CN109782741B - On-line measuring method for heat consumption of satellite power supply controller - Google Patents
On-line measuring method for heat consumption of satellite power supply controller Download PDFInfo
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Abstract
The invention relates to an on-line measuring method of heat consumption of a satellite power supply controller in the technical field of satellite power supply and distribution systems, which comprises the following steps of 1, providing closed loop backflow of a full link for power supply of a solar cell analog array; step 2, the solar battery analog array is interconnected with a test long cable, a release cable and a satellite power supply cable; step 3, calculating the total output power of the analog array; step 4, setting the final assembly state of the satellite; step 5, obtaining output power of the analog array; step 6, obtaining the power consumption of the whole satellite load; step 7, obtaining the power consumption of the storage battery according to the satellite telemetering data; step 8, obtaining the link loss according to the link loss calibration in the step 3, and obtaining the heat consumption of the power supply controller; and 9, drawing a heat consumption change curve to assist in judging the health of the internal working state of the power supply controller. The invention can measure the heat consumption of the power supply controller on line in real time, accurately measure the heat consumption of the power supply controller on line and assist the health state judgment and the whole satellite heat control design of the power supply controller.
Description
Technical Field
The invention relates to the technical field of satellite power supply and distribution systems, in particular to an on-line measuring method for heat consumption of a satellite power supply controller.
Background
The heat design of the power supply controller is a key focus link of the satellite heat control design, the heat consumption of the power supply controller can be changed differently along with different working modes, and the heat design of the power supply controller is difficult to accurately design in the satellite heat control implementation; in addition, due to the quality problem of a power MOS tube in the power supply controller, the problem of large heat consumption of the power supply controller occurs in a certain model, particularly, the heat consumption cannot be effectively dissipated under the thermal vacuum test environment, the temperature of the power supply controller is higher than the estimated temperature by more than 15 ℃, the heat balance of the whole satellite is not facilitated, and the long-term service life of the power supply controller is also not facilitated.
Through the search of the prior art, the invention name of Chinese patent 201611047723.2 is a cross-cabin design method for equipment on a satellite, and the patent discloses the following technical contents: the method comprises the following steps: the side plates are used for connecting the original platform cabin side plates and the load cabin side plates of the two large heat consumption power controllers into an integral plate to provide a large enough heat dissipation surface for the power controllers; 2 heat pipes are vertically arranged on the two large heat consumption controllers respectively, so that heat of the power controller is conducted upwards through the heat pipes, and side plates of the electronic cabin, which are not provided with any equipment, are arranged on the upper end sides of the 4 vertically arranged heat pipes to radiate the heat. Although the patent solves the heat dissipation problem of two large heat consumption power controllers of the satellite, lays a foundation for the feasibility of a satellite scheme, and has the advantages of high equipment space compatibility, good heat dissipation conditions, low cable wiring difficulty and the like, the patent cannot solve the technical problem of real-time online measurement of the heat consumption of the power controllers of the satellite in different working modes.
Therefore, it is necessary to design an on-line measurement method for the heat consumption of the power controller of the satellite, which can solve the problem of real-time on-line measurement of the heat consumption of the power controller of the satellite in different working modes, and has small measurement error of the heat consumption of the power controller and accurate measurement result.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide an on-line measurement method for the heat consumption of a satellite power supply controller, which can solve the problem of real-time on-line measurement of the heat consumption of the power supply controller in different working modes of a satellite, and has the advantages of small measurement error and accurate measurement result.
The invention relates to an on-line measuring method of heat consumption of a satellite power supply controller, which comprises the following steps:
step 1, designing a corresponding short-circuit closed-loop socket according to the contact arrangement of a power supply inlet socket of a power supply controller, wherein positive and negative contacts of a corresponding power supply channel in the short-circuit closed-loop socket are in short circuit, and a full-link closed-loop backflow is provided for power supply of a solar cell analog array through the short-circuit closed-loop socket;
step 2, the solar battery analog array is connected with a testing long cable, a release cable and a satellite power supply cable, the power supply cable is connected to the inlet end of the power supply controller, a satellite power supply cable plug is not connected with an inlet socket of the power supply controller, and the satellite power supply cable plug is connected with a short-circuit closed-loop socket;
step 3, traversing all the output settings of the common solar cell analog arrays, accumulating the voltage and current products output by each array according to the working state parameters acquired by the analog arrays, calculating the total output power of the analog arrays, working the analog arrays in a constant current mode, and enabling the load to be in a short circuit state, wherein the total output power of the analog arrays is the loss P of the power supply full linklink；
Step 4, simulating array power failure, disconnecting the satellite power supply cable from the short-circuit closed-loop socket, connecting the satellite power supply cable to a power supply inlet socket of the power supply controller, setting a satellite general assembly state, and starting satellite comprehensive test;
step 5, the satellite is electrified, the corresponding working state is set, the voltage and the current output by the power supply of the analog array are obtained according to the state parameter data of the analog array of the solar cell, the product of the voltage and the current output by each array is accumulated, and the output power P of the analog array is obtainedsas；
Step 6, obtaining bus voltage V according to satellite telemetering databusBus current IbusWhole satellite load power consumption Pbus＝Vbus*Ibus；
Step 7, obtaining the voltage V of the storage battery according to the satellite telemetering databatCurrent of storage battery IbatPower consumption of accumulator Pbat＝Vbat*Ibat；
Step 8, obtaining the link loss P under the output state of the analog array according to the link loss calibration of the step 3linkAccording to the step 5-7, obtaining the output power P of the analog array at the momentsasBus load power consumption PbusAnd battery power consumption PbatPower supply controlHeat loss P of the systempcu＝Psas-Plink-Pbus-Pbat；
And 9, calculating and measuring the heat consumption of the satellite power supply controller in real time through software according to the step 8, drawing a heat consumption change curve, and assisting the health judgment of the internal working state of the power supply controller.
Further, step 9 further includes sending the measurement information to a satellite thermal control subsystem to assist a thermal control designer in developing thermal control engineering design and implementation of the power controller.
Compared with the prior art, the invention has the following beneficial effects:
1. the on-line measurement method for the heat consumption of the satellite power supply controller can solve the problem of real-time on-line measurement of the heat consumption of the power supply controller in different working modes of a satellite, and has small measurement error and accurate measurement result of the heat consumption of the power supply controller;
2. the on-line measuring method of the heat consumption of the satellite power supply controller can measure the heat consumption of the power supply controller on line in real time, assist the internal health state judgment and the whole satellite heat control design of the power supply controller by accurately measuring the heat consumption of the power supply controller on line, and has good engineering value;
3. the on-line measurement method for the heat consumption of the satellite power supply controller prolongs the service life of the power supply controller, is beneficial to the heat design of the power supply controller and the heat balance of the satellite heat control design and the whole satellite.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, with reference to the accompanying drawings.
Fig. 1 is a schematic diagram of an online measurement method of heat consumption of a satellite power controller according to the invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
Examples
In this embodiment, the on-line measurement method for the heat consumption of the satellite power supply controller of the present invention includes the following steps:
step 1, designing a corresponding short-circuit closed-loop socket according to the contact arrangement of a power supply inlet socket of a power supply controller, wherein positive and negative contacts of a corresponding power supply channel in the short-circuit closed-loop socket are in short circuit, and a full-link closed-loop backflow is provided for power supply of a solar cell analog array through the short-circuit closed-loop socket;
step 2, the solar battery analog array is connected with a testing long cable, a release cable and a satellite power supply cable, the power supply cable is connected to the inlet end of the power supply controller, a satellite power supply cable plug is not connected with an inlet socket of the power supply controller, and the satellite power supply cable plug is connected with a short-circuit closed-loop socket;
step 3, traversing all the output settings of the common solar cell analog arrays, accumulating the voltage and current products output by each array according to the working state parameters acquired by the analog arrays, calculating the total output power of the analog arrays, working the analog arrays in a constant current mode, and enabling the load to be in a short circuit state, wherein the total output power of the analog arrays is the loss P of the power supply full linklink；
Step 4, simulating array power failure, disconnecting the satellite power supply cable from the short-circuit closed-loop socket, connecting the satellite power supply cable to a power supply inlet socket of the power supply controller, setting a satellite general assembly state, and starting satellite comprehensive test;
step 5, the satellite is electrified, the corresponding working state is set, the voltage and the current output by the power supply of the analog array are obtained according to the state parameter data of the analog array of the solar cell, the product of the voltage and the current output by each array is accumulated, and the output power P of the analog array is obtainedsas；
Step 6, obtaining bus voltage V according to satellite telemetering databusBus current IbusWhole satellite load power consumption Pbus＝Vbus*Ibus；
Step 7, obtaining the voltage V of the storage battery according to the satellite telemetering databatCurrent of storage battery IbatPower consumption of accumulator Pbat＝Vbat*Ibat；
Step 8, obtaining the link loss P under the output state of the analog array according to the link loss calibration of the step 3linkAccording to the step 5-7, obtaining the output power P of the analog array at the momentsasBus load power consumption PbusAnd battery power consumption PbatHeat loss P of power supply controllerpcu＝Psas-Plink-Pbus-Pbat；
And 9, calculating and measuring the heat consumption of the satellite power supply controller in real time through software according to the step 8, drawing a heat consumption change curve, and assisting the health judgment of the internal working state of the power supply controller.
The present invention will be described in detail below.
The invention aims to provide an on-line measurement method for the heat consumption of a satellite power supply controller, which can solve the problem of real-time on-line measurement of the heat consumption of the power supply controller under different working modes of a satellite, and has the advantages of small measurement error and accurate measurement result of the heat consumption of the power supply controller.
Step 1, designing a short-circuit closed-loop socket, and short-circuiting positive and negative wires of corresponding power supply channels according to a contact of a ground power supply inlet socket of a power supply controller to manufacture the required short-circuit closed-loop socket.
And 2, connecting the ground solar cell simulation array to the front end of a power supply inlet of the power supply controller through testing a long cable, a disconnecting and plugging cable and a satellite partial cable (according to actual design requirements, connecting a plurality of sections of cables for supplying power to a satellite), and connecting a power supply cable plug with the short-circuit closed-loop socket.
And 3, electrifying the solar cell analog array, traversing the common output setting state, and recording the output power of the corresponding analog array, wherein the power is the corresponding ground power supply link loss.
And 4, disconnecting the satellite power supply cable plug from the short-circuit closed-loop socket, connecting the satellite power supply cable plug to a power supply inlet socket of the power supply controller, setting a satellite state, powering up the ground solar battery analog array, setting different working modes of the satellite, and performing comprehensive test.
And 5, obtaining the output power of the analog array, the load power of the satellite and the power consumption of the storage battery according to the working parameter data of the solar battery analog array and the telemetering data of the satellite, and calculating the corresponding heat consumption in real time according to a heat consumption calculation formula of the power controller by combining the link loss calibrated in the step 3.
And 6, monitoring the heat consumption of the power controller under different working conditions and different modes in real time, assisting the health state judgment of the power controller, simultaneously sending the heat consumption information of the power controller to a satellite heat control subsystem, and assisting the heat control design of the power controller. ,
in conclusion, the on-line measurement method for the heat consumption of the satellite power supply controller can solve the problem of real-time on-line measurement of the heat consumption of the power supply controller in different working modes of the satellite, and has the advantages of small measurement error and accurate measurement result of the heat consumption of the power supply controller; the method can measure the heat consumption of the power supply controller on line in real time, assist the internal health state judgment and the whole satellite heat control design of the power supply controller by accurately measuring the heat consumption of the power supply controller on line, and has good engineering value; the service life of the power supply controller is prolonged, the thermal design of the power supply controller is facilitated, and the thermal control design of a satellite and the thermal balance of the whole satellite are facilitated.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (2)
1. An on-line measuring method for the heat consumption of a satellite power supply controller is characterized by comprising the following steps:
step 1, designing a corresponding short-circuit closed-loop socket according to the contact arrangement of a power supply inlet socket of a power supply controller, wherein positive and negative contacts of a corresponding power supply channel in the short-circuit closed-loop socket are in short circuit, and a full-link closed-loop backflow is provided for power supply of a solar cell analog array through the short-circuit closed-loop socket;
step 2, the solar battery analog array is connected with a testing long cable, a release cable and a satellite power supply cable, the power supply cable is connected to the inlet end of the power supply controller, a satellite power supply cable plug is not connected with an inlet socket of the power supply controller, and the satellite power supply cable plug is connected with a short-circuit closed-loop socket;
step 3, traversing all the output settings of the common solar cell analog arrays, accumulating the voltage and current products output by each array according to the working state parameters acquired by the analog arrays, calculating the total output power of the analog arrays, working the analog arrays in a constant current mode, and enabling the load to be in a short circuit state, wherein the total output power of the analog arrays is the loss P of the power supply full linklink；
Step 4, simulating array power failure, disconnecting the satellite power supply cable from the short-circuit closed-loop socket, connecting the satellite power supply cable to a power supply inlet socket of the power supply controller, setting a satellite general assembly state, and starting satellite comprehensive test;
step 5, the satellite is electrified, the corresponding working state is set, the voltage and the current output by the power supply of the analog array are obtained according to the state parameter data of the analog array of the solar cell, the product of the voltage and the current output by each array is accumulated, and the output power P of the analog array is obtainedsas；
Step 6, obtaining bus voltage V according to satellite telemetering databusBus current IbusBus load power consumption Pbus＝Vbus*Ibus；
Step 7, obtaining the voltage V of the storage battery according to the satellite telemetering databatCurrent of storage battery IbatPower consumption of accumulator Pbat＝Vbat*Ibat；
Step 8, obtaining the link loss P under the output state of the analog array according to the link loss calibration of the step 3linkAccording to the step 5-7, obtaining the output power P of the analog array at the momentsasBus load power consumption PbusAnd battery power consumption PbatHeat loss P of power supply controllerpcu＝Psas-Plink-Pbus-Pbat；
And 9, calculating and measuring the heat consumption of the satellite power supply controller in real time through software according to the step 8, drawing a heat consumption change curve, and assisting the health judgment of the internal working state of the power supply controller.
2. The method as claimed in claim 1, wherein the step 9 further comprises sending the measurement information to the satellite thermal control subsystem to assist the thermal control designer in the design and implementation of the thermal control engineering of the power controller.
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