System for inhibiting drift distance of high and low temperature constant current point for space navigation
A technology of high and low temperature and drift, which is applied in the direction of measuring devices, only measuring current, measuring electrical variables, etc., can solve the problem of affecting the normal operation of spacecraft, the large drift of high and low temperature constant current points, and the restriction of high precision constant current control accuracy of aerospace, etc. problem, to achieve the effect of good effect, strong operability and simple structure
Active Publication Date: 2021-11-16
SHANGHAI INST OF SPACE POWER SOURCES
View PDF7 Cites 0 Cited by
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
2. Differential current sampling circuit, the circuit places the current sampling resistor on the bus output loop, and the differential amplifier circuit forms a current sampling signal through the voltage signal on the current sampling resistor. Whether the output bus is stable does not affect the use of the circuit, but In the environmental test with alternating temperature (thermal cycle test or thermal vacuum test), the aerospace power converter using the differential current sampling circuit has a large drift of high and low temperature constant current points, which seriously restricts the high-precision constant current control of aerospace. accuracy, even affecting the normal operation of the spacecraft in orbit
Method used
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View moreImage
Smart Image Click on the blue labels to locate them in the text.
Smart ImageViewing Examples
Examples
Experimental program
Comparison scheme
Effect test
example 1
[0058] For example, Example 1: Taking the development process of a single model as an example, the resistance of the selected current sampling resistor R31 is a high-precision low-temperature drift SMT-3W-5mΩ resistor, and the power consumption of the resistor is about 5 / 1000*2.5*2.5=0.03 W is much less than 1.5W (50% of rated power consumption) and much less than 0.5W. The high-speed operational amplifier N1 selected is a 7F3140 chip with a serial number of 170. The parameters of the chip with this serial number are shown in Table 1:
[0059] Chip serial number High temperature △Vos(mv) Low temperature △Vos(mv) 170 -2.285 3.9
[0060] Table 1, the schematic diagram of the basic parameters of the 7F3140 chip with the chip number 170
[0061] In Table 1, high temperature △Vos=Vos 高 -Vos, low temperature △Vos=Vos 低 -Vos.
[0062] In environmental tests with alternating temperatures such as thermal cycle tests or thermal vacuum tests, it was found that...
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More PUM
Login to View More Abstract
The invention discloses a system for suppressing drift of a high and low temperature constant current point for space navigation. The system comprises a constant current source power conversion preceding stage, a filter inductor L10, a filter capacitor C10, an electric load, a sampling resistor R31, a differential current sampling circuit, a constant current function control circuit and a PWM control chip. A filter inductor L10, an electric load and a sampling resistor R31 are sequentially connected in series and then are connected with a constant current source power conversion preceding stage; the filter capacitor C10 is connected in parallel with an electric load; the differential current sampling circuit collects the voltage on the sampling resistor R31. The differential current sampling circuit, the constant current function control circuit and the PWM control chip are sequentially connected in series and then connected with the constant current source power conversion preceding stage. The system for suppressing the drift distance of the high and low temperature constant current point for aerospace aims at reducing the drift distance of the constant current point of a power supply for aerospace in a temperature alternating environment, improving the control precision of the power supply for aerospace on the constant current point and ensuring the normal operation of a spacecraft in orbit.
Description
technical field [0001] The invention belongs to the technical field of space power supplies, and in particular relates to a system for suppressing the drift of high and low temperature constant current points used in aerospace. Background technique [0002] In the field of space power supply technology, there are a large number of functions that use the constant current or constant current of the distribution power supply. For example: the charging regulator in the satellite power platform, during the light period, the charging regulator stores the energy of the solar array in the battery pack through constant current and constant voltage charging, and the charging constant voltage point and charging constant current point are selected by the ground personnel for charging Gear decision. For another example, a satellite laser load distributor has a large capacitor in its load power amplifier driver. The laser load needs to release a large amount of energy in a short time, an...
Claims
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More Application Information
Patent Timeline
Login to View More Patent Type & Authority Applications(China)
IPC IPC(8): H02M1/00G01R19/00
CPCH02M1/00G01R19/0092
Inventor 李小春吴家旺金家瑶朱诚诚张宸刘高锋张旭武腾
Owner SHANGHAI INST OF SPACE POWER SOURCES