A cruise missile boost separation system

Abstract

The present application belongs to the field of aerospace, and discloses a cruise missile boosting separation system, which comprises a combustion chamber shell (1), a nozzle (3), a plug (4), a sleeve (5), a separation spring (6), a base (7), a ring (8), an unlocking pin (9), an unlocking spring (10) and a screw plug (11). The combustion chamber shell (1) is a cylindrical structure, which is internally provided with an arrow medicine, and the lower end of the combustion chamber shell (1) is fixedly connected with the upper end of the nozzle (3). The lower end of the nozzle (3) is fixedly provided with the plug (4). The upper portion of the combustion chamber shell (1) is sleeved with the base (7). The present application is used for completing the boosting separation of the cruise missile, and can boost the cruise missile to a specified take-off speed, and throw away the residual mass without other external forces, thereby ensuring the stability for subsequent flight. The overall structure is simple, the separation mechanism is all mechanical structure, no other external force is generated, the action is reliable, the assembly is convenient, and the use is safe.

Description

Technical Field

[0001] This invention belongs to the field of aerospace, and in particular relates to a loitering munition boost-separation system. Background Technology

[0002] Boost-separation systems are widely used in weapons and equipment such as loitering munitions, target drones, rockets, and missiles. These weapons and equipment require a booster engine to rapidly propel them to a certain speed within a short period during initial takeoff, before using turbojet or rotary engines for cruise flight. A boost-separation system typically consists of a solid rocket motor and a separation mechanism. It can instantly propel the loitering munition or target drone to the required takeoff speed. Once the rocket motor fuel is exhausted, the remaining mass must be jettisoned as quickly as possible, and separation must be performed without any external forces to avoid affecting the flight attitude stability of the loitering munition or target drone.

[0003] Currently, separation systems mostly use explosive bolts or gas generators and other pyrotechnics for separation. These systems are complex, require electrical systems to provide separation signals, and generate axial and lateral forces after separation, which can affect the subsequent flight stability of loitering munitions or target drones, often causing them to stall and fall off. Furthermore, the reliability of pyrotechnic separation is low, and there are also safety hazards during transportation and storage. Summary of the Invention

[0004] The purpose of this invention is to provide a loitering munition boost-separation system to solve the technical problems of existing separation systems being complex in structure, affecting the subsequent flight stability of the loitering munition after separation, having low reliability when using pyrotechnic separation, and posing safety hazards during transportation and storage.

[0005] To achieve the above objectives, the specific technical solution of the loitering munition boost-separation system of the present invention is as follows:

[0006] A loitering munition boost-separation system includes a combustion chamber shell 1, a nozzle 3, a plug 4, a sleeve 5, a separation spring 6, a base 7, a retaining ring 8, an unlocking pin 9, an unlocking spring 10, and a screw plug 11. The combustion chamber shell 1 is a cylindrical structure containing propellant, and its lower end is fixedly connected to the upper end of the nozzle 3. A plug 4 is fixedly installed at the lower end of the nozzle 3. The base 7 is fitted on the upper part of the combustion chamber shell 1. The base 7 is thinner in the middle and thicker at both ends, with a cylindrical surface in the middle and stepped surfaces on the top and bottom outer surfaces. The sleeve 5 is fitted with... On the outside of the base 7, the upper part of the sleeve 5 is connected to the weapon that needs to be propelled. Two through holes are symmetrically arranged on the middle side of the sleeve 5. A screw plug 11 is fixedly installed on the outer end face of the through hole. An unlocking pin 9 is installed in the through hole. An unlocking spring 10 is sleeved on the outer surface of the unlocking pin 9. The head of the unlocking pin 9 is provided with a bevel. A retaining ring 8 is sleeved in the middle of the base 7. The upper and lower surfaces of the retaining ring 8 are beveled to cooperate with the bevel of the head of the unlocking pin 9. One end of the separation spring 6 contacts the upper end face of the base 7, and the other end contacts the weapon that needs to be propelled.

[0007] Furthermore, the inner surface of the bottom end of the base 7 is in contact with the outer surface of the top of the combustion chamber housing 1, and part of the contact surface between the two is an inclined surface.

[0008] Furthermore, the unlocking pin 9 has a square head structure, and correspondingly, the bottom of the through hole on the side of the sleeve 5 is square to accommodate the head of the unlocking pin 9.

[0009] Furthermore, both the top and bottom surfaces of the unlock pin 9 head are designed as bevels.

[0010] Furthermore, a circular groove is provided on the upper end surface of the base 7, and the separation spring 6 is disposed in the circular groove.

[0011] Furthermore, the retaining ring 8 is made of spring steel and has a 1mm groove for inward contraction.

[0012] Furthermore, the sleeve 5 is made of nylon material with low density.

[0013] Furthermore, the nozzle is a Laval nozzle.

[0014] Furthermore, when not separated, the head of the unlocking pin 9 extends into the interior of the sleeve 5 and contacts the stepped surface at the top of the base 7; the retaining ring 8 is located below the unlocking pin 9.

[0015] During the boost, the base 7 moves forward, compressing the separation spring 6, causing the retaining ring 8 to move upward under the action of the base 7. When it passes the unlocking pin 9, due to the action of the retaining ring and the inclined surface of the unlocking pin, the unlocking pin 9 moves backward while the retaining ring retracts, passing through the unlocking pin 9. After the rocket engine thrust disappears, the combustion chamber shell 1 and the base move downward under the action of the separation spring and gravity, causing the retaining ring to pass through the unlocking pin, compressing the unlocking spring, causing the unlocking pin to retract. The base and the retaining ring have the same outer diameter and also pass directly through the unlocking pin. Therefore, the combustion chamber shell, the base, and the separation locking spring fall off together.

[0016] The loitering munition boost-separation system of the present invention has the following advantages: it is used to complete the boost-separation of the loitering munition, boosting the munition to a specified takeoff speed while jettisoning residual mass, without generating any other external forces, thus ensuring stability for subsequent flight. The overall structure is simple, the separation mechanism is entirely mechanical, it does not generate any other external forces, it is reliable, easy to assemble, and safe to use. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the loitering munition boost-separation system before takeoff, as per the present invention.

[0018] Figure 2 This is a schematic diagram of the loitering munition boost-separation system during takeoff of the present invention;

[0019] Figure 3 This is a schematic diagram of the loitering munition boost-separation system after takeoff, according to the present invention. Detailed Implementation

[0020] To better understand the purpose, structure, and function of this invention, a loitering munition boost-separation system of this invention will be described in further detail below with reference to the accompanying drawings.

[0021] like Figures 1-3 As shown, the loitering munition boost-separation system of the present invention includes a combustion chamber shell 1, a set of propellant, a nozzle 3, a plug 4, a sleeve 5, a separation spring 6, a base 7, a retaining ring 8, two unlocking pins 9, two unlocking springs 10, and two screw plugs 11.

[0022] The combustion chamber shell 1 is a cylindrical structure containing propellant. Its lower end is connected to the upper end of the nozzle 3 by an external thread. A plug 4 is fixedly installed at the lower end of the nozzle 3. A base 7 is fitted on the upper part of the combustion chamber shell 1. The inner surface of the bottom end of the base 7 contacts the outer surface of the top of the combustion chamber shell 1, and part of the contact surface between the two is an inclined surface. The base 7 is thin in the middle and thick at both ends, with the middle part being a cylindrical surface and the outer surfaces of the top and bottom being stepped surfaces.

[0023] The sleeve 5 is fitted onto the outside of the base 7. The upper part of the sleeve 5 is connected to a loitering munition or target drone. Two Φ8 through holes are symmetrically arranged on the side of the middle part of the sleeve 5. The outer end face of the through hole is threaded and can be connected to the screw plug 11. An unlocking pin 9 is provided in the through hole, and an unlocking spring 10 is fitted on the outer surface of the unlocking pin 9. The unlocking pin 9 has a square head structure. Correspondingly, the bottom of the through hole on the side of the sleeve 5 is square to accommodate the head of the unlocking pin 9.

[0024] Furthermore, a circular groove is provided on the upper end surface of the base 7, and the separation spring 6 is disposed in the circular groove. One end of the separation spring 6 contacts the upper end surface of the base 7, and the other end contacts the loitering munition.

[0025] A retaining ring 8 is fitted in the middle of the base 7. The retaining ring 8 has beveled surfaces on both the top and bottom, which are used to engage with the beveled surface of the head of the unlocking pin 9. The outer diameter of the retaining ring 8 is the same as the outer diameter of the top of the base 7.

[0026] The outer diameter of the top of the base 7 matches the inner diameter of the sleeve 5; the outer diameter of the bottom of the base 7 is larger than its outer diameter at the top.

[0027] The nozzle is a Laval nozzle.

[0028] The booster system in this embodiment is a solid rocket motor, which adopts a conventional single-chamber single-nozzle structure. The combustion chamber shell 1 is filled with propellant. The bottom of the combustion chamber shell 1 is connected to the nozzle 3 by an external thread. The plug 4 is connected to the nozzle by a pull-off screw. It adopts an electric ignition method. After reaching the ignition pressure, the propellant 2 is ignited, the pull-off screw breaks, and the plug 4 is ejected to generate thrust.

[0029] The separation system is connected above the solid rocket motor. The sleeve 5 is made of low-density nylon material to reduce weight. The upper part of the sleeve 5 is connected to the loitering munition or target drone. The sleeve 5 has two symmetrical Φ8 through holes on its side for placing the unlocking pin 9 and the unlocking spring 10. The outer end face of the through hole is threaded and can be connected to the screw plug 11. The bottom of the through hole is a square hole for placing the head of the unlocking pin 9.

[0030] The base 7 is made of aluminum. There is a circular groove on the top for placing the separation spring 6. The separation spring 6 is placed in the circular hole. Below is a circular ring structure with threaded holes for connecting to the solid rocket motor.

[0031] The retaining ring 8 is made of spring steel and has beveled surfaces on both the top and bottom, which facilitates the left and right movement of the unlocking pin 9 on its outside. The retaining ring 8 has a 1mm groove, which helps the retaining ring to retract.

[0032] The unlocking pin 9 has a square head that extends into the square hole on the side of the sleeve 5 to prevent the unlocking pin 9 from rotating. The front end of the square head of the unlocking pin 9 has beveled surfaces on both the top and bottom, which can cooperate with the retaining ring 8. The up and down movement of the retaining ring 8 causes the unlocking pin to move left and right in the square hole on the side of the sleeve 5.

[0033] When not separated, the head of the unlocking pin 9 extends into the interior of the sleeve 5 and contacts the stepped surface at the top of the base 7; the retaining ring 8 is located below the unlocking pin 9.

[0034] The retaining ring 8 is fitted onto the base, and the unlocking pin is on the side of the sleeve. Both of their contact surfaces are inclined. The solid rocket motor ignites the ignition propellant through an electric igniter, establishes the ignition pressure, ignites the propellant, and ejects it from the nozzle. The propellant burns, and the gas is accelerated through the nozzle and ejected backward, generating thrust to help the loitering munition take off. During the boost, the rocket motor pushes the base 7 in the separation mechanism forward, compressing the separation spring 6. This causes the retaining ring 8 to move upward under the action of the base 7. When it passes the unlocking pin 9, due to the angle between the retaining ring and the unlocking pin, the unlocking pin 9 compresses the spring and moves backward while the retaining ring contracts, passing through the unlocking pin 9. After the rocket motor thrust disappears, the burnt rocket motor remnant shell and the unlocking mechanism base move downward under the action of the separation spring and gravity. When the retaining ring passes through the unlocking pin, it compresses the unlocking spring, causing the unlocking pin to retract. The base and retaining ring have the same outer diameter and also pass directly through the unlocking pin. Therefore, the rocket motor remnant shell, the base, and the separation spring all fall off together, effectively reducing the mass of the loitering munition.

[0035] The boost-separation system of this invention typically consists of a solid rocket motor and a separation mechanism. It can instantly propel a loitering munition or target drone to the required takeoff speed. Once the solid rocket motor fuel is exhausted, the remaining mass needs to be jettisoned as quickly as possible. Furthermore, separation requires no external forces to avoid affecting the flight attitude stability of the loitering munition or target drone. Its structure is simple and its manufacturing cost is low. By changing the interface size and thrust, it can be widely applied to weapons and equipment such as loitering munitions, target drones, rockets, and missiles, making it a highly versatile boost-separation system.

[0036] Although embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art will be able to make various modifications and improvements without departing from the principles of the present invention, and these modifications and improvements should also be considered to fall within the scope of protection of the present invention.

Claims

1. A loitering munition boost-separation system, characterized in that, The combustion chamber housing (1) includes a combustion chamber shell (1), a nozzle (3), a plug (4), a sleeve (5), a release spring (6), a base (7), a retaining ring (8), an unlocking pin (9), an unlocking spring (10), and a screw plug (11). The combustion chamber shell (1) is a cylindrical structure containing propellant, and its lower end is fixedly connected to the upper end of the nozzle (3). A plug (4) is fixedly installed at the lower end of the nozzle (3). A base (7) is fitted on the top of the combustion chamber shell (1). The base (7) is thin in the middle and thick at both ends, with a cylindrical surface in the middle and stepped surfaces on the top and bottom. The sleeve (5) is fitted on the bottom. The outer side of the base (7) is connected to the weapon that needs to be propelled above the sleeve (5). Two through holes are symmetrically arranged on the middle side of the sleeve (5). A screw plug (11) is fixedly installed on the outer end face of the through hole. An unlocking pin (9) is installed inside the through hole. An unlocking spring (10) is sleeved on the outer surface of the unlocking pin (9). The head of the unlocking pin (9) is provided with a bevel. A retaining ring (8) is sleeved in the middle of the base (7). Both the upper and lower surfaces of the retaining ring (8) are beveled, which are used to cooperate with the bevel of the head of the unlocking pin (9). One end of the separation spring (6) is in contact with the upper end face of the base (7), and the other end is in contact with the weapon that needs to be propelled.

2. The loitering munition boost-separation system according to claim 1, characterized in that, The bottom inner surface of the base (7) is in contact with the outer surface of the top of the combustion chamber shell (1), and part of the contact surface between the two is an inclined surface.

3. The loitering munition boost-separation system according to claim 1, characterized in that, The unlocking pin (9) has a square head, and correspondingly, the bottom of the through hole on the side of the sleeve (5) is square to accommodate the head of the unlocking pin (9).

4. The loitering munition boost-separation system according to claim 3, characterized in that, The upper and lower surfaces of the head of the unlocking pin (9) are both set as bevels.

5. The loitering munition boost-separation system according to claim 1, characterized in that, The upper surface of the base (7) is provided with a circular groove, and the separation spring (6) is disposed in the circular groove.

6. The loitering munition boost-separation system according to claim 1, characterized in that, The retaining ring (8) is made of spring steel and has a 1mm groove for inward shrinkage.

7. The loitering munition boost-separation system according to claim 1, characterized in that, The sleeve (5) is made of nylon material with low density.

8. The loitering munition boost-separation system according to claim 1, characterized in that, The nozzle is a Laval nozzle.

9. The loitering munition boost-separation system according to claim 1, characterized in that, When not separated, the head of the unlocking pin (9) extends into the interior of the sleeve (5) and contacts the stepped surface at the top of the base (7); the retaining ring (8) is located below the unlocking pin (9).

10. The loitering munition boost-separation system according to claim 1, characterized in that, During the boost, the base (7) moves forward, compressing the separation spring (6), causing the retaining ring (8) to move upward under the action of the base (7). When it passes the unlocking pin (9), due to the action of the retaining ring and the inclined surface of the unlocking pin, the unlocking pin (9) moves backward while the retaining ring retracts and passes through the unlocking pin (9). After the rocket engine thrust disappears, the combustion chamber shell (1) and the base move downward under the action of the separation spring and gravity. When the retaining ring passes through the unlocking pin, it compresses the unlocking spring, causing the unlocking pin to retract. The base and the retaining ring have the same outer diameter and also pass directly through the unlocking pin. Therefore, the combustion chamber shell, the base, and the separation locking spring fall off together.

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