10results about How to "Strong thrust" patented technology

The present application relates to the technical field of spacecraft propulsion system, and more particularly to a micro-newton hybrid mode propulsion system and method based on gas working substance. The system comprises a gas storage unit, a gas supply unit, a thruster unit and a propulsion system driving and control unit. The gas storage unit adopts symmetrically arranged high-pressure gas cylinders connected through high-pressure isolation valves, and in combination with the automatic balancing strategy of the control unit, effectively solves the problem of on-orbit centroid drift. The gas supply unit includes parallel cold gas propulsion branches and electric propulsion branches, and each branch adopts a mechanical pressure reducer to eliminate vibration and noise caused by electromagnetic valve action from the source, realizing super-static operation of the system. The propulsion system driving and control unit controls the micro-newton cold gas thruster and the micro-newton electric thruster to work alone or in cooperation according to the distribution strategy based on the thrust critical point, realizing the optimal comprehensive efficiency of high precision and high specific impulse in the full thrust range, and being suitable for ultra-high precision space scientific exploration missions.

A thrust generating device according to the present invention is a thrust generating device for irradiating a target with a laser beam to generate thrust for the target, the thrust generating device including: a laser beam generating device that generates a first laser beam having a first wavelength and a second laser beam having a second wavelength different from the first wavelength; and an irradiation device that simultaneously irradiates the target with the first laser beam and the second laser beam. The second wavelength may be a wavelength having a high absorptivity in the target than the first wavelength, and the intensity of the second laser beam may be lower than that of the first laser beam. Further, the second laser beam may be generated by converting the wavelength of the first laser beam.

The application belongs to the technical field of robots, and discloses a scalable amphibious robot driven by a paddle wheel, which comprises a shell, four wheel shafts rotatably connected to the shell and distributed on the left and right sides of the shell, four independent driving mechanisms arranged in the shell, four driving mechanisms connected with the four wheel shafts to drive the wheels to rotate independently, a scalable paddle wheel mechanism contained in the wheel mechanism, the scalable paddle wheel comprising a wheel, an independent small wheel body, a plurality of paddle plates and a scalable mechanism; the scalable mechanism is used for the expansion and contraction of the paddle plates of the paddle wheel, so that the paddle plates of the paddle wheel can be retracted into the wheel and form an integral whole with the wheel, or be expanded into a paddle wheel mechanism and be used for rowing. The single power driving system is combined with the scalable paddle wheel structure, so that the rigidity and flexibility of the hub are ensured when the amphibious robot runs on land, and the energy utilization efficiency is improved when the amphibious robot sails on water.

The invention discloses a hydraulic control type high-pressure sample transfer valve, and belongs to the technical field of sample transfer control devices for high-pressure samples in laboratories. Comprising a piston assembly and a sample transfer valve body, the piston assembly comprises a piston outer cylinder; one end of the sample transfer valve body is matched and connected with the piston outer cylinder, and the other end of the sample transfer valve body is provided with a first connecting screw thread for connecting a sampler valve; one end of the piston is connected with a piston rod, and the other end of the piston is connected with a piston stroke rod; one end of the piston stroke rod extends out of the piston outer cylinder; a hand pump pipeline connector is arranged on the wall face of a closed cavity formed by the piston outer cylinder and the piston. A needle valve assembly and a sample transfer high-pressure pipeline interface are arranged on the sample transfer valve body, and the sample transfer high-pressure pipeline interface is used for being connected with test equipment or a high-pressure brine pump; the piston of the sample transfer valve can be remotely controlled by the hand pump to perform opening and closing operation, and the hand pump is far away from the sampler, so that the safety of operators can be well protected.

The present invention provides a closed asymmetric capacitor plasma acceleration propulsion module, which relates to the technical field of plasma thrusters and comprises an array shell and a high-voltage power supply. An insulating pressure-resistant shell is arranged on one side of the array shell, and a flow-guiding connection hose is arranged at the end of the array shell. In actual use, multiple modules can be connected in series by arranging the array shell and the high-voltage power supply, thereby improving the ion injection speed at the final output end. An aerospace vehicle equipped with such an ion thruster module can permanently sail on orbit without worrying about the exhaustion of propellant. At the same time, the enhancement and improvement of its thrust make it powerful. The high-voltage electrodes are arranged inside the engine, which increases the working safety and makes the Biefeld-Brown effect have practical engineering application value. The module can be used as a full-electric propulsion engine without carrying working fluid for spacecraft attitude adjustment, orbit change, orbit enhancement, etc.

The utility model discloses an orthodontic dentition forward-moving push spring device, which relates to the technical field of orthodontic instruments, and comprises a bracket seat, a fixed seat, a connecting plate and an adjusting plate, the surface of the fixed seat is provided with a threaded hole, the surface of the connecting plate is fixedly connected with a threaded seat I, one side of the adjusting plate is fixedly connected with a threaded seat II, and the other side of the adjusting plate is fixedly connected with the threaded seat II. A push spring is fixedly connected between the two adjusting plates, a through hole is formed in the middle of the fixing seat, an orthodontic wire is slidably connected to the inner wall of the through hole in a penetrating mode, and the orthodontic wire penetrates through the interior of the push spring to provide basic supporting force for tooth orthodontics. The problems that after a traditional orthodontic push spring device is installed, the push force of a push spring cannot be flexibly adjusted, in the orthodontic process, the distance between the two ends of the push spring becomes large after teeth slightly displace, the push force of the push spring is reduced, and the subsequent orthodontic effect becomes poor are solved.

The invention relates to the technical field of fireworks, and discloses a hollow firework rocket structure with reverberation, comprising: an outer cylinder forming an external structure of a rocket; the aluminum pipe is arranged in the outer cylinder to form a hollow structure of the rocket; the gunpowder mechanism is arranged in the inner cavity of the aluminum tube and is used for igniting to generate thrust and strobe frequency reverberation; the inner barrel shell is arranged on one side of the aluminum pipe and used for forming a first layer of seal; the built-in lead is used for connecting and igniting the gunpowder mechanism; the external lead is used for initial ignition; the gunpowder mechanism comprises first gunpowder, second gunpowder and third gunpowder, and the first gunpowder and the second gunpowder are sequentially arranged in a cavity between the aluminum pipe and the outer cylinder. By adopting the hollow structure design of the first gunpowder, the combustion area is obviously increased, the combustion speed is increased, and the gunpowder can release energy more sufficiently, so that stronger thrust is provided.

The utility model discloses an intelligent foundation leveling and compacting device which comprises a slurry extracting and separating part arranged on a vehicle body part, the slurry extracting and separating part comprises a top iron plate, a slurry extracting unit, a slurry separator, a slurry conveying unit and a slurry storage box, and the top iron plate is connected with a cross beam; the slurry pumping unit comprises a slurry pump and a hose, the slurry pump is installed at the lower end of the top iron plate, and the hose is connected to the feeding port end of the slurry pump; the slurry separator is installed at the lower end of the top iron plate and comprises a machine shell and a cylindrical rotary drum installed in the machine shell, a material pushing screw is wound on the rotary drum, and the end of the rotary drum is connected with a rotary motor; the discharge port end of the slurry pump is connected with the feed port end of the rotary drum; the muddy water conveying unit comprises a mud slide way and a water pipe. According to the utility model, the integration of soil shoveling, carrying, soil filling, land leveling and compacting can be realized, and the use of other types of engineering vehicles is reduced.

The present invention belongs to the technical field of aviation test instruments, and specifically relates to a high-thrust and high-speed axial force loading device. The present invention is an independent box body, without axial positioning, and has the function of automatically compensating for axial displacement. The axial force is provided by a double-rod hydraulic cylinder and transmitted by a tilting pad thrust bearing. The present invention can stably provide an axial force from zero to the rated load by accurately controlling the oil supply pressure of the double-rod hydraulic cylinder, with high loading accuracy and a small load fluctuation range; a radial force is applied to the drive shaft by a double-rod hydraulic cylinder arranged above the box body to increase the support stiffness of the cylindrical roller bearing. When the drive shaft rotates at a high speed over a critical value, the radial force is changed, thereby changing the support stiffness of the cylindrical roller bearing, and then changing the natural frequency of the shaft system, and having the function of frequency shifting. The present invention has the characteristics of strong operability, high speed, large thrust and strong practicality.

The invention discloses an earth Mars back-and-forth powder metal fuel rotary detonation rocket ramjet combined cycle engine, and belongs to the technical field of aerospace engines, the combined engine comprises a rocket type rotary detonation engine and a ramjet type rotary detonation engine, and the whole engine system adopts powder metal as main fuel. Combustion is organized by the rocket type rotary detonation engine and the ram type rotary detonation engine respectively, and thrust is generated jointly. The advantages of a rocket engine, a ramjet engine and a rotary detonation combustion mode can be fully played, and the advantages that the powdered metal fuel is good in stability, high in energy density and capable of being subjected to combustion reaction with multiple oxidants are utilized; and the combined power propulsion requirements of an aerospace aircraft, an earth Mars back-and-forth interplanetary aircraft and the like which can be repeatedly used in the future can be met.