US20130118147A1 - Two-pulse rocket motor - Google Patents
Two-pulse rocket motor Download PDFInfo
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- US20130118147A1 US20130118147A1 US13/708,338 US201213708338A US2013118147A1 US 20130118147 A1 US20130118147 A1 US 20130118147A1 US 201213708338 A US201213708338 A US 201213708338A US 2013118147 A1 US2013118147 A1 US 2013118147A1
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- propellant
- barrier membrane
- rocket motor
- igniter
- pulse
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/10—Shape or structure of solid propellant charges
- F02K9/12—Shape or structure of solid propellant charges made of two or more portions burning at different rates or having different characteristics
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/28—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
Definitions
- the present invention relates to solid propellant rocket motors which are capable of providing two separate and distinct propulsive impulses at expected time.
- the two-phase motor includes a pressure vessel 100 having a rear opening that releases a propellant material, a first pulse explosive grain (a first propellant) 101 arranged in the rear part of the pressure vessel 100 , a second pulse explosive grain (a second propellant) 102 arranged in the front part of the pressure vessel 100 , a barrier isolator (barrier membrane) 103 for isolating the first pulse explosive grain 101 and the second pulse explosive grain 102 from each other, and a firing device means arranged in the front part of the pressure vessel 100 so that the first pulse explosive grain 101 and the second pulse explosive grain 102 can be fired selectively.
- the firing device means includes a first pulse firing device (ignition device) 108 arranged close to the first pulse explosive grain 101 and a second pulse firing device arranged close to the second pulse explosive grain 102 .
- the second pulse firing device includes a firing device blocking body 105 in which an annular chamber 104 defining a firing device chamber is arranged and a second firing device explosive grain 106 for firing the second pulse explosive grain.
- the firing device blocking body 105 is provided with at least one nozzle port 107 for providing a path leading from the annular chamber 104 to the second pulse explosive grain 102 (for example, Patent Document 1).
- FIGS. 14 and 15 a two-stage thrust type rocket motor as shown in FIGS. 14 and 15 has been proposed.
- this rocket motor an injection nozzle 113 is disposed at the rear, a first combustion chamber 110 and a second combustion chamber 111 are disposed in the named order from the injection nozzle 113 directly or via a joint 112 in a state of being connected in series.
- a first propellant 114 having a hollow part penetrating longitudinally is provided in the first combustion chamber 110
- a second propellant 115 having a hollow part penetrating longitudinally is provided.
- first igniting case In the wall surface at a position at which the first propellant 114 is selectively fired, one or more through holes are provided, and in a front-side end part of a first igniting case (ignition device) 119 , a first blocking body 121 to which a mechanism for firing a first igniting powder 117 is attached is provided. Also, the first igniting case 119 charged with the first igniting powder therein is arranged on the longitudinal axis line in the first combustion chamber.
- a second igniting case 120 In the wall surface at a position at which the hollow part wall surface of the second propellant 115 is fired directly, one or more through holes are provided, and in the front-side end part of a second igniting case 120 , a second blocking body 122 to which a mechanism for firing the second igniting powder 118 is attached is provided.
- the second igniting case (ignition device) 120 charged with the second igniting powder 118 therein is disposed in the hollow part of the second propellant 115 , and the outer peripheral end part thereof is fixed by the entire of circumference of a rocket motor shell part.
- a barrier membrane 116 to which the inner peripheral end part of the second igniting case 120 is fixed is provided between the first igniting case 119 and the second igniting case 120 so as to isolate the first propellant 114 and the second propellant 115 from each other (for example, Patent Document 2).
- the missile is accelerated by the first pulse (the propulsive impulse generated by first propellant combustion) and flies toward its target, and when it approaches the target, it is accelerated again by the second pulse (the propulsive impulse generated by second propellant combustion) to enhance maneuverability at the terminal guidance.
- first pulse the propulsive impulse generated by first propellant combustion
- second pulse the propulsive impulse generated by second propellant combustion
- first propellant mass consumed in the first pulse be increased to set burn time longer and/or thrust higher.
- the first propellant cannot have enough length because the first propellant and the second propellant are set in the axial direction of the rocket motor, and the rocket motor length is limited for equipment or storage.
- propellant grain design is an internal burning type as shown in FIGS. 12 and 14 .
- the second propellant must be shortened because the rocket motor length is restricted. In that case, since the second propellant cannot have enough burning area and its combustion gas flow is generated insufficiently, the necessary thrust cannot be achieved at second propellant combustion with the nozzle which has the same throat diameter (the minimum diameter of exhaust hole) at first propellant combustion.
- propellant grain design is such that the two propellants are set in the axial direction as shown in FIGS. 12 and 14 , the thermal barrier membrane is exposed partly to high-temperature combustion gas from the beginning of first propellant combustion. Therefore, it is necessary to make the thermal barrier membrane thicker to protect the second propellant inside it from heat until the due time of second propellant combustion, which reduces propellant mass.
- thermal barrier membrane and its holding structure shown in FIGS. 12 and 14 it is not clear either behavior (breaking properties) or condition of the remains of the thermal barrier membrane when the second igniter works. If the barrier membrane is broken in an unexpected portion, the second propellant cannot have enough burning area because the barrier membrane does not detach from the burning surface and cover it.
- the barrier membrane is broken in the forward portion, most of it will turn over and detach from the second propellant toward the nozzle. In that case, combustion or combustion gas flows of the second propellant can be hindered, and at worst, the nozzle may be closed by the broken barrier membrane. In particular, the above-mentioned troubles occur remarkably for long or small-diameter two-pulse rocket motors.
- another object of the present invention is to provide a two-pulse rocket motor in which combustion or combustion gas flows of the second propellant are not hindered by providing the barrier membrane and its holding structure considering good behavior and condition of the remains of the thermal barrier membrane and further providing a device considering the exposure of the burning surface of the second propellant and its ignitability when the second igniter works.
- the present invention solves the above-mentioned problems by the following means.
- a two-pulse rocket motor of a first means has a motor case containing a second propellant, a second igniter set on the end surface of the second propellant, a barrier membrane that covers the initial burning surface of the second propellant entirely and the second igniter, and a first propellant loaded so as to cover the barrier membrane entirely, and is characterized by the first propellant and the second propellant each have an internal burning type or an internal and end burning type of propellant grain design.
- a two-pulse rocket motor of a second means is, in the two-pulse rocket motor of the first means, characterized by the barrier membrane composed of an inner barrier membrane covering the inner surface of the second propellant and an aft barrier membrane covering the aft end surface of the second propellant, and the meeting edges of the aft barrier membrane and the inner barrier membrane are bonded throughout the entire periphery.
- a two-pulse rocket motor of a third means is, in the two-pulse rocket motor of the first means, characterized by the barrier membrane having slits on it.
- a two-pulse rocket motor of a fourth means is, in the two-pulse rocket motor of any one of the first to third means, characterized by the second igniter set on the aft end surface of the second propellant.
- a two-pulse rocket motor of a fifth means is, in the two-pulse rocket motor of any one of the first to fourth means, characterized by an igniter charge having higher ignitability and a higher burning rate than the second propellant set on the inner surface of the second propellant.
- a two-pulse rocket motor of a sixth means is, in the two-pulse rocket motor of the fifth means, characterized by the igniter charge set in plural slits, which are shaped on the inner surface of the second propellant in the axial direction around the longitudinal axis.
- the second propellant is set outside of the first propellant, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case, so that the initial burning area of the first pulse can be increased. Therefore, a large slit need not be provided in the inner surface of the first propellant, and a decrease in total thrust can be avoided.
- the first propellant is set so as to cover the entire of barrier membrane, and the barrier membrane is protected from heat in the first half of first propellant combustion. Therefore, the plate thickness of barrier membrane can be decreased.
- the burning area of the second propellant does not become extremely smaller than the burning area of the first propellant, and a varying mechanism for the throat diameter of nozzle need not be provided, so that an increase in weight can be restrained.
- the second propellant is protected from heat until the operation of the second propellant, and after the operation, there remains no component in the motor case. Therefore, the weight of heat-resisting material can be reduced.
- the barrier membrane is divided into two pieces and a joint part is provided to weaken a portion to be broken or a slit is formed in the barrier membrane to break the barrier membrane. Therefore, the barrier membrane is surely broken at an expected position (weak part) by the pressure of gas generated by the operation of the second igniter or second propellant combustion.
- the inner barrier membrane that occupies most of the barrier membrane deforms toward the center when being separated from the second propellant, and the holding part of barrier membrane after deformation lies in the front part of motor case where the flow due to combustion gas of the second propellant is relatively gentle, so that the survival properties are excellent.
- the aft barrier membrane itself after breakage is small, when being separated, the aft barrier membrane deforms naturally in the nozzle-side direction along the flow of combustion gas of the second propellant, so that the survival properties are excellent.
- the weak part (joint part or slit) of barrier membrane or a portion to be broken of the barrier membrane can be broken more surely.
- the igniter charge having higher ignitability and a higher burning rate than the second propellant is provided between the inner surface of the second propellant and the barrier membrane, the igniter charge is ignited earlier than the second propellant by the operation of the second igniter.
- the separation of the inner barrier membrane or the inside portion of the barrier membrane (exposure of burning surface of the second propellant) and the ignition of the second propellant are assisted, so that the second propellant can be burned surely.
- the invention of this means also has an effect that the pressure at the second pulse is raised quickly by combustion gas of igniter charge.
- the degree of freedom can be given to the propellant shape of the second propellant.
- FIG. 1 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a first embodiment of the present invention
- FIG. 2 is a sectional view taken along the line A-A of FIG. 1 ;
- FIG. 3 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a second embodiment of the present invention
- FIG. 4 is a sectional view taken along the line B-B of FIG. 3 ;
- FIG. 5 is a longitudinal sectional view showing a state in which a barrier membrane is deformed at the burn time of second propellant combustion in a two-pulse rocket motor in accordance with a second embodiment of the present invention
- FIG. 6( a ) is a sectional view taken along the line C-C of FIG. 5
- FIG. 6( b ) is a sectional view taken along the line D-D of FIG. 5 ;
- FIG. 7 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a third embodiment of the present invention.
- FIG. 8 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a fourth embodiment of the present invention.
- FIG. 9 is a sectional view taken along the line E-E of FIG. 8 ;
- FIG. 10 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a fifth embodiment of the present invention.
- FIG. 11 is a sectional view taken along the line F-F of FIG. 10 ;
- FIG. 12 is a configuration view of a conventional two-stage thrust type rocket motor
- FIG. 13 is a detailed view of an ignition device means of the two-stage thrust type rocket motor shown in FIG. 12 ;
- FIG. 14 is a configuration view of another conventional two-stage thrust type rocket motor.
- FIG. 15 is a detailed view of a first igniting case and a second igniting case of the two-stage thrust type rocket motor shown in FIG. 14 .
- FIG. 1 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a first embodiment of the present invention
- FIG. 2 is a sectional view taken along the line A-A of FIG. 1 .
- FIG. 3 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a second embodiment of the present invention
- FIG. 4 is a sectional view taken along the line B-B of FIG. 3 .
- FIG. 5 is a longitudinal sectional view showing a state in which a barrier membrane is deformed at the burn time of second propellant combustion in the two-pulse rocket motor in accordance with the second embodiment of the present invention.
- FIG. 6( a ) is a sectional view taken along the line C-C of FIG. 5
- FIG. 6( b ) is a sectional view taken along the line D-D of FIG. 5 .
- FIG. 7 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a third embodiment of the present invention.
- FIG. 8 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a fourth embodiment of the present invention
- FIG. 9 is a sectional view taken along the line E-E of FIG. 8 .
- FIG. 10 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a fifth embodiment of the present invention
- FIG. 11 is a sectional view taken along the line F-F of FIG. 10 .
- FIGS. 1 and 2 First, a two-pulse rocket motor in accordance with a first embodiment of the present invention is explained with reference to FIGS. 1 and 2 .
- the two-pulse rocket motor in accordance with the first embodiment burns a first propellant 4 and subsequently burns a second propellant 5 after arbitrary time has elapsed to produce two-stage thrust.
- the second propellant 5 must withstand high-temperature combustion gas and a high pressure produced by combustion of the first propellant 4 .
- first propellant 4 and the second propellant 5 can accommodate various thrust patterns by using a common nozzle 2 by the contrivance of the arrangement and propellant shape thereof
- the nozzle 2 having an exhaust hole 12 for exhausting combustion gas in the center therein is attached to the rear of a cylindrical motor case 1 .
- an end plate 3 is attached, and to the front of the end plate 3 , a first igniter 6 for burning the first propellant 4 is attached.
- the first propellant 4 and the second propellant 5 each having a hollow and cylindrical shape (a propellant shape of an internal burning type or an internal and end burning type) are charged, and the second propellant 5 is set outside and the forward part of the first propellant 4 .
- each of the first propellant 4 and the second propellant 5 can be a hollow cylindrical shape, a hollow tubular shape having polygonal inner surface and/or outer surface, a hollow conical shape, or the like shape.
- the first propellant 4 and the second propellant 5 are isolated from each other by a barrier membrane 10 .
- the barrier membrane 10 As being known publicly, as the barrier membrane 10 , a highly heat-resistant rubber such as silicone rubber or EPDM rubber, containing EPDM rubber, silicone rubber, and inorganic fiber such as Kevlar fiber as a composition thereof can be used.
- a highly heat-resistant rubber such as silicone rubber or EPDM rubber, containing EPDM rubber, silicone rubber, and inorganic fiber such as Kevlar fiber as a composition thereof can be used.
- a second igniter 8 for burning the second propellant 5 is provided.
- the second igniter 8 is not limited to one having the above-described construction.
- the second igniter 8 may be configured by a tubular chamber 104 , a nozzle port 107 , and the like shown in FIG. 13 (cited document 1).
- the shapes of the first propellant 4 , the barrier membrane 10 , and the second propellant 5 are not limited to those shown in FIGS. 1 and 2 .
- the propellant shape, the propellant length, and the like can be set appropriately according to various thrust patterns.
- the two-pulse rocket motor in accordance with the first embodiment of the present invention is configured as described above.
- the first igniter 6 is operated by a signal sent from the outside, by which combustion of the first propellant 4 is started. At this point of time, the barrier membrane 10 is not exposed to high-temperature combustion gas.
- the barrier membrane 10 When the first propellant 4 burns to the position of the barrier membrane 10 , the barrier membrane 10 is exposed to high-temperature combustion gas.
- the second igniter 8 is operated by a signal sent from the outside, by which combustion of the second propellant 5 is started.
- the inner surface of the first propellant 4 is exposed to a burning region 11 throughout the almost entire length in the axial direction of the motor case 1 . Therefore, the initial burning area can be secured, so that a large slit need not be provided in the inner surface of the first propellant 4 .
- the burning area of the second propellant 5 does not become extremely smaller than the burning area of the first propellant 4 , so that the nozzle 2 for the first propellant 4 can be used commonly.
- the second propellant 5 is set outside of the first propellant 4 and the barrier membrane 10 is provided therebetween, the time over which the barrier membrane 10 is exposed to high-temperature combustion gas can be shortened as much as possible, so that the barrier membrane 10 can be protected from heat.
- the second igniter 8 is protected from heat by the barrier membrane 10 like the second propellant 5 , and is burned down by the operation, so that the protection from heat is not needed.
- the initial burning surface of the second propellant 5 in the present invention means a surface burned from the initial stage when the second propellant 5 begins to burn, that is, a surface exposed to the burning region 11 first when the second propellant 5 is burned.
- the cylindrical inner surface on the inside of the second propellant 5 and the ring-shaped rear surface at the rear thereof are the initial burning surfaces.
- the barrier membrane 10 is divided into two pieces, and a weak part (joint part) is provided as compared with the first embodiment of the present invention.
- the barrier membrane 10 covering the second propellant 5 is formed by a circular truncated cone shaped aft barrier membrane 10 a provided on the rear surface of the second propellant 5 and a cylindrical inner barrier membrane 10 b provided on the inner surface of the second propellant 5 .
- the end part in which the aft barrier membrane 10 a and the inner barrier membrane 10 b meet provides the weak part formed by joining the aft barrier membrane 10 a and the inner barrier membrane 10 b to each other throughout the entire periphery by using a fire-resistant adhesive.
- the joint part is not broken during combustion of the first propellant 4 , and is broken surely by the pressure of gas generated by the operation of the second igniter 8 or combustion of the second propellant 5 .
- the inner barrier membrane 10 b that occupies most of the barrier membrane 10 deforms toward the center, and is held in the front part of motor case where the flow due to combustion gas of the second propellant 5 is relatively gentle. Also, the broken part of the aft barrier membrane 10 a deforms so as to be turned up to the rear along the flow of combustion gas.
- the breaking properties and the survival properties of the barrier membrane 10 are clear and reliable.
- the configuration in which the barrier membrane 10 is manufactured integrally and a slit is formed in a portion to be broken and the like configuration can achieve the same effect as that of the configuration in which the barrier membrane 10 is divided into two pieces.
- the second igniter 8 is provided at a position close to the joint part of the barrier membrane 10 (the aft barrier membrane 10 a , the inner barrier membrane 10 b ) on the rear end surface of the second propellant 5 as compared with the first and second embodiments of the present invention.
- the operation and effect of the second embodiment of the present invention are improved, and the reliability of breaking of the barrier membrane 10 (the aft barrier membrane 10 a , the inner barrier membrane 10 b ) is increased.
- an igniter charge 14 for the second propellant 5 is charged between the inner surface of the second propellant 5 and the inner barrier membrane 10 b as compared with the first to third embodiments of the present invention.
- the cylindrical igniter charge 14 is charged.
- the igniter charge 14 used has higher ignitability and a higher burning rate than the second propellant 5 .
- the two-pulse rocket motor in accordance with the fourth embodiment of the present invention is configured as described above.
- the second igniter 8 is operated by a signal sent from the outside, and the gas generated by combustion of the igniter charge 14 assists the separation of the inner barrier membrane 10 b and the ignition of the second propellant 5 .
- the igniter charge 14 increases the reliability of the exposure and ignition of burning surface of the second propellant 5 .
- the igniter charge 14 for the second propellant 5 is charged by being divided into several pieces in the circumferential direction as compared with the fourth embodiment of the present invention.
- plural slits are shaped on the inner surface of the second propellant 5 in the axial direction around the longitudinal axis, in which the igniter charge 14 is set.
- the degree of freedom can be given to the propellant shape of the second propellant 5 by arranging the igniter charge 14 so as to match the shape of the inner surface of the second propellant 5 .
- two-pulse rocket motors consisting of combinations described below, including the combinations described in the above embodiments, can be embraced in the present invention.
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Abstract
In the two-pulse rocket motor in accordance with the present invention, the second propellant is set outside of the first propellant in a motor case, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case. Therefore, the initial burning area can be secured without deteriorating the performance. Also, by providing a weak part by bonding the barrier membranes or shaping slits on the barrier membrane, the breaking portion of barrier membrane and the behavior of barrier membrane after breakage can be controlled. Further, by setting an igniter charge having higher ignitability and a higher burning rate than the second propellant between the inner surface of the second propellant and the inner barrier membrane, the detachment of barrier membrane and the ignition of the second propellant can be assisted.
Description
- This application is a Divisional of copending application Ser. No. 12/599,874, filed Nov. 12, 2009, which is a National Stage of copending PCT International Application No. PCT/JP2008/058648 filed on May 9, 2008. The entire contents of each of the above documents in hereby incorporated by reference into the present application.
- The present invention relates to solid propellant rocket motors which are capable of providing two separate and distinct propulsive impulses at expected time.
- Conventionally, a two-phase motor of a solid propellant as shown in
FIGS. 12 and 13 has been proposed. The two-phase motor includes apressure vessel 100 having a rear opening that releases a propellant material, a first pulse explosive grain (a first propellant) 101 arranged in the rear part of thepressure vessel 100, a second pulse explosive grain (a second propellant) 102 arranged in the front part of thepressure vessel 100, a barrier isolator (barrier membrane) 103 for isolating the first pulseexplosive grain 101 and the second pulseexplosive grain 102 from each other, and a firing device means arranged in the front part of thepressure vessel 100 so that the first pulseexplosive grain 101 and the second pulseexplosive grain 102 can be fired selectively. The firing device means includes a first pulse firing device (ignition device) 108 arranged close to the first pulseexplosive grain 101 and a second pulse firing device arranged close to the second pulseexplosive grain 102. The second pulse firing device includes a firingdevice blocking body 105 in which anannular chamber 104 defining a firing device chamber is arranged and a second firing deviceexplosive grain 106 for firing the second pulse explosive grain. The firingdevice blocking body 105 is provided with at least onenozzle port 107 for providing a path leading from theannular chamber 104 to the second pulse explosive grain 102 (for example, Patent Document 1). - Also, a two-stage thrust type rocket motor as shown in
FIGS. 14 and 15 has been proposed. In this rocket motor, aninjection nozzle 113 is disposed at the rear, afirst combustion chamber 110 and asecond combustion chamber 111 are disposed in the named order from theinjection nozzle 113 directly or via ajoint 112 in a state of being connected in series. In thefirst combustion chamber 110, afirst propellant 114 having a hollow part penetrating longitudinally is provided, and in thesecond combustion chamber 111, asecond propellant 115 having a hollow part penetrating longitudinally is provided. In the wall surface at a position at which thefirst propellant 114 is selectively fired, one or more through holes are provided, and in a front-side end part of a first igniting case (ignition device) 119, afirst blocking body 121 to which a mechanism for firing a firstigniting powder 117 is attached is provided. Also, the firstigniting case 119 charged with the first igniting powder therein is arranged on the longitudinal axis line in the first combustion chamber. In the wall surface at a position at which the hollow part wall surface of thesecond propellant 115 is fired directly, one or more through holes are provided, and in the front-side end part of a secondigniting case 120, asecond blocking body 122 to which a mechanism for firing the secondigniting powder 118 is attached is provided. The second igniting case (ignition device) 120 charged with thesecond igniting powder 118 therein is disposed in the hollow part of thesecond propellant 115, and the outer peripheral end part thereof is fixed by the entire of circumference of a rocket motor shell part. Abarrier membrane 116 to which the inner peripheral end part of the secondigniting case 120 is fixed is provided between the firstigniting case 119 and the secondigniting case 120 so as to isolate thefirst propellant 114 and thesecond propellant 115 from each other (for example, Patent Document 2). - [Patent Document 1] Japanese Patent No. 3231778
- [Patent Document 2] Japanese Unexamined Patent Application Publication No. 2005-171970
- Generally, in the operation of a missile equipped with a two-pulse rocket motor (a solid propellant rocket motor which is capable of providing two separate and distinct propulsive impulses at expected time), the missile is accelerated by the first pulse (the propulsive impulse generated by first propellant combustion) and flies toward its target, and when it approaches the target, it is accelerated again by the second pulse (the propulsive impulse generated by second propellant combustion) to enhance maneuverability at the terminal guidance.
- Therefore, in the case of aiming at a remote target, it is necessary that first propellant mass consumed in the first pulse be increased to set burn time longer and/or thrust higher.
- However, as for the rocket motor shown in
FIGS. 12 and 14 , the first propellant cannot have enough length because the first propellant and the second propellant are set in the axial direction of the rocket motor, and the rocket motor length is limited for equipment or storage. - If the propellant cannot have enough length, the initial burning area may reduce and the necessary initial thrust cannot be achieved in the case that propellant grain design is an internal burning type as shown in
FIGS. 12 and 14 . - For a means of improving the initial thrust, it is effective to set the plural slits on the inner surface of the propellant to increase the initial burning area. In that case, however, since propellant mass in the slit portion is removed, the total impulse will reduce, which may deteriorate the performance.
- Also, if the first propellant is lengthened, the second propellant must be shortened because the rocket motor length is restricted. In that case, since the second propellant cannot have enough burning area and its combustion gas flow is generated insufficiently, the necessary thrust cannot be achieved at second propellant combustion with the nozzle which has the same throat diameter (the minimum diameter of exhaust hole) at first propellant combustion.
- Therefore, it is necessary an additional device that can change the nozzle throat diameter appropriately at each time of first and second propellant combustion, which increases structural weight.
- Also, since propellant grain design is such that the two propellants are set in the axial direction as shown in
FIGS. 12 and 14 , the thermal barrier membrane is exposed partly to high-temperature combustion gas from the beginning of first propellant combustion. Therefore, it is necessary to make the thermal barrier membrane thicker to protect the second propellant inside it from heat until the due time of second propellant combustion, which reduces propellant mass. - Further, the same can be said of ignition devices, so it is necessary to protect them from heat until the finish of second propellant combustion (they coming off, the nozzle may be closed), which increases structural weight.
- Also, as for the thermal barrier membrane and its holding structure shown in
FIGS. 12 and 14 , it is not clear either behavior (breaking properties) or condition of the remains of the thermal barrier membrane when the second igniter works. If the barrier membrane is broken in an unexpected portion, the second propellant cannot have enough burning area because the barrier membrane does not detach from the burning surface and cover it. - Further, if the barrier membrane is broken in the forward portion, most of it will turn over and detach from the second propellant toward the nozzle. In that case, combustion or combustion gas flows of the second propellant can be hindered, and at worst, the nozzle may be closed by the broken barrier membrane. In particular, the above-mentioned troubles occur remarkably for long or small-diameter two-pulse rocket motors.
- It is an object of this invention to provide a two-pulse rocket motor that can achieve the expected propulsive impulse and initial thrust of the first propellant and can reduce structural weight of heat protection for the thermal barrier membrane and the second igniter by the idea for propellant grain design and the placement of the second igniter.
- Also, another object of the present invention is to provide a two-pulse rocket motor in which combustion or combustion gas flows of the second propellant are not hindered by providing the barrier membrane and its holding structure considering good behavior and condition of the remains of the thermal barrier membrane and further providing a device considering the exposure of the burning surface of the second propellant and its ignitability when the second igniter works.
- The present invention solves the above-mentioned problems by the following means.
- A two-pulse rocket motor of a first means has a motor case containing a second propellant, a second igniter set on the end surface of the second propellant, a barrier membrane that covers the initial burning surface of the second propellant entirely and the second igniter, and a first propellant loaded so as to cover the barrier membrane entirely, and is characterized by the first propellant and the second propellant each have an internal burning type or an internal and end burning type of propellant grain design.
- A two-pulse rocket motor of a second means is, in the two-pulse rocket motor of the first means, characterized by the barrier membrane composed of an inner barrier membrane covering the inner surface of the second propellant and an aft barrier membrane covering the aft end surface of the second propellant, and the meeting edges of the aft barrier membrane and the inner barrier membrane are bonded throughout the entire periphery.
- A two-pulse rocket motor of a third means is, in the two-pulse rocket motor of the first means, characterized by the barrier membrane having slits on it.
- A two-pulse rocket motor of a fourth means is, in the two-pulse rocket motor of any one of the first to third means, characterized by the second igniter set on the aft end surface of the second propellant.
- A two-pulse rocket motor of a fifth means is, in the two-pulse rocket motor of any one of the first to fourth means, characterized by an igniter charge having higher ignitability and a higher burning rate than the second propellant set on the inner surface of the second propellant.
- A two-pulse rocket motor of a sixth means is, in the two-pulse rocket motor of the fifth means, characterized by the igniter charge set in plural slits, which are shaped on the inner surface of the second propellant in the axial direction around the longitudinal axis.
- The inventions described in the claims employ the above means and achieve the effects described below.
- According to the two-pulse rocket motor of the first means, the second propellant is set outside of the first propellant, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case, so that the initial burning area of the first pulse can be increased. Therefore, a large slit need not be provided in the inner surface of the first propellant, and a decrease in total thrust can be avoided.
- Also, the first propellant is set so as to cover the entire of barrier membrane, and the barrier membrane is protected from heat in the first half of first propellant combustion. Therefore, the plate thickness of barrier membrane can be decreased.
- Also, since the second propellant is set outside of the first propellant, the burning area of the second propellant does not become extremely smaller than the burning area of the first propellant, and a varying mechanism for the throat diameter of nozzle need not be provided, so that an increase in weight can be restrained.
- Also, the second propellant is protected from heat until the operation of the second propellant, and after the operation, there remains no component in the motor case. Therefore, the weight of heat-resisting material can be reduced.
- According to the two-pulse rocket motor of the second or third means, the barrier membrane is divided into two pieces and a joint part is provided to weaken a portion to be broken or a slit is formed in the barrier membrane to break the barrier membrane. Therefore, the barrier membrane is surely broken at an expected position (weak part) by the pressure of gas generated by the operation of the second igniter or second propellant combustion.
- Thereafter, the inner barrier membrane that occupies most of the barrier membrane deforms toward the center when being separated from the second propellant, and the holding part of barrier membrane after deformation lies in the front part of motor case where the flow due to combustion gas of the second propellant is relatively gentle, so that the survival properties are excellent.
- Also, since the aft barrier membrane itself after breakage is small, when being separated, the aft barrier membrane deforms naturally in the nozzle-side direction along the flow of combustion gas of the second propellant, so that the survival properties are excellent.
- Thus, by breaking the barrier membrane at the expected position, the deformation shape of barrier membrane after detachment is made in a state in which condition of the remains is excellent. Thereby, combustion gas of the second propellant is exhausted through the exhaust hole of nozzle in such a manner that the flow is not hindered by the barrier membrane.
- According to the two-pulse rocket motor of the fourth means, since the second igniter is set on the aft end surface of the second propellant, the weak part (joint part or slit) of barrier membrane or a portion to be broken of the barrier membrane can be broken more surely.
- According to the two-pulse rocket motor of the fifth means, since the igniter charge having higher ignitability and a higher burning rate than the second propellant is provided between the inner surface of the second propellant and the barrier membrane, the igniter charge is ignited earlier than the second propellant by the operation of the second igniter. Thereby, the separation of the inner barrier membrane or the inside portion of the barrier membrane (exposure of burning surface of the second propellant) and the ignition of the second propellant are assisted, so that the second propellant can be burned surely.
- Also, the invention of this means also has an effect that the pressure at the second pulse is raised quickly by combustion gas of igniter charge.
- According to the two-pulse rocket motor of the sixth means, since the igniter charge is set so as to match the shape of the inner surface of the second propellant, the degree of freedom can be given to the propellant shape of the second propellant.
-
FIG. 1 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a first embodiment of the present invention; -
FIG. 2 is a sectional view taken along the line A-A ofFIG. 1 ; -
FIG. 3 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a second embodiment of the present invention; -
FIG. 4 is a sectional view taken along the line B-B ofFIG. 3 ; -
FIG. 5 is a longitudinal sectional view showing a state in which a barrier membrane is deformed at the burn time of second propellant combustion in a two-pulse rocket motor in accordance with a second embodiment of the present invention; -
FIG. 6( a) is a sectional view taken along the line C-C ofFIG. 5 , andFIG. 6( b) is a sectional view taken along the line D-D ofFIG. 5 ; -
FIG. 7 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a third embodiment of the present invention; -
FIG. 8 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a fourth embodiment of the present invention; -
FIG. 9 is a sectional view taken along the line E-E ofFIG. 8 ; -
FIG. 10 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a fifth embodiment of the present invention; -
FIG. 11 is a sectional view taken along the line F-F ofFIG. 10 ; -
FIG. 12 is a configuration view of a conventional two-stage thrust type rocket motor; -
FIG. 13 is a detailed view of an ignition device means of the two-stage thrust type rocket motor shown inFIG. 12 ; -
FIG. 14 is a configuration view of another conventional two-stage thrust type rocket motor; and -
FIG. 15 is a detailed view of a first igniting case and a second igniting case of the two-stage thrust type rocket motor shown inFIG. 14 . -
- 1 motor case
- 2 nozzle
- 3 end plate
- 4 first propellant
- 5 second propellant
- 6 first igniter
- 8 second igniter
- 10 barrier membrane
- 10 a aft barrier membrane
- 10 b inner barrier membrane
- 11 burning region
- 12 exhaust hole
- 14 igniter charge
- Tow-pulse rocket motors in accordance with embodiments of the present invention are now described with reference to the accompanying drawings.
-
FIG. 1 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a first embodiment of the present invention, andFIG. 2 is a sectional view taken along the line A-A ofFIG. 1 . -
FIG. 3 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a second embodiment of the present invention, andFIG. 4 is a sectional view taken along the line B-B ofFIG. 3 . -
FIG. 5 is a longitudinal sectional view showing a state in which a barrier membrane is deformed at the burn time of second propellant combustion in the two-pulse rocket motor in accordance with the second embodiment of the present invention.FIG. 6( a) is a sectional view taken along the line C-C ofFIG. 5 , andFIG. 6( b) is a sectional view taken along the line D-D ofFIG. 5 . -
FIG. 7 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a third embodiment of the present invention. -
FIG. 8 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a fourth embodiment of the present invention, andFIG. 9 is a sectional view taken along the line E-E ofFIG. 8 . -
FIG. 10 is a longitudinal sectional view of a two-pulse rocket motor in accordance with a fifth embodiment of the present invention, andFIG. 11 is a sectional view taken along the line F-F ofFIG. 10 . - First, a two-pulse rocket motor in accordance with a first embodiment of the present invention is explained with reference to
FIGS. 1 and 2 . - The two-pulse rocket motor in accordance with the first embodiment burns a
first propellant 4 and subsequently burns asecond propellant 5 after arbitrary time has elapsed to produce two-stage thrust. - Therefore, during the time before combustion is started, the
second propellant 5 must withstand high-temperature combustion gas and a high pressure produced by combustion of thefirst propellant 4. - Also, it is desirable that the
first propellant 4 and thesecond propellant 5 can accommodate various thrust patterns by using acommon nozzle 2 by the contrivance of the arrangement and propellant shape thereof - As shown in
FIGS. 1 and 2 , thenozzle 2 having anexhaust hole 12 for exhausting combustion gas in the center therein is attached to the rear of acylindrical motor case 1. - To the front of the
motor case 1, anend plate 3 is attached, and to the front of theend plate 3, afirst igniter 6 for burning thefirst propellant 4 is attached. - On the inside of the
motor case 1, thefirst propellant 4 and thesecond propellant 5 each having a hollow and cylindrical shape (a propellant shape of an internal burning type or an internal and end burning type) are charged, and thesecond propellant 5 is set outside and the forward part of thefirst propellant 4. - The shape of each of the
first propellant 4 and thesecond propellant 5 can be a hollow cylindrical shape, a hollow tubular shape having polygonal inner surface and/or outer surface, a hollow conical shape, or the like shape. - The
first propellant 4 and thesecond propellant 5 are isolated from each other by abarrier membrane 10. - As being known publicly, as the
barrier membrane 10, a highly heat-resistant rubber such as silicone rubber or EPDM rubber, containing EPDM rubber, silicone rubber, and inorganic fiber such as Kevlar fiber as a composition thereof can be used. - At the front end of the
second propellant 5, asecond igniter 8 for burning thesecond propellant 5 is provided. - The
second igniter 8 is not limited to one having the above-described construction. For example, thesecond igniter 8 may be configured by atubular chamber 104, anozzle port 107, and the like shown inFIG. 13 (cited document 1). - The shapes of the
first propellant 4, thebarrier membrane 10, and thesecond propellant 5 are not limited to those shown inFIGS. 1 and 2 . The propellant shape, the propellant length, and the like can be set appropriately according to various thrust patterns. - The two-pulse rocket motor in accordance with the first embodiment of the present invention is configured as described above. The
first igniter 6 is operated by a signal sent from the outside, by which combustion of thefirst propellant 4 is started. At this point of time, thebarrier membrane 10 is not exposed to high-temperature combustion gas. - When the
first propellant 4 burns to the position of thebarrier membrane 10, thebarrier membrane 10 is exposed to high-temperature combustion gas. - After combustion of the
first propellant 4 has finished and arbitrary time has elapsed, thesecond igniter 8 is operated by a signal sent from the outside, by which combustion of thesecond propellant 5 is started. - According to the two-pulse rocket motor in accordance with the first embodiment of the present invention, the inner surface of the
first propellant 4 is exposed to a burningregion 11 throughout the almost entire length in the axial direction of themotor case 1. Therefore, the initial burning area can be secured, so that a large slit need not be provided in the inner surface of thefirst propellant 4. - Also, since the
second propellant 5 is set outside of thefirst propellant 4, the burning area of thesecond propellant 5 does not become extremely smaller than the burning area of thefirst propellant 4, so that thenozzle 2 for thefirst propellant 4 can be used commonly. - Also, since the
second propellant 5 is set outside of thefirst propellant 4 and thebarrier membrane 10 is provided therebetween, the time over which thebarrier membrane 10 is exposed to high-temperature combustion gas can be shortened as much as possible, so that thebarrier membrane 10 can be protected from heat. - Further, the
second igniter 8 is protected from heat by thebarrier membrane 10 like thesecond propellant 5, and is burned down by the operation, so that the protection from heat is not needed. - The initial burning surface of the
second propellant 5 in the present invention means a surface burned from the initial stage when thesecond propellant 5 begins to burn, that is, a surface exposed to the burningregion 11 first when thesecond propellant 5 is burned. In the example shown inFIG. 1 , the cylindrical inner surface on the inside of thesecond propellant 5 and the ring-shaped rear surface at the rear thereof are the initial burning surfaces. - Next, a two-pulse rocket motor in accordance with a second embodiment of the present invention is explained with reference to
FIGS. 3 to 6 . - In the two-pulse rocket motor in accordance with the second embodiment of the present invention, the
barrier membrane 10 is divided into two pieces, and a weak part (joint part) is provided as compared with the first embodiment of the present invention. - As shown in
FIGS. 3 and 4 , thebarrier membrane 10 covering thesecond propellant 5 is formed by a circular truncated cone shapedaft barrier membrane 10 a provided on the rear surface of thesecond propellant 5 and a cylindricalinner barrier membrane 10 b provided on the inner surface of thesecond propellant 5. - The end part in which the
aft barrier membrane 10 a and theinner barrier membrane 10 b meet provides the weak part formed by joining theaft barrier membrane 10 a and theinner barrier membrane 10 b to each other throughout the entire periphery by using a fire-resistant adhesive. The joint part is not broken during combustion of thefirst propellant 4, and is broken surely by the pressure of gas generated by the operation of thesecond igniter 8 or combustion of thesecond propellant 5. - Thereafter, as shown in
FIGS. 5 and 6 , theinner barrier membrane 10 b that occupies most of thebarrier membrane 10 deforms toward the center, and is held in the front part of motor case where the flow due to combustion gas of thesecond propellant 5 is relatively gentle. Also, the broken part of theaft barrier membrane 10 a deforms so as to be turned up to the rear along the flow of combustion gas. - According to the two-pulse rocket motor in accordance with the second embodiment of the present invention, in addition to the operation and effect of the first embodiment of the present invention, the breaking properties and the survival properties of the barrier membrane 10 (the
aft barrier membrane 10 a, theinner barrier membrane 10 b) are clear and reliable. - The configuration in which the
barrier membrane 10 is manufactured integrally and a slit is formed in a portion to be broken and the like configuration can achieve the same effect as that of the configuration in which thebarrier membrane 10 is divided into two pieces. - Next, a two-pulse rocket motor in accordance with a third embodiment of the present invention is explained with reference to
FIG. 7 . - In the two-pulse rocket motor in accordance with the third embodiment of the present invention, the
second igniter 8 is provided at a position close to the joint part of the barrier membrane 10 (theaft barrier membrane 10 a, theinner barrier membrane 10 b) on the rear end surface of thesecond propellant 5 as compared with the first and second embodiments of the present invention. - According to the two-pulse rocket motor in accordance with the third embodiment of the present invention, the operation and effect of the second embodiment of the present invention are improved, and the reliability of breaking of the barrier membrane 10 (the
aft barrier membrane 10 a, theinner barrier membrane 10 b) is increased. - Next, a two-pulse rocket motor in accordance with a fourth embodiment of the present invention is explained with reference to
FIGS. 8 and 9 . - In the two-pulse rocket motor in accordance with the fourth embodiment of the present invention, an
igniter charge 14 for thesecond propellant 5 is charged between the inner surface of thesecond propellant 5 and theinner barrier membrane 10 b as compared with the first to third embodiments of the present invention. - As shown in
FIGS. 8 and 9 , between the inner surface of thesecond propellant 5 and theinner barrier membrane 10 b, thecylindrical igniter charge 14 is charged. - The
igniter charge 14 used has higher ignitability and a higher burning rate than thesecond propellant 5. - The two-pulse rocket motor in accordance with the fourth embodiment of the present invention is configured as described above. In burning the
second propellant 5, thesecond igniter 8 is operated by a signal sent from the outside, and the gas generated by combustion of theigniter charge 14 assists the separation of theinner barrier membrane 10 b and the ignition of thesecond propellant 5. - According to the two-pulse rocket motor in accordance with the fourth embodiment of the present invention, in addition to the operation and effect of the third embodiment of the present invention, the
igniter charge 14 increases the reliability of the exposure and ignition of burning surface of thesecond propellant 5. - Next, a two-pulse rocket motor in accordance with a fifth embodiment of the present invention is explained with reference to
FIGS. 10 and 11 . - In the two-pulse rocket motor in accordance with the fifth embodiment of the present invention, the
igniter charge 14 for thesecond propellant 5 is charged by being divided into several pieces in the circumferential direction as compared with the fourth embodiment of the present invention. - As shown in
FIGS. 10 and 11 , plural slits (grooves) are shaped on the inner surface of thesecond propellant 5 in the axial direction around the longitudinal axis, in which theigniter charge 14 is set. - According to the two-pulse rocket motor in accordance with the fifth embodiment of the present invention, which is configured as described above, in addition to the operation and effect of the fourth embodiment of the present invention, the degree of freedom can be given to the propellant shape of the
second propellant 5 by arranging theigniter charge 14 so as to match the shape of the inner surface of thesecond propellant 5. - The above is an explanation of the embodiments of the present invention. However, the present invention is not limited to the above-described embodiments. It is a matter of course that various changes can be made within the scope of the present invention.
- For example, in order to surely break a portion to be broken of the
barrier membrane 10, two-pulse rocket motors consisting of combinations described below, including the combinations described in the above embodiments, can be embraced in the present invention. - (1) A two-pulse rocket motor in which, as shown in
FIGS. 3 to 6 , thesecond igniter 8 is set the forward part of thesecond propellant 5, thebarrier membrane 10 is divided into theaft barrier membrane 10 a and theinner barrier membrane 10 b, and the meeting edges of theaft barrier membrane 10 a and theinner barrier membrane 10 b are bonded throughout the entire periphery (by an adhesive etc.). - (2) A two-pulse rocket motor in which the
second igniter 8 is set the forward part of thesecond propellant 5, and thebarrier membrane 10 has slits on the expected breaking portion of it. - (3) A two-pulse rocket motor in which the
second igniter 8 is set on the aft end surface of thesecond propellant 5. - (4) A two-pulse rocket motor in which, as shown in
FIG. 7 , thebarrier membrane 10 is divided into theaft barrier membrane 10 a and theinner barrier membrane 10 b, and the meeting edges of theaft barrier membrane 10 a and theinner barrier membrane 10 b are bonded throughout the entire periphery (by an adhesive etc.), and thesecond igniter 8 is set on the aft end surface of thesecond propellant 5. - (5) A two-pulse rocket motor in which the
barrier membrane 10 has slits on the expected breaking portion of it, and thesecond igniter 8 is set on the aft end surface of thesecond propellant 5. - (6) A two-pulse rocket motor in which the
second igniter 8 is set the forward part of thesecond propellant 5, and theigniter charge 14 having higher ignitability and a higher burning rate than thesecond propellant 5 is set on the inner surface of thesecond propellant 5. - (7) A two-pulse rocket motor in which the
barrier membrane 10 is divided into theaft barrier membrane 10 a and theinner barrier membrane 10 b, and the meeting edges of theaft barrier membrane 10 a and theinner barrier membrane 10 b are bonded throughout the entire periphery (by an adhesive etc.), thesecond igniter 8 is set the forward part of thesecond propellant 5, and theigniter charge 14 having higher ignitability and a higher burning rate than thesecond propellant 5 is set on the inner surface of thesecond propellant 5. - (8) A two-pulse rocket motor in which the
second igniter 8 is set on the aft end surface of thesecond propellant 5, and theigniter charge 14 having higher ignitability and a higher burning rate than thesecond propellant 5 is set on the inner surface of thesecond propellant 5. - (9) A two-pulse rocket motor in which, as shown in
FIGS. 8 and 9 , thebarrier membrane 10 is divided into theaft barrier membrane 10 a and theinner barrier membrane 10 b, and the meeting edges of theaft barrier membrane 10 a and theinner barrier membrane 10 b are bonded throughout the entire periphery (by an adhesive etc.), thesecond igniter 8 is set on the aft end surface of thesecond propellant 5, and theigniter charge 14 having higher ignitability and a higher burning rate than thesecond propellant 5 is set on the inner surface of thesecond propellant 5. - (10) A two-pulse rocket motor in which the
barrier membrane 10 has slits on the expected breaking portion of it, thesecond igniter 8 is set on the aft end surface of thesecond propellant 5, and theigniter charge 14 having higher ignitability and a higher burning rate than thesecond propellant 5 is set on the inner surface of thesecond propellant 5. - (11) A two-pulse rocket motor in which the
second igniter 8 is set the forward part of thesecond propellant 5, and theigniter charge 14 is set in the plural slits shaped on the inner surface of thesecond propellant 5 in the axial direction around the longitudinal axis. - (12) A two-pulse rocket motor in which the
barrier membrane 10 is divided into theaft barrier membrane 10 a and theinner barrier membrane 10 b, and the meeting edges of theaft barrier membrane 10 a and theinner barrier membrane 10 b are bonded throughout the entire periphery (by an adhesive etc.), thesecond igniter 8 is set the forward part of thesecond propellant 5, and theigniter charge 14 is set in the plural slits shaped on the inner surface of thesecond propellant 5 in the axial direction around the longitudinal axis. - (13) A two-pulse rocket motor in which the
second igniter 8 is set on the aft end surface of thesecond propellant 5, and theigniter charge 14 is set in the plural slits shaped on the inner surface of thesecond propellant 5 in the axial direction around the longitudinal axis. - (14) A two-pulse rocket motor in which, as shown in
FIGS. 10 and 11 , thebarrier membrane 10 is divided into theaft barrier membrane 10 a and theinner barrier membrane 10 b, and the meeting edges of theaft barrier membrane 10 a and theinner barrier membrane 10 b are bonded throughout the entire periphery (by an adhesive etc.), thesecond igniter 8 is set on the aft end surface of thesecond propellant 5, and theigniter charge 14 is set in the plural slits shaped on the inner surface of thesecond propellant 5 in the axial direction around the longitudinal axis. - (15) A two-pulse rocket motor in which the
barrier membrane 10 has slits on the expected breaking portion of it, thesecond igniter 8 is set on the aft end surface of thesecond propellant 5, and theigniter charge 14 is set in the plural slits shaped on the inner surface of thesecond propellant 5 in the axial direction around the longitudinal axis.
Claims (4)
1. A two-pulse rocket motor having a motor case, comprising:
a first propellant;
a second propellant;
a second igniter set on an end surface of the second propellant;
a barrier membrane that covers an initial burning surface of the second propellant entirely and the second igniter; and wherein
the first propellant is loaded so as to cover the barrier membrane entirely, and wherein
the first propellant and the second propellant each has an internal burning type or an internal and end burning type of propellant grain design, and
wherein the barrier membrane has notches on it.
2. The two-pulse rocket motor according to claim 1 , wherein the second igniter is set on an aft end surface of the second propellant.
3. The two-pulse rocket motor according to claim 1 , wherein an igniter charge having higher ignitability and a higher burning rate than the second propellant is set on an inner surface of the second propellant.
4. The two-pulse rocket motor according to claim 3 , wherein an igniter charge is set in plural slots, which are shaped on the inner surface of the second propellant in the axial direction around the longitudinal axis.
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US13/708,338 US20130118147A1 (en) | 2007-05-14 | 2012-12-07 | Two-pulse rocket motor |
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JP2007127801A JP4719182B2 (en) | 2007-05-14 | 2007-05-14 | 2-pulse rocket motor |
JP2007-127801 | 2007-05-14 | ||
PCT/JP2008/058648 WO2008143033A1 (en) | 2007-05-14 | 2008-05-09 | Dual-pulse rocket motor |
US59987409A | 2009-11-12 | 2009-11-12 | |
US13/708,338 US20130118147A1 (en) | 2007-05-14 | 2012-12-07 | Two-pulse rocket motor |
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PCT/JP2008/058648 Division WO2008143033A1 (en) | 2007-05-14 | 2008-05-09 | Dual-pulse rocket motor |
US59987409A Division | 2007-05-14 | 2009-11-12 |
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US12/599,874 Active 2030-01-16 US8397486B2 (en) | 2007-05-14 | 2008-05-09 | Two-pulse rocket motor |
US13/708,338 Abandoned US20130118147A1 (en) | 2007-05-14 | 2012-12-07 | Two-pulse rocket motor |
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- 2008-05-09 US US12/599,874 patent/US8397486B2/en active Active
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2012
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170058835A1 (en) * | 2014-03-26 | 2017-03-02 | Mitsubishi Heavy Industries, Ltd. | Combustor, jet engine, flying body, and operation method of jet engine |
US10697397B2 (en) | 2014-03-26 | 2020-06-30 | Mitsubishi Heavy Industries, Ltd. | Combustor, jet engine, flying body, and operation method of jet engine |
US11067036B2 (en) * | 2014-03-26 | 2021-07-20 | Mitsubishi Heavy Industries, Ltd. | Combustor and jet engine having the same |
US11415081B2 (en) * | 2020-03-17 | 2022-08-16 | Mitsubishi Heavy Industries, Ltd. | Multi-pulse gas generator device and igniter with varied flow rates |
Also Published As
Publication number | Publication date |
---|---|
US8397486B2 (en) | 2013-03-19 |
JP2008280967A (en) | 2008-11-20 |
US20100218481A1 (en) | 2010-09-02 |
JP4719182B2 (en) | 2011-07-06 |
WO2008143033A1 (en) | 2008-11-27 |
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