Abstract

Dynamic ram accelerator operation permits operation with lower acceleration, permitting launch of acceleration sensitive payloads such as crewed vehicles. Operational cost is reduced, and reliability improved, by reducing or eliminating internal consumable parts. Relative motion between a projectile and propellant at entry to the ram accelerator enables initial ram combustion at relatively lower velocity. Valves may maintain separation between sections within the ram accelerator that contain different propellant compositions. Timing of valve opening and closing is coordinated to provide conditions suitable for ram combustion. Control over propagation speed of propellant within the system may be obtained using one or more of baffle shape, baffle spacing, propellant temperature, propellant pressure, propellant mixture, temperature of components such as baffles, and so forth. Before the projectile is launched, internal separators between sections are removed, providing an open path to the ram accelerator exit.

IPC Classes  ?

• B64G 1/14 - Space shuttles
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• F41A 1/04 - Missile propulsion using the combustion of a liquid or gaseous fuel, e.g. hypergolic fuel
• F41F 1/00 - Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannonsHarpoon guns
• F41A 1/00 - Missile propulsion characterised by the use of explosive or combustible propellant charges
• F02K 7/10 - 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 fanControl thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines

Abstract

Dynamic ram accelerator operation permits operation with lower acceleration, permitting launch of acceleration sensitive payloads such as crewed vehicles. Operational cost is reduced, and reliability improved, by reducing or eliminating internal consumable parts. Relative motion between a projectile and propellant at entry to the ram accelerator enables initial ram combustion at relatively lower velocity. Valves may maintain separation between sections within the ram accelerator that contain different propellant compositions. Timing of valve opening and closing is coordinated to provide conditions suitable for ram combustion. Control over propagation speed of propellant within the system may be obtained using one or more of baffle shape, baffle spacing, propellant temperature, propellant pressure, propellant mixture, temperature of components such as baffles, and so forth. Before the projectile is launched, internal separators between sections are removed, providing an open path to the ram accelerator exit.

IPC Classes  ?

• F41A 1/02 - Hypervelocity missile propulsion using successive means for increasing the propulsive force, e.g. using successively initiated propellant charges arranged along the barrel lengthMultistage missile propulsion
• F41A 21/28 - Gas-expansion chambersBarrels provided with gas-relieving ports