17 results about "Static discharger" patented technology

The present invention discloses an electrostatic discharge device with both measurement and emission functions. The device comprises a base, one end of which is fixedly connected to an electrostatic discharger. The outer wall of the electrostatic discharger is covered with an insulating sleeve, and a microstrip patch antenna array is mounted on the outer wall of the insulating sleeve. The present invention also discloses a method for monitoring electrostatic current signals. The electrostatic discharge device with both measurement and emission functions disclosed in the present invention and the method thereof address the problem that existing electrostatic dischargers have difficulty monitoring discharge current during aircraft flight.

This utility model relates to the field of aircraft structural design technology, and discloses an integral trailing edge structure and winglet assembly for mounting an electrostatic discharger. The integral trailing edge structure for mounting the electrostatic discharger includes a trailing edge strip and a bushing. A mounting hole is provided on the edge of the trailing edge strip, located at the center of the strip's thickness direction. The bushing is interference-fitted into the mounting hole, and its inner wall has an internal thread. The mounting end of the electrostatic discharger has an external thread that matches the internal thread, allowing it to be threadedly connected to the bushing. Providing a mounting hole on the edge of the trailing edge strip, compared to the conventional method of fixing the electrostatic discharger to the winglet trailing edge using a mounting base, avoids a large area of ​​the electrostatic discharger protruding from the aerodynamic shape after mounting, thus reducing flight drag and aerodynamic wear. The electrostatic discharger and trailing edge strip are threadedly connected by the bushing. The bushing's interference fit with the mounting hole allows for easy and economical maintenance by replacing the bushing when its internal thread wears.

The invention discloses an explosion-proof human body static discharger, and particularly relates to the field of static dischargers, the explosion-proof human body static discharger comprises a mounting base, a vertical rod is fixedly mounted on the upper end face of the mounting base, a fixing rod is fixedly mounted on the upper end face of the vertical rod, and a touch ball is fixedly mounted on the upper end face of the fixing rod; a transmission device is rotatably mounted on the outer wall of the touch ball, a mounting plate is fixedly mounted at the output end of the transmission device, two mounting holes are symmetrically formed in the two sides of the mounting plate, and a cleaning device is arranged in each mounting hole. When the cleaning device is used, operation is easy, the transmission device rotates to drive the mounting plate and the cleaning device mounted on the mounting plate to rotate on the outer wall of the touch ball, the outer wall of the touch ball can be cleaned through rotation of the cleaning device, oil stains are prevented from being attached to the touch ball, the limiting rod is separated from the fixing hole, and the cleaning device is convenient to operate. And the cleaning device can be conveniently replaced.

1. The name of this design product: Electrostatic Discharger (Dolphin). 2. Purpose of this design product: used to release static electricity from the human body and objects. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture. 5. Other circumstances requiring explanation: Part A is transparent.

The invention discloses a layout design method for an aircraft electrostatic discharger. The layout design method comprises the following steps: step 1, calculating and obtaining a total deposition electrostatic current of an aircraft; 2, calculating the number of electrostatic dischargers needing to be arranged on the aircraft according to the total deposition electrostatic current; 3, airplane deposition static electricity distribution simulation is carried out, and a final static electricity discharger arrangement area and the area number are determined; 4, according to the number of the electrostatic dischargers and the number of the areas, multiple initial layout schemes of the full-machine electrostatic dischargers are formed; 5, determining a layout design scheme of the full-machine electrostatic discharger by taking the maximum total discharge current IQ or balanced discharge of the full-machine electrostatic discharger as a judgment standard; and step 6, evaluating the rationality of the layout scheme of the whole-aircraft electrostatic discharger of the aircraft to obtain a final layout scheme of the whole-aircraft electrostatic discharger of the aircraft. According to the aircraft electrostatic discharger layout design method, balanced discharge or maximum deposition electrostatic discharge of a plurality of electrostatic dischargers can be realized.

1. The name of this design product: Electrostatic Discharger (Lightning). 2. Purpose of this design product: used for the release of static electricity. 3. The design key point of this appearance design product lies in the shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture. 5. Other situations that require explanation: Part A is transparent.

The utility model belongs to the technical field of aircraft assembly, and discloses an auxiliary positioning device which is used for positioning the installation position of an electrostatic discharger base on an installation base body of an aircraft part, and positioning points are arranged on the datum plane of the installation base body. The auxiliary positioning device comprises a positioning template and a fixing frame, wherein a first positioning hole is formed in the positioning template; the positioning template is provided with a first side wall, a second side wall and a third side wall which are connected in sequence and are arranged at an included angle, and the junction of the first side wall and the second side wall is a positioning edge. When the positioning template is used, the positioning template is stacked on the reference surface, the first side wall is aligned with the side wall surface of the mounting base body, and the positioning edge is aligned and overlapped with the positioning point, so that the mounting position of the electrostatic discharger base can be determined through the first positioning hole, and a corresponding pneumatic tool is used for drilling. The positioning template abuts against the datum plane through the fixing frame, the positioning accuracy and the stability in the drilling process are ensured, operation is easy and convenient, and the working efficiency and the drilling quality can be improved.

1. The name of this design product: Electrostatic Discharger (Snowman). 2. Purpose of this design product: used to release static electricity from the human body and objects. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture. 5. Other circumstances requiring explanation: Part A is transparent.

The utility model discloses a miniaturized low-RCS base embedded electrostatic discharger suitable for a fixed-wing stealth aircraft, and relates to the technical field of aircraft electrostatic discharge equipment. The electrostatic discharger comprises a pressing lock catch which is arranged in the aircraft skin; one end of the discharge column is self-locked by pressing the lock catch, and the other end extends out of the machine body to serve as a discharge tip; one part of the high-resistance lap joint strip is tightly attached to the aircraft skin through conductive adhesive, and the other part of the high-resistance lap joint strip is arranged on the pressing lock catch; an electrostatic coating is sprayed on the surface of the pressing lock catch, and the pressing lock catch is connected with the high-resistance lap joint strip in an electrostatic conduction mode. The discharge end can be quickly and conveniently replaced and maintained by pressing the lock catch without detaching the aircraft skin, the maintenance cost is reduced, the time is saved, and more economic benefits are achieved.

1. The name of the product of this design: Electrostatic Discharger (Rocket). 2. Purpose of this design product: used for the release of static electricity. 3. The design key point of this appearance design product lies in the shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture. 5. Other situations that require explanation: Part A is transparent.

1. The name of this design product: Electrostatic Discharger (Ring Type). 2. Purpose of this design product: used to release static electricity from the human body and objects. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture.

The aircraft electrostatic discharge device layout design method disclosed by the application comprises the following steps: step 1, calculating and obtaining the total deposited static current of the aircraft; step 2, calculating the number of electrostatic discharge devices required to be arranged on the aircraft according to the total deposited static current; step 3, carrying out simulation of the distribution of the deposited static of the aircraft to determine the final electrostatic discharge device arrangement area and the number of areas; step 4, forming multiple preliminary layout schemes of the full-aircraft electrostatic discharge device according to the number of electrostatic discharge devices and the number of areas; step 5, taking the total discharge current I Q as the judgment standard, determining the layout design scheme of the full-aircraft electrostatic discharge device; and step 6, evaluating the rationality of the full-aircraft electrostatic discharge device layout scheme to obtain the final layout scheme of the full-aircraft electrostatic discharge device. The aircraft electrostatic discharge device layout design method can realize balanced discharge or maximum deposited static discharge of multiple electrostatic discharge devices.

The invention discloses an electrostatic discharge device with measurement and emission functions, which comprises a base, one end of the base is fixedly connected with an electrostatic discharger, the outer wall of the electrostatic discharger is sleeved with an insulating sleeve, and the outer wall of the insulating sleeve is provided with a microstrip patch antenna array. The invention further discloses an electrostatic current signal monitoring method. According to the electrostatic discharge device with the measurement and emission functions and the method thereof, the problem that an existing electrostatic discharger is difficult to monitor the discharge current in the flight process of an airplane is solved.

The present application belongs to the field of electrostatic protection and electromagnetic compatibility technology, and in particular, relates to a method for simulating and evaluating the discharge effect of an aircraft electrostatic discharger. The method for simulating and evaluating the discharge effect of an aircraft electrostatic discharger of the present application uses electromagnetic modeling and simulation methods to carry out an evaluation of the effect of an aircraft electrostatic discharger, is not limited by the development progress of the electrostatic discharger and the production of test pieces, and can perform a large number of iterative optimizations on the electrostatic discharger design at a very low cost; the method is applicable to all fixed-wing aircraft platforms, and belongs to the verification of the discharge effect of the entire aircraft after the electrostatic discharger is installed, and can be used as a basis for evaluating the electrostatic protection design of the entire aircraft.

Disclosed is an electro-static discharge device based on a PNPN structure. First intersection boundary is formed between first P-well and N-well; second intersection boundary is formed between N-well and second P-well; first ion injection region is arranged on surface region of first P-well; second ion injection region is arranged on surface region of second P-well; first N-ion boundary injection region is arranged at position of first intersection boundary formed by the intersection of surface region of first P-well and surface region of N-well; second N-ion boundary injection region is arranged at position of second intersection boundary formed by intersection of surface region of N-well and surface region of second P-well; and parasitic discharge circuit spans first P-well, N-well, and second P-well, and parasitic discharge circuits is connected to first ion injection region and second ion injection region respectively.

The invention provides an airplane electrostatic discharger layout method, and belongs to the technical field of airplane electrostatic protection. The airplane electrostatic discharger layout method comprises the steps that the installation number of all-airplane electrostatic dischargers is calculated; the arrangement area of the electrostatic discharger is determined, the arrangement area of the electrostatic discharger comprises an aircraft wing and an aircraft empennage trailing edge, aircraft aerodynamic characteristics of the arrangement area of the electrostatic discharger are analyzed to obtain an eddy current area in the arrangement area, and primary arrangement is conducted on the electrostatic discharger according to the eddy current area; performing electrostatic field analysis on the aircraft surface to obtain electrostatic charge distribution of the aircraft surface, and performing secondary arrangement on the electrostatic discharger according to the electrostatic charge distribution; and three-time arrangement of the electrostatic discharger is carried out by combining the electrostatic charge distribution condition and the distribution condition of the aircraft wing and the aircraft empennage trailing edge vortex region, and finally the layout scheme of the electrostatic discharger is completed. The method can effectively solve the problem that the electrostatic discharger is broken or falls off in the flying process of the airplane, and can be widely applied to the electrostatic protection design of the airplane.

The invention relates to the technical field of aircraft manufacturing, in particular to a positioning clamp and a brazing method for an aircraft static discharger, and the positioning clamp comprises a clamp mold, a plate pressing assembly and a needle pressing assembly; the top of the clamp mold is of a stepped structure and is provided with a plate positioning groove used for containing a mounting plate and a needle positioning groove used for containing a spray point. The plate pressing assembly is detachably connected with the clamp mold and used for pressing the mounting plate. The needle pressing assembly is detachably connected with the clamp mold and used for pressing the spray points. According to the technical scheme, it can be effectively guaranteed that the static discharger is fixed and clamped, the problems of position precision and welding gaps generated by the static discharger during brazing are solved, the advantages of being high in brazing joint quality, low in production cost and suitable for batch production are achieved, and connection and use of the static discharger on an airplane are met.