Abstract: The present invention provides cyclic nitro compound, pharmaceutical compositions of cyclic nitro compounds and methods of using cyclic nitro compounds and/or pharmaceutical compositions thereof to treat or prevent diseases or disorders characterized by abnormal cell proliferation, such as cancer, inflammation, cardiovascular disease and autoimmune disease.

Abstract: Downhole stimulation tools include a housing and at least one propellant structure within the housing comprising at least one propellant grain of a formulation, at least another propellant grain of a formulation different from the formulation of the at least one propellant grain longitudinally adjacent the at least one propellant grain, and at least one initiation element proximate at least one of the propellant grains. At least one pressure containment structure is secured to the housing and comprises a seal element expandable in response to gas pressure generated by combustion of a propellant grain of the at least one propellant structure. Related methods are also disclosed.

Abstract: A method of forming a flexible structure for a rocket motor assembly comprises forming a polysiloxane composition comprising at least two different silicone materials. A preliminary structure is formed from the polysiloxane composition. The preliminary structure is cured to crosslink at least a portion of different polysiloxane chains of the preliminary structure. A flexible structure for a rocket motor assembly, a flexible assembly for a rocket motor assembly, a moveable thrust nozzle assembly for a rocket motor assembly, and a rocket motor assembly are also described.

Abstract: Methods of preparing propellant compositions for power loads and firearms that include providing pre-shaped particle sized starting material, shaped consistent with a desired final propellant product shape, and thereafter nitrating and stabilizing the pre-shaped starting material using boiling stabilization processes. The resulting nitrated propellants of the methods reliably exhibit complete stabilization, high nitrogen substitution, high shelf life and acceptable ballistic performance.

Abstract: Liquid storage systems for space vehicles include at least one storage tank including a tank inlet, a tank outlet, and a plurality of liquid storage compartments coupled to each other in series between the tank inlet and the tank outlet. Each liquid storage compartment includes an end plate including a porous outlet at an end of the liquid storage compartment adjacent to another liquid storage compartment. Propulsion systems for space vehicles include at least one such liquid storage tank. Methods of providing a liquid propellant to a thruster of a space vehicle include withdrawing a liquid propellant from a first compartment within a tank and flowing the liquid propellant from a second compartment into the first compartment through a porous element associated with an end plate separating the first compartment from the second compartment.

Abstract: A grommet for installation in an opening of a panel comprises an elastically deformable material having a longitudinal axis extending from a proximal end to a distal end of a grommet body. The grommet body comprises an aperture extending longitudinally through the grommet body between the proximal end and the distal end. A wall-engaging segment defines a longitudinal segment of the aperture and is located to be enclosed by a wall of the opening when the grommet is installed in the panel. A clamping element occludes the aperture in the wall-engaging segment and comprises at least one longitudinally extending through-hole sized and configured to receive an elongated element. The clamping element is located to apply a compressive force on the elongated element to retain the elongated element in the through-hole of the grommet body responsive to disposition of the wall-engaging segment in the opening of the panel.

Abstract: An area denial system may be operationally placed with communication latency compensation. The area denial system may include a plurality of munitions, one or more sensor devices, and a command and control unit, networked together and having a command and control latency for communication between the command and control unit and the remainder of the area denial system. Latency compensation may include determining a first target position, determining a first predicted position area for the target using the command and control latency and the first target position, receiving an authorization to arm one or more of the munitions, determining a second target position, and determining that the second target position is outside a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition.

Abstract: Systems and methods are described herein for mounting a thruster onto a vehicle. A thruster mounting structure may comprise a first, second, and third rotational joint, a boom, and thruster pallet, and a thruster attached to the thruster pallet. The first rotational joint may be attached to the vehicle and configured to rotate in a first axis. The first rotational joint may be connected to the boom and configured to pivot the boom about the first axis. The boom may be connected to the second rotational joint, which is connected to the third rotational joint and configured to rotate the third rotational joint in the first axis. The third rotational joint may be connected to the thruster pallet and configured to pivot the thruster pallet in a second axis that is perpendicular to the first axis.

Abstract: Systems and methods for calculating launch sites for a satellite constellation are provided. A carrier aircraft may be configured to launch a first satellite into the first orbit and a second satellite into the second orbit. In some embodiments, information about an accessible range of the aircraft may be received. Based on the received information, a geographical area that the aircraft can access without landing may be calculated. Using received information and the orbit parameters of the first orbit and the second orbit, a first launch site for launching the first satellite and a second launch site for launching the second satellite may be calculated. The first launch site may comprise a first geographical position and a first launch time, and the second launch site may comprise a second geographical position and a second launch time. Both launch sites may be within the calculated geographical area.

Abstract: A thrust-vectoring rocket motor nozzle includes a forward assembly having a forward shell with a flange configured for connection to a motor and a throat portion opposite the flange. A ball joint sleeve may be disposed proximate the throat portion, and an exit cone assembly may include a ball joint socket configured to mate with the ball joint sleeve to allow movement of the exit cone assembly about one or more axes relative to the forward assembly. A thermal barrier may be disposed in a gap between the forward assembly and the exit cone assembly. The forward assembly may include a throat insulator mechanically locked within the forward shell. Related methods include forming thrust-vectorable rocket motor nozzles. Rocket motors may include such nozzles.

Abstract: A downhole stimulation tool comprising an outer housing exhibiting apertures extending therethrough, opposing propellant structures within the outer housing, and at least one initiator adjacent each of the opposing propellant structures. Each of the opposing propellant structures comprise at least one higher combustion rate propellant region, and at least one lower combustion rate propellant region longitudinally adjacent the at least one higher combustion rate propellant region. Additional downhole stimulation tools and methods of stimulating a producing formation are also disclosed.

Abstract: Stun grenades may include a fuze configured to ignite a delay material secured to a housing including a delay chamber in which the delay material is located. A handle of the fuze may be located over a final payload chamber of the series of payload chambers, payload material in the final payload chamber being configured to ignite after ignition of payload material in each other payload chamber of a series of payload chambers. Methods of assembling stun grenades may involve positioning an obstruction in a port extending between a delay chamber and a payload chamber of a series of payload chambers surrounding the delay chamber in a housing. A delay material may be packed in the delay chamber. The obstruction may be removed, and a payload material may be positioned in the payload chamber and the port.

Abstract: A munition, such as a projectile formed of at least one reactive material. In one embodiment, the projectile includes a body portion formed of at least one reactive material composition wherein the at least one reactive material composition defines at least a portion of an exterior surface of the projectile. In other words, a portion of the reactive material may be left “unbuffered” or exposed to the barrel of a gun or weapon from which it is launched and similarly exposed to a target with which the projectile subsequently impacts. In one embodiment, the projectile may be formed with a jacket surrounding a portion of the reactive material to provide additional structural integrity. The projectile may be formed by casting or pressing the reactive material into a desired shape, or the reactive material may be extruded into a near-net shape and then machined into the desired shape.

Abstract: An assembly comprising a first article, a second article adjacent the first article, and an electrically conductive adhesive in electrical communication with the first article and the second article. The electrically conductive adhesive comprises nickel nanostrands dispersed in a matrix comprising a reaction product of bisphenol-F epoxy resin, resorcinol diglycidyl ether epoxy monomer, and at least one amine-containing curing agent. The electrically conductive adhesive exhibits a tensile adhesion strength greater than about 5,000 psi and a volume resistivity less than about 0.01 ?·cm. Electrically conductive adhesives including nickel nanostrands, precursor packages of the electrically conductive adhesive, related methods of forming the electrically conductive adhesive and an assembly including the electrically conductive adhesive are also disclosed.

Abstract: A venting system for ordnance or rocket motors comprising a casing having at least one hole and a plug, the plug being formed from a plug slug swaged into the at least one hole. A method to fill a vent hole in a casing comprising transforming a plug slug positioned within the vent hole into a plug.

Abstract: A fire suppression system for producing an inert gas mixture having a minimal amount of carbon monoxide, particulates, or smoke. The inert gas mixture may be generated by combusting a gas generant. The gas generant may be a composition that includes hexa(ammine)-cobalt(III)-nitrate. The fire suppression system also includes a heat management system to reduce a temperature of the inert gas mixture. In one embodiment, the system includes multiple gas generators and is configured to ignite the respective gas generant of each gas generator in a predetermined, time based sequential order. For example, the gas generant of each gas generator may be ignited in a sequential order at specified time intervals. Methods of extinguishing fires are also disclosed.

Abstract: Methods of preparing propellant compositions for power loads and firearms that include providing pre-shaped particle sized starting material, shaped consistent with a desired final propellant product shape, and thereafter nitrating and stabilizing the pre-shaped starting material using boiling stabilization processes. The resulting nitrated propellants of the methods reliably exhibit complete stabilization, high nitrogen substitution, high shelf life and acceptable ballistic performance.

Abstract: Materials including support layers and fiber-free compositions are disclosed, as well as related articles and methods for making the materials. The fiber-free compositions are formed from a precursor composition that includes a nitrile butadiene rubber, a nanoclay and a cure package including a sulfur-based curing agent. The fiber-free compositions may have a substantially reduced weight and compressive modulus in comparison to conventional rubber. Thus, the fiber-free compositions may provide improved ballistic properties in addition to reduced density and thickness. Precursor compositions for forming the insulative composition may have good flow characteristics. The fiber-free compositions may be used in a variety of applications, such as personnel body armor, ground vehicle armor and aircraft armor systems.

Abstract: Retention clips for safety mechanisms of illumination flares include an abutment surface configured for abutment of an end of a rigid sleeve coupled to an igniter initiation cable and one or more protrusions configured to extend at least partially over a lateral side surface of the rigid sleeve when the rigid sleeve is retained by the clip. Safety mechanisms, illumination flares, and methods for igniting illumination flares involve such retention clips.

Abstract: Systems and methods are described herein for communications bandwidth enhancement using Orthogonal Spatial Division Multiplexing (OSDM). For example, large sparse antenna arrays may be able to distinguish between signals emitted by multiple nearly collocated antennas, even if the signals have the same frequency, polarization, and coverage. Thus, the use of a large sparse antenna array may be able to resolve/isolate individual antennas on a single platform, allowing for OSDM, analogous to Orthogonal Frequency Divisional Multiplexing (OFDM). Using OSDM, multiple antennas on the same vehicle are able to reuse the same frequencies/polarizations without interference, thereby increasing spectrum availability while still providing the same transmitter power spectral density and total RF power emission.