Abstract: According to an aspect, a system in an aircraft includes a vehicle management system (VMS) and a load control system (LCS). The LCS includes an LCS processor operable to receive and transmit a plurality of data and load management commands to one or more of: the VMS and a load control interface. The LCS processor is further operable to interact with one or more of: the VMS, one or more LCS sensors, and a load capturing interface of the aircraft to execute the load management commands as a sequence of one or more load management subcommands. The load capturing interface is operable to capture and release an external load relative to the aircraft using a load capture device. The LCS processor is also operable to report a status of execution of the load management commands to the VMS and the load control interface.

Abstract: A vehicle includes a frame, drive elements configured to drive movements of the frame, and a computer configured to receive mission planning and manual commands and to control operations of the drive elements to operate in a safe mode in which mission commands are accepted but manual commands are refused, a manual mode in which mission commands are refused but manual commands are accepted and an enroute mode. The computer is further configured to only allow mode transitions directly between the safe mode and the manual mode and directly between the safe mode and the enroute mode.

Abstract: A computer system and method is provided to filter clearance sensor data output by a sensor system during a load/offload procedure of a first object relative to a second object. A processing device of the computer system is configured to access hard threshold data, unique threshold data, and sensor data output by the sensor system sensing aspects of the load/offload procedure. The processing device is further configured to determine whether the sensor data exceeds the unique threshold, determine whether the sensor data that is determined to exceed the unique threshold is voidable data related to a non-critical event, and generate filtered sensor data that includes modifications to the voidable data.

Abstract: A clearance sensor system is provided for use in moving first and second articles and includes a driving element disposed to drive and manipulate the first article relative to the second article, a plurality of sensors arrayed about at least the second article to generate real-time readings of physical separation of the first and second articles and a controller operably coupled to the driving element and the plurality of sensors. The controller is configured to facilitate an execution of real-time or quasi-dynamic control of a driving of the first article by the driving element in accordance with the readings of the physical separation between the first and second articles provided by the plurality of sensors, and a post-processing of data relating to the real-time or quasi-dynamic control of the driving and the manipulation of the first article by the driving element.

Abstract: According to an aspect, a system in an aircraft includes a vehicle management system (VMS) and a load control system (LCS). The LCS includes an LCS processor operable to receive and transmit a plurality of data and load management commands to one or more of: the VMS and a load control interface. The LCS processor is further operable to interact with one or more of: the VMS, one or more LCS sensors, and a load capturing interface of the aircraft to execute the load management commands as a sequence of one or more load management subcommands. The load capturing interface is operable to capture and release an external load relative to the aircraft using a load capture device. The LCS processor is also operable to report a status of execution of the load management commands to the VMS and the load control interface.

Abstract: A vehicle includes a frame, drive elements configured to drive movements of the frame, and a computer configured to receive mission planning and manual commands and to control operations of the drive elements to operate in a safe mode in which mission commands are accepted but manual commands are refused, a manual mode in which mission commands are refused but manual commands are accepted and an enroute mode. The computer is further configured to only allow mode transitions directly between the safe mode and the manual mode and directly between the safe mode and the enroute mode.

Abstract: An aircraft is provided and includes a frame, drive elements configured to drive movements of the frame and a computer configured to receive mission planning and manual commands and to control operations of the drive elements to operate in a safe mode in which mission commands are accepted but manual commands are refused, a manual mode in which mission commands are refused but manual commands are accepted and an enroute mode. The computer is further configured to only allow mode transitions between the safe and manual modes and between the safe and enroute modes.

Abstract: A system and method for determining length of load sling assembly in an aircraft, includes receiving, with a processor, information via one or more sensors regarding a load length during a delivery and descent state, the load length comprising length of a load sling assembly and a load height; controlling, with the processor, a minimum altitude of operation of the aircraft that ensures that the load does not touch the ground or obstacles during one or more of a flight plan, during decent, or during delivery; determining, with the processor, when a load has touched a ground in response to the receiving of the load length information; and releasing, with the processor, the load from the load sling assembly when the processor determines that the load has touched the ground.

Abstract: An aircraft is provided and includes a frame, drive elements configured to drive movements of the frame and a computer configured to receive mission planning and manual commands and to control operations of the drive elements to operate in a safe mode in which mission commands are accepted but manual commands are refused, a manual mode in which mission commands are refused but manual commands are accepted and an enroute mode. The computer is further configured to only allow mode transitions between the safe and manual modes and between the safe and enroute modes.

Abstract: An aircraft is provided and includes a frame, drive elements configured to drive movements of the frame and a computer configured to receive mission planning and manual commands and to control operations of the drive elements to operate in a safe mode in which mission commands are accepted but manual commands are refused, a manual mode in which mission commands are refused but manual commands are accepted and an enroute mode. The computer is further configured to only allow mode transitions between the safe and manual modes and between the safe and enroute modes.

Abstract: A ground-based aircraft control system including at least one data receiver/transmitter module configured to transmit aircraft control and data signals to an aircraft to control the flight of the aircraft and to receive data signals from the aircraft. At least one controller including a voice command recognition module configured to receive voice commands, to generate control signals based on the voice commands, and to transmit the control signals and command audio signals to the aircraft via the at least one data receiver/transmitter module. The at least one controller is configured to receive non-command voice audio signals and to transmit the non-command voice audio signals to the aircraft via the at least one data receiver/transmitter module.

Abstract: A system and method for determining length of load sling assembly in an aircraft, includes receiving, with a processor, information via one or more sensors regarding a load length during a delivery and descent state, the load length comprising length of a load sling assembly and a load height; controlling, with the processor, a minimum altitude of operation of the aircraft that ensures that the load does not touch the ground or obstacles during one or more of a flight plan, during decent, or during delivery; determining, with the processor, when a load has touched a ground in response to the receiving of the load length information; and releasing, with the processor, the load from the load sling assembly when the processor determines that the load has touched the ground.

Abstract: An aircraft is provided and includes a frame, drive elements configured to drive movements of the frame and a computer configured to receive mission planning and manual commands and to control operations of the drive elements to operate in a safe mode in which mission commands are accepted but manual commands are refused, a manual mode in which mission commands are refused but manual commands are accepted and an enroute mode. The computer is further configured to only allow mode transitions between the safe and manual modes and between the safe and enroute modes.

Abstract: Embodiments are directed to receiving, by a control station, an input including a command for re-location of a vehicle from a first location to a second location, the input identifying the second location, determining, by the control station, at least one of a distance, a direction, an altitude, and a latitude and longitude for the vehicle to travel from the first location to the second location, and transmitting, by the control station, the command and the at least one of a distance, a direction, an altitude, and a latitude and longitude to the vehicle.

Abstract: A control system for portable control of a rotary-wing aircraft includes a portable, hand-held, control device executing a control application, the control device operating in a loaded mode when a load is attached to the rotary-wing aircraft and an unloaded mode when no load is attached to the rotary-wing aircraft, the control device presenting command icons in response to being in loaded mode and unloaded mode; a vehicle management system in the rotary-wing aircraft; a sensor package on the rotary-wing aircraft; and a communication system providing communications between the control device and the rotary-wing aircraft, vehicle management system and sensor package; wherein the control device communicates commands to the vehicle management system to implement loading and unloading of the rotary-wing aircraft.

Abstract: A method of releasing cargo suspended from at least one cargo hook release pendant in a suspension system coupled to a cargo hook release system includes receiving a voltage release signal at a cargo hook control interface and a cargo release harness assembly; receiving an energizing voltage signal at the cargo release harness assembly; energizing a relay in response to receiving the energizing voltage signal, the relay being electrically coupled to the cargo release harness assembly; automatically transmitting the voltage release signal from the cargo release harness assembly to at least one cargo hook release pendant in response to energizing the relay; and automatically releasing the cargo from at least one cargo hook release pendant in response to automatically transmitting the voltage release signal. Also, the cargo hook release system includes the cargo hook control interface, the cargo release harness assembly, and at least one cargo hook release pendant.

Abstract: Embodiments are directed to receiving, by a control station, an input including a command for re-location of a vehicle from a first location to a second location, the input identifying the second location, determining, by the control station, at least one of a distance, a direction, an altitude, and a latitude and longitude for the vehicle to travel from the first location to the second location, and transmitting, by the control station, the command and the at least one of a distance, a direction, an altitude, and a latitude and longitude to the vehicle.

Abstract: A method of releasing cargo suspended from at least one cargo hook release pendant in a suspension system coupled to a cargo hook release system includes receiving a voltage release signal at a cargo hook control interface and a cargo release harness assembly; receiving an energizing voltage signal at the cargo release harness assembly; energizing a relay in response to receiving the energizing voltage signal, the relay being electrically coupled to the cargo release harness assembly; automatically transmitting the voltage release signal from the cargo release harness assembly to at least one cargo hook release pendant in response to energizing the relay; and automatically releasing the cargo from at least one cargo hook release pendant in response to automatically transmitting the voltage release signal. Also, the cargo hook release system includes the cargo hook control interface, the cargo release harness assembly, and at least one cargo hook release pendant.

Abstract: A control system for portable control of a rotary-wing aircraft includes a portable, hand-held, control device executing a control application, the control device operating in a loaded mode when a load is attached to the rotary-wing aircraft and an unloaded mode when no load is attached to the rotary-wing aircraft, the control device presenting command icons in response to being in loaded mode and unloaded mode; a vehicle management system in the rotary-wing aircraft; a sensor package on the rotary-wing aircraft; and a communication system providing communications between the control device and the rotary-wing aircraft, vehicle management system and sensor package; wherein the control device communicates commands to the vehicle management system to implement loading and unloading of the rotary-wing aircraft.