Honeywell International Inc.

Honeywell G.m.b.h.

Sperry Corporation

Byron F Birkedahl

Marc M Pos

Brett Allen Eddy

Brendan Hall

Kenneth Paul Hoyme

Kalimulla Khan

Nicholas J Wilt

Aaron Raymond Larson

William F Potter

Jayasenthilnathan Balasubramanian

Srihari Jayathirtha

Douglas G Endrud

Art McCready

Disclosed are systems, methods, and non-transitory computer-readable medium for providing a safe landing for an aerial vehicle. The method may include: displaying, on one or more displays, an aerial vehicle, an intended landing zone, and a real-time flight path of the vehicle as the vehicle approaches the intended landing zone; receiving data related to one or more of the vehicle, the flight path of the vehicle, the intended landing zone, and an obstacle; determining the proximity of the vehicle relative to the center of the intended landing zone based on the received data; displaying the proximity of the vehicle relative to the center of the intended landing zone; displaying the obstacle when present; displaying an alert when the vehicle deviates in proximity to the center of the intended landing zone and/or approaches the obstacle; and upon determining a failure to respond to the alert computing flight controls to modify landing.

Systems and methods for providing safe landing assistance for an aerial vehicle

Techniques for allowing a vehicle equipped with at least one radar to take-off and land using radar return images of a landing site. The at least one radar generates radar return image(s) of the landing site, specifically of reflective symbols attached to the landing site, allowing the vehicle to orient itself to the landing site and providing information specific to the landing site. Position and velocity in relation to a landing site can be determined using at least one radar and a guidance and landing system. Using the position and velocity information, the guidance and landing system can guide the vehicle to and from the landing site and/or determine whether an obstacle requires the use of an alternate landing site.

Systems and methods for landing and takeoff guidance

Techniques for allowing a vehicle to detect and avoid obstacles comprises at least one radar and a navigation system including a three-dimensional map database. The at least one radar generates radar return image(s) which can be compared by the navigation system to the three-dimensional map to determine a three-dimensional position of the vehicle. Based upon position determination, the navigation system can guide the vehicle to a destination whilst avoiding obstacles. If the vehicle also includes a Global Navigation Satellite System (GNSS) receiver, such techniques are desirable when the GNSS receiver is unable to provide accurate position data, which can occur in urban environments where obstacles are numerous.

Systems and methods for vehicle navigation

In a system that uses a switched network and virtual links (for example, an AFDX, TT-ETHERNET, or TT-Gigabit ETHERNET switched ETHERNET network), the system is configured so that, for at least one virtual link, the end system that sources frames for that virtual link can change (for example, when an end system that was previously sourcing frames for that virtual link fails). The switches used in such a system are configured to be able to accept frames if there is such a change.

Multiple source virtual link reversion in safety critical switched networks

Methods and systems for a scalable self-checking processing platform are described herein. According to one embodiment, during an execution frame, a first processing element executes both a high-criticality application and a first low-criticality application. During that same execution frame, a second processing element executes both the high-criticality application and a second low-criticality application. The high-criticality application output from the first processing element is compared with that from the second processing element before the next execution frame, and a fault occurs when the output does not match. The low-criticality application is not duplicated or compared. This and other embodiments allow high-criticality applications to be appropriated checked while avoiding the over-dedication of resources to low-criticality applications that do not warrant self-checking.

Scalable self-checking processing platform including processors executing both coupled and uncoupled applications within a frame

A network architecture () that supports periodic and aperiodic data transmissions over a network databus. The network () comprising a plurality of Network Interface Controller (NIC) modules () configured to communicate with each other with at least one of the modules acting as a master NIC modules () and configured to allocate data transmission bandwidth on the network databus () using a set of priority sequences stored in a table () accessible by the master NIC () within the master timing NIC module (). The table () is used by the master NIC () to allocate bandwidth on the network databus () after transmission of periodic data and according to priority, length and frame sequence. In this way, aperiodic data from some NIC modules is guaranteed a certain amount of bandwidth on the network databus ().

Method and system for transmitting periodic and aperiodic data over a critical avionics databus

A communications system capable of providing enhanced data integrity and reliability through redundant buses, and a network interface controller for use therewith. Redundant conductors conforming to well-known ethernet standards interconnect electronics components. Each component communicates with the conductors through a single network interface card (NIC). Each NIC comprises an ethernet compliant transceiver for each ethernet conductor in communication with the component. Microcontrollers embedded in each NIC synchronously and deterministically place data on the ethernet conductors according to a timing scheme stored in a non-volatile memory means. A heartbeat/power monitor is also provided to ensure that data cannot be transmitted in the event of a microcontroller failure. The communications system provides a high degree of redundancy and fault-tolerance and is therefore well-suited to critical applications in avionics communication.

Low cost redundant communications system

A self adaptive limiter for use in aircraft control systems during approach and landing is disclosed. Estimated flight path angle is continuously computed during the glidepath tracking phase until a predetermined lock altitude above ground when a nominal flight path angle is latched. Nominal vertical speed is continuously computed below the lock altitude as a function of the latched nominal flight path angle and ground speed of the aircraft. A vertical speed limit function is generated as a function of the nominal vertical speed and radio altitude. During approach and landing a pitch limit is computed from the vertical speed limit, vertical speed, ground speed, and pitch. When a pitch command to the autopilot exceeds the pitch limit(i.e. commands excessive pitch down attitude), it is limited to the pitch limit thus preventing the aircraft from descending below a safe altitude. The invention is self-adaptive since the pitch limit varies in response to changes in the ground speed of the aircraft, wind, and ILS beam angles.

Self adaptive limiter for automatic control of approach and landing

An aircraft control system improves system flexibility, scalability, redundancy, and separation. The system uses a 'virtual backplane' architecture which maximizes system flexibility and scalability and allows easy integration of new functions. The architecture comprises four major elements: processing modules; input and output modules (i.e. I/O modules); database modules; and an aircraft wide system network. Inter module communication occurs via the aircraft wide system network thereby eliminating the need for point to point communication and making modules independent of physical location or what modular units (MUs) they are in. Predetermined periodic and deterministic broadcast techniques improve the safety and communications efficiency of the system.

Aircraft display and control system with virtual backplane architecture

An apparatus for providing asymmetrical torque-switching for an aircraft autopilot. The invention provides an increased amount of available pitch servo torque at high altitude. The direction of pitch of the aircraft is sensed. An increased amount of torque is provided for the pitch-up direction thereby providing more positive control of the aircraft.

Growing community of inventors

Glendale, AZ, United States of America

Byron F Birkedahl