Abstract: A dragonfly-like miniature four-winged ornithopter includes: a fuselage (101), two front flapping wings (102), two front wing connectors (103) with first connecting rods, two rear flapping wings (104), two rear wing connectors (105) with second connecting rods, a driving gear (106), a shaft gear (107), a first-stage gear (108), two second-stage gears (109) with third connecting rods, two third-stage gears (114) with fourth connecting rods, two front ball joint connecting rods (110), two rear ball joint connecting rods (111), two steering engine connecting rods (112), two steer engines (113), and a brushless direct current motor.

Abstract: The present disclosure discloses an energy management system suitable for a solar-powered unmanned aerial vehicle and a control method thereof, which are used for an aerospace vehicle energy system. The system comprises a photovoltaic module, an MPPT controller, a first DC-DC circuit, a battery pack, a first anti-reverse circuit, a second DC-DC circuit, a second anti-reverse circuit, an ESC, a BLDC, an on-board controller, a communication link and a voltage stabilizing module. During cruising, the battery pack directly supplies power to the ESC through the first anti-reverse circuit; when high-power power output is needed, the battery pack supplies power to the ESC through the second DC-DC circuit and the second anti-reverse circuit in sequence, wherein the output voltage of the second DC-DC circuit and the accelerator signal input of the ESC are controlled by the on-board controller.

Abstract: The present disclosure provides an efficient control system and method for a brushless motor with a wide working range, which are applied to an aerospace vehicle energy system. The system of the present disclosure includes a power supplying module, a first DC-DC circuit, a battery pack, a second DC-DC circuit, an anti-reverse-connection circuit, an electronic speed control (ESC), a brushless direct current motor (BLDC), an airborne controller and a communication link. Electric energy from the power supplying module is configured to charge the battery pack via the first DC-DC circuit, and electric energy of the battery pack sequentially flows through the second DC-DC circuit and the anti-reverse-connection circuit to energize the ESC, wherein output voltage of the second DC-DC circuit and throttle signal input of the ESC are controlled in real time by the airborne controller according to a power demand of an aircraft.

Abstract: The present disclosure discloses an energy management system suitable for a solar-powered unmanned aerial vehicle and a control method thereof, which are used for an aerospace vehicle energy system. The system comprises a photovoltaic module, an MPPT controller, a first DC-DC circuit, a battery pack, a first anti-reverse circuit, a second DC-DC circuit, a second anti-reverse circuit, an ESC, a BLDC, an on-board controller, a communication link and a voltage stabilizing module. During cruising, the battery pack directly supplies power to the ESC through the first anti-reverse circuit; when high-power power output is needed, the battery pack supplies power to the ESC through the second DC-DC circuit and the second anti-reverse circuit in sequence, wherein the output voltage of the second DC-DC circuit and the accelerator signal input of the ESC are controlled by the on-board controller.

Abstract: The present disclosure provides an efficient control system and method for a brushless motor with a wide working range, which are applied to an aerospace vehicle energy system. The system of the present disclosure includes a power supplying module, a first DC-DC circuit, a battery pack, a second DC-DC circuit, an anti-reverse-connection circuit, an electronic speed control (ESC), a brushless direct current motor (BLDC), an airborne controller and a communication link. Electric energy from the power supplying module is configured to charge the battery pack via the first DC-DC circuit, and electric energy of the battery pack sequentially flows through the second DC-DC circuit and the anti-reverse-connection circuit to energize the ESC, wherein output voltage of the second DC-DC circuit and throttle signal input of the ESC are controlled in real time by the airborne controller according to a power demand of an aircraft.

Abstract: One embodiment of the present invention provides a method for fabricating a solar cell. The method includes: melting a metallurgical-grade (MG) Si feedstock, lowering a single-crystalline Si seed to touch the surface of the molten MG-Si, slowly pulling out a single-crystal Si ingot of the molten MG-Si, processing the Si ingot into single crystal Si wafers to form MG-Si substrates for subsequent epitaxial growth, leaching out residual metal impurities in the MG-Si substrate, epitaxially growing a layer of single-crystal Si thin film doped with boron on the MG-Si substrate, doping phosphor to the single-crystal Si thin film to form an emitter layer, depositing an anti-reflection layer on top of the single-crystal Si thin film, and forming the front and the back electrical contacts.

Abstract: Substrates for solar cells are prepared by the reverse of the standard RCA clean. The substrates are first cleaned in RCA-2 solution and then in RCA-1 solution. A pyramids rounding step using HF/HNO3 solution is inserted between the two RCA clean procedures. This solves all the issues relating to surface contaminations and sharp areas. It also avoids the stain layer on the surface to some extent by RCA-1 treatment. A thin layer of amorphous or micro-crystalline intrinsic silicon may be deposited to passivate the surface.

Abstract: One embodiment of the present invention provides a method for fabricating a solar cell. The method includes: melting a metallurgical-grade (MG) Si feedstock, lowering a single-crystalline Si seed to touch the surface of the molten MG-Si, slowly pulling out a single-crystal Si ingot of the molten MG-Si, processing the Si ingot into single crystal Si wafers to form MG-Si substrates for subsequent epitaxial growth, leaching out residual metal impurities in the MG-Si substrate, epitaxially growing a layer of single-crystal Si thin film doped with boron on the MG-Si substrate, doping phosphor to the single-crystal Si thin film to form an emitter layer, depositing an anti-reflection layer on top of the single-crystal Si thin film, and forming the front and the back electrical contacts.