Systems and methods of airspeed control with dynamic asymmetric airspeed reference

A system for an airborne platform, comprising:

• a sensing device provided with the airborne platform and configured to measure a current airspeed at one or more repeating time intervals;
• an automatic throttling system;
• an aircraft data database configured to store historical flight data, the aircraft data database further configured to store a control law and a look-up table;
• and
• a processing circuit having a processor and a memory, the processing circuit communicably coupled to the sensing device, the aircraft data database, and to the automatic throttling system, the processing circuit configured to:
• receive a control input comprising a current airspeed value measured by the sensing device, an airspeed reference value, a maximum adder threshold, and a minimum adder threshold, the current airspeed value measured by the sensing device received at a predetermined frequency;
• transmit the current airspeed value measured by the sensing device to the aircraft data database to store with a time value;
• calculate an airspeed error value based on the control input;
• determine a programmed error value based on a sign of the calculated airspeed error value and a magnitude of the calculated airspeed error value according to at least one of the look-up table or the control law stored in the aircraft data database, the determined programmed error value being zero when the calculated airspeed error value is within a predetermined deadzone range;
• calculate an adder value by applying an integration function to the determined programmed error value, the integration function configured to increase the adder value when the programmed error value is a positive value or configured to decrease the adder value when the programmed error value is a negative value;
• determine a dynamic airspeed reference value based on the adder value, the dynamic airspeed reference value being calculated using the airspeed error value and the adder value;
• and
• transmit the dynamic airspeed reference value to the automatic throttling system;
• and
• where, by the processing circuit and the integration function, at least one of a proportion function, an integral function, or a derivative function transmit the dynamic airspeed reference value to the automatic throttling system of at least one of an unmanned or remotely piloted aircraft vehicle, in order to maintain the aircraft velocity at the desired dynamic airspeed reference value.

A processing circuit of an aircraft, the processing circuit having a processor and a memory, and configured to:

• receive a control input comprising a current airspeed value, an airspeed reference value, a maximum adder threshold, and a minimum adder threshold, the current airspeed value measured at one or more repeating time intervals via a sensing device, the current airspeed value measured by the sensing device received at a predetermined frequency;
• transmit the current airspeed value measured by the sensing device to an aircraft data database configured to store the current airspeed value, the aircraft data database further configured to store a control law and a look-up table:
• calculate an airspeed error value based on the control input;
• determine a programmed error value based on a sign of the calculated airspeed error value and a magnitude of the calculated airspeed error value according to at least one of the look-up table or the control law stored in the aircraft data database, the determined programmed error value being zero when the calculated airspeed error value is within a predetermined deadzone range;
• calculate an adder value by applying an integration function to the determined programmed error value, the integration function configured to increase the adder value when the programmed error value is a positive value or configured to decrease the adder value when the programmed error value is a negative value;
• and
• determine a dynamic airspeed reference value based on the adder value, the dynamic airspeed reference value being equal to a sum of the airspeed error value and the adder value;
• and
• where, by the processing circuit and the integration function, at least one of a proportion function, an integral function, or a derivative function transmit the dynamic airspeed reference value to the automatic throttling system of at least one of an unmanned or remotely piloted aircraft vehicle, in order to maintain the aircraft velocity at the desired dynamic airspeed reference value.