An initial turning separation device for vertically launched missiles

Abstract

An initial turning and separation device for vertically launched missiles is disclosed. This device is suitable for vertically launched cold-launched missiles. After launch, the attitude control pulse device group and the radome separation device group inside the separation radome ignite sequentially to generate an initial attitude adjustment and turning separation torque, propelling the missile to a predetermined position to complete the initial turn, and then unlocking and separating the radome. The device includes a roll device, an elevation device, a separation device, and a separation radome. This device can be applied to vertically launched cold-launched missiles of various sizes. The distribution of the attitude control pulse device group and the separation device group is flexibly designed according to the missile's radome structure, resulting in a compact layout that fully utilizes the space at the missile's head, achieving complementary spatial structures without occupying the missile's axial space. The integrated design of the device's nozzle and the separation radome reduces the mass of the connecting structure and improves the device's mass-to-impulse ratio. This enables the missile to quickly complete a vertical turn and radome separation after cold launch, effectively enhancing missile maneuverability.

Description

Technical Field

[0001] The invention relates to an initial turning separation device for a vertically launched missile, belonging to the technical field of attitude and orbit control of solid rocket devices. Background Art

[0002] With the rapid development of the new generation of offensive and defensive confrontation technologies, a new combat mode of multi-batch, all-round, rapid and continuous attacks has been formed.

[0003] The conventional inclined launch method has a complicated launch device, which seriously restricts the stealth performance. The vertical launch missile has a short reaction time, rapid fire transfer, can realize all-round air defense operations, simple launch device structure, large missile load, and good stealth performance. In addition, although the conventional lateral force engine can realize the function of vertical launch and turning, the lateral force attitude control pulse engine has a complex structure, a large number, poor stability, and occupies more axial length and missiles.

[0004] Therefore, how to achieve vertical launch without affecting the amount of charge and increasing the axial length, so that the missile can turn to the designated direction of the target after vertical launch and smoothly separate the separation head cover from the missile body without affecting the subsequent flight of the missile, is a problem that needs to be solved. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and provide a device suitable for vertical launch, a multi-diameter and wide-range engine with initial turning capability, so as to achieve vertical launch without affecting the charge amount and increasing the axial length, so as to achieve the goal of turning the missile to the designated direction of the target after vertical launch, and smoothly separating the separation head cover from the missile body without affecting the subsequent flight of the missile.

[0006] The technical solution of the present invention is:

[0007] A separation device for initial turning of vertically launched missiles, the structure of which includes: a separation hood 1, a rolling device 2, a pitching device 3, and a separation device 4. Among them, the rolling device 2, the pitching device 3, and the separation device 4 are inside the separation hood 1. The rolling device 2 is distributed along the plane of the missile diameter, generates thrust in the tangential direction of the missile body, ensures the rolling movement of the engine, and the rolling device 2 is connected and fastened with the separation hood 1 by screws; the pitching device 3 is distributed along the plane of the missile diameter, generates thrust in the pitch direction of the missile, ensures the pitch movement of the engine, and the pitching device 3 is connected and fastened with the separation hood 1 by screws; the separation device 4 is distributed along the axial direction, generates a backward thrust along a certain angle of the missile body, ensures the separation hood 1 is separated from the missile body, and the separation device 4 is connected and fastened with the separation hood 1 by screws, and the separation hood 1 is connected with the missile body by mature technology product devices such as explosive bolts and cutting locks, so as to form a separation device that can adjust the missile posture as a whole.

[0008] The rolling device 2 can provide thrust in two opposite directions tangential to the circumference of the missile body. It generally exists in pairs and is symmetrically distributed on the inner wall of the separation head cover 1. Its structure includes two charge combustion chambers, two oblique nozzles, two plugging covers and other sealing structures. Two openings of a size matching the outlet of the oblique nozzle are opened on the separation head cover 1, so that the gas is ejected from the oblique nozzle outlet to generate thrust. The thrust acts on the separation head cover 1, and the torque generated by the head cover drives the missile body to roll. The charge amount of the charge combustion chamber is adjusted according to the working time, thrust and total impulse requirements required by missiles with different diameters and functions to adapt to various types of missiles.

[0009] The pitch device 3 can provide thrust along the projectile diameter direction. It generally exists in pairs and is symmetrically distributed on the inner wall of the separation head cover 1. Its structure includes a charge combustion chamber, a nozzle, a plug cover, and a connection seal. Two openings of a size matching the nozzle opening of the pitch device 3 are opened on the separation head cover 1, so that the gas is ejected from the nozzle opening to generate thrust along the projectile diameter direction. The thrust generates a torque and acts on the head cover to drive the projectile to pitch. Similarly, the pitch device 3 can design the structure and charge amount of the charge combustion chamber according to the requirements of different types of projectile diameters to meet the requirements of the projectile pitch deflection angle.

[0010] The separation device 4 can provide thrust at a certain angle along the axial direction of the projectile. It generally exists in pairs and is symmetrically distributed on the inner wall of the separation head cover. Its structure includes a charge combustion chamber, an oblique nozzle, a plug cover and a connection seal. Two openings of a size matching the oblique nozzle opening of the separation device 1 are opened on the separation head cover, so that the gas is ejected from the nozzle opening to generate a thrust component along the axial direction of the projectile diameter, so that the entire separation head cover 1 is separated from the projectile body. Similarly, the separation device 4 can also design the structure and charge amount of the charge combustion chamber according to the requirements of different types of projectile diameters to meet the requirements of the pitch and deflection angle of the projectile body.

[0011] Furthermore, the material of the separation head cover 1 can be a fiber-reinforced composite molded part, which can greatly reduce the mass of the projectile body and reduce the difficulty of separation. At the same time, the lightweight and high-strength composite material can effectively ensure the structural integrity of its internal attitude control device and effectively transmit the thrust.

[0012] Furthermore, a heat protection coating is bonded to the outer wall surface of the separation head cover 1.

[0013] Furthermore, the combustion chambers of the rolling device 2, the pitching device 3, and the separation device 4 all use high-burning-rate solid propellants, which are safe, non-toxic, easy to use, and long-lasting.

[0014] Furthermore, the combustion chamber distribution direction of the rolling device 2 can be adjusted to be along the diameter direction or along the axial direction according to the spatial distribution of the separation head cover 1 and the antenna cover.

[0015] Furthermore, the nozzle outlet of the rolling device 2 extends out and is clamped on the shell of the separation head cover 1 for circumferential positioning, and the screw fixing position is in the middle of the two nozzles for restraint and positioning.

[0016] Furthermore, the combustion chamber of the pitch device 3 is relatively large and is distributed near the bottom of the separation head cover 1 .

[0017] Furthermore, the rolling device 2 and the pitching device 3 can be distributed on the same horizontal plane, or on different planes, and can be appropriately adjusted depending on the spatial distribution in the hood.

[0018] Furthermore, the charge amounts of the two combustion chambers of the separation device 4 are adjusted, and the separation device 4 is controlled to generate two different thrusts and working times respectively, so as to ensure that when the hood is separated, under the action of different separation thrusts, the gravity of the hood is offset during the separation process, and the hood is detached from the antenna cover along the straight line direction of the bullet diameter.

[0019] Furthermore, according to the turning angle and direction requirements of the missile after launch, the two obliquely opposite combustion chambers of the rolling device 2 are ignited and opened for use at the same time, only one combustion chamber of the pitch device 3 is opened at a time to work independently, and the two combustion chambers of the separation device 4 are ignited and work at the same time. The rolling device 2 and the pitch device 3 can work simultaneously or intermittently, and the separation device 4 works subsequently.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] (1) The present invention realizes vertical launch without affecting the charge amount and increasing the axial length, so that the missile can turn to the designated direction of the target after vertical launch, and the separation head cover can be separated from the missile body smoothly without affecting the subsequent flight of the missile.

[0022] (2) The separation device of the present invention is located at the top of the missile, does not occupy axial space, and is farthest from the center of mass of the missile. It can generate a large torque with a small power to achieve missile attitude adjustment.

[0023] (3) The separation device of the present invention has strong adaptability and can be applied to vertically launched missiles of various ranges and diameters. It also has good designability and can adjust the distribution angle and position of the rolling device, the pitching device and the separation device according to needs to meet the initial turning requirements of various missiles.

[0024] (4) The device of the present invention can be applied to vertical cold ejection projectiles of various sizes. According to the structural shape of the missile radome, the distribution positions of the attitude control pulse device group and the separation device group can be flexibly designed. The device group has a compact layout, which makes full use of the natural space of the missile radome head to achieve efficient complementarity of the spatial structure without occupying the axial space of the missile body. By adopting an integrated design of the device nozzle and the separation hood, the mass of the connection structure is reduced and the mass-to-impulse ratio of the device is improved. The missile can complete a vertical rapid turn and hood separation within 2-3 seconds after cold ejection, effectively enhancing the maneuverability of the missile. It is easy to install and simple to maintain, realizing low-cost technology transformation. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a structural outline diagram of an initial turning separation device for vertically launched missiles;

[0026] Figure 2 It is the working principle diagram of the pitch device 3;

[0027] Figure 3 It is the working principle diagram of the rolling device 2;

[0028] Figure 4 It is the working principle diagram of the separation device 4. DETAILED DESCRIPTION

[0029] The specific embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0030] The present invention provides an initial turning separation device for a vertically launched missile, which is suitable for a vertical cold ejection missile after launch. The device generates a torque for adjusting the initial attitude of the missile and a turning separation torque by igniting an attitude control pulse device group and a hood jettisoning separation device group inside the hood in sequence, so as to send the missile to a predetermined position to complete the initial turning, and unlock and separate the hood.

[0031] The present invention proposes an initial turning separation device for vertically launching a missile, and specifically solves the following problems:

[0032] 1. The missile needs to be able to turn and adjust its attitude after vertical launch;

[0033] Second, the device that realizes the attitude control function occupies the missile charge space, affecting the missile's mass-to-impulse ratio;

[0034] 3. There are many types of vertical launch missiles, such as range and diameter, and there is an urgent need for vertical turning functions, requiring the turning device to be highly universal;

[0035] 4. The turning device has a simple structure, strong designability, and meets the missile's requirements for attitude adjustment and control;

[0036] Fifth, the device must be safe, harmless, easy to use, and durable. The above problems are common in all types of vertical launch engines and need to be solved urgently.

[0037] like Figure 1 As shown, the present invention proposes an initial turning separation device for a vertically launched missile, comprising a separation hood 1, a rolling device 2, a pitching device 3 and a separation device 4, wherein the rolling device 2, the pitching device 3 and the separation device 4 are inside the separation hood 1.

[0038] The assembly sequence of the structural model given in this example should be: first, place the pitch device 3 symmetrically distributed along the 0° direction of the missile diameter plane, and connect and fasten it to the separation head cover 1 through external screws; then install the roll device 2 at the specified position, and connect and fasten it to the separation head cover 1 through screws. In the example, the roll device 2 and the pitch device are at the same 0° position; finally, install the separation device 4 at 90°, and connect and fasten it to the separation head cover 1 from the outside through screws; the separation head cover 1 is connected to the missile body through mature technology product devices such as explosive bolts and cutting locks, forming a separation device that can adjust the missile posture as a whole.

[0039] The rolling device 2, the pitching device 3, and the separation device 4 are distributed in the separation hood 1. The distribution direction of the combustion chamber of the rolling device 2 and the pitching device 3 can be adjusted according to the space size between the antenna cover and the separation hood 1 to avoid interference with the antenna cover inside the separation hood 1.

[0040] The rolling device 2 and the pitching device 3 are distributed in the radial direction of the missile and along the wall of the separation head cover 1, and the separation device 4 is distributed in the axial direction of the missile.

[0041] like Figure 3 As shown, the rolling device 2 in the example can provide thrust in two opposite directions tangential to the circumference of the missile body. It generally exists in pairs and is symmetrically distributed on the inner wall of the separation head cover 1. Its structure includes two charge combustion chambers, two oblique nozzles, two plugging covers and other sealing structures. Two openings of a size matching the outlet of the oblique nozzle are opened on the separation head cover 1, so that the gas is ejected from the oblique nozzle outlet to generate thrust. The thrust acts on the separation head cover 1, and the torque generated by the head cover drives the missile body to roll. The charge amount of the charge combustion chamber is adjusted according to the working time, thrust and total impulse requirements required by missiles with different diameters and functions to adapt to the use of various types of missiles.

[0042] The rolling device 2 is an obliquely cut nozzle, two of which form a group, and the nozzle outlet direction is tangent to the radial direction of the separation head cover 1 and in the opposite direction.

[0043] like Figure 2As shown, the pitch device 3 in the example can provide thrust along the projectile diameter direction, generally exists in pairs and is symmetrically distributed on the inner wall of the separation head cover 1, and its structure includes a charge combustion chamber, a nozzle, a plug cover and connection seals. Two openings of a size matching the nozzle opening of the pitch device 3 are opened on the separation head cover 1, so that the gas is ejected from the nozzle opening to generate thrust along the projectile diameter direction. The thrust generates a torque and acts on the head cover to drive the projectile to pitch. Similarly, the pitch device 3 can design the structure and charge amount of the charge combustion chamber according to the requirements of different types of projectile diameters to meet the requirements of the projectile pitch deflection angle.

[0044] like Figure 4 As shown, the separation device 4 in the example can provide thrust at a certain angle along the axial direction of the projectile. It generally exists in pairs and is symmetrically distributed on the inner wall of the separation head cover. Its structure includes a charge combustion chamber, an oblique nozzle, a plug cover and a connection seal. Two openings of a size matching the oblique nozzle opening of the separation device 1 are opened on the separation head cover, so that the gas is ejected from the nozzle opening to generate a thrust component along the axial direction of the projectile diameter, so that the entire separation head cover 1 is separated from the projectile body. Similarly, the separation device 4 can also design the structure and charge amount of the charge combustion chamber according to the requirements of different types of projectile diameters to meet the requirements of the pitch and deflection angle of the projectile body.

[0045] The separation device 4 is an oblique nozzle, and the nozzle outlet direction forms a certain angle with the axial direction of the missile body, generating a thrust in the separation direction to promote the separation of the hood. The separation device 4 controls the angle of the hood separation through the working time to avoid contact with the missile antenna cover.

[0046] In the embodiment of the present invention, the material of the separation head cover 1 can be a fiber-reinforced composite molded part, which can greatly reduce the mass of the projectile body and reduce the difficulty of separation. At the same time, the lightweight and high-strength composite material can effectively ensure the integrity of the internal attitude control device structure and effectively transmit the thrust.

[0047] In the embodiment of the present invention, a heat protection coating is bonded to the outer wall surface of the separation head cover 1.

[0048] In the embodiment of the present invention, the combustion chambers of the rolling device 2, the pitching device 3, and the separation device 4 all use high-burning-rate solid propellants, which are safe, non-toxic, easy to use, and long-lasting. The solid propellant content can be designed according to the thrust and time required for turning.

[0049] In the embodiment of the present invention, the combustion chamber distribution direction of the rolling device 2 can be adjusted to be along the diameter direction or along the axial direction according to the spatial distribution of the separation head cover 1 and the antenna cover.

[0050] In the embodiment of the present invention, the nozzle outlet of the rolling device 2 extends out and is clamped on the shell of the separation head cover 1 for circumferential positioning, and the screw fixing position is in the middle of the two nozzles for constraint and positioning.

[0051] In the embodiment of the present invention, the combustion chamber of the pitch device 3 is relatively large and is distributed near the bottom of the separation head cover 1 .

[0052] In the embodiment of the present invention, the rolling device 2 and the pitching device 3 can be distributed on the same horizontal plane or on different planes, and can be appropriately adjusted depending on the spatial distribution in the hood.

[0053] In the embodiment of the present invention, the charge amounts of the two combustion chambers of the separation device 4 are adjusted, and the separation device 4 is controlled to generate two different thrusts and working times respectively, so as to ensure that when the hood is separated, under the action of different separation thrusts, the gravity of the hood is offset during the separation process, and the hood is detached from the antenna cover along the straight line direction of the projectile diameter.

[0054] In the embodiment of the present invention, according to the turning angle and direction required for the missile after launch, the two obliquely opposite combustion chambers of the rolling device 2 are ignited and opened for use at the same time, such as Figure 3 As shown, the combustion chamber of the pitch device 3 is opened only one at a time to work independently, such as Figure 2 As shown, the two combustion chambers of the separation device 4 are ignited and work at the same time. Figure 4 As shown, the rolling device 2 and the pitching device 3 can work simultaneously or sequentially, and the separation device 4 works subsequently.

[0055] The separation device of the present invention is located on the top of the missile, does not occupy the axial space, and is at the farthest distance from the center of mass of the missile. A large torque can be generated by a small power to achieve missile attitude adjustment.

[0056] The separation device of the present invention has strong adaptability and can be applied to vertically launched missiles of various ranges and diameters. It also has good designability and can adjust the distribution angles and positions of the rolling device, the pitching device and the separation device as required to meet the initial turning requirements of various missiles.

[0057] The initial turning and separation device for vertically launched missiles proposed in the present invention has completed sample trial production, and the processability and manufacturability of the product have been verified. At the same time, ground tests have been carried out to meet the working performance requirements for the initial attitude adjustment of the engine for vertical launch.

[0058] It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention.

[0059] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. An initial turning separation device for a vertically launched missile, characterized in that: include: A separation head cover (1), a rolling device (2), a pitching device (3), and a separation device (4); The rolling device (2), the pitching device (3), and the separation device (4) are arranged inside the separation head cover (1); wherein the rolling device (2) is provided in two groups, the pitching device (3) is provided in two groups, and the separation device (4) is provided in two groups; The pitch devices (3) are symmetrically distributed along the 0° direction of the projectile diameter plane and are connected and fastened to the separation head cover (1) through external screws to provide thrust along the projectile diameter direction; the rolling devices (2) are arranged in pairs and symmetrically distributed on the inner wall surface of the separation head cover (1), and the rolling devices (2) and the pitch devices (3) are at the same 0° position; the rolling devices (2) provide thrust in two opposite directions that are tangential to the circumference of the projectile body; The separation device (4) is installed at a 90° angle and is connected and fastened to the separation head cover (1) from the outside by screws; the separation device (4) provides a thrust force at a certain angle along the axial direction of the missile; the separation head cover (1) is connected to the missile body by explosive bolts or cutting locks, and the separation device is formed as a whole to adjust the initial turning posture of the vertically launched missile; The rolling device (2) comprises two charge combustion chambers, two obliquely cut nozzles, and two plugging covers; two openings of a size matching the outlets of the obliquely cut nozzles are opened on the separation head cover (1), so that the gas is ejected from the outlets of the obliquely cut nozzles to generate thrust, and the thrust acts on the separation head cover (1), and the torque generated by the separation head cover drives the missile body to roll; the charge amount of the charge combustion chamber is adjusted according to the working time, thrust and total impulse requirements required by missiles with different diameters and functions, so as to adapt to the use of various types of missiles; the plugging cover of the rolling device is used for sealing; The charge combustion chambers of the rolling device (2), the pitching device (3) and the separation device (4) all use high burning rate solid propellant; The charge amounts of the charge combustion chambers of the two separation devices (4) are adjusted, and the separation devices (4) are controlled to respectively generate two different thrusts and working times, so as to ensure that when the nose cover is separated, under the action of different separation thrusts, the gravity of the nose cover is offset during the separation process, and the nose cover is separated from the antenna cover along the linear direction of the projectile diameter; The rolling device (2) and the pitching device (3) are ignited and operated after the missile leaves the tube, and the missile pitches and rolls to push the missile to a designated position; The pitch devices (3) exist in pairs and are symmetrically distributed on the inner wall of the separation hood, and their structure includes a charge combustion chamber, a nozzle, and a plugging cover; the plugging cover of the pitch device is used for sealing; the separation devices (4) exist in pairs and are symmetrically distributed on the inner wall of the separation hood, and their structure includes a charge combustion chamber, a beveled nozzle, and a plugging cover; The two obliquely opposite charge combustion chambers of the rolling device (2) are ignited and opened for use at the same time; only one of the charge combustion chambers of the pitching device (3) is opened at a time to work independently; the charge combustion chambers of the two separation devices (4) are ignited and work at the same time; the rolling device (2) and the pitching device (3) work simultaneously or intermittently, and the separation device (4) works subsequently; After the rolling device (2) and the pitching device (3) have completed their work, the separation device (4) is ignited in sequence at a certain time interval to form a displacement difference, so that the separation head cover (1) separates and flies out in a specified direction, and the separation and flying process does not affect the normal operation of the missile antenna cover.

2. The initial turning separation device for vertically launched missiles according to claim 1, characterized in that: Two openings of a size matching the nozzle openings of the elevation device are opened on the separation hood, so that the gas is ejected from the nozzle opening to generate thrust along the direction of the projectile diameter. The thrust generates a torque and acts on the separation hood to drive the projectile to pitch. Similarly, the structure and charge of the propellant combustion chamber of the elevation device are designed according to the requirements of different types of projectile diameters to meet the requirements of the projectile's pitch and deflection angles.

3. The initial turning separation device for vertically launched missiles according to claim 1, characterized in that: Two openings of a size matching the beveled nozzle openings of the separation device are opened on the separation hood, so that the combustion gas can be ejected from the beveled nozzle openings to generate a thrust component along the axial direction of the projectile diameter, so that the entire separation hood is separated from the projectile body. Similarly, the separation device designs the structure and charge of the propellant combustion chamber according to the requirements of different types of projectile diameters to meet the requirements of the pitch and deflection angles of the projectile body.

4. The initial turning separation device for vertically launched missiles according to claim 1, characterized in that: The separation head cover (1) is made of a fiber-reinforced composite material molded part; and a heat protection coating is bonded to the outer wall surface of the separation head cover (1).

5. The initial turning separation device for vertically launched missiles according to claim 1, characterized in that: The distribution direction of the charge combustion chamber of the rolling device (2) is adjusted to be along the diameter direction of the projectile body or along the axial direction according to the spatial distribution of the separation head cover (1) and the antenna cover; The rolling device (2) extends out from the outlet of the oblique nozzle and is clamped on the shell of the separation head cover (1) for circumferential positioning. The screw fixing position is located in the middle of the two oblique nozzles for restraint and positioning.

6. The initial turning separation device for vertically launched missiles according to claim 1, characterized in that: The charge combustion chamber of the pitch device (3) is distributed near the bottom of the separation hood (1); the roll device (2) and the pitch device (3) are distributed on the same horizontal plane or on different planes, and are appropriately adjusted depending on the space distribution in the hood.

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