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

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 probe type refractive index sensor based on surface plasma resonance, comprising a photonic crystal fiber, wherein one end of the photonic crystal fiber is connected with a single mode fiber, the other end is plated with a reflecting layer, and one end of the photonic crystal fiber plated with the reflecting layer is in contact with a sample to be tested; an outer surfaceof the photonic crystal fiber is plated with a metal thin film layer; a plurality of air holes are formed in the photonic crystal fiber, and the air hole pass through two end faces of the photonic crystal fiber; and the air holes are periodically arranged in the photonic crystal fiber in a regular hexagon and are arranged from the center of the photonic crystal fiber outward in multiple layers, and the apertures of the air holes in the horizontal direction are smaller than those of the air holes. The outer surface of the PCF is plated with metal thin film silver, the SPR effect is used as a refractive index sensing mechanism, and the performance of the sensor in the coating mode can be ensured by reducing the diameters of the air holes in the horizontal direction. Since the outer surfaceof the PCF is plated with the metal thin film silver, the difficulty of the manufacturing process is also reduced.

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 an MEMS oscillator based on a parameter pump. A low-frequency resonator module is respectively connected with a low-frequency resonator first excitation module and a low-frequency resonator second excitation module through low-frequency resonant beams; the high-frequency resonator module is respectively connected with the high-frequency resonator first excitation module and the high-frequency resonator second excitation module through high-frequency resonant beams; the common beam module is used for connecting a low-frequency resonant beam and a high-frequency resonant beam in a mechanical connection mode; the low-frequency resonator module is connected with the low-frequency oscillator closed-loop oscillation circuit and is connected with the parameter pump module through the summator, and the high-frequency resonator module is connected with the high-frequency oscillator closed-loop oscillation circuit; and the low-frequency oscillator closed-loop oscillation circuit and the high-frequency oscillator closed-loop oscillation circuit respectively enable the low-frequency resonant beam and the high-frequency resonant beam to generate closed-loop oscillation at the resonant frequency, and the parameter pump module applies a dynamic stiffness modulation signal to the low-frequency resonant beam. According to the invention, the frequency stability of the MEMS oscillator is improved, and the parameter locking phenomenon between the oscillators is realized.

The invention provides a zero backward thrust composite wing aircraft with ducted fan composite ailerons. The zero backward thrust composite wing aircraft with the ducted fan composite ailerons comprises an aircraft body and composite lift wings which are fixedly mounted on the two sides of the aircraft body, wherein the aircraft body is arranged as a deck platform; self-sealing ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; ducted fan propellers are arranged at the front ends of ducted fan thrust self-energizedcomposite ailerons; the self-sealing ducted fans are arranged in the ducted fan thrust self-energized composite ailerons; electricity, liquid and gas ports and the wing hinges are arranged on one sides or two sides of the ducted fan thrust self-energized composite ailerons; and the ducted fan thrust self-energized composite ailerons are movably connected with the composite lift wings through thewing hinges. The zero backward thrust composite wing aircraft with the ducted fan composite ailerons has the characteristics 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, the safety is high and so on; and the ailerons adopt compositelift forces to guarantee appropriate power.

The invention provides a foldable composite wing aircraft with twin-propeller thrust composite ailerons. The foldable composite wing aircraft with the twin-propeller thrust composite ailerons comprises an aircraft body and composite lift wings, wherein the composite lift wings are mounted on the two sides of the aircraft body in a foldable manner; the aircraft body is arranged as a deck platform;self-sealing ducted fans are embedded in the composite lift wings; wing hinges are designed on the external sides of the composite lift wings; propellers are arranged at the front ends of propeller thrust self-energized composite ailerons; self-sealing ducted fans are arranged in the propeller thrust self-energized composite ailerons; electricity, liquid and gas ports and wing hinges are arrangedon one side or two sides of the propeller thrust self-energized composite ailerons; and the propeller thrust self-energized composite ailerons are movably connected with the composite lift wings through the wing hinges. The foldable composite wing aircraft with the twin-propeller thrust composite ailerons has the advantages that the take-off and landing distance is short, the flying speed is high,the structural intensity of the wings is high, the wings can store energy, the flying energy consumption is low, the hang time is long, the safety is high and so on; the ailerons adopt composite lifts so that the adaption range of the power is guaranteed.

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 relates to an internal combustion engine combustion chamber structure which comprises a combustion cavity, an ignition device and a flow choking shell, the combustion cavity is a closed cavity, the ignition end of the ignition device extends into the combustion cavity, and the flow choking shell is located in the combustion cavity and surrounds the ignition end to form a pre-combustion chamber. A main combustion chamber is formed between the flow choking shell and the inner wall of the combustion cavity, the flow choking shell is provided with at least one flow guide hole communicated with the pre-combustion chamber and the main combustion chamber, and the connecting line of the ignition end and any point of the flow guide hole is blocked. The device is ingenious in design, simple in structure, easy to manufacture, high in applicability and low in cost.

The invention discloses a rear single-paddle type compound wing airplane with twin-duct thrust compound auxiliary wings and additional wings. The rear single-paddle type compound wing airplane comprises an airplane body, compound lift force wings fixedly mounted on two sides of the airplane body and ducted fan propellers, wherein self-enclosed ducted fans are arranged in the compound lift force wings; wing hinges are designed on the outer sides of the compound lift force wings; the ducted fan propellers are arranged at the front ends of propeller thrust self-powered compound auxiliary wings; self-enclosed ducted fans are arranged in the propeller thrust self-powered compound auxiliary wings; electricity liquid gas connection ports and the wing hinges are arranged on both sides of the propeller thrust self-powered compound auxiliary wings which are movably connected with the compound lift force wings through the wing hinges on one sides. The rear single-paddle type compound wing airplane has the characteristics of short take-off and landing distance, high flying speed, high wing structure strength, capability of energy storage in the wings, low flying energy consumption, long hang time, high safety and the like; the auxiliary wings adopt compound lift force to guarantee an application range of power.

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.

The invention discloses a battery management system adopting double-buses of energy and data The battery management system adopting double-buses of energy and data comprises a master controller and a plurality of single-chip microcomputers used for energy balance controlling, wherein the single-chip microcomputers are connected with energy balance driver modules. The battery management system further comprises energy buses used as energy transfer storages in the process of energy balancing between single batteries. The master controller is provided with data buses, and each of the single-chip microcomputers is connected with the master controller through the data buses. The aim of the battery management system adopting double-buses of energy and data is that with the energy buses as energy transfers of all the single batteries in the process of energy balancing, a point to point balance between any two single batteries inside the battery box is realized, meanwhile, the master controller is connected with each of controlling devices through the data buses so that the data transmission of the battery management system is achieved, therefore, the whole battery box is capable of only using one master controller to accurately realize the point to point balance of single batteries, thereby improving the balancing speed and saving the cost of the balancing controller.

The invention relates to a rear single ducted fan type composite wing aircraft with double ducted fan composite ailerons. The rear single ducted fan type composite wing aircraft with the double ductedfan composite ailerons comprises a rear single ducted fan type composite wing aircraft and ducted fan thrust self-energized composite ailerons which are assembled on the two sides of the rear singleducted 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 the aircraft body; the aircraft body is a deck platform; self-sealed ducted fans are placed 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 ducted fan thrust self-energized composite ailerons; electric, liquid and gas interfaces and wing hinges are arranged on one sides or two sides of the ducted fan thrust self-energized composite ailerons; and the ducted fan thrust self-energized composite ailerons are movably connected with the composite lift wingsthrough the wing hinges. The rear single ducted fan type composite wing aircraft with the double ducted fan composite ailerons has the advantages of short takeoff and landing distance, high flying speed, high wing structural strength, energy storage ability of the wing, low flying energy consumption, long hang time and so on; and the large-area composite lift wings can have effects of gliders inan emergency case, the safety of the aircraft is greatly enhanced, and safeties of personnel and materials are 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 composite lift force aircraft with a development platform. The composite lift force aircraft consist of a rear single-propeller type composite wing aircraft, thrust-free self-powered composite auxiliary wings assembled at the two sides of the rear single-propeller type composite wing aircraft and an manned bin, wherein the rear single-propeller type composite wing aircraft comprises a machine body, composite lift force wings which are mounted at the two sides of the machine body in a foldable mode, and a propeller; the machine body is a deck platform; self-sealing ducted fans are arranged in the composite lift force wings; wing hinges are designed at the outer sides of the composite lift force wings; self-sealing ducted fans are arranged in the thrust-free self-powered composite auxiliary wings; an electric-liquid gas interface and a wing hinge are arranged at one side or the two sides of each propeller thrust self-powered composite auxiliary wing, and are movably connected with the composite lift force wings through the wing hinges; and the manned bin 112 is mounted below the machine body. The composite lift force aircraft has the characteristics of beingshort in takeoff and landing distance, high in flying speed, high in wing structural strength, capable of storing energy by wings, low in flying energy consumption, long in hang time, high in safetyand the like.

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 relates to a rear single screw foldable composite wing manned craft with an additional wing. The rear single screw foldable composite wing manned craft comprises a craft body, the composite lift force wings mounted at the two sides of the craft body in a foldable manner and a propeller, wherein the craft body is arranged as a deck platform, the self-sealing ducted fans are arranged in the composite lift force wings, and the wing hinges are designed at the outer sides of the composite lift force wings; a manned cabin is arranged below the craft body, a magnetic type automatic interlocking interface male connector and a magnetic type automatic interlocking interface female connector are respectively arranged in front of and behind the composite lift force wings, and the magnetic type automatic interlocking interface male connector and the magnetic type automatic interlocking interface female connector have the same size. A wing hinge and an electric-hydraulic-gas interfaceare arranged on one side, facing the craft body, of the additional wing, and the additional wings are installed at the outer sides of the composite lift force wings in a foldable manner through the wing hinges. The craft has the characteristics of short take-off and landing distances, high flight speed, high structural strength of the wings, energy storage wings, low flight energy consumption, long hang time, high safety and the like.

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.

A foldable composite-wing manned aircraft with double-propeller-thrust composite auxiliary wings is provided. A rear-thrust-free type composite-wing aircraft includes a fuselage and composite liftingwings mounted, in a foldable manner, at two sides of the fuselage. The fuselage is a deck platform. Self-sealing ducted fans are disposed in the composite lifting wings. Hinges are arranged at outer sides of the composite lifting wings. Front ends of propeller-thrust self-powered composite auxiliary wings are provided with propellers. Self-sealing ducted fans are disposed in the propeller-thrust self-powered composite auxiliary wings. Electro-hydraulic gas connectors and wing hinges are disposed on one or two sides of the propeller-thrust self-powered composite auxiliary wings. The composite auxiliary wings are movably connected to the composite lifting wings through the wing hinges. A manned bin is mounted at the lower part of the fuselage. The aircraft has characteristics of short take-off and landing distances, a high flight speed, high wing structural strength, a characteristic that the wings can store energy, low flight energy consumption, long flying time, high safety, and the like. Composite lifting force is adopted by the auxiliary wings, thus ensuring the adaptive range of power.

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 relates to a combined-wing cargo aircraft with double propeller thrust combined ailerons. A rear thrust-free combined-wing aircraft comprises a body, combined lift wings fixedly mountedon two sides of the body, and a freight cabin, wherein the body is a deck platform; self-sealing ducted fans are arranged in the combined lift wings; wing hinges are designed outside the combined liftwings; propellers are arranged at the front ends of propeller thrust self-energizing combined ailerons; self-sealing ducted fans are arranged in the propeller thrust self-energizing combined ailerons; an electro-hydraulic gas interface and a wing hinge are arranged on one side or both sides of each propeller thrust self-energizing combined aileron; the propeller thrust self-energizing combined ailerons are movably connected to the combined lift wings through the wing hinges; the freight cabin is mounted below the body. The invention has the characteristics of being short in take-off and landing distances, fast in flying speed, high in wing structural strength, capable of storing energy in the wings, low in flight energy consumption, long in hang time, and high in safety; the ailerons adopt combined lift, to ensure power adaptability.

The invention provides a zero rear thrust composite-wing cargo aircraft with turbofan composite ailerons and additional wings. An aircraft body is arranged as a deck platform; a self-sealing ducted fans are embedded in composite lift wings; wing hinges are designed on the external sides of the composite lift wings; turbofan propellers are arranged under turbofan thrust self-energized composite ailerons; self-sealing ducted fans are arranged in the turbofan thrust self-energized composite ailerons; electricity, liquid and gas interfaces and wing hinges are arranged on one sides or two sides ofthe turbofan thrust self-energized composite ailerons; the turbofan thrust self-energized composite ailerons are movably connected with the composite lift wings through the wing hinges; wing hinges are arranged on one sides, facing towards the aircraft body, of the additional wings; the additional wings are mounted on the external sides of the composie lift wings through the wing hinges in a foldable manner; and a cargo compartment is mounted at the bottom of the aircraft body. The zero rear thrust composite-wing cargo aircraft with the turbofan composite ailerons and the additional wings hasthe 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, the safety is high, the ailerons adopt composite lift forces to guarantee the power application range and so on.

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.