US3844118A - Aft inlet ramjet powered missile - Google Patents

Aft inlet ramjet powered missile Download PDF

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Publication number
US3844118A
US3844118A US00392380A US39238073A US3844118A US 3844118 A US3844118 A US 3844118A US 00392380 A US00392380 A US 00392380A US 39238073 A US39238073 A US 39238073A US 3844118 A US3844118 A US 3844118A
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United States
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fuel grain
air
fuel
grain
inlet
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Expired - Lifetime
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US00392380A
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D Wilkinson
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US Air Force
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US Air Force
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Priority to US00392380A priority Critical patent/US3844118A/en
Priority to GB3725874A priority patent/GB1421719A/en
Priority to CA207,893A priority patent/CA991418A/en
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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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/18—Composite ram-jet/rocket engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/105—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines using a solid fuel

Definitions

  • ABSTRACT A solid fuel ramjet powered missile having the air inlsz] Cl gy g gg gg lets positioned adjacent the aft end of the fuel grain [5 1 1 Int Cl F02k 7/10 with a channel provided adjacent the fuel grain to pro- [58] Fieid 253 256 vide primary air into the forward end of the fuel grain 261 with the secondary air being supplied directly to the secondary combustor.
  • a valve is provided in the pri- [56] References Cited znai'y air flow channel to control the air flow into the UNITED STATES PATENTS gram 2,977,753 4/1961 Boulet 60/270 R 2 Claims 2 Drawing Figures 1 AFT INLET RAMJET POWERED MISSILE I BACKGROUND OF THE INVENTION Solid fuel ramjet powered missiles have several advantages over liquid fuel ramjets. The fuel is safer because fuel leakage cannot occur. Also, burning is more stable since the hot fuel grain tends to stabilize combustion in the primary zone and fuel utilization automatically responds to changes in altitude and velocity.
  • the engine air inlet is placed forward of the forward end of the fuel grain with bypass channels being provided to channel air to the secondary combustor as in the US. Pat. to Chandler No. 2,799,987. Since the primary air flow is normally only a small percentage of the total flow, large ducts are required to supply the major portion of the air to the secondary combustor. Also, since the rate of burning of the fuel grain is a function of the exposed area, either the fuel grain has to be specially designed to provide a uniform burning rate or an uneven burning rate with poor thrust control will result.
  • the air inlets are positioned near the aft end of the fuel grain to provide increased missile stability since the static aerodynamic stability of the missile is reduced as the inlets are moved forward. With the aft inlets, the large air flow is directly into the secondary combustor which reduces pipe flow losses. Also, since the primary air flow is normally much less than the secondary air flow, a smaller size duct can be used for primary air flow thus reducing the overall weight of the missile.
  • a flow control valve is provided in the primary air flow channel so that the burning rate of the fuel grain can be controlled.
  • FIG. 1 is a schematic partially cut away sectional view of a solid fuel ramjet according to the invention.
  • FIG. 2 is a sectional view of the device of H0. 1 along the line 2-2.
  • FIG. 1 of the drawing shows a solid fuel ramjet missile having a conventional payload such as a target acquisition section 12, an ordnance section 14, a flight control section 16 and a ramjet section 18, with stabilizing fins 19 located at the aft end of the missile.
  • the ramjet section 18 has a solid fuel grain 20 positioned within chamber 22 with the exit nozzle 24 at the aft end of the secondary combustor 26.
  • the solid fuel grain may be any conventional air burning fuel grain such as magnesium and aluminum with a rubber binder.
  • a small amount of oxidizer may be added with the amount added being insufficient to maintain combustion in the absence of air.
  • the ram air inlet 28 has its lip 29 positioned near the trailing end of the fuel grain with about percent of the ram air being directed into the secondary combustor 26 by flow vanes 30.
  • a conventional boundary layer bleed is provided at 25.
  • a small portion of the ram air, for example about l5 percent, is bled off by flow director 32 and passed along channel 34 to the forward end of the fuel grain to provide primary air for burning the fuel grain.
  • Primary combustion occurs under fuel rich conditions in the longitudinal channel 35 through the center of the fuel grain. Fuel rich products of primary combustion are further burned in the secondary combustor 26.
  • a valve 37 is provided to control the flow of primary air into the fuel grain channel 35.
  • the valve 37 may be positioned by a hydraulic, pneumatic or screw jack drive system 38 which may be controlled either by a command signal from the flight control section or in response to a preset program.
  • the missile could be programmed to provide a constant thrust as the area of the fuel grain changes with burning.
  • a conventional igniter 41 such as a pyrotechnic material ignited with squib, initiates the burning of the fuel grain in a conventional manner upon command from the flight control section, through lines 43, which may also carry the control signal to fins 19.
  • the missile can be adapted for use with a rocket-ramjet engine by providing a rocket fuel grain in chamber 26 and configuring nozzle 24 for hybrid operation in a conventional manner.
  • a solid fuel ramjet powered missile having a pay-load section and a ramjet section including a fuel grain with an air passage therethrough and means for igniting the fuel grain; a secondary combustor positioned at the aft end of the fuel grain; apparatus for supplying air to said fuel grain and said secondary combustor comprising; an air inlet having its lip positioned near the aft end of said fuel grain; means within said inlet for directing a major portion of the air, entering the inlet, into the secondary combustor; a channel adjacent the fuel grain, extending from said inlet to a position adjacent the forward end of the fuel grain, for providing primary air to the forward end of the fuel grain.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

A solid fuel ramjet powered missile having the air inlets positioned adjacent the aft end of the fuel grain with a channel provided adjacent the fuel grain to provide primary air into the forward end of the fuel grain with the secondary air being supplied directly to the secondary combustor. A valve is provided in the primary air flow channel to control the air flow into the fuel grain.

Description

6 O-'-2 5 1 SR Unlted States Patent 1 1 1 1111 3,844,118 Wilkinson Oct. 29, 1974 AFT INLET RAMJET POWERED MISSILE 3,22l,496 l2/l965 Haake 60/270 s 3,535,881 l0/l970 Schubert 60/270 S [75] lnvemor- 33: w'lk'nsom New Carhsle, 3,807,169 4/1974 Bradford 60/270 R [73] Assignee: The United States of America as Primary Examiner-Carlton R. Croyle represented by the Secretary of the Assistant ExaminerRobert E. Garrett Air Force, Washmgton, D.C. Attorney, Agent, or Firm-Harry A. Herbert, Jr.; g. 2 David wllkmson [21] Appl. No.: 392,380 [57] ABSTRACT A solid fuel ramjet powered missile having the air inlsz] Cl gy g gg gg lets positioned adjacent the aft end of the fuel grain [5 1 1 Int Cl F02k 7/10 with a channel provided adjacent the fuel grain to pro- [58] Fieid 253 256 vide primary air into the forward end of the fuel grain 261 with the secondary air being supplied directly to the secondary combustor. A valve is provided in the pri- [56] References Cited znai'y air flow channel to control the air flow into the UNITED STATES PATENTS gram 2,977,753 4/1961 Boulet 60/270 R 2 Claims 2 Drawing Figures 1 AFT INLET RAMJET POWERED MISSILE I BACKGROUND OF THE INVENTION Solid fuel ramjet powered missiles have several advantages over liquid fuel ramjets. The fuel is safer because fuel leakage cannot occur. Also, burning is more stable since the hot fuel grain tends to stabilize combustion in the primary zone and fuel utilization automatically responds to changes in altitude and velocity. In prior art solid fuel ramjet powered missiles, the engine air inlet is placed forward of the forward end of the fuel grain with bypass channels being provided to channel air to the secondary combustor as in the US. Pat. to Chandler No. 2,799,987. Since the primary air flow is normally only a small percentage of the total flow, large ducts are required to supply the major portion of the air to the secondary combustor. Also, since the rate of burning of the fuel grain is a function of the exposed area, either the fuel grain has to be specially designed to provide a uniform burning rate or an uneven burning rate with poor thrust control will result.
BRIEF SUMMARY OF THE INVENTION According to this invention, the air inlets are positioned near the aft end of the fuel grain to provide increased missile stability since the static aerodynamic stability of the missile is reduced as the inlets are moved forward. With the aft inlets, the large air flow is directly into the secondary combustor which reduces pipe flow losses. Also, since the primary air flow is normally much less than the secondary air flow, a smaller size duct can be used for primary air flow thus reducing the overall weight of the missile. A flow control valve is provided in the primary air flow channel so that the burning rate of the fuel grain can be controlled.
IN THE DRAWING HO. 1 is a schematic partially cut away sectional view of a solid fuel ramjet according to the invention.
FIG. 2 is a sectional view of the device of H0. 1 along the line 2-2.
DETAILED DESCRlPTlON OF THE DRAWING Reference is now made to FIG. 1 of the drawing which shows a solid fuel ramjet missile having a conventional payload such as a target acquisition section 12, an ordnance section 14, a flight control section 16 and a ramjet section 18, with stabilizing fins 19 located at the aft end of the missile.
The ramjet section 18 has a solid fuel grain 20 positioned within chamber 22 with the exit nozzle 24 at the aft end of the secondary combustor 26. The solid fuel grain may be any conventional air burning fuel grain such as magnesium and aluminum with a rubber binder. For some applications, a small amount of oxidizer may be added with the amount added being insufficient to maintain combustion in the absence of air.
The ram air inlet 28 has its lip 29 positioned near the trailing end of the fuel grain with about percent of the ram air being directed into the secondary combustor 26 by flow vanes 30. A conventional boundary layer bleed is provided at 25. A small portion of the ram air, for example about l5 percent, is bled off by flow director 32 and passed along channel 34 to the forward end of the fuel grain to provide primary air for burning the fuel grain. Primary combustion occurs under fuel rich conditions in the longitudinal channel 35 through the center of the fuel grain. Fuel rich products of primary combustion are further burned in the secondary combustor 26.
Since the fuel system of the solid propellant burner is easily throttleable by throttling the primary air flow, a valve 37 is provided to control the flow of primary air into the fuel grain channel 35. The valve 37 may be positioned by a hydraulic, pneumatic or screw jack drive system 38 which may be controlled either by a command signal from the flight control section or in response to a preset program. For example, the missile could be programmed to provide a constant thrust as the area of the fuel grain changes with burning.
A conventional igniter 41, such as a pyrotechnic material ignited with squib, initiates the burning of the fuel grain in a conventional manner upon command from the flight control section, through lines 43, which may also carry the control signal to fins 19.
Though not shown, the missile can be adapted for use with a rocket-ramjet engine by providing a rocket fuel grain in chamber 26 and configuring nozzle 24 for hybrid operation in a conventional manner.
While only one inlet scoop and one primary air channel are shown, more than one may be provided if desired.
There is thus provided a solid fuel ramjet powered missile with increased static stability, lower inlet air pipe flow losses and a controlled burning rate.
I claim:
1. in a solid fuel ramjet powered missile, having a pay-load section and a ramjet section including a fuel grain with an air passage therethrough and means for igniting the fuel grain; a secondary combustor positioned at the aft end of the fuel grain; apparatus for supplying air to said fuel grain and said secondary combustor comprising; an air inlet having its lip positioned near the aft end of said fuel grain; means within said inlet for directing a major portion of the air, entering the inlet, into the secondary combustor; a channel adjacent the fuel grain, extending from said inlet to a position adjacent the forward end of the fuel grain, for providing primary air to the forward end of the fuel grain.
the flow of air into the fuel grain.

Claims (2)

1. In a solid fuel ramjet powered missile, having a pay-load section and a ramjet section including a fuel grain with an air passage therethrough and means for igniting the fuel grain; a secondary combustor positioned at the aft end of the fuel grain; apparatus for supplying air to said fuel grain and said secondary combustor comprising; an air inlet having its lip positioned near the aft end of said fuel grain; means within said inlet for directing a major portion of the air, entering the inlet, into the secondary combustor; a channel adjacent the fuel grain, extending from said inlet to a position adjacent the forward end of the fuel grain, for providing primary air to the forward end of the fuel grain.
2. The device as recited in claim 1 wherein said missile includes a flight control section; means responsive to a signal from the flight control section for controlling the flow of air into the fuel grain.
US00392380A 1973-08-28 1973-08-28 Aft inlet ramjet powered missile Expired - Lifetime US3844118A (en)

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US00392380A US3844118A (en) 1973-08-28 1973-08-28 Aft inlet ramjet powered missile
GB3725874A GB1421719A (en) 1973-08-28 1974-08-23 Ramjet powered missiles
CA207,893A CA991418A (en) 1973-08-28 1974-08-27 Aft inlet ramjet powered missile

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Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4050243A (en) * 1976-05-17 1977-09-27 The United States Of America As Represented By The Secretary Of The Navy Combination solid fuel ramjet injector/port cover
US4137712A (en) * 1976-07-06 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Fluidic combustion control of a solid fuel ramjet
FR2468752A1 (en) * 1979-10-31 1981-05-08 Messerschmitt Boelkow Blohm DEVICE FOR MOUNTING AND DRIVING A VALVE COMMANDING THE TRANSVERSE SECTION FOR THE FLOW OF HOT GASES, PARTICULARLY GASES RICH IN FUEL ENTERING THE COMBUSTION CHAMBER OF STATOREACTORS
FR2504201A1 (en) * 1981-04-15 1982-10-22 Messerschmitt Boelkow Blohm ROTARY SHUTTER VALVE INTENDED IN PARTICULAR FOR DETERMINING FUEL-RICH GASES IN STATORE-ENGINE FLOOR ENGINES
FR2519377A1 (en) * 1977-02-08 1983-07-08 Messerschmitt Boelkow Blohm STATOREACTOR, PARTICULARLY COMBUSTIBLES CONTAINING, IN THE FORM OF PARTICLES, BORON OR OTHER ENERGY MATERIALS OF HIGH TEMPERATURE OF FUSION AND VAPORIZATION
US4416112A (en) * 1981-12-28 1983-11-22 Hercules Incorporated Fuel injector for ducted rocket motor
US4628688A (en) * 1983-08-29 1986-12-16 The United States Of America As Represented By The Secretary Of The Navy Solid fuel ramjet flow control device
DE3633387C1 (en) * 1986-10-01 1987-08-13 Messerschmitt Boelkow Blohm Gas generator of a rocket/ram jet motor
US4745740A (en) * 1982-09-30 1988-05-24 The Boeing Company Velocity controller for ramjet missile and method therefor
US4840024A (en) * 1984-08-20 1989-06-20 Morton Thiokol, Inc. Multiple propellant solid rocket motor
FR2650341A1 (en) * 1989-07-27 1991-02-01 Messerschmitt Boelkow Blohm GAS GENERATOR FOR STATUS-FUSEES
US5817968A (en) * 1987-08-03 1998-10-06 The United States Of America As Represented By The Secretary Of The Air Force Gas generation with high pressure sensitivity exponent propellant
US5831155A (en) * 1996-12-02 1998-11-03 Atlantic Research Corporation Apparatus and method for simulating rocket-to-ramjet transition in a propulsion system
US6446427B1 (en) 2000-07-18 2002-09-10 The United States Of America As Represented By The Secretary Of The Navy Solid fuel regression rate control method and device
US20050284128A1 (en) * 2004-06-29 2005-12-29 Anderson Morris G Rocket motor nozzle throat area control system and method
US20090217525A1 (en) * 2008-02-28 2009-09-03 Fuller Jerome K Stereolithographic rocket motor manufacturing method
US20090217642A1 (en) * 2008-02-28 2009-09-03 Fuller Jerome K Radial flow stereolithographic rocket motor
US20100281850A1 (en) * 2008-02-28 2010-11-11 Fuller Jerome K Buried radial flow stereolithographic rocket motor
US9032737B2 (en) 2009-12-30 2015-05-19 Rolls-Royce North American Technologies, Inc. Combustor added to a gas turbine engine to increase thrust
US9038368B2 (en) 2011-08-01 2015-05-26 The Aerospace Corporation Systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor
USD739706S1 (en) * 2014-10-17 2015-09-29 Briggs & Stratton Corporation Cable lock
US9429104B2 (en) 2011-08-01 2016-08-30 The Aerospace Corporation Systems and methods for casting hybrid rocket motor fuel grains
RU171406U1 (en) * 2016-10-27 2017-05-30 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Plug of the intake device of a ramjet engine
CN109098891A (en) * 2018-10-11 2018-12-28 中国人民解放军国防科技大学 Cross-medium ramjet based on solid propulsion
US20230193856A1 (en) * 2020-05-05 2023-06-22 Atlantis Research Labs Inc. Multi-mode propulsion system
US11999500B2 (en) 2021-10-20 2024-06-04 General Electric Company Deployable inlet assembly for aerial vehicle

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2863665B1 (en) * 1988-10-12 2007-03-30 Aerospatiale STATOREACTOR HAVING A TUBULAR AND MISSILE STRUCTURE PROPULATED BY SUCH STATOREACTOR

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2977753A (en) * 1954-02-13 1961-04-04 Rech Etudes Prod Improvements in continuous flow gas engines
US3221496A (en) * 1962-06-26 1965-12-07 Frederick L Haake Ramjet motor with multi-stage burning
US3535881A (en) * 1967-10-18 1970-10-27 Bolkow Gmbh Combination rocket and ram jet engine
US3807169A (en) * 1973-06-13 1974-04-30 Us Air Force Integral precombustor/ramburner assembly

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2977753A (en) * 1954-02-13 1961-04-04 Rech Etudes Prod Improvements in continuous flow gas engines
US3221496A (en) * 1962-06-26 1965-12-07 Frederick L Haake Ramjet motor with multi-stage burning
US3535881A (en) * 1967-10-18 1970-10-27 Bolkow Gmbh Combination rocket and ram jet engine
US3807169A (en) * 1973-06-13 1974-04-30 Us Air Force Integral precombustor/ramburner assembly

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4050243A (en) * 1976-05-17 1977-09-27 The United States Of America As Represented By The Secretary Of The Navy Combination solid fuel ramjet injector/port cover
US4137712A (en) * 1976-07-06 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Fluidic combustion control of a solid fuel ramjet
FR2519377A1 (en) * 1977-02-08 1983-07-08 Messerschmitt Boelkow Blohm STATOREACTOR, PARTICULARLY COMBUSTIBLES CONTAINING, IN THE FORM OF PARTICLES, BORON OR OTHER ENERGY MATERIALS OF HIGH TEMPERATURE OF FUSION AND VAPORIZATION
FR2468752A1 (en) * 1979-10-31 1981-05-08 Messerschmitt Boelkow Blohm DEVICE FOR MOUNTING AND DRIVING A VALVE COMMANDING THE TRANSVERSE SECTION FOR THE FLOW OF HOT GASES, PARTICULARLY GASES RICH IN FUEL ENTERING THE COMBUSTION CHAMBER OF STATOREACTORS
FR2504201A1 (en) * 1981-04-15 1982-10-22 Messerschmitt Boelkow Blohm ROTARY SHUTTER VALVE INTENDED IN PARTICULAR FOR DETERMINING FUEL-RICH GASES IN STATORE-ENGINE FLOOR ENGINES
US4416112A (en) * 1981-12-28 1983-11-22 Hercules Incorporated Fuel injector for ducted rocket motor
US4745740A (en) * 1982-09-30 1988-05-24 The Boeing Company Velocity controller for ramjet missile and method therefor
US4628688A (en) * 1983-08-29 1986-12-16 The United States Of America As Represented By The Secretary Of The Navy Solid fuel ramjet flow control device
US4840024A (en) * 1984-08-20 1989-06-20 Morton Thiokol, Inc. Multiple propellant solid rocket motor
DE3633387C1 (en) * 1986-10-01 1987-08-13 Messerschmitt Boelkow Blohm Gas generator of a rocket/ram jet motor
US5817968A (en) * 1987-08-03 1998-10-06 The United States Of America As Represented By The Secretary Of The Air Force Gas generation with high pressure sensitivity exponent propellant
FR2650341A1 (en) * 1989-07-27 1991-02-01 Messerschmitt Boelkow Blohm GAS GENERATOR FOR STATUS-FUSEES
US5831155A (en) * 1996-12-02 1998-11-03 Atlantic Research Corporation Apparatus and method for simulating rocket-to-ramjet transition in a propulsion system
US6446427B1 (en) 2000-07-18 2002-09-10 The United States Of America As Represented By The Secretary Of The Navy Solid fuel regression rate control method and device
US20050284128A1 (en) * 2004-06-29 2005-12-29 Anderson Morris G Rocket motor nozzle throat area control system and method
US7464535B2 (en) * 2004-06-29 2008-12-16 Honeywell International Inc. Rocket motor nozzle throat area control system and method
US20090217525A1 (en) * 2008-02-28 2009-09-03 Fuller Jerome K Stereolithographic rocket motor manufacturing method
US20090217642A1 (en) * 2008-02-28 2009-09-03 Fuller Jerome K Radial flow stereolithographic rocket motor
US20100281850A1 (en) * 2008-02-28 2010-11-11 Fuller Jerome K Buried radial flow stereolithographic rocket motor
US8225507B2 (en) * 2008-02-28 2012-07-24 The Aerospace Corporation Stereolithographic rocket motor manufacturing method
US20120285016A1 (en) * 2008-02-28 2012-11-15 Fuller Jerome K Stereolithographic Rocket Motor Manufacturing Method
US8601790B2 (en) 2008-02-28 2013-12-10 The Aerospace Corporation Buried radial flow rapid prototyping rocket motors
US8707676B2 (en) 2008-02-28 2014-04-29 The Aerospace Corporation Radial flow rapid prototyping rocket motors
US8844133B2 (en) * 2008-02-28 2014-09-30 The Aerospace Corporation Stereolithographic rocket motor manufacturing method
US9032737B2 (en) 2009-12-30 2015-05-19 Rolls-Royce North American Technologies, Inc. Combustor added to a gas turbine engine to increase thrust
US9038368B2 (en) 2011-08-01 2015-05-26 The Aerospace Corporation Systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor
US9429104B2 (en) 2011-08-01 2016-08-30 The Aerospace Corporation Systems and methods for casting hybrid rocket motor fuel grains
USD739706S1 (en) * 2014-10-17 2015-09-29 Briggs & Stratton Corporation Cable lock
RU171406U1 (en) * 2016-10-27 2017-05-30 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Plug of the intake device of a ramjet engine
CN109098891A (en) * 2018-10-11 2018-12-28 中国人民解放军国防科技大学 Cross-medium ramjet based on solid propulsion
CN109098891B (en) * 2018-10-11 2019-11-01 中国人民解放军国防科技大学 Cross-medium ramjet based on solid propulsion
US20230193856A1 (en) * 2020-05-05 2023-06-22 Atlantis Research Labs Inc. Multi-mode propulsion system
US12078127B2 (en) * 2020-05-05 2024-09-03 Atlantis Research Labs Inc. Multi-mode propulsion system
US11999500B2 (en) 2021-10-20 2024-06-04 General Electric Company Deployable inlet assembly for aerial vehicle

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GB1421719A (en) 1976-01-21
CA991418A (en) 1976-06-22

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