System and method for monitoring the state of an unmanned aircraft

Patent metadata

Field	Value
Publication number	US-11753147-B2
Application number	US-201916517173-A
Country	US
Kind code	B2
Filing date	Jul 19, 2019
Priority date	Jul 31, 2018
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

A system for monitoring the state of an unmanned aircraft includes a first communication unit, a second communication unit that can be integrated within the aircraft, a state transmission unit that can be integrated within the aircraft for transferring state data of the aircraft, a receiving unit integrated within the aircraft for receiving control commands, a computing unit assigned to the aircraft for validating the state of the aircraft, and an external control and monitoring unit connected to the computing unit. The computing unit executes a simulation model of the aircraft, which is based on numerical integration of a system of equations with a simulation state vector. The computing unit sends a warning signal to the control and monitoring unit on the occurrence of one or repeated instances of a model error correction term exceeding specified interval limits.

First claim

What is claimed is:

1. A system for monitoring the state of an unmanned aircraft, comprising: a first communication unit;
a second communication unit that can be integrated into the aircraft;
a state transmission unit that can be integrated into the aircraft to transmit state data of the aircraft;
a computing unit assigned to the aircraft to validate the state of the aircraft; and an external control and monitoring unit connected to the computing unit; wherein the computing unit is configured to:
carry out a simulation model of the aircraft in question, wherein the simulation model is based on numerical integration of a system of equations with a simulation state vector;
repeatedly track the simulation state vector of at least one subset of previously measured flight status data by stepwise adjustment of at least one functional element of the simulation model by at least one model error correction term, wherein the model error correction term is determined from a difference between a measured state variable and a simulated state variable; and
monitor the variation of the at least one model error correction term and send a warning signal to the control and monitoring unit if the model error correction term exceeds predetermined interval limits once or multiple times;
wherein the control and monitoring unit is configured to issue a warning message directly to a user on receiving a warning signal, to continuously display flight status data of the aircraft received from the status transmission unit and to change a control mode of the aircraft to direct control by the user by sending a corresponding switching command to the aircraft.

2. The system according to claim 1 , wherein at least one functional element comprises a recursive filter algorithm that is influenced by the model error correction term.

3. The system according to claim 1 , wherein at least one functional element comprises a Kalman filter.

4. The system according to claim 1 , wherein the computing unit is an internal computing unit.

5. The system according to claim 1 , wherein the computing unit is an external computing unit and wherein the external computing unit is designed to receive state data of the aircraft via a communication unit.

6. The system according to claim 5 , wherein the computing unit is configured to simulate an inherent time delay of the communication device and the devices coupled thereto.

7. The system according to claim 1 , comprising a plurality of computing units, each assigned to an individual aircraft and coupled to a single control and monitoring unit.

8. The system according to claim 7 , wherein:
the control and monitoring unit comprises a display device; and
the control and monitoring unit is configured to bring at least the flight status data of an aircraft to the foreground on the display device when the aircraft in question is exhibiting unexpected behavior.

9. The system according to claim 1 , wherein the flight status data is selected from a group of flight status data comprising translational and rotational accelerations, system status data, position data, and position angle.

10. A method for monitoring the state of an unmanned aircraft, comprising the steps of:
executing a simulation model of the aircraft in question by numerical integration of a system of equations with a simulation state vector in a computing unit;
repeatedly tracking the simulation state vectors of at least one subset of previously measured flight status data by stepwise adjustment of at least one functional element of the simulation model by at least one model error correction term, wherein the model error correction term is determined from a difference between a measured state variable and a simulated state variable;
monitoring the variation of the at least one model error correction term and sending a warning signal to the control and monitoring unit on detecting a single or repeated instance of the model error correction term exceeding predetermined interval limits; and
outputting a warning to a control and monitoring unit coupled to the computing unit on receiving a warning signal, continuously displaying flight status data of the aircraft transmitted by a state transmission unit disposed in the aircraft concerned and changing a control mode of the aircraft to direct control by the user by sending a corresponding switching command to a communication unit in the aircraft.

11. The method according to claim 10 , wherein the adjustment of the at least one functional element includes the execution of a recursive filter algorithm that is influenced by the at least one model error correction term.

12. The method according to claim 10 , wherein at least one functional element comprises a Kalman filter.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Hunkel Peter

Classifications

• G05D1/0027

  involving a plurality of vehicles, e.g. fleet or convoy travelling (fleet control of land vehicles from a control room G05D1/0297; traffic control systems for road vehicles G08G1/00; for marine craft G08G3/00; for aircraft G08G5/00) · CPC title

• G05D1/101 Primary

  specially adapted for aircraft · CPC title

• G05B23/0254 Primary

  based on a quantitative model, e.g. mathematical relationships between inputs and outputs; functions: observer, Kalman filter, residual calculation, Neural Networks · CPC title

• B64C19/00 Primary

  Aircraft control not otherwise provided for · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title