CN112484569A

CN112484569A - Airborne embedded vertical launching device

Info

Publication number: CN112484569A
Application number: CN202011332736.0A
Authority: CN
Inventors: 岳智敏; 王玉浩; 张健
Original assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Current assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date: 2020-11-24
Filing date: 2020-11-24
Publication date: 2021-03-12

Abstract

The application belongs to the technical field of vertical emission, and particularly relates to an airborne embedded vertical emission device. The method comprises the following steps: mounting bracket, gas discharge pipe way, thermal-insulated box and launch controller. A plurality of vertical launching wells arranged in a matrix manner are arranged on the mounting frame, guided missiles are installed in the vertical launching wells, and guided missile launching port covers are arranged at the ends of the vertical launching wells; one end of a gas discharge pipeline is connected with the mounting frame, an internal channel of the gas discharge pipeline is communicated with the vertical launching well, and the other end of the gas discharge pipeline is provided with a flame discharge port cover of the machine body; the heat insulation box body is arranged in the machine body and is used for accommodating the mounting rack, the vertical launching well and the gas discharge pipeline; the launch controller is used for controlling the launching of the missile. After the airplane is assembled to the airplane, the airplane not only retains forward missile attacking capacity, but also has attacking capacity towards the upper part and the lower part of the airplane body, and the attacking and defending capacity of the fighting airplane in short-distance air combat is improved.

Description

Airborne embedded vertical launching device

Technical Field

The application belongs to the technical field of vertical emission, and particularly relates to an airborne embedded vertical emission device.

Background

The combat air-to-air missile is a main short-distance air combat weapon of the current operational aircraft and is influenced by a weapon mounting mode, and the combat air-to-air missile usually adopts a forward-course externally-hung/internally-buried suspension mode. Although advanced combat air-to-air missiles have been provided with large off-axis launch angles, in actual use, to improve the hit rate, a second half-ball launch attack from the target is sought.

With the improvement of the dynamic capability of a novel unmanned/manned combat aircraft in the future, the traditional short-distance combat missile launching mode limits the exertion of the maneuvering and attacking potential of the combat aircraft in short-distance air combat.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

The utility model aims at providing an airborne buries vertical transmitting device to solve at least one problem that prior art exists.

The technical scheme of the application is as follows:

an airborne buried vertical launch device comprising:

the missile launching system comprises a mounting rack, a plurality of vertical launching wells and a missile launching port cover, wherein the vertical launching wells are arranged on the mounting rack in a matrix arrangement mode, missiles are installed in the vertical launching wells, and the end parts of the vertical launching wells are provided with the missile launching port cover;

one end of the gas discharge pipeline is connected with the mounting frame, an internal channel of the gas discharge pipeline is communicated with the vertical launching well, and a flame discharge port cover of the machine body is arranged at the other end of the gas discharge pipeline;

the heat insulation box body is arranged in the machine body and is used for accommodating the mounting rack, the vertical launching well and the gas discharge pipeline;

a launch controller for controlling launching of the missile.

Optionally, the missile is a small combat missile or a tip intercept missile.

Optionally, guide rails are symmetrically arranged on the inner side wall of the vertical launching well along the vertical direction, and the guide rails are used for fixedly hanging the guided missile.

Optionally, both ends of the missile launching port cover in the direction perpendicular to the heading direction are provided with saw-tooth structures.

Optionally, both ends of the fuselage exhaust port cover in the direction perpendicular to the heading direction are provided with saw-tooth structures.

Optionally, the airborne embedded vertical transmitting devices are respectively arranged at the front position of the back of the airplane body, the front position of the abdomen of the airplane body and the rear position of the abdomen of the airplane body.

The invention has at least the following beneficial technical effects:

after the airborne embedded vertical launching device is assembled to an airplane, the airplane not only retains the forward missile attacking capacity, but also has the attacking capacity towards the upper part and the lower part of the airplane body, and the attacking and defending capacity of the combat airplane in short-distance air combat is improved.

Drawings

FIG. 1 is a schematic view of an airborne buried vertical launch device according to an embodiment of the present application;

fig. 2 is a schematic illustration of a combat aircraft according to an embodiment of the present application.

Wherein:

1-vertical launching well; 2-missile launching port cover; 3-a gas discharge pipeline; 4-fuselage exhaust flap.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1-2.

The application provides an airborne embedded vertical transmitting device, includes: mounting bracket, gas discharge pipe 3, thermal-insulated box and launch controller.

Specifically, as shown in fig. 1, a plurality of vertical launching wells 1 are arranged on a mounting rack in a matrix arrangement, missiles are installed in the vertical launching wells 1, and missile launching port covers 2 are arranged at the end parts of the vertical launching wells 1; one end of a gas discharge pipeline 3 is connected with the mounting frame, an internal channel of the gas discharge pipeline 3 is communicated with the vertical launching well 1, and a machine body flame exhaust port cover 4 is arranged at the other end of the gas discharge pipeline 3; the heat insulation box body is arranged in the machine body and is used for accommodating the mounting frame, the vertical launching well 1 and the fuel gas discharge pipeline 3; the launching controller is used for controlling launching of the missile according to the received target information of the helmet display aiming system and the onboard DAS system.

According to the airborne embedded vertical launching device, the vertical launching wells 1 are arranged in a matrix manner, and the installed guided missiles can be small combat guided missiles or tail-end intercepting guided missiles. In this embodiment, the vertical launching wells 1 provided with 4 × 6 units are provided, and the guided rails are symmetrically arranged on the inner side walls of the vertical launching wells 1 along the vertical direction, so that the guided missiles are fixedly hung on the guided rails.

The utility model provides a machine carries and buries vertical launcher in, 4 equipartitions of guided missile launching port lid 2 and fuselage row's flame mouth lid are arranged on the aircraft skin, can open under hydraulic actuator's control, and the cooperation launch controller realizes the transmission and the row's flame of guided missile. Advantageously, in this embodiment, the missile launching port cover 2 and the fuselage exhaust port cover 4 are designed with sawtooth structures at two ends in a direction perpendicular to the heading direction, so as to improve the stealth effect.

The airborne embedded vertical transmitting device is arranged on an airplane according to the operational requirements. In this embodiment, the airborne embedded vertical transmitting device is respectively arranged at the front position of the back of the airplane body, the front position of the abdomen of the airplane body and the rear position of the abdomen of the airplane body.

The utility model provides a machine carries and buries perpendicular emitter, but mounting bracket, gas discharge pipe 3 and thermal-insulated box integrated into one piece, be convenient for maintain or the dismouting is changed. The missile vertical launching wells 1 are combined into an embedded vertical missile launching module, each vertical launching well 1 can contain a small combat missile or a tail end interception missile, the missile adopts a thermal launching mode, the bottom of the launching module is provided with a gas discharge pipeline 3, and a missile launching port and a gas discharge port are provided with cover plates with stealth design. When the combat aircraft fights with the enemy plane, the sighting system is linked with the airborne DAS system through the helmet display of the pilot. When the missile enters a combat air war, the missile launching port cover 2 is turned left and right to be opened, the launching controller automatically selects one or more missiles to be launched to enable the missiles to enter a to-be-launched state, the missiles are linked with a helmet aiming system and an airborne DAS system of a pilot, the missile infrared imaging seeker captures a target under the guidance of the missile infrared imaging seeker, the missiles are automatically launched, the missiles are ignited in the vertical launching wells 1, and generated tail flames enter the inner channel of the gas emission pipeline 3 and are discharged through the body flame emission port cover 4. The vertical launching well 1 of the missile is arranged in the heat insulation box body so as to avoid the influence of high temperature on the structure and equipment in the missile. Advantageously, the outer side of the fuselage exhaust flame vent cover 4 is also provided with a thermal insulation material to avoid high temperatures affecting the external structure.

The utility model provides a perpendicular emitter is buried in machine carries, see figure 2, assemble behind the aircraft of fighting for the attack and the defense area of aircraft of fighting in the short distance air battle increase by a wide margin, expand to only have a little dead angle in the back by preceding hemisphere. When the missile is in circling combat with an enemy plane, the missile can be launched from the back or the abdomen accidentally, and the air war winning is improved. And moreover, the air-to-air missile launched by an enemy can be subjected to independent and effective implementation of terminal interception, and the viability of close-range air battles is greatly improved. For large aerial platforms with poor maneuverability, the airborne embedded vertical launching device can also provide an effective end defense means.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An airborne embedded vertical transmitting device, comprising:

the missile launching system comprises a mounting rack, wherein a plurality of vertical launching wells (1) are arranged on the mounting rack in a matrix arrangement mode, missiles are installed in the vertical launching wells (1), and missile launching port covers (2) are arranged at the ends of the vertical launching wells (1);

one end of the gas discharge pipeline (3) is connected with the mounting frame, an internal channel of the gas discharge pipeline (3) is communicated with the vertical launching well (1), and the other end of the gas discharge pipeline (3) is provided with a flame discharge port cover (4);

a heat insulation box body mounted in the machine body for accommodating the mounting frame, the vertical launching well (1) and the gas discharge pipeline (3);

a launch controller for controlling launching of the missile.

2. The airborne buried vertical launch device of claim 1 wherein the missile is a small combat missile or a tip intercept missile.

3. The airborne buried vertical launching device according to claim 2, characterized in that the vertical launching shaft (1) has guide rails symmetrically arranged on its inner side wall in the vertical direction, and the guide rails are used for fixing the hitched missile.

4. The airborne buried vertical launching device according to claim 1, characterized in that the missile launch port cover (2) is provided with a saw-tooth structure at both ends in the direction perpendicular to the heading.

5. The airborne buried vertical emission device of claim 1, characterized in that the fuselage exhaust port cover (4) is provided with a saw-tooth structure at both ends in a direction perpendicular to the heading direction.

6. The on-board embedded vertical transmitting device of claim 1, wherein the on-board embedded vertical transmitting device is disposed at a front position on the back of the aircraft body, at a front position on the abdomen of the aircraft body, and at a rear position on the abdomen of the aircraft body.