Neighbor complementary power supply and distribution device for solar aircraft

A technology for power supply and distribution of solar cells, which is applied in the field of aviation aircraft, can solve the problems that the propulsion power cannot be guaranteed to be maintained in full, it is difficult to meet the requirements, and the loss is large, so as to solve the problem of long-distance loss, improve work reliability, reduce The effect of small concentrated stress

Active Publication Date: 2018-05-11
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to improve the aerodynamic efficiency of solar-powered aircraft, large-aspect-ratio wings and distributed propulsion systems are usually designed, which puts forward new requirements for the weight distribution of the aircraft power distribution system and long-term stable work. Traditional centralized aircraft Power distribution design has been difficult to meet the requirements
A power supply and distribution device for solar aircraft proposed earlier adopts the method of direct parallel backup between the same components of the power supply and distribution subsystem. The farther the components are from the power supply and distribution subsystem, the greater the loss; and the failure of solar cells and lithium batteries , the problem that the propulsion power cannot be guaranteed to be maintained at a sufficient level

Method used

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  • Neighbor complementary power supply and distribution device for solar aircraft
  • Neighbor complementary power supply and distribution device for solar aircraft
  • Neighbor complementary power supply and distribution device for solar aircraft

Examples

Experimental program
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Embodiment 1

[0018] Such as figure 1 As shown, it is a schematic diagram of the overall functional structure of a solar aircraft adjacent to the complementary power supply and distribution device of the present invention, including 2 power supply and distribution subsystems with the same structure (or 3 or more), and each power supply and distribution subsystem includes 2 sets of identical components, each set includes solar cell sub-arrays, unidirectional DC / DC converters, propulsion systems, bidirectional DC / DC converters and energy storage lithium battery stacks that are electrically connected in sequence. The device adopts the DC power supply mode, and the components are electrically connected through two wires (positive pole and negative pole). It is assumed that the solid line in the figure is the positive pole wire, and the dotted line is the negative pole wire.

[0019] Control switches (S1-S4, S9-S12) are set between multiple components of each set of components of each supply and...

Embodiment 2

[0023] Such as figure 2 with image 3 As shown, it is a structural diagram of a solar-powered aircraft adjacent complementary power supply and distribution device installed on the aircraft in a centralized-distributed manner according to the present invention. The aircraft includes a fuselage 11 and a wing 12, and four sets of supply and distribution subsystems (21, 22, 23, 24) with the same structure are distributed and installed on the wing, and the solar battery sub-arrays of each supply and distribution subsystem 25 is installed on the upper surface of the wing 12, and the propulsion system 26 is installed at the position corresponding to the solar battery sub-array 25 in front of the wing; the unidirectional DC / DC converter, bidirectional DC / DC converter and energy storage lithium battery stack Placed in the independent equipment compartment 28 in the corresponding lower wing of the solar battery sub-array; the key unidirectional DC / DC converter of key components is ins...

Embodiment 3

[0025] This embodiment provides another structural schematic diagram of a solar-powered aircraft adjacent to the complementary power supply and distribution device installed on the aircraft in a centralized-distributed manner according to the present invention.

[0026] Embodiment 3 adopts a structure similar to that of Embodiment 2, and the only difference is that the unidirectional DC / DC converters and bidirectional DC / DC converters and bidirectional The DC / DC converter and the energy storage lithium battery stack adopt a distributed structure, which are divided into multiple modules and correspondingly installed under each solar battery module, so as to maximize the weight distribution arrangement.

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Abstract

The invention discloses a neighbor complementary power supply and distribution device for a solar aircraft, and the device comprises more than two power supply and distribution subsystems of the samestructure, wherein each power supply and distribution subsystem comprises two sets of assemblies, and the electric connection and disconnection of the same parts in the assemblies can be achieved through switch control. The device employs a centralized-distributed design, and each power supply and distribution subsystem employs a centralized installation mode, has the functions of different powersupply and distribution, and can work independently. The power supply and distribution subsystems employ a distributed installation mode, are suitable for the characteristics of the large wingspan ofa solar plane and the distribution characteristics of a propelling system, and can effectively reduce the centralized stress. Meanwhile, the controllable and parallel connection mode of two sets of assemblies of each power supply and distribution subsystem achieves the neighbor complementation and redundant backup in the subsystems, and the fault isolation at the assembly level and the redundant backup in the power supply and distribution subsystems are achieved, thereby solving a problem that the backup distance is large in loss, and improving the work reliability of the device.

Description

technical field [0001] The invention belongs to the technical field of aviation aircraft, and relates to an adjacent complementary power supply and distribution device for solar aircraft. Background technique [0002] Solar aircraft has the advantages of powerful functions, strong adaptability, good flexibility, and low cost, and has been increasingly widely used. In order to improve the aerodynamic efficiency of solar aircraft, large aspect ratio wings and distributed propulsion system design are usually adopted, which puts forward new requirements for the weight distribution and long-term stable operation of the aircraft power distribution system. Traditional centralized aircraft Power distribution design has been difficult to meet the requirements. A power supply and distribution device for solar aircraft proposed earlier adopts the method of direct parallel backup between the same components of the power supply and distribution subsystem. The farther the components are ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02J7/35H02J1/10
CPCH02J1/10H02J7/35Y02E10/56
Inventor 孙康文董佳琦史立峰孙谋
Owner BEIHANG UNIV
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