56results about How to "Realize energy exchange" patented technology

The invention provides a thrust compound auxiliary wing with double ducts and a rear single-propeller type compound wing man carrying aircraft with the auxiliary wings. The rear single-propeller typecompound wing man carrying aircraft is composed of a rear single-propeller type compound wing aircraft and the ducted fan thrust self-energy-supply compound auxiliary wings arranged on the two sides of wings of the rear single-propeller type compound wing aircraft. The rear single-propeller type compound wing aircraft comprises an aircraft body, the compound lift force wings fixedly installed on the two sides of the aircraft body and a thruster. The aircraft body is arranged as a deck platform; self-sealed ducted fans are arranged in the compound lift force wings, and wing hinges are arrangedon the outer sides of the compound lift force wings; and the thruster is a propeller thruster. The rear single-propeller type compound wing man carrying aircraft has the beneficial effects that the take-off and landing distance is short, the flight speed is high, the wing structural strength is high, the wings can store energy, flight energy consumption is low, and the hang time is long, the auxiliary wings adopt compound lift force, the adaption range of power is guaranteed, meanwhile, the large-area compound lift force wings can achieve the effect of a glider under an emergency, the safety of the aircraft is greatly improved, and safety of personnel, goods and materials is guaranteed.

The invention discloses a propeller-thrusted composite wing manned aircraft with additional wings. A composite wing aircraft with a rear single-propeller comprises an airframe, additional wings assembled on two sides of a wing, and a manned cabin; a self-enclosed ducted fan is arranged in the composite lift wing, and wing hinges are designed on the outside of the composite lift wing; the wing hinge and an electro-hydraulic gas interface are arranged on one side, towards the airframe, of each additional wing, and the additional wing is arranged on the outside of the composite lift wing in a folding way through the hinge wing; the electro-hydraulic gas interface is provided with a cover, and battery and fuel are built in the additional wing; and the manned cabin is arranged below the airframe. The composite wing manned aircraft disclosed by the invention is not only short in take off and land distance, fast in flight speed, high in wing structure intensity, low in flight energy consumption, long in hang time and high in security, and the wing can store energy; the electro-hydraulic gas interface is arranged on one side or two sides of the additional wing, the energy intercommunication between the additional wing and the composite lift aircraft airfoil is realized, and the flexibility of the whole aircraft is improved since the action is controlled by the composite lift aircraft.

The invention provides a rear single ducted fan type composite-wing aircraft with zero thrust composite ailerons and additional wings. The rear single ducted fan type composite-wing aircraft with thezero thrust composite ailerons and the additional wings comprises a rear single ducted fan type composite-wing aircraft, zero thrust self-energized ailerons and additional wings, wherein the zero thrust self-energized ailerons and the additional wings are assembled on the two sides of wings; the additional wings are mounted on the external sides of the zero thrust self-energized ailerons through wing hinges in a foldable manner. The rear single ducted fan type composite-wing aircraft with the zero thrust composite ailerons and the additional wings has the advantages that the taking-off and landing distance is short, the flying speed is high, the structural strength of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, large-compositelift wings can have effects of gliders in the case of emergency, the safety of the aircraft is greatly enhanced, and safeties of personnel and materials are guaranteed.

The invention discloses a modular isolation type battery energy storage convertor and a modulation method therefor. A topological structure of the converter is that a primary side bridge arm of a transformer consists of m H bridges connected in series and is connected with a primary side of the transformer through filter inductance Lp; and one end of a secondary side of the transformer is connected with the negative electrode of a direct-current power grid bus through filter inductance Ls and a secondary side bridge arm while the other end of the secondary side of the transformer is connected with the positive electrode of the direct-current power grid bus. According to the method, the direction and capacity of energy transmission between an energy storage battery and a direct-current power grid are controlled by adjusting a phase difference between a primary side square-wave voltage and a secondary side square-wave voltage of the isolation transformer; direct-current bus capacitance voltages of all sub-modules of the secondary side bridge arm of the transformer are stabilized by correcting the phase difference; and a secondary side current average, namely, a direct-current power distribution network side current, of the transformer is adjusted by adjusting output voltages and currents of all the sub-modules of the secondary side bridge arm of the transformer, so that the purposes of stabilizing the module voltages and controlling the grid-connection currents are achieved and a system can run stably and reliably.

The invention discloses a rectangular wave modulation method for a modular isolation type battery energy storage converter. According to the invention, the duty ratio of the alternating voltage at the primary and secondary sides of a transformer in a half switching cycle is less than 0.5, the direction and size of energy transfer between an energy storage battery and a direct-current power grid are controlled by adjusting the phase difference between the primary rectangular wave voltage and the secondary rectangular wave voltage, the direct-current bus capacitor voltage of each sub module of the bridge arm at the secondary side of the transformer is stabilized by correcting the phase difference, and the average of current at the secondary side of the transformer, namely, the direct-current distribution network current is adjusted by adjusting the direct-current component of the output voltage of all the sub modules of the bridge arm at the secondary side of the transformer. Therefore, the purpose of module voltage stabilizing and grid-connected current controlling is achieved, and stable and reliable operation of the system is realized.

The invention provides a rear single ducted fan type composite wing aircraft with zero thrust composite ailerons. The rear single ducted fan type composite wing aircraft with the zero thrust compositeailerons comprises a rear single ducted fan type composite wing aircraft and zero thrust self-energized composite ailerons which are assembled on the two sides of the rear single ducted fan type composite wing aircraft, wherein the rear single ducted fan type composite wing aircraft comprises an aircraft body, composite lift wings and a propeller, wherein the composite lift wings are fixedly mounted on the two sides of aircraft body; the aircraft body is arranged as a deck platform; self-sealed ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; self-sealed ducted fans are arranged in the zero thrust self-energized composite ailerons; electricity, liquid and gas ports and wing hinges are arranged on one sides ortwo sides of the zero thrust self-energized composite ailerons; and the zero thrust self-energized composite ailerons are movably connected with the composite lift wings through the wing hinges. Therear single ducted fan type composite wing aircraft with the zero thrust composite ailerons has the advantages that the take-off and landing distance is short, the flying speed is high, the wing structural strength is high, the wing can store energy, the flying energy consumption is low, the aircraft can stay in the air for long time and so on; and the large-area composite lift wings can have effects of a glider in case of emergency so that the safety of the aircraft is greatly enhanced and safeties of personnel and materials are guaranteed.

The invention provides a rear-single-propeller-type composite wing airplane with double-duct thrust composite auxiliary wings. The rear-single-propeller-type composite wing airplane is composed of a rear-single-propeller-type composite wing aircraft and the duct fan thrust self-energy-supply composite auxiliary wings assembled on the two sides of wings of the rear-single-propeller-type composite wing aircraft. The rear-single-propeller-type composite wing aircraft comprises an aircraft body, the composite lifting force wings fixedly mounted on the two sides of the aircraft body and a thruster.The aircraft body is arranged to be a deck platform, the composite lifting force wings are internally provided with self-sealing duct fans, and wing hinges are designed on the outer sides of the composite lifting force wings. The thruster is a propeller thruster. The rear-single-propeller-type composite wing airplane with the double-duct thrust composite auxiliary wings have the characteristics that the taking-off and landing distance is short, the flying speed is high, the wing structural strength is high, the wings can store energy, the flying energy consumption is low, the hang time is long, and the safety is high, the auxiliary wings adopt composite lifting force, and the power application range is ensured.

The invention provides a composite lift force aircraft with an extended platform. The aircraft is composed of a rear single-propeller type composite wing aircraft, non-thrust self-energy-supply composite auxiliary wings assembled on the two sides of the rear single-propeller type composite wing aircraft and a freight transport bin. The rear single-propeller type composite wing aircraft comprises an aircraft body, composite lift force wings installed on the two sides of the aircraft body in a foldable mode and a propeller thruster. The aircraft body is arranged as a deck platform; self-sealingducted fans are arranged in the composite lift force wings, and wing hinges are designed on the outer sides of the composite lift force wings; and self-sealing ducted fans are arranged in the non-thrust self-energy-supply composite auxiliary wings, an electro-hydraulic-gas interface and a wing hinge are arranged on one side or two sides of each non-thrust self-energy-supply composite auxiliary wing, the non-thrust self-energy-supply composite auxiliary wings are movably connected with the composite lift force wings through the wing hinges, and the freight transport bin is installed below the aircraft body. The composite lift force aircraft has the advantages that the take-off and landing distance is short, the flight speed is high, the wing structural strength is high, the wings can storeenergy, flight energy consumption is low, the hang time is long, and safety is high.

The invention is applicable to the technical field of power grids, and provides a control method and device of a multi-energy coupling system and terminal equipment, and the method comprises the steps: obtaining an electric energy quality parameter of a new energy power generation system, a load parameter of a traction power supply system and a working parameter of a hybrid energy storage system;and according to the electric energy quality parameter of the new energy power generation system, the load parameter of the traction power supply system and the working parameter of the hybrid energystorage system, controlling the working states of a grid-connected inverter and a railway power adjusting device so as to enable the new energy power generation system, the traction power supply system and the hybrid energy storage system to realize energy intercommunication. Energy intercommunication among the new energy power generation system, the traction power supply system and the hybrid energy storage system can be achieved, the problems that the traction power supply system is poor in electric energy quality and regenerative braking energy is wasted can be solved, and the electric energy quality problem of new energy power generation can also be solved.

The invention discloses a composite lift aircraft with an extended platform. The composite lift aircraft is composed of a rear single-ducted fan type composite wing aircraft body, non-thrust self-energy-supply composite auxiliary wings assembled on the two sides of the rear single-ducted fan type composite wing aircraft body, and a manned bin. The rear single-ducted fan type composite wing aircraft body comprises a fuselage, composite lift wings fixedly mounted on the two sides of the fuselage, and a propeller thruster. The fuselage is arranged as a deck platform; the composite lift wings areinternally provided with self-closed ducted fans, and wing hinges are designed on the outer sides of the composite lift wings; and self-closed ducted fans are arranged inside the non-thrust self-energy-supply composite auxiliary wings, and one sides or the two sides of the non-thrust self-energy-supply composite auxiliary wings are provided with electro-hydraulic gas connectors and wing hinges, and movably connected with the composite lift wings through the wing hinges. The manned bin is mounted on the lower portion of the fuselage. The composite lift aircraft has the characteristics that thetakeoff and landing distance is short, the flight speed is high, the wings are high in structural strength and can store energy, flight energy consumption is low, and the hang time is long; and the large-area composite lift wings can achieve the effect of a glider under the emergency situation, the safety of the aircraft is greatly improved, and the safety of personnel and materials is guaranteed.

The invention provides a composite lift force aircraft with an expansion platform. The aircraft is composed of a rear single-propeller type composite wing aircraft and propeller thrust self-energy-supply composite auxiliary wings assembled on the two sides of the rear single-propeller type composite wing aircraft. The rear single-propeller type composite wing aircraft comprises an aircraft body, composite lift force wings installed on the two sides of the aircraft body in a foldable mode and a propeller thruster, wherein the aircraft body is arranged to be a deck platform; self-sealed ducted fans are arranged in the composite lift force wings, and wing hinges are arranged on the outer sides of the composite lift force wings; and self-sealed ducted fans are arranged in the propeller thrustself-energy-supply composite auxiliary wings, electro-hydraulic-gas ports and wing hinges are arranged on one side or two sides of each propeller thrust self-energy-supply composite auxiliary wing, and the propeller thrust self-energy-supply composite auxiliary wings are movably connected with the composite lift force wings through the wing hinges. The aircraft has the beneficial effects that thetake-off and landing distance is short, the flight speed is high, the wing structural strength is high, the wings can store energy, the auxiliary wings adopt composite lift force and have propeller power, the flight energy consumption is low, the aerial duration time is long, and safety is high.

The invention relates to a ship-based foldable dual magnetic anomaly detection anti-submarine warfare aircraft with a vertical take-off and landing function. The ship-based foldable dual magnetic anomaly detection anti-submarine warfare aircraft is composed of a composite wing aircraft, self-powered power composite auxiliary wings assembled on both sides of wings, a manned cabin and a telescopic metal detector. The ship-based foldable dual magnetic anomaly detection anti-submarine warfare aircraft is provided with the cruising speed of a fixed wing anti-submarine warfare aircraft, the cruisingspeed is hundreds of times that of ship anti-submarine. The aircraft can hover directly over the sky for a long time or even stay stationary to lock a submarine. At the same time, the difference value can be calculated combined with the coordinates of a cruise satellite and flight trajectory according to the magnitude and difference value of metal induction values on both sides by adopting the scheme of a two-way magnetic anomaly detection rod to directly calculate and locate the underwater submarine. The positioning efficiency can be multiplied many, many times. And the anti-submarine warfare aircraft can hover and lock the submarine for a long time in a low-power gliding state.

The invention discloses a material 3D printing system in a microgravity environment, belonging to the field of material 3D printing equipment. The system works in a sealed system that is thermally insulated from the external environment and protected by an inert atmosphere in the internal environment, including: space capsule, printing head subsystem, printing platform subsystem, and control subsystem. The inner surface of the upper part of the nozzle of the present invention is rough, which generates capillary force to drag the fluid to move in a directional direction, and the inner surface of the lower part of the nozzle is smooth, which is conducive to the accelerated movement of the fluid droplets; the negative pressure drive of the inert gas realizes the speed control of the fluid; the crystal oscillator rod realizes the movement of the fluid droplets. Size and volume control. The invention can be widely used in microgravity or no-gravity working environments such as manned spacecraft, space stations, space bases, and deep-sea submersibles.

The invention discloses a quasi-square wave modulation method for a modularized isolation type battery energy storage converter. Primary and secondary side AC voltage of a transformer is not a standard quasi-square wave, and the rising edge and the falling edge are step-shaped, i.e. duty ratio of AC output voltage of all the H-bridges of a primary side bridge arm Arm_p1 and all the submodules of a secondary side bridge arm Arm_s1 is less than or equal to 0.5 and is not equal to each other. The energy transfer direction and size of an energy storage battery and a DC power gird are controlled by adjusting phase difference between primary side quasi-square wave voltage and secondary side quasi-square wave voltage. DC bus capacitance voltage of all the submodules of the secondary side bridge arm of the transformer is stabilized by correcting the phase difference. The secondary side average current value, i.e. DC power distribution network side current, of the transformer is adjusted by adjusting the output voltage DC components of all the submodules of the secondary side bridge arm of the transformer so that the objective of stabilizing module voltage and controlling grid-connected current can be achieved, and system stable and reliable operation can be realized.