Her Majesty the Queen in Right of Canada, As Represented by the Minister

Her Majesty the Queen in Right of Canada, As Represented by the Minister of National Defence

Other

National Research Council of Canada

Her Majesty the Queen As Represented by the Minister of National Defence of Her Majesty's Canadian Government

Andrew J. Higgins

Fan Zhang

Stephen Burke Murray

Andrew J Higgins

Clayton G Coffey

David Hudak

Andrew McQuilkin

David S Weiss

Paul A Thibault

Ingar O Moen

Joseph L Labbe

Stephen A Ward

Donald L Bayly

David V Ritzel

A method for effecting physicochemical transformations and detonation properties in a material using super-compressed detonation includes: providing an insensitive energetic material to be compressed; super-compressing the material by exposure to at least one of a normally or obliquely oriented cylindrical imploding shock wave, generated from a first detonation; effecting transformations from the super-compression in the material including increasing at least material density, structural transformations and electronic energy gap transitions relative to a material unexposed to the super-compression; exposing the super-compressed material to a second detonation; and effecting transformations from the second detonation in the material including increasing at least detonation pressure, velocity and energy density relative to a material unexposed to the super-compression and second detonation.

Super compressed detonation method and device to effect such detonation

A method and apparatus are provided for detonation of a super-compressed insensitive energetic material by cylindrical implosion followed by an axial detonation to a detonation velocity several times that of TNT and a detonation pressure in excess of ten times that of TNT. The device provides a conical metal flyer shell within which is disposed a cylindrical anvil surrounded by explosive. The anvil retains an insensitive energetic material to be compressed and detonated. A first detonation of explosive by impact of the flyer shell generates a reverberating oblique shock wave system for sample compression. Axial detonation of the compressed sample through any length of a sample is achieved following the principal of matching the axial velocity and compression time of the oblique shock wave system to the detonation velocity and induction delay time of the compressed sample. The method and apparatus are also applicable to enhancing the effect of anti-armor and anti-hard-target munitions. The apparatus is also applicable to inert sample compression to the megabar range without using the axial detonation.

A method and apparatus are provided for detonation of a super-compressed insensitive energetic material by cylindrical implosion followed by an axial detonation to a detonation velocity several times that of TNT and a detonation pressure in excess of ten times that of TNT. The device provides a conical metal flyer shell within which is disposed a cylindrical anvil surrounded by explosive. The anvil retains an insensitive energetic material to be compressed and detonated. A first detonation of explosive by impact of the flyer shell generates a reverberating oblique shock wave system for sample compression. Axial detonation of the compressed sample through any length of a sample is achieved following the principal of matching the axial velocity and compression time of the oblique shock wave system to the detonation velocity and induction delay time of the compressed sample. The method and apparatus are also applicable to enhancing the effect of anti-armour and anti-hard-target munitions. The apparatus is also applicable to inert sample compression to the megabar range without using the axial detonation.

A relatively low drag, completely free-flying, tubular vehicle comprises a body that defines a leading edge and a trailing edge and includes an external surface and an internal surface each extending from the leading to the trailing edge. The internal surface has an axially converging upstream section extending from the leading edge to a discontinuity that constitutes a throat in the vehicle. The internal surface also has an axially diverging downstream section extending from the throat to the trailing edge. The internal surface is configured to enable introduction and mixing of fuel into an airstream flowing therethrough, and to generate a shock wave when in flight. The shock wave is of such magnitude and direction as to create a hot spot that subsequently causes ignition and combustion of the fuel-air mixture. The combustion causes formation of a detonation bubble and migration of the associated wave front upstream to stabilize slightly downstream of the throat. The combustion of the fuel results in rapid expansion of combustion products, generating forward thrust against the internal surface of the vehicle.

Free-flying tubular vehicle

A main charge of explosive is positioned symmetrically about a passageway-forming tubular member, such as a well pipe assembly. The charge is outwardly and radially spaced from the member and is coupled thereto by a dense medium, such as soil, which is adapted to transfer the produced explosive energy to the tubular member in the form of a pressure pulse applied by the medium. Initiation charges are supplied at the outer surface of the main charge, to initiate a detonation wave directed at the tubular member. A layer of dense medium is provided to confine the non-coupled surface of the charge and retard venting of explosive gases away from the tubular member. In the end result, concentrated, converging pressure pulses are applied to the tubular member on detonation, to cause it to be symmetrically crimped to restrict the passageway.

Explosive pipe crimping method and devices

The invention provides a system for breaching a lane in a minefield containing pressure sensitive mines. A mobile carrier mounts fuel, nitrogen and water tanks, a hose magazine and a launch rail. A flexible hose is folded into the magazine for rapid deployment therefrom and carries a detonating cord therein. A tow vehicle, such as a rocket, is connected to the free end of the hose so that when it is launched it will pull the hose across the minefield. Thereafter, pressurized nitrogen is used to drive liquid fuel into the hose, followed by a slug of water between the fuel-containing section and the carrier. Detonation of the cord creates a fuel droplets-in-air-cloud above the hose, which cloud is subsequently detonated to create a pressure wave which, in turn, detonates or neutralizes the mines along the desired lane, allowing vehicles and personnel to travel therealong. Means are provided to space the detonating cord from the inner wall of the hose so as to prevent the formation of hot spots as the cord detonates, which hot spots could result in premature local deflagration of the fuel droplet-air cloud.

Fuel-air line-charge ordnance neutralizer

Film cooling apparatus adapted to be connected into a conduit carrying a hot exhaust gas. The apparatus comprises single walled contoured duct means connectible to said conduit and a center-body aerodynamically shaped and supported within said duct means so as to form therewith an annular channel of zero pressure gradient. Slot means are provided in the single walled contoured duct means and in the center-body to enable a flow of cooling air over exterior surfaces thereof to maintain said surfaces at an acceptably low temperature. A network of ducting carries the cooling air to the contoured duct means and interior of the center-body. The duct means and center-body are preferably of circular cross-section taken orthogonally of the overall flow direction. The center-body is an axisymmetric bulb having annular slots for directing the cooling air over the exterior of said bulb. The center-body connects with a plenum chamber formed by said single walled duct means and an exterior section of the network of ducting. The plenum chamber is also connected to a source of cooling air. An entraining diffuser is connected to said contoured duct means downstream of the center-body. Slots in the center-body, duct means and entraining diffuser are preferably from about 0.25' to about 0.750' in width.

Growing community of inventors

Medicine Hat, Canada

Stephen Burke Murray