Power supply and distribution device for solar-powered aircraft
A power supply and distribution device for solar-powered aircraft includes at least two power supply and distribution sub-systems having same configurations. A disconnection of an electrical connection between a plurality of components of each power supply and distribution sub-system can be controlled through a first switch. An electrical connection between the same components of the power supply and distribution sub-systems can be established by controlling a second switch. The power supply and distribution device for solar-powered aircraft has a centralized-distribution design. Specifically, each power supply and distribution sub-system is designed in a centralized mounting manner and has separated power supply and power distribution functions that can work separately. The power supply and distribution systems are designed in a distributed mounting manner which is suitable for solar aircrafts having characteristics of large wingspan and distributed propulsion system, thereby effectively reducing the concentrated stress.
1. A power supply and distribution device for solar-powered aircraft, comprising:
at least two power supply and distribution sub-systems having a same configuration;
wherein
an electrical connection between a plurality of components of each power supply and distribution sub-system can be disconnected by controlling a first switch; and
an electrical connection between identical components of the at least two power supply and distribution sub-systems can be established by controlling a second switch, and
wherein
the plurality of components of each power supply and distribution sub-system comprises a solar cell sub-array, a unidirectional DC/DC converter, a propulsion system, a bidirectional DC/DC converter, and an energy-storing lithium battery pack; and
the solar cell sub-array, the unidirectional DC/DC converter, the propulsion system, the bidirectional DC/DC converter, and the energy-storing lithium battery pack are sequentially and electrically connected.
2. The power supply and distribution device for solar-powered aircraft of claim 1 , wherein
the power supply and distribution device for solar-powered aircraft has a DC power supply mode including a positive pole and a negative pole;
the first switch for disconnecting the electrical connection between the plurality of components of one power supply and distribution sub-system is connected to one of the positive pole or the negative pole; and
the second switch for electrically connecting the identical components in the at least two power supply and distribution sub-systems is connected to the other of the positive pole or the negative pole.
3. The power supply and distribution device for solar-powered aircraft of claim 2 , wherein
the power supply and distribution device for solar-powered aircraft further comprises a key component for electrically connecting to an output end of the unidirectional DC/DC converter and/or the bidirectional DC/DC converter of each power supply and distribution sub-system.
4. The power supply and distribution device for solar-powered aircraft of claim 3 , wherein
the key component comprises a key unidirectional DC/DC converter, a load system, and a flight control system.
5. The power supply and distribution device for solar-powered aircraft of claim 1 , wherein
the power supply and distribution device for solar-powered aircraft comprises four power supply and distribution sub-systems distributively mounted on a wing.
6. The power supply and distribution device for solar-powered aircraft of claim 5 , wherein
the solar cell sub-array of each power supply and distribution sub-system is distributively mounted on an upper surface of the wing;
the propulsion system is mounted at a position corresponding to the solar cell sub-array in a front side of the wing;
the unidirectional DC/DC converter, the bidirectional DC/DC converter, and the energy-storing lithium battery pack are centrally mounted inside the wing below the solar cell sub-array.
7. The power supply and distribution device for solar-powered aircraft of claim 5 , wherein
the solar cell sub-array of each power supply and distribution sub-system is distributively mounted on an upper surface of the wing;
the propulsion system is distributively mounted at a position corresponding to the solar cell sub-array in a front side of the wing;
the energy-storing lithium battery pack is distributively mounted inside the wing below the solar cell sub-array; and
the unidirectional DC/DC converter and the bidirectional DC/DC converter are centrally mounted inside the wing.