According to a first aspect of the present invention, there is provided a fuse system (22) for a munitions projectile, the system comprising: a first electro-optic transmitter (24); a first electro-optic receiver (30); the first electro-optic transmitter (24) being arranged to receive electrical power, and to use that received electrical power to transmit an optical signal (28) to the first electro-optic receiver (30); the first electro-optic receiver (30) being arranged to receive the optical signal (28), and to use that received optical signal (28) to transmit electrical power to an element (34) of the fuse system (22) connected to the first electro-optic receiver (30).

A method for generating power in a gravity dropped munition, the method including: winding a cable around a drum of a generator associated with the munition; attaching the cable from the generator to a portion of an aircraft; separating the munition from the aircraft to unwind the cable from the drum to release the cable from the drum after a predetermined amount of rotation of the drum; converting the rotation of the drum to energy in a spring as the cable is unwound from the drum; restricting movement of an intermediate member connecting the drum to the generator while the cable is being unwound from the drum; and ending the restricting when the cable is released from the drum allowing the intermediate member to engage the drum with the generator to produce power from the generator.

A powered projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments a collar is rotatably mounted to a control support portion with a plurality of aerodynamic surfaces thereon for despinning the collar. An alternator configured as an axial flux machine with a stator arranged can be axially adjacent to one or more rotors, the stator including a plurality of windings and the one or more rotors each including a plurality of permanent magnets arranged about the face of the respective one or more rotor. In various embodiments the projectile includes an assembly of projectile control circuitry. In one or more embodiments, upon relative motion of the rotor with respect to the stator, magnetic flux from the magnets interacts with the windings of the stator and passes through an air gap between the one or more rotors and stator.

A detonator installation (10) in which a detonator fire capacitor (36) which is connected in series with an inductor (18) is charged from a low voltage source (16) by repeatedly opening and closing a switch (20) thereby to cause a collapsing magnetic field in the inductor (18) which results in a charging current flow to the capacitor (36).

A device responsive to an acceleration pulse event, the device including: a piezoelectric device configured to generate a voltage over a duration responsive to one or more acceleration pulse events; an electrical storage device configured to receive a portion of the generated voltage to accumulate a charge; an energy dissipating device coupled to the electrical storage device and configured to dissipate the accumulated charge following the one or more acceleration pulse events and not to substantially dissipate the accumulated charge during the one or more acceleration pulse events; and a voltage limiting device coupled to the electrical storage device and configured to limit the portion of the generated voltage applied to the electrical storage device to a predetermined limit.

A wireless electronic initiation device for a detonator via a shock tube comprises an initiation member for initiation the shock tube and an energy storage for providing initiation energy to said initiation member. The initiation device comprises also a wireless communication device with a receiver for receiving an initiation command in a wireless way from an initiation arrangement. The initiation device comprises also a controller, which is configured to determine said received initiation command and based on said received initiation command configured to activate said initiation member to ignite the detonator initiator (108) by the energy fed from the energy storage.

A method for storing energy in a device upon acceleration of the device. The method including: permitting a first movable member configured to be movable in one direction relative to a base; biasing the first movable member in a second direction opposed to the first direction; permitting a plurality of second movable members, to be each movable towards an engagement surface of the first movable member when subjected to a predetermined acceleration event in a direction offset from the first direction; and sequentially engaging a portion of the engagement surface, which when pressed causes a movement of the first movable member in the one direction against a biasing force of the first biasing member, upon an increasing acceleration of the base such that energy is stored in the first biasing member.

A wireless detonator (10) includes a detonation side receiving antenna (11), a detonation side transmitting antenna (18), an initiator (14) and a detonation side electronic circuit. The detonation side receiving antenna (11) receives energy for driving the detonation side electronic circuit, a control signal and an initiation signal. The detonation side electronic circuit receives the energy, the control signal and the initiation signal via the detonation side receiving antenna (11), transmits a response signal via the detonation side transmitting antenna (18) and ignites the initiator (14) in accordance with the initiation signal. A response frequency of the response signal is set to be greater than or equal to 100 MHz and less than or equal to 1 GHz.

A Projectile Continuous Power Module (PCMP) is configured to take incoming or oncoming airflow of an inflight projectile and direct the airflow to a turbine for converting the airflow into electrical power. The PCMP is mounted within or otherwise coupled to an airframe of the projectile. The PCMP is coupled to the projectile in a manner such that an air inlet of the projectile is positioned to capture incoming or oncoming boundary layer airflow as the projectile travels.

A micro-electro-pyrotechnic energy-harvesting apparatus to harvest an incidental portion of a propellant energy utilized when a munition is fired freeing a magnet to strike an impact pin that strains a piezoelectric element. The piezoelectric element generates a collected voltage, which triggers a pyrotechnic initiator that, on activation, produces a straining force on a plurality of stacks of piezoelectric elements. The strained piezoelectric elements, in turn, generate a high voltage output sufficient to ignite the munition's explosive material. The apparatus may be quite small, for example, the cross-sectional size of a pen, which is about one centimeter, yet suitable for generating an electrical ignition of the explosive material.