9 results about "Pulsed plasma thruster" patented technology

The invention discloses a rapid estimation device and method for pulse plasma thruster element impulse, the device comprises a skeleton, a swing arm, a holder and a target, the swing arm is arranged on one side of the skeleton, the upper end of the swing arm is in running fit with the skeleton, and the holder is installed in the skeleton and used for fixedly installing a thruster; and the target is connected with the swing arm and is arranged opposite to a thruster nozzle in the retainer. The method has the remarkable technical advantages of being rapid, convenient, economical, easy to operate and the like, and important technical support is provided for research, development and application of the pulse plasma thruster.

The application discloses a coaxial pulse plasma thruster with a magnet as an outer electrode, and belongs to the technical field of microsatellite aerospace propulsion. The coaxial pulse plasma thruster with a magnet as an outer electrode mainly comprises an anode, a magnet cathode, a metal cathode, a propellant, an insulating outer shell, an insulating base, a supply spring and a spark plug. The metal cathode is divided into a perforated metal cathode and a non-perforated metal cathode. The thruster is coaxial in shape; the inner electrode is a solid cylinder, the outer electrode is a hollow pipe with a circular cross section, the solid propellant is located between the inner and outer electrodes, the supply spring is arranged between the tail of the propellant and the insulating base, and the outer electrode adopts segmented magnets and metal as the cathode. The application utilizes the magnetic field to restrict the radial movement of plasma so as to improve the collision ionization level, and provides Lorentz force to better accelerate the plasma. The segmented magnetic field provided by the segmented magnets with different magnetic poles opposite to each other can provide the magnetic field while reducing the overall mass of the thruster, and is beneficial to adjusting the magnetic field distribution in the thruster pipeline.

The application belongs to the technical field of plasma plume diagnosis of electric thrusters, and relates to a multi-mode TOF probe system for pulse plume velocity measurement of electric thrusters, which is a kind of diagnosis technology for the pulse plume generated by a pulse plasma thruster. The TOF probe system can realize several different working modes, and can measure the velocities of different components of the pulse plasma plume. The probe loop current signal is realized by using an indirect measurement technology, so that the problems of electrostatic suspension and isolation in the direct current measurement technology can be avoided.

The application relates to the technical field of aerospace propulsion, and particularly discloses a vacuum arc pulse plasma thruster. The vacuum arc pulse plasma thruster comprises a vacuum arc ignition system and a pulse plasma acceleration system. The vacuum arc ignition system forms an arc to generate plasma based on high-voltage pulse discharge ablation of metal, and injects the plasma into the pulse plasma acceleration system; the pulse plasma acceleration system axially accelerates the plasma based on the Lorentz force generated by the internal formed orthogonal electromagnetic field, and the high-speed ejection of the plasma from the discharge channel forms a recoil force. The introduction of the pulse plasma propulsion acceleration mechanism promotes the efficient conversion of the capacitor energy storage into axial directional kinetic energy, and improves the thrust, specific impulse and energy conversion efficiency of the thruster.

The invention discloses an electric heating type pulse plasma thruster, which is applied to the technical field of electric propulsion and is used for solving the problems of non-uniform ablation and lower specific impulse of an electric heating type pulse plasma thruster in the prior art. Specifically, an ablation cavity extending in the axis direction of the thruster is formed in the doped working medium; a cathode is arranged at one end of the doped working medium along the axis direction, and an anode is arranged at the other end of the doped working medium along the axis direction; the anode is connected with the cathode of an external power supply, and the cathode is connected with the anode of the external power supply; an insulating shell is arranged outside the doped working medium; the spark plug is embedded into the cathode, and the injection direction of the spark plug coincides with the axis direction. The spraying direction of the sparking plug is arranged to coincide with the axis direction, so that the ablation uniformity is improved; the sparking plug is embedded into the cathode, the movement direction of the electric arc is the same as that of the peeled ablation product, the ablation product continuously obtains energy from the electric arc, higher acceleration efficiency is achieved, and the specific impulse of the thruster is improved.

The invention discloses a thrust measuring device and method for a pulse plasma thruster, the device comprises a fulcrum shaft, a swing arm, a suspension rope and a counterweight, the counterweight is mounted at one end of the swing arm, the other end of the swing arm is used for mounting the thruster, the swing arm is suspended on the fulcrum shaft through the suspension rope, and the thruster is mounted on the fulcrum shaft through the suspension rope. And the swing arm is in a horizontal state under the action of the counter weight and the thruster. The device has the remarkable technical advantages of being high in precision, free of damping, simple in structure, low in cost and the like, and important technical support is provided for thrust measurement of the pulse plasma thruster.

The invention provides a pulse plasma thruster discharge channel test system, which comprises a moving frame, a lens assembly, a monochromator, a current sensor and an oscilloscope, and is characterized in that the moving frame and the lens assembly are arranged in a vacuum cabin, and the moving frame is used for loading a thruster to be tested; the lens assembly is used for acquiring spectral data of a point location to be measured in the discharge channel and transmitting the spectral data to the monochromator, the current sensor is used for acquiring discharge current of the thruster, and finally the oscilloscope synchronously records the spectral data and the discharge current. According to the invention, the discharge current is used as a combination reference among different times of measurement spectral data, and accurate combination of different times of measurement plasma parameters is realized by taking the discharge current as the reference, so that a real rule of plasma characteristic space distribution is obtained, and the problem of time asynchronization of data measurement in different times is solved; pseudo-synchronization reconstruction based on a physical process is realized.

The application discloses a PPT body anti-carbon deposition structure and method, which comprises a shell and at least one thrust chamber arranged on the shell; the thrust chamber comprises a thrust chamber frame shell, a cathode plate, an anode plate, a spark plug, a solid working medium and an anti-carbon deposition assembly, and one end of the thrust chamber is a thrust outlet; the cathode plate and the anode plate are arranged on upper and lower inner walls of the thrust chamber frame shell, and one end of the solid working medium is in the thrust chamber and in contact with the cathode plate and the anode plate; the anti-carbon deposition assembly comprises two anti-carbon insulation sheets, the two anti-carbon insulation sheets are located on left and right inner walls of the thrust chamber frame shell close to the outlet, and a notch extending to the inside of the thrust chamber is arranged in a middle region of the anti-carbon insulation sheet corresponding to one end of the thrust outlet. The application is applied to the field of spacecraft propulsion and can avoid forming a discharge loop between the cathode plate and the anode plate in the process of long-time operation of the pulsed plasma thruster, thereby ensuring long-time stable and reliable operation of the thruster.

The invention discloses a coaxial liquid pulse plasma thruster which comprises a cathode, an anode, a ceramic medium and an insulating ring, the cathode and the anode are coaxially arranged, the ceramic medium is located between the anode and the cathode, and the insulating ring is arranged between the anode and the ceramic medium; a porous capillary structure is arranged in the ceramic medium, ionic liquid is uniformly infiltrated on the porous capillary structure, the ionic liquid in the ceramic medium actively permeates to the end face of the ceramic medium through the capillary action to form a uniform liquid film, and the liquid film is punctured by pulse to form plasma. According to the application, the collaborative design of the ionic liquid working medium and the porous medium capillary supply system is adopted, the active infiltration of the ionic liquid is realized through the capillary force of the high borosilicate porous ceramic, a uniform liquid film is formed on a discharge interface, and the hysteresis ablation is eliminated; single pulse only consumes surface controllable mass, the utilization rate of a working medium is improved, and element impulse fluctuation is reduced.