Description:FIELD OF THE INVENTION:

The present invention generally relates in the field of missile propulsion system. Particularly, the invention relates to the separation device for rocket motor to provide isolation between the multiple chambers of the rocket motor. More particularly, the invention relates to a pulse separation device for the chamber of dual pulse rocket motor.

BACKGROUND OF THE INVENTION:

Rocket Motor is the subsystem in any missile. The rocket motor consists of solid propellant which are especially required for initiating the launch, to boost or sustain the missiles/rocket. Generally, the rocket motor comprises a metallic cylindrical casing along with insulation called as combustion chamber. The insulation is used as safeguard of the metallic casing from hot gases produced in the combustion process. The combustion chamber is filled with solid propellant which upon ignition and burning generates large volumes of gases at high pressures and temperatures.

The burn rate of solid propellant is designed to control the generated thrust by the flow of gases through nozzle, which is placed at the end of the combustion chamber, to control the movement of the missile. As per the requirement, some missiles use dual pulse rocket motor, for them separation of the chamber is required with the help of a separation device. There are many types of separation device in the missile propulsion technology described in the prior arts. Some existing prior arts are as follows:

Pulse separation device is described in “Journal of the Korean Society of Propulsion Engineers, A Parametric Study on Double-Slit-Type Rupture Disc of Pulse Separation Device, Volume 14, Issue 5, Pages 101-110, 2010, 1226-6027(pISSN), 2288-4548(eISSN)”, it discloses a dual pulse rocket propulsion engine which is a solid propulsion engine in which two propellants with different characteristics are separated in two spaces by a bulkhead in one combustion tube. The rupture analysis of the rupture disk of the pulse separator was performed by the elasto-plastic dynamic behavior analysis using the finite element method. The effect of the slit design variables on the rupture disk was examined by analyzing the rupture shape and rupture point by performing an analysis in which the slit size of the rupture disk was changed. Analysis results can be used to adjust the bursting pressure by changing the slit size of the rupture disk of the pulse separator.

Further separation device is described by “Wang Chunguang et. al., Investigation on metal diaphragm of pulse separation device in dual-pulse solid rocket motor, DOI: 10.1177/0954410016638876”, it discloses a pulse separation device to achieve the feasible configuration of metal diaphragm, which could play a very important role in dual-pulse solid rocket motor. The metal diaphragm occupies an important role in the design of PSD. According to the research methods of valve rupture diaphragm of liquid rocket motor. The support has been designed as spoke shape to reduce weight and enlarge the gas passage area.

US patent no. US9151245B2 discloses pulse rocket motor including a dividing sheet for separating the first grain propellant from the second grain propellant. The pulse rocket motor has a hollow cylinder-like first grain situated in a rear section of a pressure vessel. A first igniter for igniting the first grain and a hollow cylinder-like second grain situated in a front section of the pressure vessel. A second igniter for igniting the second grain and a dividing sheet member that covers the second grain within the pressure vessel. The dividing sheet member includes a dividing sheet expanding at least along the inner circumferential surface of the second grain and holders formed integrally with the dividing sheet at both ends of the dividing sheet by cure adhesion and attached to the pressure vessel. The dividing sheet includes a brittle portion that expands along the inner circumferential surface of the second grain through a rear end face of the second grain and is more brittle than other portions.

US patent no. US4972673A discloses solid rocket motor with dual interrupted thrust. It discloses a solid propellant rocket motor, capable of providing two separate propulsive impulses to a missile. The rocket motor is connected at one end to the propulsion system, the other end including an exhaust nozzle. The rocket motor comprises two stages connected by an interstage bulkhead. The bulkhead includes a port opening which is closed by a frangible cover which prevents the second stage from igniting during burning of the first stage but breaks up into harmless fragments during firing of the second stage.

The main drawback in the above existing prior arts is that there is possibility of malfunctioning (not opening) and eventually bursting the rocket motor. In these methods, the disc is ruptured, which may result into obstruction by debris and damaging of nozzle or choking of the nozzle by the chunks thereby hindering mass flow of the gases and disturbing the thrust profile thereby leading to trajectory profile disturbance. The other limitation in prior arts is that there is possibility of rupturing of disc at the first place itself, therefore initiating the other motor also, thereby causing the damage of other systems.

Thus, the aim of present invention is to solve all these issues by aiming to provide a pulse separation device (PSD) for the chamber of dual pulse rocket motor in the missile.

OBJECTIVES OF THE INVENTION:

The principal object of the present invention is to provide a pulse separation device for the chamber of dual pulse rocket motor.

Another main object of the present invention is to provide a division of rocket motor chamber into two partitions, so that two separate combustions take place on either side of pulse separation device (PSD).

Another object of the invention is to provide a PSD without any leakage of gases at elevated temperature and pressure and breakage/rupture of PSD and therefore, the flow hindrance is avoided.

Another object of the invention is to provide and design a PSD with sliding mechanism to avoid breakage or rupturing of any components in the propulsion system.

Yet another object of the invention is to provide a PSD with higher reliability in operating the device.

SUMMARY OF THE INVENTION:

Accordingly, the present invention provides a pulse separation device for the chamber of dual pulse rocket motor. The invention designs a novel pulse separation device which is used in the dual pulse solid rocket motor to isolate both the chambers of the dual pulse rocket motor in missile. It provides the operation without any leakage of gases produced in the launch side, at elevated temperature and pressure and breakage/rupture of PSD, hence avoiding obstruction by debris.

In one aspect of the present invention, the present invention provides a pulse separation device (10) for the chamber of dual pulse rocket motor, wherein the rupture-free pulse separation device (PSD) (10) separates the dual pulse rocket motor chamber into two partitions/chambers (1 and 2), wherein the pulse separation device (10) comprising:
- a support ring (5);
- a stopper (6);
- a rubber pad (7);
- a perforated cylinder (8); and
- a perforated cylinder liner (8’),
wherein the two separate combustions take place on either side of pulse separation device (10) without leakage of gases;
wherein higher reliability in the operation is ensured by the said PSD (10).

The support ring (5) and the rubber pad (7) are fixed at the mouth end of the chamber-I (1) of the propulsion system (100).

The stopper (6) is arranged at one end of the perforated cylinder (8) and is placed inside the mouth of chamber-I (1) of the propulsion system (100).

The said support ring (5) provides support to the perforated cylinder (8) and is made up of metal to sustain the generated temperature and pressure of the produced gas.

The said stopper (6) is fixed at the mouth of the perforated cylinder (8) for obstructing the flow of gases produced in the launch side from unwanted initiation;
wherein the stopper (6) is provided with threaded portion to hold the perforated cylinder (8).

A passage of flow of gases produced in the launch side, is created in the said perforated cylinder (8);
wherein the perforated cylinder (8) is provided with the perforated cylinder liner (8’) for insulation.

The perforated cylinder (8) is made up of metal to withstand ultra-high temperature; and
wherein the insulation material for perforated cylinder liner (8’) is selected from Sp-16 or Carbon Phenolic.

The operation of said device (10) is shock-free by the rubber pad (7) placed at the mouth end of the chamber-I (1).

The PSD (10) separates the chamber by sliding mechanism to avoid the breakage or rupturing of components;
wherein the perforated cylinder (8) slides along with stopper (6) by force produced from the pressurized gases;
wherein the assembly of perforated cylinder (8) and stopper (6) provides the opening for gases and fixed on support ring (5).

A method for pulse separation device (10), wherein the method comprising steps of:
- initiating the ignition in the solid propellants present in the first chamber-I (1);
- generating high amount of temperature and pressurized gas inside first chamber-I (1);
- applying force on the surface of perforated cylinder (8) and stopper (6) by produced gases;
- sliding of the assembly of perforated cylinder (8) and stopper (6) towards forward direction;
- providing opening for gases, and the assembly of perforated cylinder (8) and stopper (6) sits on support ring (5); and
- absorbing shock by the rubber pad (7) present at the mouth end of the first chamber-I (1).

Thus, the aim of the present invention is to design a novel pulse separation device for providing separation between two pulses generated on either side of rocket motor chamber.

The above description merely is an outline of the technical solution of the present disclosure; in order to know the technical means of the present disclosure more clearly so that implementation may be carried out according to contents of the specification, and in order to make the above and other objectives, characteristics and advantages of the present disclosure more clear and easy to understand, specific embodiments of the present invention will be described in detail below.

BRIEF DESCRIPTION OF DRAWINGS:

The accompanying drawing which is incorporated herein constitute a portion of this specification and illustrate exemplary practices according to the invention which, together with the general description above and the detailed description set forth below will serve to explain the principle of the invention wherein:

Fig. 1 shows the schematic perspective view of close condition of pulse separation device (10) for the dual pulse rocket motor integration with the propulsion system (100) of the present invention.

Fig. 2 shows the schematic perspective view of open condition of pulse separation device (10) for the dual pulse rocket motor integration with the propulsion system (100) of the present invention.

Fig. 3 shows the schematic perspective view of support ring (5) for the pulse separation device (10) of the present invention.

Fig. 4 shows the schematic perspective view of stopper (6) for the pulse separation device (10) of the present invention.

Fig. 5 shows the schematic perspective view of rubber pad (7) for the pulse separation device (10) of the present invention.

Fig. 6 and Fig. 7 show the schematic perspective view of perforated cylinder (8) and perforated cylinder liner (8’) for the pulse separation device (10) of the present invention.

Fig. 8 shows the side view of the close condition of pulse separation device (10) of the present invention.

Fig. 9 shows the angled view of close condition pulse separation device (10) of the present invention. It specifically shows the bottom of the PSD (10).

Fig. 10 shows the angled view of the open condition of pulse separation device (10) of the present invention. It specifically shows the top of the PSD (10).

Fig. 11 shows the side view of the open condition of pulse separation device (10) of the present invention.

DETAILED DESCRIPTION OF THE INVENTION:

Accordingly, the present invention provides a pulse separation device for the chamber of dual pulse rocket motor. Generally, the rocket motor is provided along with the missile. The rocket motor of the missile comprises a metallic casing along with insulation called as combustion chamber. The said combustion chamber is filled with solid propellant for ignition. Once the ignition is completed the burning of the propellants generates large volume of gases at high pressures and temperatures.

The burn rate of solid propellent is designed to control the generated thrust i.e. force produced by the flow of gases through nozzle. The nozzle of the missile which is designed at the other end of the missile, for the flowing of gases produced in missile. As per the requirement, some missiles use dual pulse rocket motor, such missiles consist of single nozzle and same chamber is used for launching as well as flight motor. Also, some missile uses two separate rocket motors to be initiate at different time as required. Imperative that while initiating the firing of Launch Motor at the time of launching the missile, the flight motor ignition shall not be initiate or initiating the firing of first rocket motor in initial phase, the second rocket motor ignition shall not be initiated. Therefore, for this dual pulse motor separation of the chamber is required. The existing separation devices have some drawbacks.

Therefore, the present invention discloses a mechanism realized through a pulse separating device (PSD) for the separation of the rocket motor chamber. The pulse separation device is used to divide the rocket motor chamber into two partitions. Therefore, two separate combustions take place on either side of pulse separation device.

The pulse separation device is useful, when dual-pulse solid rocket motor is used. The pulse separation device is accommodated between the two chambers of the missile. It separates the launch motor side chamber from the nozzle side chamber. It consists of multiple components, out of which, one insulated component withstands ultra-high temperature, and another one absorbs shock. The absorption of the shock will occur when perforated cylinder slides to provide the passage to flow of the gases and stops at rubber pad.

The said pulse separation device provides two separate combustions taking place on either side of PSD without any leakage of gases at elevated temperature and pressure. Further, because of separate combustion breakage/rupture of PSD does not occur and hence, avoiding obstruction by debris. The novel design of PSD ensures higher reliability in operating.

In one aspect of the present invention, the present invention provides a pulse separation device for the rocket motor of the missile. The said PSD provides separation between two pulses generated on either side of rocket motor chamber.

Fig. 1 shows the perspective view of close condition of pulse separation device (10) for the dual pulse rocket motor integration with the propulsion system (100) of the present invention. The propulsion system (100) has a cylindrical tube-like structure. In one embodiment, the said tube-like structure of propulsion system (100) is made up of metal. The propulsion system (100) comprises two chambers i.e., chamber-I denoted by (1) and chamber-II denoted by (2). The one end side of the propulsion system (100) is chamber-I (1), and the other end side of the propulsion system (100) is chamber-II (2).

A dual pulse solid rocket motor (4) is connected with the one end of the propulsion system (100) and placed in chamber-I (1). The dual pulse rocket motor (4) consists of solid propellent. The solid propellants of the dual pulse rocket motor (4) are divided into two sections by an internal barrier. The said solid propellent is used in the ignition and after the ignition a heavy amount of gas produced with high temperature.

A nozzle (3) having a hollow conical shaped structure and is connected with another end of the propulsion system (100). The said nozzle (3) has a nozzle neck and is placed in chamber-II (2) which is used for flowing of the gases produced in the launch side.

A pulse separation device (10) is used in the propulsion system (100) between the chamber-I (1) and chamber-II (2) to separate both the chambers. It separates the burning of fuel or solid propellent in the launch side from the either side of the rocket motor chamber. The said pulse separation device (10) has multiple components. It includes a support ring (5), a stopper (6), a rubber pad (7) and a cylinder (8) along with cylinder liner (8’). The said components are arranged between the first chamber-I (1) and second chamber-II (2).

The support ring (5), stopper (6), rubber pad (7), cylinder (8) and cylinder liner (8’) are assembled at the mouth end of the chamber-I (1) of the propulsion system (100) to provide a controlled flow of gases produced from the launch side. The assembly of these components provide a shock free operation of the missile.

The said stopper (6) is arranged at one end of the cylinder (8). The assembly of cylinder (8) and stopper (6) is placed at inside the mouth of the chamber-I (1). In one embodiment, the assembly of cylinder (8) and stopper (6) is arranged by sliding mechanism. The support ring (5) and rubber pad (7) are fixed at the mouth end of the chamber-I (1).

In one embodiment, dowel pins (9) are also used to keep the cylinder (8) in required position initially, so that a controlled gases can pass through it. In one another embodiment, if required the dowel pins (9) can be used to provide the stability or hold at particular position. If the dowel pins (9) are used, the force required to shear off the dowel pin(s) (9) has to be taken into consideration while designing the PSD (10).

Once the ignition starts in solid propellants present in the chamber-I (1), combustion take place in dual pulse rocket motor (4) thereby a large amount of gas produced in the chamber-I (1). The produced gases have high pressure therefore, the gases applied pressure on the surface of cylinder (8), as shown by arrow in Fig. 1. The said force or pressure slides the cylinder (8) towards the forward direction i.e., towards chamber-II (2).

Fig. 2 shows the perspective view of close condition of pulse separation device (10) for the dual pulse rocket motor integration with the propulsion system (100) of the present invention. The high pressure produced in chamber-I (1) forcedly push the cylinder (8), thereby the cylinder (8) moves in forward direction and fixes on the support ring (5). Thus, the assembly of cylinder (8) and stopper (6) provides opening of the gas to the second chamber-II (2). Further, the rubber pad (7) is already provided at the mouth end of chamber-I to absorb the shock. It shows the open condition of PSD (10).
Fig. 3 shows the structure of support ring (5) of the pulse separation device (10). It shows a ring like structure (5) which is fixed at the end of the mouth of the chamber-I (1). The said support ring (5) is provided at the surrounding of the mouth end of chamber-I (1) of the propulsion system (100). The said ring like structure provides support to the cylinder (8) which are accommodate inside the mouth end of chamber-I (1) and also assembled with chambers. In one embodiment, the said support ring (5) is made up of metal to sustain the generated temperature and pressure of the produced gas.

Fig. 4 shows the stopper (6) of the PSD (10). The stopper (6) is fixed at the mouth end of the cylinder (8). It obstructs the flow of gases produced from the launch side. In one embodiment, the said stopper (6) is dome shaped which is placed at the mouth of the cylinder (8) to stop the gases produced in launch side. The stopper (6) stops the flow of gases to prevent unwanted initiation. In one embodiment, the stopper (6) is made up of metal. In one embodiment, the stopper (6) having threaded portion or press fit mechanism which can be made to hold the cylinder (8) as per the requirement. However, in one preferred embodiment, the stopper (6) is provided with threaded portion to hold the cylinder (8).

Fig. 5 shows the pad (7) of PSD (10). The said pad (7) is ring like structure and it provides at the end of the chamber-I (1) to provide shock free operation. In one embodiment, the said pad (7) is a rubber pad for absorbing the shock.

Fig. 6 and Fig. 7 show the cylinder liner (8’) and cylinder (8) of the PSD (10). The said cylinder (8) is assembled at the mouth end of the chamber-I (1). In one embodiment, the said cylinder (8) is perforated to provide the opening of the gas produced at the launch side. The said perforated cylinder (8) provides the controlled gases in chamber-II (2). The cylinder (8) provides passage of flow of gases produced from the dual pulse solid rocket motor (4) as per the requirement. In one embodiment, the said perforated cylinder (8) is made up of metal to withstand ultra-high temperature.

The perforated cylinder liner (8’) as shown in Fig. 6, is provided for insulating of the perforated cylinder (8). In one embodiment, the insulated material of said perforated cylinder liner (8’) is selected from Sp-16 or Carbon Phenolic.

Fig. 8 and Fig. 9 show the complete structure of pulse separation device. The figures show the close condition of the pulse separation device (10) wherein support ring (5) and rubber pad (7) are arranged at one end of the assembly of the perforated cylinder (8) and stopper (6). The close condition of PSD (10) obstructs the flow of gases produced at the launch side.

Fig. 10 and Fig. 11 show the complete structure of pulse separation device. The figures show the open condition of pulse separation device. The support ring (5), and the rubber pad (7) are arranged at another end of the assembly of the perforated cylinder (8) and stopper (6), after the assembly of the perforated cylinder (8) and stopper (6) slides in forward direction to provide the passage of gas produced from the launch side.

The pulse separation device (10) can be summarized as:
A pulse separation device (10) for the chamber of dual pulse rocket motor, wherein the rupture-free pulse separation device (PSD) (10) separates the dual pulse rocket motor chamber into two partitions chamber-I (1) and chamber-II (2), wherein the pulse separation device (10) comprising:
- a support ring (5);
- a stopper (6);
- a rubber pad (7);
- a perforated cylinder (8); and
- a perforated cylinder liner (8’),
wherein the two separate combustions take place on either side of pulse separation device (10) without leakage of gases;
wherein higher reliability in the operation is ensured by the said PSD (10).

Working of Pulse Separation Device (PSD):

The pulse separation device (10) separates the rocket motor chambers into two partitions so that the combustions take place on either side of PSD (10). For the functioning of PSD (10), it uses sliding mechanism to avoid breakage or rupturing of any component. When ignition starts in solid propellent present in chamber-I (1), the combustion starts in chamber-I (1) of dual pulse rocket motor (4). The high amount of pressurized gas generated inside the chamber-I (1). The pressurized gases apply pressure on the surface of insulated perforated cylinder (8) as well as stopper (6), imperative that force pushes the components towards the forward direction. Thus, the perforated cylinder (8) slides along with stopper (6) and provides the opening for gases produced from launch side and the assembly of perforated cylinder (8) and stopper (6) sits on support ring (5), where rubber pad (7) is already provided to absorb the shock.

The method of pulse separation device (10) can be summarized as:
- initiating the ignition in the solid propellants present in the chamber-I (1);
- generating high amount of temperature and pressurized gas inside chamber-I (1);
- applying force on the surface of perforated cylinder (8) and stopper (6) by produced gases;
- sliding of the assembly of perforated cylinder (8) and stopper (6) towards the forward direction;
- providing opening for gases, and the assembly of perforated cylinder (8) and stopper (6) sits on support ring (5); and
- absorbing shock by the rubber pad (7) present at the mouth end of the chamber-I (1).

In the novel design of PSD (10), rupture of disc does not occur, hence, there is no debris and no damaging of nozzle (3). Further, the design of PSD (10) provides one stopper (6) which stops the flow of the gases to prevent unwanted initiation and perforated cylinder (8) used to provide passage to flow of the gases from other side, whenever required. It can be further customized for different temperatures and pressures with minimal modifications.

ADVANTAGES OF THE INVENTION:

This present designed pulse separation device (PSD) has following advantageous features:
a) The novel design of PSD can work for pressure difference of any magnitude.
b) Manufacturing and assembly of the PSD is easy.
c) The PSD separates the rocket motor chamber without any leakage of gases.
d) It has high application adaptability.
e) It ensures higher reliability in the operating.
, Claims:
1. A pulse separation device (10) for the chamber of dual pulse rocket motor, wherein the rupture-free pulse separation device (PSD) (10) separates the dual pulse rocket motor chamber into two partitions/chambers (1 and 2), wherein the pulse separation device (10) comprising:
- a support ring (5);
- a stopper (6);
- a rubber pad (7);
- a perforated cylinder (8); and
- a perforated cylinder liner (8’),
wherein the two separate combustions take place on either side of pulse separation device (10) without leakage of gases;
wherein higher reliability in the operation is ensured by the said PSD (10).

2. The pulse separation device (10) as claimed in claim 1, wherein the support ring (5) and the rubber pad (7) are fixed at the mouth end of the chamber-I (1) of the propulsion system (100).

3. The pulse separation device (10) as claimed in claim 1, wherein the stopper (6) is arranged at one end of the perforated cylinder (8) and is placed inside the mouth of chamber-I (1) of the propulsion system (100).

4. The pulse separation device (10) as claimed in claim 1, wherein the said support ring (5) provides support to the perforated cylinder (8) and is made up of metal to sustain the generated temperature and pressure of the produced gas.

5. The pulse separation device (10) as claimed in claim 1, wherein the said stopper (6) is fixed at the mouth of the perforated cylinder (8) for obstructing the flow of gases produced in the launch side from unwanted initiation;
wherein the stopper (6) is provided with threaded portion to hold the perforated cylinder (8).

6. The pulse separation device (10) as claimed in claim 1, wherein a passage for flow of gasses produced in the launch side, is created in the said perforated cylinder (8);
wherein the perforated cylinder (8) is provided with the perforated cylinder liner (8’) for insulation.

7. The pulse separation device (10) as claimed in claim 6, wherein the perforated cylinder (8) is made up of metal to withstand ultra-high temperature; and
wherein the insulation material for perforated cylinder liner (8’) is selected from Sp-16 or Carbon Phenolic.

8. The pulse separation device (10) as claimed in claim 1, wherein the operation of the said device (10) is shock-free by the rubber pad (7) placed at the mouth end of the chamber-I (1).

9. The pulse separation device (10) as claimed in claim 1, wherein the PSD (10) separates the chamber by sliding mechanism to avoid the breakage or rupturing of components;
wherein the perforated cylinder (8) slides along with stopper (6) by force produced from the pressurized gases;
wherein the assembly of perforated cylinder (8) and stopper (6) provides the opening for gases and fixed on support ring (5).

10. A method for pulse separation device (10), wherein the method comprising steps of:
- initiating the ignition in the solid propellants present in the chamber-I (1);
- generating high amount of temperature and pressurized gas inside chamber-I (1);
- applying force on the surface of perforated cylinder (8) and stopper (6) by produced gases;
- sliding of the assembly of perforated cylinder (8) and stopper (6) towards forward direction;
- providing opening for gases, and the assembly of perforated cylinder (8) and stopper (6) sits on support ring (5); and
- absorbing shock by the rubber pad (7) present at the mouth end of the chamber-I (1).