Electric propulsion is used for all electric propulsion satellites to perform the orbit transfer,attitude control and station-keeping tasks. Generally electric propulsion subsystem contains 4 thrusters. But if one thr...Electric propulsion is used for all electric propulsion satellites to perform the orbit transfer,attitude control and station-keeping tasks. Generally electric propulsion subsystem contains 4 thrusters. But if one thruster fails in the beginning of satellite lifetime,other thrusters will undertake all the firing tasks. The firing time will be 2 to 3 times of thrusters without failure. Thus it may go beyond the allow ed lifetime of thruster. This paper puts forward two thruster redundancy configuration solutions with 6 thrusters to solve this problem. Two layout configurations and their corresponding station-keeping strategies are simulated and compared. The results show that the maximum firing time of both layout configurations can meet the lifetime limitation. This solution is a good reference for all electric propulsion satellites design.展开更多
The successful market uptake of all-electric propulsion systems is closely related to the performance metrics of the electrical motor used within.In light of this,various road-maps have been set for the next two decad...The successful market uptake of all-electric propulsion systems is closely related to the performance metrics of the electrical motor used within.In light of this,various road-maps have been set for the next two decades by aerospace and automotive bodies targeting ambitious future targets of the motor's power densities and efficiencies.In achieving motors with such step-improvement performance metrics,often the thermal management is a key challenge.In this paper,a cooling structure for a propulsion motor of solar unmanned aircraft is proposed which combines the stator windings with heat pipes,and which is shown to simultaneously improve the heat dissipation as well as the efficiency.This paper firstly determines the heat transfer characteristic of the heat pipe experimentally which is then used in the development of a bespoke thermal network model of the motor.The effects of the cooling structure on the motor's temperature rise,copper losses,torque,and efficiency are studied in detail.Finally,a prototype is developed and a test platform is built.The experimental results are consistent with the analytical result,verifying the correctness of the thermal network model and the benefits of the proposed mechanism.Compared to the motor without heat pipes,the temperature rise of the motor is reduced by 35%,while its efficiency is improved by a significant 1.5%.展开更多
文摘Electric propulsion is used for all electric propulsion satellites to perform the orbit transfer,attitude control and station-keeping tasks. Generally electric propulsion subsystem contains 4 thrusters. But if one thruster fails in the beginning of satellite lifetime,other thrusters will undertake all the firing tasks. The firing time will be 2 to 3 times of thrusters without failure. Thus it may go beyond the allow ed lifetime of thruster. This paper puts forward two thruster redundancy configuration solutions with 6 thrusters to solve this problem. Two layout configurations and their corresponding station-keeping strategies are simulated and compared. The results show that the maximum firing time of both layout configurations can meet the lifetime limitation. This solution is a good reference for all electric propulsion satellites design.
基金the Natural Science Foundation for Outstanding Young Scholar[grant numbers 52122704]the National Natural Science Foundation of China[grant numbers U2141224 and 52077044].
文摘The successful market uptake of all-electric propulsion systems is closely related to the performance metrics of the electrical motor used within.In light of this,various road-maps have been set for the next two decades by aerospace and automotive bodies targeting ambitious future targets of the motor's power densities and efficiencies.In achieving motors with such step-improvement performance metrics,often the thermal management is a key challenge.In this paper,a cooling structure for a propulsion motor of solar unmanned aircraft is proposed which combines the stator windings with heat pipes,and which is shown to simultaneously improve the heat dissipation as well as the efficiency.This paper firstly determines the heat transfer characteristic of the heat pipe experimentally which is then used in the development of a bespoke thermal network model of the motor.The effects of the cooling structure on the motor's temperature rise,copper losses,torque,and efficiency are studied in detail.Finally,a prototype is developed and a test platform is built.The experimental results are consistent with the analytical result,verifying the correctness of the thermal network model and the benefits of the proposed mechanism.Compared to the motor without heat pipes,the temperature rise of the motor is reduced by 35%,while its efficiency is improved by a significant 1.5%.
