CN102589725B - Method for acquiring satellite temperature based on ontrack telemetry data - Google Patents
Method for acquiring satellite temperature based on ontrack telemetry data Download PDFInfo
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Abstract
A method for acquiring satellite temperature based on ontrack telemetry data includes selecting relative telemetry parameter from satellite temperature telemetry parameter, defining the relative telemetry parameter as satellite temperature simulation model reference temperature, building a reference temperature control area according to the reference temperature distribution, controlling device temperature in the area to be elements belonging to the temperature area, excavating numerical relation between the elements and the reference temperature from ontrack temperature telemetry data by utilizing mathematical statistics to form a satellite temperature relation numerical matrix, achieving acquisition of historical and current flying temperature of the whole satellite through operation between the reference temperature telemetry data and the temperature relation numerical matrix. On the basis, simulation prediction of satellite temperature in a future flying time domain can be achieved through the method for extrapolating the reference temperature. The method is simple in principle, small in operand, high in calculation accuracy, high in application performance and capable of removing a plurality of effects of uncertain factors which affects ontrack satellite heat characteristics on flying temperature prediction and providing real-time data accordance for early warning of satellite abnormal faults.
Description
Technical field
The invention belongs to satellite thermal control technical field, relate to a kind of satellite at rail flight temperature acquisition methods.
Background technology
At present, satellite temperature obtain and predict the thermoanalytical method of common employing, the thermal model that this method is set up based on satellite general layout and heat transfer theory basis, the satellite steady-state thermal analysis checking that only be adapted to design, the ground experiment stage has definite boundary condition.
Along with satellite was passed in the rail flight time, following uncertainty will appear:
1) degenerating appears in the hot rerum natura performance of satellite surface control coating layer (OSR, multilayer and thermal control lacquer etc.), and it is unpredictable in the true rule of rail performance degradation;
2) the on-board equipment heat dissipation increases along with the decline of work efficiency, and it is uncertain that it changes magnitude;
3) useful load system equipment mode of operation is because of user's applying working condition random variation, and the unknown of equipment thermal capacitance;
4) control of satellite transit target track allows to exist deviation.
Above-mentioned uncertain factor will directly influence satellite to a great extent in rail practical flight temperature transient change, therefore use thermal model and estimate that satellite will cause the error of calculation that can not estimate in rail flight temperature.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of satellite temperature acquisition methods is provided, utilize the accurately flight temperature of the whole star of portrayal of limited satellite thermal control boundary temperature telemetry, solve a difficult problem of accurately obtaining and estimating at rail mission phase satellite temperature.
Technical solution of the present invention is: a kind of based on the satellite temperature acquisition methods in the rail telemetry, step is as follows:
(1) chooses satellite thermal control boundary temperature telemetry parameter as reference temperature, described reference temperature is divided into main body reference temperature and individual reference temperature two classes, described main body reference temperature is the telethermograph of satellite structure plate inside surface, described individual reference temperature is the inside and outside telethermograph of taking autonomous temperature controlling instruments of celestial body, and takes Design on thermal insulation and its temperature to have the telethermograph of the equipment of relatively independent Changing Pattern in the star;
(2) determine main body reference temperature control domain and individual reference temperature control domain, wherein main body reference temperature control domain is to be geometric center with main body reference temperature point for measuring temperature place structural slab position coordinates, with the heat pipe network at its place or with the temperature field domain of cabin plate temperature gradient less than setting value; Individual reference temperature control domain is the temperature field domain that is made of whole individual reference temperatures; Wherein, the device temperature that has the relatively independent Changing Pattern equipment except that autonomous temperature control and temperature thereof in the main body reference temperature control domain is the element of main body reference temperature control domain, and the reference temperature of each equipment is the element of individual reference temperature control domain in the individual reference temperature control domain;
(3) for main body reference temperature control domain, utilize the historical telemetry of satellite, calculate the difference of the main body reference temperature of each main body reference temperature control domain interior element and this main body reference temperature control domain, form satellite temperature and concern numerical matrix; Utilize formula
Calculate next main body reference temperature of main body reference temperature control domain constantly, and utilize satellite temperature to concern that numerical matrix obtains the predicted temperature of each element in next moment main body reference temperature control domain, T in the formula
Mbj, tFor the reference temperature t of temperature field j indicates temperature, T constantly
Mbj, 0Be the reference temperature initial time telemetry of temperature field j, Δ Q
OutBe the space heat flux increment that temperature field j absorbs, σ is a Boltzmann constant, ε
jBe the hemispherical emissivity of temperature field j, A towards deep cooling space outside surface
jSurface area for temperature field j;
(4), utilize remote mode to obtain the temperature of each element in the individual reference temperature control domain in real time for individual reference temperature control domain; Form the basic spline cycle data of each element in the individual reference temperature territory by the corresponding arithmetic mean of historical telemetry constantly in each individual reference temperature Changing Pattern cycle, utilize the predicted temperature of basic spline cycle data match corresponding each element of individual reference temperature territory constantly of following one-period.
The present invention's advantage compared with prior art is: the inventive method distributes according to satellite heat exchange principle and telethermograph, the quantitative relation of applied satellite between rail remote temperature sensing data mining on-board equipment temperature and its installation boundary temperature, utilize the limited whole star flight of satellite thermal control boundary temperature telemetry portrayal temperature, principle is simple, operand is little, the computational accuracy height, application is strong, can eliminate the influence that many uncertain factors that influences the hot feature of satellite in orbit are estimated the flight temperature, can realize satellite in orbit history, the flight temperature simulation of current and following time domain, result of calculation can be applicable in the performance analysis of rail temperature changing regularity, diagnosis, early warning is for the early warning of satellite abnormal failure provides the real time data foundation; Also can be applicable to the satellite hot control system health evaluating, and field such as the hot feature affects analysis of satellite in orbit, provide the foundation of adjusting strategy, the safety and the life-span of whole star are played crucial effects for satellite reaches the optimum temperature environment.
The inventive method has completed successfully GEO and LEO satellite in orbit mission phase temperature computation, through simulation calculation result and telemetry relatively, and the error of calculation＜3 ℃.
Description of drawings
Fig. 1 is the FB(flow block) of the inventive method.
Embodiment
Satellite is the space environment near vacuum in orbit, so only have conduction and two kinds of heat exchange modes of radiation.The satellite structure plate is satellite temperature control border, and equipment (parts) is installed on the structural slab in the star, dispels the heat by the structural slab implementation space.According to heat exchanging relation in the star, there is certain quantitative relationship in the star between device temperature and its mounting structure plate temperature, can be briefly described as follows:
In the formula, q
E, j-equipment i thermal value (hear rate), unit: W;
T
E, iEquipment i temperature, unit: ℃;
T
SPM, jThe mounting structure plate j temperature of-equipment i, unit: ℃;
R
IjEquivalent thermal resistance between-equipment i and its mounting structure plate j, unit: ℃/W.
Can obtain by formula (1):
T
E，i＝T
SPM，j+q
E，i·R
ij (2)
Generally speaking, under the prerequisite that equipment mounting means and duty are determined, equivalent thermal resistance (R
Ij) and equipment heating amount (q
E, i) two physical quantitys are constant substantially, all can be approximately steady state value, so the two product can be handled by constant.Wherein, equivalent thermal resistance (R
Ij) be the synthesis result of thermal contact resistance and radiation thermal resistance.Therefore, when the mounting structure plate temperature of known device, can directly calculate by formula (2) and to obtain device temperature.
Based on above-mentioned principle, the inventive method is chosen relevant telemetry parameter and is defined as satellite temperature realistic model reference temperature from the satellite temperature telemetry parameter, the reference temperature control domain is set up in distribution according to reference temperature, device temperature in the control domain is the element of affiliated temperature field, the utilization mathematical statistics forms satellite temperature and concerns numerical matrix from excavate the numerical relation between element and the reference temperature rail remote temperature sensing data.By the computing between reference temperature telemetry and the temperature relation numerical matrix, realize obtaining of whole ephemeris history, current flight temperature.On this basis, by method, can realize that the emulation of following flight time domain satellite temperature is estimated to the reference temperature extrapolation.
The flow process of the inventive method as shown in Figure 1, key step is as follows:
1) satellite temperature telemetry parameter
The satellite temperature telemetry station generally is distributed in equipment casing surface and structural slab inside surface, and wherein, most of point for measuring temperature is distributed in directly measuring equipment temperature of equipment casing surface, adheres to relevant subsystem device temperature telemetry station separately; Have only the small part point for measuring temperature to be distributed in the mounting structure plate inside surface or the structural member surface of equipment, be used for satellite thermal control boundary temperature and measure, belong to thermal control or structure subsystem remote temperature sensing point.
2) definition datum temperature
According to satellite general layout and remote temperature sensing parameter distribution, therefrom choose satellite thermal control boundary temperature telemetry parameter as reference temperature, reference temperature is divided into two classes: a class is the main body reference temperature, i.e. the telethermograph of satellite thermal control border (structural slab inside surface); Another kind of is individual reference temperature, promptly takes autonomous temperature control or is subjected to equipment (parts) the housing telethermograph that the satellite body heat affecting is little and its temperature has the independent variation rule.
The main body reference temperature is generally on-board equipment and installs the corresponding structural slab temperature in zone concentratedly, in the telethermograph of satellite thermal control, structure subsystem, chooses usually, and be main body reference temperature core wherein with thermal control subsystem cabin plate telethermograph.
Individual reference temperature is because of autonomous temperature control or be subjected to that the satellite body heat affecting is little to have a relatively independent temperature changing regularity, be generally equipment (parts) temperature of the outer autonomous temperature control of star, and have special temperature control requirement to take equipment (parts) temperature of Design on thermal insulation or autonomous temperature control in the star.
3) set up the reference temperature territory
After the definition of main body reference temperature, divide main body reference temperature control area scope.Distribute according to the main body reference temperature, with main body reference temperature point for measuring temperature place structural slab position coordinates is geometric center, is main body reference temperature control domain scope (abbreviation temperature field) with the heat pipe network at its place or with cabin plate temperature gradient less than 5 ℃ temperature field domain, and equipment (except the individual reference temperature) temperature that is distributed in the temperature field is affiliated element.According to said method, the corresponding temperature field of each main body reference temperature comprises some elements in the temperature field, all elements certain definite quantitative relation of existence all and between the main body reference temperature of the territory territory in.
After the individual reference temperature definition, whole individual reference temperatures constitute a temperature field, be that some equipment with independent variation rule (being generally the equipment of taking autonomous temperature control or Design on thermal insulation) telethermograph is formed a set, wherein each individual reference temperature is called element.Different with main body reference temperature territory is that individual reference temperature territory is the existence domain reference temperature not, does not also have any association in the territory between each element.
4) temperature relation numerical matrix
The temperature relation numerical matrix calculates and only is applicable to main body reference temperature territory.According to the preamble analysis, main body reference temperature territory is by main body reference temperature class definition, element is the minimum unit of temperature field, has certain quantitative relation of determining between element and the affiliated temperature field main body reference temperature, represents quantitative relationship between the two with the element temperature increment.
Adopt the direct differentiation method of telemetry to calculate the temperature increment of element, the device temperature remote measurement value that is about to the element representative is carried out algebraically with the affiliated temperature field main body reference temperature remote measurement value of synchronization and is asked poor, its algebraically difference is the temperature increment of this element, algorithm such as formula (3).
ΔT
j，i＝TE
j，i-T
mb，j (3)
In the formula, Δ T
J, iThe temperature increment of element i among the-temperature field j, unit: ℃;
T
Ej, iThe remote temperature sensing data of element i among the-temperature field j, unit: ℃;
T
Mb, jThe main body reference temperature telemetry of-temperature field j, unit: ℃.
Generally speaking, the temperature gap of element is the sample data assembly average, when by formula calculate (3), at first intercept in rail flight time domain as length sample time, the calculating of choosing some in sample time in the length is the sampling calculation level constantly, element and the same sampling instant of its territory main body reference temperature calculated the corresponding temperature gap of sampling calculation level at rail telemetry substitution formula (3), the temperature gap of each calculation level of sampling is by the arithmetic mean value, and its arithmetic mean is the temperature increment of element.Obviously, prolong length or increase sampling sample size sample time, and encrypt the sampling calculation level and all can reduce the error of calculation of element temperature increment, but will pay the cost that calculated amount heightens for this reason.Therefore, should choose suitable length sample time, quantity of sampling quantity and sampling calculation level according to the computational accuracy requirement.
In sum, the corresponding temperature field of each main body reference temperature, the usable temp increment that concerns under main body reference temperature and its territory between the element characterizes, therefore, set up the temperature increment between whole reference temperatures and the element (equipment), form a satellite temperature and concern numerical matrix, concern that by reference temperature and satellite temperature simple operation between the numerical matrix can describe whole star temperature.Satellite temperature concerns that the numerical matrix tabulation is as shown in table 1.
Table 1 satellite temperature concerns the numerical matrix table
Annotate: n-main body reference temperature quantity; The individual reference temperature quantity of m-; I, j, k, l, p-number of elements;
T
RC, j-individual reference temperature j.
5) reference temperature extrapolation
Under the prerequisite that on-board equipment and well heater mode of operation do not change, satellite reference temperature Changing Pattern only depends on the Changing Pattern of space heat flux, and the space heat flux Changing Pattern depends on the solar absorptance (α of satellite transit track and thermal control coating
s) degenerate.α after the degeneration
sCan obtain (α in the historical telemetry computing of rail match extrapolation by reference temperature
sExtrapolation algorithm sees for details hereinafter), can be similar to constant in a short time.Therefore, according to satellite actual motion track, can accurately calculate following certain moment space heat flux numerical value and regularity of distribution in advance by theoretical formula, outer hot-fluid numerical value substitution energy conservation equation can be calculated following certain satellite reference temperature constantly, the reference temperature extrapolation is calculated as formula (4).
In the formula, T
Mbj, tThe reference temperature t of-temperature field j indicates temperature constantly, unit: ℃;
T
Mbj, 0The reference temperature initial time telemetry of-temperature field j, unit: ℃;
Δ Q
OutThe space heat flux increment that-temperature field j absorbs, unit: W;
σ-Boltzmann constant (5.67 * 10
-8W/ (m
2K
4));
ε
jThe outside surface of-temperature field j (towards the deep cooling space) hemispherical emissivity;
A
jThe surface area of-temperature field j, unit: m
2
The α of satellite in orbit thermal control coating
sThe match extrapolation algorithm is as follows:
In the historical flight of rail time domain, choose some quantity time points as α at satellite by certain time interval
sThe sampling calculation level, according to energy conservation equation by formula (5) calculate the α of each sampling time point correspondence
s, by the α of each sampling time point
sCalculated value simulates α
sThe change with time function can be extrapolated by this function and to be calculated any flight α of each temperature field thermal control coating constantly
sNumerical value.
In the formula, α
Sj, i-i moment temperature field j is towards the solar absorptance of the thermal control coating of deep cooling space outside surface;
T
Mbj, i-i is the reference temperature telemetry of temperature field j constantly, unit: ℃;
Q
Inj, iThe interior hot-fluid of-i temperature field j absorption constantly, unit: W;
Q
Ej, iThe earth light and the infrared radiation hot-fluid of-i temperature field j absorption constantly, unit: W;
σ-Boltzmann constant (5.67 * 10
-8W/ (m
2K
4));
ε
jThe outside surface of-temperature field j (towards the deep cooling space) hemispherical emissivity;
A
jThe surface area of-temperature field j, unit: m
2
S
J, i-i moment temperature field j is subjected to according to solar constant unit: W/m
2
θ
J, i-i temperature field j normal direction constantly is subjected to according to the sunray angle unit with it: °.
In formula (4), (5), outer hot-fluid (Q
Out) be generally solar irradiation heat, earth light heat and earth infrared radiation heat three part sums.When orbit altitude during, can ignore earth light heat and earth infrared radiation heat greater than 10000Km.
By the following flight of formula (4) extrapolation satellite reference temperature temperature constantly, reference temperature and the satellite temperature by extrapolation concerns that the computing between the numerical matrix can estimate to put in order the star temperature.
In addition, when on-board equipment and well heater mode of operation change, should gather operating mode satellite temperature telemetry after changing and recomputate the temperature relation numerical matrix, promptly equipment and well heater are reflected in satellite temperature to the influence of satellite temperature and concern in the numerical matrix.
Individual reference temperature has relatively independent Changing Pattern, and its temperature changing regularity generally is periodically, good reproducibility.According to each individual reference temperature Changing Pattern cyclophysis, some periods of change in satellite each individual reference temperature of intercepting in the historical flight of rail time domain, the historical telemetry of the individual reference temperature of a period of change is a sample data, with corresponding sample data arithmetic mean value constantly of each sample period, form the basic spline cycle data of individual reference temperature by each sample data arithmetic mean constantly.Obtain the basic spline cycle data of each element in the individual reference temperature territory as stated above, utilize the predicted temperature of basic spline cycle data corresponding each element of individual reference temperature territory constantly of approximate following one-period of each element of individual reference temperature territory.
Embodiment
With certain GEO satellite in orbit is example, uses the inventive method temperature simulation that flies and calculates.Because this satellite temperature measuring point quantity is more,, therefore randomly draws representative temperature measuring point (point for measuring temperature can cover whole star) and carry out method validation in view of reducing workload.
1) satellite temperature telemetry parameter
Have 142 remote temperature sensing points in the star.Wherein, thermal control subsystem remote temperature sensing point is 11, and structure subsystem remote temperature sensing point is 11.
2) definition emulation reference temperature
According to satellite general layout and remote temperature sensing parameter distribution, definition main body reference temperature and individual reference temperature, because each piece cabin plate point for measuring temperature of satellite platform part seldom or do not have a point for measuring temperature, therefore terrace part main body reference temperature is chosen representational equipment point for measuring temperature (generally choosing the device temperature that is positioned at the temperature field center), and the main body reference temperature of each piece cabin plate of satellite is as shown in table 1.Individual reference temperature is made up of battery temp, tank temperature, pipeline temperature, gas cylinder temperature, and individual reference temperature is as shown in table 2.
3) set up the reference temperature territory
With main body reference temperature point for measuring temperature position coordinates is geometric center, the heat pipe network at point for measuring temperature place or cabin plate temperature gradient are its control area less than 5 ℃ temperature field scope, the device temperature (except the individual reference temperature) that is distributed in this scope is this main body reference temperature field element, and main body reference temperature and its element corresponding relation see Table 1.
All individual reference temperature set constitute individual temperature field, and each individual reference temperature is a field element, sees table 2 for details.
Table 1 model main body reference temperature
Annotate:
*The indication equipment temperature.
The individual reference temperature of table 2 model
4) the temperature relation numerical matrix calculates
Sample time, length was the annual flight time in 2009 years, and 0:00,6:00,12:00 and 18:00 were sampling instant in 22 days every month, amounted to 48 sampling time points.Corresponding each sampling time point carries out algebraically according to formula (3) with element telemetry and its main body reference temperature telemetry and asks poor, and its difference is the temperature increment that element was put in this sampling time.With the temperature increment arithmetic mean of identity element at each sampling time point, its mean value is the temperature increment of this element.
Because satellite temperature is more, randomly draw the temperature relation numerical matrix of part reference temperature (can cover whole star) and its element, see table 3 for details.
Table 3 part reference temperature and element temperature relation numerical matrix
Annotate: T
J, iThe simulation calculation temperature of element i among the-temperature field j; T
j-temperature field j main body reference temperature is distant
Survey data; Δ T
J, iThe temperature increment of element i among the-temperature field j.
5) the satellite flight temperature simulation calculates
Reference temperature in the table 3 and element temperature relation numerical matrix are carried out computing by operation relation in the table 3, try to achieve the simulation calculation result such as the table 4 of element (equipment).
Table 4 compares in rail flight temperature simulation result of calculation and telemetry
Annotate: T
Imitative-satellite temperature simulation calculation data; T
Distant-satellite temperature telemetry; Δ T-Δ T=T
Imitative-T
Distant
By simulation calculation result in the table 4 with in rail practical flight remote temperature sensing data more as can be known: simulation calculation temperature and be 73.7% the two deviation of rail telethermograph (| Δ T|)≤1 ℃, 1 ℃＜| Δ T|≤2 ℃ are 21.1%, 2 ℃＜| Δ T|＜3 ℃ are 5.2%, and deviation is all in 3 ℃.
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 (1)
1. one kind based on the satellite temperature acquisition methods in the rail telemetry, it is characterized in that step is as follows:
(1) chooses satellite thermal control boundary temperature telemetry parameter as reference temperature, described reference temperature is divided into main body reference temperature and individual reference temperature two classes, described main body reference temperature is the telethermograph of satellite structure plate inside surface, described individual reference temperature is the inside and outside telethermograph of taking autonomous temperature controlling instruments of celestial body, and takes Design on thermal insulation and its temperature to have the telethermograph of the equipment of relatively independent Changing Pattern in the star;
(2) determine main body reference temperature control domain and individual reference temperature control domain, wherein main body reference temperature control domain is to be geometric center with main body reference temperature point for measuring temperature place structural slab position coordinates, with the heat pipe network at its place or with the temperature field domain of cabin plate temperature gradient less than setting value; Individual reference temperature control domain is to be scope by the temperature field domain that whole individual reference temperatures constitute; Wherein, the device temperature that has the relatively independent Changing Pattern equipment except that autonomous temperature control and temperature thereof in the main body reference temperature control domain is the element of main body reference temperature control domain, and the reference temperature of each equipment is the element of individual reference temperature control domain in the individual reference temperature control domain;
(3) for main body reference temperature control domain, utilize the historical telemetry of satellite, calculate the difference of the main body reference temperature of each main body reference temperature control domain interior element and this main body reference temperature control domain, form satellite temperature and concern numerical matrix; Utilize formula
Calculate next main body reference temperature of main body reference temperature control domain constantly, and utilize satellite temperature to concern that numerical matrix obtains the predicted temperature of each element in next moment main body reference temperature control domain, T in the formula
Mbj, tFor the main body reference temperature t of main body reference temperature control domain j indicates temperature, T constantly
Mbj, 0Be the main body reference temperature initial time telemetry of main body reference temperature control domain j, Δ Q
OutBe the space heat flux increment that main body reference temperature control domain j absorbs, σ is a Boltzmann constant, ε
jBe the hemispherical emissivity of main body reference temperature control domain j, A towards deep cooling space outside surface
jSurface area for main body reference temperature control domain j;
(4), utilize remote mode to obtain the temperature of each element in the individual reference temperature control domain in real time for individual reference temperature control domain; Form the basic spline cycle data of each element in the individual reference temperature territory by the corresponding arithmetic mean of historical telemetry constantly in each individual reference temperature Changing Pattern cycle, utilize the predicted temperature of basic spline cycle data match corresponding each element of individual reference temperature territory constantly of following one-period.
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| CN103698044B (en) * | 2013-12-06 | 2016-05-11 | 上海卫星工程研究所 | Temperature measurement error analytical method based on satellite temperature remote measurement |
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| CN109324648A (en) * | 2018-12-07 | 2019-02-12 | 银河航天(北京)通信技术有限公司 | A kind of method of temperature control system, spacecraft and spacecraft temperature control |
| CN109813456B (en) * | 2019-01-31 | 2021-12-07 | 中国空间技术研究院 | Semi-physical simulation measurement method and system for temperature of communication satellite load cabin equipment |
| CN110297258B (en) * | 2019-06-18 | 2021-03-09 | 中国科学院国家空间科学中心 | Monotone incremental counting type remote measurement parameter abnormity automatic discrimination method and system |
| CN110793998B (en) * | 2019-08-06 | 2022-03-04 | 北京空间飞行器总体设计部 | On-orbit correction method for spacecraft star surface material characteristic attenuation |
| CN110595017B (en) * | 2019-08-15 | 2021-05-14 | 深圳数联天下智能科技有限公司 | Air conditioner temperature setting method and device, computer equipment and storage medium |
| CN115586803A (en) * | 2021-01-11 | 2023-01-10 | 中国科学院微小卫星创新研究院 | Intelligent self-adaptive thermal control management method |
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