Abstract: In one embodiment, the instant invention provides a method that includes: outputting a first laser beam having: a beam quality factor (M2) between 1 and 5, and a spectral width of less than 0.15 nm, where the outputting is performed by a laser generating component that includes a alexandrite laser oscillator; converting the first laser beam through a first Raman cell to produce a second laser beam, where the first Raman cell is filled with a first gas; and converting the second laser beam through a second Raman cell to produce a final laser beam, where the second Raman cell is filled with a second gas and is operationally positioned after the first Raman cell, where the first gas and the second gas are different gasses, and where the final laser beam having: a second energy of at least 1 mJ, and at least one wavelength longer than 2.5 micron.

Abstract: In one embodiment, the instant invention provides a method that includes: outputting a first laser beam having: a beam quality factor (M2) between 1 and 5, and a spectral width of less than 0.15 nm, where the outputting is performed by a laser generating component that includes a alexandrite laser oscillator; converting the first laser beam through a first Raman cell to produce a second laser beam, where the first Raman cell is filled with a first gas; and converting the second laser beam through a second Raman cell to produce a final laser beam, where the second Raman cell is filled with a second gas and is operationally positioned after the first Raman cell, where the first gas and the second gas are different gasses, and where the final laser beam having: a second energy of at least 1 mJ, and at least one wavelength longer than 2.5 micron.

Abstract: In one embodiment, the instant invention provides a method that includes: outputting a first laser beam having: a beam quality factor (M2) between 1 and 5, and a spectral width of less than 0.15 nm, where the outputting is performed by a laser generating component that includes a alexandrite laser oscillator; converting the first laser beam through a first Raman cell to produce a second laser beam, where the first Raman cell is filled with a first gas; and converting the second laser beam through a second Raman cell to produce a final laser beam, where the second Raman cell is filled with a second gas and is operationally positioned after the first Raman cell, where the first gas and the second gas are different gasses, and where the final laser beam having: a second energy of at least 1 mJ, and at least one wavelength longer than 2.5 micron.

Abstract: In one embodiment, the instant invention provides a method that includes: outputting a first laser beam having: a beam quality factor (M2) between 1 and 5, and a spectral width of less than 0.15 nm, where the outputting is performed by a laser generating component that includes a alexandrite laser oscillator; converting the first laser beam through a first Raman cell to produce a second laser beam, where the first Raman cell is filled with a first gas; and converting the second laser beam through a second Raman cell to produce a final laser beam, where the second Raman cell is filled with a second gas and is operationally positioned after the first Raman cell, where the first gas and the second gas are different gasses, and where the final laser beam having: a second energy of at least 1 mJ, and at least one wavelength longer than 2.5 micron.

Abstract: A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs.

Abstract: A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs.

Abstract: A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs.

Abstract: A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs.

Abstract: A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs.

Abstract: A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs.