An aircraft angle of attack and sideslip angle indicator includes a display responsive to angle of attack and sideslip angle measurements from an angle of attack sensor and a sideslip angle sensor on an aircraft. The display depicts angle of attack along a first (preferably vertical) axis, and sideslip angle along a second (preferably horizontal) axis, with the axes intersecting at a display datum which represents acceptable angle of attack and sideslip angle values from the aircraft. The display depicts the aircraft's current angle of attack and sideslip angle with respect to the display datum, thereby indicating to the pilot whether non-optimal (and perhaps dangerous) flight conditions are occurring.

The present invention achieves technical advantages as a pilot and passenger seating. An aircraft employs a pilot seat, comprising a contoured structure having ergonomically formed and padded surfaces, with left and right arm supports that include an articulated control knob, movable in three rectangular axes and rotatable about a vertical axis to provide one or more aircraft steering functions for an aircraft, and a touch-sensitive control surface for controlling one or more power system components. A passenger seat, having a contoured structure, having ergonomically formed and padded surfaces, a headrest, a seat, a left support member, and a right support member are adapted to cradle a portion of a passenger's body to support the passenger during travel.

A method comprises computing position information from a global navigation satellite system (GNSS); computing an altitude measurement based on retrieved information from a vertical position sensor; determining a vertical protection level (VPL) associated with the position information; splitting the VPL into an upward VPL component and a downward VPL component; determining a vertical alert limit (VAL) associated with the altitude measurement; and splitting the VAL into an upward VAL component and a downward VAL component. The method optimizes an integrity budget allocation between the upward and downward VPL components. The method then recomputes the upward and downward VPL components given the optimized integrity budget allocation.

The present disclosure provides a compliance test method and system for Receiver Autonomous Integrity Monitoring (RAIM) performance of a BeiDou navigation satellite system (BDS) airborne equipment. The method includes: acquiring BDS almanac parameters and test parameters (101); determining whether the satellites are visible according to the almanac parameters and the test parameters (102); acquiring space-time points when the satellites are visible (103); computing the Horizontal Protection Limit (HPL) of each of the space-time points (104); selecting marginal geometries space-time points according to the HPL (105); test the space-time points and the marginal geometries space-time points to obtain a first test result (106); acquiring the configuration parameters and the BDS almanac of the satellite navigation vector signal generator for the marginal geometries space-time points (107); decoding the configuration parameters and the BDS almanac to obtain the number of visible satellites (108); determining whether the number of visible satellites is greater than a threshold (109); testing the marginal geometries space-time points to obtain the second test result if yes (110); and determining whether the first test result is matched with the second test result (111). The method can check whether the BDS airborne equipment meets airworthiness requirements.

This method for displaying information relative to an aircraft is carried out by computer and includes the acquisition of a message from among a meteorological message and an aeronautical information message, each message including at least one mission object identifier; searching, among the mission object identifier(s) contained in each acquired message, for at least one mission object identifier verifying at least one criterion from among first, second and third predefined criteria, the first criterion depending on a received mission plan, the second criterion depending on the current position of the aircraft, and the third criterion depending on both the current position of the aircraft and the received mission plan; and if at least one mission object identifier is detected verifying at least one of the first, second and third predefined criteria, displaying each detected identifier.

A method is provided for calculating the prediction of required navigation performance for a trajectory associated with a list of segments of a flight plan. A method is also provided for displaying the navigation performance as a corridor trajectory and adapted to guarantee compliance with the navigation performance requirements while offering immediate viewing of the navigation latitude in a corridor.

A method of calculation, by a flight management system termed FMS, of a trajectory flown by an aircraft comprises the steps, calculated by the FMS, of: for at least one transition of the trajectory arising from the flight plan: 1) determining an initial transition comprising at least one arc exhibiting a single initial turning radius, 2) determining an initial trajectory incorporating the initial transition, 3) determining for each parameter a plurality of predicted values of the parameter in the course of the initial transition, 4) determining a plurality of ordered subdivisions of the arc of the initial transition according to a predetermined criterion, 5) determining, for each subdivision, an associated turning radius, 6) determining an improved transition on the basis of the ordered subdivisions and of the successive associated turning radii, 7) determining an improved trajectory incorporating the improved transition, 8) displaying the improved trajectory to a pilot of the aircraft.

Flight guidance systems and methods that provide an airport selection in response to an EO condition in a single engine plane. The airport selection takes into consideration factors such as optimal approach type, runway length, weather, terrain, remaining battery time, and the like. Additionally, various also generate and display a visual indication of a remaining glide range when the EO condition is happening; the remaining glide range determination is based, at least in part, on terrain.

A method of targeting, which involves capturing a first video of a scene about a potential targeting coordinate by a first video sensor on a first aircraft; transmitting the first video and associated potential targeting coordinate by the first aircraft; receiving the first video on a first display in communication with a processor, the processor also receiving the potential targeting coordinate; selecting the potential targeting coordinate to be an actual targeting coordinate for a second aircraft in response to viewing the first video on the first display; and guiding a second aircraft toward the actual targeting coordinate; where positive identification of a target corresponding to the actual targeting coordinate is maintained from selection of the actual targeting coordinate.

A system and method for high-confidence error overbounding of multiple optical pose solutions receives a set of candidate correspondences between 2D image features captured by an aircraft camera and 3D constellation features including at least one ambiguous correspondence. A candidate estimate of the optical pose of the camera is determined for each of a set of candidate correspondence maps (CMAP), each CMAP resolving the ambiguities differently. Each candidate pose estimate is evaluated for viability and any non-viable estimates eliminated. An individual error bound is determined for each viable candidate pose estimate and CMAP, and based on the set of individual error bounds a multiple-pose containment error bound is determined, bounding with high confidence the set of candidate CMAPs and multiple pose estimates where at least one is correct. The containment error bound may be evaluated for accuracy as required for flight operations performed by aircraft-based instruments and systems.