A tail rod assembly for dual-channel firing control of a 40-mm rocket projectile

Abstract

The present invention provides a tail rod assembly for dual-channel firing control of a 40-mm rocket, which includes a combustion chamber bottom, a magneto, a power connection switch, a dual-channel output high-precision logic control module, and a finned tail rod. The gunpowder gas generated at the combustion chamber bottom is transmitted to the magneto. The magneto does work to generate dual-channel electromotive force, which is transmitted through two wires. One wire is connected to the dual-channel output high-precision logic control module to detonate the ignition pyrotechnics of the launch engine, and the other wire charges the capacitor in the dual-channel output high-precision logic control module. When the rocket leaves the launch tube, the fins of the finned tail rod open and the power connection switch is turned on. When the delay reaches the set time, the dual-channel output high-precision logic control module controls the capacitor to discharge, causing the combustion chamber bottom to ignite the rocket propellant of the flight engine. The present invention can achieve precise ignition control with high reliability and high safety.

Description

Technical Field

[0001] The invention relates to the technical field of firing control of small-caliber ammunition, and in particular to a tail rod assembly for dual-path firing control of a 40mm rocket. Background Art

[0002] The 40mm rocket is an infantry anti-tank assault weapon. It is simple to operate, light, and powerful. It is still equipped in large quantities by grassroots infantry units and has become a weapon for infantry to penetrate armor and attack in the process of combat. However, since it uses a recoilless artillery firing method, the firing overload is high, the smoke and flame noise are large, and it cannot be fired in a limited space, thus limiting the combat environment of the weapon system. Especially in urban street fighting, it cannot give full play to its combat advantages.

[0003] The soft-launch 40mm rocket features low launch overload and low smoke and flame noise, and can be used in combat in semi-confined spaces to improve the combat effectiveness of the weapon system and the safety of personnel. However, the significant reduction in launch overload means that the original "mechanical-primer" firing method can no longer meet the soft-launch rocket system's requirements for the ignition of the soft-launch device and the safety control of the launch process. To this end, the firing control requirements for soft launch are proposed without changing the original mechanical firing method of the 40mm rocket. Summary of the invention

[0004] In view of this, the present invention provides a 40mm rocket dual-path firing control tail rod assembly, which can achieve precise ignition control with high reliability and high safety.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A tail rod assembly for dual-path firing control of a 40mm rocket, the tail rod assembly comprising a combustion chamber bottom, a magneto, a power switch, a dual-path output high-precision logic control module and a tail rod with fins;

[0007] The gunpowder gas generated at the bottom of the combustion chamber is transmitted to the magneto. The magneto generates a dual-path electromotive force when doing work and is transmitted through two wires. One wire is connected to the dual-path output high-precision logic control module to detonate the ignition pyrotechnics of the launch engine, and the other wire charges the capacitor in the dual-path output high-precision logic control module. When the rocket leaves the launch tube, the wings of the tail rod with wings open and the power switch is turned on; when the delay reaches the set time, the dual-path output high-precision logic control module controls the capacitor to discharge, so that the bottom of the combustion chamber ignites the flight engine rocket powder.

[0008] Furthermore, the power switch is a push rod switch, which includes two electrodes, a conductive ring, a non-metallic body, a push rod and a push spring;

[0009] The non-metal body is a cylindrical structure with both ends open. An electrode is fixedly connected to each end of the non-metal body, enclosing the moving space of the ejector rod. A conductive ring is fixed in the middle of the outer circumference of the ejector rod and is located within the moving space. One end of the ejector rod is in clearance fit with one of the electrodes and is limited by the conductive ring. The other end is sleeved with a push spring. At the same time, one end of the push spring contacts the end face of the conductive ring, and the other end of the push spring contacts the other electrode. The push spring is always in a compressed state. When the fin is folded, the protruding ejector rod is pushed, and the conductive ring presses the push spring against the inner wall of the other electrode, and the conductive ring is separated from the electrode. When the fin is opened, the ejector rod moves under the action of the push spring, the conductive ring contacts the electrode, and the two electrodes are conducted through the conductive ring and the push spring.

[0010] Further, the conductive ring and the electrode are in conical contact.

[0011] Further, the power connection switch is an overload switch, and a thyristor is provided in the dual-channel output high-precision logic control circuit module. When the rocket is launched, an overload is generated to close the overload switch, and the thyristor in the dual-channel output high-precision logic control circuit module is conducted. When the delay reaches the set time, the capacitor discharges.

[0012] Further, the tail rod assembly further includes a magneto base, and the magneto base includes an aluminum base body, a baffle plate and a retaining cover.

[0013] A channel for the movement of the magneto core rod is provided inside the aluminum base body, and both ends of the channel are sealed by a baffle plate and a retaining cover respectively. The magneto core rod moves under the pressure of the gunpowder gas, shears the baffle plate and continues to move until it reaches the retaining cover.

[0014] Beneficial effects:

[0015] 1. The dual-channel output high-precision logic control module of the present invention not only realizes the output of dual-channel firing signals in a small-size structure, but also ensures the accurate ignition control requirements during the use of the rocket. At the same time, the combination of the power connection switch and the dual-channel output high-precision logic control module has a low cost, high reliability and strong versatility, and can be widely applied to the transformation of soft launch of individual rockets.

[0016] Secondly, with dual-channel firing control, if a failure occurs in the launch engine during the launch of the rocket and the magneto has functioned, since the power connection switch is not conducted, after the set delay time, the electric energy of the capacitor is exhausted, and the dual-channel output high-precision logic control module cannot work, and the flight engine will not be ignited, and the rocket is in an absolutely safe state. Moreover, under the logic control of the dual-channel output high-precision logic control module, the capacitor is charged, the switch is conducted, then the delay is performed, and finally the capacitor discharges, with precise control and high reliability and safety.

[0017] 2. The magneto base of the present invention can ensure the safety during the daily service handling of the rocket projectile. In case of impact and collision during the process of moving the projectile, the baffle restricts the movement of the magneto core rod, preventing the magneto from generating power and supplying energy, thus enhancing the safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is the working flow chart of the dual - firing control of the present invention;

[0019] Figure 2 is the structural schematic diagram of the present invention;

[0020] Figure 3 is the structural schematic diagram of the bottom of the combustion chamber;

[0021] Figure 4 is the structural schematic diagram of the magneto;

[0022] Figure 5 is the structural schematic diagram of the finned tail rod;

[0023] Figure 6 is the structural schematic diagram of the magneto base;

[0024] Figure 7 is the structural schematic diagram of the firing circuit component;

[0025] Figure 8 is the structural schematic diagram of the push - rod switch;

[0026] Among them, 1 - bottom of the combustion chamber, 2 - finned tail rod, 3 - magneto, 4 - magneto base, 5 - wire - passing rod, 6 - firing circuit component, 7 - push - rod switch, 8 - dual - output high - precision logic control module, 9 - combustion chamber bottom housing, 10 - primer, 11 - electric igniter, 12 - compression screw, 13 - tail rod housing, 14 - fin, 15 - fin shaft, 16 - torsion spring, 17 - magneto housing, 18 - dual - route coil, 19 - core rod, 20 - aluminum seat body, 21 - baffle, 22 - retaining cover, 23 - wire, 24 - non - metallic seat body, 25 - electrode, 26 - conducting ring, 27 - non - metallic body, 28 - ejector rod, 29 - push spring. SPECIFIC EMBODIMENTS

[0027] The following are specific embodiments of the present invention with reference to the drawings for detailed description.

[0028] This embodiment provides a tail rod assembly for the dual - firing control of a 40 - mm rocket projectile. As Figure 2 shown, the tail rod assembly includes the bottom of the combustion chamber 1, the magneto 3, the magneto base 4, the power - on switch, the dual - output high - precision logic control module 8 and the finned tail rod 2.

[0029] As Figure 3As shown in the figure, the combustion chamber bottom includes a combustion chamber bottom housing 9, a primer 10, an electric igniter 11, and a compression screw 12. The primer 10 is installed on the side of the combustion chamber bottom housing 9, and the electric igniter 11 is installed at the tail end of the combustion chamber bottom housing 9 and connected to a wire. The compression screw 12 is fixed at the other end of the combustion chamber bottom housing 9, and a through hole is provided on the compression screw 12. A gas transmission channel and a wire avoidance annular groove are provided inside the combustion chamber bottom housing 9, and the gas passes through the gas transmission channel of the combustion chamber bottom housing 9 and then exits through the through hole of the compression screw 12.

[0030] As Figure 5 shown in the figure, the finned tail rod 2 includes a tail rod housing 13, fins 14, a fin shaft 15, and a torsion spring 16. This mechanism mainly functions to stabilize the flight of the rocket projectile. At the same time, the opening and folding of the fins 14 also control the on-off of the push rod switch 7. The fins 14 are rotatably installed on the tail rod housing 13 through the fin shaft 15, and the fins 14 are opened under the elastic force of the torsion spring 16.

[0031] As Figure 4 shown in the figure, the magneto 3 is used to output the energy required for the dual-channel output high-precision logic control module 8 and the ignition pyrotechnic device, and includes a magneto housing 17, a dual-channel coil 18, and a core rod 19. The dual-channel coil 18 is arranged inside the magneto housing 17, and the core rod 19 is slidably matched with the magneto housing 17. When the core rod 19 moves, it passes through the dual-channel coil 18 to generate a dual-channel electromotive force.

[0032] As Figure 6 shown in the figure, the magneto base 4 includes an aluminum base body 20, a baffle 21, and a retaining cover 22; a channel for the magneto core rod 19 to move is provided inside the aluminum base body 20, and both ends of the channel are sealed by the baffle 21 and the retaining cover 22 respectively; the magneto core rod 19 moves under the pressure of the propellant gas, cuts the baffle 21, and continues to move until it reaches the retaining cover 22. An inner hole for the wire 23 to pass through is also provided inside the aluminum base body 20.

[0033] The power-on switch, the non-metallic seat body 24, and the dual-output high-precision logic control circuit module 8 together constitute the firing circuit component 6. As Figure 7 shown in the figure, it is used to store electrical energy and output a firing signal at an accurate time to ignite the rocket propellant of the flight engine.

[0034] The power-on switch can adopt a push rod switch 7 or an overload switch.

[0035] As Figure 8 shown in the figure, the push rod switch 7 includes an upper electrode 25, a lower electrode, a conductive ring 26, a non-metallic body 27, a push rod 28, and a push spring 29;

[0036] The non-metal body 27 is a cylindrical structure with both ends open. The upper electrode 25 and the lower electrode are fixedly connected to the two ends of the non-metal body 27 respectively, surrounding and forming the moving space of the ejector rod 28. The conductive ring 26 is fixed in the middle of the outer circumference of the ejector rod 28 and is located within the moving space; one end of the ejector rod 28 is in clearance fit with the upper electrode 25 and is limited by the conductive ring 26, and the other end is sleeved with a push spring 29. The push spring 29 is arranged within the moving space. At the same time, one end of the push spring 29 contacts the end face of the conductive ring 26, and the other end of the push spring 29 contacts the lower electrode. The push spring 29 is always in a compressed state.

[0037] When the wing is folded, the extended ejector rod 28 is pressed down and moves towards the lower electrode. The conductive ring 26 presses the push spring 29 against the inner wall of the lower electrode, and the conductive ring 26 is separated from the upper electrode 25; when the wing opens, the ejector rod 28 moves upward under the action of the push spring 29, that is, moves towards the upper electrode 25, and the conductive ring 26 contacts the upper electrode 25. The two electrodes are conducted through the conductive ring 26 and the push spring 29.

[0038] The lower electrode is provided with a through hole, which can exhaust the internal air flow to eliminate the influence of air pressure on the movement of the ejector rod 28; moreover, this through hole can be used as an observation window to confirm whether the push spring 29 is compressed in place or whether the internal structure is complete.

[0039] Preferably, the conductive ring 26 and the upper electrode 25 are in conical contact. The inner wall surface of the upper electrode 25 is provided with an inclined surface that cooperates with the conical surface of the conductive ring 25.

[0040] If an overload switch is adopted, a thyristor needs to be set in the dual-channel output high-precision logic control module 8; when the rocket is launched and an overload occurs, the overload switch closes, conducting the thyristor in the dual-channel output high-precision logic control module 8. When the delay reaches the set time, the capacitor discharges, detonating the electric igniter 11 and igniting the rocket propellant of the flight engine.

[0041] During assembly, first install the finned tail rod 2. Install the four fins 14, the four fin shafts 15, and the four torsion springs 16 on the tail rod housing 13. The shaft end of the fin shaft 15 is provided with an open slot, and the positioning of the fin shaft 15 can be achieved by expanding and riveting. The torsion spring 16 provides the power for the fin to open. After installation, tie the fins 14 with nylon thread to prevent them from opening.

[0042] Then start installing the firing circuit component 6. First, install the push rod switch 7 into the non-metallic seat body 24. Weld the two wires 23 output from the electrode 25 of the push rod switch 7 onto the dual-output high-precision logic control module 8. The six wires 23 on the dual-output high-precision logic control module 8 are led out through the wire groove and pass through the inner hole of the wire threading rod 5. The wire threading rod 5 is installed on the non-metallic seat body 24, and the wire threading rod 5 is axially parallel to the winged tail rod 2. Integrally install the firing circuit component 6 and the wire threading rod 5 into the tail rod housing 13. The ejector rod 28 on the push rod switch 7 passes through the corresponding through hole of the tail rod housing 13 and ejects, and the moving direction of the ejector rod 28 is perpendicular to the axis straight line direction of the winged tail rod 2.

[0043] After that, lead out the six wires 23 through the inner hole of the aluminum seat body 20 of the magneto base 4. Then connect the aluminum seat body 20 to the wire threading rod 5 by threads, and install the retaining cap 22, the baffle 21 and the magneto 3 in sequence. The moving direction of the core rod 19 of the magneto 3 is axially parallel to the winged tail rod 2. Four wires on the magneto 3 (two of which are grounded) are connected to four of the six wires 23. The other two are connected to the two wires led out from the electric igniter 11 on the bottom of the combustion chamber 1. After connecting the wires 23, place them in the avoidance annular groove. The bottom of the combustion chamber 1 and the tail rod housing 13 are connected by radial screws. Thus, the assembly of the soft launch tail rod assembly is completed.

[0044] This tail rod assembly with dual firing control replaces the primer and powder transfer fire mechanism of the original 40-mm rocket projectile. The working process is as Figure 1 shown. The firing pin on the launcher trigger hits the primer 10. The gunpowder gas generated by the primer 10 is transmitted through the gas transmission channel on the bottom of the combustion chamber 1 to the end face of the core rod 19 of the magneto 3. The core rod 19 moves axially along the winged tail rod 2 under the pressure of the gunpowder gas, shears the baffle 21, passes through the dual coils 18, and reaches the retaining cap 22. During the process of the core rod 19 passing through the dual coils 18, the magneto 3 generates a dual-path electromotive force and is transmitted out by the two-way wires 23. One wire is directly connected to the dual-output high-precision logic control module 8 to detonate the ignition pyrotechnics of the launch engine, and the other wire charges the capacitor in the dual-output high-precision logic control module 8. When the rocket projectile leaves the launcher, the fins of the winged tail rod 2 open, and the push rod switch 7 closes and conducts. At this time, the precise timer in the dual-output high-precision logic control module 8 starts timing. When the delay reaches the set time, the dual-output high-precision logic control module 8 controls the capacitor to discharge, precisely detonates the electric igniter 11, and ignites the rocket propellant of the flight engine.

[0045] In summary, the above is only the preferred embodiment of the present invention and is not used to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A tail rod assembly for dual-channel firing control of a 40-mm rocket projectile, characterized in that The tail rod assembly includes a combustion chamber bottom, a magneto, a power connection switch, a dual-output high-precision logic control module, and a winged tail rod; The gunpowder gas generated at the combustion chamber bottom is transmitted to the magneto. The magneto does work to generate a dual-path electromotive force, which is transmitted through two wires. One wire is connected to the dual-output high-precision logic control module to detonate the ignition pyrotechnics of the launch engine, and the other wire charges the capacitor in the dual-output high-precision logic control module. When the rocket projectile breaks away from the launch tube, the fins of the winged tail rod open, and the power connection switch is turned on; when the delay reaches the set time, the dual-output high-precision logic control module controls the capacitor to discharge, causing the combustion chamber bottom to ignite the rocket propellant of the flight engine.

2. The tail rod assembly for dual-channel firing control of a 40-mm rocket as claimed in claim 1, characterized in that, The power connection switch is a push rod switch, which includes two electrodes, a conductive ring, a non-metal body, a push rod, and a push spring; The non-metal body is a cylindrical structure with open ends. One electrode is fixedly connected to each end of the non-metal body, enclosing the moving space of the push rod; a conductive ring is fixed in the middle of the outer circumference of the push rod and is located within the moving space. One end of the push rod has a clearance fit with one of the electrodes and is limited by the conductive ring. The other end is sleeved with a push spring. At the same time, one end of the push spring contacts the end face of the conductive ring, and the other end of the push spring contacts the other electrode. The push spring is always in a compressed state; when the fins are folded, the protruding push rod is pushed, and the conductive ring presses the push spring against the inner wall of the other electrode, and the conductive ring is separated from the electrode; when the fins open, the push rod moves under the action of the push spring, the conductive ring contacts the electrode, and the two electrodes are conducted through the conductive ring and the push spring.

3. The tail rod assembly for dual-channel firing control of a 40-mm rocket projectile according to claim 2, characterized in that, The conductive ring and the electrode are in conical contact.

4. The tail rod assembly for dual-channel percussion control of a 40-mm rocket projectile as claimed in claim 1, characterized in that, The power connection switch is an overload switch, and a thyristor is provided in the dual-output high-precision logic control circuit module; when the rocket projectile is launched, overload causes the overload switch to close, turning on the thyristor in the dual-output high-precision logic control circuit module. When the delay reaches the set time, the capacitor discharges.

5. The tail rod assembly for dual-channel firing control of a 40-mm rocket projectile according to claim 1, wherein The tail rod assembly further includes a magneto base, which includes an aluminum base body, a baffle, and a retaining cover; A channel for the movement of the magneto core rod is provided inside the aluminum base body, and the two ends of the channel are respectively encapsulated by the baffle and the retaining cover; the magneto core rod moves under the pressure of the gunpowder gas, shears the baffle, and continues to move until it reaches the retaining cover.

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