Abstract: A signal testing apparatus is provided. The signal testing apparatus generally comprises a recording device that is configured to receive a plurality of signals representative of a plurality of electromagnetic waves that correspond to a pre-defined period of time. The recording device is further configured to record a plurality of digital representations of the signals such that each digital representation corresponds to a separate signal. A processing device is coupled to the recording device, wherein the processing device is configured to introduce at least one operational parameter to each of the digital representations. A play-back assembly is coupled to the recording device and to the processing device, wherein the play-back device is configured to play each of the digital representations simultaneously in real-time to facilitate verification of each of the signals.

Abstract: A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft.

Abstract: Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise.

Abstract: Embodiments of the present invention provide systems and methods for depositing materials on either side of a freestanding film using selectively thermally-assisted chemical vapor deposition (STA-CVD), and structures formed using same. A freestanding film, which is suspended over a cavity defined in a substrate, is exposed to a fluidic CVD precursor that reacts to form a solid material when exposed to heat. The freestanding film is then selectively heated in the presence of the precursor. The CVD precursor preferentially deposits on the surface(s) of the freestanding film.

Abstract: In a method for dynamically optimizing resource utilization in a system over time according to one or more objectives, data including information indicative of current environmental conditions, upcoming environmental conditions, a current state of a system configuration, and current system operating conditions is dynamically updated. Automatic analysis of the data using a probabilistic model based on conditional relationships is performed periodically. For each periodically generated set of possible system control actions, a probabilistic model is used to automatically analyze each possible system control action and an optimal system control action is selected based on a set of current utility functions. For each periodically generated set of possible system control actions, control of the system according to the optimal system control action selected from the possible system control actions.

Abstract: A photostructurable ceramic is processed using photostructuring process steps for embedding devices within a photostructurable ceramic volume, the devices may include one or more of chemical, mechanical, electronic, electromagnetic, optical, and acoustic devices, all made in part by creating device material within the ceramic or by disposing a device material through surface ports of the ceramic volume, with the devices being interconnected using internal connections and surface interfaces.

Abstract: Embodiments of the invention relate to a supersonic inlet having a cowl lip configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.

Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.