Methods and systems of generating a data driven digital chart. The methods and systems include retrieving a data driven chart for a requested terminal area procedure chart from a database of data driven charts. The data driven charts describe digital terminal area procedure charts by way of data elements for each terminal area procedure chart including geodetic straights, arcs, text elements and symbols defined with respect to location. Some of the data elements are further defined with respect to altitude values assuming a standard atmospheric temperature value. The systems and methods include calculating compensated altitude values for the data elements of the retrieved data driven chart based on a deviation between the outside air temperature value and the standard atmospheric temperature value. The methods and systems include generating a presentation for a display device of the aircraft of the terminal area procedure chart.

An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.

A method of isolating a source of an altitude split in a plurality of altitude sensors includes receiving a static pressure reading from a first altitude sensor and receiving a static pressure reading from a second altitude sensor. The method also includes comparing each of the static pressure readings with an expected static pressure value to determine which of the altitude sensors is the source of a split in altitude readings of the altitude sensors.

A method for determining position of an aircraft with reference to a location on the ground includes transmitting an acoustic signal from a position on the aircraft to an array of spaced apart acoustic sensors proximate the location. The method includes at least one of (i) determining a time difference of arrival of the acoustic signal between each of the acoustic sensors and a reference acoustic sensor and (ii) determining an arrival time of the acoustic signal at each of the spaced apart acoustic sensors. The position of the aircraft is determined from the time differences of arrival and/or the arrival times.

Techniques are provided for vision-based altitude estimation using one or more platform mounted cameras. An embodiment includes generating projected ground imagery of imagery provided by cameras of the platform, the projection based on a hypothesized altitude. The method also includes obtaining reference ground imagery based on the location of the platform, the location based on platform navigation data. The method further includes registering the projected ground imagery to the reference ground imagery and generating a match score associated with the registration. The method further includes selecting the hypothesized altitude as the estimated altitude based on the match score (e.g., if the match score exceeds a threshold value or is maximized over a set of hypothesized altitudes. The method may further include otherwise adjusting the hypothesized altitude and repeating the altitude estimation process based on the adjusted hypothesized altitude to search for an improved estimated altitude based on the match score.

A ground proximity warning system for an aircraft includes a plurality of alarm generators, each able to generate an alarm by verifying evolution conditions of the aircraft specific to each alarm generator, the verification using data obtained from at least one measuring sensor of the aircraft. The ground proximity warning system includes a unit for selective deactivation of at least some of the alarm generators, able to be implemented during a search and rescue mission carried out by the aircraft, and an auxiliary alarm generator, capable of emitting a ground proximity alarm based on the safety height chosen for the search and rescue mission, when the selective deactivation unit is implemented.

A method is described that is implemented by computer for optimizing the vertical descent profile of an aircraft, the vertical profile being broken down into an altitude profile and a speed profile. One or more altitudes of passage can be determined by minimizing the overall deviation between the speed profile and one or more speed constraints previously received. The optimized descent profile can comprise one or more of these altitudes of passage. Different developments are described, in particular embodiments in which an optimized altitude of passage minimizes the engine thrust, the descent profile is of OPEN IDLE, FPA or VS type, the optimized descent profile is determined backward, a speed constraint is of AT or AT OR ABOVE type, and the use of the airbrakes. Display modalities are described, as are system and software aspects.

There are provided systems and methods for providing a barometric altitude monitor that assist pilots by providing alerts when a barometric altitude of the ownship aircraft is may be incorrect. Various embodiments of the present invention determine whether significant errors in barometric altitude occur though comparisons to alternate altitude information sources. Through aspects of the present invention, errors arising from manual entry of barometric pressure information by a pilot may be identified before safety issues arise, thus helping to prevent events such as controlled flight into terrain (CFIT).

The present invention relates to a method for calibrating an altitude sensing stereo vision device (122) of an unmanned aerial vehicle (100), wherein the method includes: arranging the unmanned aerial vehicle to take off from ground (G) and ascend; deriving at least one first altitude value (10a-15a) from the stereo vision device and obtaining at least one corresponding second altitude value (10b-15b) from another device (123) of the unmanned aerial vehicle during the ascent (1) of the unmanned aerial vehicle; recording the derived at least one first altitude value and the obtained at least one corresponding second altitude value as calibration data; deriving an additional first altitude value from the stereo vision device while the unmanned aerial vehicle flies a route; and adjusting the derived additional first altitude value based on the recorded calibration data.

A radio altimeter includes an electronically scanned array antenna. Orthogonal sweeps by the electronically scanned array antenna are used to identify a highest point in a region beneath the aircraft without the need for strong reflection. The electronically scanned array antenna may be reconfigured to scan a subregion including the highest point with a higher frequency beam and/or integrate multiple sweeps over time for a more accurate measurement.