Multi-redundance aircraft electric power source and starting method thereof
A redundant, aviation technology, applied in the direction of emergency power supply, electrical components, circuit devices, etc., can solve the problems of reducing the size, weight and circuit cost of redundant aviation power supply, and increasing the manufacturing process of transformers, so as to reduce power consumption, extend Service life, effect overcoming volume and weight
Inactive Publication Date: 2014-12-31
BEIJING UNIV OF TECH
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Problems solved by technology
Power is supplied to the chip by the auxiliary winding of the transformer, so that the start-up voltage of the chip is clamped at 10V. Although the problem of the direct power supply method is solved, the cost of the circuit and the manufacturing process of the transformer are increased, and it is not conducive to satisfying the redundant aviation power supply. Requirements for size reduction and weight reduction
Method used
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[0045] figure 1 It is an embodiment of redundant aviation power supply, including: batteries 1, 2, DC / DC converters 1, 2, voltage detection 1, 2, switching circuit S 1 , S 2 , S 3 , S 4 , Control circuit and start circuit.
[0046]Batteries 1 and 2 provide 72V / 4Ah DC power supply, and adopt a centralized power supply method to supply power to the DC / DC converter. The battery uses Anhua's 72V / 4Ah lithium iron phosphate battery.
[0047] The electrical schematic diagrams of DC / DC converters 1 and 2 are shown in image 3 shown. The forward topology is adopted, and the output of the current control chip UC1844 controls the conduction state of the MOS tube, thereby adjusting the output of the DC / DC circuit. The converter uses a step-down transformer with a transformation ratio of 11:4. The 72V / 4Ah input DC voltage is internally stepped down, rectified, and filtered to output a stable 6V / 20A DC power supply. Step-down transformer adopts planar transformer RDH72V-6.
[0048]...
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The invention discloses a multi-redundance aircraft electric power source and a starting method thereof, belonging to the field of aerospace power supplies. The multi-redundance aircraft electric power source comprises a battery pack, a DC / DC (Direct Current / Direct Current) converter, a voltage detection circuit, a switching circuit and a control circuit, wherein the battery pack supplies a 72V DC input voltage to a power supply system by adopting a concentrated power supply mode, and the DC / DC converter outputs a stable 6V DC power supply to supply power to a load. A redundance technology is adopted in the battery pack and the DC / DC converter, thus the reliability of working of the power supply system is greatly improved. The starting method of the multi-redundance aircraft electric power source comprises the steps of: during electrifying, supplying a 16V DC starting voltage to the DC / DC converter by a starting circuit; and after the DC / DC converter normally works, switching a power supply into a DDS (Direct Digital Synthesis) self-powered system under the action of the control circuit to ensure that the working voltage of a current control chip is changed into 10V from 16V, thus the power consumption of the chip is reduced, and the service life of the chip is prolonged.
Description
technical field [0001] The invention belongs to the field of aerospace power supplies, and in particular relates to a redundant aviation power supply and a starting method. Background technique [0002] In the entire aviation equipment, the power supply system is responsible for the important task of providing payload power for other systems, and the quality of its power supply directly affects the overall working status of the aviation equipment. With the rapid development of modern science and aviation technology, the number of avionics equipment is increasing, the power consumption is increasing, and the temperature of the circuit is rising. These changes make the structure and control of the aviation power system more and more complex, and put forward higher requirements for the reliability and safety of the aviation power supply. The increase in power consumption will lead to an increase in the driving current of the power switching tube. At the same time, the influenc...
Claims
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IPC IPC(8): H02M3/335H02M1/32H02J9/06
CPCY02B70/30Y04S20/20
Inventor 张一鸣王海娟张旭曹智文高俊侠
Owner BEIJING UNIV OF TECH