US2481059A - Adjustable rocket nozzle - Google Patents

Adjustable rocket nozzle Download PDF

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Publication number
US2481059A
US2481059A US551574A US55157444A US2481059A US 2481059 A US2481059 A US 2481059A US 551574 A US551574 A US 551574A US 55157444 A US55157444 A US 55157444A US 2481059 A US2481059 A US 2481059A
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Prior art keywords
nozzle
rocket
holes
motor
temperature
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Expired - Lifetime
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US551574A
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Africano Alfred
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United States, WAR, Secretary of
US SEC WAR
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US SEC WAR
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/665—Steering by varying intensity or direction of thrust characterised by using a nozzle provided with at least a deflector mounted within the nozzle
    • 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
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control

Definitions

  • This invention relates to an adjustable nozzle for rocket propelled projectiles.
  • the propellent material frequently used in rocket projectiles comprises a double ⁇ base powder.
  • the burning rate of such powder inherently varies considerably with the temperature of the powder.
  • the optimum performance of a rocket projectile can be obtained only when the powder temperature is such that the burning rate will produce a certain equilibrium operating pressure within the rocket.
  • the mass rate of formation of the combustion products will be increased by the increased burning rate.
  • an object of this invention to provide an adjustable nozzle for a rocket projectile to permit such rocket projectile to be operative under extreme variations in atmospheric temperature.
  • Cil Fig. 3 is a detail longitudinal cross sectional view of the nozzle shown in Fig. 1.
  • Fig. 4 is a side elevational view of the lockin collar showing the port opening graduations.
  • Fig. 5 is a detail longitudinal sectional view of the adjustable rocket nozzle adapter.
  • Fig. 6 is a fragmentary side elevational view of a.l rocket motor showing a modified form of an adjustable rocket nozzle.
  • Fig. 7 is a longitudinal sectional view taken along the plane 1-1 of Fig. 6.
  • Fig. 8 is a cross sectional view taken along the plane 8-8 of Fig. 7.
  • the rockets of this invention consist mainly of a combustion chamber containing the double base propellent material, a nozzle having a conother objects and advantages thereof will clearly 55 stricted port opening or throat formed at the rear of the chamber and a pay load carried by the motor.
  • the equilibrium pressure developed within such a rocket motor chamber is dependent upon the rate of discharge of the gases as well as upon their rate of formation.
  • the equilibrium pressure can be regulated by adjusting the port opening for the discharge of the combustion products.
  • an adjustable port area for the discharge of the combustion gases is readily obtained by providing a plurality of auxiliary jets formed in the motor chamber just forward of the throat where the walls of the chamber converge to form the approach to the nozzle throat and providing means for varying the area of such auxiliary jets.
  • Fig. 1 there is shown a rear portion of a rocket motor I.
  • a cup shaped nozzle adapter 2 is welded to the end of rocket motor l, a suitable bearing surface and locking shoulder as shown at 3 being preferably provided to increase the rigidity of support of the nozzle adapter 2.
  • the inside corner 4 of the forward end of nozzle adapter 2 is rounded as shown in Fig. 1 so as not 35"' to obstruct the flow of propellent gases thru the nozzle.
  • An axial hole 5 is provided in the end of nozzle adapter 2 thru which is inserted a nozzle 6.
  • the nozzle 6 is a cylindrical tube provided at the forward end with an integral ange I.
  • the flange 'I bears against the inside surface of the end of nozzle adapter 2.
  • a plurality of radially disposed holes 8 are provided. in flange 'I of nozzle 6.
  • a corresponding number of identical holes 9 are likewise radially disposed about the face of nozzle adapter 2.
  • Holes 8 in the flange 'I of nozzle 6 can be readily brought into alignment with holes 9 in the nozzle adapter 2 by merely rotating nozzle 6 until such holes are in alignment.
  • a locking collar I Il is provided to lock nozzle 6 in any desired position so that holes 8 may be wholly or partially aligned with holes 9.
  • Collar I is secured to nozzle 6 as by threads II provided on the outer periphery of nozzle 6.
  • the outer surface I2 of locking collar I0' is preferably knurled to provide a nonslipping, grasping surface.
  • nozzle 6 may be locked with the holes 8 open or closed or in any other desired position by simply screwing collar I0 tightly against the end of nozzle adapter 2. This procedure draws the inside of flange I tightly against the inside of nozzle adapter 2 thereby locking nozzle 6 to nozzle adapter 2, If desired suitable temperature graduation marks Il may be provided in the periphery of collarl I0 to indicate the proper port opening for any particular atmospheric temperature.
  • the port area of the rocket motor may be varied to permit greater or lesser escape of propellent gases through the port.
  • holes 8 may be brought into alignment with holes 9 by unloosening collar I IJ and revolving nozzle 6 until such alignment is effected whereupon collar I Il is again tightened.
  • the holes 8 exposed to the atmosphere it is obvious that greatly increased port area is available and hence the propellent gases can escape more readily in order that equilibrium may be retained within rocket motor I when high temperatures are prevalent and the burning rate of powder is exceedingly high.
  • the holes 9 may be closed by turning nozzle 6 a suflicient amount to block the holes. The port area is thereby lessened and as there is less escape of the propellent gases, greater pressure can be built up within rocket motor I. Hence faster burning of the propellent charge will be promoted and will thus sustain ignition of such charge.
  • FIG. '1 A modification of the adjustable nozzle is illustrated in Fig. '1.
  • a rocket motor I4 is iiared inwardly to form a conical section as shown at I5.
  • Adjacent conical section I5 a reduced diameter portion I6 is provided and such portion has threads I'I thereon.
  • a nozzle I8 is screwed onto threads II.
  • 'I'he nozzle I8 defines an orifice 26 and is provided with a conical interior surface I9 which mates with conical surface I 5 on the rear end of rocket motor I.
  • a plurality of collapsible ns 20 are pivotally secured to the rear end of nozzle I8 asshown inFigs.6 and7.
  • are provided spaced about the conical surface I5 of rocket motor I.
  • Corresponding holes 22 are provided in conical surface I9 of nozzle I8.
  • the holes 2i in rocket motor I may be either Wholly or partially blocked oil by simply rotating nozzle I8 suiiiciently to produce the desired blocking eect.
  • Nozzle I8 may then be locked by tightening a plurality of screws 23. Such screws are .inserted in suitable slots 24 in nozzle I8 and engage tapped holes in'rocket motor I.
  • a graduated temperature scale 25 is preferably prov ded about the periphery of rocket motor I as shown in Fig. 6 to indicate the proper port opening' to be utilized for particular ambient temperature.
  • a rocket motor embodying this invention can be readily adjusted to compensate for variations in atmospheric temperature which strongly affect the burning time of the propellent material generally utilized in rocket projectiles.
  • the rate of burning of the propellent material can be controlled to a very large degree which in turn controls the internal pressure within the rocket motor.
  • this invention is independent of the shape o! the holes 8 and 9 as such could take a variety of forms.
  • a nozzle for a rocket motor including a first cylindrical member having a fianged surface extending generally inwardly thereof, said surface having a plurality of openings formed therein, a second member of smaller cross section than said first member forming a constriction and discharge passage for the propulsion iiuid within said motor, said second member having a flanged surface extending outwardly therefrom and conforming generally with the anged surface of said first member, said fianged surface of said second member also having a plurality of openings therein, means securing said first and second members to said motor with their respective fianged surfaces abutting, said means permitting relative rotational movement to vary the overlapping portions of said opening to vary the port area for discharge of the propulsion fluid of said motor, and means locking said first and second members against relative angular movement.

Description

@t 6, H949. A. AFRlcANo 4819059 ADJUSTABLE ROCKET NOZZLE V 2 Sheets-Sheet l Filed Aug. 28, 1944 O N A R F A A.
ADJUSTABLE ROCKET NOZZLE 2 Sheets-Sheetl 2 Filed Aug. 28, 1944 D Wn wi mwxm A d E :m A
atented Sept. 6, 1949v ADJUSTABLE ROCKET NOZZLE Alfred Africano, Cumberland, Md., assigner to the United States of America. as represented by the Secretary of War Application August 28, 1944, Serial No. 551,574
1 Claim. (Cl. 60-35.6)
This invention relates to an adjustable nozzle for rocket propelled projectiles.
The propellent material frequently used in rocket projectiles comprises a double `base powder. The burning rate of such powder inherently varies considerably with the temperature of the powder. The optimum performance of a rocket projectile can be obtained only when the powder temperature is such that the burning rate will produce a certain equilibrium operating pressure within the rocket. In other Words, if the temperature of the powder rises above the optimum temperature to produce a burning rate required for the desired equilibrium conditions, the mass rate of formation of the combustion products will be increased by the increased burning rate.
Conversely, if the temperature of the powder is lower than the prescribed optimum temperature for such powder the mass rate of formation of the combustion products will then be decreased by the lower burning rate of the powder. At
equilibrium conditions the mass rate of formation up the pressure within the rocket motor chamber,
frequently beyond safe limits. As it has been theoretically shown and substantiated by experiment that the dispersion of a rocket increases as the cube of the burning time of powder, it is apparent that an increase in the burning timeis not desired from a ballistic standpoint. Further, if the temperature of the powder falls so low that pressure will not be built up within the chamber, it is extremely difcult to sustain ignition of the powder charge.
Because burning rates of the particular powder propellants which are used in prior art motors are sensitive to temperature variations it has been found necessary to limit the temperature range of operation of the rocket and to design such rocket for optimum performance only thru the upper limit of the range of atmospheric temperatures.
Accordingly, it is an object of this invention to provide an adjustable nozzle for a rocket projectile to permit such rocket projectile to be operative under extreme variations in atmospheric temperature.
The specic nature of the invention as well as Cil Fig. 3 is a detail longitudinal cross sectional view of the nozzle shown in Fig. 1.
Fig. 4 is a side elevational view of the lockin collar showing the port opening graduations.
Fig. 5 is a detail longitudinal sectional view of the adjustable rocket nozzle adapter.
Fig. 6 is a fragmentary side elevational view of a.l rocket motor showing a modified form of an adjustable rocket nozzle.
Fig. 7 is a longitudinal sectional view taken along the plane 1-1 of Fig. 6.
Fig. 8 is a cross sectional view taken along the plane 8-8 of Fig. 7.
The rockets of this invention consist mainly of a combustion chamber containing the double base propellent material, a nozzle having a conother objects and advantages thereof will clearly 55 stricted port opening or throat formed at the rear of the chamber and a pay load carried by the motor. The equilibrium pressure developed within such a rocket motor chamber is dependent upon the rate of discharge of the gases as well as upon their rate of formation. Thus, the equilibrium pressure can be regulated by adjusting the port opening for the discharge of the combustion products. In order to obtain a substantially constant motor chamber pressure at all i temperatures within the operating range, it would be necessary to increase or decrease the port opening with an increase or decrease in pressure to provide a greater or smaller discharge rate to compensate for the higher or lower rates of burn- 111g.
In accordance with this invention an adjustable port area for the discharge of the combustion gases is readily obtained by providing a plurality of auxiliary jets formed in the motor chamber just forward of the throat where the walls of the chamber converge to form the approach to the nozzle throat and providing means for varying the area of such auxiliary jets.
In Fig. 1 there is shown a rear portion of a rocket motor I. A cup shaped nozzle adapter 2 is welded to the end of rocket motor l, a suitable bearing surface and locking shoulder as shown at 3 being preferably provided to increase the rigidity of support of the nozzle adapter 2. The inside corner 4 of the forward end of nozzle adapter 2 is rounded as shown in Fig. 1 so as not 35"' to obstruct the flow of propellent gases thru the nozzle. An axial hole 5 is provided in the end of nozzle adapter 2 thru which is inserted a nozzle 6. The nozzle 6 is a cylindrical tube provided at the forward end with an integral ange I. The flange 'I bears against the inside surface of the end of nozzle adapter 2.
A plurality of radially disposed holes 8 are provided. in flange 'I of nozzle 6. A corresponding number of identical holes 9 are likewise radially disposed about the face of nozzle adapter 2. Holes 8 in the flange 'I of nozzle 6 can be readily brought into alignment with holes 9 in the nozzle adapter 2 by merely rotating nozzle 6 until such holes are in alignment. A locking collar I Il is provided to lock nozzle 6 in any desired position so that holes 8 may be wholly or partially aligned with holes 9. Collar I is secured to nozzle 6 as by threads II provided on the outer periphery of nozzle 6. The outer surface I2 of locking collar I0' is preferably knurled to provide a nonslipping, grasping surface. Hence nozzle 6 may be locked with the holes 8 open or closed or in any other desired position by simply screwing collar I0 tightly against the end of nozzle adapter 2. This procedure draws the inside of flange I tightly against the inside of nozzle adapter 2 thereby locking nozzle 6 to nozzle adapter 2, If desired suitable temperature graduation marks Il may be provided in the periphery of collarl I0 to indicate the proper port opening for any particular atmospheric temperature.
From the above description it is readily apparent to any one skilled in the art that the port area of the rocket motor may be varied to permit greater or lesser escape of propellent gases through the port. In the event of high temperatures where rapid burning time of the propellant may be anticipated, holes 8 may be brought into alignment with holes 9 by unloosening collar I IJ and revolving nozzle 6 until such alignment is effected whereupon collar I Il is again tightened. With holes 8 exposed to the atmosphere it is obvious that greatly increased port area is available and hence the propellent gases can escape more readily in order that equilibrium may be retained within rocket motor I when high temperatures are prevalent and the burning rate of powder is exceedingly high. Conversely, if the temperature is low, the holes 9 may be closed by turning nozzle 6 a suflicient amount to block the holes. The port area is thereby lessened and as there is less escape of the propellent gases, greater pressure can be built up within rocket motor I. Hence faster burning of the propellent charge will be promoted and will thus sustain ignition of such charge.
A modification of the adjustable nozzle is illustrated in Fig. '1. Referring to Fig. 7 the extreme rear end of a rocket motor I4 is iiared inwardly to form a conical section as shown at I5. Adjacent conical section I5 a reduced diameter portion I6 is provided and such portion has threads I'I thereon. A nozzle I8 is screwed onto threads II. 'I'he nozzle I8 defines an orifice 26 and is provided with a conical interior surface I9 which mates with conical surface I 5 on the rear end of rocket motor I. A plurality of collapsible ns 20 are pivotally secured to the rear end of nozzle I8 asshown inFigs.6 and7.
7u Number A plurality of holes 2| are provided spaced about the conical surface I5 of rocket motor I. Corresponding holes 22 are provided in conical surface I9 of nozzle I8. The holes 2i in rocket motor I may be either Wholly or partially blocked oil by simply rotating nozzle I8 suiiiciently to produce the desired blocking eect. Nozzle I8 may then be locked by tightening a plurality of screws 23. Such screws are .inserted in suitable slots 24 in nozzle I8 and engage tapped holes in'rocket motor I. Thus the port area of the rocket may be readily varied by slight rotation of nozzle I8 with respect to motor I4. A graduated temperature scale 25 is preferably prov ded about the periphery of rocket motor I as shown in Fig. 6 to indicate the proper port opening' to be utilized for particular ambient temperature.
From the foregoing description it is apparent that a rocket motor embodying this invention can be readily adjusted to compensate for variations in atmospheric temperature which strongly affect the burning time of the propellent material generally utilized in rocket projectiles. By increasing or decreasing the port area of the rocket projectile the rate of burning of the propellent material can be controlled to a very large degree which in turn controls the internal pressure within the rocket motor. It should be understood that this invention is independent of the shape o! the holes 8 and 9 as such could take a variety of forms.
I claim:
In combination, a nozzle for a rocket motor including a first cylindrical member having a fianged surface extending generally inwardly thereof, said surface having a plurality of openings formed therein, a second member of smaller cross section than said first member forming a constriction and discharge passage for the propulsion iiuid within said motor, said second member having a flanged surface extending outwardly therefrom and conforming generally with the anged surface of said first member, said fianged surface of said second member also having a plurality of openings therein, means securing said first and second members to said motor with their respective fianged surfaces abutting, said means permitting relative rotational movement to vary the overlapping portions of said opening to vary the port area for discharge of the propulsion fluid of said motor, and means locking said first and second members against relative angular movement.
ALFRED AFRICANO.
REFERENCES CITED The following references are oi' record in the file of this patent:
UNITED STATES PATENTS Name Date Shoots Sept. 15, 1896 Allen Nov. 13, 1906 Monfee Apr. 17, 1917 Vedovelli Sept. 22, 1931 Herwig Dec. 22, 1931 Hoagland Dec. 10, 1946 FOREIGN PATENTS Country Date Great Britain July 11, 1921 Number
US551574A 1944-08-28 1944-08-28 Adjustable rocket nozzle Expired - Lifetime US2481059A (en)

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Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2590272A (en) * 1948-06-21 1952-03-25 Boeing Co Adjustable jet orifice
US2612747A (en) * 1945-01-25 1952-10-07 Leslie A Skinner Rocket having adjustable discharge passage
US2762193A (en) * 1953-02-03 1956-09-11 Scaife Company Welded end closure means for rocket motors
US2956400A (en) * 1957-06-05 1960-10-18 Curtiss Wright Corp Internal-ribbed exhaust nozzle for jet propulsion devices
US2958184A (en) * 1950-10-17 1960-11-01 Aerojet General Co Jet propulsion motor with safety pressure relief means
US2972225A (en) * 1950-12-04 1961-02-21 James M Cumming Motor mechanism for missiles
US2978866A (en) * 1957-09-30 1961-04-11 Curtiss Wright Corp Adjustable nozzle for rocket
US3003312A (en) * 1957-08-19 1961-10-10 Thompson Ramo Wooldridge Inc Exhaust nozzle for jet engines
US3048112A (en) * 1959-02-06 1962-08-07 Phillips Petroleum Co Gas generator
US3102383A (en) * 1961-06-05 1963-09-03 Martin A Rex Temperature compensated catapult
US3177655A (en) * 1961-01-24 1965-04-13 Thiokol Chemical Corp Rocket motor thrust termination and reversal device
US3341129A (en) * 1964-07-13 1967-09-12 Atlantic Res Corp Rocket nozzle
US3367112A (en) * 1965-10-18 1968-02-06 Mb Assoc Multiple plate rocket nozzle
US3442083A (en) * 1967-07-21 1969-05-06 Avco Corp Adjustable variable thrust propulsion device
US3478965A (en) * 1966-10-19 1969-11-18 Thomas E Llewellyn Variable thrust rocket engine
US3712546A (en) * 1970-05-08 1973-01-23 Messerschmitt Boelkow Blohm Rocket engine exhaust nozzle with boundary layer control
US4378674A (en) * 1981-03-26 1983-04-05 Thiokol Corporation Variable aperture annular nozzle for rocket motor igniter
US4432512A (en) * 1978-08-31 1984-02-21 British Aerospace Public Limited Company Jet propulsion efflux outlets
FR2614650A1 (en) * 1987-04-30 1988-11-04 Messerschmitt Boelkow Blohm SHUTTERING DEVICE FOR HOT GASES LOADED WITH PARTICLES, IN PARTICULAR FOR CONTROLLING THE FLOW RATE OF FUEL-RICH HOT GASES COMING OUT OF THE PRE-COMBUSTION CHAMBER OF A SOLID PROPERGOL STATOREACTOR
US4967599A (en) * 1980-05-19 1990-11-06 Societe Europeenne De Propulsion Mechanical and insulating connection between a nozzle and the filament-wound casing of the combustion chamber of a solid propellant rocket motor
US20070163227A1 (en) * 2006-01-17 2007-07-19 Aerojet-General Corporation Nozzles with rotatable sections for variable thrust
US10000289B2 (en) 2012-02-02 2018-06-19 Senior Ip Gmbh Temperature control gasper apparatus
US20190153820A1 (en) * 2016-07-07 2019-05-23 Impulse Downhole Solutions Ltd. Flow-through pulsing assembly for use in downhole operations

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US212266A (en) * 1879-02-11 Improvement in stove-linings
US567925A (en) * 1896-09-15 Spray-nozzle
US835928A (en) * 1906-05-10 1906-11-13 Felix W Allen Nozzle for leaching-vats.
US1222972A (en) * 1916-05-24 1917-04-17 Andrew Jackson Monfee Blow-off valve.
GB166583A (en) * 1919-05-09 1921-07-11 Mordoukhaj Wassermann Improvements in or relating to explosive shells
US1824518A (en) * 1925-02-27 1931-09-22 Mrs E Vedovelli Water displaying and illuminating device
US1837549A (en) * 1931-12-22 A cobpokatioil of oiiio

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US212266A (en) * 1879-02-11 Improvement in stove-linings
US567925A (en) * 1896-09-15 Spray-nozzle
US1837549A (en) * 1931-12-22 A cobpokatioil of oiiio
US835928A (en) * 1906-05-10 1906-11-13 Felix W Allen Nozzle for leaching-vats.
US1222972A (en) * 1916-05-24 1917-04-17 Andrew Jackson Monfee Blow-off valve.
GB166583A (en) * 1919-05-09 1921-07-11 Mordoukhaj Wassermann Improvements in or relating to explosive shells
US1824518A (en) * 1925-02-27 1931-09-22 Mrs E Vedovelli Water displaying and illuminating device

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2612747A (en) * 1945-01-25 1952-10-07 Leslie A Skinner Rocket having adjustable discharge passage
US2590272A (en) * 1948-06-21 1952-03-25 Boeing Co Adjustable jet orifice
US2958184A (en) * 1950-10-17 1960-11-01 Aerojet General Co Jet propulsion motor with safety pressure relief means
US2972225A (en) * 1950-12-04 1961-02-21 James M Cumming Motor mechanism for missiles
US2762193A (en) * 1953-02-03 1956-09-11 Scaife Company Welded end closure means for rocket motors
US2956400A (en) * 1957-06-05 1960-10-18 Curtiss Wright Corp Internal-ribbed exhaust nozzle for jet propulsion devices
US3003312A (en) * 1957-08-19 1961-10-10 Thompson Ramo Wooldridge Inc Exhaust nozzle for jet engines
US2978866A (en) * 1957-09-30 1961-04-11 Curtiss Wright Corp Adjustable nozzle for rocket
US3048112A (en) * 1959-02-06 1962-08-07 Phillips Petroleum Co Gas generator
US3177655A (en) * 1961-01-24 1965-04-13 Thiokol Chemical Corp Rocket motor thrust termination and reversal device
US3102383A (en) * 1961-06-05 1963-09-03 Martin A Rex Temperature compensated catapult
US3341129A (en) * 1964-07-13 1967-09-12 Atlantic Res Corp Rocket nozzle
US3367112A (en) * 1965-10-18 1968-02-06 Mb Assoc Multiple plate rocket nozzle
US3478965A (en) * 1966-10-19 1969-11-18 Thomas E Llewellyn Variable thrust rocket engine
US3442083A (en) * 1967-07-21 1969-05-06 Avco Corp Adjustable variable thrust propulsion device
US3712546A (en) * 1970-05-08 1973-01-23 Messerschmitt Boelkow Blohm Rocket engine exhaust nozzle with boundary layer control
US4432512A (en) * 1978-08-31 1984-02-21 British Aerospace Public Limited Company Jet propulsion efflux outlets
US4967599A (en) * 1980-05-19 1990-11-06 Societe Europeenne De Propulsion Mechanical and insulating connection between a nozzle and the filament-wound casing of the combustion chamber of a solid propellant rocket motor
US4378674A (en) * 1981-03-26 1983-04-05 Thiokol Corporation Variable aperture annular nozzle for rocket motor igniter
FR2614650A1 (en) * 1987-04-30 1988-11-04 Messerschmitt Boelkow Blohm SHUTTERING DEVICE FOR HOT GASES LOADED WITH PARTICLES, IN PARTICULAR FOR CONTROLLING THE FLOW RATE OF FUEL-RICH HOT GASES COMING OUT OF THE PRE-COMBUSTION CHAMBER OF A SOLID PROPERGOL STATOREACTOR
US20070163227A1 (en) * 2006-01-17 2007-07-19 Aerojet-General Corporation Nozzles with rotatable sections for variable thrust
US10000289B2 (en) 2012-02-02 2018-06-19 Senior Ip Gmbh Temperature control gasper apparatus
US20190153820A1 (en) * 2016-07-07 2019-05-23 Impulse Downhole Solutions Ltd. Flow-through pulsing assembly for use in downhole operations
US10968721B2 (en) * 2016-07-07 2021-04-06 Impulse Downhole Solutions Ltd. Flow-through pulsing assembly for use in downhole operations
US20210198979A1 (en) * 2016-07-07 2021-07-01 Impulse Downhole Solutions Ltd. Flow-through pulsing assembly for use in downhole operations
US11788382B2 (en) * 2016-07-07 2023-10-17 Impulse Downhole Solutions Ltd. Flow-through pulsing assembly for use in downhole operations

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