Abstract: The present disclosure describes autonomous flight safety systems (AFSSs) that incorporate an autonomous flight termination unit (AFTU) enabling AFSS monitoring for various termination conditions that are used to activate a flight termination system (e.g., in the event a termination condition is detected). Such termination conditions include boundary limit detection (e.g., whether a vehicle position is outside or projected outside a planned flight envelope), as well as body instability detection (e.g., whether a pitch rate and yaw rate exceed some threshold indicative of vehicle instability). For instance, an AFTU may incorporate a three-axis gyroscope sensor and may implement instability detection processing based on information obtained via the sensor.

Abstract: Provided is a tailstock type vertical take-off and landing unmanned aerial vehicle and a control method thereof. The unmanned aerial vehicle is mainly composed of a fuselage, wings, ailerons, empennages, an elevator, a rudder, an engine, an attitude adjustment nozzle, a landing gear, and the like. The wings are symmetrically arranged on both sides of the middle of the fuselage; the ailerons are hinged to the trailing edges of the wings on the both sides; the empennages are located at the tail of the fuselage, and a form of vertical empennages+horizontal empennages or V-shaped empennages can be used; the elevator and rudder are hinged to the trailing edges of the empennages; the engine is arranged at the tail of the fuselage for producing main thrust.

Abstract: An aircraft controlled by compressed air according to an embodiment of the present invention comprises: a fuselage (10) having main wings (20) on both sides thereof; a first nozzle (12) mounted to the roof of the fuselage (10); second nozzles (22) mounted on the top surfaces of the main wings (20); a first tank (31) disposed in the fuselage (10) or the main wings (20) and storing compressed air; and a main control valve (40) for controlling the compressed air so that the compressed air is provided to the first nozzle (12) or the second nozzles (22).

Abstract: A hypersonic missile defense system for protecting a target from a hypersonic weapon, wherein the system includes a plurality of globule spheres in a defensive formation between the target and the hypersonic weapon. The globule sphere may include a proximity fuse; a plurality of fission spheres; a capacitor capsule; and a membrane separating a first formation material from a second formation material, both contained within the globule sphere.

Abstract: An augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface. An engine includes a high pressure chamber and the augmented aerospike nozzle. A vehicle for supersonic flight includes the engine with the augmented aerospike nozzle.

Abstract: A method of propulsion includes providing a high-speed-launch ramjet boost (HSLRB) stage and HSLRB engine attached to a launch aircraft providing a speed ?1.5 Mach. The HSLRB engine includes a combustion system and inlet(s) for air flow to the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator exhausts gas from combustion. A processor receives sensing signals from sensor(s) during flight that provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle, and if the inlet is a VG inlet to an inlet actuator to dynamically control the VG inlet shape. The HSLRB engine is ignited while attached to the aircraft at 1.5 to 1.99 Mach if assisting the aircraft to accelerate to 2.0 Mach, or at a speed of ?2.0 Mach if the aircraft can accelerate to 2.0 Mach autonomously, then the HSLRB stage is separated from the aircraft.

Abstract: An air to air refueling system that monitors and adapts the movement at an end of an air to air refueling hose of a tanker aircraft to counteract undesirable movements at the end of the hose though generating aerodynamic loads in the end of the hose. The system includes grid fins at the end of the hose that are automatically rotated to counteract the undesirable movements.

Abstract: A method includes determining a rotational position of a rotating projectile as a function of an orientation of a sensor on the rotating projectile. The method also includes actuating a steering mechanism on the rotating projectile at the determined rotational position. The method also includes altering the trajectory of the rotating projectile.

Abstract: A guided projectile including a precision guidance munition assembly utilizes at least one maneuver envelope to optimally control movement of at least one canard to steer the guided projectile during flight. The maneuver envelopes optimize movements of the at least one canard that effectuate movement in either the range direction or the cross-range direction, or both. The maneuver envelope enables optimal timing such that maneuvering in one direction does not come at the expense of maneuver authority in the other direction.

Abstract: An aircraft steering system includes an electric actuator, a clutch, at least one plasma actuator, and a controller. The electric actuator is configured to vary an angle of a flight control surface of an aircraft. The clutch is configured to cut off torque by driving of the electric actuator. The torque is to be transmitted to the flight control surface. The at least one plasma actuator is configured to form a flow of air on a surface of the flight control surface when the torque is cut off. The controller is configured to control the electric actuator, the clutch, and the at least one plasma actuator.

Abstract: An intelligent munition can position circuitry in a 12 gauge form factor that detects the distance from a target in real-time in order to deploy a parachute to slow the munition to a speed that is conducive to accurate, but non-lethal, deployment of at least one electrode toward the target. The munition can intelligently discharge electrical charge into the target via an electrode to disable the target. The munition may further monitor the target and deliver a subsequent electrical discharge in response to detected target movement.

Abstract: A vehicle capable of taking off and landing vertically and operating in water, land, air and submarine environments includes a fuselage, two main wings, ailerons, a vertical tail, a rudder, a horizontal tail, elevators, a propeller, rotor wings, rotor wing supports, etc. The vehicle has the advantages of adaptability to various environments, good concealment and strong survivability. Compared with a traditional unmanned rotorcraft, the vehicle has longer endurance time and larger load. Compared with a fixed wing UAV, the vertical take-off and landing function makes the work more convenient. Compared with unmanned diving equipment, the vehicle is applicable to richer environments, and can complete designated missions in air, land, water and submarine environments. Compared with a tilt rotor UAV in water, land, air and submarine environments, the vehicle is rapider in switching of various modes and is higher in stability.

Abstract: The first solid propellant is formed to have a columnar shape so as for a combustion surface to move to a first direction, and to have an end surface exposed to a combustion space. The surface of first solid propellant except for the end surface is covered with a barrier membrane. The position of combustion surface in the first direction is detected by a position sensor device in an always-on measurement or a fixed-point measurement. Based on the detected result, the consumption amount of the first solid propellant is estimated.

Abstract: A projectile with selectable angle of attack for increased impact on a target includes an active charge and controllable initiation device for initiation of the active charge, wherein the projectile also includes at least one side-acting impulse motor for tilting the projectile relative to its trajectory from a substantially vertical position, in which the front face of the projectile is directed toward the target, into a more horizontal position, in which the outer surface of the projectile is directed toward the target.

Abstract: A flow control system includes a movable wing attachable to a wing of an aircraft, and a plasma actuator mountable on a surface of the movable wing. The flow control system is configured to control air flow around the wing by having the changing of the steering angle of the movable wing work in conjunction with the operation of the plasma actuator.

Abstract: A pointing mechanism for use in an electric propulsion system of a spacecraft, the pointing mechanism comprises a mobile plate adapted to receive a thruster and defining a thrust vector of the thruster received on the mobile plate. The pointing mechanism further comprises a rotary actuator coupled to the mobile plate by means of a connecting element, the rotary actuator being configured to rotate the connecting element about a rotational axis of the rotary actuator such that the thrust vector defined by the mobile plate rotates about the rotational axis, wherein the thrust vector is inclined relative to the rotational axis.

Abstract: A method for controlling the attitude and/or flight path of a flight vehicle includes burning propellant in a gas generator to produce hot gas, storing the hot gas in an accumulator, and releasing the hot gas in the accumulator through one or more thrusters to control the attitude and/or flight path of the flight vehicle.

Abstract: A service satellite for providing station keeping services to a host satellite has a body, and a gripping mechanism attached to the body. The gripping mechanism is adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring forms an interconnected unit having a combined center of mass. The service satellite has at least two movable thrusters and at least one controller. The at least one controller maintains the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters do not pass through the combined center of mass, and are each offset from the combined center of mass.

Abstract: A system allowing for the tilting of the rocket motor such that, in the tilted position, the centre of the nozzle is located at least approximately on the neutral orientation axis of said rocket motor.

Abstract: Attitude of a vehicle may be controlled using movable mass. The movable mass may move inside a vehicle or its outline, outside of the vehicle or its outline, inside-to-outside and/or outside-to-inside of the vehicle or its outline, or any combination thereof. The movable mass may be a solid, liquid, and/or gas. When the center-of-mass of the vehicle is moved relative to the line-of-action of applied forces such as thrust, drag, or lift, a torque can be generated for attitude control or for other purposes as a matter of design choice. In the case of external movable masses that extend from the vehicle or its outline, when operating in endoatmospheric flight, or general travel through a fluid, aerodynamic forces from the atmosphere or general fluid forces may further be leveraged to control the attitude of the vehicle (e.g., aerodynamic flaps).

Abstract: A reaction control system (RCS) is provided for use with an air vehicle having a nose portion and a center of gravity aft of the nose portion. The RCS includes a belt element configured for selectively securing the RCS to the nose portion, and also includes a plurality of micro-rocket modules affixed to the belt element, each micro-rocket module being configured for being selectively activated to provide corresponding control moments to the air vehicle when secured to the nose portion thereof. A corresponding air vehicle, and a method for modifying an air vehicle, are also provided.

Abstract: An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.

Abstract: A control system for a missile includes a plurality of control surfaces that can be arrayed across a surface of the missile body, and a controller connected to the control surfaces to selectively move the control surfaces between an aerodynamic stowed position where the control surfaces conform to the surface of the body, and a deployed control position removed from the aerodynamic stowed position where the control surfaces extend from the surface of the body to interact with airflow over the body. The control surfaces are made of a material that includes a shape-memory alloy. Heating the control surfaces causes the shape-memory alloy to move the control surfaces from the aerodynamic stowed position to the deployed control position. By selectively extending and retracting the control surfaces, the control system provides the ability to control the missile's direction of travel or to reduce roll about a longitudinal axis of the body.

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

Abstract: A combined steering and drag reduction device for a missile is disclosed. The device includes a base and an upper part which are arranged in succession along a main axis of navigation of the missile. Advantageously, the device also includes a pressurized-gas generator and at least one lateral thruster having at least one nozzle configured to deliver a thrust, by expanding gas transmitted by the generator and oriented along an axis substantially perpendicular to the main axis. The at least one lateral thruster also has at least one stabilizing chamber configured to expand the gas transmitted by the generator and expel it through an outlet section of the base substantially perpendicular to the main axis.

Abstract: An orbit attitude control device includes a plurality of nozzles and a control section. The nozzles inject a combustion gas supplied from a combustion chamber, opening degrees being controlled in accordance with opening degree command values. The control section calculates nozzle opening degree correction values for the opening degree command values in response to a detection value of a pressure of the combustion chamber and a command value for the pressure, and correct the opening degree command values by the nozzle opening degree correction values. Each nozzle opening degree correction value is determined based on each opening degree command value.

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: A flight vehicle includes a nose portion, a fuselage retaining structure aft of the nose portion, and an axial motor for expelling axial thrust along a longitudinal axis of the flight vehicle. Radial motors are coupled to the retaining structure and axisymmetrically arranged about the axial motor. Each radial motor is configured to expel radial thrust radially outwardly in respect to the flight vehicle. Roll thrusters are operatively coupled with the radial motors and coupled to the fuselage retaining structure. The roll thrusters are configured to provide a roll moment of the flight vehicle about a central longitudinal axis of the flight vehicle. Ejectors are operatively coupled to the radial motors, and a controller is operatively coupled to the radial motors and the ejectors. The controller is configured to selectively fire and selectively eject the radial motors to maintain relative centering of a center of gravity of the flight vehicle.

Abstract: An orbit attitude control device includes a divert thruster including a plurality of nozzles. First group nozzles inject combustion gas in opposite directions along a first axis. Second group nozzles inject combustion gas in opposite directions along a second axis. A control section calculates correction values for opening degree commands based on a detection value of a pressure of the combustion chamber and a command value of the pressure, and corrects the opening degree command values by the correction values. The device further includes a first axis acceleration sensor for detecting acceleration along the first axis and a second axis acceleration sensor for detecting acceleration along the second axis. The correction values for the opening degrees of the first group nozzles are determined by a first axis acceleration, and the correction values for the opening degrees of the second group nozzles are determined by a second axis acceleration.

Abstract: System for steering a flying object using pairs of lateral nozzles—It comprises a gas generator (5) capable of being connected to lateral nozzles (7) via moveable plug devices (8), controlling the flow of gases coming from the generator through said nozzles. The lateral nozzles (7) are associated with at least one pair (P1, P2, P3, P4) such that the nozzles of the pair are aligned in a given axis (A1) and arranged opposite to each other, and, between the two aligned nozzles of the pair, a single controllable plug device (8) is provided, connected to said generator (5) and capable of controlling the flow of gases through said nozzles (7) in both directions.

Abstract: A system for in-flight attitude control and side-force steering includes a thruster body and a plurality of valves capable of generating side thrusts put into communication with the thruster body. The valves are arranged in two sets of valves spaced apart from each other towards the front and towards the rear of the thruster body in substantially symmetrical manner relative to the center of gravity of the vehicle situated on a longitudinal axis (A) of the vehicle. Each set comprises a first pair of valves generating thrust in opposite directions along axes that are not in alignment and are parallel to a first axis, and a second pair of valves generating thrust in opposite directions along axes that are not aligned and are parallel to a second axis. The first and second axes are distinct and perpendicular to the longitudinal axis of the vehicle.

Abstract: An automotive headlamp includes: a light source; a movable shade configured to be movable between a first position shielding a part of light emitted from the light source and a second position having a different light shielding volume; a motor configured to generate a driving force to move the shade from the first position to the second position; and a stopper for high beam to fix the movable shade, which has been moved from the first position to the second position, at the second position. The motor is configured such that a motor phase is lag when the motor moves the movable shade to the second position by the driving force generated by supplied power and fixes the same, and an electric current is applied to the motor when the movable shade is fixed at the second position.

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes one or more radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the plurality of aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes a rocket motor to accelerate the eject vehicle along an intercept vector, alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, and divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector. The eject vehicle activates at least one of the alignment thrusters responsive to the intercept vector.

Abstract: A projectile includes a propulsion booster for producing pressurized gases, a nozzle for expelling the pressurized gases produced by the booster, and a supplementary integrated actuation system. The integrated actuation system selectively directs propellant from a storage reservoir of the integrated actuation system through an interiorly-located outlet of the integrated actuation system located at the nozzle and into the nozzle, thus changing a direction of the pressurized gases expelled by the booster. The integrated actuation system also selectively directs propellant from the storage reservoir through a peripherally-located outlet of the integrated actuation system, to produce thrust at an external periphery of the projectile, thus diverting the projectile.

Abstract: System for steering, about its axes of rotation, a moving body propelled by jet reaction, particularly a missile. The system (1) comprises two first flow deflectors (3, 4) of which one (3) is able to act exclusively on the outlet flow from one of the nozzles (17) of the moving body (M) which is provided with two jet nozzles (17, 18), and of which the other (4) is able to act exclusively on the outlet flow from the other jet nozzle (18) of said moving body (M), these two first flow deflectors (3, 4) interacting in such a way as to be able to steer the moving body (M) about two of its three axes of rotation, and a second flow deflector (5) which is able to act on the outlet flows from the two jet nozzles (17, 18), but on just one outlet flow at a time, so as to be able to steer the moving body (M) about the third of its axes of rotation.

Abstract: An exoatmospheric vehicle uses a control system that includes a thrust system to provide thrust to control flight of the vehicle. A regenerative heat system is used to preheat portions of the thrust system, prior to their use in control of the vehicle. The heat for preheating may be generated by consumption of a fuel of the vehicle, such as a monopropellant fuel. The fuel may be used to power a pump (among other possibilities), to pressurize the fuel for use by thrusters of the thrust system. The preheated portions of the thrust system may include one or more catalytic beds of the thrust system, which may be preheated using exhaust gasses from the pump. The preheating may reduce the response time of the thrusters that have their catalytic beds preheated. Other thrusters of the thrust system may not be preheated at all before operation.

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: An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fixed, there is no servo control to the main nozzles or fins to affect attitude control. The use of a common pressure vessel enables an integrated propulsion and ACS that can be compact, lightweight and inexpensive.

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: A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks.

Abstract: Projectiles that include a propulsion system and a launch motor which are located on opposing sides of a payload and a method of directing a projectile toward a target are generally described herein. Placing the propulsion system and the launch motor on opposing sides of the payload may provide many potential advantages when designing the projectile. These design advantages may make it easier to create a projectile that includes more propellant and/or payload while still permitting the projectile to be stored within existing containers having a fixed size.

Abstract: New missile systems are provided, implementing reduced pre-deployment weight, higher impact and greater deployment flexibility, among other advantages. In some embodiments, mid-flight oxygen filtration from atmospheric air, followed by concentration, compression and/or storage in ideal oxidizer deployment locations, leads to enriched, greatly increased oxidizer load and/or far greater missile weight just prior to impact. Among additional benefits, missiles implementing the system may be far less volatile, and therefore safer, prior to deployment and the concentration of oxidizer may be more concentrated than with ambient oxygen, overcoming the limitations of current fuel/air and other thermobaric explosives.

Abstract: Embodiments of a flight vehicle are provided, as are embodiments of a method for manufacturing a flight vehicle. In one embodiment, the flight vehicle includes a solid-propellant rocket motor, control circuitry, and an electrically-interconnective support structure. The electrically-interconnective support structure includes a load-bearing frame and a plurality of electrical conductors embedded within the load-bearing frame. The solid-propellant rocket motor is mounted to the load-bearing frame, and the plurality of electrical conductors embedded within the frame electrically couples the solid-propellant rocket motor to the control circuitry.

Abstract: An air vehicle, such as a missile or a steerable submunition released from a missile or another air vehicle, has a bilateral thrust system for steering. The thrust system includes a pair of diametrically-opposed divert thrusters that provide thrust having radial components in opposite radial directions. In order to control the direction of thrust, the air vehicle controls rotation of the divert thrusters and/or timing of the firing of the thrusters. The air vehicle (or some part of the air vehicle that includes the divert thrusters) may be discretely rolled to position the divert thrusters to produce desired steering thrust. Alternatively, the air vehicle or part of the air vehicle may be continuously rolled, with the steering controlled by timing the thrust to the divert thrusters, such as by allocating thrust between the diametrically-opposed thrusters. Pressurized gas may be allocated between the two thrusters by use of pintle valve.

Abstract: System for steering a flying object using pairs of lateral nozzles—It comprises a gas generator (5) capable of being connected to lateral nozzles (7) via moveable plug devices (8), controlling the flow of gases coming from the generator through said nozzles. The lateral nozzles (7) are associated with at least one pair (P1, P2, P3, P4) such that the nozzles of the pair are aligned in a given axis (A1) and arranged opposite to each other, and, between the two aligned nozzles of the pair, a single controllable plug device (8) is provided, connected to said generator (5) and capable of controlling the flow of gases through said nozzles (7) in both directions.

Abstract: A method for deploying a control surface from an exterior surface of a spinning projectile during flight is provided. The method including: moving the control surface in an interior of the projectile such that a portion of the movement retracts the control surface into the interior and a portion of the movement extends the control surface from the exterior surface of the projectile; determining a roll angle of the projectile; and synchronizing the movement of the control surface with the roll angle of the projectile.

Abstract: A shape memory stored energy assembly includes a projectile housing having a projectile lumen. A projectile is within the projectile lumen and the projectile is movable relative to the projectile housing. A shape memory actuator is coupled between the projectile anchored end and the projectile housing. The shape memory actuator is configured to transition from a strained energy stored configuration to a fractured kinetic delivery configuration at a specified temperature range to propel the projectile through the projectile lumen. A method includes storing energy in a shape memory actuator coupled with a projectile. The stored energy in the shape memory actuator is released and propels the projectile. Releasing the stored energy includes heating the shape memory actuator, tensioning the shape memory actuator, and fracturing the tensioned shape memory actuator at a fracture locus to propel the projectile away from the fracture locus.

Abstract: An air vehicle, such as a missile, for example an interceptor, includes control surfaces and a vectored thrust system, both used for steering the missile. A controller is operatively coupled to both steering mechanisms, and is configured to operate in a low dynamic pressure mode, which uses the vectored thrust system for at least part of the steering, only when the dynamic pressure is low, such as when the missile is at high altitude. At higher dynamic pressure, such as at lower altitude, the controller is configured to operate in a high dynamic pressure mode that uses only the control surfaces for steering. This allows the interceptor to operate at higher altitudes than interceptors that use only control surfaces for steering during flight. During flight for a high altitude interception the missile shifts from the high dynamic pressure mode to the low dynamic pressure mode.

Abstract: Embodiments of a propulsion and maneuvering system that may be suitable for use during a terminal phase in an interceptor are generally described herein. The propulsion and maneuvering system may include one or more axial thrusters to provide thrust along axial thrust lines that run through a center-of-gravity of the interceptor and a plurality of divert thrusters to provide thrust in radial directions. The combination of divert and axial thrusters may allow the interceptor to respond to a maneuvering target and may allow the interceptor to increase its velocity along a line-of-sight (LOS) to a target to change target impact/engagement time.

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes one or more radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the plurality of aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes a rocket motor to accelerate the eject vehicle along an intercept vector, alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, and divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector. The eject vehicle activates at least one of the alignment thrusters responsive to the intercept vector.