USA as Represented by Secretary of the Navy

Other

Donald Patrick Hilliard

Dean Lucian Mensa

Michael Patrick Hilliard

Glenda Esnardo Hilliard

Nathan Andrew Alday

Paul E Nelson

Christina Ann Hilliard

Robert Barreto

Andrew Hamilton Kay

Christopher F Calderon

Yogeshkumar M Patel

Leroy Francis Mumma

Mickey Benson

Wai-Mao Yu

A system for augmenting 360-degree aspect monostatic radar cross section of an aircraft. The system may comprise a pair of pods mountable on opposing wing tips of an aircraft and each having a pod housing with an elongate body tapering forwardly to a nose and rearwardly to a tail. Each pod may comprise a forward SDL disposed within the nose, a rear SDL disposed within the tail, and a pair of mid-body SDLs disposed within a mid-section of the pod housing. The SDLs may be arranged within the pods to reflect radiation and provide coverage around the aircraft over a region of about 360 azimuth degrees. Each SDL may comprise radar absorbing material located on an interior reflective surface, and portions of the elongate bodies may be constructed of radome material. The SDLs may be Luneburg lens having diameters of at least approximately 8-inches.

System for augmenting 360-degree aspect monostatic radar cross section of an aircraft

A GPS collision avoidance apparatus which uses Global Positioning System (GPS) information and computer processing to determine the location of man made and natural occurring obstacles to allow a user to avoid a collision with these obstacles. The collision avoidance apparatus has a collision decision processor which analyzes position and motion dynamics data including a direction of motion, a velocity and an acceleration for a user utilizing collision avoidance apparatus to determine whether a collision will occur and then to provide protection for the user in the event a collision is likely to occur.

GPS collision avoidance apparatus

A variable scattering device comprising a object which may be an antenna, a load impedance which is optimal and a switch which connects the scattering object to the load impedance. By using the switch to switch the load impedance in and out of the connection with the scattering object a large dynamic range for a fluctuating scattered signal may be achieved.

Variable scattering device

A sensor transmits a pulse in the direction of travel of a user and receives reflections from any obstacle in the path. The sensor provides two signals which indicate the relative range and the relative velocity between the user and the obstacle. A decision logic and control circuit processes the signals and determines whether the user and the obstacle are close enough and there is sufficient closing velocity to present a hazard to the user. When the circuit determines there is a hazard, the circuit activates a warning device. An activation signal is also generated when the circuit determines that the user cannot avoid the obstacle. This signal is supplied to an automatic protection system which includes an air bag located on the front portion of a jacket worn by the user. The air bag is inflated by the activation signal to protect the user when colliding with the obstacle.

Personal collision warning and protection system

A parachute recovery system which provides for the recovery of a payload such as a target drone without damage by allowing for a safe, non-destructive landing of the payload at a desired location. The parachute recovery system comprises a payload, a parachute or parasail and a guidance control electronics and servo system. The parachute, which is rectangular in shape, is connected by a plurality of control lines to the guidance control electronics and servo system, which is attached to the payload. The payload may be an air launch component such as a spacecraft, a target drone, unmanned air vehicle, camera film, or similar apparatus. The guidance control electronics and servo system is used to control glide path trajectory and provide for a safe non-destructive landing of the payload. Servo system adjust the length of each of the plurality of control lines attached to the parachute to provide a means for controlling the parachute so as to control the speed, direction and lift of the parachute recovery system.

Precision parachute recovery system

A parachute recovery system which provides for the recovery of a payload such as a target drone without damage by allowing for a safe, non-destructive landing of the payload at a desired landing location. The parachute recovery system comprises a payload, a parachute or parasail and a guidance control electronics and servo system. The parachute, which is rectangular in shape, is connected by a plurality of control lines to the guidance control electronics and servo system, which is attached to the payload. The payload may be an air launch component such as a spacecraft, a target drone, unmanned air vehicle, camera film, or similar apparatus. The guidance control electronics and servo system is used to control glide path trajectory and provide for a safe non-destructive landing of the payload. Servo system adjust the length of each of the plurality of control lines attached to the parachute to provide a means for controlling the parachute so as to control the speed, direction and lift of the parachute recovery system.

A multistatic radar signature measurement apparatus comprising a curvilin sensor array of photonic sensors which are used to measure the radar cross section of a target. The array of photonic sensors provide for the simultaneous collection of target scattered measurement data over an approximately semi-spherical field of view. Laser light passing through each photonic sensor of the sensor array is modulated by the photonic sensor in direct proportion to the strength/intensity of scattered waves from the target as the scattered waves pass through each photonic sensor of the sensor array. The modulated light from each sensor of the sensor array is then transmitted to an optical switching network which samples the optical signals from the array. The sampled optical signals are next provided to an RF receiver which converts the sampled optical signals to equivalent RF electrical signals. An analog to digital converter then samples and digitizes the RF signals from the RF receiver providing at its output a serial data stream which is supplied to a digital computer. The digital computer processes the serial data stream from the analog to digital converter calculating the radar cross section for the target.

Multistatic radar signature measurement apparatus

An electromagnetic field sensing apparatus which detects an incoming electromagnetic field and provides an RF electrical signal indicative of the strength of the field. The electromagnetic field sensing apparatus includes a metallic antenna which intercepts the incoming planar electromagnetic wave and provides an electrical signal indicative of the strength/intensity of the field. A microwave amplifier receives the electrical signal, amplifies the signal by a factor of at least 100 and then supplies the amplified signal to an electro-optic modulator. A first light source located along a first optical path transmits polarized laser light through the electro-optic modulator. The electro-optic modulator, in response to the amplified electrical signal modulates the polarized light when the metallic antenna detects the incident electromagnetic wave. A photodetector located along the first optical path detects the modulated light as it exists from the electro-optic modulator. In this manner incident planar wave electromagnetic fields are detected and measured. A second light source, located along a second optical path, transmits a monochromatic laser light beam along the second optical path to a photovoltaic cell which then provides a DC bias voltage to the microwave amplifier.

Optically powered amplifier used by an electromagnetic field sensor to

An electromagnetic field sensor for use in a target seeking missile which asures the amplitude, phase, frequency and polarization of an incoming electromagnetic field as well as the angle of arrival of the incident electromagnetic field. A Luneberg lens is mounted in the radome of the missile. The Luneberg lens focuses an electromagnetic wave reflected from a target which then passes through the radome and enters the Luneberg lens on one side of the lens onto a point on the opposite side of the lens. A photonic sensor which may be a single electro-optic modulator or a pair of electro-optic modulators is positioned on the Luneberg lens at the point upon which the incident electromagnetic wave is focused. When a pair of electro-optic modulators are used as the sensor the sensing axis of one of the electro-optic modulators is generally perpendicular to the sensing axis of the other electro-optic modulator. Polarized light is provided to each electro-optic modulator of the sensor along an optical path which passes through the modulator. Each electro-optic modulator modulates the polarized light passing therethrough when the electro-optic modulator detects the incident electromagnetic wave. A photo-detector located along the optical path for each electro-optic modulator detects the modulated light as it exits from the electro-optic modulator.

Photonic electromagnetic field sensor for use in a missile

An improved tamper-resistant seal for use with generally U-shaped flexible closure devices, such as tabs and wire wraps, comprising an annular band dimensioned to encircle a flexible closure device and heat-shrinking the band to closely fit about the closure device to prevent removal of the closure device without prior destruction of the annular band.

Bag having tamper-resistant seal

An electromagnetic field sensor apparatus which measures the amplitude, pe, frequency and polarization of an incoming electromagnetic field as well as the angle of arrival of an incident electromagnetic field. A Luneberg lens focuses an incoming electromagnetic wave entering on one side of the Luneberg lens onto a point on the opposite side of the lens. A pair of photonic sensor which may be electro-optic modulators or Pockel cells are positioned on the Luneberg lens at the point upon which the incident electromagnetic wave is focused. The sensing axis of one of the electro-optic modulators is perpendicular to the sensing axis of the other electro-optic modulator. Polarized light is provided to each photonic sensor along an optical path which passes through the sensor. Each photonic sensor modulates the polarized light passing therethrough when the photonic sensor detects the incident electromagnetic wave. A photo-detector located along the optical path for each photonic sensor detects the modulated light as it exits from the photonic sensor. The signal output of each photo-detector is electrically coupled to a power combiner and divider circuit which in combination with a network analyzer is utilized to measure the polarization of an incident electromagnetic wave.

Photonic electromagnetic field sensor apparatus

An electromagnetic field sensor apparatus which measures the field strength and phase of an incident electromagnetic field as well as the angle of arrival of an incident electromagnetic field. The electromagnetic field sensor apparatus comprises a Luneberg lens which focuses an incoming planar electromagnetic wave entering on one side of the Luneberg lens onto a point on the opposite side of the lens. A photonic sensor is positioned on the Luneberg lens at the point upon which the electromagnetic wave is focused. A light source is located along an optical path which passes through the photonic sensor for transmitting polarized light through the sensor. The photonic sensor modulates the polarized light passing therethrough when the photonic sensor detects the incident electromagnetic wave. A photodetector located along the optical path detects the modulated light as it exists from the photonic sensor. In this manner incident electromagnetic fields may be detected and measured without having scattered fields effect the measurement.

Growing community of inventors

Camarillo, CA, United States of America

Donald Patrick Hilliard