The Boeing Company

Continental Automotive Gmbh

Siemens Aktiengesellschaft

Michael W Hardt

Ralf Böhnig

Glenn Scott Bushnell

Francisco A Navarro

Francisco A Navarro Felix

Eduardo Gallo

Grzegorz Marian Kawiecki

Peter Ruβe

Example navigation aids for increasing the accuracy of a navigation system are disclosed herein. An example method disclosed herein identifying, with an aircraft intent description language (AIDL) aid, an AIDL instruction as associated with a first dynamic activity level of a plurality of dynamic activity levels and determining, with the AIDL aid, an aircraft state to be affected by the AIDL instruction. The example method also includes changing, with a navigation filter, a weighting scheme for a measurement of the aircraft state obtained by an inertial navigation system (INS) of the aircraft and estimating, with the navigation filter, a trajectory of the aircraft based on the weighting scheme and the measurement.

Navigation aids for unmanned aerial systems in a GPS-denied environment

Various techniques are provided for a winged drone platform. In one example, a drone can be provided. The drone can include a drone body, a plurality of wings, a plurality of tiling propeller assemblies, and a drone controller. The wings can be coupled to the drone body and configured to generate lift when the drone travels in a first travel direction. The tilting propeller assemblies can each be supported by one of the wings, can include a propeller and a propeller powerplant connected to the propeller, and can be configured to move between at least a first position and a second position. The drone controller can provide instructions to the tilting propeller assemblies to move between at least the first position and the second position. Additional systems and related methods are also provided.

Systems and methods for winged drone platform

Apparatus to generate aircraft intent and related methods are disclosed. An example apparatus includes one or more processors configured to determine a discrete automaton of a UAV by translating boundary constraint information into linear temporal logic (LTL), determine a maneuver automaton by calculating a set of motion primitives in aircraft intent description language (AIDL), combine the discrete automaton and the maneuver automaton to generate a product automaton corresponding to a motion plan to move the UAV from the first position to a second position different from the first position, determine whether the product automaton satisfies a trajectory specification threshold, produce a second aircraft intent description of the UAV in AIDL representative of second flight plan instructions different from the first flight plan instructions when the product automaton satisfies the trajectory specification threshold, and execute the second flight plan instructions with the UAV to move the UAV to the second position.

Apparatus to generate aircraft intent and related methods

Apparatus to generate aircraft intent and related methods are disclosed. An example automated aircraft intent generation method based on specifications expressed in formal languages includes: calculating first motion primitives associated with an aircraft intent description and a position of an aircraft; representing the first motion primitives in a second formal language as second motion primitives; collecting first information associated with at least one of 1) an aircraft performance model, 2) an environmental model, 3) a flight dynamic model, or 4) at least one of the first motion primitives or the second motion primitives; initializing a maneuver automaton based on the first information; collecting second information associated with at least one of: 1) flight plan instructions, 2) user preference indications, or 3) operational context indications; representing the second information as third information in a first formal language; combining the maneuver automaton and the third information to form a product automaton; determining that the product automaton satisfies a trajectory specification threshold; and in response to the product automaton satisfying the trajectory specification threshold, producing a representation of the aircraft intent description in the second formal language.

In order to determine the quality of fuel in an auto-igniting internal combustion engine, a defined fuel amount is injected at defined crank shaft angles during a deceleration fuel shut-off phase of the internal combustion engine. The thereby created crankshaft torque contribution is detected and an absolute or relative measure is determined for the fuel quality thereof.

Determining the quality of fuel in an auto-igniting internal combustion engine

In a method for estimating at least one control parameter of an injection system in an internal combustion engine for a target injection quantity, the estimation of the control parameter is based on linear regression, which is determined between predefined grid points and calculated test points in an operating range of the injection system.

Method and device for the robust estimation of the ratio of injection control parameters to resultant injected fuel quantity

In a method for estimating an injected quantity of fuel of an isolated injection, the segment time of the cylinder in which the isolated injection takes place is evaluated numerically by forming the second temporal derivation. With the aid of the second temporal derivation of the segment time the injection parameters are updated using test quantity-test torque characteristic map.

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Madrid, Spain

Michael W Hardt