CN112208805A - External heat flow simulation method and device for space load - Google Patents
External heat flow simulation method and device for space load Download PDFInfo
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- CN112208805A CN112208805A CN202010917735.6A CN202010917735A CN112208805A CN 112208805 A CN112208805 A CN 112208805A CN 202010917735 A CN202010917735 A CN 202010917735A CN 112208805 A CN112208805 A CN 112208805A
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Abstract
The invention provides a method and a device for simulating external heat flow of space load, which comprises the following steps: acquiring heat flow parameters and temperature parameters related to space load according to a pre-established simulation model; performing region division on the outer surface of the space load based on the heat flow parameters and the temperature parameters to obtain a plurality of outer heat flow simulation subareas; setting electric heaters in the plurality of outer heat flow simulation subareas based on the subarea attribute information of the plurality of outer heat flow simulation subareas; the space load is placed in a space environment simulator, the electric heater is connected with the program-controlled direct-current power supply, the program-controlled direct-current power supply is used for applying input current capable of generating heating power consumption to the electric heater, and external heat flows of a plurality of external heat flow simulation subareas are obtained through simulation. The method can accurately calculate the deviation value between the actually applied external heat flow and the regulated applied external heat flow of the test while saving a large amount of test time and cost, improves the accuracy of external heat flow simulation, and can be applied to the scene of transient test.
Description
Technical Field
The invention relates to the technical field of spacecraft thermal tests, in particular to a method and a device for simulating external heat flow of space load.
Background
At present, the external heat flow simulation equipment during the spacecraft or load thermal test mostly adopts modes such as an infrared cage, an infrared lamp or a solar simulator and the like.
The infrared cage is a heat source with a single spectrum, can be made into an aircraft or a load envelope surface, but has large test workload of manufacturing, measuring and calibrating, poor heat flow transient characteristics and difficult adaptation to external heat flow simulation of complex appearance and maneuvering load. The infrared lamp array is designed as a flat plate, is not suitable for loads with different angular coefficients and complicated shapes, and is also not suitable for heat flow simulation of illuminated surfaces with different thermophysical properties. The solar simulator needs to be additionally provided with a motion simulator and an auxiliary counterweight for the maneuvering and posture change of the load; in order to simulate infrared radiation, boundary simulation needs to be added, and adding excessive maneuvering and boundary simulation conditions can increase the difficulty of the test and the complexity of the simulation.
As space technology evolves, aircraft and loads become increasingly complex. For example, the configuration of some space multi-attitude maneuvering optical electromechanical devices is complex, the attitude is variable, and due to the shielding of external heat flow, cold and black space and other devices, the temperature difference between different surfaces of the devices facing the sun and the cold and black space can reach hundreds of degrees centigrade, and the temperature distribution is extremely uneven. The optical electromechanical device has the characteristics of both an optical system and a motion mechanism, the temperature index of the optical electromechanical device is high, the configuration of the optical electromechanical device is complex, the optical electromechanical device moves relative to other parts of a star body, in order to ensure the performance of the optical system and the motion mechanism, the thermal test of the device is an important link for verifying the thermal control design of the device, and the accuracy of external heat flow simulation is the basis for verifying the effectiveness or not.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, and the method and the device for simulating the external heat flow of the space load are provided.
The technical solution of the invention is as follows:
in order to solve the technical problem, the invention provides an external heat flow simulation method of space load, which comprises the following steps:
according to a pre-established simulation model, obtaining heat flow parameters and temperature parameters related to the space load;
based on the heat flow parameters and the temperature parameters, carrying out region division on the outer surface of the space load to obtain a plurality of outer heat flow simulation subareas;
setting electric heaters of corresponding types in the plurality of outer heat flow simulation subareas based on the subarea attribute information corresponding to the plurality of outer heat flow simulation subareas;
and placing the space load in a space environment simulator, connecting the electric heater with a programmable direct-current power supply, and applying an input current capable of generating heating power consumption to the electric heater by using the programmable direct-current power supply so as to simulate and obtain the external heat flows of the plurality of external heat flow simulation subareas.
Optionally, the obtaining, according to a pre-established simulation model, a heat flow parameter and a temperature parameter associated with the space load includes:
acquiring total heat flow absorbed by the space load in a space track according to a pre-established space external heat flow simulation model;
acquiring temperature data of the space load in a space orbit and a life cycle according to a pre-established temperature field simulation model;
obtaining effective infrared radiation heat flow of the test equipment to the space load according to a pre-established test heat flow simulation model;
taking the total heat flow and the effective infrared radiation heat flow as the heat flow parameters and the temperature data as the temperature parameters.
Optionally, based on the heat flow parameter and the temperature parameter, performing region division on the outer surface of the space load to obtain a plurality of outer heat flow simulation partitions, including:
acquiring the surface shape of the outer surface of the space load;
based on the surface shape, the heat flow parameters, the temperature parameters and a preset rule, carrying out region division on the outer surface to obtain a plurality of outer heat flow simulation subareas;
the preset rules include: the adjacent rules of the areas, the same rules of the surface coating, the same rules of the main body substrate, the similar rules of the heat flow density change rules and the similar rules of the temperature.
Optionally, setting the corresponding type of electric heater in the plurality of outer heat flow simulation partitions based on the partition attribute information corresponding to the plurality of outer heat flow simulation partitions includes:
and arranging electric heaters corresponding to the partition shapes in the plurality of outer heat flow simulation partitions according to the partition shapes corresponding to the plurality of outer heat flow simulation partitions.
Optionally, placing the space load in a space environment simulator, connecting the electric heater with a programmable dc power supply, and applying an input current capable of generating heating power consumption to the electric heater by using the programmable dc power supply to simulate the external heat flow to obtain the plurality of external heat flow simulation partitions, including:
placing the space load in a space environment simulator, and connecting the electric heater with the program-controlled direct-current power supply outside the space environment simulator through a lead;
according to the test type, applying current corresponding to the test type to the electric heater through the programmable direct current power supply; wherein the current is calculated according to the electric heating power consumption of the plurality of outer heat flow simulation subareas and the resistance value of the electric heater arranged in the plurality of outer heat flow simulation subareas;
and calculating the power consumption of the electric heater according to the current, and simulating the actually applied external heat flow of the plurality of external heat flow simulation subareas according to the power consumption.
Optionally, the applying, according to the test type, a current corresponding to the test type to the electric heater by the programmed dc power supply includes:
applying transient current to the electric heater through the programmable DC power supply to simulate the segmented simulation of the external heat flow of the plurality of external heat flow simulation partitions in a track cycle if the test type is a transient test type;
and applying a steady-state current to the electric heater through the programmable direct current power supply to simulate the average external heat flow of the plurality of external heat flow simulation partitions in the orbit period under the condition that the test type is a steady-state test type.
In order to solve the above technical problem, the present invention further provides an external thermal current simulation apparatus for space load, including:
the heat flow temperature parameter acquisition module is used for acquiring heat flow parameters and temperature parameters related to the space load according to a pre-established simulation model;
the heat flow simulation subarea acquisition module is used for carrying out area division on the outer surface of the space load based on the heat flow parameters and the temperature parameters to obtain a plurality of outer heat flow simulation subareas;
the electric heater setting module is used for setting electric heaters of corresponding types in the plurality of outer heat flow simulation subareas based on the subarea attribute information corresponding to the plurality of outer heat flow simulation subareas;
and the subarea external heat flow simulation module is used for placing the space load in the space environment simulator, connecting the electric heater with a programmable direct-current power supply, and applying input current capable of generating heating power consumption to the electric heater by using the programmable direct-current power supply so as to simulate and obtain external heat flows of the plurality of external heat flow simulation subareas.
Optionally, the heat flow temperature parameter obtaining module includes:
the total heat flow obtaining unit is used for obtaining total heat flow absorbed by the space load in the space track according to a pre-established space external heat flow simulation model;
the temperature data acquisition unit is used for acquiring temperature data of the space load in a space orbit and a life cycle according to a pre-established temperature field simulation model;
the radiation heat flow obtaining unit is used for obtaining effective infrared radiation heat flow of the test equipment to the space load according to a pre-established test heat flow simulation model;
and the heat flow temperature parameter acquisition unit is used for taking the total heat flow and the effective infrared radiation heat flow as the heat flow parameters and taking the temperature data as the temperature parameters.
Optionally, the heat flow simulation partition acquiring module includes:
a surface shape acquiring unit for acquiring a surface shape of an outer surface of the space load;
the simulation subarea obtaining unit is used for carrying out regional division on the outer surface based on the surface shape, the heat flow parameters, the temperature parameters and a preset rule to obtain a plurality of outer heat flow simulation subareas;
the preset rules include: the adjacent rules of the areas, the same rules of the surface coating, the same rules of the main body substrate, the similar rules of the heat flow density change rules and the similar rules of the temperature.
Optionally, the electric heater setting module comprises:
and the electric heater setting unit is used for setting the electric heaters corresponding to the partition shapes in the plurality of outer heat flow simulation partitions according to the partition shapes corresponding to the plurality of outer heat flow simulation partitions.
Optionally, the out-of-zone heat flow determination module comprises:
the electric heater connecting unit is used for placing the space load in a space environment simulator and connecting the electric heater with the program-controlled direct-current power supply outside the space environment simulator through a lead;
the current applying unit is used for applying current corresponding to the test type to the electric heater through the program-controlled direct-current power supply according to the test type; wherein the current is calculated according to the electric heating power consumption of the plurality of outer heat flow simulation subareas and the resistance value of the electric heater arranged in the plurality of outer heat flow simulation subareas;
and the external heat flow determining unit is used for calculating the power consumption of the electric heater according to the current and simulating the power consumption to obtain the actually applied external heat flows of the external heat flow simulation subareas.
Optionally, the current applying unit includes:
the first current applying unit is used for applying transient current to the electric heater through the program-controlled direct-current power supply under the condition that the test type is a transient test type so as to simulate the sectional simulation of the external heat flow of the plurality of external heat flow simulation subareas in a track period;
and the second current applying unit is used for applying a steady-state current to the electric heater through the programmable direct-current power supply under the condition that the test type is a steady-state test type so as to simulate the average external heat flow of the plurality of external heat flow simulation partitions in the track period.
Compared with the prior art, the invention has the advantages that:
according to the scheme provided by the embodiment of the invention, the heat flow parameters and the temperature parameters associated with the space load are obtained according to the pre-established simulation model, the outer surface of the space load is subjected to regional division based on the heat flow parameters and the temperature parameters to obtain a plurality of outer heat flow simulation subareas, the electric heaters of corresponding types are arranged in the outer heat flow simulation subareas based on the subarea attribute information corresponding to the outer heat flow simulation subareas, the space load is placed in the space environment simulator, the electric heaters are connected with the program-controlled direct-current power supply, and the program-controlled direct-current power supply is used for applying the input current capable of generating heating power consumption to the electric heaters to simulate the outer heat flow of the outer heat flow simulation subareas. According to the embodiment of the invention, the electric heating power of each external heat flow simulation subarea is determined by establishing simulation models (a track external heat flow calculation model, a temperature field calculation model and a heat test heat flow calculation model) and performing external heat flow analysis calculation, an external heat flow simulation subarea method and an electric heater implementation method are provided, and the external heat flow application condition can be adjusted in time according to the calculation result. On the basis of saving a large amount of test time and cost, the external heat flow simulation method can accurately calculate the deviation value between the actually applied external heat flow and the specified applied external heat flow in the test, and improves the accuracy of external heat flow simulation.
Drawings
FIG. 1 is a flowchart illustrating steps of a method for determining an external heat flow of a space load according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of an external heat flow simulation system according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an optical communication terminal according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of an optical antenna of an optical communication terminal according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of an optical substrate and an optical element of an optical communication terminal according to an embodiment of the present invention;
fig. 6 is a schematic view of an optical enclosure assembly of an optical communication terminal according to an embodiment of the present invention;
fig. 7 is a schematic structural diagram of a two-dimensional turntable servo mechanism of an optical communication terminal according to an embodiment of the present invention;
fig. 8 is a schematic structural diagram of an external heat flow determination device for space loading according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, a flowchart illustrating steps of a method for simulating an external heat flow of a space load according to an embodiment of the present invention is shown, and as shown in fig. 1, the method may specifically include the following steps:
step 110: and acquiring heat flow parameters and temperature parameters associated with the space load according to a pre-established simulation model.
The embodiment of the invention can be applied to the scene of acquiring the external heat flow applied to the space load surface.
The simulation model refers to a pre-established model for obtaining the heat flow parameters and the temperature parameters associated with the space load, and in this embodiment, the simulation model may include an external space heat flow simulation model, a temperature field simulation model, and a test heat flow simulation model.
The heat flow parameter refers to the heat flow parameter absorbed by the outer surface of the space load, and in this embodiment, the heat flow parameter may include: direct solar radiation heat flow, solar heat flow reflected by a satellite platform and the like.
The temperature parameter refers to the temperature parameter of space load in the space orbit and the service life.
When the external heat flow of the outer surface of the space load needs to be calculated, a pre-established simulation model may be first adopted to obtain heat flow parameters and temperature parameters associated with the space load, and specifically, the following detailed description may be made in combination with the following specific implementation manner.
In a specific implementation manner of the present invention, the step 110 may include:
substep A1: acquiring total heat flow absorbed by the space load in a space track according to a pre-established space external heat flow simulation model;
substep A2: acquiring temperature data of the space load in a space orbit and a life cycle according to a pre-established temperature field simulation model;
substep A3: obtaining effective infrared radiation heat flow of the test equipment to the space load according to a pre-established test heat flow simulation model;
substep A4: taking the total heat flow and the effective infrared radiation heat flow as the heat flow parameters and the temperature data as the temperature parameters.
In the embodiment of the present invention, the process of obtaining the heat flow parameter and the temperature parameter can be divided into the following three steps:
1. the method comprises the steps of establishing a space external heat flow simulation model of the space load, wherein the model comprises a space cold and black background, an aircraft, a load and heat related components, and calculating solar direct radiation heat flow Q1, earth albedo heat flow Q2 and earth infrared radiation heat flow Q3 of the space load in a space orbit and a service life by using the space external heat flow simulation model. For the load on the aircraft, the other aircraft reflects solar heat flow Q4, aircraft reflects infrared heat flow Q5, and infrared radiation heat flow Q6 of other heat-related equipment of the aircraft. And calculating the heat flux density of the heat flux. The aircraft or load absorbs a total heat flow Qin in the space trajectory, which is the sum of the above heat flows, i.e. the total heat flow, which can be used as a heat flow parameter.
2. And establishing a temperature field simulation model of the space load, and calculating temperature data of the space load in the space orbit and the service life by using the temperature field simulation model, wherein the temperature data can be used as temperature parameters.
3. And establishing a test heat flow simulation model of the space load integrated with the ground test tool in the space environment simulator, and calculating effective infrared radiation heat flow Qg of the test equipment such as the heat sink and the test tool on the aircraft or the load, wherein the effective infrared radiation heat flow Qg is also used as a heat flow parameter.
After the heat flow parameters and temperature parameters associated with the space load are obtained according to the pre-established simulation model, step 120 is performed.
Step 120: and carrying out region division on the outer surface of the space load based on the heat flow parameters and the temperature parameters to obtain a plurality of outer heat flow simulation subareas.
After obtaining the temperature parameter and the heat flow parameter, the outer surface of the space load may be subjected to area division in combination with the temperature parameter and the heat flow parameter to obtain a plurality of outer heat flow simulation partitions, which may be described in detail in combination with the following specific implementation manner.
In a specific implementation manner of the present invention, the step 120 may include:
substep B1: obtaining a surface shape of an outer surface of the space load.
In the present embodiment, the surface shape refers to the shape of the outer surface of the space load.
When the outer surface of the space load is partitioned, the surface shape of the outer surface of the space load may be acquired, and sub-step B2 may be performed.
Substep B2: and carrying out region division on the outer surface based on the surface shape, the heat flow parameters, the temperature parameters and a preset rule to obtain a plurality of outer heat flow simulation subareas.
In this embodiment, the preset rule may include: the adjacent rules of the areas, the same rules of the surface coating, the same rules of the main body substrate, the similar rules of the heat flow density change rules and the similar rules of the temperature.
After the surface shape of the outer surface of the space load is obtained, the outer surface can be divided into a plurality of outer heat flow simulation subareas by area division based on the surface shape, heat flow parameters, temperature parameters and preset rules, and specifically, the surface is divided into a plurality of outer heat flow simulation subareas according to the principle that the areas are adjacent, the surface coatings are the same, the main body base materials are the same, the heat flow density change rules are similar, and the temperatures are similar by combining the surface shape and the surface absorption total heat flow and the temperatures of each part of the space load.
Wherein the' change rule of heat flux density is similar, namely that the change trends of the heat flux density at all positions of the surface of the subarea are the same, and the unevenness (qmax-qmin)/(qmax + qmin) of the periodically and averagely absorbed heat flux is less than 0.1. In the above formula, qmax is the maximum heat flow density of the partition surface, and qmin is the minimum heat flow density of the partition surface.
Wherein the 'similar temperatures' are generally the maximum temperature difference Tmax-Tmin of the temperatures at all positions on the surface of the partition and less than 3 ℃; for parts with high temperature stability requirements, if the temperature fluctuation of the track is required to be less than n ℃, the temperature is similar, namely the maximum temperature difference Tmax-Tmin of the temperature at each position of the surface of the subarea is less than n/2 ℃; for parts with high temperature uniformity requirements, if the temperature gradient of the track is required to be less than m ℃, the temperature is similar, namely the temperature at each position of the surface of the subarea Tmax-Tmin is less than m/2 ℃. In the above formula, Tmax is the maximum temperature of the partition surface, and Tmin is the minimum temperature of the partition surface.
After the outer surface of the space load is zoned to obtain a plurality of outer heat flow simulation zones, step 130 is performed.
Step 130: and setting electric heaters of corresponding types in the plurality of outer heat flow simulation subareas based on the subarea attribute information corresponding to the plurality of outer heat flow simulation subareas.
The partition attribute information refers to attribute information of the external heat flow simulation partition, and specifically, the partition attribute information may include attribute information of a material, a shape, and the like of the simulation partition.
After the outer surface of the space load is divided into the plurality of outer heat flow simulation partitions, the electric heaters of corresponding types may be set in the plurality of outer heat flow simulation partitions according to partition attribute information of the plurality of outer heat flow simulation partitions, and specifically, detailed description may be made in conjunction with the following specific implementation manner.
In a specific implementation manner of the present invention, the step 130 may include:
substep C1: and arranging electric heaters corresponding to the partition shapes in the plurality of outer heat flow simulation partitions according to the partition shapes corresponding to the plurality of outer heat flow simulation partitions.
In the embodiment of the invention, the electric heater is arranged on the surface of each external heat flow simulation subarea, and the power consumption Q of the electric heater of each external heat flow simulation subarea is the total heat flow absorbed by each part in the region minus the effective infrared radiation heat flow of the ground test equipment, namely Q is Qin-Qg.
The electric heater consists of an electric heating element, an insulating layer and a lead. According to different shapes of the space load surface, the electric heater can be packaged into a film type electric heating sheet, an electric heating wire and the like so as to be conveniently attached to the aircraft or the load surface.
And for the surface of the coated multilayer heat insulation assembly, the heating sheet is adhered to a film with the same hemispherical emissivity as the multilayer heat insulation assembly, and then the film is fixed on the outer surface of the multilayer heat insulation assembly, wherein the film faces outwards.
For the surface of the overcoating, the following can be chosen:
sticking the heating sheet on the simulated surface, and spraying a paint type substitute coating with the same hemispherical emissivity on the outer surface;
for a member having a high thermal conductivity such as a copper alloy, an aluminum alloy, or a magnesium alloy as a base material, the heater chip may be attached to the peripheral or back surface region of the member, for example, if the influence of the positional deviation of heat flow on the temperature distribution is small or the difference in the temperature field of the member is not concerned.
For optical lenses, a heat patch may be affixed to the adjacent barrel surface.
For the rod-shaped member, a heating wire or a band-shaped heating tape can be selected for winding.
For the cable (bundle), the heating wire may be wound or built in the cable (bundle).
After the corresponding type of electric heater is set in the plurality of external heat flow simulation partitions, step 140 is performed.
Step 140: and placing the space load in a space environment simulator, connecting the electric heater with a programmable direct-current power supply, and applying an input current capable of generating heating power consumption to the electric heater by using the programmable direct-current power supply so as to simulate and obtain the external heat flows of the plurality of external heat flow simulation subareas.
After the electric heaters of corresponding types are arranged in the plurality of outer heat flow simulation subareas, the electric heaters can be arranged in the space simulation environment device and connected with a program-controlled direct-current power supply outside the space simulation environment device through leads, and input current capable of generating heating power consumption is applied to the electric heaters by utilizing the program-controlled direct-current power supply, so that the outer heat flows of the plurality of outer heat flow simulation subareas can be simulated. In particular, the detailed description may be combined with the following specific implementations.
In a specific implementation manner of the present invention, the step 140 may include:
substep D1: and placing the space load in a space environment simulator, and connecting the electric heater with the program-controlled direct-current power supply outside the space environment simulator through a lead.
In this embodiment, after disposing the electric heaters in the plurality of external heat flow simulation partitions of the space load, the space load may be disposed in the space environment simulator, and the electric heaters may be connected to the programmable dc power supply outside the space environment simulator through the leads, so as to perform sub-step D2.
Substep D2: according to the test type, applying current corresponding to the test type to the electric heater through the programmable direct current power supply; wherein the current is calculated according to the electric heating power consumption of the plurality of outer heat flow simulation subareas and the resistance value of the electric heater arranged in the plurality of outer heat flow simulation subareas.
After the electric heater is connected with a program-controlled direct-current power supply outside the space environment simulator through a lead, current corresponding to the test type can be applied to the electric heater through the program-controlled direct-current power supply according to the test type, specifically, when the test type is a transient test type, the program-controlled direct-current power supply outputs transient current to control the power consumption of the electric heater, transient external heat flow simulation of each simulation partition is performed in a segmented mode, the more segments in a track period are, the closer to the real external heat flow change is, and the specific number of segments needs to be combined with the heat capacity of space load so as to meet the engineering target. And when the test type is a steady-state test type, the program-controlled direct-current power supply outputs steady-state current to control the power consumption of the electric heater, and the track period average external heat flow simulation of each simulation subarea is carried out.
In the embodiment, the current applied to each external heat flow simulation subarea by the program-controlled direct current power supply is calculated according to the electric heating power consumption Q of the external heat flow simulation subarea and the resistance value R of an electric heater arranged in the external heat flow simulation subarea,
in the process of testing, corresponding current can be applied to the external heat flow simulation subarea through the program-controlled direct-current power supply according to the calculated current I value. The present embodiment determines the actually applied external heat flow by monitoring the applied current I in real time and calculating the actually applied power consumption. The deviation value of the actually applied external heat flow and the theoretically regulated applied external heat flow shows the accuracy of the applied external heat flow, and if the deviation is too large, the adjustment can be intervened in time.
After applying a current corresponding to the test type to the electric heater by the programmed dc power supply, substep D3 is performed.
Substep D3: and calculating the power consumption of the electric heater according to the current, and simulating and obtaining the actually applied external heat flow of the plurality of external heat flow simulation subareas according to the power consumption.
After the current corresponding to the test type is applied to the electric heater through the program control direct current power supply, the power consumption of the electric heater can be calculated, the external heat flows of the plurality of external heat flow simulation partitions can be determined according to the power consumption, and specifically, the accuracy of external heat flow simulation of the space load thermal test can be evaluated according to actual conditions of an external heat flow simulation system in the test, a vacuum low-temperature system and the like in combination with the test simulation of the external heat flows and the calculation of the external heat flows.
The external heat flow simulation method provided by the invention overcomes the defects that the existing non-contact external heat flow simulation method cannot accurately simulate transient and variable external heat flows, cannot adapt to complex and maneuvering loads, is not economical and difficult to realize, can accurately simulate the energy distribution of the external heat flows borne by various complex space aircrafts or loads on rails, and has the advantages of high simulation precision, good uniformity, good transient characteristic, high realizability, good universality and the like.
The invention is an external heat flow simulation method combining calculation and test, which can greatly save the test cost and has good economical efficiency. In the thermal test of the GEO theodolite type optical communication terminal, compared with a test method using a solar simulator, the test cost is saved by 70%.
According to the external heat flow simulation method provided by the invention, the deviation value between the actually applied external heat flow and the regulated applied external heat flow is obtained through the calculation and test comparison results, and the accuracy of external heat flow simulation is improved compared with the traditional external heat flow simulation method. The thermal test result of the GEO theodolite type optical communication terminal shows that: in designed transient and steady test working conditions, the deviation between the external heat flow simulation result and the calculated external heat flow is less than 5 percent; the temperature is predicted by using the thermal simulation model corrected by the test result, compared with the on-rail temperature, the deviation of 81% temperature measuring points is less than 4 ℃, and the deviation of other parts is within 6 ℃, so that the effectiveness of the external heat flow simulation method is further explained.
In the embodiment of the present invention, an external heat flow simulation method for a thermal balance test of an optical communication terminal may be designed, and specifically, the following description may be performed in conjunction with fig. 2 to 7.
Next, the structure provided by the embodiment of the present invention is described below with reference to fig. 2 to 7.
Referring to fig. 2, a schematic structural diagram of an external thermal current simulation system according to an embodiment of the present invention is shown, and as shown in fig. 2, the external thermal current simulation system may include a space environment simulator, a program-controlled dc power supply, a computer, an external thermal current simulation circuit, a tool holder, an electric heater, and a satellite, where the program-controlled dc current is disposed outside the space environment simulator, the computer is connected to the space environment simulator, and is connected to the external thermal current simulation circuit through a wall-penetrating flange, the tool holder is used to support the satellite, the spacecraft, the electric heater, and the like, the electric heater is disposed on an outer surface of the spacecraft, and the external thermal current simulation circuit is connected to the outer surface of the spacecraft to provide electric power to the spacecraft, and when performing external thermal current simulation, the spacecraft may be placed in the space environment simulator for testing.
Referring to fig. 3, a schematic structural diagram of an optical communication terminal according to an embodiment of the present invention is shown, and as shown in fig. 3, the optical communication terminal includes an optical communication 101, an optical platform 102, and a two-dimensional turntable servo 103.
Referring to fig. 4, a schematic structural diagram of an optical antenna of an optical communication terminal according to an embodiment of the present invention is shown, and as shown in fig. 4, the optical antenna may include: the optical lens comprises an optical lens barrel 1, an optical primary mirror 2, an optical substrate 3, a secondary mirror mounting base 4, an optical secondary mirror 5, a secondary mirror bracket 6, a light shield 11 and a telescope lens barrel 12.
Referring to fig. 5, a schematic structural diagram of an optical substrate and an optical element of an optical communication terminal according to an embodiment of the present invention is shown, as shown in fig. 5, 4 is an optical substrate, 401 is a CCD (Charge-coupled Device), and 402 is an optical platform.
Referring to fig. 6, there is shown a schematic structural diagram of an optical enclosure of an optical communication terminal according to an embodiment of the present invention, as shown in fig. 6, the structure of the optical enclosure is 503.
Referring to fig. 7, a schematic structural diagram of a two-dimensional turntable servo mechanism of an optical communication terminal according to an embodiment of the present invention is shown, and as shown in fig. 7, the two-dimensional turntable servo mechanism may include: the device comprises an O frame 10, a U frame 20, an azimuth axis motor 30, an azimuth axis code wheel 40, a pitch axis motor 50 and a pitch axis code wheel 60.
First, a simulation model of the optical communication terminal, including an external heat flow simulation model and a temperature simulation model, can be established. Under each working condition, the heat flow of the terminal which absorbs direct solar radiation, the heat flow of the satellite platform which reflects the solar radiation, the infrared radiation heat flow of the satellite platform to the optical terminal, the heat flow density of the heat flow and the temperature of each part are calculated.
And establishing a test heat flow simulation model. And calculating to obtain the heat sink absorbed by the outer surface of the terminal and the effective infrared radiation heat flow of the test tool.
According to the principle that areas are adjacent, surface coatings are the same, main body substrates are the same, heat flux density change rules are similar, and temperatures are similar, the simulation of heat flux outside the terminal is divided into 67 subareas, wherein the OSR heat dissipation surface of the azimuth axis motor is divided into 1 heating subarea, and the multilayer coating subarea is divided into 4 heating subareas; the OSR radiating surface of the azimuth axis coded disc is divided into 1 heating subarea, the F46 radiating surface is divided into 1 heating subarea, and the multilayer coating subarea is divided into 4 heating subareas; the OSR heat dissipation surface of the pitch axis motor is divided into 1 heating subarea, and the multilayer coating subarea is divided into 4 heating subareas; the OSR radiating surface of the pitch shaft coded disc is divided into 1 heating subarea, and the multilayer coating subarea is divided into 4 heating subareas; the multilayer coating area of the O frame is 14 heating areas; the multilayer coating layer of the U frame is divided into 7 heating subareas; the OSR radiating surface of the optical sealing cover is divided into 1 heating subarea, and the multilayer coating subarea is divided into 4 heating subareas; the multilayer coating area of the outer ring of the back surface of the optical substrate is divided into 4 heating areas; the outer surface of the telescope tube is coated in multiple layers and divided into 4 heating subareas; the inner surface of the telescope tube is coated with black extinction paint and divided into 4 heating subareas; the outer surface of the light shield is an F46 radiating surface and is divided into 8 heating subareas.
And calculating the power consumption Q of each external heat flow analog partition electric heater.
And (3) selecting a film type electric heating sheet type external heat flow simulator, designing the shape of the heating sheet and implementing. The adaptive design is carried out on different surfaces, and the specific description is as follows:
(1) for the surface condition of the multi-layer thermal insulation assembly, the heating sheet is adhered to the polyimide film and then hung on the outer surface of the multi-layer thermal insulation assembly, and the polyimide film faces outwards. Simulating the external heat flow absorbed by the multiple layers.
(2) For the heat dissipation surface to which the OSR sheet (F46 film) is attached, two measures are taken to simulate the external heat flow absorbed by the heat dissipation surface, depending on whether the heat patch can be attached to the back surface: a) sticking a heating sheet on the back surface of the heat dissipation surface, and sticking an OSR sheet (F46 film) on the front surface according to the original design; b) the heating plate is pasted on the simulated surface, and the OSR replacing coating (F46 film replacing coating) is sprayed on the outer surface.
(3) The heating plate is adhered in a groove of the extinction ring, and the external surface is sprayed with extinction paint to simulate external heat flow absorbed by the extinction ring.
(4) For optical components such as the primary and secondary mirrors which cannot break the surface state, external heat flow is absorbed and applied to the inner surface of the lens barrel.
The electric heater is connected to a program-controlled direct-current power supply outside the space environment simulator through a through-wall flange by a cable, and the program-controlled direct-current power supply is connected with a computer.
Heat balance test designs 4 high and low temperature extreme test working conditions
And for the steady-state working condition, applying the track cycle integral average outer heat flow or the integral average heat flow in the time period according to the power consumption of the heating plate calculated in the step 4).
And for the quasi-transient working condition, when the external heat flow is applied, the integral average external heat flow is applied in a stepped manner by taking 30min as a time period, and the cyclic test of a plurality of periods is repeated until the temperature field at the terminal is stable in period.
The external heat flow application result has decisive significance on the accuracy of the thermal test verification, and the deviation between the applied external heat flow and the theoretical external heat flow is obtained according to the actual current change, the low-temperature heat sink temperature and the test tool temperature. And evaluating the accuracy of the external heat flow simulation of the terminal test, wherein the external heat flow deviation of each part is within the range of 0.4-5%.
According to the external heat flow simulation method of the space load, provided by the embodiment of the invention, the heat flow parameters and the temperature parameters related to the space load are obtained according to the pre-established simulation model, the outer surface of the space load is subjected to region division based on the heat flow parameters and the temperature parameters to obtain a plurality of external heat flow simulation subareas, the electric heaters of corresponding types are arranged in the plurality of external heat flow simulation subareas based on the subarea attribute information corresponding to the plurality of external heat flow simulation subareas, the space load is placed in the space environment simulator, the electric heaters are connected with the program-controlled direct current power supply, and the program-controlled direct current power supply is used for applying the input current capable of generating heating power consumption to the electric heaters so as to simulate the external heat flow of the plurality of external heat flow simulation subareas. According to the embodiment of the invention, the electric heating power of each external heat flow simulation subarea is determined by establishing simulation models (a track external heat flow calculation model, a temperature field calculation model and a heat test heat flow calculation model) and performing external heat flow analysis calculation, an external heat flow simulation subarea method and an electric heater implementation method are provided, and the external heat flow application condition can be adjusted in time according to the calculation result. On the basis of saving a large amount of test time and cost, the external heat flow simulation method can accurately calculate the deviation value between the actually applied external heat flow and the specified applied external heat flow in the test, and improves the accuracy of external heat flow simulation.
Referring to fig. 8, a schematic structural diagram of an external heat flow simulation apparatus for space loading according to an embodiment of the present invention is shown, and as shown in fig. 8, the apparatus may specifically include the following modules:
a heat flow temperature parameter obtaining module 810, configured to obtain a heat flow parameter and a temperature parameter associated with the space load according to a pre-established simulation model;
a heat flow simulation partition obtaining module 820, configured to perform area division on the outer surface of the space load based on the heat flow parameter and the temperature parameter, so as to obtain a plurality of outer heat flow simulation partitions;
the electric heater setting module 830 is configured to set electric heaters of corresponding types in the plurality of outer heat flow simulation partitions based on partition attribute information corresponding to the plurality of outer heat flow simulation partitions;
and the subarea external heat flow simulation module 840 is used for placing the space load in the space environment simulator, connecting the electric heater with a programmable direct-current power supply, and applying input current capable of generating heating power consumption to the electric heater by using the programmable direct-current power supply so as to simulate and obtain external heat flows of the plurality of external heat flow simulation subareas.
Optionally, the heat flow temperature parameter obtaining module 810 includes:
the total heat flow obtaining unit is used for obtaining total heat flow absorbed by the space load in the space track according to a pre-established space external heat flow simulation model;
the temperature data acquisition unit is used for acquiring temperature data of the space load in a space orbit and a life cycle according to a pre-established temperature field simulation model;
the radiation heat flow obtaining unit is used for obtaining effective infrared radiation heat flow of the test equipment to the space load according to a pre-established test heat flow simulation model;
and the heat flow temperature parameter acquisition unit is used for taking the total heat flow and the effective infrared radiation heat flow as the heat flow parameters and taking the temperature data as the temperature parameters.
Optionally, the heat flow simulation partition acquiring module 820 includes:
a surface shape acquiring unit for acquiring a surface shape of an outer surface of the space load;
the simulation subarea obtaining unit is used for carrying out regional division on the outer surface based on the surface shape, the heat flow parameters, the temperature parameters and a preset rule to obtain a plurality of outer heat flow simulation subareas;
the preset rules include: the adjacent rules of the areas, the same rules of the surface coating, the same rules of the main body substrate, the similar rules of the heat flow density change rules and the similar rules of the temperature.
Optionally, the electric heater setting module 830 includes:
and the electric heater setting unit is used for setting the electric heaters corresponding to the partition shapes in the plurality of outer heat flow simulation partitions according to the partition shapes corresponding to the plurality of outer heat flow simulation partitions.
Optionally, the out-of-zone heat flow simulation module 840 comprises:
the electric heater connecting unit is used for placing the space load in a space environment simulator and connecting the electric heater with the program-controlled direct-current power supply outside the space environment simulator through a lead;
the current applying unit is used for applying current corresponding to the test type to the electric heater through the program-controlled direct-current power supply according to the test type; wherein the current is calculated according to the electric heating power consumption of the plurality of outer heat flow simulation subareas and the resistance value of the electric heater arranged in the plurality of outer heat flow simulation subareas.
And the external heat flow determining unit is used for calculating the power consumption of the electric heater according to the current and simulating the power consumption to obtain the actually applied external heat flows of the external heat flow simulation subareas.
Optionally, the current applying unit includes:
the first current applying unit is used for applying transient current to the electric heater through the program-controlled direct-current power supply under the condition that the test type is a transient test type so as to simulate the sectional simulation of the external heat flow of the plurality of external heat flow simulation subareas in a track period;
and the second current applying unit is used for applying a steady-state current to the electric heater through the programmable direct-current power supply under the condition that the test type is a steady-state test type so as to simulate the average external heat flow of the plurality of external heat flow simulation partitions in the track period.
According to the external heat flow simulation device for the space load, provided by the embodiment of the invention, the heat flow parameters and the temperature parameters associated with the space load are obtained according to the pre-established simulation model, the outer surface of the space load is subjected to region division based on the heat flow parameters and the temperature parameters to obtain a plurality of external heat flow simulation subareas, the electric heaters of corresponding types are arranged in the plurality of external heat flow simulation subareas based on the subarea attribute information corresponding to the plurality of external heat flow simulation subareas, the space load is placed in the space environment simulator, the electric heaters are connected with the program-controlled direct-current power supply, and the program-controlled direct-current power supply is used for applying the input current capable of generating heating power consumption to the electric heaters so as to simulate the external heat flows of the plurality of external heat flow simulation subareas. According to the embodiment of the invention, the electric heating power of each external heat flow simulation subarea is determined by establishing simulation models (a track external heat flow calculation model, a temperature field calculation model and a heat test heat flow calculation model) and performing external heat flow analysis calculation, an external heat flow simulation subarea method and an electric heater implementation method are provided, and the external heat flow application condition can be adjusted in time according to the calculation result. On the basis of saving a large amount of test time and cost, the external heat flow simulation method can accurately calculate the deviation value between the actually applied external heat flow and the specified applied external heat flow in the test, and improves the accuracy of external heat flow simulation.
While the present invention has been described with reference to the embodiments shown in the drawings, the present invention is not limited to the embodiments, which are illustrative and not restrictive, and it will be apparent to those skilled in the art that various changes and modifications can be made therein without departing from the spirit and scope of the invention as defined in the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (12)
1. A method of external heat flow simulation of space loading, comprising:
according to a pre-established simulation model, obtaining heat flow parameters and temperature parameters related to the space load;
based on the heat flow parameters and the temperature parameters, carrying out region division on the outer surface of the space load to obtain a plurality of outer heat flow simulation subareas;
setting electric heaters of corresponding types in the plurality of outer heat flow simulation subareas based on the subarea attribute information corresponding to the plurality of outer heat flow simulation subareas;
and placing the space load in a space environment simulator, connecting the electric heater with a programmable direct-current power supply, and applying an input current capable of generating heating power consumption to the electric heater by using the programmable direct-current power supply so as to simulate and obtain the external heat flows of the plurality of external heat flow simulation subareas.
2. The method of claim 1, wherein obtaining heat flow parameters and temperature parameters associated with the space load according to a pre-established simulation model comprises:
acquiring total heat flow absorbed by the space load in a space track according to a pre-established space external heat flow simulation model;
acquiring temperature data of the space load in a space orbit and a life cycle according to a pre-established temperature field simulation model;
obtaining effective infrared radiation heat flow of the test equipment to the space load according to a pre-established test heat flow simulation model;
taking the total heat flow and the effective infrared radiation heat flow as the heat flow parameters and the temperature data as the temperature parameters.
3. The method of claim 1, wherein the regionalizing the outer surface of the space load based on the heat flow parameter and the temperature parameter to obtain a plurality of outer heat flow simulation partitions comprises:
acquiring the surface shape of the outer surface of the space load;
based on the surface shape, the heat flow parameters, the temperature parameters and a preset rule, carrying out region division on the outer surface to obtain a plurality of outer heat flow simulation subareas;
the preset rules include: the adjacent rules of the areas, the same rules of the surface coating, the same rules of the main body substrate, the similar rules of the heat flow density change rules and the similar rules of the temperature.
4. The method of claim 1, wherein the setting of the corresponding type of electric heater in the plurality of outer heat flow simulation partitions based on the partition property information corresponding to the plurality of outer heat flow simulation partitions comprises:
and arranging electric heaters corresponding to the partition shapes in the plurality of outer heat flow simulation partitions according to the partition shapes corresponding to the plurality of outer heat flow simulation partitions.
5. The method of claim 1, wherein said placing said space load in a space environment simulator and connecting said electric heater to a programmable dc power supply, and applying an input current capable of generating heating power consumption to said electric heater using said programmable dc power supply to simulate said external heat flow to said plurality of external heat flow simulation zones, comprises:
placing the space load in a space environment simulator, and connecting the electric heater with the program-controlled direct-current power supply outside the space environment simulator through a lead;
according to the test type, applying current corresponding to the test type to the electric heater through the programmable direct current power supply; wherein the current is calculated according to the electric heating power consumption of the plurality of outer heat flow simulation subareas and the resistance value of the electric heater arranged in the plurality of outer heat flow simulation subareas;
and calculating the power consumption of the electric heater according to the current, and simulating the actually applied external heat flow of the plurality of external heat flow simulation subareas according to the power consumption.
6. The method of claim 5, wherein said applying a current to the electric heater corresponding to a type of test by the programmed DC power supply according to the type of test comprises:
applying transient current to the electric heater through the programmable DC power supply to simulate the segmented simulation of the external heat flow of the plurality of external heat flow simulation partitions in a track cycle if the test type is a transient test type;
and applying a steady-state current to the electric heater through the programmable direct current power supply to simulate the average external heat flow of the plurality of external heat flow simulation partitions in the orbit period under the condition that the test type is a steady-state test type.
7. An external heat flow simulator for space loading, comprising:
the heat flow temperature parameter acquisition module is used for acquiring heat flow parameters and temperature parameters related to the space load according to a pre-established simulation model;
the heat flow simulation subarea acquisition module is used for carrying out area division on the outer surface of the space load based on the heat flow parameters and the temperature parameters to obtain a plurality of outer heat flow simulation subareas;
the electric heater setting module is used for setting electric heaters of corresponding types in the plurality of outer heat flow simulation subareas based on the subarea attribute information corresponding to the plurality of outer heat flow simulation subareas;
and the subarea external heat flow simulation module is used for placing the space load in the space environment simulator, connecting the electric heater with a programmable direct-current power supply, and applying input current capable of generating heating power consumption to the electric heater by using the programmable direct-current power supply so as to simulate and obtain external heat flows of the plurality of external heat flow simulation subareas.
8. The apparatus of claim 7, wherein the heat flow temperature parameter acquisition module comprises:
the total heat flow obtaining unit is used for obtaining total heat flow absorbed by the space loader in the space track according to a pre-established space external heat flow simulation model;
the temperature data acquisition unit is used for acquiring temperature data of the space load in a space orbit and a life cycle according to a pre-established temperature field simulation model;
the radiation heat flow obtaining unit is used for obtaining effective infrared radiation heat flow of the test equipment to the space load according to a pre-established test heat flow simulation model;
and the heat flow temperature parameter acquisition unit is used for taking the total heat flow and the effective infrared radiation heat flow as the heat flow parameters and taking the temperature data as the temperature parameters.
9. The apparatus of claim 7, wherein the heat flow simulation partition acquisition module comprises:
a surface shape acquiring unit for acquiring a surface shape of an outer surface of the space load;
the simulation subarea obtaining unit is used for carrying out regional division on the outer surface based on the surface shape, the heat flow parameters, the temperature parameters and a preset rule to obtain a plurality of outer heat flow simulation subareas;
the preset rules include: the adjacent rules of the areas, the same rules of the surface coating, the same rules of the main body substrate, the similar rules of the heat flow density change rules and the similar rules of the temperature.
10. The apparatus of claim 7, wherein the electric heater setting module comprises:
and the electric heater setting unit is used for setting the electric heaters corresponding to the partition shapes in the plurality of outer heat flow simulation partitions according to the partition shapes corresponding to the plurality of outer heat flow simulation partitions.
11. The apparatus of claim 7, wherein the out-of-zone heat flow simulation module comprises:
the electric heater connecting unit is used for placing the space load in a space environment simulator and connecting the electric heater with the program-controlled direct-current power supply outside the space environment simulator through a lead;
the current applying unit is used for applying current corresponding to the test type to the electric heater through the program-controlled direct-current power supply according to the test type; wherein the current is calculated according to the electric heating power consumption of the plurality of outer heat flow simulation subareas and the resistance value of the electric heater arranged in the plurality of outer heat flow simulation subareas;
and the external heat flow determining unit is used for calculating the power consumption of the electric heater according to the circuit and simulating and obtaining the actually applied external heat flows of the external heat flow simulation subareas according to the power consumption.
12. The apparatus of claim 11, wherein the current applying unit comprises:
the first current applying unit is used for applying transient current to the electric heater through the program-controlled direct-current power supply under the condition that the test type is a transient test type so as to simulate the sectional simulation of the external heat flow of the plurality of external heat flow simulation subareas in a track period;
and the second current applying unit is used for applying a steady-state current to the electric heater through the programmable direct-current power supply under the condition that the test type is a steady-state test type so as to simulate the average external heat flow of the plurality of external heat flow simulation partitions in the track period.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114544212A (en) * | 2022-01-14 | 2022-05-27 | 上海卫星工程研究所 | Design method and system for heat balance test of complex external heat flow antenna |
| CN114674589A (en) * | 2022-05-27 | 2022-06-28 | 中国飞机强度研究所 | System and method for applying instantaneous thermal impact load in aerospace plane thermal test |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03157300A (en) * | 1989-11-13 | 1991-07-05 | Natl Space Dev Agency Japan<Nasda> | Artificial satellite |
| CN102092487A (en) * | 2009-12-11 | 2011-06-15 | 上海卫星工程研究所 | Heat flow compensation method for ground simulation test on infrared heating cage of spacecraft |
| CN104071360A (en) * | 2014-06-12 | 2014-10-01 | 上海微小卫星工程中心 | Transient heat balance test method and system based on radiation coupling heat-transfer equivalent simulation |
| CN105346737A (en) * | 2015-11-30 | 2016-02-24 | 中国空间技术研究院 | Heat control method of laser device of GEO satellite |
-
2020
- 2020-09-03 CN CN202010917735.6A patent/CN112208805A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03157300A (en) * | 1989-11-13 | 1991-07-05 | Natl Space Dev Agency Japan<Nasda> | Artificial satellite |
| CN102092487A (en) * | 2009-12-11 | 2011-06-15 | 上海卫星工程研究所 | Heat flow compensation method for ground simulation test on infrared heating cage of spacecraft |
| CN104071360A (en) * | 2014-06-12 | 2014-10-01 | 上海微小卫星工程中心 | Transient heat balance test method and system based on radiation coupling heat-transfer equivalent simulation |
| CN105346737A (en) * | 2015-11-30 | 2016-02-24 | 中国空间技术研究院 | Heat control method of laser device of GEO satellite |
Non-Patent Citations (1)
| Title |
|---|
| 刘绍然等: "外露式星载光机电设备热设计的间接验证", 《光学精密工程》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114544212A (en) * | 2022-01-14 | 2022-05-27 | 上海卫星工程研究所 | Design method and system for heat balance test of complex external heat flow antenna |
| CN114544212B (en) * | 2022-01-14 | 2023-11-10 | 上海卫星工程研究所 | Design method and system for heat balance test of complex external heat flow antenna |
| CN114674589A (en) * | 2022-05-27 | 2022-06-28 | 中国飞机强度研究所 | System and method for applying instantaneous thermal impact load in aerospace plane thermal test |
| CN114674589B (en) * | 2022-05-27 | 2022-08-26 | 中国飞机强度研究所 | System and method for applying instantaneous thermal impact load in aerospace plane thermal test |
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