Abstract: An inverted F antenna for use in a projectile includes a ground plane and a radiating element oriented orthogonal to the ground plane and centered on the ground plane. The radiating element includes a ground stub trace having a relatively thick width, a meandering trace with a vertical orientation and a relatively high ground clearance and a feed trace having a tapered head.

Abstract: A blind-spot detection system includes an angle-detector, a radar-sensor, and a controller. The angle-sensor is used to determine a trailer-angle relative to a host-vehicle of a trailer being towed by the host-vehicle. The radar-sensor is used to detect an other-vehicle present in a blind-zone proximate to the host-vehicle. The controller is in communication with the angle-detector and the radar-sensor. The controller is configured to adjust a sensing-boundary that defines the blind-zone based on the trailer-angle.

Abstract: A plurality of GNSS satellite signals feeds the signal processing engine operating in certain processing mode including carrier phase smoothed pseudorange positioning, precise point positioning (PPP), pseudorange differential (DGNSS), and carrier phase differential (RTK). The processing engine calculates two estimates of the ionosphere delay for each satellite: the filtered delay and the instant delay. Comparison of them allows to detect turbulent variation of the ionosphere and adjust parameters of two-parametric dynamic mode which improves positioning precision.

Abstract: A quadrature self-injection-locked radar utilizes a phase shifter to make a oscillation signal operating in two phase modes, and utilizes a frequency demodulator for frequency demodulation and a signal processor for signal processing to eliminate the nonlinear distortion caused by self-injection locked phenomenon. Therefore, the self-injection locked radar can be applied to more cases for detecting displacement variations with any range.

Abstract: An electronic circuit includes adjustment units configured to receive a same oscillating signal having a predetermined frequency and to adjust a phase and an amplitude of the oscillating signal to produce output oscillating signals, coupling points configured to supply the output oscillating signals produced by the adjustment units to antennas, couplers provided in one-to-one correspondence with outputs of the adjustment units, equal-length lines sharing the same length and extending from the couplers, respectively, mixer circuits coupled to the equal-length lines, respectively, each of the mixer circuits being configured to receive a same reference oscillating signal having the predetermined frequency and a corresponding one of the output oscillating signals, and a control circuit configured to cause the adjustment units to adjust at least one of the phase and the amplitude in response to direct-current components in outputs of the mixer circuits.

Abstract: Systems, methods and non-transitory, computer-readable storage mediums are disclosed for a multimode GNSS odometer. In some implementations, a method comprises: obtaining, by a device, position and velocity data from a sensor embedded in, or coupled to the device; statistically combining, by the device, the position and velocity data to generate a first delta distance travelled by the device over a period of time, the statistical combining including weighting a contribution of an integrated speed to the first delta distance, the integrated speed derived from the obtained velocity data and period of time; filtering, by the device, the first delta distance to generate a filtered first delta distance; and generating, by the device, a first estimate of total distance travelled by the device based on the filtered first delta distance.

Abstract: Systems, methods, and software described herein provide enhancements for orbital satellite platform. In one example, a satellite system includes satellite devices in low-earth orbit (LEO) configured to establish a pseudo-geosynchronous configuration corresponding to a ground communication system by at least transferring instructions for traffic routing from outgoing satellite devices leaving the pseudo-geosynchronous window for receipt by target satellite devices entering the pseudo-geosynchronous window. During passage within the pseudo-geosynchronous window, the target satellite devices are each configured to route communications received in the target satellite devices from ones of the satellite devices through the ground communication system in accordance with the instructions for traffic routing.

Abstract: A spacecraft includes a payload subsystem, the payload subsystem including a phased array of feed elements configured to illuminate an antenna reflector, a beam forming network (BFN) disposed proximate to the array of feed elements, and a plurality of power amplifiers disposed between the BFN and the array of feed elements. The BFN includes a plurality of variable amplitude and phase adjusting arrangements disposed between (i) m:1 power combiners that are communicatively coupled with the power amplifiers and (ii) at least one 1:n power splitter, where m is greater than 1, and n is greater than 2.

Abstract: An object is to provide in a positioning device of a moving body such as a vehicle, a technique which can modify a built-in clock error of a moving body to increase accuracy of a velocity. The positioning device includes a built-in clock error estimating unit which estimates a built-in clock error of the vehicle as a built-in clock error based on a difference between a delta range and a calculated range rate, and a range rate estimating unit which estimates a vehicle stop range rate based on position and velocity of GPS satellite based on transmission signal and a vehicle position, and modifies a calculated range rate, based on the built-in clock error. Further, the positioning device includes an own vehicle velocity calculating unit which calculates own vehicle velocities in three axial directions which form an orthogonal coordinate system, based on a navigation matrix, the vehicle stop range rate and the modified calculated range rate.

Abstract: There is provided an inflatable dummy target comprising a chassis wrapped with a sheet. The chassis can be formed by individual inflatable ducts and can comprise at least two ring-shaped ducts interconnected by one or more elongate ducts. The inflatable dummy target can further comprise rigidizing ducts. The inflatable dummy target geometry can be conical, cylindrical, etc. Optionally, the inflatable dummy target can comprise several attached axi-symmetrical sections, wherein each section has a chassis wrapped with a sheet, the chassis formed by individual inflatable ducts. Optionally, the shape of each section can be selected from the group consisting of conical, frustoconical and cylindrical forms.

Abstract: Embodiments for providing dynamic azimuth scanning are generally described herein. In some embodiments, weather survey measurements are performed to estimate environmental losses as a function of azimuth angles. Gain improvements are determined based on the amount of energy increase used at different azimuth angles derived from the azimuth loss survey measurements. A gain profile is generated based on the determined gain improvements. An azimuth offset profile is derived using the gain profile to define azimuth angles where progressive scan back is used in the area of environmental losses to provide additional power and to define azimuth angles where progressive scan forward is used in regions of low loss. Dynamic electronic azimuth beam steering provides a near-constant average target detection range as a function of azimuth in the presence of non-uniform loss.

Abstract: An antenna apparatus for connection to a fill level measurement device for detecting a topology of a filling material surface is provided, including an antenna configured to emit a measurement signal towards the surface and to receive the measurement signal reflected from the surface; a drive shaft configured to rotate the antenna about the drive axis while the measurement signal is being emitted; a first energy store configured to supply the antenna apparatus with electrical energy, wherein the antenna includes an array of radiator elements configured to emit the measurement signal and to receive the reflected measurement signal, and wherein the first energy store is attached to the antenna apparatus such that it rotates with the antenna when the antenna is rotated by the drive shaft.

Abstract: A device for radar applications includes a computing engine, a radar acquisition unit connected to the computing engine, a timer unit connected to the computing engine, a cascade input port, and a cascade output port. The cascade input port is configured to convey an input signal to the computing engine and the cascade output port is configured to convey an output signal from the computing engine. Further, an according system, a radar system, a vehicle with such radar system and a method are provided.

Abstract: Systems and methods according to one or more embodiments are provided for a true time delay function. The true time delay function may be implemented, for example, as a selectable signal delay circuit for broad bandwidth time control of phased array antenna element signals. In one example, a system comprises a selectable signal delay circuit including a plurality of delay lines, an input port, and an output port, wherein the delay lines are disposed between the input port and the output port. A plurality of amplifiers are coupled to corresponding ones of the plurality of delay lines and coupled between the input port and the output port. A plurality of switches are configured to selectively couple the plurality of delay lines and corresponding amplifiers to provide a selectable delay and amplification between the input port and the output port. Additional systems and methods are also provided.

Abstract: One example embodiment includes an aircraft system. The system includes a body comprising a payload and a propulsion system. The propulsion system can be configured to enable launch of the aircraft system. The system also includes a shrouding system that substantially encloses at least a portion of the body in a shrouded state. The shrouding system includes a fairing portion and a sleeve portion that are arranged as detachably coupled with respect to each other and with respect to the at least a portion of the body. The fairing portion can separate from the sleeve portion in a deployed state and the body can become axially separated from the sleeve portion in the deployed state. The aircraft system can switch from the shrouding state to the deployed state during a detach stage of the launch of the aircraft system.

Abstract: The invention relates to a method for computing a bound B up to a given confidence level 1??, of an error in a state vector estimation KSV of a state vector TSV of a physical system as provided by a Kalman filter. The method decomposes the errors of the Kalman solution as a sum of the errors due to each of the measurement types used in the filter, In addition, the contribution of each type of measurement is bounded by a multivariate t-distribution that considers the error terms from all the epochs processed. Then, the method implements three main operations: computing a probability distribution of the measurement errors for each epoch and measurement type; summing the previous distributions to obtain a global distribution that models the Kalman solution error; and computing the error bound B for a given confidence level from the resulting distribution.

Abstract: An antenna apparatus for a fill level measurement device including an antenna unit that is rotatably mounted and comprises an array made up of a plurality of radiator elements. The radiator elements are arranged in a plane which, together with the axis of rotation of the antenna unit, forms an angle ? that does not equal 90 degrees.

Abstract: This invention relates to devices and processes for geophysical prospecting, subsurface fluid monitoring and, more particular, to the use of interferometric techniques using Control Source Electromagnetic (“CSEM”) and Magnetoturelic (“MT”) signals to create images of sub-surface structures and fluids.

Abstract: Aspects of the present disclosure involve a method for determining a road vehicle velocity and slip angle. The current disclosure presents a technique for identifying a vehicle's velocity and slip angle, in the vehicle's coordinate frame. In one embodiment, two or more sensors are orthogonally located on the underside of the vehicle in order to obtain longitudinal and lateral velocity information for slip angle determination. In another embodiment, the two or more sensors can include an array of elements for beam steering and receiver beamforming. Spatial diversity is leveraged in identifying at least a slip angle and/or velocity of the vehicle. Doppler mapping is used as a means for slip angle determination and the clutter ridge of the Doppler map is embraced for identifying the slip angle.

Abstract: A projectile, such as a railgun-launched projectile, includes a single-piece body that is additively manufactured. The single piece body includes fuel within it, and one or more cavities for receiving an oxidizer. The body also defines one or more combustion chambers therein for combustion of the fuel and oxidizer as part of a divert thruster system. Thus the projectile is able to fully contain the divert thruster system within the single-piece body without using any hot gas seals as part of the system. The body may also define a cavity for receiving a pressurized fluid, used as part of a cold-gas attitude control system of the projectile. The body may also define passages between the pressurized fluid cavity and other parts of the attitude control system, such as valves and/or nozzles that are outside of the body, for example being aft of the one-piece body.