6 results about "Static discharger" patented technology

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 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.

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.

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.

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.