi-static loads that acts on satellite barycenter place causes and the support reaction N that delivers interface
1Computing formula be:
N
1＝Mg(kP
1-P
0)/2πR
Wherein M is the satellite gross mass, and g is the gravity acceleration constant, and R is satellite and the radius that delivers interface, P
1Be axial load factor coefficient, P
0For satellite from heavy load, k is a safety coefficient, the span of k is 1.25～1.5.
4, the load input method that feeds back based on strain in the whole-satellite experiment according to claim 2 is characterized in that: satellite that the described normal direction quasi-static loads that acts on satellite barycenter place causes and the support reaction N that delivers interface
2Computing formula be:
N
2＝k?MHg?P
2/πR
2
Wherein M is the satellite gross mass, and g is the gravity acceleration constant, and R is satellite and the radius that delivers interface, P
2Be the normal g-load coefficient, the satellite height of center of mass of H for counting by interface, k is a safety coefficient, the span of k is 1.25～1.5.
5, the load input method that feeds back based on strain in the whole-satellite experiment according to claim 1 and 2, it is characterized in that: the method for determining the proportionate relationship of strain stress and interface support reaction N in the described step (2) is: adopt vibration test under particular frequency static(al) or power, fixed frequency frequently is not more than 0.5 times of satellite natural vibration frequency, amount of acceleration fraction a, the 2.0a of input load and 4.0a are three grades during vibration test under particular frequency, at least carry out three tests for each acceleration magnitude, satellite and the strain value E that delivers interface
a, ε
2.0aAnd ε
4.0aGet the mean value that test records data; Simultaneously by formula N
a=agM/2 π R or N
a=agMH/ π R
2Calculate satellite and the support reaction N that delivers interface when input load acceleration magnitude is a
a, in like manner obtain satellite and the support reaction N that delivers interface when input load acceleration magnitude is 2.0a, 4.0a
2.0a, N
4.0aThereby, proportionate relationship ε/N=ε of acquisition strain stress and interface support reaction N
a/ N
a=ε
2.0a/ N
2.0a=ε
4.0a/ N
4.0a, M is the satellite gross mass in the formula, and g is the gravity acceleration constant, and R is satellite and the radius that delivers interface, the satellite height of center of mass of H for being counted by interface.
6, the load input method that feeds back based on strain in the whole-satellite experiment according to claim 1 and 2 is characterized in that: the threshold value ε of strain stress when the satellite body vibration is tested in the described step (3)
MaxComputing method be: ε
Max=AN
Max, N wherein
MaxBe the interface support reaction maximal value between the satellite that calculates in the step (1) and the delivery interface, A is the satellite that calculates in the step (2) and deliver the strain stress that produces between the interface and the proportionate relationship of interface support reaction N.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102494859A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Fixed frequency calibration test method of spacecraft vibration |
| CN102539097A (en) * | 2011-12-09 | 2012-07-04 | 北京卫星环境工程研究所 | Forecasting system for high-magnitude test condition of sinusoidal vibration test for spacecraft |
| CN103091722A (en) * | 2013-01-22 | 2013-05-08 | 中国科学院测量与地球物理研究所 | Satellite gravity inversion method based on load error analysis theory |
| CN104296897A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | Star arrow six-degree-of-freedom interface force computing method based on star arrow connecting ring strain measurement |
| CN105631179A (en) * | 2014-10-31 | 2016-06-01 | 北京宇航***工程研究所 | Carrier transient response indication method based on star satellite load couple analysis result |
| CN107782520A (en) * | 2017-09-22 | 2018-03-09 | 上海卫星工程研究所 | The recessed control method of microsatellite random vibration test |
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| CN102494859A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Fixed frequency calibration test method of spacecraft vibration |
| CN102494859B (en) * | 2011-11-15 | 2014-05-14 | 上海卫星工程研究所 | Fixed frequency calibration test method of spacecraft vibration |
| CN102539097A (en) * | 2011-12-09 | 2012-07-04 | 北京卫星环境工程研究所 | Forecasting system for high-magnitude test condition of sinusoidal vibration test for spacecraft |
| CN102539097B (en) * | 2011-12-09 | 2014-11-12 | 北京卫星环境工程研究所 | Forecasting system for high-magnitude test condition of sinusoidal vibration test for spacecraft |
| CN103091722A (en) * | 2013-01-22 | 2013-05-08 | 中国科学院测量与地球物理研究所 | Satellite gravity inversion method based on load error analysis theory |
| CN103091722B (en) * | 2013-01-22 | 2015-06-17 | 中国科学院测量与地球物理研究所 | Satellite gravity inversion method based on load error analysis theory |
| CN104296897A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | Star arrow six-degree-of-freedom interface force computing method based on star arrow connecting ring strain measurement |
| CN104296897B (en) * | 2014-09-12 | 2016-08-17 | 上海卫星工程研究所 | The satellite and the rocket six degree of freedom interfacial force computational methods of ring strain measurement are connected based on the satellite and the rocket |
| CN105631179A (en) * | 2014-10-31 | 2016-06-01 | 北京宇航***工程研究所 | Carrier transient response indication method based on star satellite load couple analysis result |
| CN105631179B (en) * | 2014-10-31 | 2018-09-28 | 北京宇航***工程研究所 | Vehicle transient response predicting method based on satellite and the rocket load coupling analysis result |
| CN107782520A (en) * | 2017-09-22 | 2018-03-09 | 上海卫星工程研究所 | The recessed control method of microsatellite random vibration test |
| CN107782520B (en) * | 2017-09-22 | 2019-08-30 | 上海卫星工程研究所 | The recessed control method of microsatellite random vibration test |
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