A high-safety electromechanical trigger fuze at the base of a single-soldier rocket

Abstract

The present invention discloses a high-safety electromechanical trigger fuze at the base of a single-soldier rocket, comprising a main body, a shell, an electric detonator, a detonating tube, a booster tube, a vertical rotor explosion-proof mechanism, a recoil safety mechanism, a gunpowder delayed release explosion-proof and safety mechanism, an inertia needle piercing ignition mechanism, a linear generator module, a gunpowder self-destruction and fire-extinguishing mechanism, a base, an inertia trigger switch, a percussion trigger switch, and an electronic control module. A redundant safety design in a weak launch environment is achieved by utilizing a dual-degree-of-freedom recoil safety mechanism and a gunpowder delayed release explosion-proof and safety mechanism ignited by an igniter on the bottom rocket motor partition, thereby delaying the release of explosion-proof protection. The main ignition is achieved by percussion triggering the detonating electric detonator, while the backup ignition is achieved by triggering the closed detonating electric detonator with an inertia switch and triggering the detonating needle piercing detonator with an inertia firing pin. The fuze has self-destruction and fire-extinguishing functions, ensuring the safe disposal of unexploded explosives caused by fuze misfires. The fuze has a simple structure and is low in cost.

Description

Technical Field

[0001] The invention belongs to a fuze for individual rockets, and in particular relates to a high-safety electromechanical trigger fuze at the base of an individual rocket. Background Art

[0002] The Dian-2 (Russian BP-7) individual rocket fuze has only one recoil safety and lacks a second safety, failing to meet redundancy requirements. Furthermore, the piezoelectric crystals used in the Dian-2 fuze suffer from aging and performance degradation after long-term storage, making reliability unsatisfactory. The integrated ground-contact piezoelectric fuze described in Chinese Patent 201310172651.4 is only part of the fuze, namely the triggering mechanism. Spanish Patent ES07290832T describes an impact piezoelectric fuze, in which the fuze body comprises a piezoelectric generator, a piston, a cover, and a plastic deformation device. The piezoelectric generator and the body are placed together on a bracket and form an anvil. The piston applies mechanical restraint to the generator and receives the impact force transmitted by the cover. The piston includes a plastic deformation device, located between the cover and the body. During impact with the target, the device deforms due to the displacement of the cover, thereby causing the piston to move. This allows the energy consumed by the medium deformation to be used to minimize the shattering of the piezoelectric generator during impact. This piezoelectric fuze also fails to meet the requirements for fuze redundancy and lacks self-destruction, fire-stopping, and self-deactivation features, making it difficult to ensure the safe disposal of explosives after a misfire. The selection of a second arming environment for non-rotating projectile fuzes has always been a key issue in non-rotating projectile fuze design. The 82 rapid-fire mortar base fuze directly opens a hole to allow priming gas pressure to enter the base fuze cavity, posing a safety hazard. If the seal fails, it could cause a chamber or muzzle burst. Similar problems have occurred on certain small-caliber rockets. Summary of the Invention

[0003] To address these issues, a bulkhead igniter is applied to the spacer between the rocket engine and the warhead. While the bulkhead remains sealed, the rocket engine combustion signal is transmitted through the bulkhead igniter into the warhead chamber. This flame ignites the relay tube on the fuze, located at the center of the warhead's base, thus arming the fuze's secondary safety. Bulkhead igniters are a mature technology used in pyrotechnics and are widely used in aerospace. Their application in conventional weapons technology requires miniaturization.

[0004] The present invention aims to provide a highly secure, base-mounted electromechanically triggered fuze for individual rockets. While maintaining the same dimensions as the Dian-2 (Russian BP-7) fuze, it utilizes a dual-degree-of-freedom recoil safety mechanism and a delayed-release explosion-proof safety mechanism ignited by a powder ignited by a base rocket motor diaphragm, achieving a redundant safety design in weak launch environments and delayed explosion-proof release. The primary ignition is achieved by impact-triggered detonation of an electric detonator, while backup ignition is achieved by inertia switches triggering closed detonation of electric detonators and inertia firing pins triggering detonation of needle detonators. The fuze has both self-destruction and fire-stopping functions, ensuring the safe disposal of unexploded explosives resulting from fuze misfires.

[0005] A technical solution for achieving the purpose of the present invention: A high-safety electromechanical trigger fuze at the base of a single-soldier rocket comprises a body, an outer shell, an electric detonator, a detonating tube, a detonating tube, a vertical rotor explosion-proof mechanism, a dual-degree-of-freedom recoil safety mechanism, a gunpowder delayed release explosion-proof and safety mechanism, an inertial needle ignition mechanism, a linear generator module, a gunpowder self-destruction and fire-extinguishing mechanism, a second locating pin, a base, an inertial trigger switch, a bottom cap, an electronic control module and an impact trigger switch; the body is approximately in the shape of a rotating body, and a first step hole is opened from its top surface along its center downward, including a first step hole, a second step hole, a third step hole and a fourth step hole in sequence; a second step hole is opened radially on the outer wall of the body, which is connected to its third step hole, and from left to right are the fifth step hole, the sixth step hole and the seventh step hole in sequence. and the eighth step hole; a third step hole communicating with its seventh step hole is eccentrically provided at the bottom of the body along the axial direction; a fourth step hole communicating with its eighth step hole is eccentrically provided at the bottom of the body along the axial direction, the first step hole, the third step hole and the fourth step hole are coplanar, and the third step hole is located between the fourth step hole and the first step hole; a fifth step hole is eccentrically provided at the bottom of the body along the axial direction; two first blind holes are eccentrically provided at the bottom of the body along the axial direction, and the first blind holes do not interfere with the third step hole, the fourth step hole and the fifth step hole; a first through hole communicating with its sixth step hole is radially provided on the side of the body; the body is arranged in the shell; the detonating tube is arranged in the first step hole, the detonating tube is arranged above the body, abutting the detonating tube below it, and the detonating tube, the detonating tube and the body, i.e., the fuze, are coaxial.The vertical rotor explosion-proof mechanism is arranged in the second step hole, the inertia needle piercing ignition mechanism is arranged in the third step hole, and the linear generator module is arranged in the fifth step hole; the base is arranged in the bottom cap and is fixed to the bottom of the main body through the bottom cap; the two second positioning pins are pressed into the first blind hole along one axial end, and the other end extends into the preset blind hole of the base; the double-degree-of-freedom recoil safety mechanism is arranged in the preset axial step hole in the end cover of the vertical rotor explosion-proof mechanism; the gunpowder delayed release explosion-proof and safety mechanism is arranged in the first through hole; the inertia trigger switch is arranged in the axial preset blind hole on the other side of the end cover; the gunpowder self-destruction and fire-extinguishing mechanism is arranged in the blind hole at the bottom center of the base and the fourth step hole, and a fire transmission channel is preset between the blind hole and the fourth step hole; the electronic control module is arranged between the end cover and the main body; the needle piercing detonator of the inertia needle piercing ignition mechanism is used to sympathetically detonate the flame detonator of the vertical rotor explosion-proof mechanism; the flame detonator of the vertical rotor explosion-proof mechanism is used to detonate the detonating cord , it is usually in a dislocated explosion-proof state, with its axis offset from the axis of the detonating tube at an angle of 60° to 120°; after the fuze is released, it aligns with the detonating tube in front of it and the electric detonator behind it; the double-degree-of-freedom recoil safety mechanism realizes the recoil safety of the vertical rotor explosion-proof mechanism; the gunpowder delayed release explosion-proof and safety mechanism realizes the insurance and delayed release of the vertical rotor explosion-proof mechanism; the linear generator module is driven by the explosion of the first relay tube to generate electricity to power the fuze electronic control module; the gunpowder self-destruction and fire-extinguishing mechanism realizes the self-destruction and fire-extinguishing functions of the ignition failure fuze; the detonating tube and the booster tube are used to amplify the output energy of the flame detonator; the impact trigger switch is an existing technology, located in the warhead, used to realize the impact trigger function, including large-angle ignition and ground-blasting functions; the inertial needle ignition mechanism and the inertial trigger switch realize the backup trigger function of the impact trigger switch of the rocket head fuze; the electronic control module is used to store energy and control the ignition of the electric detonator.

[0006] Compared with the prior art, the present invention has the following significant advantages:

[0007] (1) It meets the requirements of redundant insurance and has the functions of ground explosion, large angle impact, self-destruction, self-deactivation and fire prevention, which can ensure the safety of explosive disposal of unexploded bombs.

[0008] (2) The structure is compact, the volume is not increased, the functions are complete, the cost is low, the safety is high, and the function is reliable. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 The present invention provides a schematic structural diagram of an electromechanical trigger fuze at the base of a high-safety individual rocket along an axial cross-section.

[0010] Figure 2 This is a cross-sectional view of the electromechanical trigger fuze at the base of a high-safety individual rocket of the present invention along the axial BB section; wherein the BB section is perpendicular to Figure 1 profile.

[0011] Figure 3 This is a cross-sectional view of the radial CC section of the electromechanical trigger fuze at the base of a high-safety individual rocket according to the present invention; the CC section passes through the axis of the horizontal rotor of the fuze and is perpendicular to the axis of the fuze.

[0012] Figure 4 This is a radial DD cross-sectional view of the electromechanical trigger fuze at the base of a high-safety individual rocket of the present invention; wherein the DD cross-sectional view passes through the axis of the fuze electric detonator and is perpendicular to the fuze axis.

[0013] Figure 5 This is a cross-sectional view of the electromechanical trigger fuze at the base of a high-safety individual rocket according to the present invention along the axial FF section; wherein the FF section is parallel to the fuze axis.

[0014] Figure 6 This is a cross-sectional view of the electromechanical trigger fuze at the base of a high-safety individual rocket according to the present invention, taken along the axial GG section; wherein the GG section is parallel to the fuze axis.

[0015] Figure 7 This is a cross-sectional view of the electromechanical trigger fuze at the base of a high-safety individual rocket according to the present invention, taken along the axial HH section; wherein the HH section is parallel to the fuze axis.

[0016] Figure 8 The figure is a cross-sectional view of the base electromechanical trigger fuze of a high-safety individual rocket according to the present invention along the radial JJ section; wherein the JJ section is perpendicular to the fuze axis.

[0017] Figure 9 This is a cross-sectional view of the base electromechanical trigger fuze of a high-safety individual rocket according to the present invention along the radial KK section; wherein the KK section is perpendicular to the fuze axis.

[0018] Figure 10 This is a cross-sectional view of the base electromechanical trigger fuze of a high-safety individual rocket according to the present invention along the radial LL section; wherein the LL section is perpendicular to the fuze axis.

[0019] Figure 11 This is a cross-sectional view of the electromechanical trigger fuze at the base of a high-safety individual rocket according to the present invention along the axial MM section; wherein the MM section is parallel to the fuze axis.

[0020] Figure 12 This is a sectional view of the base electromechanical trigger fuze of a high-safety individual rocket according to the present invention along the radial NN section; wherein the NN section is perpendicular to the fuze axis.

[0021] Figure 13 This is a cross-sectional view of the electromechanical trigger fuze at the base of a high-safety individual rocket according to the present invention, taken along the axial PP section; wherein the PP section is parallel to the fuze axis.

[0022] Figure 14 This is a cross-sectional view of the electromechanical trigger fuze at the base of a high-safety individual rocket according to the present invention, taken along the axial QQ section; wherein the QQ section is parallel to the fuze axis.

[0023] In the figure, 1 is the body, 2 is the shell, 3 is the electric detonator, 4 is the detonating tube, 5 is the booster tube, 6 is the vertical rotor explosion-proof mechanism, 7 is the double-degree-of-freedom recoil safety mechanism, 8 is the gunpowder delayed release explosion-proof and safety mechanism, 9 is the inertia needle ignition mechanism, 10 is the linear generator module, 11 is the gunpowder self-destruction and fire-extinguishing mechanism, 12 is the second positioning pin, 13 is the base, 14 is the inertia trigger switch, 15 is the bottom cap, 16 is the electronic control module; 41 is the detonating tube shell, 42 is the explosive charge, 43 is the first reinforcement cap, 51 is the booster tube shell, 52 is the booster charge, 53 is the second reinforcement cap, 61 is the end cover, 62 is the vertical rotor, 6 3 is the first positioning pin, 64 is the torsion spring, 65 is the flame detonator, 66 is the screw, 67 is the spacer, 68 is the third positioning pin, 71 is the safety ball, 72 is the upper inertia cylinder, 73 is the lower inertia cylinder, 74 is the first inertia spring, 75 is the second inertia spring, 76 is the baffle, 81 is the delay charge, 82 is the safety pin, 83 is the spiral coil, 91 is the needle detonator, 92 is the firing pin spring, 93 is the firing pin, 94 is the gasket, 101 is the safety plate, 102 is the linear generator, 103 is the bracket, 104 is the first baffle, 105 is the first relay tube, 111 is the self-destruct delay tube, 112 is the second baffle, and 113 is the second relay tube.

[0024] In the above-mentioned component unit, only the first locating pin, the second locating pin and the screw are two, and the rest are all one. In order to save volume, many parts have multiple functions and participate in different mechanisms. DETAILED DESCRIPTION

[0025] The present invention will be described in further detail below with reference to the accompanying drawings.

[0026] Combine Figures 1 to 14The high-security electromechanical trigger fuze at the base of a single-soldier rocket described in the present invention comprises a body 1, an outer shell 2, an electric detonator 3, a detonating tube 4, a detonating tube 5, a vertical rotor explosion-proof mechanism 6, a dual-degree-of-freedom recoil safety mechanism 7, a gunpowder delayed release explosion-proof and safety mechanism 8, an inertia needle ignition mechanism 9, a linear generator module 10, a gunpowder self-destruction and fire-extinguishing mechanism 11, a second positioning pin 12, a base 13, an inertia trigger switch 14, a bottom cap 15, an electronic control module 16 and an impact trigger switch; the body 1, the outer shell 2 and the base 13 are structural parts; the body 1 is approximately in the shape of a rotating body, and a first step hole is opened from its top surface along its center downward, including a first step hole, a second step hole, a third step hole and a fourth step hole in sequence; the outer wall of the body 1 is radially opened with a second step hole connected to its third step hole, and from left to right are the fifth step holes in sequence. , sixth step hole, seventh step hole and eighth step hole; a third stepped hole communicating with its seventh step hole is eccentrically provided at the bottom of the body 1 along the axial direction; a fourth stepped hole communicating with its eighth step hole is eccentrically provided at the bottom of the body 1 along the axial direction, the first step hole, the third step hole and the fourth step hole are coplanar, and the third step hole is located between the fourth step hole and the first step hole; a fifth stepped hole is eccentrically provided at the bottom of the body 1 along the axial direction; two first blind holes are eccentrically provided at the bottom of the body 1 along the axial direction, the first blind holes do not interfere with the third step hole, the fourth step hole and the fifth step hole; a first through hole communicating with its sixth step hole is radially provided on the side of the body 1; the body 1 is arranged in the shell 2; the detonating tube 4 is arranged in the first step hole, the detonating tube 5 is arranged above the body 1, abutting the detonating tube 4 below it, and the detonating tube 4, the detonating tube 5 and the body 1, i.e., the fuze, are coaxial.The vertical rotor explosion-proof mechanism 6 is arranged in the second stepped hole, the inertia needle ignition mechanism 9 is arranged in the third stepped hole, and the linear generator module 10 is arranged in the fifth stepped hole; the base 13 is arranged in the bottom cap 15 and is fixed to the bottom of the body 1 through the bottom cap 15; the two second positioning pins 12 are respectively pressed into the first blind hole along one end of the axial direction, and the other end extends into the preset blind hole of the base 13; the double-degree-of-freedom recoil safety mechanism 7 is arranged in the preset axial stepped hole in the end cover 61 of the vertical rotor explosion-proof mechanism 6; the gunpowder delayed release explosion-proof and safety mechanism 8 is arranged in the first through hole ; The inertia trigger switch 14 is arranged in the axial preset blind hole on the other side of the end cover 61; the gunpowder self-destruction and fire-extinguishing mechanism 11 is arranged in the blind hole and the fourth stepped hole at the center bottom of the base 13, and a fire transmission channel is preset between the blind hole and the fourth stepped hole; the electronic control module 16 is arranged between the end cover 61 and the body 1; the needle puncture detonator 91 of the inertia acupuncture ignition mechanism 9 is used to sympathetically detonate the flame detonator 65 of the vertical rotor explosion-proof mechanism 6; the flame detonator 65 of the vertical rotor explosion-proof mechanism 6 is used to detonate the detonating tube 4, which is usually in a dislocated explosion-proof state, and its axis is staggered with the axis of the detonating tube. Angle of 60° to 120°; after the fuze is released, the detonating tube 4 in front of it and the electric detonator 3 behind it are aligned; the impact trigger switch adopts mature technology and is independently set, not shown in the figure; the double-degree-of-freedom recoil safety mechanism 7 realizes the recoil safety of the vertical rotor explosion-proof mechanism 6; the gunpowder delayed release explosion-proof and insurance mechanism 8 realizes the insurance and delayed release of the vertical rotor explosion-proof mechanism 6; the linear generator module 10 is driven by the explosion of the first relay tube 105 to generate electricity to power the fuze electronic control module 16; the gunpowder self-destruction and fire-extinguishing mechanism 11 It realizes the self-destruction and fire-extinguishing functions of the ignition failure fuse; the detonating tube 4 and the booster tube 5 are used to amplify the output energy of the flame detonator 65; the impact trigger switch is an existing technology, located in the warhead, and is used to realize the impact trigger function, including large-angle ignition and ground-breaking (small-angle ignition) functions; the inertial needle ignition mechanism 9 and the inertial trigger switch 14 realize the backup trigger function of the impact trigger switch of the rocket head fuze, among which the inertial trigger switch 14 is a mature technology and can realize the ground-breaking (small-angle ignition) function; the electronic control module 16 is used to store energy and control the ignition of the electric detonator 3.

[0027] Furthermore, the vertical rotor explosion-proof mechanism 6 includes an end cover 61, a vertical rotor 62, a torsion spring 64, a flame detonator 65, a spacer 67, a third positioning pin 68, a body 1, two first positioning pins 63 and two screws 66. The end cover 61 is located in the fifth step hole, and its inner end surface is close to the bottom of the fifth step hole. The end cover 61 is fixed to the body 1 by the two first positioning pins 63 and the two screws 66; the vertical rotor 62 is composed of a first cylinder, a second cylinder, a third cylinder, and a fourth cylinder from left to right. The first cylinder passes through the preset through hole of the end cover 61 to the right, the second cylinder, the third cylinder and the fourth cylinder are arranged in the sixth-step hole, the fifth cylinder is arranged in the seventh-step hole, and the first cylinder is provided with a first axial through groove. The vertical rotor 62 is axially limited by the inner end face of the fourth cylinder, the bottom of the sixth-step hole and the inner end face of the end cover 61; a second-step through hole is provided along the radial direction of the third cylinder and at an angle of 60° to 120° to the axis of the detonator tube, of which the larger diameter is the ninth-step hole and the smaller diameter is The tenth step hole, the flame detonator input end is located inwardly in the ninth step hole and fixed by point rivets; in the assembled state, the axis of the flame detonator and the axis of the detonating tube form an angle of 60° to 120°; the bottom of the fifth cylinder is slightly offset from its center and a second blind hole is provided along the vertical rotor axis, and the second blind hole is connected to the tenth step hole; the side of the fourth cylinder is provided with a first fire transmission hole along the vertical rotor radial direction, and the first fire transmission hole is connected to the second blind hole; the third cylinder is provided with a third blind hole eccentrically along the vertical rotor axis, and the third positioning pin 68 is stepped, and its straight The end with a larger diameter is pressed into the third blind hole and fixed by point rivets, and the end with a smaller diameter is inserted into the preset arc groove on the end cover 61; the torsion spring 64 is in a pre-twisted state, one end of which is sleeved in the first axial through groove, and the other end is embedded in the eccentric axial hole on the end cover 61; a sixth stepped hole is opened on the side of the end cover 61 along the axis parallel to the fuze, and the double-degree-of-freedom recoil safety mechanism 7 is arranged in the stepped hole; a fourth blind hole is opened on the other side of the end cover 61 along the axis parallel to the fuze, and the inertia trigger switch 14 is arranged in the blind hole.

[0028] Furthermore, the vertical rotor 62 is provided with two explosion transmission channels, namely, central axial electric ignition (including head impact trigger switch, backup inertia trigger switch 14 and electronic delayed self-destruction / extinguishing control), radial mechanical ignition (backup inertia needle pricking ignition mechanism 9) and flame ignition (through needle pricking detonator 91 after delay tube timing), which improves the reliability of triggering ignition, self-destruction ignition and extinguishing fire while ensuring the instantaneousness of the fuse.

[0029] Furthermore, a pressure relief hole is provided on the main body 1 near the output end of the detonator, and a spacer 67 is provided at the hole opening. There is also a shell 1 outside the spacer 67, which is conducive to solving the contradiction between explosion-proof safety and initiation safety.

[0030] Furthermore, a radial input needle detonator 91 is eccentrically arranged on the shaft of the vertical rotor 62. Normally, the shaft wall blocks the firing pin 93 from reaching the detonator. After the vertical rotor 62 is straightened, the needle puncture firing channel is opened and no longer blocks the firing, thereby simplifying the structure.

[0031] Furthermore, the power generation function of the linear generator module 10, the fire extinguishing and self-destruction function of the gunpowder self-destruction and fire extinguishing mechanism 11, and the insurance and delayed release of the gunpowder explosion-proof and safety mechanism 8 share the ignition environment of the bottom rocket engine partition igniter, which simplifies the structure, makes it compact, fully functional, highly safe, and reliable.

[0032] Furthermore, a second axial through groove is eccentrically opened on the side of the body 1 along its axis, and a third axial through groove is eccentrically opened on the side of the base 13 along its axis. The second axial through groove and the third axial through groove have the same groove type and can be visually aligned during assembly.

[0033] Furthermore, the gunpowder delayed release explosion-proof and safety mechanism 8 includes a delay charge 81, a safety pin 82, a coil 83, a main body 1, an outer shell 2, a base 13 and a second relay tube 113. The delay charge 81, the safety pin 82 and the coil 83 are all in the shape of a rotating body. The coil 83 has a two-step through hole along its axial direction, of which the larger diameter is the eleventh-step hole and the smaller diameter is the twelfth-step hole; the delay charge 81 is arranged in the eleventh-step hole and the twelfth-step hole, and a through hole is opened in the center thereof; the left end of the safety pin 82 is hemispherical and abuts against the preset arc groove on the inner end face of the third cylinder, and its right end extends into the eleventh-step hole and abuts against the left end face of the delay charge 81.

[0034] Furthermore, the linear generator module 10 includes a safety plate 101, a linear generator 102, a bracket 103, a first retaining ring 104, a first relay tube 105 and a body 1; the fifth stepped hole is the twelfth step hole, the thirteenth step hole and the fourteenth step hole from bottom to top, the upper end face of the safety plate 101 is against the step surface between the thirteenth step hole and the fourteenth step hole, and the lower end face is against the upper end face of the linear generator 102; the first retaining ring 104 is fixed in the twelfth step hole by spot riveting; the bracket 103 is set between the linear generator 102 and the first step hole A retaining ring 104 is provided; a seventh step hole is opened on the top surface of the bracket 103 along its axial direction, and from top to bottom are the fifteenth step hole, the sixteenth step hole and the seventeenth step hole. The first relay tube 105 is fixed in the seventeenth step hole with rivets, and its output end is against the step surface between the sixteenth step hole and the seventeenth step hole, and its input end is against the upper end surface of the first retaining ring 104; part of the magnetic core of the linear generator 102 extends into the fifteenth step hole; a blind hole is eccentrically provided along the axial direction of the body, which is connected to the bottom of the fourteenth step hole, and the output line of the linear generator 102 is led out from the blind hole.

[0035] Furthermore, the gunpowder self-destruction and fire-extinguishing mechanism 11 includes a self-destruction delay tube 111, a second retaining ring 112, a second relay tube 113 and a body 1; a sixth blind hole is opened axially upward along the center at the bottom end of the base 13, and the input end of the second relay tube 113 is fixed in the sixth blind hole with a downward rivet; a second fire transmission hole is opened downward on the upper end surface of the base 13, and the hole is connected to the sixth blind hole, serving as a detonation transmission channel for the second relay tube 113; the fourth step hole is the eighteenth step hole from bottom to top The second retaining ring 112 is riveted and fixed in the eighteenth-step hole, and the input end of the self-destruction delay tube 111 is fixed in the nineteenth-step hole with the input end facing downward. The output end of the self-destruction delay tube 111 is radially aligned with the rotor shaft. Regardless of whether the vertical rotor 62 is rotated normally, the self-destruction delay tube 111 will detonate the needle detonator 91 in the rotor shaft. This ensures the reliability of the fuze self-destruction and the fire transmission.

[0036] The main safety principles of the high-safety electromechanical trigger fuze at the base of a single-soldier rocket of the present invention are as follows:

[0037] During service, the fuze is in its explosion-proof state, or factory-assembled state. Even credible impacts and vibrations, including accidental drops and transport vibrations, will not cause the fuze to accidentally arm or explode. The dual-degree-of-freedom recoil safety mechanism 7, via its safety ball 71 and the powder-delayed explosion-proof safety mechanism 8, via its safety pin 82, provides redundant safety for the explosion-proof vertical rotor 62, ensuring that the vertical rotor 62 is normally positioned in its explosion-proof state. If the fuze or projectile falls toward any target at a height below 1.5 meters, in any posture, the dual-degree-of-freedom recoil safety mechanism 7 will not accidentally arm the vertical rotor 62. If the fuze head accidentally falls downward to the ground, the firing pin spring 92 within the inertia-stirring firing mechanism 9 ensures that the firing pin will not strike the vertical rotor shaft wall and damage the firing pin tip. Failure of any individual safety mechanism will not arm the vertical rotor 62, preventing it from accidentally rotating upright. This ensures the safety of the fuze even in the event of a credible safety mechanism failure. When the vertical rotor 62 is not armed, the axis of the detonator tube 4 and the flame detonator 65, located within the first-stage hole, are misaligned. Even if the flame detonator 65 accidentally ignites or explodes, the detonator tube 4 will not explode. When the vertical rotor 62 is not armed, the ninth-stage hole, which serves as the explosive transmission path, is misaligned with the detonator tube 4. Even if the needle detonator 91 accidentally ignites or explodes, the flame detonator 65 will detonate, but not the detonator tube 4. This renders the fuze explosion-proof and flame-proof. Pressure relief cavities surround both the needle detonator 91 and the flame detonator 65. If either or both of these detonators accidentally ignite or explode, this ensures that the internal pressure of the fuze decays, preventing disintegration and the generation of dangerous fragments.

[0038] The main working process of the high-safety individual rocket base electromechanical trigger fuze of the present invention is as follows:

[0039] When the rocket is launched, the upper and lower inertia cylinders in the dual-degree-of-freedom recoil safety mechanism 7 will compress the inertia spring under the action of recoil overload and move downward until the upper end surface of the upper inertia cylinder 72 is lower than the safety ball 71, releasing the limit on the safety ball 71. The safety ball 71 will move downward along the inclined hole under the action of recoil until it falls into the blind hole preset on the upper end surface of the upper inertia cylinder 71, releasing the first safety of the vertical rotor 62. The rocket engine combustion signal is transmitted through the partition igniter, while the partition remains sealed, through the partition and into the warhead chamber. The flame ignites the second relay tube 113 located on the fuze at the center of the warhead bottom. A portion of the flame generated by the combustion of the second relay tube 113 is transmitted through the second flame transmission hole to the fourth stepped hole, and then through the center hole of the second retaining ring 112 to ignite the self-destruction delay tube 111. Another portion of the flame is transmitted through the second flame transmission hole, the third axial slot, and the second axial slot to the gunpowder delayed release explosion-proof and safety mechanism 8, igniting the delay charge 81 through the center hole of the spiral coil 83. The remaining portion of the flame is transmitted through the second flame transmission hole to the fifth stepped hole, and then through the first retaining ring 104 to ignite the first relay tube 105. After the first relay tube 105 ignites and explodes, the explosion is transmitted through the sixteenth stepped hole to the magnetic core of the linear generator 102, pushing it upward to shear the fuse 101, thereby cutting the magnetic lines of force in the coil to generate electricity to power the electronic control module 16.

[0040] During the rocket's flight, the combustion of delay charge 81 causes the delay charge 81 in the explosion-proof and safety mechanism 8, which delays the release of the gunpowder, to change from solid to gaseous, releasing the safety pin 82, which in turn releases the safety pin 82 from the vertical rotor 62. Subsequently, under the action of its pre-torque, the torsion spring 64 causes the vertical rotor 62, via its arcuate groove, to push against the safety pin 82 and rotate through a predetermined angle (60° to 120°), aligning the tenth-step hole with, or substantially aligning with, the axis of the detonating tube. This aligns the detonation sequence, effectively aligning the flame detonator 65 in the vertical rotor 62 with the detonating tube 4, disarming the fuse and placing it in a ready-to-fire state.

[0041] After the rocket hits the target or target area, including at a large angle, a small angle and a ground-grazing explosion, the impact trigger switch located at the head of the rocket is closed, and the electric detonator 3 is ignited through the firing control circuit, and the fuze functions normally (under the premise of normal release of the safety) or the fire-stop function (under the condition of accidental non-release of the safety).

[0042] If the impact trigger switch at the head of the rocket fails to work accidentally due to factors such as the impact posture, impact speed and target strength, the inertial trigger switch 14 located in the fourth blind hole of the end cover 61 is closed, and the electric detonator 3 ignites and explodes through the ignition control electronic control module 16, detonating the flame detonator 65 located in the ninth-step hole. The flame detonator 65 explodes through the tenth-step hole, i.e., the detonation channel, to detonate the subsequent detonating tube 4, and then detonate the subsequent detonating tube 5, and the fuze completes the predetermined backup inertial electric trigger detonation effect.

[0043] If the above process still fails, i.e., due to various unexpected reasons, the electric detonator 3 fails to fire or fails to reliably detonate the flame detonator 65 after firing, then when the rocket hits the target or target area, the firing pin 93 in the fuze will move forward under the action of the forward overload, compressing the firing pin spring 92, causing the firing pin tip on it to penetrate the blind hole pre-opened in the fifth cylindrical side of the vertical rotor 62 and pierce the needle detonator 91. After the needle detonator 91 fires, it detonates the flame detonator 65, and then detonates the subsequent detonator tube 4 through the tenth-step hole, i.e., the detonation channel, and then detonates the subsequent detonator tube 5, thus achieving the predetermined backup inertial triggering function of the fuze. If the rocket lands at a small angle, i.e., by ground contact, the inertial trigger switch 14 can still move according to the predetermined operating process, ensuring that the electric detonator 3 fires and explodes, ensuring the reliable ground contact explosion function of the fuze.

[0044] If the fuze fails to arm properly, or unexpectedly fails to trigger after arming, the delayed self-destruct delay tube 111 will detonate the needle detonator 91 in the vertical rotor 62 through the ninth-step hole after the rocket lands. This in turn detonates the flame detonator 65 in the tenth-step hole through the ninth-step hole, and simultaneously detonates the electric detonator 3 below it through the first fire transmission hole in the fourth cylinder. The fuze will then either self-destruct (assuming the safety has been disarmed) or cease to fire (assuming the safety has not been disarmed). A fuze in the cease to fire state ensures the safe disposal of unexploded ordnance. If the firing pin 93 properly pierces the needle detonator 91, the delayed self-destruct delay tube 111 will also explode. In addition to the aforementioned self-destruction of the delay tube gunpowder, the fuze also features an electronically timed self-destruct function implemented by the electronic control module 16. While ensuring the full ballistic flight of the rocket, the electric detonator 3 is detonated after a set time. If the fuze arming occurs, it self-destructs. If the fuze unexpectedly fails to arm, it ceases to fire. In addition, the fuze electronic control module 16 is also designed with an electric ignition energy dissipation characteristic. With the launch timing, the rocket will dissipate the electric ignition energy intended for the electric detonator 3 within a few minutes after landing.

[0045] The fuze booster is made of polyblack-14, which meets the requirements of GJB373B-2019 "Fuze Safety Design Guidelines" for boosters, and can ensure that it will not accidentally ignite and cause premature explosion during assembly, service processing and launch.

Claims

1. A high-security electromechanical trigger fuze for a rocket projectile, characterized by: The invention comprises a body (1), a shell (2), an electric detonator (3), a detonating tube (4), a detonating tube (5), a vertical rotor explosion-proof mechanism (6), a double-degree-of-freedom recoil safety mechanism (7), a gunpowder delayed release explosion-proof and safety mechanism (8), an inertia needle piercing ignition mechanism (9), a linear generator module (10), a gunpowder self-destruction and fire-extinguishing mechanism (11), a second positioning pin (12), a base (13), an inertia trigger switch (14), a bottom cap (15), an electronic control module (16) and a collision trigger switch; the body (1) is in the shape of a rotating body, and a first step hole is opened from its top surface along its center downward, which includes a first step hole, a second step hole, a third step hole and a fourth step hole in sequence; the outer wall of the body (1) is radially opened. There is a second step hole connected to the third step hole, and from left to right are the fifth step hole, the sixth step hole, the seventh step hole and the eighth step hole; the bottom of the body (1) is eccentrically provided with a third step hole connected to the seventh step hole; the bottom of the body (1) is eccentrically provided with a fourth step hole connected to the eighth step hole, the first step hole, the third step hole and the fourth step hole are coplanar, and the third step hole is located between the fourth step hole and the first step hole; the bottom of the body (1) is eccentrically provided with a fifth step hole; the bottom of the body (1) is eccentrically provided with two first blind holes, the first blind holes do not interfere with the third step hole, the fourth step hole and the fifth step hole; the side of the body (1) is radially provided with a The first through hole of the hole; the body (1) is arranged in the shell (2); the detonating tube (4) is arranged in the first step hole, the detonating tube (5) is arranged above the body (1), the bottom surface of the detonating tube (5) is adjacent to the detonating tube (4), and the detonating tube (4), the detonating tube (5) and the body (1) are coaxial; the vertical rotor flameproof mechanism (6) is arranged in the second step hole, the inertia needle ignition mechanism (9) is arranged in the third step hole, and the linear generator module (10) is arranged in the fifth step hole; the base (13) is arranged in the bottom cap (15) and is fixed to the bottom of the body (1) through the bottom cap (15); the two second positioning pins (12) are respectively pressed into the first blind hole at one end along the axial direction, and the other end extends into the base (13 ) in a preset blind hole; a double-degree-of-freedom recoil safety mechanism (7) is arranged in a preset axial stepped hole in the end cover (61) of the vertical rotor explosion-proof mechanism (6); a gunpowder delayed release explosion-proof and safety mechanism (8) is arranged in the first through hole; an inertia trigger switch (14) is arranged in an axial preset blind hole on the other side of the end cover (61); a gunpowder self-destruction and fire-extinguishing mechanism (11) is arranged in a blind hole at the center bottom of the base (13) and a fourth stepped hole, and a fire transmission channel is preset between the blind hole and the fourth stepped hole; an electronic control module (16) is arranged between the end cover (61) and the body (1); a needle detonator (91) of the inertia needle ignition mechanism (9) is used to sympathetically detonate a flame detonator (65) of the vertical rotor explosion-proof mechanism (6);The flame detonator (65) of the vertical rotor explosion-proof mechanism (6) is used to detonate the detonating tube (4). It is usually in a dislocated explosion-proof state. Its axis is staggered with the axis of the detonating tube at an angle of 60° to 120°. After the fuse is released, it is aligned with the detonating tube (4) in front of it and the electric detonator (3) behind it; the double-freedom recoil safety mechanism (7) realizes the recoil safety of the vertical rotor explosion-proof mechanism (6); the gunpowder delayed release explosion-proof and safety mechanism (8) realizes the insurance and delayed release of the vertical rotor explosion-proof mechanism (6); the linear generator module (10) is connected to the first relay tube (105) The explosion drives the generated electricity to power the fuze electronic control module (16); the gunpowder self-destruction and fire-extinguishing mechanism (11) realizes the self-destruction and fire-extinguishing functions of the fuze with ignition failure; the detonating tube (4) and the booster tube (5) are used to amplify the output energy of the flame detonator (65); the impact trigger switch is located in the warhead and is used to realize the impact trigger function, including large-angle ignition and ground-blasting functions; the inertia needle ignition mechanism (9) and the inertia trigger switch (14) realize the backup trigger function of the impact trigger switch of the rocket head fuze; the electronic control module (16) is used to store energy and control the firing of the electric detonator (3).

2. The high-security electromechanical trigger fuze for the base of a single-soldier rocket according to claim 1, characterized in that: The vertical rotor explosion-proof mechanism (6) comprises an end cover (61), a vertical rotor (62), a torsion spring (64), a flame detonator (65), a spacer (67), a third positioning pin (68), two first positioning pins (63) and two screws (66). The end cover (61) is located in the fifth step hole, and its inner end surface is close to the bottom of the fifth step hole. The end cover (61) is fixed to the body (1) by the two first positioning pins (63) and the two screws (66); the vertical rotor (62) is composed of a first cylinder, a second cylinder, The third cylinder, the fourth cylinder and the fifth cylinder are composed of the first cylinder passing through the preset through hole of the end cover (61) to the right, the second cylinder, the third cylinder and the fourth cylinder are arranged in the sixth step hole, and the fifth cylinder is arranged in the seventh step hole. The first cylinder is provided with a first axial through groove, and the vertical rotor (62) is axially limited by the inner end face of the fourth cylinder and the bottom of the sixth step hole and the inner end face of the end cover (61); a second-order through hole is provided along the radial direction of the third cylinder and at an angle of 60° to 120° with the axis of the detonator tube, wherein the larger diameter is the ninth step hole, and the straight The tenth-step hole has a smaller diameter, and the input end of the flame detonator (65) is located inwardly in the ninth-step hole and fixed by point rivets; in the assembled state, the axis of the flame detonator and the axis of the detonating tube form an angle of 60° to 120°; a second blind hole is eccentrically provided at the bottom of the fifth cylinder along the vertical rotor axis, and the second blind hole is connected to the tenth-step hole; a first fire transmission hole is opened on the side of the fourth cylinder along the vertical rotor radial direction, and the first fire transmission hole is connected to the second blind hole; a third blind hole is opened eccentrically along the vertical rotor axis, and the third positioning pin (68) is stepped, and the larger diameter one is provided. The end is pressed into the third blind hole and fixed by point riveting, and the end with a smaller diameter is inserted into the arc groove preset on the end cover (61); the torsion spring (64) is in a pre-twisted state, one end of which is sleeved in the first axial through groove, and the other end is embedded in the eccentric axial hole on the end cover (61); a sixth stepped hole is opened on the side of the end cover (61) along the axis parallel to the fuze, and the double-degree-of-freedom recoil safety mechanism (7) is arranged in the sixth stepped hole; a fourth blind hole is opened on the other side of the end cover (61) along the axis parallel to the fuze, and the inertia trigger switch (14) is arranged in the fourth blind hole.

3. The high-security electromechanical trigger fuze for the base of a single-soldier rocket according to claim 2, characterized in that: The vertical rotor (62) is provided with two explosion transmission channels, namely, electric ignition in the central axis, mechanical ignition in the radial direction and flame ignition, which improves the reliability of trigger ignition, self-destruction ignition and fire suppression while ensuring the instantaneousness of the fuze.

4. The high-security electromechanical trigger fuze for the base of a single-soldier rocket according to claim 2, characterized in that: A pressure relief hole is provided on the body (1) near the output end of the flame detonator (65), and a spacer (67) is provided at the hole opening. A housing (2) is provided outside the spacer (67), which is conducive to resolving the contradiction between explosion-proof safety and detonation safety.

5. The high-security electromechanical trigger fuze for the base of a single-soldier rocket according to claim 2, characterized in that: The vertical rotor (62) is eccentrically provided with a radial input needle piercing detonator (91). Usually, there is an obstruction of the shaft wall, and the firing pin (93) cannot be pierced. After the vertical rotor (62) is turned straight, the needle piercing firing channel is opened and the needle piercing firing is no longer obstructed, thereby simplifying the structure.

6. The high-security electromechanical trigger fuze for the base of a single-soldier rocket according to claim 1, characterized in that: The power generation function of the linear generator module (10), the fire-extinguishing and self-destruction functions of the gunpowder self-destruction and fire-extinguishing mechanism (11), and the insurance and delayed release of the gunpowder explosion-proof and insurance mechanism (8) share the ignition environment of the bottom rocket engine partition igniter, simplifying the structure, making it compact, fully functional, highly safe, and reliable.

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