An electro-mechanical trigger fuse for a loitering munition

Abstract

The present invention discloses an electro-mechanical trigger fuse for a loitering munition, which includes a housing, a base screw, a booster tube, a first detonator tube, a safety and arming mechanism, an inertial trigger switch, an electronic control module, an impact trigger switch, a potting shell, a rotor seat, a first positioning pin and a second positioning pin. Applying the time window arming principle, the fuse is ensured not to be armed before the active section of the projectile by using the recoil environment and the system launch control information, realizing redundant insurance design under weak launch environments. The fuse detonates an electric detonator through impact triggering and inertial triggering via the electronic control module to achieve firing, and has functions of ground graze detonation, high angle of impact firing, self-destruction, self-disabling and misfire prevention, which can significantly reduce the rate of unexploded ordnance, and can ensure the safety of unexploded ordnance disposal and the return and recovery of the loitering munition; it has a simple structure and low cost.

Description

Technical Field

[0001] The present invention belongs to the technical field of fuzes for low-launch-overload non-rotating projectiles, and particularly relates to an electro-mechanical trigger fuze for loitering projectiles. Background Art

[0002] The key to the technology of loitering projectile fuzes is safety design, mainly the problem of redundant insurance design, that is, to solve the contradiction between the reliability of arming under the ballistic environment of low launch overload and the safety under the credible service handling environment. The zigzag groove recoil safety mechanism, the two-degree-of-freedom recoil safety mechanism, and the clockwork recoil safety mechanism of the fuze can identify the drop and low launch overload environments through the impact experience time. The document "Research and Design on the Dynamic Characteristics of the Recoil Safety and Inertial Switch of Loitering Projectile Fuzes" (Ni Qingle. Research and Design on the Recoil Safety Mechanism and Inertial Switch of Loitering Projectile Fuzes [D]. Nanjing University of Science and Technology, 2017) introduced the structures and principles of these three typical mechanisms.

[0003] The working principle of the zigzag groove recoil safety mechanism is as follows: Under the action of launch overload, the inertial cylinder moves downward under the inertial force, and the inertial cylinder can move a sufficient displacement along the zigzag groove. When it reaches the bottom, the insured part is armed. When subjected to a drop impact, the inertial cylinder moves downward along the zigzag groove under the drop impact. However, due to the short action time, the inertial cylinder does not have time to complete the whole journey of the zigzag groove, and the action of inertial overload has disappeared, and the distance that the inertial cylinder descends is not enough, so the insured part cannot be armed.

[0004] The working principle of the two-degree-of-freedom recoil safety mechanism is as follows: Under the action of launch overload, the lower inertial cylinder first compresses the lower inertial spring and moves. When the lower inertial cylinder moves to the bottom, the upper inertial cylinder component starts to move and releases the insured part when it reaches a certain position. When subjected to a drop impact, the lower inertial cylinder still starts to move first, and the upper inertial cylinder moves later. However, due to the short duration of the drop impact, the upper inertial cylinder will not move to the armed position, and the upper and lower inertial cylinders return to the safe state under the resistance of the upper and lower inertial springs. The lower inertial cylinder part is arranged in the preset hole of the upper inertial cylinder, and its drop vibration will not affect the movement of the upper inertial cylinder.

[0005] The working principle of the clockwork recoil safety mechanism is as follows: Under the action of launch overload, the slider moves under the recoil force. When it is subjected to the resistance of the clockwork recoil safety mechanism, its movement is slow, but the action time of launch overload is long enough, and the slider can still move to the position, aligning the detonator with the booster tube, and then the latch drops, locking the mechanism in the armed position. When hitting a hard target during a drop, due to the short impact overload time, the slider cannot move to the position. After the overload disappears, the slider returns to the safe state under the action of the return spring.

[0006] These three recoil safety mechanisms are independent and require long travel and large volume to ensure safety when falling from a height of 1.5 m. However, it is difficult to obtain a large travel and volume for the design of cruise missile fuzes, so these three recoil safety mechanisms are difficult to use for cruise missile fuzes.

[0007] The document "A kind of electromechanical fuze for cruise missiles" (Tan Yongjun, Zhou Wenjie, Tang Biwen. A kind of electromechanical fuze for cruise missiles [J]. Computers and Information Technology, 2021, 29(01): 31-34) designed a fuze adapted for cruise missiles, which is mainly composed of a safety control circuit, a horizontal rotor explosion-proof mechanism, an inertial trigger mechanism, a detonation sequence and a shell. In the safe state, the horizontal rotor is locked in the explosion-proof position by two safety parts. When the fuze receives the release safety command, the two safety parts will release the horizontal rotor in turn. The horizontal rotor rotates positively under the drive of the torsion spring, so that the electric ignition head, the needle detonator and the detonating cord are aligned, and the fuze is in a ready-to-fire state. There is no specific discussion in the paper on whether the design meets the standard redundant insurance requirements of the "Fuze Safety Design Guidelines".

[0008] Literature "Recoil insurance in weak emission environment with electromagnetic locking function" (Liu Xiaogang, Deng Zhenfeng, Lei Junming. Recoil insurance in weak emission environment with electromagnetic locking function [J]. Journal of Detection and Control, 2022, 44(01): 13-

[0009] 17) designed a recoil safety mechanism with electromagnetic locking, that is, a circular electromagnet is set under the classic recoil safety cylinder. The normal safety of the recoil safety cylinder depends on its "lateral limit". When there is no launch overload and no power is supplied, the recoil safety cylinder is in the high safety position under the action of the recoil safety spring resistance and the lateral limit; before launching, the lateral limit and the electromagnet coil are energized to release the lateral limit, which is equivalent to opening the time window for the recoil safety mechanism to release the safety. During launching, the recoil safety cylinder overcomes the resistance of the recoil safety spring under the action of the launch overload and moves downward to contact the upper end surface of the iron core. The electromagnet absorbs and locks the recoil safety cylinder through magnetic attraction, which is equivalent to realizing the anti-recovery effect. After power failure, the recoil safety cylinder resets, but the "lateral limit" fails to reset, so the recovery is not the "initial position", and it cannot be ensured that it will not shift or release the safety after reset during the trusted service handling and explosive disposal process, and the service handling and explosive disposal safety cannot be guaranteed. The electromagnet used only realizes the anti-recovery function, and the safety problem of explosive disposal is not completely solved.

[0010] A fuse safety and detonation device for a micro miniaturized loitering munition disclosed in Chinese Patent No. 202210632767.0, comprising a body, an electromechanical safety mechanism, a second electric igniter, a paper gasket, a safety pin, a vertical rotor, a flame detonator, a torsion spring, an end cap, a rotation stop pin, a booster tube and a positioning pin. The flame detonator is installed in the vertical rotor and forms an explosion isolation mechanism with the help of the body. A pressure relief cavity is provided in the body, which helps to improve the explosion isolation safety at a small size. The electromechanical safety mechanism includes a first electric igniter, a compression screw, a safety piece and the body. The safety piece is usually inserted into the transverse groove at the end of the vertical rotor shaft to restrict the vertical rotor to achieve the safety function, and the safety is released based on the target information provided by the UAV flight control system. The safety pin safety mechanism composed of the safety pin and the body is a backup safety mechanism, and the safety is released by manual operation before takeoff. The fuse detonation device is simple and compact, small in size and light in weight (about 10 g), and has functions of explosion isolation, redundant safety, delayed safety release, fault safety and flame extinction, and is suitable for micro miniaturized loitering munitions.

[0011] The literature "Program Design and Simulation of the Electronic Safety System of Loitering Munitions" (Li Shaoqing, Peng Zhiling, Zhao Heming, etc. Journal of Ordnance Equipment Engineering, 2022, 43(5): 303-308) proposed that an electronic safety and arming device should be selected for loitering munitions. In fact, at present, the electronic safety and arming device is large in volume, high in cost, and has complex electrical interfaces, which is not very suitable for engineering applications on loitering munitions that are gradually being popularized.

[0012] The fuse similar to the UAV-triggered fuse is the missile-triggered fuse, especially the anti-tank missile-triggered fuse. The launch environments of the two are similar, and both have control systems and power supplies. The literature "Fuse Structure and Function" (edited by Ma Baohua. Fuse Structure and Function. Beijing: National Defense Industry Press, 1984) introduced that the fuse 9Э212ДЧ of the Soviet 9M14M anti-tank missile consists of two major parts: a warhead piezoelectric power supply and a fuse at the bottom of the missile. The fuse at the bottom of the missile uses a slider explosion isolation mechanism, and its safety mechanism is a rigid cross support piece. The electric ignition tube ignites the delay charge by the action of the launch signal, and then ignites the thrust primer to cut off the cross support piece to release the safety. When hitting the target, the wind cap presses the piezoelectric ceramic at the warhead to generate an electrical pulse, causing the electric detonator in the slider to detonate. This fuse has only one safety release environment (launch electrical signal), and has no self-destruction, self-disabling and self-failure characteristics, and it is also difficult to ensure the firing reliability at large impact angles and small landing angles and the triggering sensitivity to non-armored targets.

[0013] The literature "Fuzes - Structure and Function" (edited by Ma Baohua, Fuzes - Structure and Function, Beijing: National Defense Industry Press, 1984) introduced that the fuze S70 of the French and German HOT anti - tank missiles is an electro - mechanical impact fuze, which consists of a contact switch, an ignition power source and a base fuze. The contact switch includes a wind cap and an inner cover, and is connected to the socket in the base fuze through a wire. The plastic wind cap is tinned on the surface, and its strength can meet the requirements of insensitivity. The inner cover is spun from a brass plate. The contact switch is normally open, and the fuze firing circuit is open. The ignition power source is located in the missile's electronic compartment. The base fuze mainly consists of an arming mechanism, an intermediate - safety mechanism, an ignition device and a power - connection mechanism. The intermediate - safety mechanism uses a spring - driven slider structure, and a flame detonator is installed in the slider. Its arming mechanism is a rigid shear pin, and the arming power comes from the gas pressure of the sustainer engine. When the missile hits the target, the wind cap deforms, the contact switch closes, the ignition power source supplies high - voltage electricity, causing the electric igniter to fire and detonating the detonator. This fuze has only one arming environment (the gas pressure of the rocket engine), and it also has no self - destruction, self - disabling and self - deactivation characteristics.

[0014] The literature "Fuzes - Structure and Function" (edited by Ma Baohua, Fuzes - Structure and Function, Beijing: National Defense Industry Press, 1984) introduced that the electro - mechanical impact fuze M114 of the American TOW anti - tank missile consists of a head contact switch, a base fuze and an electrical device. The structure of the head double - cone cover crushing the contact switch is similar to that of the above - mentioned S70 fuze, except that the materials of the wind cap and the inner cover are different. The base fuze uses a vertical rotor intermediate - safety mechanism and has a set of electro - mechanical arming mechanisms. When the sustainer engine is working, the ignition piston actuator releases the insurance of the interlocking latch mechanism. After that, under the action of the recoil overload, the interlocking latch - type recoil arming mechanism releases the insurance of the vertical rotor. With the action of a non - return torque clock mechanism, an arming delay time of about 0.3 s is achieved. When hitting the target, the head contact switch closes, and the capacitor in the electrical device discharges to the electric detonator, causing it to fire and explode. The two sets of arming mechanisms of this fuze are in series, that is, they are interrelated, and the non - return torque clock mechanism only plays the role of delaying arming. Therefore, this fuze does not meet the requirements of redundant arming and has no self - destruction, self - disabling and self - deactivation characteristics.

[0015] The literature "Fuzes - Structure and Function" (edited by Ma Baohua, Fuzes - Structure and Function, Beijing: National Defense Industry Press, 1984) introduced that the electro - mechanical impact fuze 9K32M of the Soviet SAM - 7 man - portable air - defense missile uses a torsion - spring - driven horizontal rotor intermediate - safety mechanism. Its arming mechanisms are respectively a powder arming (arming delay) mechanism that controls ignition by launch information and a recoil arming mechanism with a fail - safe characteristic, meeting the requirements of redundant arming. When hitting the target, the impact closer in the fuze or the body trigger switch causes the electric detonator to fire. This fuze has a self - destruction function but lacks self - disabling and self - deactivation characteristics. This system has a relatively complex structure and occupies a relatively large space.

[0016] The literature "Fuse Structure and Function" (edited by Ma Baohua. Fuse Structure and Function. Beijing: National Defense Industry Press, 1984) introduces that the fuse safety and arming mechanism of the American AIM-7 air-to-air missile Mk5Mod1 consists of an insensitive munition mechanism, an electromagnetic locker, an inertial slider safety mechanism, a clockwork mechanism, etc. This fuse safety and arming mechanism releases one safety each by using the electrical signal (generating electromagnetic force) during launch and the recoil environment, meeting the requirements of redundant safety, but no self-destruction, self-neutralization, and self-invalidation characteristics are seen.

[0017] The literature "Fuse Structure and Function" (edited by Ma Baohua. Fuse Structure and Function. Beijing: National Defense Industry Press, 1984) introduces that the fuse safety and arming mechanism of the American AIM-9B air-to-air missile is similar in structure and principle to the above-mentioned Mk5Mod1. It also releases one safety each by using the electrical signal during launch and the recoil environment, meeting the requirements of redundant safety. The difference is that the applied electrical signal is converted into the power for releasing safety after the pyrotechnic pusher ignites. This fuse safety and arming mechanism also shows no self-destruction, self-neutralization, and self-invalidation characteristics.

[0018] MIL-HDBK-757 (MILITARY HANDBOOK. FUZES. DEPARTMENT OF DEFENSE, UNITED STATES OF AMERICA, 15 April 1994.) introduces the safety and arming mechanism of the electro-mechanical impact fuse M934 of the American surface-to-air Stinger missile, including a vertical rotor insensitive munition mechanism, a recoil safety mechanism, and an electronically timed piston driver safety mechanism, which sense the recoil overload of the takeoff engine and the launch signal generated by the umbilical cable detachment respectively to release safety. This fuse has a firing performance at an impact angle of 80°, has a timed self-destruction characteristic, but no self-neutralization and self-invalidation characteristics. The diameter of this fuse is 63.4 mm and the mass is 107 g.

[0019] MIL-HDBK-757 (MILITARY HANDBOOK. FUZES. DEPARTMENT OF DEFENSE, UNITED STATES OF AMERICA, 15 April 1994.) introduces the safety and arming mechanism of the electro-mechanical impact fuse M820 of the American air-to-ground Hellfire missile, including a rotor insensitive munition mechanism, a recoil safety mechanism, and an electromagnetic safety mechanism controlled by an electrical signal during launch. A double-cone cover closing trigger switch is provided at the warhead. The diameter of this fuse is 89.4 mm, the length is 50.8 mm, and the mass is 317.5 g. This fuse has no function of exploding on contact with the ground, nor self-destruction, self-neutralization, and self-invalidation characteristics.

[0020] GJB / Z 135-2002 "Fuzing Engineering Design Manual" (Li Zhanxiong, Guo Zhanhai, Wang Shulai, etc. Fuzing Engineering Design Manual. Beijing: Military Standard Publishing and Distribution Department of the General Armaments Department, 2003) introduced that the first-stage insurance of the electro-mechanical impact fuze of a certain ship-to-ship missile is a change-over switch connected to the missile. After the missile is launched and the booster falls off, the insurance is released; the pressure signaler of the second-stage insurance has its normally closed contacts disconnected when the dynamic pressure of the missile flight reaches 24.5 kPa, and the insurance is released only after the normally open contacts are closed when the dynamic pressure reaches 34.3 kPa. The disconnection condition of the normally closed contacts of the second-stage insurance is equivalent to a flight speed of about 190 m / s, and the closing condition of the normally open contacts is equivalent to a flight speed of about 220 m / s.

[0021] ML-HDBK-145C (MILITARY HANDBOOK, ACTIVE FUZE CATALOG. DEPARTMENT OF DEFENSE, UNITED STATES OF AMERICA, 10 March 2000.) does not cover unmanned aerial vehicle fuzes or loitering munition fuzes. The missile fuzes given in it are almost all in somewhat more detail and almost all meet the redundant insurance requirements. The insurance release environments mostly apply pre-launch electrical signals (including on-board power supplies, firing latches excited by electromagnetic coils, etc.) and recoil overloads. Individually, air pressure and rocket engine pressure are also used. The vast majority of fuzes do not have self-destruction and ground-strike explosion characteristics, and no fuzes are seen to adopt self-disabling and self-failure designs.

[0022] A micro missile fuze disclosed in Chinese Patent 201810229767.X mainly consists of a fuze body, a striker seat, a striker body, a striker, a striker sleeve and a lock. This invention adopts an insurance method combining manual and electric means. Manual insurance is achieved through an insurance bolt, and electro-mechanical insurance is achieved through the missile central computer, a stepping motor, a lock and a striker body. The problem is that this invention does not meet the basic requirements of modern fuzes - "Fuzing Safety Design Criteria", the safety is not guaranteed and it has no practical value.

[0023] The literature "Research on Key Technologies of an Electromechanical Impact Fuze for an Air Defense Missile" (Fan Weimin. Research on Key Technologies of an Electromechanical Impact Fuze for an Air Defense Missile [D]. Shenyang Ligong University, 2020) designed an electromechanical impact fuze for an air defense missile. The fuze uses a spring-driven slider as the explosion isolation mechanism and has two safety mechanisms, namely the recoil safety mechanism and the electromechanical safety mechanism that releases the safety by the closing electrical signal of the fin switch when the fins open. Among them, an interlock structure is provided between the safety part of the recoil safety mechanism and the slider, aiming to lock the recoil safety part in the safe position with the help of the slider spring in case the electromechanical safety mechanism accidentally releases the safety. However, in fact, due to the relatively large mass of the slider component and the limited resistance of the slider spring, the interlock stroke between the slider and the recoil safety part is limited, so such an interlock is unreliable and may accidentally release the interlock (safety) under the environments of dropping, vibration, and bumping that may occur during credible service handling and explosive handling processes. This means that the design of the recoil safety mechanism cannot independently perform the safety function and does not meet the redundant safety requirements of the fuze. In addition, no self-disabling and self-failure designs are found for this fuze. Summary of the Invention

[0024] The purpose of the present invention is to provide an electromechanical impact fuze for a loitering munition, which applies the principle of safety release by time window and uses the recoil environment and system launch control information to ensure that the fuze does not release the safety before the active section of the projectile, realizing redundant safety design under weak launch environments. The fuze uses impact trigger and inertial trigger to detonate the electric detonator via an electronic control module to achieve firing, and has functions such as ground strike explosion, high angle of attack firing, self-destruction, self-disabling, and misfire prevention, which can significantly reduce the rate of unexploded ordnance and ensure the safety of unexploded ordnance disposal and the return and recovery of the loitering munition. In addition, while meeting high safety and high reliability requirements, the fuze can real-time feedback its own safety status to the ground control terminal of the loitering munition, providing a basis for operators to judge the warhead status and make decisions. The fuze is not only applicable to loitering munitions, but also applicable to missiles in principle.

[0025] Technical solution for achieving the object of the present invention: An electro-mechanical impact fuse for a loitering munition, comprising a housing, a base screw, a booster tube, a first detonator tube, an electronic control module, an impact trigger switch, a safety and arming mechanism, a potting shell, a rotor seat, a first positioning pin, two inertial trigger switches and two second positioning pins. The safety and arming mechanism includes a horizontal rotor interrupter mechanism, a recoil safety mechanism with a fail-safe function, an anti-recovery mechanism, an electric detonator and a compression screw, and an electro-mechanical safety and delay arming mechanism; the housing is in a rotary body shape, and a first stepped hole is opened downward along its central axis from its top surface, successively including a first-step hole, a second-step hole, a third-step hole, a fourth-step hole and a fifth-step hole; a first through hole communicating with the fifth-step hole is opened radially on the side surface of the housing; the booster tube is arranged in the first-step hole, and the first detonator tube is arranged in the second-step hole; the safety and arming mechanism and the rotor seat are mainly arranged in the fourth-step hole, and the remaining part is arranged in the fifth-step hole, and the base screw and the potting shell are arranged in the fifth-step hole; the first positioning pin extends radially into the safety and arming mechanism through the first through hole; both ends of the two second positioning pins are axially pressed into preset blind holes in the housing, and the other ends extend into preset blind holes in the rotor seat; the electronic control module is arranged in the potting shell and fixed and protected by potting glue, and two inertial trigger switches arranged in a cross shape are respectively arranged in the rotor seat and between the electronic control module and the rotor seat; the electric detonator is the first explosive element in the fuse detonation train; the second detonator tube in the horizontal rotor interrupter mechanism is usually in an interrupter state, and faces the first detonator tube in front of it and the electric detonator behind it after the fuse is armed; the recoil safety mechanism with a fail-safe function realizes the recoil safety of the horizontal rotor interrupter mechanism; the anti-recovery mechanism prevents the recoil safety mechanism from recovering safety after being armed; the electro-mechanical safety and delay arming mechanism realizes the delay arming function of the horizontal rotor interrupter mechanism; the first detonator tube and the booster tube are used to amplify the output energy of the electric detonator and the second detonator tube; the electronic control module is used to control the timing of the horizontal rotor arming, delay arming, the firing of the electric detonator, self-destruction, and self-disabling and recovery of safety in the case of accidental misfire of the electric detonator, and the impact trigger switch is used to realize the impact trigger function, and the inertial trigger switch is used to realize the standby inertial trigger function.

[0026] Compared with the prior art, the remarkable advantages of the present invention are:

[0027] (1) It has functions of ground-skimming explosion, high-angle ignition, self-destruction, self-disabling, misfire prevention and recovery of safety, and can ensure the safety of explosive disposal of unexploded bombs.

[0028] (2) It has a simple structure, low cost, convenient use and high reliability. Description of the Drawings

[0029] Figure 1 It is a schematic structural diagram of an electro-mechanical impact fuse for a loitering munition of the present invention along the axial section.

[0030] Figure 2 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the axial B-B section.

[0031] Figure 3 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the axial C-C section.

[0032] Figure 4 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the radial D-D section.

[0033] Figure 5 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the radial F-F section.

[0034] Figure 6 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the radial G-G section.

[0035] Figure 7 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the radial H-H section.

[0036] Figure 8 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the axial J-J section.

[0037] Figure 9 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the axial K-K section.

[0038] Figure 10 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the axial L-L section.

[0039] Figure 11 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the axial M-M section.

[0040] Figure 12 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the radial N-N section.

[0041] Figure 13 This is a sectional view of the electro-mechanical trigger fuse of a loitering munition of the present invention along the radial P-P section.

[0042] In the figure, 1 is the housing, 2 is the bottom screw, 3 is the detonator transfer tube, 4 is the first detonator tube, 5 is the safety and arming mechanism, 6 is the inertial trigger switch, 7 is the electronic control module, 8 is the potting case, 9 is the second positioning pin, 10 is the rotor seat, 11 is the first positioning pin, 12 is the countersunk head screw; 31 is the reinforcing cap, 32 is the detonator transfer tube housing, 33 is the booster explosive, 41 is the cover plate, 42 is the detonating explosive, 43 is the detonator tube housing, 51 is the horizontal rotor interrupter mechanism, 52 is the recoil safety mechanism, 53 is the anti-recovery mechanism, 54 is the electro-mechanical safety and delay arming mechanism, 55 is the electric detonator, 56 is the compression screw; 511 is the horizontal rotor, 512 is the second detonator tube, 513 is the torsion spring, 514 is the end cover, 521 is the safety pin, 522 is the recoil spring, 523 is the plug screw, 531 is the anti-recovery pin, 532 is the anti-recovery spring, 533 is the plug piece, 541 is the lock washer, 542 is the safety piece, 543 is the electric ejector, 544 is the slotted screw, 545 is the electric ejector plug. Specific embodiments

[0043] The present invention will be further described in detail below with reference to the accompanying drawings.

[0044] Combined with Figures 1 to 13The electromechanical trigger fuze of a cruise missile described in the present invention comprises a shell 1, a bottom screw 2, a detonator tube 3, a first detonator tube 4, a safety and release insurance mechanism 5, an electronic control module 7, an impact trigger switch, a potting shell 8, a rotor seat 10, a first positioning pin 11, two inertial trigger switches 6 and two second positioning pins 9, wherein the shell 1, the bottom screw 2, the potting shell 8, the rotor seat 10, the first positioning pin 11, the end cover 514 and the two second positioning pins 9 are main structural parts, and the safety and release insurance mechanism 5 comprises a horizontal rotor explosion-proof mechanism 51, a recoil insurance mechanism 52 with a fault insurance function, an anti-recovery mechanism 53, an electromechanical insurance and delayed release insurance mechanism 54, an electric detonator 55 and a pressure screw 56; the shell 1 is in the shape of a rotating body, A first stepped hole is opened downward from its top surface along its central axis, including a first step hole, a second step hole, a third step hole, a fourth step hole and a fifth step hole in sequence; a first through hole connected to the fifth step hole is opened radially on the side of the shell 1; a wrench hole is opened radially on the side of the shell 1 to facilitate threaded connection and assembly; the detonator 3 is arranged in the first step hole, and the first detonator 4 is arranged in the second step hole; the safety and release insurance mechanism 5 and the rotor seat 10 are mainly arranged in the fourth step hole, and the remaining part is arranged in the fifth step hole, and the bottom screw 2 and the potting shell 8 are arranged in the fifth step hole; the first locating pin 11 extends into the safety and release insurance mechanism 5 through the first through hole in the radial direction; the two second locating pins 9 are pressed into the preset blind hole of the shell 1 at one end along the axial direction, and the other end extends into the rotor The rotor base 10 is provided with a blind hole; the electronic control module 7 is arranged in the potting shell 8 and fixed and protected by the potting glue; two inertial trigger switches 6 arranged in a cross shape are respectively arranged in the rotor base 10 and between the electronic control module 7 and the rotor base 10; the impact trigger switch adopts mature technology and is independently arranged, which is not drawn in the figure; the electric detonator 55 is the first explosive element of the fuze transmission sequence; the second detonating tube 512 in the horizontal rotor explosion-proof mechanism 51 is usually in a dislocated state, that is, it is staggered with a certain distance from the first detonating tube 4 in front of it and the electric detonator 55 behind it, so as to realize explosion-proofing for the electric detonator 55; after the fuze is released, that is, the horizontal rotor is turned straight, the second detonating tube 512 is directly opposite to the first detonating tube 4 in front of it and the electric detonator 5 behind it. 5; the recoil insurance mechanism 52 with fault insurance function realizes the recoil insurance of the horizontal rotor explosion-proof mechanism 51; the anti-recovery mechanism 53 prevents the recoil insurance mechanism 52 from restoring the insurance after the insurance is released; the electromechanical insurance and delayed release insurance mechanism 54 realizes the delayed release insurance function of the horizontal rotor explosion-proof mechanism 51; the first detonating tube 4 and the transmission tube 3 are used to amplify the output energy of the electric detonator 55 and the second detonating tube 512; the electronic control module 7 is used to control the horizontal rotor 511 to release the insurance timing, delay the release of the insurance, the ignition and self-destruction of the electric detonator 55, and the self-destruction and restoration of the insurance in the event of an accidental misfire of the electric detonator 55, the impact trigger switch is used to realize the impact trigger function, and the inertia trigger switch 6 is used to realize the standby inertia trigger function.

[0045] Further, a second stepped hole is eccentrically formed in the axial direction on the top surface of the rotor base 10. From top to bottom, it is successively a sixth-order hole, a seventh-order hole, and an eighth-order hole. The horizontal rotor explosion-proof mechanism 51 is arranged in the second stepped hole; a third stepped hole with diameters decreasing successively from bottom to top is eccentrically formed in the axial direction at the bottom of the rotor base 10, which are successively a ninth-order hole, a tenth-order hole, and an eleventh-order hole. The eleventh-order hole is communicated with the sixth-order hole, and the recoil safety mechanism 52 with a fail-safe function is arranged in the third stepped hole; a fourth stepped hole with diameters decreasing successively is axially formed upward at the center of the bottom of the rotor base 10, which are successively a twelfth-order hole, a thirteenth-order hole, a fourteenth-order hole, and a fifteenth-order hole. The electric detonator 55 and the compression screw 56 are arranged in the fourth stepped hole; a fifth stepped hole is eccentrically formed in the axial direction upward at the bottom of the rotor base 10, which is composed of four sixteenth-order holes, seventeenth-order holes, and eighteenth-order holes with diameters decreasing successively. The fifth stepped hole is radially away from the second stepped hole and is not communicated with the second-order hole. The electromechanical safety and delay arming mechanism 54 is arranged in the fifth stepped hole; a sixth stepped hole communicating with the tenth-order hole is radially formed on the side surface of the rotor base 10, and the anti-restoration mechanism 53 of the recoil safety mechanism 52 is riveted and fixed in the sixth stepped hole; three second through holes are eccentrically formed in the axial direction at the bottom of the rotor base 10, and the second through holes are not communicated with other stepped holes. An inertial trigger switch 6 is arranged in one of the second through holes and is fixed by potting glue; a transverse groove is formed upward at the bottom edge of the rotor base 10, and another inertial trigger switch 6 is arranged in the transverse groove.

[0046] Further, the horizontal rotor explosion-proof mechanism 51 located within the rotor seat 10 includes a horizontal rotor 511, a second detonator tube 512, a torsion spring 513, an end cap 514, and two countersunk head screws 12; the horizontal rotor 511 is composed of a first cylinder, a second cylinder, a third cylinder, and a fourth cylinder from top to bottom. The first cylinder, the second cylinder, and the third cylinder are located within the sixth-order hole, and the fourth cylinder is located within the seventh-order hole and the eighth-order hole. The fourth cylinder has a radial through groove opened along its axis. The third cylinder is limited by the step surface between the sixth-order hole and the seventh-order hole; the top end of the second cylinder is axially downwardly offset from its axis to form a sixth-step hole, where the smaller-diameter hole is the nineteenth-order hole at the top and the larger-diameter hole is the twentieth-order hole at the bottom. The second detonator tube 512 is located within the twentieth-order hole and is fixed by bonding or dot riveting. Its axis is usually offset from the axis of the first detonator tube 4, forming an angle of approximately 60°. In this state, even if the electric detonator 55 accidentally ignites and explodes, it will not detonate the first detonator tube 4 and the transfer detonator tube 3, nor will it cause the structure of the housing 1 to be damaged and generate dangerous fragments, thereby achieving explosion-proof safety; the torsion spring 513 is in a pre-twisted state. One end of it is sleeved on the bottom of the radial through groove of the fourth cylinder, and the other end is stuck in the groove on the hole wall between the eighth-order hole and the twelfth-order hole outside it through its spring head; the end cap 514 is fixed to the bottom of the rotor seat 10 by two countersunk head screws 12. The preset blind hole on the end cap 514 is used to make space for the fourth cylinder. The side of the end cap 514 is provided with a first axial through groove. The first positioning pin 11 passes through the first through hole and extends into the first axial through groove. One end of it abuts against the bottom of the first axial through groove, and the other end is fixed by dot riveting at the orifice of the housing 1. The horizontal rotor 511 has two sets of independent safety mechanisms, namely the recoil safety mechanism 52 and the electro-mechanical safety and delayed arming mechanism 54 described below, to achieve redundant safety.

[0047] Further, the electro-mechanical safety and delayed arming mechanism 54 located within the rotor seat 10 includes three sets of safety discs 542, three sets of electric ejectors 543, three sets of slotted screws 544, three sets of lock washers 541, and three sets of electric ejector plugs 545; the electric ejectors 543 are mainly arranged within the seventeenth-order hole, and their bottoms are fixed by the electric ejector plugs 545 threadedly connected to the seventeenth-order hole. The electric ejector rods extend into the eighteenth-order hole; the safety discs 542 are fixed within the preset groove of the rotor seat 10 by the slotted screws 544 and the lock washers 541. One end of the safety discs 542 extends into the preset axial groove of the horizontal rotor 511, restricting the accidental rotation of the explosion-proof part, i.e., the horizontal rotor 511, so that it is in the assembled state, the firing state, and the armed state respectively. Among them, both the assembled state and the firing state are explosion-proof states.

[0048] Further, the transfer detonator tube 3 includes a reinforcing cap 31, a transfer detonator tube 32, and a transfer explosive 33. The transfer detonator tube 3 is riveted and fixed within the first-order hole.

[0049] Further, the first detonator tube 4 includes a cover piece 41, a detonator tube shell 42, and a detonating charge 43, and the first detonator tube 4 is riveted and fixed in the second-order hole.

[0050] Further, the recoil safety mechanism includes a safety pin 521, a recoil spring 522, a plug screw 523, and a rotor seat 10. The safety pin 521 is composed of a fifth cylinder, a sixth cylinder, and a seventh cylinder from top to bottom. A first blind hole is opened upward at the bottom of the seventh cylinder. The fifth cylinder passes through a preset through hole on the horizontal rotor 511 and extends into a preset blind hole in the housing 1. The top end of the recoil spring 522 abuts against the bottom of the first blind hole, and the bottom end abuts against the bottom of a preset hole in the plug screw 523.

[0051] Further, a C-shaped groove is axially opened upward at the interface between the third-order hole and the fourth-order hole on the housing 1 to make room for the electro-mechanical safety and delay arming mechanism 54, and at the same time, it will increase the explosion relief cavity, which is beneficial to ensuring the explosion isolation safety.

[0052] Further, the material of the housing 1 is made of aluminum alloy or titanium alloy, which helps to reduce the weight. At the same time, the aluminum alloy or titanium alloy material has an electromagnetic shielding effect, so that the electronic control module 7 installed in the housing 1 will not be affected by external electromagnetic interference.

[0053] The main safety principle of an electro-mechanical trigger fuse for a loitering munition of the present invention is as follows:

[0054] The electric detonator 55, the first detonator tube 4, and the booster tube 3 are arranged in series on the fuse axis. The horizontal rotor 511 usually blocks the detonation transfer between the electric detonator 55 and the first detonator tube 4 to achieve explosion isolation safety, that is, once the electric detonator 55 accidentally fires, the first detonator tube 4 and the subsequent booster tube 3 will not accidentally fire and explode. At the component level, the omission of the horizontal rotor 511 can be prevented by visual inspection.

[0055] The recoil safety mechanism 52 and the electro-mechanical safety and delay arming mechanism 54 serve as redundant safety mechanisms for the horizontal rotor 511 to ensure that the horizontal rotor 511 is positioned in the explosion isolation state usually. The recoil spring 522 of the recoil safety mechanism 52 is usually in a pre-compressed state, pushing the safety pin 521 to extend into a specific through hole of the horizontal rotor 511 to prevent the horizontal rotor 511 from rotating. The intermediate safety piece 542 of the electro-mechanical safety and delay arming mechanism 54 extends into the lateral through groove of the horizontal rotor 511 to prevent the horizontal rotor 511 from rotating. At this time, the horizontal rotor 511 turns through a small angle and gets stuck at the sixth cylinder on the safety pin 521, so that the safety pin 521 cannot move down to release the recoil safety.

[0056] Since the center of mass of the horizontal rotor 511 is designed to be on the axis of its rotating shaft, the inertial overload caused by the impact of accidental falling and vibration during service handling and launching will not generate additional torque to cause the horizontal rotor 511 to rotate. That is, the horizontal rotor 511 will always be stuck on the sixth cylinder on the safety pin 521, so that the safety pin 521 cannot move down and release the safety.

[0057] For the convenience of description, Figure 4 That is, on the DD section view, the safety plate 542, electric sales pitch lug 543 and slotted screw 544 on the CC section are numbered 1, the safety plate 542, electric sales pitch lug 543 and slotted screw 544 on the JJ section are numbered 2, and the safety plate 542, electric sales pitch lug 543 and slotted screw 544 on the KK section are numbered 3.

[0058] The normal action sequence is that No. 1 electric sales pitcher 543 acts first, No. 3 electric sales pitcher 543 acts last, and No. 2 electric sales pitcher 543 acts in the middle.

[0059] If No. 2 electric sales pitcher 543 acts before No. 1 electric sales pitcher 543 and No. 3 electric sales pitcher 543 due to an unexpected failure of the control circuit, then when No. 1 electric sales pitcher 543 acts, the horizontal rotor 511 will directly turn to the fault safety state on the other side under the action of the torsion spring 513, and the recoil safety pin 521 will be stuck, and the fuze will directly enter the fault safety state.

[0060] If electric sales pitcher No. 3 543 operates before electric sales pitcher No. 1 543 or electric sales pitcher No. 2 543 due to an unexpected failure of the control circuit, then after electric sales pitcher No. 1 543 and electric sales pitcher No. 2 543 operate normally, the horizontal rotor 511 will rotate past the safety release state under the action of the torsion spring 513 and directly enter the "safety restoration" state, which is also a "fault safety" state.

[0061] When hitting the target or target area, the impact trigger switch located at the warhead is closed, and the electric detonator 55 is ignited through the ignition control circuit, and the fuze acts normally (under the premise of normal release of the safety) or the fire-stopping effect (under the accidental non-release of the safety).

[0062] If the impact trigger switch of the warhead fails to work accidentally due to factors such as the impact posture, impact speed and target strength, the two cross-arranged inertial trigger switches 6 in the fuze will be closed due to the forward impact of the target. As long as one of them is closed, the electric detonator 55 will be ignited in an instant through the ignition control circuit, and the subsequent action of the fuze is the same as above.

[0063] If the inertial trigger switch 6 fails to close accidentally and fails to detonate the electric detonator 55, the electric detonator 55 is detonated again by the firing control circuit at a predetermined time, causing the fuse to self-destruct (under the premise of normal arming) or cut off the fire (in the state of accidental non-arming).

[0064] If the above self-destruction (or fire cut-off) function fails to be realized accidentally due to the failure of the electric detonator 55, at a predetermined time (within 30 minutes), the bypass resistor of the firing circuit dissipates the firing electrical energy of the fuse below the critical misfiring energy of the electric detonator 55, and the fuse completes the dissipation of the electric firing energy to achieve the self-disabling function.

[0065] Before the above self-destruction and self-disabling or after the self-destruction and self-disabling functions fail, if necessary, an instruction can also be provided by the flight control system (including interrupting the predetermined self-destruction function) to activate the No. 3 electric pusher 543. The horizontal rotor 511 continues to rotate under the action of the torsion spring 513, turns through the armed state, and enters the out-of-position safety state again, which is equivalent to "restoring the safety". After confirming "restoring the safety" and turning off the electric trigger firing function, the loitering munition can be recovered after landing, and the safety of the recovery process is guaranteed. After the recovered loitering munition replaces the fuse and the flight battery, it can be reused.

[0066] Since the center of mass of the horizontal rotor 511 component is designed on its axis of rotation, the inertial overload will not generate an additional torque to affect the rotation of the horizontal rotor 511, that is, the remaining torque of the torsion spring 513 will keep the horizontal rotor 511 in the out-of-position "restoring the safety" state.

[0067] The main working process of an electro-mechanical trigger fuse for a loitering munition of the present invention is as follows:

[0068] Instantly before launch, under the control of the safety control electronic module, the No. 1 electric pusher 543 is driven to push open the No. 1 safety piece 542 and release the horizontal rotor 511. The horizontal rotor 511 turns through an angle under the action of the pre-torsion moment of the torsion spring 513 and is circumferentially positioned by the No. 2 safety piece 542. At this time, the horizontal rotor 511 no longer blocks the safety pin 521, and the safety pin 521 is released and can perform a recoil movement axially, which is equivalent to opening the time window for the recoil movement of the safety pin 521.

[0069] During launch, the recoil overload causes the safety pin 521 to recoil and compress the recoil spring 522. After moving into place, it is blocked by the anti-restoring pin 531 and cannot be reset, releasing the horizontal rotor 511.

[0070] After the loitering munition flies away from the launch point by more than the safe distance, with the information provided by the flight control system, under the control of the safety control electronic module, the No. 2 electric pusher 543 is driven to push open the No. 2 safety piece 542, further releasing the horizontal rotor 511. The horizontal rotor 511 turns through a large angle under the further action of the pre-torsion moment of the torsion spring 513 and is circumferentially positioned by the No. 3 safety piece 542. After that, the horizontal rotor 511 is turned upright, and the second detonator tube 512 on it is aligned with the electric detonator 55 and the first detonator tube 4, and the fuze is in the armed state.

[0071] After the munition hits the target or the target area, as long as one of the two types and three in total of the impact trigger switch located at the warhead of the munition and the inertial trigger switch 6 arranged crosswise in the fuze is closed, through the firing control electronic module, the electric detonator 55 fires and explodes, detonating the subsequent second detonator tube 512, and then detonating the subsequent first detonator tube 4 and the booster 3, and the fuze completes the predetermined detonation function.

Claims

1. An electro-mechanical triggered fuse for a loitering munition, characterized in that: It includes a housing (1), a bottom screw (2), a booster tube (3), a first detonator tube (4), a safety and arming mechanism (5), an electronic control module (7), an impact trigger switch, a potting housing (8), a rotor seat (10), a first positioning pin (11), two inertia trigger switches (6) and two second positioning pins (9). The safety and arming mechanism (5) includes a horizontal rotor interrupter mechanism (51), a recoil safety mechanism (52) with a fail-safe function, an anti-recovery mechanism (53), an electric detonator (55) and a compression screw (56), and an electromechanical safety and delay arming mechanism (54). The housing (1) is in the shape of a rotating body and has a first stepped hole opened downward along its central axis from its top surface, which successively includes a first-stage hole, a second-stage hole, a third-stage hole, a fourth-stage hole and a fifth-stage hole. A first through hole communicating with the fifth-stage hole is radially opened on the side surface of the housing (1). The booster tube (3) is arranged in the first-stage hole, and the first detonator tube (4) is arranged in the second-stage hole. The safety and arming mechanism (5) and the rotor seat (10) are mainly arranged in the fourth-stage hole, and the remaining part is arranged in the fifth-stage hole. The bottom screw (2) and the potting housing (8) are arranged in the fifth-stage hole. The first positioning pin (11) extends into the safety and arming mechanism (5) through the first through hole along the radial direction. One end of each of the two second positioning pins (9) is pressed into a preset blind hole of the housing (1) along the axial direction, and the other end extends into a preset blind hole of the rotor seat (10). The electronic control module (7) is arranged in the potting housing (8) and is fixed and protected by potting compound. The two inertia trigger switches (6) arranged in a cross shape are respectively arranged in the rotor seat (10) and between the electronic control module (7) and the rotor seat (10). The electric detonator (55) is the first exploding element in the fuse detonation train. The second detonator tube (512) in the horizontal rotor interrupter mechanism (51) is usually in an interrupter state and faces the first detonator tube (4) in front of it and the electric detonator (55) behind it after the fuse is armed. The recoil safety mechanism (52) with a fail-safe function realizes the recoil safety of the horizontal rotor interrupter mechanism (51). The anti-recovery mechanism (53) prevents the recoil safety mechanism (52) from recovering safety after being armed. The electromechanical safety and delay arming mechanism (54) realizes the delay arming function of the horizontal rotor interrupter mechanism (51). The first detonator tube (4) and the booster tube (3) are used to amplify the output energy of the electric detonator (55) and the second detonator tube (512). The electronic control module (7) is used to control the timing of the horizontal rotor arming release, the delay arming release and the firing of the electric detonator (55). The impact trigger switch is used to realize the impact trigger function, and the inertia trigger switch (6) is used to realize the standby inertia trigger function.

2. The electro-mechanical trigger fuse for a loitering munition according to claim 1, characterized in that: The top surface of the rotor seat (10) is eccentrically provided with a second stepped hole along the axial direction, which is successively a sixth-order hole, a seventh-order hole, and an eighth-order hole from top to bottom. The horizontal rotor explosion-proof mechanism (51) is arranged in the second stepped hole; the bottom of the rotor seat (10) is eccentrically provided with a third stepped hole along the axial direction with diameters decreasing successively from bottom to top, which are successively a ninth-order hole, a tenth-order hole, and an eleventh-order hole. The eleventh-order hole is communicated with the sixth-order hole, and the recoil safety mechanism (52) with a fail-safe function is arranged in the third stepped hole; the center of the bottom of the rotor seat (10) is provided with a fourth stepped hole along the axial direction with diameters decreasing successively, which are successively a twelfth-order hole, a thirteenth-order hole, a fourteenth-order hole, and a fifteenth-order hole. The electric detonator (55) and the compression screw (56) are arranged in the fourth stepped hole; the bottom of the rotor seat (10) is eccentrically provided with a fifth stepped hole along the axial direction upward, which is composed of three sixteenth-order holes, seventeenth-order holes, and eighteenth-order holes with diameters decreasing successively. The fifth stepped hole is radially away from the second stepped hole and is not communicated with the second stepped hole. The electromechanical safety and delay arming mechanism (54) is arranged in the fifth stepped hole; the bottom of the rotor seat (10) is eccentrically provided with three second through holes along the axial direction, and the second through holes are not communicated with other stepped holes. An inertial trigger switch (6) is arranged in one of the second through holes and is fixed by potting glue; a transverse groove is opened upward at the bottom edge of the rotor seat (10), and another inertial trigger switch (6) is arranged in the transverse groove; the horizontal rotor explosion-proof mechanism (51) located in the rotor seat (10) includes a horizontal rotor (511), a second detonator tube (512), a torsion spring (513), an end cover (514), and two countersunk head screws (12); the horizontal rotor (511) is composed of a first cylinder, a second cylinder, a third cylinder, and a fourth cylinder from top to bottom. The first cylinder, the second cylinder, and the third cylinder are located in the sixth-order hole, and the fourth cylinder is located in the seventh-order hole and the eighth-order hole. A radial through groove is opened through the axis of the fourth cylinder, and the third cylinder is limited by the step surface between the sixth-order hole and the seventh-order hole; a sixth stepped hole is opened downward along the axial direction deviating from the axis at the top end of the second cylinder, where the smaller diameter is the nineteenth-order hole at the top and the larger diameter is the twentieth-order hole at the bottom. The second detonator tube (512) is located in the twentieth-order hole and is fixed by bonding or dot riveting; the torsion spring (513) is in a pre-twisted state. One end of it is sleeved on the bottom of the radial through groove of the fourth cylinder, and the other end is stuck in the groove on the hole wall between the eighth-order hole and the twelfth-order hole outside it through its spring head; the end cover (514) is fixed to the bottom of the rotor seat (10) by two countersunk head screws (12). The preset blind hole on the end cover (514) is used to make space for the end of the fourth cylinder and the torsion spring (513). A first axial through groove is opened on the side surface of the end cover (514). The first positioning pin (11) passes through the first through hole and then extends into the first axial through groove. One end of it abuts against the bottom of the first axial through groove, and the other end is fixed by dot riveting at the orifice of the housing (1).The electromechanical safety and delay arming mechanism (54) located inside the rotor seat (10) includes three sets of safety discs (542), three sets of electric pushers (543), three sets of slotted screws (544), three sets of lock washers (541) and three sets of electric pusher plugs (545); the electric pusher (543) is mainly arranged in the seventeenth-order hole, and its bottom is fixed by an electric pusher plug (545) threadedly connected to the seventeenth-order hole, and the electric pusher extends into the eighteenth-order hole; the safety disc (542) is fixed in the preset groove of the rotor seat (10) by a slotted screw (544) and a lock washer (541), and one end of the safety disc (542) extends into the preset axial groove of the horizontal rotor (511).;

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