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.