CN117870478A - Unmanned aerial vehicle carries balanced big gun grenade warhead machinery trigger fuze - Google Patents

Abstract

The invention discloses a mechanical trigger fuse of a warhead of an unmanned aerial vehicle-mounted balance grenade, which is assembled at the front end of the unmanned aerial vehicle-mounted balance grenade and comprises an upper body, a covering service safety mechanism, an explosion-proof mechanism, a double-freedom-degree recoil safety mechanism, an aerodynamic rotor wing delay release safety mechanism and a collision trigger needle ignition mechanism, a recoil safety mechanism, an anti-recovery mechanism of the recoil safety mechanism, a gunpowder timing self-destruction mechanism, a double-freedom-degree recoil needle ignition mechanism, an anti-recovery mechanism of the explosion-proof mechanism, a detonating tube and a detonating tube. The design of redundant insurance in a weak emission environment is realized by utilizing manual operation, squat and head-on airflow to remove the insurance, and the related requirements of GJB373B-2019 'fuze safety design criterion' are met. The fuze is ignited by utilizing a collision triggering mode, has self-destruction and fire-insulation functions, and can ensure the explosion treatment safety of the non-explosive; simple structure and low cost.

Description

Unmanned aerial vehicle carries balanced big gun grenade warhead machinery trigger fuze

Technical Field

The invention belongs to a no-recoil gun fuze technology, and particularly relates to an unmanned aerial vehicle-mounted balance gun grenade warhead mechanical trigger fuze.

Background

The non-recoil gun is an artillery system which uses gunpowder gas to spray or cast a balance body backwards to eliminate the recoil of the gun body and make the gun body reach basic balance. Compared with the traditional gun system, the recoil force of the non-recoil gun is reduced, and the non-recoil gun can be kept stable better due to the design, so that the shooting precision and the shooting frequency are improved. Because the no recoil gun is different from a common artillery, the structure, performance and principle of the fuze of the accessory are also different. Literature (reviewed in swedish ancient tatar fuze technology (xiaojian, wang Yushi, wen Quan, etc.. Reviewed in swedish ancient tatar fuze technology [ J ]. The detection and control school report, 2018, 40 (04): 34-39.)) discusses, and in the six and seventies, china developed a fumeless weapon system, mainly 65-type 82mm fumeless and 78-type 82mm fumeless, wherein 78-type 82mm fumeless includes DR04, no-dure-3 and electric-1-type fumels. The No-recoil cannon of M3 type ancient Taff was matched with a rocket extended range projectile at the end of 70 th century, and a novel primer F/551 for detonating at the bottom of the projectile was also developed. Along with the development of the non-recoil firecracker and ammunition thereof, the types and types of the non-recoil firecracker fuse are more and more rich, the same fuse type can be adapted to different types of similar ammunition systems, and the universality is stronger. The fuze models of the current ancient Taff recoil-free firecracker equipment in Sweden are ZTZ A1, FFV447, FFV 502, FFV 957 and F/551.

ZZT 42A1 gunpowder time warhead fuze matched with 545B type lighting bomb is relieved by utilizing a recoil overload environment, and the fuze is ensured to be in a safe state when the fuze does not reach the target by means of delay medicine disc setting time. The fuse design has no redundant insurance, and does not meet the related requirements of MIL-STD-1316C fuse safety design criterion.

FFV 957 bullet trigger fuze for 469B type smoke bullet, the first safety is released by the recoil overload environment, the second safety is released by the rotation environment, and other safety is to fix the firing pin at the safety position by using a spring loaded safety pin and release the safety by the rotation environment. The fuse has the redundancy safety characteristic, but has no fire-proof and self-destruction functions, cannot ensure the safety of the explosion treatment of the non-explosive and does not meet the related requirements of MIL-STD-1316C fuse safety design rule.

FFV 502 primer matched with 502 type dual-purpose explosion-proof bomb uses the recoil overload environment to release the first safety and uses the rotor lock to release the second safety. The fuse has the redundancy safety characteristic, but has no fire-proof and self-destruction functions, and does not meet the related requirements of MIL-STD-1316C fuse safety design rule.

The FFV 447 warhead mechanical time/flash trigger fuse for the 441B type explosive-proof bomb was configured with a first safety for recoil safety and a second safety for centrifugal safety, the other safety including a safety piece locking clockwork and spring loaded safety pin to lock the striker in the safe position. The fuse has the redundancy safety characteristic, but has no self-destruction and fire-insulation functions in design, cannot ensure the safety of the explosion treatment of the non-explosive, and does not meet the related requirements of MIL-STD-1316C fuse safety design rule.

The F/551 primer for 551 type soft-shelled turtle shell is relieved by using a recoil environment, no redundant safety is designed, no fire-insulating and self-destroying functions are provided, the safety of explosive explosion treatment of the non-explosive bomb cannot be ensured, and the related requirements of MIL-STD-1316C primer safety design criteria are not met.

Disclosure of Invention

The invention aims to provide a mechanical trigger fuze for the warhead of an unmanned aerial vehicle-mounted balance grenade, which is assembled at the front end of the unmanned aerial vehicle-mounted balance grenade, and the safety is relieved by manual operation, squat and head-on airflow, so that the redundant safety design under the weak emission environment is realized, and the related requirements of GJB373B-2019 fuze safety design criterion are met. The fuze is ignited by utilizing a collision triggering mode, has self-destruction and fire-insulation functions, and can ensure the explosion treatment safety of the non-explosive.

The technical solution for realizing the purpose of the invention is as follows: an unmanned aerial vehicle-mounted balance grenade warhead mechanical triggering fuze comprises an upper body, a cover cap service safety mechanism, an explosion-proof mechanism, a double-degree-of-freedom recoil safety mechanism, an aerodynamic rotor wing delay release safety mechanism and a collision trigger needle piercing firing mechanism, a recoil safety mechanism reverse recovery mechanism of the gunpowder timing self-destruction mechanism, a double-degree-of-freedom recoil needle piercing firing mechanism, a flame-proof mechanism reverse recovery mechanism, a detonating tube and a detonating tube; the upper body is approximately a revolution body, the outer contour of the upper half part is a round table with a small upper part and a big lower part, the outer contour of the lower half part is a cylinder, and external threads are arranged on the lower half part; a first stepped hole with diameters decreasing in sequence is formed upwards from the bottom surface of the upper body along the axis of the upper body, and the first stepped hole, the second stepped hole and the third stepped hole are sequentially formed; three radial through hole groups communicated with the second step holes are uniformly distributed on the outer side wall of the upper half part of the upper body along the axial direction, namely a first through hole group, a second through hole group and a third through hole group, and 8 radial through holes are uniformly distributed on each radial through hole group along the circumferential direction; a fourth through hole communicated with the first-stage hole is formed in the outer side wall of the upper body in the radial direction; the body is approximately a revolution body, the outer contour of the upper half part of the body is a round table with a small upper part and a big lower part, the outer contour of the lower half part of the body is a cylinder, and an external thread connected with the projectile body is arranged on the lower half part of the body; a second stepped hole is formed upwards from the bottom surface of the body along the axis of the body, and sequentially comprises a fourth stepped hole and a fifth stepped hole, wherein the diameter of the fourth stepped hole is larger than that of the fifth stepped hole; after the cylinder of the lower half part of the upper body is fixedly connected with the fifth-order hole through threads, the round table of the upper half part of the outer contour of the body is connected with the round table of the upper half part of the outer contour of the upper body to form a larger round table, and the larger round table is used as an exposed part of the fuze, namely an outer conical surface; the cover cap in the cover cap service safety mechanism is buckled on the fuze outer conical surface; the explosive-proof mechanism, the dual-degree-of-freedom recoil safety mechanism and the detonating tube of the explosive-proof mechanism are all arranged in a fourth-order hole of the body, and the gunpowder timing self-destruction mechanism and the dual-degree-of-freedom recoil needling ignition mechanism are both arranged in the explosive-proof mechanism; the aerodynamic rotor wing delay releasing safety mechanism and the impact trigger acupuncture ignition mechanism are arranged in the first-stage hole, the second-stage hole, the fifth-stage hole and the fourth hole; the recoil safety mechanism and the reverse recovery mechanism of the recoil safety mechanism are both arranged in the aerodynamic rotor wing delay release safety mechanism and the impact trigger needle spark ignition mechanism, the detonating tube is arranged below the detonating tube, the upper part of the detonating tube is arranged in the fourth-order hole, and the lower part of the detonating tube extends out of the body; the cover service safety mechanism is mainly used for delaying the release of the safety mechanism and the collision of the aerodynamic rotor wing and triggering the safety of the acupuncture ignition mechanism during service treatment and sealing the radial through hole on the upper body; the explosion-proof mechanism is used for ensuring that the explosive element in the explosion-proof mechanism is in a dislocation state at ordinary times, preventing the explosive element from accidental ignition from causing in-line charge in a post-detonating tube and aligning the detonating sequence in a releasing safety state; the dual-degree-of-freedom squat safety mechanism realizes squat safety of the explosion-proof mechanism; the aerodynamic rotor wing delay release safety mechanism and the impact trigger acupuncture ignition mechanism realize the impact trigger ignition of the acupuncture fire cap of the explosion-proof mechanism; the recoil safety mechanism realizes the recoil safety of the aerodynamic rotor wing delay release safety mechanism and the impact trigger acupuncture ignition mechanism; the anti-restoring mechanism of the squat safety mechanism is used for preventing the squat safety mechanism from restoring safety after releasing the safety; the gunpowder timing self-destruction mechanism realizes the self-destruction and fire-insulation functions of the ignition fault fuze; the dual-degree-of-freedom recoil needling ignition mechanism realizes recoil inertial needling ignition of a long-delay needling cap of the gunpowder timing self-destruction mechanism; the anti-recovery mechanism of the explosion-proof mechanism is used for preventing the explosion-proof mechanism from recovering the safety after releasing the safety; the detonating tube and the detonating tube are used for amplifying the output energy of the short delay flame detonator in the explosion-proof mechanism.

Compared with the prior art, the invention has the remarkable advantages that:

(1) Has self-destruction and fire-insulation functions, and can ensure the safety of explosive treatment of the non-explosive.

(2) Compact structure, complete functions, low cost, high safety and reliable action.

Drawings

Fig. 1 is a schematic structural view of an unmanned aerial vehicle-mounted balance grenade warhead mechanical trigger fuse in an axial section.

Figure 2 is a cross-sectional view of a mechanical trigger fuze B-B of an unmanned airborne balance grenade warhead of the present invention. The B-B profile is parallel to the fuse axis.

Figure 3 is a cross-sectional view of a mechanical trigger fuze C-C of an unmanned airborne balance grenade warhead of the present invention. The C-C section is perpendicular to the fuze axis.

Fig. 4 is a cross-sectional view of a mechanical trigger fuze D-D of an unmanned airborne balance grenade warhead of the present invention. The D-D profile is parallel to the fuse axis.

Fig. 5 is a cross-sectional view of a mechanical trigger fuze F-F of an unmanned airborne balance grenade warhead of the present invention. The F-F profile is parallel to the fuse axis.

Fig. 6 is a cross-sectional view of a mechanical trigger fuze G-G of an unmanned airborne balance grenade warhead of the present invention. The G-G section is parallel to the fuse axis.

Fig. 7 is a cross-sectional view of a mechanical trigger fuze H-H of an unmanned airborne balance grenade warhead of the present invention. The H-H profile is perpendicular to the fuse axis.

Fig. 8 is a cross-sectional view of a mechanical trigger fuze J-J of an unmanned airborne balance grenade warhead of the present invention. The J-J section is perpendicular to the fuze axis.

Fig. 9 is a cross-sectional view of a mechanical trigger fuse K-K of an unmanned airborne balance grenade warhead of the present invention. The K-K profile is perpendicular to the fuse axis.

Fig. 10 is a cross-sectional view of an unmanned airborne balance grenade warhead mechanical trigger fuze L-L in accordance with the present invention. The L-L section is perpendicular to the fuze axis.

Fig. 11 is a cross-sectional view of a mechanical trigger fuse M-M of an unmanned airborne balance grenade warhead of the present invention. The M-M section is perpendicular to the fuse axis.

Fig. 12 is a top view of an upper body of a mechanically triggered fuse of an unmanned airborne balance grenade warhead of the present invention.

Fig. 13 is a cross-sectional view of an upper body N-N of a mechanically triggered fuse of an unmanned airborne balance grenade warhead of the present invention. The N-N profile is parallel to the upper body axis.

Fig. 14 is a top view of a mechanically triggered fuse body for an unmanned airborne balance grenade warhead in accordance with the present invention.

Fig. 15 is a sectional view of a P-P section of a mechanically triggered fuse body of an unmanned airborne balance grenade warhead according to the present invention. The P-P profile is parallel to the body axis.

Fig. 16 is a top view of a mechanical trigger fuze slider seat for an unmanned airborne balance grenade warhead of the present invention.

Fig. 17 is a cross-sectional view of a Q-Q section of a mechanical trigger fuse slide block of an unmanned airborne balance grenade warhead of the present invention. The Q-Q profile is parallel to the slider seat axis.

Fig. 18 is a top view of a mechanical trigger fuze slider for an unmanned airborne balance grenade warhead of the present invention.

Fig. 19 is a cross-sectional view of a mechanical trigger fuse slide R-R of an unmanned airborne balance grenade warhead of the present invention. The R-R profile is parallel to the slider axis.

Fig. 20 is a cross-sectional view of an unmanned airborne balance grenade warhead mechanically triggered fuze slider S-S in accordance with the present invention. The S-S profile is parallel to the slider axis.

Fig. 21 is a cross-sectional view of a mechanical trigger fuze slider T-T of an unmanned airborne balance grenade warhead of the present invention.

Fig. 22 is a top view of a first firing pin of an unmanned airborne balance grenade warhead mechanical trigger fuze of the present invention.

Fig. 23 is a cross-sectional view of a first striker pin U-U of an unmanned airborne balance grenade warhead mechanical trigger fuse of the present invention. The U-U section is parallel to the first needle striking axis.

Fig. 24 is a top view of a mechanical trigger fuse holder for an unmanned airborne balance grenade warhead of the present invention.

Fig. 25 is a cross-sectional view of a V-V section of a mechanical trigger fuse holder for an unmanned airborne balance grenade warhead of the present invention. The V-V section is parallel to the stent axis.

Fig. 26 is an isometric view of a mechanical trigger fuze slider for an unmanned airborne balance grenade warhead of the present invention.

Fig. 27 is an isometric view of a mechanical trigger fuze slider seat for an unmanned airborne balance grenade warhead of the present invention.

In the figure, 1 is an upper body, 2 is a body, 3 is an anti-recovery mechanism of a squat safety mechanism, 4 is a cover service safety mechanism, 5 is a squat safety mechanism, 6 is an aerodynamic rotor wing delay release safety mechanism and collision trigger needle-punching ignition mechanism, 7 is an explosion-proof mechanism, 8 is a double-freedom squat safety mechanism, 9 is a gunpowder timing self-destruction mechanism, 10 is a double-freedom squat needle-punching ignition mechanism, 11 is an anti-recovery mechanism of the explosion-proof mechanism, 12 is a detonating tube, and 13 is a detonating tube; 31 is the reverse recovery pin, 32 is the reverse recovery spring, 33 is the flap, 41 is the cover, 42 is the post, 43 is the shear pin, 51 is the squat pin, 52 is the squat spring, 53 is the spacer, 61 is the first striker, 62 is the bracket, 71 is the slider, 72 is the first push spring, 73 is the short delay flame detonator, 74 is the second push spring, 75 is the acupuncture cap, 76 is the cover plate, 77 is the plug plate, 78 is the slider seat, 81 is the upper inertia cylinder, 82 is the inertia spring, 83 is the safety ball, 84 is the lower inertia cylinder, 85 is the spacer, 91 is the long delay flame detonator, 92 is the long delay acupuncture cap, 101 is the top plate, 102 is the second striker, 103 is the spring, 104 is the inertia cylinder, 111 is the sealing plate, 112 is the check spring, 113 is the check pin; 14 is a first stepped hole, 15 is a first through hole group, 16 is a second through hole group, 17 is a third through hole group, 18 is a fourth through hole, 19 is a second stepped hole, 20 is a third stepped hole, 21 is a fourth stepped hole, 22 is a fifth stepped hole, 23 is a fifth through hole, 24 is a first blind hole, 25 is a second blind hole, 26 is a sixth stepped hole, 27 is a seventh stepped hole, 28 is a third blind hole, 29 is a sixth through hole, 30 is a fourth blind hole, 34 is a fifth blind hole, 35 is a seventh stepped hole, 36 is an eighth stepped hole; 141 is the first order hole, 142 is the second order hole, 143 is the third order hole, 191 is the fourth order hole, 192 is the fifth order hole, 211 is the sixth order hole, 212 is the seventh order hole, 213 is the eighth order hole, 261 is the ninth order hole, 262 is the tenth order hole, 271 is the eleventh order hole, 272 is the tenth order hole, 221 is the thirteenth order hole, 222 is the fourteenth order hole, 223 is the fifteenth order hole, 351 is the sixteenth order hole, 352 is the seventeenth order hole.

In the above-mentioned constituent units, the inertial spring, the spring and the strut are two, and the rest is one.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by one of ordinary skill in the art without creative efforts, are within the scope of the present invention based on the embodiments of the present invention.

It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.

Furthermore, descriptions such as those referred to as "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implying an order of magnitude of the indicated technical features in the present disclosure. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.

In the present invention, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; the "connection" may be mechanical or electrical. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

Referring to fig. 1 to 27, an unmanned airborne balance grenade warhead mechanical trigger fuse comprises an upper body 1, a body 2, a cover service safety mechanism 4, an explosion-proof mechanism 7, a double-degree-of-freedom recoil safety mechanism 8 (prior art), an aerodynamic rotor delay release safety mechanism and impact trigger needle ignition mechanism 6, a recoil safety mechanism 5 (prior art), a recoil safety mechanism reverse recovery mechanism 3 (prior art), a gunpowder timing self-destruction mechanism 9, a double-degree-of-freedom recoil needle ignition mechanism 10, an explosion-proof mechanism reverse recovery mechanism 11 (prior art), a detonating tube 12 (prior art) and a detonating tube 13 (prior art); the upper body 1 is approximately a revolution body, the outer contour of the upper half part is a round table with a small upper part and a big lower part, the outer contour of the lower half part is a cylinder, and external threads are arranged on the lower half part; a first stepped hole 14 with diameters decreasing in sequence is formed upwards from the bottom surface of the upper body 1 along the axis of the upper body, and the first stepped hole 141, the second stepped hole 142 and the third stepped hole 143 are sequentially formed; three layers of radial through hole groups communicated with the second step holes 142 are uniformly distributed on the outer side wall of the upper half part of the upper body 1 along the axial direction, namely a first through hole group 15, a second through hole group 16 and a third through hole group 17, and 8 radial through holes are uniformly distributed on each layer of radial through hole group along the circumferential direction; a fourth through hole 18 communicated with the first-stage hole 141 is formed on the outer side wall of the upper body 1 along the radial direction; the body 2 is approximately a revolution body, the outer contour of the upper half part of the body is a round table with a small upper part and a big lower part, the outer contour of the lower half part of the body is a cylinder, and an external thread connected with the projectile body is arranged on the body; a second stepped hole 19 is formed upwards from the bottom surface of the body 2 along the axis of the body, and sequentially comprises a fourth stepped hole 191 and a fifth stepped hole 192, wherein the diameter of the fourth stepped hole 191 is larger than that of the fifth stepped hole 192; after the cylinder of the lower half part of the upper body 1 is fixedly connected with the fifth-order hole 192 through threads, the round table of the upper half part of the outer contour of the body 2 is connected with the round table of the upper half part of the outer contour of the upper body 1 to form a larger round table, and the larger round table is used as an exposed part of the fuze, namely an outer conical surface; the cover cap in the cover cap service safety mechanism 4 is buckled on the fuze outer conical surface; the explosion-proof mechanism 7, the double-degree-of-freedom squat safety mechanism 8 and the detonating tube 12 of the explosion-proof mechanism 7 are arranged in the fourth-order hole 191 of the body 2, and the gunpowder timing self-destruction mechanism 9 and the double-degree-of-freedom squat needling ignition mechanism 10 are arranged in the explosion-proof mechanism 7; the aerodynamic rotor wing delay releasing safety mechanism and the impact trigger acupuncture ignition mechanism 6 are arranged in the first-stage hole 141, the second-stage hole 143, the fifth-stage hole 192 and the fourth through hole 18; the recoil safety mechanism 5 and the recoil safety mechanism 3 are both arranged in the aerodynamic rotor wing delay release safety mechanism and impact trigger needle puncture firing mechanism 6, the booster 13 is arranged below the booster 12, the upper part of the booster 13 is positioned in the fourth-order hole 191, and the lower part extends out of the body 2; the cover service safety mechanism 4 is mainly used for delaying the release of the safety mechanism of the aerodynamic rotor wing during service treatment and triggering the safety of the acupuncture ignition mechanism 6 by touching, and sealing the radial through hole on the upper body 1; the explosion-proof mechanism 7 is used for ensuring that the explosive elements in the explosion-proof mechanism are in a dislocation state at ordinary times, preventing accidental ignition from causing in-line charge in the post-detonating tube 13 and aligning the detonating sequence in a releasing safety state; the dual-degree-of-freedom squat safety mechanism 8 realizes squat safety of the explosion-proof mechanism 7; the aerodynamic rotor wing delay release safety mechanism and the impact trigger acupuncture ignition mechanism 6 realize the impact trigger ignition of the acupuncture fire cap 21 of the explosion-proof mechanism 7; the recoil safety mechanism 5 realizes the recoil safety of the aerodynamic rotor wing delay release safety mechanism and the impact trigger acupuncture ignition mechanism 6; the anti-restoring mechanism 3 of the squat safety mechanism is used for preventing the squat safety mechanism 5 from restoring the safety after releasing the safety; the gunpowder timing self-destruction mechanism 9 realizes the self-destruction and fire-insulation functions of the ignition fault fuze; the dual-degree-of-freedom recoil needling ignition mechanism 10 realizes recoil inertial needling ignition of the long-delay needling cap 30 of the gunpowder timing self-destruction mechanism 9; the anti-recovery mechanism 11 of the explosion-proof mechanism is used for preventing the explosion-proof mechanism 7 from recovering the safety after releasing the safety; the detonating tube 12 and the booster tube 13 are used to amplify the output energy of the short-delay flame detonator 19 in the flameproof mechanism 7.

Further, the flameproof mechanism 7 comprises a sliding block 71, a first push spring 72, a short delay flame detonator 73, a second push spring 74, a needling flame cap 75, a cover plate 76, a blocking plate 77 and a sliding block seat 78, wherein the cover plate 76 is positioned on the top surface of the sliding block 71 and limited by a step surface between a fourth step hole 191 and a fifth step hole 192; the sliding block seat 78 is a second-order cylinder, and is a first cylinder and a second cylinder from top to bottom, wherein the diameter of the first cylinder is larger than that of the second cylinder; the first cylinder is provided with a first radial through groove, a needling cap 75, a short delay flame detonator 73, a gunpowder timing self-destruction mechanism 9 and a blocking piece 77 are all arranged on the sliding block 71 to jointly form a sliding block part, and the sliding block part, the first pushing spring 72, the second pushing spring 74 and the cover piece 76 are all arranged in the first radial through groove; a third stepped hole 20 with a decreasing diameter is formed in parallel with the axis while deviating upward from the axis from the bottom surface of the slider seat 78, and the dual-degree-of-freedom squat safety mechanism 8 is provided in the third stepped hole 20; a fourth stepped hole 21 is formed downwards from the top surface of the sliding block 71 along the axial direction, and sequentially comprises a sixth stepped hole 211, a seventh stepped hole 212 and an eighth stepped hole 213, wherein the diameters of the sixth stepped hole 211 and the eighth stepped hole 213 are equal, the seventh stepped hole 212 has the smallest diameter, the input end of the needling cap 75 is outwards arranged in the sixth stepped hole 211 and fixed through spot riveting, the input end of the short-delay flame detonator 73 is inwards arranged in the eighth stepped hole 213 and fixed through spot riveting, and the seventh stepped hole 212 is used as a fire transmission channel between the sixth stepped hole 211 and the eighth stepped hole 213; a fifth stepped hole 22 is formed on the top surface of the slider 71 axially downward away from the axis but parallel to the axis, and the dual-degree-of-freedom recoil needling ignition mechanism 10 is disposed in the fifth stepped hole 22; a fifth through hole 23 is formed along the radial direction of the sliding block 9 from the side surface of the sliding block, the fifth through hole 23 is communicated with the seventh step hole 212 and the fifth step hole 22, and the axis of the fifth through hole 23 is perpendicular to the axis of the fourth step hole 21; the side surface of the sliding block 71 is provided with a first blind hole 24 and a second blind hole 25 along the radial direction from left to right, the first blind hole 24 is parallel to the second blind hole 25 and is positioned above the second blind hole 25, and the diameter of the first blind hole 24 is smaller than that of the second blind hole 25; the first push spring 72 is arranged in the first blind hole 24, the second push spring 74 is arranged in the second blind hole 25, and both the first push spring and the second push spring are in a pre-pressing state; a sixth stepped hole 26 with a decreasing diameter is formed in the bottom of the second blind hole 25 along the radial direction, a ninth stepped hole 261 and a tenth stepped hole 262 are sequentially formed from left to right, and the ninth stepped hole 261 is communicated with the eighth stepped hole 213; a seventh stepped hole 27 with a diameter decreasing is formed at the bottom of the second blind hole 25 along the radial direction, an eleventh stepped hole 271 and a twelfth stepped hole 272 are sequentially formed from left to right, the eleventh stepped hole 271 is communicated with the fourth stepped hole 21, and the fifth stepped hole 22 is parallel to the sixth stepped hole 26; the gunpowder timing self-destruction mechanism 9 is arranged in the ninth order hole 261 and the eleventh order hole 271; the side of the slider 71 is provided with a third blind hole 28 along the radial direction, a sixth through hole 29 with an upward inclined opening direction is formed at the bottom of the third blind hole 28, the sixth through hole 29 is communicated with a tenth hole 262 and a twelfth hole 272, and the blocking piece 77 is positioned in the third blind hole 28 and fixed by spot riveting.

Further, the first cylinder of the slider seat 78 is provided with crisscrossed through holes, and the fifth through holes 23 are aligned for pressure relief after the slider 71 is released.

Further, the powder timing self-destruction mechanism 9 comprises a long-delay flame detonator 91 and a long-delay needling flame cap 92, wherein the long-delay flame detonator 91 is positioned in the ninth-order hole 261, and the long-delay needling flame cap 92 is positioned in the eleventh-order hole 271 and fixed by spot riveting; the tenth order holes 262, the sixth through holes 29, and the tenth order 272 holes serve as flame propagation passages for the long delay acupuncture flame cap 92 and the long delay flame detonator 91.

Further, the dual degree of freedom squat needling ignition mechanism 10 includes a top sheet 101, a second firing pin 102, an inertial barrel 104, a long delay needling cap 92, a slider 71, and two springs 103; the fifth stepped hole 22 comprises a thirteenth stepped hole 221, a fourteenth stepped hole 222 and a fifteenth stepped hole 223 in sequence from top to bottom, the top sheet 101 is positioned in the thirteenth stepped hole 221 and fixed by spot riveting, and the second firing pin 102, the inertia cylinder 104 and the spring 103 are all arranged in the fourteenth stepped hole; the inertial tube 104 is a third-order cylinder, and a central through hole is arranged along the axis of the inertial tube; the second firing pin 102 is composed of a third cylinder, a fourth cylinder and a needle tip from top to bottom, and a central through hole of the inertia cylinder 104 penetrates into the fourth cylinder; the two springs 103 are in a pre-pressing state and respectively reside right above and right below the inertia cylinder 104, wherein the top end of the spring 103 located right above abuts against the inner ring surface of the second firing pin 102, and the bottom end of the spring 103 located right below abuts against the bottom of the fourteenth-order hole 222.

Further, the aerodynamic rotor delay releasing safety mechanism and the strike trigger pin spark ignition mechanism 6 comprise a bracket 62 and a first strike pin 61; the first striking pin 61 is a revolving body, the upper part of the first striking pin is a second-order cylinder, a fifth cylinder and a sixth cylinder are arranged from top to bottom, and two ring grooves with different diameters are formed in each of the fifth cylinder and the sixth cylinder and serve as a rotor wing structure; a fourth blind hole 30 is formed in the bottom surface of the sixth cylinder upwards along the axial direction, and the fourth blind hole 30 is not interfered with the rotor wing structure; the bracket 62 is a cylinder, is arranged below the sixth cylinder and is in threaded connection with the first striking pin 61 through a central threaded through hole; two radial through grooves are formed on two sides of the bracket 62 along the radial direction respectively, so that the overall weight of the bracket 62 is reduced; the side surface of the bracket 62 is provided with a fifth blind hole 34 from left to right along the radial direction, and the fifth blind hole 34 is coaxial with the fourth through hole 18; the bottom surface of the bracket 62 is eccentrically provided with a seventh stepped hole 35 upwards along the axial direction, and the squat safety mechanism 5 is arranged in the seventh stepped hole 35 and the fourth blind hole 30; the fifth blind hole 34 is provided with an eighth stepped hole 36 which is communicated with the seventh stepped hole 35 from right to left along the radial direction on the other side of the bracket symmetrical with respect to the axis of the bracket 62, and the anti-restoring mechanism 3 of the squat safety mechanism is arranged in the eighth stepped hole 36.

Further, the seventh stepped hole 35 is a sixteenth stepped hole 351 and a seventeenth stepped hole 352 in order from bottom to top, the seventh stepped hole 35 is coaxial with the fourth blind hole 30, and the fourth blind hole 30 is the same size as the seventeenth stepped hole 352.

Further, the cover service safety mechanism 4 includes a shear pin 43 and a cover 41 and two posts 42, the shear pin 43 and the two posts 42 being disposed within the fifth blind hole 34 and the fourth through hole 18; the cover 41 is sleeved outside the upper body 1 and the body 2, and the bottom of the cover is buckled on the side annular table of the body 2; the upper internal protrusion of the cover 1 is inserted into the third step hole 143, and the tip thereof abuts the top surface of the first striker 61.

Further, both of the struts 42 are made of a rubber material.

The main safety principle of the mechanical trigger fuze of the warhead of the unmanned airborne balance grenade is as follows:

during service treatment, the fuze is in an explosion-proof state, namely a factory assembly state, and is subjected to trusted impact and vibration, including accidental falling, transportation vibration and the like, so that the fuze cannot be accidentally relieved of insurance and accidentally exploded. The shroud 41 is buckled on the fuze external conical surface, on one hand, the upward movement of the first needle 61 is blocked, the first needle 61 is prevented from accidentally releasing the safety of the explosion-proof mechanism 7, and on the other hand, the air inlet channels of the first through hole group 15, the second through hole group 16 and the third through hole group 17 of the upper body 1 are blocked, so that the fuze storage tightness requirement is met. The recoil safety mechanism 5 realizes the safety of the first striker 61 through the recoil pin 51 therein, and ensures that the first striker 61 is positioned in an explosion-proof state at ordinary times. The movement of the squat pin 51 in the squat safety mechanism 5 is reversible, i.e. the squat pin 51 will release the safety of the first striker 61 during an unexpected upward drop and transport shock impact of the fuze head, but after the drop and transport shock impact has disappeared or substantially disappeared, the squat pin 51 will reset under the influence of the squat spring 52, restoring the safety of the first striker 61. The aerodynamic rotor wing delay release safety mechanism and the impact trigger pin piercing firing mechanism 6 realize redundant safety of the flameproof slider 71 through the safety ball 83 in the first firing pin 61 and the double-freedom-degree squat safety mechanism 8, and ensure that the slider 71 is positioned in a flameproof state at ordinary times. Failure of any single safety mechanism will not unsecure the slider 71, i.e., the slider 71 will not be accidentally aligned, thereby ensuring the safety of the fuze in the event of a trusted failure of the safety mechanism. When the fuze head falls upwards and falls on the ground accidentally, the gunpowder timing self-destruction mechanism 9 can ensure that the second firing pin 102 cannot collide with the long-delay-time needling fire cap 92 to be needled through the spring 37 in the fuze timing self-destruction mechanism. In the case where the slider 71 is not relieved, the pin cap 75 located in the sixth-stage hole 211 and the short-delay flame detonator 73 located in the eighth-stage hole 213 are offset from the axis of the squib 12, and the squib 12 and the booster 13 are not detonated even if either one or both of the pin cap 75 or the short-delay flame detonator 73 accidentally fires and explodes. In the case where the slider 71 is not unsecured, either or both of the long-delay flame detonator 91 located in the tenth-stage hole 262 and the long-delay acupuncture flame cap 92 located in the twelfth-stage hole 272 are accidentally fired and exploded at the same time, the short-delay flame detonator 73 and the acupuncture flame cap 75 are detonated, but the squib 12 is not detonated, and the detonator is safe in flame-isolation and enters an insulated state.

The invention relates to a mechanical trigger fuze of a warhead of an unmanned airborne balance grenade, which comprises the following main working processes:

the cap 41, which snaps onto the outer conical surface of the fuze, is manually removed prior to firing the projectile.

During the firing, the projectile is in the barrel, under the effect of the recoil force, the upper and lower inertial barrels in the dual-degree-of-freedom recoil safety mechanism 8 compress the inertial spring 82 to move downwards under the effect of the recoil overload until the upper end face of the upper inertial barrel 81 is lower than the safety ball 83, the limit on the safety ball 83 is released, the safety ball 83 moves downwards along the inclined hole under the effect of the recoil force until the safety ball 83 falls on the top face of the upper inertial barrel 81, and the first safety of the sliding block 71 is released. Also, the recoil pin 51 in the recoil safety mechanism 5 compresses the recoil spring 52, i.e., the recoil pin 51 moves downward under the recoil force until the upper end surface of the recoil pin 51 is completely disengaged from the fourth blind hole 30 of the first striker 61, and the recoil pin 51 releases the safety of the first striker 61. After the squat pin 51 is squat in place, the anti-recovery pin 31 of the anti-recovery mechanism 3 of the squat safety mechanism can move from right to left, namely from the orifice to the orifice bottom relative to the bracket 8 under the resistance action of the anti-recovery spring 32, so that the front end of the squat pin 51 is inserted into the fourteenth order orifice 352, thereby blocking the upward recovery movement of the squat pin 51 after the squat force is lost, and ensuring that the squat pin 51 can not recover the safety function to the first firing pin 61. The needle-punching ignition mechanism of the gunpowder timing self-destruction mechanism 9 simultaneously stabs the long-delay needle-punching fire cap 92 under the action of the recoil force to burn the long-delay needle-punching fire cap and start self-destruction timing. Thereafter, under the recoil force, the first striker 61 remains stationary and is still inserted into the flame-proof slider 71, with the fuze in the flame-proof state.

After the projectile moves in the bore to approach the muzzle and fly out of the muzzle, air enters the fuze through the first through hole group 15, the second through hole group 16, the third through hole group 17 and the third step hole 143 of the upper body 1 in the form of head-on airflow, the first striking pin 61 continuously rotates under the action of the rotor wing structure until the sliding block 71 is pulled out, the sliding block 71 is released, and at the moment, the upper end face of the first striking pin 61 protrudes out of the end face of the fuze head. After that, the slider 71 moves to the explosion-proof releasing position under the action of the first push spring 72 and the second push spring 74, that is, the instantaneous needle in the explosion-proof position is aligned with the first needle 61 on the spark cap 75 and aligned with the detonating tube 12 under the short delay flame detonator 73. The anti-recovery mechanism 11 of the explosion-proof mechanism acts to lock the slider 71 at the arming position, and the fuse is in the armed state. The process in which the first striker 61 is screwed out of the slider 71 under the aerodynamic force is a delay-releasing process. Because the carrying platform is unmanned plane, the safety problem of launching personnel does not exist, and the distance between the target area such as the window of a high-rise building to which the carrying platform attacks cannot be far (otherwise, the carrying platform is difficult to accurately shoot), the releasing delay is about 5-10 m.

The shape, area of the rotor on the first striker 61, the number, size and layout of the corresponding radial vents on the upper fuse body 1, the speed of flight of the projectile and the depth of insertion of the first striker 61 on the slide 71 determine the time of unscrewing of the first striker 61 in the slide 71, i.e. the arming time of the fuse. Since the windows of the high-rise building are shot by unmanned aerial vehicle-mounted balance cannons, the shooting distance is not too far in consideration of the stability of the balance cannons. And because the transmitting platform is an unmanned plane, the delay releasing isolation performance can be theoretically not designed, so that the fuse releasing insurance distance can be shortened as much as possible, and the minimum attack distance can be shortened.

After the projectile hits the window of the high-rise building, the end face of the first striking pin protruding from the fuse head contacts the window glass to move downwards, the shearing pin 43 is sheared, the striking point of the first striking pin 61 is further penetrated into the instantaneous-needle-shaped fire cap 75, the instantaneous-needle-shaped fire cap 75 is ignited, the following short-delay flame detonator 73 is ignited, the projectile is detonated after penetrating indoors, the detonating tube 12 is detonated again, and the detonating tube 13 and the warhead are detonated.

Because the fuse head collision triggering mechanism adopts a structure with a striking pin protruding outwards, and the glass and the wall of a high-rise building are thicker and harder, the reason that the fuse collides with the fire failure is mostly that the fuse fails to release the safety in advance. In this case, the impact of the fuse with the target such as window or wall will likely cause the first needle 61 to be inserted back into the original needle hole of the slider 71, so that the fuse will be "restored to safety" and the safety of the explosive treatment will be ensured.

After the fuze blind shots fall into a room or fall to the ground, a timing self-destruction mechanism which is positioned in the sliding block 71 below the opening of the shot body and consists of a long delay needling cap 92 and a long delay flame detonator 91, and after the combustion timing action is finished, a short delay flame detonator 73 which is also positioned in the sliding block 71 is detonated. In the state that the fuze is not released from the explosion suppression, the result is fire insulation. And the result is self-destruction in the state that the fuze releases the explosion suppression.

The self-destruction time can be determined according to the height of the attacked building, and the time that the blind ammunition only falls down is ensured. If the height of the attacked building is 50m, the self-destruction time should be more than 3.2 s.

Claims (9)

1. The utility model provides an unmanned aerial vehicle carries balanced big gun grenade warhead machinery trigger fuse which characterized in that: the device comprises an upper body (1), a body (2), a cover service safety mechanism (4), an explosion-proof mechanism (7), a dual-degree-of-freedom recoil safety mechanism (8), an aerodynamic rotor wing delay release safety mechanism and a collision trigger needle-punching ignition mechanism (6), a recoil safety mechanism (5), a recoil safety mechanism reverse recovery mechanism (3), a gunpowder timing self-destruction mechanism (9), a dual-degree-of-freedom recoil needle-punching ignition mechanism (10), an explosion-proof mechanism reverse recovery mechanism (11), a detonating tube (12) and a detonating tube (13); the upper body (1) is approximately a revolution body, the outer contour of the upper half part is a round table with a small upper part and a big lower part, the outer contour of the lower half part is a cylinder, and external threads are arranged on the lower half part; a first stepped hole (14) with diameters decreasing in sequence is formed upwards from the bottom surface of the upper body (1) along the axis of the upper body, and the first stepped hole (141), the second stepped hole (142) and the third stepped hole (143) are sequentially formed; three radial through hole groups which are communicated with the second step holes (142) are uniformly distributed on the outer side wall of the upper half part of the upper body (1) along the axial direction, namely a first through hole group (15), a second through hole group (16) and a third through hole group (17), and 8 radial through holes are uniformly distributed on each radial through hole group along the circumferential direction; a fourth through hole (18) communicated with the first-order hole (141) is formed on the outer side wall of the upper body (1) along the radial direction; the body (2) is approximately a revolution body, the outer contour of the upper half part of the body is a round table with a small upper part and a large lower part, the outer contour of the lower half part of the body is cylindrical, and external threads connected with the projectile body are arranged on the body; a second stepped hole (19) is formed upwards from the bottom surface of the body (2) along the axis of the body, and the second stepped hole sequentially comprises a fourth stepped hole (191) and a fifth stepped hole (192), wherein the diameter of the fourth stepped hole (191) is larger than that of the fifth stepped hole (192); after the cylinder of the lower half part of the upper body (1) is fixedly connected with the fifth step hole (192) through threads, the round table of the upper half part of the outer contour of the body (2) is connected with the round table of the upper half part of the outer contour of the upper body (1) to form a larger round table, and the larger round table is used as an exposed part of the fuze, namely an outer conical surface; the cover cap in the cover cap service safety mechanism (4) is buckled on the fuze outer conical surface; the explosion-proof mechanism (7), the dual-degree-of-freedom squat safety mechanism (8) and the detonating tube (12) of the explosion-proof mechanism (7) are arranged in a fourth-order hole (191) of the body (2), and the gunpowder timing self-destruction mechanism (9) and the dual-degree-of-freedom squat needle-punched ignition mechanism (10) are arranged in the explosion-proof mechanism (7); the aerodynamic rotor wing delay releasing safety mechanism and the impact trigger acupuncture ignition mechanism (6) are arranged in the first-stage hole (141), the second-stage hole (143), the fifth-stage hole (192) and the fourth hole (18); the recoil safety mechanism (5) and the recoil safety mechanism (3) are both arranged in the aerodynamic rotor wing delay release safety mechanism and the impact trigger needle spark ignition mechanism (6), the detonating tube (13) is arranged below the detonating tube (12), the upper part of the detonating tube (13) is arranged in the fourth-order hole (191), and the lower part of the detonating tube extends out of the body (2); the cover cap service safety mechanism (4) is mainly used for delaying the release of the safety mechanism and the collision of the aerodynamic rotor wing and triggering the safety of the acupuncture ignition mechanism (6) during service treatment and sealing the radial through hole on the upper body (1); the explosion-proof mechanism (7) is used for ensuring that the explosion elements in the explosion-proof mechanism are in a dislocation state at ordinary times, preventing accidental ignition from causing in-line charge in the post-detonating tube (13) and aligning the detonating sequence in a releasing safety state; the dual-degree-of-freedom squat safety mechanism (8) realizes squat safety of the explosion-proof mechanism (7); the aerodynamic rotor wing delay release safety mechanism and the impact trigger acupuncture ignition mechanism (6) realize the impact trigger ignition of the acupuncture fire cap of the explosion-proof mechanism (7); the recoil safety mechanism (5) realizes the recoil safety of the aerodynamic rotor wing delay release safety mechanism and the impact trigger needle ignition mechanism (6); the anti-restoring mechanism (3) of the squat safety mechanism is used for preventing the squat safety mechanism (5) from restoring safety after releasing the safety; the gunpowder timing self-destruction mechanism (9) realizes the self-destruction and fire-insulation functions of the ignition fault fuze; the dual-degree-of-freedom recoil needling ignition mechanism (10) realizes recoil inertial needling ignition of a long-delay needling fire cap of the gunpowder timing self-destruction mechanism (9); the anti-recovery mechanism (11) of the explosion-proof mechanism is used for preventing the explosion-proof mechanism (7) from recovering the safety after releasing the safety; the detonating tube (12) and the detonating tube (13) are used for amplifying the output energy of the short delay flame detonator in the explosion-proof mechanism (7).

2. The mechanical trigger fuze of an unmanned airborne balance grenade warhead of claim 1, wherein: the flameproof mechanism (7) comprises a sliding block (71), a first push spring (72), a short delay flame detonator (73), a second push spring (74), a needling cap (75), a cover plate (76), a blocking plate (77) and a sliding block seat (78), wherein the cover plate (76) is positioned on the top surface of the sliding block (71) and limited by a step surface between a fourth-order hole (191) and a fifth-order hole (192); the sliding block seat (78) is a second-order cylinder, a first cylinder and a second cylinder are arranged from top to bottom, and the diameter of the first cylinder is larger than that of the second cylinder; the first cylinder is provided with a first radial through groove, a needling fire cap (75), a short delay flame detonator (73), a gunpowder timing self-destruction mechanism (9) and a blocking piece (77) are all arranged on the sliding block (71) to jointly form a sliding block part, and the sliding block part, the first pushing spring (72), the second pushing spring (74) and the blocking piece (76) are all arranged in the first radial through groove; a third stepped hole (20) with a diameter decreasing from the bottom surface of the sliding block seat (78) to the upper side to deviate from the axis but is parallel to the axis, and a dual-freedom-degree squat safety mechanism (8) is arranged in the third stepped hole (20); a fourth stepped hole (21) is formed in the top surface of the sliding block (71) downwards along the axial direction, a sixth stepped hole (211), a seventh stepped hole (212) and an eighth stepped hole (213) are sequentially formed, the diameters of the sixth stepped hole (211) and the eighth stepped hole (213) are equal, the seventh stepped hole (212) is minimum in diameter, the input end of the needling cap (75) is outwards arranged in the sixth stepped hole (211) and fixed through spot riveting, the input end of the short-delay flame detonator (73) is inwards arranged in the eighth stepped hole (213) and fixed through spot riveting, and the seventh stepped hole (212) is used as a fire transmission channel between the sixth stepped hole and the eighth stepped hole; a fifth stepped hole (22) is formed on the top surface of the sliding block (71) axially downwards deviating from the axis but parallel to the axis, and the dual-freedom-degree back-seat needling ignition mechanism (10) is arranged in the fifth stepped hole (22); a fifth through hole (23) is formed in the side surface of the sliding block (9) along the radial direction of the sliding block, the fifth through hole (23) is communicated with the seventh step hole (212) and the fifth step hole (22), and the axis of the fifth through hole (23) is perpendicular to the axis of the fourth step hole (21); the side surface of the sliding block (71) is provided with a first blind hole (24) and a second blind hole (25) along the radial direction from left to right, the first blind hole (24) is parallel to the second blind hole (25) and is positioned above the second blind hole (25), and the diameter of the first blind hole (24) is smaller than that of the second blind hole (25); the first pushing spring (72) is arranged in the first blind hole (24), the second pushing spring (74) is arranged in the second blind hole (25), and both the first pushing spring and the second pushing spring are in a pre-pressing state; a sixth stepped hole (26) with the diameter decreasing is formed in the bottom of the second blind hole (25) along the radial direction, a ninth stepped hole (261) and a tenth stepped hole (262) are formed in sequence from left to right, and the ninth stepped hole (261) is communicated with the eighth stepped hole (213); a seventh stepped hole (27) with the diameter decreasing is formed in the bottom of the second blind hole (25) along the radial direction, an eleventh stepped hole (271) and a twelfth stepped hole (272) are formed in sequence from left to right, the eleventh stepped hole (271) is communicated with the fourth stepped hole (21), and the fifth stepped hole (22) is parallel to the sixth stepped hole (26); the gunpowder timing self-destruction mechanism (9) is arranged in the ninth-order hole (261) and the eleventh-order hole (271); a third blind hole (28) is formed in the side face of the sliding block (71) along the radial direction, a sixth through hole (29) with an upward opening direction inclined is formed in the bottom of the third blind hole (28), the sixth through hole (29) is communicated with a tenth-order hole (262) and a twelfth-order hole (272), and the blocking piece (77) is located in the third blind hole (28) and fixed through spot riveting.

3. The mechanical trigger fuze of an unmanned airborne balance grenade warhead of claim 2, wherein: a first cylinder of the slide block seat (78) is provided with a crisscrossed through hole, and the first cylinder is aligned with a fifth through hole (23) after the slide block (71) is relieved of safety for pressure relief.

4. The mechanical trigger fuze of an unmanned airborne balance grenade warhead of claim 2, wherein: the gunpowder timing self-destruction mechanism (9) comprises a long-delay flame detonator (91) and a long-delay needling fire cap (92), wherein the long-delay flame detonator (91) is positioned in a ninth-order hole (261), and the long-delay needling fire cap (92) is positioned in an eleventh-order hole (271) and fixed through spot riveting; the tenth-order hole (262), the sixth through hole (29) and the twelfth-order hole (272) are used as fire transmission channels of the long-delay needling fire cap (92) and the long-delay flame detonator (91).

5. The mechanical trigger fuze of an unmanned airborne balance grenade warhead of claim 2, wherein: the dual-degree-of-freedom squat needling ignition mechanism (10) comprises a top sheet (101), a second firing pin (102), an inertia cylinder (104), a long-delay needling hood (92), a sliding block (71) and two springs (103); the fifth stepped hole (22) sequentially comprises a thirteenth stepped hole (221), a fourteenth stepped hole (222) and a fifteenth stepped hole (223) from top to bottom, the top sheet (101) is positioned in the thirteenth stepped hole (221) and fixed through spot riveting, and the second firing pin (102), the inertia cylinder (104) and the spring (103) are all arranged in the fourteenth stepped hole; the inertial cylinder (104) is a third-order cylinder, and a central through hole is arranged along the axis of the inertial cylinder; the second firing pin (102) consists of a third cylinder, a fourth cylinder and a needle tip from top to bottom, and a center through hole of the inertia cylinder (104) penetrates into the fourth cylinder; the two springs (103) are in a pre-pressing state and respectively located right above and right below the inertia cylinder (104), wherein the top end of the spring (103) located right above is abutted against the inner annular surface of the second firing pin (102), and the bottom end of the spring (103) located right below is abutted against the bottom of the fourteenth-order hole (222).

6. The mechanical trigger fuze of an unmanned airborne balance grenade warhead of claim 1, wherein: the aerodynamic rotor wing delay releasing safety mechanism and the impact trigger needle piercing firing mechanism (6) comprise a bracket (62) and a first striking needle (61); the first striking pin (61) is a revolving body, the upper part of the first striking pin is a second-order cylinder, a fifth cylinder and a sixth cylinder are arranged from top to bottom, and two ring grooves with different diameters are formed in the fifth cylinder and the sixth cylinder and serve as rotor structures; a fourth blind hole (30) is formed in the bottom surface of the sixth cylinder upwards along the axial direction, and the fourth blind hole (30) is not interfered with the rotor wing structure; the bracket (62) is a cylinder, is arranged below the sixth cylinder and is in threaded connection with the first striking pin (61) through the central threaded through hole; two radial through grooves are formed on two sides of the bracket (62) along the radial direction respectively, so that the overall weight of the bracket (62) is reduced; a fifth blind hole (34) is formed in the side surface of the bracket (62) from left to right along the radial direction, and the fifth blind hole (34) is coaxial with the fourth through hole (18); a seventh stepped hole (35) is eccentrically arranged on the bottom surface of the bracket (62) upwards along the axial direction, and the squat safety mechanism (5) is arranged in the seventh stepped hole (35) and the fourth blind hole (30); the fifth blind hole (34) is provided with an eighth stepped hole (36) communicated with the seventh stepped hole (35) from right to left along the radial direction on the other side of the bracket (62) symmetrical with the axis of the bracket (62), and the anti-restoring mechanism (3) of the squat safety mechanism is arranged in the eighth stepped hole (36).

7. The unmanned airborne balance grenade warhead mechanical triggering fuse of claim 6, wherein: the seventh stepped hole (35) is a sixteenth stepped hole (351) and a seventeenth stepped hole (352) from bottom to top, the seventh stepped hole (35) is coaxial with the fourth blind hole (30), and the fourth blind hole (30) and the seventeenth stepped hole (352) have the same size.

8. The mechanical trigger fuze of an unmanned airborne balance grenade warhead of claim 1, wherein: the cover cap service safety mechanism (4) comprises a shearing pin (43), a cover cap (41) and two support posts (42), wherein the shearing pin (43) and the two support posts (42) are arranged in the fifth blind hole (34) and the fourth through hole (18); the cover cap (41) is sleeved outside the upper body (1) and the body (2), and the bottom of the cover cap is buckled on the side annular table of the body (2); the inner bulge at the upper part of the cover cap (1) is plugged into the third-stage hole (143), and the end of the inner bulge is propped against the top surface of the first striker (61).

9. The unmanned airborne balance grenade warhead mechanical triggering fuse of claim 8, wherein: both struts (42) are made of rubber material.