Multi-platform target projectile modified based on retired rocket projectile

Abstract

The invention relates to the technical field of weapon equipment testing and training technologies, in particular to a multi-platform target projectile modified based on an out-of-service rocket projectile, which comprises the out-of-service rocket projectile. The retired rocket projectile is provided with a rectification cabin section, a solid rocket engine, a spray pipe in threaded connection with the solid rocket engine, an electric igniter, an ignition mechanism in threaded connection with the rectification cabin section, an infrared simulation cabin section and an empennage stabilizing mechanism, and the ignition mechanism is consistent with a fuze of the retired rocket projectile in appearance; an infrared source shell and an infrared source are arranged in the infrared simulation cabin section, the infrared source is located in the infrared source shell, the infrared simulation cabin section, the solid rocket engine and the spray pipe are sequentially connected in a screwed mode through threads, and the empennage stabilizing mechanism is connected to the end of the spray pipe in a sleeving mode through threads. The method has the advantage of meeting troop target missile training.

Description

Technical Field

[0001] This application relates to the technical field of weapon equipment testing and training technologies, and particularly relates to a multi-platform target missile refitted from retired rocket projectiles. Background Art

[0002] In recent years, with the rapid development of unmanned aerial vehicles such as drones and cruise missiles, modern warfare mainly relies on air raids and long-range strikes as the main offensive means. Most of these aircraft have subsonic and transonic flight characteristics, are difficult to capture, and have great lethality. This has imposed higher and higher requirements on the air defense and anti-missile combat capabilities of troops. However, due to factors such as cost and training means, medium- and low-speed target drones are still commonly used for live ammunition target shooting in actual combat training of troops, which has a large gap with actual combat.

[0003] Live ammunition shooting training of air defense missiles is an important subject in the daily military exercises of the Marine Corps. The Marine Corps has clearly put forward the need for a target that can simulate the flight characteristics of high-subsonic and transonic classes to cope with the increasingly complex maritime military environment. In addition, the Xichang Base and air-land forces have also put forward clear requirements for high-speed target missiles.

[0004] At present, there are generally two ways to develop target missiles at home and abroad: 1. Special development of target missiles: It can realistically simulate cruise missiles in terms of flight speed, altitude, attitude, radar scattering characteristics, and infrared characteristics. This solution integrates many disciplinary fields such as missiles, targets, and range tests. It is a large-scale test project with high technology intensity and strong professionalism. The special functional requirements such as its demanding high reliability, high precision, and high safety target supply exceed the technical standards of conventional missiles and targets, and the engineering difficulty is extremely great.

[0005] 2. Modification using in-service or to-be-retired missiles: Remove redundant components from existing missiles and additionally install equipment such as infrared light sources. However, this solution has a high cost, is difficult to mass-produce, and will cause great waste, resulting in its inability to meet the extensive and large-scale needs of range test appraisal and troop combat training. Summary of the Invention

[0006] In order to meet the needs of troop target missile training, this application provides a multi-platform target missile refitted from retired rocket projectiles.

[0007] The multi-platform target missile refitted from retired rocket projectiles provided by this application adopts the following technical solutions: A multi-platform target missile refitted from a retired rocket includes a retired rocket, which is provided with a fairing section, a solid rocket motor, a nozzle threadedly connected to the solid rocket motor, an electric igniter fixedly connected to the nozzle, an ignition mechanism threadedly connected to the fairing section, an infrared simulation section, and a fin stabilization mechanism. The ignition mechanism has the same external shape as the fuse of the retired rocket. An infrared source housing and an infrared source are arranged inside the infrared simulation section, and the infrared source is located inside the infrared source housing. The infrared simulation section, the solid rocket motor, and the nozzle are sequentially screwed together, and the fin stabilization mechanism is threadedly sleeved on the end of the nozzle.

[0008] By adopting the above technical solution, the troops currently have a large number of unguided retired rockets of various models with low cost. A large part of them will be scrapped and destroyed in the next few years. The main disadvantages of unguided rockets are poor technical performance indicators: parabolic flight trajectory, rapid decrease in flight altitude, short hang time, low target supply accuracy, and inability to be used as target missiles. A large number of retired rockets can be transformed to change their flight characteristics to meet the tactical and technical index requirements of target missiles. This not only avoids the losses of manpower, financial resources and safety risks brought by scrapping old ammunition, but also meets the requirements of the troops for low-cost and extensive target practice. At the same time, the infrared simulation section and the infrared source provide infrared characteristics for the target missile to meet the training needs of the troops.

[0009] Optionally, the nozzle is a Laval nozzle.

[0010] By adopting the above technical solution, it can not only ensure that the engine has sufficient thrust throughout the trajectory, but also has a small structural mass.

[0011] Optionally, the infrared source housing includes an upper cover, an upper sleeve, an upper plate, a lower plate, a connecting rod, a lower sleeve, and a lower cover. The number of infrared sources is two. The upper cover is threadedly sleeved on one end of the upper sleeve, the upper plate is clamped and sealed at the other end of the upper sleeve, the lower cover is threadedly sleeved on one end of the lower sleeve, the lower plate is clamped and sealed at the other end of the lower sleeve, the upper plate and the lower plate are fixed by a connecting rod, and both ends of the connecting rod are threadedly connected to the upper plate and the lower plate respectively. The two infrared sources are respectively located inside the upper sleeve and the lower sleeve, and the connecting rod is located at the opening position of the infrared simulation section.

[0012] By adopting the above technical solution, the stable installation of two infrared sources is realized, providing infrared characteristics for the target missile to meet the training needs of the troops.

[0013] Optionally, a slide rail groove and a flexible fastening belt are arranged outside the infrared simulation section, and the slide rail groove is fixedly connected to the outside of the infrared simulation section through the flexible fastening belt.

[0014] By adopting the above technical solution, the present application can be used to dock with the launch rail during air launch, thereby realizing the air launch of the present application.

[0015] Optionally, the tail stabilizing mechanism is connected to the outside of the nozzle, and the tail adopts an "X"-shaped layout.

[0016] By adopting the above technical solution, the performance is better than the "+" font layout.

[0017] Optionally, the electric ignition device is bonded to the nozzle by epoxy glue, and the electric ignition device adopts a phenolic bakelite shell.

[0018] By adopting the above technical solution, the electric ignition device is light in weight, simple to modify, and can ignite reliably. At the same time, the electric ignition device also has a pressure-maintaining function, which can make the electric ignition device pop out when the internal pressure of the engine reaches a certain G value, ensuring that the engine thrust meets the requirements.

[0019] Optionally, the ignition mechanism ignites the infrared source in an inertial delay manner, and the ignition mechanism has a built-in inertial switch, a power supply and a delay circuit.

[0020] By adopting the above technical solution, the purpose of ignition is achieved.

[0021] In summary, the present application includes at least one of the following beneficial technical effects: The infrared simulation cabin section in this application achieves the purpose of deceleration under the premise of satisfying basic infrared recognition and without changing the engine; The electric igniter in the present application can not only ignite the engine, but also maintain pressure, so that the electric igniter can be ejected when the internal pressure of the engine reaches a certain G value, ensuring that the engine thrust meets the requirements; The target missile in the present application is equipped with a slide rail design, which can be suitable for launching from both ground and air platforms. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the structure of a multi-platform target missile modified from retired rockets disclosed in an embodiment of the present application.

[0023] Figure 2 It is a structural schematic diagram of the ignition mechanism in the embodiment of the present application.

[0024] Figure 3 It is a schematic diagram of the structure of the rectifier compartment in the embodiment of the present application.

[0025] Figure 4 It is a schematic diagram of the structure of the infrared simulation cabin in the embodiment of the present application.

[0026] Figure 5It is a schematic structural diagram of a solid rocket motor in an embodiment of the present application.

[0027] Figure 6 It is a schematic structural diagram of a fin stabilization mechanism in an embodiment of the present application.

[0028] Figure 7 It is a schematic structural diagram of a nozzle in an embodiment of the present application.

[0029] Figure 8 It is a schematic structural diagram of an electric igniter in an embodiment of the present application.

[0030] Explanation of reference numerals: 1, ignition mechanism; 2, fairing section; 3, infrared simulation section; 4, solid rocket motor; 5, fin stabilization mechanism; 6, nozzle; 7, electric igniter; 8, infrared source housing; 9, infrared source; 10, upper cover; 11, upper sleeve; 12, upper plate; 13, lower plate; 14, connecting rod; 15, lower sleeve; 16, lower cover. Detailed implementation manners

[0031] The following further Figure 1 - with reference to the Figure 8 explains the present application in detail.

[0032] Currently, in order to meet the training requirements of the troops, an embodiment of the present application proposes a multi-platform target missile refitted from a retired rocket projectile.

[0033] A multi-platform target missile refitted from a retired rocket projectile, with a missile length of 1267 mm and an outer diameter of Φ107 mm, referring to Figure 1 , which includes a retired rocket projectile, the retired rocket projectile is provided with a fairing section 2, a solid rocket motor 4, a nozzle 6 threadedly connected to the solid rocket motor 4, an electric igniter 7 fixedly connected to the nozzle 6, an ignition mechanism 1 threadedly connected to the fairing section 2, an infrared simulation section 3 and a fin stabilization mechanism 5. The solid rocket motor 4 uses the original 107 mm retired rocket projectile motor, and the original fuse is modified into an ignition mechanism 1. The ignition mechanism 1, the fairing section 2, the infrared simulation section 3, the solid rocket motor 4, the fin stabilization mechanism 5 and the nozzle 6 are connected in sequence. The ignition mechanism 1 has the same outer shape as the fuse of the retired rocket projectile. An infrared source housing 8 and an infrared source 9 are arranged in the infrared simulation section 3. The infrared source 9 is located inside the infrared source housing. The infrared simulation section 3, the solid rocket motor 4, and the nozzle 6 are sequentially screwed together. The fin stabilization mechanism 5 is threadedly sleeved on the end of the nozzle 6.

[0034] The military currently has a large number of unguided retired rockets of various models with low costs. A large portion of them will be scrapped and destroyed in the next few years. The main drawbacks of unguided rockets are poor technical performance indicators: a parabolic flight trajectory, a rapid decrease in flight altitude, a short stay in the air, low target supply accuracy, and inability to be used as target projectiles. A large number of retired rockets can be transformed to change their flight characteristics to meet the tactical and technical requirements of target projectiles. This not only avoids the losses of manpower, financial resources, and safety risks brought by scrapping old ammunition but also meets the low-cost and extensive demand for targets in actual combat training of the military. At the same time, the infrared simulation section 3 and the infrared source 9 provide the infrared characteristics for the target projectile, meeting the training needs of the military. After installing the infrared simulation section 3, the purpose of deceleration is achieved on the premise of meeting basic infrared recognition and without changing the engine.

[0035] Referring to Figure 2, the external shape design of the ignition mechanism 1 is the same as that of the original 107mm retired rocket. The inertial delay method is used to ignite the infrared source 9, and an inertial switch, a power supply, and a delay circuit are built-in to achieve the purpose of ignition.

[0036] Referring to Figure 3 Figure 3, the fairing section 2 uses the warhead of the original 107mm retired rocket, with the charge emptied. The internal arc structure can be used to fix the housing 8 of the infrared source 9 inside the infrared simulation section 3. This structural design is simple and low-cost.

[0037] Referring to Figure 4 Figure 4, the housing 8 of the infrared source 9 includes an upper cover 10, an upper sleeve 11, an upper plate 12, a lower plate 13, a connecting rod 14, a lower sleeve 15, and a lower cover 16. The number of infrared sources 9 is two. The upper cover 10 is threadedly sleeved at one end of the upper sleeve 11, and the upper plate 12 is snap-fitted and sealed at the other end of the upper sleeve 11. The lower cover 16 is threadedly sleeved at one end of the lower sleeve 15, and the lower plate 13 is snap-fitted and sealed at the other end of the lower sleeve 15. The infrared sources 9 are respectively fixed through the upper cover 10, the lower cover 16, the upper plate 12, and the lower plate 13. Inside the upper sleeve 11 and the lower sleeve, the stable installation of the two infrared sources 9 is achieved, providing the infrared characteristics for the target projectile and meeting the training needs of the military. The upper plate 12 and the lower plate 13 are fixed through the connecting rod 14. The two ends of the connecting rod 14 are respectively threadedly connected to the upper plate 12 and the lower plate 13. The two infrared sources 9 are respectively located inside the upper sleeve 11 and the lower sleeve 15, and the connecting rod 14 is located at the opening position of the infrared simulation section 3. The design of the infrared simulation section 3 lengthens the overall length of the original 107mm retired rocket, stabilizes the flight trajectory, and has a good aerodynamic shape. Without changing the charge structure, the speed is reduced from the original 600m / s to 300m / s, meeting the design requirements of the target projectile.

[0038] Referring to Figure 4A slide rail groove and a flexible fastening belt are provided on the outside of the infrared simulation cabin 3. The slide rail groove is fixedly connected to the outside of the infrared simulation cabin 3 by the flexible fastening belt. An air launch rail is added. The slide rail groove is used for docking with the launch rail during air launch, so that the present application can be used for docking with the launch rail during air launch, thereby realizing the air launch of the present application.

[0039] Reference Figure 6 The tail stabilizing mechanism 5 is screwed onto the outside of the nozzle 6 through a thread, and the tail adopts an "X"-shaped layout, which is superior to the "X"-shaped layout in terms of overall missile stability, control efficiency, transportation and launch. The tail stabilizing mechanism 5 is made of aluminum alloy, which can reduce the weight of the tail and ensure the strength of flight.

[0040] Reference Figure 7 The nozzle 6 adopts a single conical Laval nozzle 6, which can ensure that the engine has sufficient thrust in the entire trajectory while also having a smaller structural mass. The material of the nozzle 6 is 17-4PH, a precipitated, hardened, martensitic stainless steel composed of copper, niobium / column. After heat treatment, the mechanical properties of the product are more perfect, and the compressive strength can reach up to 1100-1300Mpa (160-190ksi). The front end of the nozzle 6 is provided with an M100x2-g6 thread to ensure the connection strength with the engine. The thread in the middle of the nozzle 6 ensures that the inner and outer surfaces of the nozzle 6 are tightly connected. The outer cylindrical feature at the tail of the nozzle 6 serves as the circumferential positioning surface of the inner and outer surfaces of the nozzle 6, which improves the overall coaxiality and concentricity after the target missile is installed.

[0041] Reference Figure 7 and Figure 8 The electric igniter 7 is bonded to the nozzle 6 by epoxy adhesive. The electric igniter 7 adopts a phenolic bakelite shell. The electric igniter 7 adopts the design of the original 107mm retired rocket igniter, which is light in weight, simple to transform, and can ignite reliably. At the same time, the electric igniter 7 also has a pressure-maintaining function, which can make the electric igniter 7 pop out when the internal pressure of the engine reaches a certain G value, ensuring that the engine thrust meets the requirements.

[0042] The implementation principle of this application is as follows: This application is transformed from a retired 107mm rocket projectile, with high reliability, short transformation time, and low cost. The target projectile of this application can be launched on the ground and in the air. The ground launch method is as follows: Start the engine to work, and the ignition mechanism 1 activates the infrared source 9 under the overload force for a certain period of time. After the target projectile rises to a certain height, it realizes stable flight, and then descends under the action of gravity until it lands; The air launch method is as follows: The target projectile is carried by an aircraft (unmanned aircraft). The aircraft (unmanned aircraft) flies to the area where the target projectile can be launched. The ground control terminal ignites, and the target projectile leaves the rail. The ignition mechanism 1 activates the infrared source 9 under the overload force for a certain period of time. The target projectile realizes stable flight, and then descends until it lands. The target projectile mainly completes the corresponding tactical exercise requirements during the level flight section and the descent section. Compared with ground launch, air launch can better simulate the randomness of hostile targets, and the ballistic trajectory is closer to the target, and the target supply time is longer, which can better approximate actual combat.

[0043] The above are all the preferred embodiments of this application, and the protection scope of this application is not limited accordingly. Therefore, all equivalent changes made according to the structure, shape, and principle of this application should be covered within the protection scope of this application.

Claims

1. A multi-platform target missile modified from a retired rocket, comprising a retired rocket, wherein the retired rocket is provided with a fairing compartment (2), a solid rocket engine (4), a nozzle (6) threadedly connected to the solid rocket engine (4), and an electric igniter (7) fixedly connected to the nozzle (6), characterized in that: It also includes an ignition mechanism (1) threadedly connected to the fairing compartment (2), an infrared simulation compartment (3) and a tail stabilization mechanism (5), wherein the ignition mechanism (1) is consistent with the appearance of the fuze of the retired rocket, an infrared source (9) shell (8) and an infrared source (9) are arranged in the infrared simulation compartment (3), and the infrared source (9) is located inside the infrared source (9) shell, the infrared simulation compartment (3), the solid rocket engine (4) and the nozzle (6) are screwed in sequence, and the tail stabilization mechanism (5) is threadedly sleeved on the end of the nozzle (6).

2. The multi-platform target missile modified from retired rockets according to claim 1, characterized in that: The nozzle (6) is a Laval nozzle (6).

3. The multi-platform target missile modified from retired rockets according to claim 1, characterized in that: The infrared source (9) housing (8) comprises an upper cover (10), an upper sleeve (11), an upper plate (12), a lower plate (13), a connecting rod (14), a lower sleeve (15) and a lower cover (16). The number of the infrared sources (9) is two. The upper cover (10) is threadedly sleeved on one end of the upper sleeve (11), the upper plate (12) is snap-connected and sealed on the other end of the upper sleeve (11), and the lower cover (16) is threadedly sleeved on the lower end of the lower sleeve (15). One end, the lower plate (13) is snap-fitted and sealed to the other end of the lower sleeve (15), the upper plate (12) and the lower plate (13) are fixed by a connecting rod (14), the two ends of the connecting rod (14) are respectively threadedly connected to the upper plate (12) and the lower plate (13), two infrared sources (9) are respectively located inside the upper sleeve (11) and the lower sleeve (15), and the connecting rod (14) is located at the opening position of the infrared simulation cabin section (3).

4. The multi-platform target missile modified from retired rockets according to claim 3, characterized in that: The outside of the infrared simulation cabin section (3) is provided with a slide rail groove and a flexible fastening belt, and the slide rail groove is fixedly connected to the outside of the infrared simulation cabin section (3) via the flexible fastening belt.

5. The multi-platform target missile modified from retired rockets according to claim 1, characterized in that: The tail stabilizing mechanism (5) is connected to the outside of the nozzle (6), and the tail adopts an "X"-shaped layout.

6. The multi-platform target missile modified from retired rockets according to claim 1, characterized in that: The electric igniter (7) is bonded to the nozzle (6) by epoxy adhesive, and the electric igniter (7) adopts a phenolic bakelite shell.

7. The multi-platform target missile modified from retired rockets according to claim 1, characterized in that: The ignition mechanism (1) ignites the infrared source (9) in an inertial delay manner, and the ignition mechanism (1) has an inertial switch, a power supply and a delay circuit built in.

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