Long-endurance small air-to-air missile with variable aerodynamic configuration

Abstract

The invention discloses a long-endurance small air-to-air missile with a variable aerodynamic configuration, which belongs to the technical field of air-to-air missiles and comprises a first-stage booster, a second-stage missile and a main wing. The first-stage booster is arranged at the rear end of the second-stage missile, and a first explosive bolt is arranged between the first-stage booster and the second-stage missile; the main wings are symmetrically arranged on the two sides of the secondary missile; after the air-to-air missile is launched by a carrier aircraft, the main wings are used for changing from a folded state to an unfolded state in the launching process, and meanwhile, the first-stage booster is ignited to provide main lift force for the air-to-air missile; when the air-to-air missile finds and locks a target, the main wings are separated from the two sides of the second-stage missile, meanwhile, the first explosive bolts explode so that the first-stage booster can be separated from the second-stage missile, and the second-stage missile continues to fly to the target to complete a task. The cruise duration of the missile is prolonged through the variable aerodynamic configuration and the small turbojet engine, and therefore the range of the air-to-air missile is increased.

Description

Technical Field

[0001] The invention belongs to the technical field of air-to-air missiles, and more specifically, relates to a small air-to-air missile with a long-flight variable aerodynamic shape. Background Art

[0002] The contest of air power is an important part of modern warfare, and air-to-air missiles are the main weapons and equipment for gaining air superiority. Air-to-air missiles continue to develop with the changes in war requirements and the progress of science and technology.

[0003] Existing air-to-air missiles are mainly divided into close-range combat, medium-range interception and long-range types. Close-range combat types usually have a short range and focus more on the missile's maneuverability, rapid response, size and weight, etc.; medium-range and long-range types focus more on the missile's launch distance, have higher requirements on the missile's power performance, are generally larger in size and mass, and are more expensive.

[0004] Therefore, it is urgent to design an air-to-air missile that can simultaneously meet the high maneuverability of close-range combat air-to-air missiles and the launch distance of medium- and long-range air-to-air missiles, and has a low cost. Summary of the invention

[0005] In view of the above defects or improvement needs of the prior art, the present invention provides a small air-to-air missile with a long flight time and a variable aerodynamic shape, thereby solving the technical problem that the air-to-air missiles in the prior art cannot perform short, medium and long-range missions.

[0006] To achieve the above object, according to one aspect of the present invention, there is provided a small air-to-air missile with a long-flight variable aerodynamic shape, comprising: a first-stage booster, a second-stage missile and a main wing;

[0007] The first-stage booster is arranged at the rear end of the second-stage missile, and a first explosive bolt is arranged between the first-stage booster and the second-stage missile;

[0008] The secondary missile comprises a main wing compartment, and the main wings are symmetrically arranged on both sides of the main wing compartment;

[0009] The main wing cabin comprises a cabin body and an unfolding and separating mechanism, wherein the unfolding and separating mechanism is fixedly arranged on both sides of the cabin body;

[0010] When in cruising state, the main wing is used to change from a folded state to an unfolded state under the drive of the unfolding and separation structure, and at the same time the first-stage booster is ignited to provide main lift for the air-to-air missile; when in combat state, the main wing is separated from both sides of the second-stage missile under the drive of the unfolding and separation mechanism, and at the same time the first explosive bolt explodes to separate the first-stage booster from the second-stage missile, and the second-stage missile continues to fly towards the target to complete the mission.

[0011] Preferably, the first-stage booster includes a fuel tank, a turbojet engine, an air inlet and a tail fin; the fuel tank is arranged at one end of the turbojet engine for providing fuel to the turbojet engine; the air inlet is arranged at the bottom of the turbojet engine; and the tail fin is arranged at the tail of the turbojet engine.

[0012] Preferably, the tail fins are provided with four pieces, and the four tail fins are arranged around the tail of the first-stage booster.

[0013] Preferably, the second-stage missile includes an infrared imaging seeker, a control cabin, a ignition cabin, a main wing cabin, a solid rocket engine and an electric servo connected in sequence; the control cabin is equipped with an onboard computer for controlling the separation of the first-stage booster from the main wing; the solid rocket engine is used to provide flight power for the second-stage missile in an air-to-air missile combat state and to provide driving force during the separation of the first-stage booster.

[0014] Preferably, the second-stage missile also includes a front wing and a lifting lug, wherein the front wing is arranged around the outside of the control cabin; two lifting lugs are provided, and the two lifting lugs are respectively located at the upper end of the ignition cabin and the solid rocket engine.

[0015] Preferably, the unfolding and separation structure includes a second explosive bolt, a rotating shaft, a mounting seat, a limiting plate, a nut, a block and a spiral spring; the rotating shaft is arranged in a through hole in the middle of the mounting seat, the blocks are installed on both sides of the mounting seat, and the blocks are located in the annular groove of the rotating shaft, and are used to limit the rotating shaft; the second explosive bolt passes through the hole in the middle of the rotating shaft and is fastened by the limiting plate and the nut; a cavity is provided at the bottom of the mounting seat, and the spiral spring is arranged between the cavity and the rotating shaft, and the spiral spring is used to drive the rotating shaft and drive the second explosive bolt and the main wing to rotate.

[0016] Preferably, the main wing compartment further comprises a limiting boss, which is arranged at one side of the connection between the main wing and the compartment body and is used to limit the deployment angle of the main wing.

[0017] In general, the above technical solutions conceived by the present invention can achieve the following beneficial effects compared with the prior art:

[0018] 1. The small air-to-air missile with a long-flight and variable aerodynamic shape proposed by the present invention has main wings arranged on both sides of the secondary missile. The main wings change from a folded state to an unfolded state after the air-to-air missile is dropped by a carrier aircraft, and are separated from both sides of the secondary missile after the air-to-air missile finds and locks a target, so that the air-to-air missile has a variable aerodynamic shape. After being dropped by a carrier aircraft, the air-to-air missile first flies a long distance in a cruising state, and then changes to a combat mode with high maneuverability after arriving at a designated area, and has a high energy utilization rate.

[0019] 2. The small air-to-air missile with a long flight time and a variable aerodynamic shape proposed by the present invention realizes an organic combination of the long-range flight and maneuverability of the air-to-air missile within a limited size by providing a detachable first-stage booster and a main wing.

[0020] 3. The small air-to-air missile with long flight time and variable aerodynamic shape proposed by the present invention has higher maneuverability than cruise missiles of the same level and higher range than traditional air-to-air missiles of the same level, but at the same cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the launch of a small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0022] Figure 2 It is a structural schematic diagram of a small air-to-air missile with a long-flight variable aerodynamic shape in a launching state according to the present invention;

[0023] Figure 3 It is a structural schematic diagram of a small air-to-air missile with a long-flight variable aerodynamic shape in a cruising state according to the present invention;

[0024] Figure 4 It is a structural schematic diagram of a secondary missile of a small air-to-air missile with a long-flight variable aerodynamic shape in a combat state according to the present invention;

[0025] Figure 5 It is a structural top view of a small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0026] Figure 6 It is a structural front view of a small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0027] Figure 7 It is a structural left view of a small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0028] Figure 8 It is a schematic diagram of the operation of the main wing compartment in a small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0029] Fig. 9 It is a structural schematic diagram of the main wing compartment in a small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0030] Fig.10 It is a structural schematic diagram of the deployment and separation mechanism of the small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0031] Fig.11 It is a structural schematic diagram of the deployment and separation mechanism of the small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0032] Fig.12It is a bottom schematic diagram of the deployment and separation mechanism in the small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0033] Fig.13 It is a structural schematic diagram of a mounting seat in a small air-to-air missile with a long-flight variable aerodynamic shape according to the present invention;

[0034] Fig.14 The present invention is a schematic structural diagram of a rotating shaft of a small air-to-air missile with a long-flight variable aerodynamic shape.

[0035] In all the drawings, the same reference numerals are used to represent the same elements or structures, among which: 1-first stage booster; 11-fuel tank; 12-turbojet engine; 13-air inlet; 14-tail; 2-second stage missile; 21-infrared imaging guidance head; 22-control cabin; 23-ignition cabin; 24-main wing cabin; 241-cabin body; 242-limiting boss; 243-deployment and separation mechanism; 2431-second explosive bolt; 2432-rotating shaft; 2433-mounting seat; 2434-limiting plate; 2435-nut; 2436-block; 2437-volute spring; 244-gasket; 245-second nut; 25-solid rocket engine; 26-electric servo; 27-front wing; 28-lifting ear; 3-main wing; 4-first explosive bolt. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0037] like Figure 1-Figure 4 As shown, the present invention proposes a small air-to-air missile with a long flight time and a variable aerodynamic shape. The air-to-air missile is launched by a carrier aircraft and has three working states, namely: a launching state, a cruising state and a combat state.

[0038] Specifically, the air-to-air missile is composed of a first-stage booster 1, a second-stage missile 2 and a main wing 3 (two pieces). When the air-to-air missile is dropped by a carrier aircraft, the folded main wing 3 is automatically unfolded to provide the main lift for the missile. After being dropped, the air-to-air missile in a cruising state cruises for a long time under the action of the first-stage booster 1.

[0039] Further explanation, after reaching the designated area or locking the target, under the command given by the secondary missile 2, the unfolded main wing 3 separates and falls off; at the same time, the first explosive bolt 4 connecting the first stage booster 1 and the second stage missile 2 works, and the first stage booster 1 that is physically connected is automatically separated. The air-to-air missile is transformed from the aerodynamic shape of the cruise state to the aerodynamic shape of the combat state.

[0040] To further explain, the solid rocket engine of the second-stage missile 2 in the combat state ignites and autonomously flies to the target and destroys the target.

[0041] One embodiment of the present invention provides a small air-to-air missile with a long flight time and a variable aerodynamic shape, such as Figure 5-Figure 7 As shown, the first-stage booster 1 is composed of a fuel tank 11, a small turbojet engine 12, an air inlet 13 and a tail wing 14, which provides power for the long-term cruise of the air-to-air missile.

[0042] Further explanation, the secondary missile 2 is a normal aerodynamic layout of "XX", consisting of an infrared imaging seeker 21, a control cabin 22, a ignition cabin 23, a main wing cabin 24, a solid rocket engine 25, and an electric servo 26. The control cabin 22 is equipped with an onboard computer to realize the separation control of the first-stage booster 1 and the main wing 3, as well as the flight control of the air-to-air missile. The solid rocket engine 25 provides flight power for the second-stage missile 2 in the combat state, and provides driving force for its separation after the first-stage booster 1 is physically disconnected.

[0043] To further explain, the main wing 3 provides the main lift for the air-to-air missile during the cruising phase, and can be automatically unfolded from a folded state under the action of the main wing cabin 24; after receiving the separation signal from the control cabin 22, the connection can be released and the wing can be separated and fallen off under the action of aerodynamic force.

[0044] One embodiment of the present invention provides a small air-to-air missile with a long flight time and a variable aerodynamic shape, such as Figure 8-Figure 12 As shown, the main wing compartment 24 is composed of a compartment 241, a limiting boss 242 and an unfolding separation mechanism 243. The unfolding separation mechanism 243 is installed on both sides of the compartment 241 and fastened by countersunk screws. The main wing 3 passes through the second explosive bolt 2431, and the main wing 3 is fastened to the rotating shaft 2432 through the gasket 244 and the second nut 245, and the main wing 3 rotates with the rotating shaft 2432. After the main wing 3 rotates to the designed angle, the end face fits with the limiting boss 242 to achieve the main wing unfolding angle limit.

[0045] Further explanation, the unfolding and separating mechanism 243 is composed of a second explosive bolt 2431, a rotating shaft 2432, a mounting seat 2433, a limiting plate 2434, a nut 2435, a clamping block 2436, and a spiral spring 2437. The rotating shaft 2432 passes through the through hole in the middle of the mounting seat 2433, and the clamping blocks 2436 are installed on both sides of the mounting seat 2433. The clamping blocks extend into the annular groove of the rotating shaft 2432 to limit the rotating shaft 2432. The clamping block 2436 is fastened to the mounting seat 2433 by screws. The second explosive bolt 2431 passes through the hole in the middle of the rotating shaft 2432 and is fastened by the nut 2435. Through the above design, the rotating shaft 2432 together with the second explosive bolt 2431 only has the freedom to rotate along the axial direction in the mounting seat 2433.

[0046] Further explanation, the bottom of the mounting seat 2433 is designed with a cavity, and the volute spring 2437 is installed between the cavity and the rotating shaft 2432, and the volute spring 2437 drives the rotating shaft 2432 to drive the second explosive bolt 2431 and the main wing 3 to rotate. The inner ear of the volute spring 2437 is installed in the groove of the rotating shaft 2432, and the outer ear is installed in the groove of the mounting seat 2433.

[0047] To further explain, after the second explosive bolt 2431 receives the separation signal from the control cabin 22, the second explosive bolt 2431 breaks off at the contact plane with the rotating shaft 2432, and the main wing 3 connected to the rotating shaft 2432 by the second explosive bolt 2431 loses its constraint and automatically separates and falls off under the action of aerodynamic force.

[0048] The workflow of one embodiment of the present invention is as follows:

[0049] After the carrier aircraft arrives at the designated area, it sets the parameters of the air-to-air missile and launches the missile. After the air-to-air missile is launched, the main wing that is retracted forward automatically unfolds under the action of the unfolding and separation mechanism; at the same time, the onboard computer in the control cabin ignites the small turbojet engine of the first-stage booster, and the air-to-air missile cruises at a certain speed (about 0.8Ma).

[0050] When the infrared imaging seeker finds and locks the target, the onboard computer in the control cabin gives a main wing release signal, and the deployment and separation mechanism in the main wing cabin releases the mechanical connection to the main wing, and the main wing separates and falls off; at the same time, the onboard computer gives a first-stage booster separation signal, and the explosive bolts connecting the first-stage booster and the second-stage missile ignite, and the mechanical connection of the first-stage booster is unlocked; then the second-stage missile ignition signal is given, the solid rocket engine ignites, and the first-stage booster that loses the mechanical connection quickly separates under the action of the solid rocket engine airflow. The second-stage missile continues to fly towards the target in a combat state and completes the combat mission.

[0051] At this point, the air-to-air missile provided by the present invention has completed the process of changing its aerodynamic shape and achieved the transition from long-distance cruising to a high-maneuverability combat state.

[0052] It will be easily understood by those skilled in the art that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A small air-to-air missile with a long flight time and variable aerodynamic shape, characterized in that: include: The first stage booster (1), the second stage missile (2) and the main wing (3); The first-stage booster (1) is arranged at the rear end of the second-stage missile (2), and a first explosive bolt (4) is arranged between the first-stage booster (1) and the second-stage missile (2); The secondary missile (2) comprises a main wing compartment (24), and the main wing (3) is symmetrically arranged on both sides of the main wing compartment (24); The main wing cabin (24) comprises a cabin body (241) and an unfolding and separating mechanism (243), wherein the unfolding and separating mechanism (243) is fixedly arranged on both sides of the cabin body (241); When in the cruising state, the main wing (3) is used to change from a folded state to an unfolded state under the drive of the unfolding and separating structure (243), and at the same time, the first-stage booster (1) is ignited to provide the main lift for the air-to-air missile; when in the combat state, the main wing (3) is driven by the unfolding and separating mechanism (243) to separate from both sides of the second-stage missile (2), and at the same time, the first explosive bolt (4) explodes to separate the first-stage booster (1) from the second-stage missile (2), and the second-stage missile (2) continues to fly towards the target to complete the mission.

2. A small air-to-air missile with a long-flight variable aerodynamic shape according to claim 1, characterized in that: The first-stage booster (1) comprises a fuel tank (11), a turbojet engine (12), an air inlet (13) and a tail wing (14); the fuel tank (11) is arranged at one end of the turbojet engine (12) and is used to provide fuel to the turbojet engine (12); the air inlet (13) is arranged at the bottom of the turbojet engine (12); and the tail wing (14) is arranged at the tail of the turbojet engine (12).

3. A small air-to-air missile with a long flight time and a variable aerodynamic shape according to claim 2, characterized in that: The tail fins (14) are provided with four pieces, and the four tail fins are arranged around the tail of the first-stage booster (1).

4. A small air-to-air missile with a long flight time and a variable aerodynamic shape according to claim 1, characterized in that: The second-stage missile (2) comprises an infrared imaging seeker (21), a control cabin (22), a ignition cabin (23), a main wing cabin (24), a solid rocket engine (25) and an electric servo (26) which are connected in sequence; an onboard computer is installed in the control cabin (22) for controlling the separation of the first-stage booster (1) from the main wing (3); the solid rocket engine (25) is used to provide flight power for the second-stage missile (2) in an air-to-air missile combat state and to provide driving force during the separation process of the first-stage booster (1).

5. A small air-to-air missile with a long flight time and a variable aerodynamic shape according to claim 4, characterized in that: The two-stage missile (2) further comprises a front wing (27) and a lifting lug (28), wherein the front wing (27) is arranged around the outside of the control cabin (22); and two lifting lugs (28) are provided, and the two lifting lugs are respectively located at the upper ends of the ignition cabin (23) and the solid rocket engine (25).

6. A small air-to-air missile with a long flight time and a variable aerodynamic shape according to claim 5, characterized in that: The unfolding and separating structure (243) comprises a second explosive bolt (2431), a rotating shaft (2432), a mounting seat (2433), a limiting plate (2434), a nut (2435), a clamping block (2436) and a volute spring (2437); the rotating shaft (2432) is arranged in a through hole in the middle of the mounting seat (2433), the clamping block (2436) is installed on both sides of the mounting seat (2433), and the clamping block (2436) is located in an annular groove of the rotating shaft (2432) for clamping the rotating shaft (2432) The rotating shaft (2432) is limited; the second explosive bolt (2431) passes through the hole in the middle of the rotating shaft (2432) and is fastened by the limiting plate (2434) and the nut (2435); a cavity is provided at the bottom of the mounting seat (2433), and the volute spring (2437) is arranged between the cavity and the rotating shaft (2432), and the volute spring (2437) is used to drive the rotating shaft (2432) and drive the second explosive bolt (2431) and the main wing (3) to rotate.

7. A small air-to-air missile with a long flight time and a variable aerodynamic shape according to claim 6, characterized in that: The main wing compartment (24) further comprises a limiting boss (242), wherein the limiting boss (242) is arranged on one side of the connection between the main wing (3) and the compartment body (241) and is used to limit the unfolding angle of the main wing (3).

Images