CN212482270U - Tail rod assembly for 40 mm rocket projectile double-path firing control - Google Patents

Abstract

The utility model provides a tail rod component for controlling double-path firing of a 40 mm rocket projectile, which comprises a combustion chamber bottom, a magneto, an electric switch, a double-path output high-precision logic control module and a tail rod with fins; gunpowder gas generated at the bottom of the combustion chamber is transmitted to a magneto, the magneto acts to generate double-path electromotive force and transmits the electromotive force through two paths of leads, one path of lead is connected to a double-path output high-precision logic control module to detonate ignition initiating explosive of a launching engine, the other path of lead charges a capacitor in the double-path output high-precision logic control module, and when a rocket projectile is separated from a launching tube, a fin with a fin tail rod is opened and is connected with a power switch for conduction; and after the time is delayed to the set time, the dual-output high-precision logic control module controls the capacitor to discharge, so that the propellant of the flying engine is ignited at the bottom of the combustion chamber. The utility model discloses can realize the accurate ignition control under high reliability, the high security.

Description

Tail rod assembly for 40 mm rocket projectile double-path firing control

Technical Field

The utility model relates to a small-bore ammunition percussion control technical field, concretely relates to tail-stock subassembly of 40 millimeters rocket projectile double-circuit percussion control.

Background

The 40 mm rocket projectile is an anti-tank attack-hardening weapon for infantry, has simple operation, light weight and high power, is still provided with a large number of basic infantry units, and becomes a sharp device for infantry to fight against armor and attack hardening. However, because the firing mode of the recoilless artillery is adopted, the firing overload is high, the smoke noise is high, and the limited space firing cannot be realized, thereby limiting the environment for the weapon system to use in battle. Especially in urban street battles, the operational advantages cannot be fully exerted.

The soft-launch type 40 mm rocket projectile is characterized by low launch overload and low smoke flame noise, and can be suitable for the system to be used in battle under the semi-closed space condition, so that the battle efficiency of the weapon system and the safety of personnel are improved. However, the great reduction of the transmission overload makes the original 'mechanical-primer' firing mode unable to meet the requirements of soft-fire rocket projectile systems for ignition of soft-fire devices and safety control of the firing process. Therefore, the firing control requirement for realizing soft firing on the premise of not changing the original mechanical firing mode of the 40 mm rocket projectile is provided.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides a tail-stock subassembly of 40 millimeter rocket projectile double-circuit percussion control can realize the accurate ignition control under high reliability, the high security.

The utility model adopts the following technical scheme:

a tail rod assembly for controlling double-path firing of a 40 mm rocket projectile comprises a combustion chamber bottom, a magneto, an electric switch, a double-path output high-precision logic control module and a tail rod with fins, wherein the combustion chamber bottom is provided with a combustion chamber;

gunpowder gas generated at the bottom of the combustion chamber is transmitted to a magneto, the magneto acts to generate double-path electromotive force and transmits the electromotive force through two paths of leads, one path of lead is connected to a double-path output high-precision logic control module to detonate ignition initiating explosive of a launching engine, the other path of lead charges a capacitor in the double-path output high-precision logic control module, and when a rocket projectile is separated from a launching tube, a fin with a fin tail rod is opened and is connected with a power switch for conduction; and after the time is delayed to the set time, the dual-output high-precision logic control module controls the capacitor to discharge, so that the propellant of the flying engine is ignited at the bottom of the combustion chamber.

Furthermore, the power connection switch is a push rod switch, and the push rod switch comprises two electrodes, a conducting ring, a non-metal body, a push rod and a push spring;

the non-metal body is of a cylindrical structure with two open ends, and two ends of the non-metal body are respectively fixedly connected with an electrode to form a movable space of the ejector rod in a surrounding manner; a conducting ring is fixed in the middle of the outer circumference of the ejector rod and is positioned in the moving space, one end of the ejector rod is in clearance fit with one electrode and limited by the conducting ring, a push spring is sleeved at the other end of the ejector rod, one end of the push spring is in contact with the end face of the conducting ring, the other end of the push spring is in contact with the other electrode, and the push spring is always in a compressed state; when the wing panel is folded, the extended ejector rod is pushed and pressed, the push spring is pressed on the inner wall of the other electrode by the conducting ring, and the conducting ring is separated from the electrode; when the wing is opened, the ejector rod moves under the action of the push spring, the conducting rings are contacted with the electrodes, and the two electrodes are conducted through the conducting rings and the push spring.

Furthermore, the conducting ring is in conical surface contact with the electrode.

Furthermore, the electric switch is an overload switch, and a controlled silicon is arranged in the dual-output high-precision logic control circuit module; overload is generated during rocket projectile launching to close the overload switch, the controllable silicon in the double-output high-precision logic control circuit module is conducted, and when the time is delayed to the set time, the capacitor discharges.

Furthermore, the tail rod assembly also comprises a magneto base, wherein the magneto base comprises an aluminum base body, a baffle plate and a baffle cover;

a channel for moving a core bar of the magneto is arranged in the aluminum seat body, and two ends of the channel are respectively packaged by a baffle plate and a baffle cover; the core rod of the magneto moves under the pressure of gunpowder gas, and the core rod continues to move until the baffle cover after the baffle is cut.

Has the advantages that:

1. the utility model discloses the high accuracy logic control module of dual output has not only realized the output of dual-circuit firing signal under the small volume structure, also guarantees the accurate ignition control demand when the rocket bomb uses; meanwhile, the combination of the power connection switch and the dual-output high-precision logic control module has low cost, high reliability and strong universality, and can be widely applied to the transformation of single-soldier rocket projectile soft launching;

secondly, double-path firing control is adopted, if a launching engine fails when the rocket projectile is launched and a magneto is acted, and because the electric switch is not conducted, after a set delay time, electric energy of a capacitor is exhausted, the double-path output high-precision logic control module cannot work, the flying engine cannot be ignited, and the rocket projectile is in an absolute safety state; and under the logic control of the dual-output high-precision logic control module, the capacitor charging, the switch conduction, the delay and the final capacitor discharging are sequentially carried out, so that the control is accurate, and the reliability and the safety are high.

2. The utility model discloses a safety when magnet motor seat can guarantee rocket projectile daily service and handle, to removing the impact that appears in the bullet process and the condition of colliding with, the removal of baffle restriction magneto core bar makes the magneto can not do the work energy supply, improves the security.

Drawings

FIG. 1 is a flow chart of the dual-way percussion control of the present invention;

FIG. 2 is a schematic structural view of the present invention;

FIG. 3 is a schematic view of the structure of the combustion chamber bottom;

FIG. 4 is a schematic diagram of a magneto;

FIG. 5 is a schematic view of a winged tail boom;

FIG. 6 is a schematic diagram of a magneto mount;

FIG. 7 is a schematic structural view of a striking circuit component;

FIG. 8 is a schematic structural view of a push rod switch;

the device comprises a combustion chamber bottom, a 2-tail rod with fins, a 3-magneto, a 4-magneto base, a 5-threading rod, a 6-trigger circuit component, a 7-push rod switch, an 8-double-output high-precision logic control module, a 9-combustion chamber bottom shell, a 10-primer, an 11-electric igniter, a 12-pressing screw, a 13-tail rod shell, a 14-fin, a 15-fin shaft, a 16-torsion spring, a 17-magneto shell, an 18-double-circuit coil, a 19-core rod, a 20-aluminum base, a 21-baffle, a 22-baffle cover, a 23-lead, a 24-nonmetal base, a 25-electrode, a 26-nonmetal body, a 27-nonmetal body, a 28-ejector rod and a 29-pushing spring, wherein the combustion chamber bottom is provided with a combustion chamber, the tail rod is provided with fins, and.

Detailed Description

The present invention will be described in detail below with reference to the accompanying drawings by way of examples.

The embodiment provides a tail rod assembly for controlling two-way firing of a 40 mm rocket projectile, and as shown in fig. 2, the tail rod assembly comprises a combustion chamber bottom 1, a magneto 3, a magneto base 4, an electric switch, a two-way output high-precision logic control module 8 and a tail rod 2 with a wing piece.

As shown in fig. 3, the combustion chamber bottom comprises a combustion chamber bottom shell 9, a primer 10, an electric igniter 11 and a pressing screw 12, wherein the primer 10 is installed on the side surface of the combustion chamber bottom shell 9, and the electric igniter 11 is installed at the tail end of the combustion chamber bottom shell 9 and is connected with a lead. The pressing screw 12 is fixed at the other end of the combustion chamber bottom shell 9, and a through hole is arranged on the pressing screw 12. A gas transmission channel and a lead avoiding annular groove are arranged in the combustion chamber bottom shell 9, and gas is transmitted out through a through hole of the pressing screw 12 after passing through the gas transmission channel of the combustion chamber bottom shell 9.

As shown in FIG. 5, the finned tail rod 2 comprises a tail rod shell 13, fins 14, a fin shaft 15 and a torsion spring 16, and the mechanism mainly plays a role in stabilizing the flight of a rocket projectile, and meanwhile, the opening and the folding of the fins 14 also control the on-off of the push rod switch 7. The wing 14 is rotatably mounted on the tail lever housing 13 by a wing shaft 15, and the wing 14 is opened by the elastic force of a torsion spring 16.

As shown in fig. 4, the magneto 3 is used for outputting the energy required by the high-precision logic control module 8 and the ignition explosive device in a double-way manner, and comprises a magneto shell 17, a double-way coil 18 and a core rod 19, wherein the double-way coil 18 is arranged in the magneto shell 17, the core rod 19 is in sliding fit with the magneto shell 17, and when the core rod 19 moves, the core rod passes through the double-way coil 18 to generate a double-way electromotive force.

As shown in fig. 6, the magneto holder 4 includes an aluminum holder body 20, a baffle plate 21 and a shield cover 22; a channel for moving the magneto core rod 19 is arranged in the aluminum seat body 20, and two ends of the channel are respectively packaged by a baffle 21 and a baffle cover 22; the magneto core rod 19 is moved under the pressure of the gunpowder gas and continues to move until the shield cover 22 after shearing the shield 21. An inner hole for the lead 23 to pass through is also arranged in the aluminum base body 20.

The power switch, the non-metal base 24 and the dual-output high-precision logic control circuit module 8 together form a firing circuit part 6, as shown in fig. 7, for storing electric energy, outputting a firing signal according to precise time, and igniting the propellant of the flying engine rocket.

The power connection switch can adopt a push rod switch 7 or an overload switch.

As shown in fig. 8, the push switch 7 includes an upper electrode 25, a lower electrode, a conductive ring 26, a non-metal body 27, a push rod 28 and a push spring 29;

the nonmetal body 27 is a cylinder structure with two open ends, and the two ends of the nonmetal body 27 are respectively and fixedly connected with the upper electrode 25 and the lower electrode to form a movable space of the mandril 28 in a surrounding manner. The conducting ring 26 is fixed in the middle of the outer circumference of the mandril 28 and is positioned in the moving space; one end of the push rod 28 is in clearance fit with the upper electrode 25 and is limited by the conducting ring 26, the other end is sleeved with a push spring 29, the push spring 29 is arranged in the moving space, one end of the push spring 29 is in contact with the end face of the conducting ring 26, the other end of the push spring 29 is in contact with the lower electrode, and the push spring 29 is in a compressed state all the time.

When the wing is folded, the push rod 28 which extends downwards is pressed to move towards the lower electrode, the push spring 29 is pressed on the inner wall of the lower electrode by the conducting ring 26, and the conducting ring 26 is separated from the upper electrode 25; when the wing is opened, the top rod 28 moves upward under the action of the push spring 29, i.e. moves toward the upper electrode 25, the conductive ring 26 contacts with the upper electrode 25, and the two electrodes are conducted through the conductive ring 26 and the push spring 29.

The lower electrode is provided with a through hole, so that internal airflow can be removed, and the influence of air pressure on the movement of the ejector rod 28 is eliminated; also, the through hole can serve as a viewing window to confirm whether the push spring 29 is compressed in place or whether the internal structure is intact.

Preferably, the conductive ring 26 is in conical contact with the upper electrode 25. The inner wall surface of the upper electrode 25 is provided with an inclined surface which is in conical fit with the conducting ring 25.

If an overload switch is adopted, a silicon controlled rectifier is required to be arranged in the dual-output high-precision logic control module 8; when the rocket projectile is launched, overload is generated to close the overload switch, the controllable silicon in the dual-output high-precision logic control module 8 is conducted, and when the time is delayed to a set time, the capacitor discharges to detonate the electric igniter 11 and ignite the rocket powder of the flying engine.

During assembly, the tail rod 2 with the wing pieces is installed firstly, the four wing pieces 14, the four wing piece shafts 15 and the four torsion springs 16 are installed on the tail rod shell 13, open grooves are formed in the shaft ends of the wing piece shafts 15, and the wing piece shafts 15 can be located through expansion riveting. The torsion spring 16 provides the motive force for the opening of the wings. The wings 14 are tied using nylon thread after installation to prevent splaying.

Then, installing the triggering circuit component 6, firstly installing the push rod switch 7 in the non-metal seat body 24, welding two wires 23 output by the electrodes 25 of the push rod switch 7 on the dual-output high-precision logic control module 8, leading out six wires 23 on the dual-output high-precision logic control module 8 through the wiring grooves, penetrating through an inner hole of the threading rod 5, installing the threading rod 5 on the non-metal seat body 24, and enabling the threading rod 5 to be axially parallel to the tail rod with the wing piece 2. The striking circuit component 6 and the threading rod 5 are integrally installed in the tail rod shell 13, the ejector rod 28 on the push rod switch 7 penetrates through the corresponding through hole of the tail rod shell 13 to be ejected out, and the motion direction of the ejector rod 28 is vertical to the axial linear direction of the tail rod 2 with the wing piece.

And then the six wires 23 are led out through the inner hole of the aluminum seat body 20 of the magneto seat 4. Then, the aluminum seat body 20 is connected with the threading rod 5 through threads, the blocking cover 22, the blocking plate 21 and the magneto 3 are sequentially installed, the moving direction of the core rod 19 of the magneto 3 is axially parallel to the tail rod 2 with the fin, and four leads (two of the leads are grounded) on the magneto 3 are connected with four of the six leads 23. The other two wires are connected with the two wires led out by the electric igniter 11 on the combustion chamber bottom 1, the wires 23 are placed in the avoiding annular groove after being connected, and the combustion chamber bottom 1 is connected with the tail rod shell 13 through radial screws, so that the assembly of the soft launching tail rod assembly is completed.

The tail rod component controlled by two-way firing replaces the original 40 mm rocket shell primer and gunpowder transfer mechanism, the working process is shown in figure 1, the firing pin on the trigger of the launching tube impacts the primer 10, and the gunpowder gas generated by the primer 10 is transferred to the end surface of the core rod 19 of the magneto 3 through the gas transmission channel on the combustion chamber bottom 1. The core rod 19 is moved axially along the finned tail rod 2 by the pressure of the propellant gas, shearing the baffle 21, passing through the two-way coil 18, and reaching the baffle cap 22. During the passage of the core rod 19 through the two-way coil 18, the magneto 3 generates a two-way electromotive force, which is transmitted by the two-way conductor 23. One path of conducting wire is directly connected to the double-output high-precision logic control module 8, an ignition initiating explosive device of the launching engine is detonated, the other path of conducting wire charges a capacitor in the double-output high-precision logic control module 8, when the rocket projectile is separated from the launching tube, the wing with the wing tail rod 2 is opened, the push rod switch 7 is closed and conducted, at the moment, an accurate timer in the double-output high-precision logic control module 8 starts timing, after the time is delayed to the set time, the double-output high-precision logic control module 8 controls the capacitor to discharge, the electric igniter 11 is detonated accurately, and the rocket propellant of the flying engine is ignited.

In summary, the above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (5)

1. A tail rod assembly for controlling double-path firing of a 40 mm rocket projectile is characterized by comprising a combustion chamber bottom, a magneto, an electric switch, a double-path output high-precision logic control module and a tail rod with fins, wherein the combustion chamber bottom is provided with a combustion chamber;

gunpowder gas generated at the bottom of the combustion chamber is transmitted to a magneto, the magneto acts to generate double-path electromotive force and transmits the electromotive force through two paths of leads, one path of lead is connected to a double-path output high-precision logic control module to detonate ignition initiating explosive of a launching engine, the other path of lead charges a capacitor in the double-path output high-precision logic control module, and when a rocket projectile is separated from a launching tube, a fin with a fin tail rod is opened and is connected with a power switch for conduction; and after the time is delayed to the set time, the dual-output high-precision logic control module controls the capacitor to discharge, so that the propellant of the flying engine is ignited at the bottom of the combustion chamber.

2. The tail-lever assembly of claim 1, wherein the electrical switch is a push-lever switch comprising two electrodes, a conductive ring, a non-metallic body, a push-rod, and a push-spring;

the non-metal body is of a cylindrical structure with two open ends, and two ends of the non-metal body are respectively fixedly connected with an electrode to form a movable space of the ejector rod in a surrounding manner; a conducting ring is fixed in the middle of the outer circumference of the ejector rod and is positioned in the moving space, one end of the ejector rod is in clearance fit with one electrode and limited by the conducting ring, a push spring is sleeved at the other end of the ejector rod, one end of the push spring is in contact with the end face of the conducting ring, the other end of the push spring is in contact with the other electrode, and the push spring is always in a compressed state; when the wing panel is folded, the extended ejector rod is pushed and pressed, the push spring is pressed on the inner wall of the other electrode by the conducting ring, and the conducting ring is separated from the electrode; when the wing is opened, the ejector rod moves under the action of the push spring, the conducting rings are contacted with the electrodes, and the two electrodes are conducted through the conducting rings and the push spring.

3. The tail-bar assembly for a 40 mm rocket projectile dual firing control as claimed in claim 2 wherein said conductive ring is in conical contact with said electrode.

4. The tail rod assembly for the 40 mm rocket projectile dual-path firing control of claim 1, wherein the electric switch is an overload switch, and a thyristor is arranged in the dual-path output high-precision logic control circuit module; overload is generated during rocket projectile launching to close the overload switch, the controllable silicon in the double-output high-precision logic control circuit module is conducted, and when the time is delayed to the set time, the capacitor discharges.

5. The tail-bar assembly for a 40 mm rocket projectile dual fire control as claimed in claim 1 wherein said tail-bar assembly further comprises a magneto mount, said magneto mount comprising an aluminum base, a baffle plate and a shield cover;

a channel for moving a core bar of the magneto is arranged in the aluminum seat body, and two ends of the channel are respectively packaged by a baffle plate and a baffle cover; the core rod of the magneto moves under the pressure of gunpowder gas, and the core rod continues to move until the baffle cover after the baffle is cut.

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