Abstract: A system for estimating flight range of an electric aircraft. The system generally includes at least a sensor and a computing device. The at least a sensor is communicatively connected to at least a flight component. The at least a sensor is configured to detect a performance datum of the at least a flight component. The computing device is communicatively connected to the at least a sensor. The computing device is configured to receive the performance datum from the at least a sensor, determine an energy performance datum from the performance datum, determine a flight performance datum from the performance datum, generate a projected flight range datum as a function of the energy performance datum and the flight performance datum, and display the projected flight range datum. A method for estimating flight range of an electric aircraft is also provided.

Abstract: A sensor waveguide system includes a sensor waveguide and a plurality of sensors. The sensor waveguide includes a main body defining a peak, a base, an axis of rotation, and a plurality of waveguide channels. The main body converges from the base to the peak to create a predetermined tapered profile. The plurality of waveguide channels are oriented parallel to the axis of rotation of the sensor waveguide and each waveguide channel defines an exit disposed at the base of the main body. A sensor is disposed at the exit of each of the plurality of waveguide channels.

Abstract: A method and apparatus for lifting a payload wherein a first mechanical-rotor is driven by an internal combustion engine. A portion of the mechanical work developed by the internal combustion engine is used to generate electrical power, which is either stored in a battery or used to power an electric motor that drives a second rotor. Thrust developed by the mechanical and electrical rotors is directed downward to provide lift for the payload.

Abstract: Disclosed is a space cold gas thruster operating with a solid propellant. The cold gas thruster includes a tank suitable for containing a solid propellant and a tank heating device suitable for sublimating the solid propellant and forming gaseous propellant, the tank having an aperture for transferring the gaseous propellant outside the tank, such as a nozzle. Also disclosed is a process for determining the amount of remaining propellant in the propellant tank of the disclosed cold gas thruster.

Abstract: Modular cartridges are disclosed that can be initially assembled, disassembled, and reprocessed by hand. The cartridge case is suitable for use with a variety of projectile designs and weights and for use with a range of propellant amounts and primer types. The variety of projectiles and range of propelling forces permits the present invention to provide cartridges for all types of uses, including indoor and outdoor target shooting, training, non-lethal self-protection, and lethal uses. The cartridges include a case, a projectile, a primer, and a selectable amount of propellant (if any), and primer housing insert” and which is configured to be releasably attached to the striking end of the case and to contain the primer and the desired amount of propellant.

Abstract: A system for estimating flight range of an electric aircraft. The system generally includes at least a sensor and a flight controller. The at least a sensor is communicatively connected to at least a flight component. The at least a sensor is configured to detect a performance datum of the at least a flight component. The flight controller is communicatively connected to the at least a sensor. The flight controller is configured to receive the performance datum from the at least a sensor, determine an energy performance datum from the performance datum, determine a flight performance datum from the performance datum, generate a projected flight range datum as a function of the energy performance datum and the flight performance datum, and display the projected flight range datum. A method for estimating flight range of an electric aircraft is also provided.

Abstract: An ammunition storage compartment includes a plurality of connected walls defining an interior region to store ammunition, wherein at least one of the walls includes an outer armor plate having an outer surface and an inner surface. A layer of energy absorbing material is located proximate the inner surface of the armor plate in the interior region. A spall mitigating panel is located inward of the layer of energy absorbing material in the interior region. At least one air gap is in between the layer of energy absorbing material and the spall mitigating panel.

Abstract: A jet engine has an inlet 11 configured to introduce air, and a combustor 12 having a fuel injection port 30a that injects a fuel, and configured to combust the fuel injected from the fuel injection port 30a by using the air. The combustor 12 has a separation section 14 defining the air passage FA through which the air flows, between a rear end 15 of the inlet and the fuel injection port 30a. A plurality of turbulent flow generating sections (20;25) are arranged in the separation section 14 to makes the air flow turbulent. Each of the plurality of turbulent flow generating sections (20;25) contains a member (21;22;25B) which can restrain the turbulence of the air flow by moving or disappearing. It can be prevented that a high-pressure region reaches the inlet so that the thrust of the jet engine is reduced.

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) including: a fuselage; a first pair of airfoils rotatable between a retracted position and a deployed position, the deployed position extending out from the fuselage and the retracted position extending substantially along a first portion on an exterior of the fuselage; a second pair of airfoils rotatable between a second retracted position and a second deployed position, the second deployed position extending out from the fuselage and the second retracted position extending substantially along the first portion on the exterior of the fuselage; and a rudder foldable against the fuselage in a pre-deployment position.

Abstract: A uniform projectile casing which is utilized for projectiles with different ranges. A projectile of relatively short range can in this case be optimized with regard to payload, whereas a projectile with the relatively long range is subjected to a range optimization, with a reduction in payload. The payload of a projectile of relatively long range is generally lower in relation to a projectile with relatively short range. The artillery projectiles have a projectile casing of equal size for the projectiles of different range. To create an artillery projectile, for example 155 mm, a uniform payload-optimized 30 km projectile casing) is used, from which 40 km projectiles can be generated (produced, assembled) by means of a reduction in payload. The range is selected and defined by mutually different projectile bases. The artillery projectile has multiple modular parts which are assembled in order to create the artillery projectile.

Abstract: There is provided a multicopter having a frame, four rotors attached to the frame and each having an input shaft, four motor-generators installed one on each of the rotors and each having an input-output shaft, a single gas-turbine engine connected to the motor-generators and having an output shaft. The input shaft of each rotor, the input-output shaft of each motor-generator and the output shaft of the engine are respectively connected with each other by a speed reducer mechanism having a sun gear, ring gear and planetary carrier.

Abstract: A hybrid gas turbine engine comprises a turbine, a compressor, and a gear system that is driven by the turbine where the gear system includes a sun gear, a ring gear and a plurality of planet gears, where the ring gear has a ring gear radius of RRing gear and the sun gear has a sun gear radius of RSun gear such that the gear system provides a reduction ratio of RRing gear/RSun gear. A fan is driven by the ring gear, and a generator is driven by the ring gear and provides a generator output signal. A power circuit receives the generator output signal and provides a gain RRing gear/RSun gear to the generator output signal and provides a gain signal indicative thereof to an electrical load.

Abstract: The thrust force generation device is provided with: a turbo fan engine unit that includes a generator for generating power using a rotation force of a drive shaft, and that drives a fan placed on the drive shaft using gas produced by combusting fuel; a motor driven fan unit that includes a motor driven by power supplied from the generator, that is placed in parallel with the turbo fan engine unit, and that drives a fan by using the motor; and a conducting unit that connects the generator to the motor, and supplies the power generated by the generator to the motor. The turbo fan engine unit and the motor driven fan unit are integrated with each other, and the conducting unit is placed between the turbo fan engine unit and the motor driven fan unit.

Abstract: Systems and methods for generating an oblique shock in a supersonic inlet are disclosed. The system can comprise an inlet with a slot disposed at an oblique angle to the main incoming air stream. High-pressure air can be provided through the slot into the main air stream. The high-pressure air can be introduced at a high enough pressure ratio—i.e., the ratio of pressure of the air stream from the slot to the pressure for the main flow—such that an aerodynamic ramp is created in the main air flow. The aerodynamic ramp, in turn, can cause one or more oblique shock waves to eventually slow the main air stream velocity to a subsonic speed prior to the face of the engine. Systems and methods for controlling the slot pressure ratio to create these shocks are also disclosed.

Abstract: The present disclosure provides a projectile with a self-contained internal chamber. Reaction of propellant inside the internal chamber can generate high pressure and the resultant exhaust gases can be used for projectile linear acceleration, rotational acceleration or other purposes. Torque can be produced by exhausting the pressure via radially placed, tangential nozzles or other outlets and can be configured to induce sufficient projectile spin to stabilize the projectile without the need for barrel rifling. The internal chamber may be separate or integral to the projectile itself. The projectile may include two or more chambers or compartments internal to the chambers. The disclosed projectile allows for higher pressures in the internal chamber than in the barrel and greater flexibility on pressure manipulation in the barrel and the projectile, allowing for a more efficient propellant combustion and manipulation of projectile characteristics such as muzzle and rotational speeds.

Abstract: A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.

Abstract: A projectile for use with a firearm having a rifled barrel including helical grooves extending longitudinally along an inner surface thereof can include: a substantially cylindrical projectile body having at a front end an ogival nose section and at a rear end a tail section; a driving band section formed on the projectile body between the nose section and the tail section; a bore rider section formed on the projectile body between the nose section and the tail section; and a pilot band section formed on the projectile body forward of the driving band section. The pilot band section can be formed having an LD-Haack profile.

Abstract: Reforestation capsules composed of biodegradable materials are operable to be used in aerial reforestation operations. Capsules may contain one or more seedlings, compacted fertilizer, soil, and/or nutrients. Capsules include a flight platform component and cone tip component. The capsule structure survives impact and may serve as additional nutrient for the seedling(s). A housing unit sized and configured to contain and dispense capsules can be mounted or otherwise housed in an aircraft to deliver capsules.

Abstract: A ramjet projectile comprising: an outer assembly that is tubular and comprises first, second and third portions; solid ramjet fuel attached to and disposed inside the first portion of the outer assembly; an inner assembly disposed inside the outer assembly and comprising a first portion threadably coupled to the second portion of the outer assembly and a second portion surrounded by the third portion of the outer assembly to form an annular air passageway having an air inlet. The first portion of the inner assembly comprising a plurality of openings spatially distributed about a circumference. The inner assembly is rotatable relative to the outer assembly between first and second locations displaced by a distance from each other during travel along the gun barrel. The openings are not in flow communication with the annular air passageway when the inner assembly is at the first location and are in flow communication with the annular air passageway when the inner assembly is at the second location.

Abstract: An existing munition may be modified, using a modification kit, to provide enhanced fragmentation effects. The munition may be enclosed in an airframe, which also contains preformed fragments, and one or more adapters may be used to provide connections through the airframe. The adapters may be used to substitute for types of connectors already on the existing munition. The adapters may include one or more of an adapter for coupling a tail kit to a tail of the munition, an adapter for coupling a nose kit to a nose of the munition, and an adapter for coupling lugs to the munition. The adapters may engage couplers on the munition, and/or may engage the airframe. The modification of the existing munition may transform the existing munition into a fragmentation weapon, for example usable for height-of-burst detonation to spread fragments over a large area.

Abstract: An airplane, which includes an airframe and a full-segregated thrust hybrid propulsion system mounted on the airframe. The propulsion system includes: one or more sustainer thrust producers; a plurality of electrically powered thrust producers disposed in predetermined positions as a means for providing additional thrust to the airplane, and to supplement airflow over the wings, flaps, and roll control devices of said airplane; whereby increasing the lift of the wing surfaces and providing enhanced control in the roll axis. The trust producers operate independently from one another, with no aerodynamic, electrical or mechanical inter-connection. Safety is enhanced by the ability of either the sustainer thrust producer(s), or the electrically powered augmentation thrust producers to sustain flight to a suitable landing area, should the other system fail.

Abstract: A fragmentation body comprising a substantially monolithic structure comprising a metal material and comprising a major surface having an indentation pattern therein, and an opposing major surface having an opposing indentation pattern therein, the opposing indentation pattern being substantially aligned with the indentation pattern. A warhead and an article of ordnance are also described.

Abstract: The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC.

Abstract: A rocket is provided and includes booster stages at a rear of the nose cone, the booster stages being configured for propelling the nose cone in a propulsion direction and a divert control system housed entirely in the nose cone for controlling an orientation of the propulsion direction.

Abstract: A fragmentation body comprising a substantially monolithic structure comprising a metal material and comprising a major surface having an indentation pattern therein, and an opposing major surface having an opposing indentation pattern therein, the opposing indentation pattern being substantially aligned with the indentation pattern. A warhead and an article of ordnance are also described.

Abstract: Apparatus for providing electrically initiated and/or controlled combustion of electrically ignitable propellants is provided. In one example, the apparatus includes a volume of electrically ignitable propellant (liquid and/or gas) capable of self sustaining combustion, and electrodes operable to ignite the propellant. The apparatus may further include a power supply and controller in electrical communication with the electrodes for supplying a potential across the electrodes to initiate combustion of the propellant and/or control the rate of combustion of the propellant. Various configurations and geometries of the propellant, electrodes, and apparatus are possible. In one example, the electrodes are supplied a direct current, which causes combustion of the propellant at the positive electrode. In another example, the electrodes are supplied an alternating current, which initiates combustion of the propellant at both electrodes.

Abstract: A bomb for deployment from an air vehicle includes a rocket motor for propelling the bomb. The rocket motor includes propellant which at least partially defines a void downstream of an initial burning surface. As the propellant is burned the void will be exposed, increasing the surface area of the burning surface of the propellant to increase the thrust of the rocket motor.

Abstract: Systems and methods described herein provide for the protection of personnel within vehicles and structures from rocket-propelled grenades and other incoming threats. According to one aspect of the disclosure provided herein, a countermeasure system includes an interceptor vehicle configured to stow and launch an expandable countermeasure. The countermeasure may have a flexible body with attached deployment mechanisms that expand the flexible body into the path of an incoming threat to capture the threat.

Abstract: A fragmentation body comprising a substantially monolithic structure comprising a metal material and comprising a major surface having an indentation pattern therein, and an opposing major surface having an opposing indentation pattern therein, the opposing indentation pattern being substantially aligned with the indentation pattern. A warhead and an article of ordnance are also described.

Abstract: Disclosed is a flying object in which a covering unit and a wing unit installed in a nozzle assembly are integrally formed to form a smooth outer surface of the flying object, thus minimizing drag, and the covering unit and the nozzle assembly are fastened by using a fastening member having one end fastened to a slit, thereby preventing the flying object from being damaged by thermal deformation.

Abstract: A projectile (and munition including the projectile) and a method of assembling the same, includes a body having a cavity, a propellant disposed in the cavity and a base including an ignition flash column extending into the cavity containing the propellant and a nozzle formed so as to be openable and closeable.

Abstract: An apparatus for deploying stowed control surfaces of a projectile is disclosed. The apparatus for deploying stowed control surfaces of a projectile includes a first and second hot gas generators, a first and second gas chambers, a piston wedge, a piston and a barrel. Initially, the first hot gas generator discharges a surge of hot gas into the first gas chamber. In response to the surge of hot gas being discharged into the first gas generator, the piston wedge displaces at least one of the control surfaces to break an environmental seal covering the projectile. After a predetermined amount of time has lapsed, the second hot gas generator discharges a surge of hot gas into the second gas chamber. The surge of hot gas displaces the piston and barrel for deploying the control surfaces completely.

Abstract: A vehicle for launching from a gun such as a gas gun and having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: Exemplary multi-shell structured blast effect charges as well as shaped charge or shaped-charge-like explosive charges are disclosed which contain metal carbonyls in the form of pure substances, granulates, mixtures with inorganic fuels, or as granulates of mixtures with inorganic fuels integrated in suitable closed containers. The metal carbonyls serve in the form proposed herein as fuel, which during the intended conversion of the total charge exhibit an undirected (multi-shell structured blast effect charges) or at least partially directed (shaped charges or shaped-charge-like explosive charges) pressure enhancing effect.

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary submunitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect. The incendiary portion includes a solid propellant and, optionally, one or more energetic materials selected from the group consisting of phosphorous, boron, magnesium, aluminum, Fluorinert™-aluminum and BKNO3. The incendiary submunition may be in the shape of a ball or a circular disk with a rocket motor therein.

Abstract: A gun fired projectile includes a rocket motor housing including a pressure chamber and an exhaust nozzle. A plurality of propellant cells are positioned within the pressure chamber. The rocket motor propellant is mechanically supported during the severe gun fire event. This support may take several forms, each of which is discussed herein. The projectile further includes a support structure including one or more supports: wherein each of the one or more supports is engaged with the rocket motor housing. Each of the one or more supports is engaged with one propellant cell of the plurality of propellant cells, and each of the one or more supports suspends an individual propellant cell from the remainder of the plurality of propellant cells. All of these approaches provide the opportunity to tailor the performance of the rocket motor by combining a combination of propellant formulations and geometries to optimize the projectile performance.

Abstract: A projectile (and munition including the projectile) and a method of assembling the same, includes a body having a cavity, a propellant disposed in the cavity and a base including an ignition flash column extending into the cavity containing the propellant and a nozzle formed so as to be openable and closeable.

Abstract: A bomb for deployment from an air vehicle includes a rocket motor (1) for propelling the bomb. The rocket motor includes propellant (5) which at least partially defines a void (11) downstream of an initial burning surface. As the propellant (5) is burned the void 11 will be exposed, increasing the surface area of the burning surface (9) of the propellant (5) to increase the thrust of the rocket motor.

Abstract: An apparatus for adapting a rocket-assisted artillery projectile of a first caliber for firing from a smooth bore tube of a second caliber may include an adapter for connecting to an aft end of the rocket-assisted artillery projectile. The adapter may include a main channel for receiving rocket exhaust, a plurality of sub-channels that lead from the main channel to an exterior of the adapter, and an ignition channel that leads from the main channel to an ignition delay disposed in the adapter. A tail boom may be fixed to an aft end of the adapter. The tail boom may include an opening in a fore end that communicates with the ignition delay in the adapter. Lifting surfaces, such as fins, may be attached to the tail boom.

Abstract: The present invention relates to a method and a shell (1) for achieving variable firing range and effect when firing from a launcher, which shell (1) contains a firing charge (10), a rocket motor charge (6) with gas outlet (8), a rocket motor nozzle (9) and an active part (5). According to the invention, this is achieved by virtue of the fact that the shell (1) also contains a release mechanism (15) for releasing the rocket motor nozzle (9) from the rocket motor charge (6) after a time delay determined with regard to firing range and effect, and that the rocket motor charge (6) comprises a propellant which is detonable.

Abstract: A compressed air launched munition comprises a projectile which after firing forms a multiplicity of elongated ropes held in a tubular configuration by a series of stiff spacers. The stiff spacers retain a rope tube diameter of at least about 8 inches. The ropes and stiff spacers have an essentially neutral specific gravity in water. The projectile is effective in entangling a boat propeller and stopping an uncooperative boat with little damage.

Abstract: Methods of forming energetic compositions include forming a premix comprising a nitrate ester, a polymer, and a stabilizer, and combining solids with the premix. Additional stabilizer may be added with the solids and may remain in a crystalline state. Some methods include dissolving a stabilizer in at least one of a plurality of nitrate esters. Energetic compositions include a continuous matrix and a stabilizer. The continuous matrix includes a nitrate ester and surrounds a solid energetic material. Some compositions include a first nitrate ester, a second nitrate ester having a decomposition rate lower than the first nitrate ester, and a stabilizer. An article includes a housing and an energetic composition in the housing.

Abstract: Embodiments of the invention are directed toward benzoxazine composite structures and the application thereof. In some embodiments, a radome can be constructed from a benzoxazine composite structure. A benzoxazine structure can include a low density core with one or two benzoxazine composite face skins. The benzoxazine face skins can include reinforcement materials to provide structural strength. Such radomes and/or benzoxazine structures can be used in various maritime, aircraft, rocket, missile, and/or automobile applications. In particular, radomes can be used to house communication equipment such as antennas and the like.

Abstract: A launcher system includes a launcher having a barrel adapted to receive a projectile with a charge of propellant and a magazine adapted to hold additional projectiles, with each projectile including a piston shiftably mounted for movement relative to a main body. When propellant in the projectile is ignited, either mechanically or electrically, the propellant forces the piston from a retracted position during a period of initial thrust and then the propellant exits through at least one vent hole to provide an additional thrust for the projectile upon the piston moving to a fully extended position and safely discharge pressure from within the projectile. The projectile may be fired at lethal or non-lethal velocities.

Abstract: A surface skimming munition comprises a hull, a traction propulsion motor positioned in the hull and having a combustion chamber for combustion of a propellant, at least one aft directed nozzle coupled to the hull at a position forward of a center of gravity of the hull and comprising an inlet section and an outlet section, the inlet section in fluid communication with the combustion chamber and the outlet section directing combustion gas received from the combustion chamber through the inlet section in the aft direction, and at least one stabilizing plane coupled to the hull and moveable between a stowed position and a deployed position.

Abstract: This invention relates to the construction of a rocket motor and fuel system thereof and, in particular to a new and useful Viscous Liquid Monopropellant (VLM) rocket motor containing a liquid propellant that is pumped into the combustion chamber, atomised and then ignited. The atomisation step significantly increases the surface area of the propellant, delivering faster burn rates and smoother combustion. VLM is a non-Newtonian fluid containing both oxidisers and fuels. These monopropellants are comprised of a variety of liquid and solid components, mixed together to form a homogenous fluid, although heterogeneous in composition. The solid constituents are retained within the liquid phase by dispersion, suspension, bonding or chemical emulsification techniques, so as when a motive force is applied to the propellant, all the constituents are also transported, and held in correct proportion whilst doing so.

Abstract: A spin rate tracking system comprising a guidance system suitable for adjusting a flight path of a vehicle based on a spin rate of the vehicle, a signal reception system configured for receiving signal information from a global navigation system wherein a spin rate of the vehicle is derived from a substantially harmonic pattern produced amongst a global navigation signal.

Abstract: A method for producing a missile nose cone is disclosed. The method consists of manufacturing a first missile nose cone from a first lot of polymeric material and determining a first rupture value. The method further consists of manufacturing a second missile nose cone from a second lot of polymeric material and determining a second rupture value of the second missile nose cone. Both first and second lots of material are mixed into a test batch with one another based on their associated rupture values. An evaluation missile nose cone is then manufactured from the test batch and a determination is made as to whether the evaluation missile nose cone has a desired rupture value. If a desired rupture value is not obtained, then the mixing and evaluation steps are repeated.

Abstract: A system for firing multiple projectiles in a parallel or diverging manner is provided. The system can comprise tail-end portions of projectiles that add structure to a cartridge, provide for efficient combustion, allow projectiles to transition from a straight configuration in the cartridge to a splayed configuration in a chamber, and ensure complete evacuation of the chamber. The system can include a tail-end portion of a particular projectile with openings that distribute energy from combustion of an ignition charge, facilitating firing of multiple projectiles. A tail-end portion of a projectile can include a ball joint upon which the body portion of the projectile moves causing an angle between the body portion and the tail-end portion. A space can exist in the body portion adjacent to the ball joint to allow off-center shifting of the body portion with respect to the ball joint.

Abstract: A system and process for the aerodynamic stabilization of rocket-assisted artillery projectiles launched from smooth-bore cannons comprises multiple stabilization fins stowed circumferentially and held by a cap until muzzle exit. At muzzle exit, the cap separates and allows the fins to self-deploy using the energy stored within the fin material, which is either shape memory alloy or spring steel. The fins are then locked into place and serve to stabilize the projectile without interfering with the discharge of hot propelling gasses from the rocket nozzle.