A launching mechanism for cruise target missile

Abstract

This utility model discloses a launching mechanism for a loitering target missile, including a base frame and a launching platform connected to the base frame via hinges. The launching platform and the base frame are connected by an electrically controlled lifting system. Two parallel target missile mounting slots are installed on the rear of the launching platform away from the base frame. A balance control bracket is installed within each target missile mounting slot. A sliding guide rail located on the central axis of the two target missile mounting slots is provided at the front of the launching platform. A limit device is provided on the side of the sliding guide rail near the balance control bracket. An ignition and disengagement control system is provided at the top of the balance control bracket. A flash baffle is installed between the balance control bracket and the launching platform. This utility model provides tooling for launching medium-to-large target missiles and is used for collecting relevant data in preliminary experiments. It solves the problem of controlling different parameters required for multiple experiments during the development of new medium-to-large target missiles, and can also meet the needs of operation in different environments.

Description

Technical Field

[0001] The utility model relates to the technical field of target missile launching, in particular to a launching mechanism for a cruising target missile. Background Art

[0002] The existing target missile launcher consists of a chassis, leveling legs, a turntable, a bracket, a support, a guide rail, a servo device and a control device. The chassis adopts a self-propelled chassis. The power for leveling the whole vehicle, rotating the turntable and erecting the bracket is generally completed by taking power from the chassis engine to drive the hydraulic system. There are many interfaces between the chassis and the chassis, and the workload of the transformation is large. The ejection placement frame of the target missile and the target drone needs to adjust its launch angle when in use, so as to facilitate the flight angle of the unmanned target drone during launch. There is an urgent need for a launch mechanism for a cruise target missile to solve the different parameter control required for multiple experiments during the development of new medium and large target drones. Utility Model Content

[0003] According to the technical problems to be solved, a mechanism for launching cruise target missiles is provided. The tooling is used when launching medium and large target missiles and is used to collect relevant data in preliminary experiments. This solves the problem of different parameter control required for multiple experiments during the development of new medium and large target aircraft and can meet the needs of operations in different environments.

[0004] To achieve the above-mentioned purpose, the utility model discloses a mechanism for launching a cruising target missile, including a base frame and a launcher connected to the base frame by a hinge, the launcher and the base frame are connected by an electric-controlled lifting system, two parallel target drone mounting grooves are installed on the side of the rear of the launcher away from the base frame, a balance control bracket is installed in the target drone mounting groove, a sliding guide rail located on the central axis of the two target drone mounting grooves is arranged at the front of the launcher, a limiting device is arranged on the side of the sliding guide rail close to the balance control bracket, an ignition and disconnection control system is arranged on the top of the balance control bracket, and a flame shield is installed between the balance control bracket and the launcher.

[0005] Furthermore, leveling devices are arranged around the base frame, push rod connecting seats connected to the electric control lifting system are respectively arranged at corresponding positions of the base frame and the launching frame, and a lifting seat is arranged on the base frame outside the push rod connecting seat.

[0006] Furthermore, the electric-controlled lifting system includes two sets of electric push rods connecting the base frame and the launcher, a control system installed on the base frame, and an angle detector installed on the launcher.

[0007] Furthermore, indicator dials located near the hinges are arranged on both sides of the base frame, and angle marks are arranged on the indicator dials.

[0008] Furthermore, the sliding guide rail is fixed to the surface of the launch frame through a guide rail mounting frame, and the sliding block on the sliding guide rail is connected to the limiting device.

[0009] Furthermore, the limiting device is composed of a break pin and is connected to the sliding block via a U-shaped connecting plate fixed on the end surface of the guide rail mounting frame. The break pin is provided with a threaded section connected to the sliding block, and a break structure smaller than the diameter of the threaded section is provided between the threaded section and the locking nut.

[0010] Furthermore, the ignition and unplugging control system includes a plugging and unplugging mounting frame fixed across the launching frame and a push rod mounting frame fixed on the plugging and unplugging mounting frame, wherein a push rod and an adjustment frame connected to one side of the push rod are arranged in the push rod mounting frame, and the other end of the push rod is connected to the plugging and unplugging mounting interface via a steel wire rope.

[0011] Compared with the prior art, the utility model has the following beneficial effects:

[0012] 1. Through the electronic control system, a specific opening angle can be set and the ignition control system of the target drone can be synchronized;

[0013] 2. The high-precision slide rail system is configured in three directions to achieve the launch control accuracy of the target drone;

[0014] 3. The launcher and the target drone are connected with an easy-to-fall-off system. After the target drone flies out of the tooling, the limit device will automatically fall off;

[0015] 4. The launcher is equipped with a target drone ignition control system. After the target drone completes the ignition command, the connected aviation plug is automatically retracted. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The utility model is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0017] Figure 1 It is a schematic diagram of the overall structure of the utility model.

[0018] Figure 2 It is an overall schematic diagram of the utility model from another perspective.

[0019] Figure 3 It is a schematic diagram of the utility model in a closed state.

[0020] Figure 4 It is a schematic diagram of the chassis of the utility model.

[0021] Figure 5 It is a schematic diagram of a launching rack of the present utility model.

[0022] Figure 6 For this utility model Figure 5 A partial enlarged view of point A.

[0023] Figure 7 It is a schematic diagram of the breakaway pin of the utility model.

[0024] Figure 8 It is a schematic diagram of the ignition disconnection control system of the utility model.

[0025] In the figure: 1 is a base frame; 11 is a leveling device; 12 is a lifting seat; 13 is a hinge; 14 is an indicator dial; 2 is a launcher; 21 is a target drone mounting slot; 22 is a sliding guide rail; 221 is a guide rail mounting frame; 222 is a sliding block; 23 is a push rod connecting seat; 3 is an electric lifting system; 4 is an ignition and disconnection control system; 41 is a disconnection mounting frame; 42 is a push rod mounting frame; 43 is a push rod; 44 is an adjustment frame; 45 is a wire rope; 46 is a disconnection mounting interface; 5 is a balance control bracket; 6 is a flame baffle; 7 is a limit device; 71 is a break pin; 72 is a connecting plate. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the protection scope of the utility model.

[0027] An embodiment of the utility model, as Figure 1 , Figure 2 and Figure 5 As shown, the launcher 2 and the base frame 1 both adopt a steel frame structure, and the launcher 2 and the base frame 1 are connected by an electric control lifting system 3. Two parallel target drone mounting grooves 21 are installed on the side of the tail of the launcher 2 away from the base frame 1, and a balance control bracket 5 is installed in the target drone mounting groove 21. A sliding guide rail 22 located on the central axis of the two target drone mounting grooves 21 is arranged at the front of the launcher 2, and a limiting device 7 is arranged on the side of the sliding guide rail 22 close to the balance control bracket 5. An ignition and disconnection control system 4 is arranged on the top of the balance control bracket 5, and a flame baffle 6 is installed between the balance control bracket 5 and the launcher 2. The flame baffle 6 is made of carbon fiber phenolic composite laminate and is used to resist the influence of the tail flame of the target drone engine on the electrical mechanism. The launch angle is adjustable and electrically automatically controlled. When meeting the launch of medium and large target missiles, tooling is used for collecting relevant data in the early stage of experiments, which solves the different parameter control required for multiple experiments in the development process of new medium and large target drones, and can meet the operation requirements of different environments.

[0028] like Figure 4As shown, leveling devices 11 are arranged around the base frame 1. The leveling device 11 adopts a screw ejection mechanism to achieve height adjustment of the base frame 1. Push rod connecting seats 23 connected to the electric control lifting system 3 are respectively arranged at the corresponding positions of the base frame 1 and the launching frame 2. A lifting seat 12 is arranged on the base frame 1 outside the push rod connecting seat 23 to meet the installation and fixing problems of different working surfaces.

[0029] The electric-controlled lifting system 3 includes two sets of electric push rods connecting the base frame 1 and the launch frame 2, a control system installed on the base frame 1, and an angle detector installed on the launch frame 2. The angle detector on the balance control bracket 5 detects whether it is adjusted to a horizontal state. A control handle is also installed on the base frame 1 to facilitate real-time adjustment by the staff.

[0030] like Figure 3 As shown, indicator dials 14 are provided on both sides of the chassis 1 near the hinges 13, and angle markings are provided on the indicator dials 14 to facilitate the staff to observe and quickly identify the launch angle in real time.

[0031] like Figure 6 As shown, the sliding guide rail 22 is fixed to the surface of the launch frame 2 through the guide rail mounting frame 221, and the sliding block 222 on the sliding guide rail 22 is connected to the limit device 7. The high-precision sliding guide rail is used to meet the low friction resistance and high positioning accuracy requirements during the target drone launch process. The position deviation between the sliding guide rail 22 and the target drone mounting groove 21 is controlled within 0.5mm to ensure the stability of the target drone launch.

[0032] like Figure 7 As shown, the limit device 7 is composed of a break pin 71, and is connected to the sliding block 222 through a U-shaped connecting plate 72 fixed on the end surface of the guide rail mounting frame 221. A threaded section is provided on the break pin 71 to connect with the sliding block 222, and a break structure smaller than the diameter of the threaded section is provided between the threaded section and the locking nut. An easy-to-break pin is used to connect the target drone and the launch frame, which can control the fixation of the target drone before launch. After the target drone is launched and flies out of the tooling, the limit device 7 automatically falls off. The break pin 71 made of aluminum alloy fixes the target drone engine before it is started, and the thrust breaks the limit device 7 after ignition.

[0033] like Figure 8As shown, the ignition and unplugging control system 4 includes an unplugging mounting frame 41 fixed across the launcher 2 and a push rod mounting frame 42 fixed on the unplugging mounting frame 41, a push rod 43 and an adjustment frame 44 connected to one side of the push rod 43 are arranged in the push rod mounting frame 42, the other end of the push rod 43 is connected to a unplugging mounting interface 46 through a wire rope 45, which is connected to the connecting aviation plug on the target drone before use, a control signal is sent by the control system before use, the push rod 43 performs a contraction action, and the unplugging mounting interface 46 is disconnected from the target drone, the launcher 2 is equipped with a target drone ignition control system, and the connecting aviation plug is automatically retracted after the target drone completes the ignition command.

[0034] Several points that need to be explained are: First, in the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, and can be mechanical or electrical connections, or internal connectivity between two elements, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative position relationships. When the absolute position of the object being described changes, the relative position relationship may change; secondly, in this article, relational terms such as first and second, etc. are only used to distinguish one entity from another, and do not necessarily require or imply that there is any such actual relationship or order between these entities.

[0035] The above examples are merely illustrative of the present utility model and do not constitute a limitation on the protection scope of the present utility model. All designs that are identical or similar to the present utility model fall within the protection scope of the present utility model.

Claims

1. A mechanism for launching a loitering target missile, comprising a base frame (1) and a launching frame (2) connected to the base frame (1) via a hinge (13), characterized in that: The launcher (2) is connected to the base frame (1) via an electric-controlled lifting system (3); two parallel target drone mounting grooves (21) are installed on the rear side of the launcher (2) away from the base frame (1); a balance control bracket (5) is installed in the target drone mounting groove (21); a sliding guide rail (22) located on the central axis of the two target drone mounting grooves (21) is arranged at the front of the launcher (2); a limiting device (7) is arranged on the side of the sliding guide rail (22) close to the balance control bracket (5); an ignition and disconnection control system (4) is arranged on the top of the balance control bracket (5); and a flame shield (6) is installed between the balance control bracket (5) and the launcher (2).

2. A mechanism for launching a loitering target missile according to claim 1, characterized in that: Leveling devices (11) are arranged around the base frame (1), push rod connection seats (23) connected to the electric control lifting system (3) are arranged at corresponding positions of the base frame (1) and the launching frame (2), and a lifting seat (12) is arranged on the base frame (1) outside the push rod connection seat (23).

3. A mechanism for launching a loitering target missile according to claim 2, characterized in that: The electric-controlled lifting system (3) comprises two sets of electric push rods connecting the base frame (1) and the launch frame (2), a control system installed on the base frame (1), and an angle detector installed on the launch frame (2).

4. A mechanism for launching a loitering target missile according to claim 2, characterized in that: Indicator dials (14) located near the hinges (13) are provided on both sides of the base frame (1), and angle markings are provided on the indicator dials (14).

5. A mechanism for launching a loitering target missile according to claim 1, characterized in that: The sliding guide rail (22) is fixed to the surface of the launch frame (2) via a guide rail mounting frame (221), and a sliding block (222) on the sliding guide rail (22) is connected to a limiting device (7).

6. A mechanism for launching a loitering target missile according to claim 5, characterized in that: The limit device (7) is composed of a breaking pin (71) and is connected to the sliding block (222) via a U-shaped connecting plate (72) fixed on the end surface of the guide rail mounting frame (221); a threaded section is provided on the breaking pin (71) and is connected to the sliding block (222); a breaking structure smaller than the diameter of the threaded section is provided between the threaded section and the locking nut.

7. A mechanism for launching a loitering target missile according to claim 1, characterized in that: The ignition plug-in / out control system (4) comprises a plug-in / out mounting frame (41) fixed across the launch frame (2) and a push rod mounting frame (42) fixed on the plug-in / out mounting frame (41); a push rod (43) and an adjustment frame (44) connected to one side of the push rod (43) are arranged in the push rod mounting frame (42); the other end of the push rod (43) is connected to a plug-in / out mounting interface (46) via a steel wire rope (45).

Images