Low-overload simulation test bomb

Abstract

The invention discloses a low-overload simulation test bomb, and belongs to the technical field of ammunition engineering and weapon launching. The test bomb comprises a wind cap, a counterweight body, a bomb shell, an engine assembly, a rocket engine and an empennage assembly. The wind cap is fixedly connected to the front end of the projectile shell through a wind cap seat, the wind cap is internally provided with a mounting space for the counterweight bodies, and the mounting number of the counterweight bodies is adjusted as required; the fuse mounting mechanism is fixedly mounted in the projectile shell, the engine assembly is mounted at the rear end of the projectile shell through the connector, the rocket engine is mounted in the engine assembly, and the empennage assembly is fixedly connected to the engine assembly; the simulation test bomb is launched through a launching tube, and launching and flying power is provided by a rocket engine. According to the invention, the low-overload running state of a missile can be simulated, regulation and control of main test parameters such as overload, flight time and flight distance can be realized, and the device can be widely applied to safety release of a safety mechanism and related research of guided ammunition ballistic science under the low-overload condition.

Description

Technical Field

[0001] The invention relates to the field of ammunition engineering and weapon launching technology, and in particular to a low-overload simulation test bomb. Background Art

[0002] The fuze is a control device (system) installed in the ammunition, which uses target information and environmental information to detonate or ignite the charge in the warhead of the ammunition under predetermined conditions. The fuze safety actuator is an important component of the fuze. It prevents the firing mechanism, explosion-proof mechanism and other mechanisms of the fuze from unexpected dangers, and can only release the fuze insurance (i.e. "release") under predetermined conditions. This mechanism ensures the safety and reliability of the fuze and is a key link in the normal operation of the fuze. Whether the safety actuator can release the insurance normally is directly related to the reliability of the ammunition. Therefore, after the design of the safety actuator is completed, it needs to be tested and verified in the actual release environment. There are many verification methods for this test, mainly including live ammunition, rocket pry, simulated endurance engine propulsion and other test methods.

[0003] Testing methods such as live ammunition and rocket prying are very expensive and have stringent requirements on the test site, so they are rarely used in actual tests.

[0004] The overload of artillery ammunition is relatively high (generally tens of thousands of g), and the high-pressure gas generated by the intense combustion of gunpowder charges is used to push the shells out of the barrel. Unlike artillery shells, missiles have a lower overload (generally dozens of g or even a few g), and their launch and transportation mainly rely on rocket engines. The combustion of propellant charges in rocket engines generates pressure, and the ejected high-pressure gas generates thrust, providing power for the launch and transportation of missiles. Rocket engines can be divided into takeoff engines and endurance engines. The takeoff engine has a shorter working time, so it is generally not selected as the release environment of the safety enforcement agency; although the endurance engine has a smaller overload, it has a longer working time and is often selected as the release environment in the design of the safety enforcement agency.

[0005] The simulated endurance engine propulsion test method can be divided into two types: "walking on a tightrope" (or rope) and "tube launching". Among them, the "walking on a tightrope" (or rope) method requires the test projectile to be suspended on a wire (or rope), and the test projectile is launched along the wire (or rope) under the action of the engine. The required wire (rope) is relatively long, and this method is difficult to implement when the projectile flies a long distance. In contrast, the use of "tube launching" (or track launching) is a very cost-effective method. During the storage and use of the launch tube, the inner wall of the launch tube may be worn and corroded, thereby affecting the running state of the ammunition in the launch tube, and then affecting the range, flight time and accuracy of the ammunition. In addition, the use of the "tube launching" (or track launching) method requires the structure and parameters of the simulated test projectile to be rationally designed to adjust the main test parameters such as overload, flight time and flight distance, so as to meet the relevant technical requirements. Summary of the invention

[0006] In view of this, the present invention provides a low-overload simulation test bomb, which can simulate the low-overload operating state of a missile and realize the regulation of major test parameters such as overload, flight time and flight distance. It can be widely used in related research on safety mechanism release and guided ammunition ballistics under low-overload conditions.

[0007] A low overload simulation test projectile, comprising a wind cap, a counterweight, a projectile shell, an engine assembly, a rocket engine and a tail assembly, and the peripheral equipment is a fuze safety mechanism and a launch tube to be tested;

[0008] The wind hood is fixedly connected to the front end of the projectile shell through a wind hood seat, and an installation space for a counterweight body is provided inside the wind hood, and the installation quantity of the counterweight body is adjusted according to needs; a fuze safety mechanism is fixedly installed inside the projectile shell, an engine assembly is installed at the rear end of the projectile shell through a connector, a rocket engine is installed inside the engine assembly, and a tail wing assembly is fixedly connected to the engine assembly; the simulated test projectile is launched through a launch tube, and the launch and flight power are provided by the rocket engine.

[0009] Furthermore, the hood is in the shape of a long nose, with screw holes arranged thereon, the counterweight body is connected to the hood with screws, the hood is fixedly connected to the hood seat behind it with threads, and the hood seat is connected to the projectile shell with screws.

[0010] Furthermore, the number of the counterweights is related to the total weight of the simulated test projectile.

[0011] Furthermore, the projectile shell is cylindrical, and screw holes are provided around the barrel body for fixing the fixing bracket of the fuze safety mechanism. The fuze safety mechanism is installed inside the projectile shell through the fixing bracket, and the battery supplies power to the fuze safety mechanism; screw holes are provided at the front and rear ends of the projectile shell, which are respectively connected to the front hood seat and the rear connector with screws.

[0012] Furthermore, the size of the projectile housing is related to the number of safety devices.

[0013] Furthermore, the engine assembly includes an engine chamber tube, a centering valve, a centering ring and an engine clamping ring. The rocket engine is inserted into the engine chamber tube and positioned by the centering valve and centering ring outside it. The tail is fixed by the engine clamping ring. The engine chamber tube is fixed to the front connector and the rear tail wing seat by threads.

[0014] Furthermore, the tail wing assembly comprises a tail wing seat, a torsion spring, a cotter pin and a tail wing piece, and the tail wing piece is fixed to the tail wing seat by means of the torsion spring and the cotter pin.

[0015] Beneficial effects:

[0016] 1. The present invention uses the rocket engine at the tail of the test missile as a power source, and launches the simulated test missile through the launch device. Therefore, the overload is related to the thrust of the engine assembly and the total weight of the simulated test missile. Changing these two factors can change the size of the overload, thereby achieving "low overload". The total weight of the test missile can be changed by adjusting the counterweight in the wind cap and the relevant dimensions of the test missile, and the thrust can be changed by using rocket engines with different thrusts and action times. Therefore, the present invention can achieve adjustable overload and flight time of the test missile, thereby meeting different technical requirements.

[0017] 2. The low-overload simulation test projectile provided by the present invention can be equipped with a counterweight in the wind cap at the front end of the device on the basis of the stability of the tail wing, so that the center of mass of the projectile moves forward and the pressure center moves backward, the ratio of the equatorial moment of inertia to the polar moment of inertia of the projectile is reduced, and the overturning torque is also reduced, thereby further improving the flight stability of the projectile, effectively preventing the projectile from flying around, providing convenience for the recovery of the safety enforcement mechanism, and also improving the controllability and safety of the test process.

[0018] 3. The low overload simulation test bomb provided by the present invention is mainly composed of a hood, a counterweight, a projectile shell and an engine assembly, while a missile live ammunition is generally composed of a warhead, a guidance system, a rocket engine device and a projectile body. Among them, the warhead is mainly composed of a shell, a combat charge, a detonation device and a safety device, and the guidance system is mainly composed of a measuring device (radar or visible light, infrared, laser detector / accelerometer, gyroscope and other inertial measurement devices, etc.), a computing device (guidance computer), a control circuit, a servo system (composed of a motor, a reducer, a transmission mechanism and a rudder, etc.), and other precision equipment. Since the expensive warhead and guidance system in the missile live ammunition are omitted, the production and test costs are greatly reduced.

[0019] 4. The low-overload simulation test bomb provided by the present invention can adjust the weight of the entire test bomb by adjusting the weight of the counterweight in the wind cap at the front end of the device, and with the assistance of rocket engines with different thrusts and working times, it can realize the regulation of major test parameters such as overload, flight time and flight distance, and can be widely used in related research on safety mechanism release and guided ammunition ballistics under low-overload conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the structure of the low overload simulation test bomb of the present invention;

[0021] Figure 2 It is a schematic diagram of the installation structure of the counterweight and the fuze safety mechanism of the present invention;

[0022] Figure 3 It is a schematic structural diagram of the tail wing seat assembly of the present invention;

[0023] Figure 4 It is a schematic diagram of the structure of the launch device of the present invention.

[0024] Among them, 1- wind hood, 1-1- counterweight, 2- wind hood seat, 3- shell barrel, 3-1- screw, 3-2- screw, 3-3- screw, 4- fuze safety mechanism, 5- connector, 6- rocket engine, 7- tail assembly, 7-1- tail seat, 7-2- tail, 7-3- parallel double torsion spring, 7-4- splint parent and child screw, 7-5- cotter pin, 7-6- pin shaft, 8- test device, 8-1- screw, 8-2- electrical connector bracket, 8-3- electrical connector. DETAILED DESCRIPTION

[0025] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0026] As attached Figure 1 As shown, the present invention provides a low overload simulation test bomb, including a front hood 1, a hood seat 2, a middle shell barrel 3, a connecting body 4, and a tail engine assembly 6 and a tail wing seat assembly 7. The hood 1 is equipped with a counterweight 1-1, and the shell barrel 3 is equipped with a fuze safety mechanism 4 and a test device 8 to be tested.

[0027] The wind cap 1 is used to reduce the wind resistance of the ammunition and increase the range; the shell barrel 3 is used to install the fixing bracket 3-1, and the fixing bracket 3-1 is used to install the fuze safety mechanism 4 to be tested. A test device 8 is fixed behind the fuze safety mechanism 4, and the purpose of the test device 8 is to test the release status of the fuze safety mechanism 4; the engine assembly 6 provides a power source for the launch of the simulated test projectile; the tail wing assembly 7 is used to improve the flight stability of the projectile.

[0028] like Figure 2As shown, there is space for installing the counterweight 1-1 in the hood 1 structure, and screw holes are left on the hood. M4×8mm internal countersunk screws can be used to install and fix different numbers of counterweights 1-1 to adjust the total weight of the test device, thereby regulating the overload, flight time, flight distance, etc. The existence of the hood 1 can also move the center of mass of the missile forward, thereby improving the flight stability of the simulated test missile. In this embodiment, the hood 1 structure is a cylindrical structure of Ф60×312mm, and the material is LY12 aluminum alloy. The function is to reduce the wind resistance of the simulated test missile during flight and increase the range; the tail of the hood 1 is threadedly connected to the rear hood seat 2 with an M68×1.5-6g thread.

[0029] The hood seat 2 is a disc structure with a front protrusion, the protrusion size is Ф75×40mm, the disc part size is Ф332×25mm, and the material is LY12 aluminum alloy. It is threadedly connected to the hood 1 in front of it with M68×1.5-7H threads. There are screw holes on the hood seat 2, and M5×10mm internal countersunk screws are used to form a screw connection with the shell barrel behind it. The counterweight body 5 is a round rod-shaped structure of Ф60×46mm, made of 45# steel, and can be installed and fixed in the hood 1 with M4×8mm internal countersunk screws 1-2. The number of counterweight bodies 1-1 can be increased or decreased according to actual needs.

[0030] The shell barrel 3 is a cylindrical structure of Ф334×332mm, made of LY12 aluminum alloy, with screw holes reserved in the barrel, and the fixing bracket is installed with M4×8mm internal angle countersunk screws; the fixing bracket in the figure has four layers, and the fixing brackets are arranged at equal intervals, and can install four fuze safety mechanisms 4 to be tested.

[0031] The front end of the shell barrel 3 is screwed to the hood seat 2 in front of it with an M5×10mm internal countersunk screw, and the rear end is screwed to the connector 4 behind it with an M5×16mm internal countersunk screw.

[0032] The connector 5 is a convex, curved disc-like structure with a total height of 70mm, a disc diameter of 323mm, a convex part of a cylindrical structure of 105×23mm, and is made of LY12 aluminum alloy. The front end is screwed to the housing barrel 3 in front of it with an M5×16mm internal angle countersunk screw, and the rear end is screwed to the engine chamber tube behind it with an M96×1.5-7H thread. The rocket engine used is installed in the engine chamber tube. A 22mm through hole is left at the bottom of the connector 5, which is a mounting hole for mounting the disconnecting socket.

[0033] Screw 3-1, screw 3-2, and screw 3-3 are respectively M5×10mm, M4×8mm, and M5×16mm internal angle countersunk screws, and screw 8-1 is a M2×20mm cross recessed pan head screw, which are used to fix the electrical connector 8-3 in the test device 8; the electrical connector bracket 8-2 and the electrical connector 8-3 are matching components in the test device 8, and the purpose of the test device 8 is to test the release status of the fuze safety mechanism 4.

[0034] like Figure 3 As shown, the tail assembly 7 includes: a tail seat 7-1, a tail 7-2, a parallel double torsion spring 7-3, a clamping plate screw 7-4, a cotter pin 7-5 and a pin shaft 7-6.

[0035] The tail seat 7-1 is based on a cylindrical structure of M170×40mm, with 6 tail brackets extending from the outside, symmetrically arranged at an angle of 60°. The tail seat 7-1 is threadedly connected to the engine chamber tube in front of it with a thread of M96×1.5-7H; the tail 7-2 is based on a plate-like structure of 417×95×4mm, with a protrusion on one side. The tail 7-2 has a total of 6 pieces, symmetrically arranged at an angle of 60°. The tail 7-2 is usually in an open state, and becomes closed after being loaded into the launch tube. In the folded state, after the simulated test projectile is fired out of the launch tube, it is changed back to the open state under the elastic force of the torsion spring, thereby improving the flight stability of the projectile; the parallel double torsion springs 7-3 and the cotter pin 7-5 are used to install the tail 7-2 on the tail bracket, first extend the protruding part of the tail 7-2 into the groove of the tail bracket, then press it with the torsion spring, and finally use the cotter pin to fix the tail 7-2; the purpose of the splint screw 7-4 and the pin shaft 7-6 is to fix the tail bracket.

[0036] like Figure 4 As shown, the launch device includes a launch tube and a launch frame. The launch tube is made of 45# steel, and the launch frame is made of channel steel. The assembled simulated test bomb is loaded into the launch tube, and subsequent test work can be carried out after connecting the ignition line.

[0037] The working process of the low-overload simulation test bomb provided by the present invention is as follows: the rocket engine 6 inside the engine assembly receives the ignition command to ignite the ignition device, the ignition device ignites the powder column, the combustion of the powder column generates pressure, and the ejected high-pressure gas generates thrust, and the simulation test bomb is ejected from the launch tube. The tail 7-2 in the tail assembly 7 unfolds after exiting the tube and controls the simulation test bomb to fly along the trajectory to complete the launch mission. The test device 8 tests the release status of the fuze safety mechanism 4 during the flight, and searches and recovers the simulation test bomb after the flight ends, and subsequently analyzes the release status.

[0038] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A low overload simulation test bomb, characterized in that: It includes the wind cap, counterweight, projectile shell, engine assembly, rocket engine and tail assembly, and the peripheral equipment is the fuze safety mechanism and launch tube to be tested; The wind hood is fixedly connected to the front end of the projectile shell through a wind hood seat, and an installation space for a counterweight body is provided inside the wind hood, and the installation quantity of the counterweight body is adjusted according to needs; a fuze safety mechanism is fixedly installed inside the projectile shell, an engine assembly is installed at the rear end of the projectile shell through a connector, a rocket engine is installed inside the engine assembly, and a tail wing assembly is fixedly connected to the engine assembly; the simulated test projectile is launched through a launch tube, and the launch and flight power are provided by the rocket engine.

2. The low overload simulation test bomb according to claim 1, characterized in that: The hood is in the shape of a long nose, with screw holes arranged thereon, the counterweight body is connected to the hood by screws, the hood is fixedly connected to the hood seat behind it by threads, and the hood seat is connected to the projectile shell by screws.

3. The low overload simulation test bomb according to claim 2, characterized in that: The number of the counterweight bodies is related to the total weight of the simulated test projectile.

4. The low overload simulation test bomb according to claim 3, characterized in that: The projectile shell is cylindrical, and screw holes are provided around the barrel body for fixing the fixing bracket of the fuze safety mechanism. The fuze safety mechanism is installed inside the projectile shell through the fixing bracket, and the battery supplies power to the fuze safety mechanism. Screw holes are provided at the front and rear ends of the projectile shell, which are respectively connected to the front hood seat and the rear connector with screws.

5. The low overload simulation test bomb according to claim 4, characterized in that: The size of the projectile housing is related to the number of safety devices.

6. The low overload simulation test bomb according to claim 5, characterized in that: The engine assembly includes an engine chamber tube, a centering valve, a centering ring and an engine clamping ring. The rocket engine is inserted into the engine chamber tube and positioned by the centering valve and centering ring outside it. The tail is fixed by the engine clamping ring. The engine chamber tube is fixedly connected to the front connector and the rear tail wing seat by threads.

7. The low overload simulation test bomb according to claim 6, characterized in that: The tail wing assembly comprises a tail wing seat, a torsion spring, a cotter pin and a tail wing piece, and the tail wing piece is fixed on the tail wing seat by means of the torsion spring and the cotter pin.

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