Abstract: An aircraft may include a tail having a rudder and a pair of wings. The pair of wings may include at least one flap and at least one roll control device. The aircraft may also include at least two thrust-producing devices. The aircraft may also include a differential thrust control system including a computing device having at least one processor. The at least one processer may be configured to control an attitude of the aircraft by selectively operating the at least two thrust-producing devices, the rudder, and the at least one roll control device based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected mode setting of a mode control panel. The computing device may be communicatively coupled to the at least two thrust-producing devices, the rudder, and the at least one roll control device.

Abstract: A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

Abstract: In accordance with some embodiments, a system for controlling an aircraft is provided. The system can include a computing device, wherein the computing device includes at least one processor configured to control a flight path angle of the aircraft, and wherein the aircraft is a blown lift aircraft. The system can also include a control operator communicatively coupled to the computing device, wherein the control operator is configured to have at least two selectable settings. The system can also include at least two thrust-producing devices operatively coupled to a pair of wings on the aircraft and communicatively coupled to the computing device. The computing device may control the flight path angle of the aircraft by selectively operating the at least two thrust-producing devices based on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected setting of the control operator.

Abstract: An aircraft may include a tail having a rudder and a pair of wings. The pair of wings may include at least one flap and at least one roll control device. The aircraft may also include at least two thrust-producing devices. The aircraft may also include a differential thrust control system including a computing device having at least one processor. The at least one processer may be configured to control an attitude of the aircraft by selectively operating the at least two thrust-producing devices, the rudder, and the at least one roll control device based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected mode setting of a mode control panel. The computing device may be communicatively coupled to the at least two thrust-producing devices, the rudder, and the at least one roll control device.

Abstract: In accordance with some embodiments, a system for controlling an aircraft is provided. The system can include a computing device, wherein the computing device includes at least one processor configured to control a flight path angle of the aircraft, and wherein the aircraft is a blown lift aircraft. The system can also include a control operator communicatively coupled to the computing device, wherein the control operator is configured to have at least two selectable settings. The system can also include at least two thrust-producing devices operatively coupled to a pair of wings on the aircraft and communicatively coupled to the computing device. The computing device may control the flight path angle of the aircraft by selectively operating the at least two thrust-producing devices based on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected setting of the control operator.

Abstract: A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

Abstract: An aircraft may include a tail having a rudder and a pair of wings. The pair of wings may include at least one flap and at least one roll control device. The aircraft may also include at least two thrust-producing devices. The aircraft may also include a differential thrust control system including a computing device having at least one processor. The at least one processer may be configured to control an attitude of the aircraft by selectively operating the at least two thrust-producing devices, the rudder, and the at least one roll control device based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected mode setting of a mode control panel. The computing device may be communicatively coupled to the at least two thrust-producing devices, the rudder, and the at least one roll control device.

Abstract: In some embodiments, a lift augmentation system for a blown lift aircraft includes a blown lift tailplane operatively coupled to the blown lift aircraft. The blown lift tailplane may include a leading edge and a trailing edge, an upper surface and a lower surface, and a first side and a second side. The lift augmentation system may include one or more tailplane thrust-producing devices on the first side and the second side of the blown lift tailplane operatively coupled to the leading edge of the blown lift tailplane. The one or more tailplane thrust-producing devices on the first side and the second side of the blown lift tailplane may produce a plurality of slipstreams corresponding to each of the tailplane thrust-producing devices. The plurality of slipstreams corresponding to each of the tailplane thrust-producing devices may blow over the upper surface and the lower surface of the blown lift tailplane.

Abstract: In accordance with some embodiments, a system for controlling an aircraft is provided. The system can include a computing device, wherein the computing device includes at least one processor configured to control a flight path angle of the aircraft, and wherein the aircraft is a blown lift aircraft. The system can also include a control operator communicatively coupled to the computing device, wherein the control operator is configured to have at least two selectable settings. The system can also include at least two thrust-producing devices operatively coupled to a pair of wings on the aircraft and communicatively coupled to the computing device. The computing device may control the flight path angle of the aircraft by selectively operating the at least two thrust-producing devices based on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected setting of the control operator.

Abstract: A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

Abstract: A dental laser treatment system includes a treatment laser beam and a pilot (e.g., aiming/marking) laser beam sharing a collinear beam path, where the beam path is guided by a guidance system through a handpiece/main chamber assembly having a beam exit. A laser beam presence detector is removably affixed to or within the handpiece/main chamber assembly. The laser beam presence detector provides feedback to a computer which can control actuation of the treatment laser beam and the pilot laser beam, and the beam guidance system. The computer performs a search for determining the center location of the beam exit based on the feedback and controls the beam guidance system to guide the beam path approximately to the center of the beam exit, thereby providing automatic alignment of the laser beam with the beam exit or an optional hollow waveguide.

Abstract: A dental laser treatment system includes a treatment laser beam and a pilot (e.g., aiming/marking) laser beam sharing a collinear beam path, where the beam path is guided by a guidance system through a handpiece/main chamber assembly having a beam exit. A laser beam presence detector is removably affixed to or within the handpiece/main chamber assembly. The laser beam presence detector provides feedback to a computer which can control actuation of the treatment laser beam and the pilot laser beam, and the beam guidance system. The computer performs a search for determining the center location of the beam exit based on the feedback and controls the beam guidance system to guide the beam path approximately to the center of the beam exit, thereby providing automatic alignment of the laser beam with the beam exit or an optional hollow waveguide.

Abstract: A dental laser treatment system includes a treatment laser beam and a pilot (e.g., aiming/marking) laser beam sharing a collinear beam path, where the beam path is guided by a guidance system through a handpiece/main chamber assembly having a beam exit. A laser beam presence detector is removably affixed to or within the handpiece/main chamber assembly. The laser beam presence detector provides feedback to a computer which can control actuation of the treatment laser beam and the pilot laser beam, and the beam guidance system. The computer performs a search for determining the center location of the beam exit based on the feedback and controls the beam guidance system to guide the beam path approximately to the center of the beam exit, thereby providing automatic alignment of the laser beam with the beam exit or an optional hollow waveguide.

Abstract: A dental laser treatment system includes a treatment laser beam and a pilot (e.g., aiming/marking) laser beam sharing a collinear beam path, where the beam path is guided by a guidance system through a handpiece/main chamber assembly having a beam exit. A laser beam presence detector is removably affixed to or within the handpiece/main chamber assembly. The laser beam presence detector provides feedback to a computer which can control actuation of the treatment laser beam and the pilot laser beam, and the beam guidance system. The computer performs a search for determining the center location of the beam exit based on the feedback and controls the beam guidance system to guide the beam path approximately to the center of the beam exit, thereby providing automatic alignment of the laser beam with the beam exit or an optional hollow waveguide.