Abstract: Commercial supersonic aircraft and associated systems and methods. A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between 20 and 60 passengers, a delta wing mounted to the fuselage, and a propulsion system carried by at least one of the wing and the fuselage, the propulsion system including a plurality of engines, at least one variable-geometry inlet, and at least one variable-geometry nozzle.

Abstract: Methods and systems for testing an aircraft in-flight are described herein. The method can include receiving a test deck including one or more test cards, with an individual test card including an ordered list of points. For an individual test card, points of the ordered list of points can be performed, a status for the performed points of the ordered list of points can be assigned, a current fuel value for the aircraft can be received, and the current fuel value can be compared to an expected amount of fuel required to perform the remaining test cards. In response to the comparison indicating that the current fuel value is not sufficient for the remaining test cards, the method can include modifying the test deck at least until the current fuel value is sufficient for executing a subset of remaining test cards.

Abstract: An aircraft propulsion system having a variable airflow capture area is provided. The propulsion system includes a main propulsion source and an auxiliary propulsion source. In a first mode, the auxiliary propulsion source is stowed within an aerodynamic profile of the aircraft, and the main propulsion source provides all of the propulsion force for powering flight of the aircraft. In a second mode, the auxiliary propulsion source is deployed to augment the airflow capture area of the main propulsion source and increase an overall airflow capture area of the propulsion system. In the second mode, the auxiliary power source is operated by power extracted from the main propulsion source. The main propulsion source may include one or more low bypass ratio engines. The auxiliary power source may include one or more auxiliary thrust fans coupled at a plurality of locations on the aircraft.

Abstract: Output signals from ground power units can be combined to supply more energy for aircraft to use for starting a jet engine. The combining can be possible when the outputs from the ground power units are synchronized. In a synchronization process, a first ground power unit may be started so that its first output signal serves as a reference for the synchronization. Then, an interconnect on a second ground power unit can be toggled to start and stop the generation of a second output signal at different times until the signals are in phase (i.e., synchronized).

Abstract: Systems and methods according to embodiments of the present technology vary engine throttle and flight control surfaces (such as high-lift devices, which can include flaps and/or slats) during takeoff, climb, approach, and/or landing of a supersonic aircraft to reduce noise. A representative computing device automatically controls thrust output of the propulsion system according to a schedule of thrust output, such that the thrust output remains below levels at which the jet exhaust becomes supersonic, and such that noise is reduced to comply with noise regulations or other limitations. The computing device also automatically controls the position and configuration of flight control surfaces to compensate for the reduced thrust and to maintain an appropriate climb and/or descent rate.

Abstract: Commercial supersonic aircraft and associated system and methods. A representative real time sonic boom warning system can detect when the trajectory of the commercial supersonic aircraft is likely to cause sonic booms that disturb designated areas (e.g., over land or population centers) and notify the operator accordingly.

Abstract: A GPU output from a ground power unit (GPU) can be converted to power suitable for starting a jet engine of an aircraft by an auto-transformer rectifier unit (ATRU) of the aircraft. Multiple ATRUs, each connected to a corresponding GPU, may output multiple ATRU outputs, and combining these multiple ATRU outputs can generate a combined power, which can satisfy the power requirements for starting a jet engine when they exceed what can be supplied by a single GPU. The combining is possible when the outputs of the ATRUs are synchronized, which can require generating and sharing a sync signal between the ATRUs that is synchronous with an ATRU designated as the master (i.e., reference) for the other ATRUs.

Abstract: Dissimilarly shaped aircraft nozzles with tandem mixing devices, and associated systems and methods are disclosed. An ejector nozzle in a representative embodiment includes a nozzle duct having a nozzle flow axis, a first axial position and a second axial position. The nozzle duct has a first cross-sectional shape at the first axial position, and a second cross-sectional shape at the second axial position, with the second shape being geometrically non-similar to the first shape. The nozzle further includes a fan flow duct portion and a core flow duct portion, both upstream of the first axial position. An ejector duct is positioned in fluid communication with the nozzle duct, and has at least one portion with a cross-sectional shape geometrically similar to the second cross-sectional shape.

Abstract: Commercial supersonic aircraft and associated systems and methods. A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between 20 and 60 passengers, a delta wing mounted to the fuselage, and a propulsion system carried by at least one of the wing and the fuselage, the propulsion system including a plurality of engines, at least one variable-geometry inlet, and at least one variable-geometry nozzle.