System and method for aircraft design optimization and performance

Inventors

Courtin, Christopher • Kays, Cory

Assignees

Aurora Flight Sciences Corp

Abstract

An aircraft design optimization system and associated aircraft design optimization architecture. The aircraft design optimization system may comprise an input circuit to provide input data and an optimizer circuit to receive the input data and to communicate with a plurality of modules to create output data. At least one abstraction layer can be provided between the optimizer circuit and each of the plurality of modules. The optimizer circuit is configured to output the output data to a post-processing circuit. Each of the plurality of modules implements a different function.

Core Innovation

An aircraft design optimization system and method generate aircraft (A) data and mission (M) data relating to a modified aircraft design by using an optimizer circuit that receives initial aircraft (IA) data and initial mission (IM) data. The processor-controlled design optimization convergence loop uses a vehicle sizing circuit and a secondary model circuit that are operatively coupled with the optimizer circuit. The vehicle sizing circuit provides mission history (MH) data to the optimizer circuit, and the secondary model circuit provides model output (MO) data to the optimizer circuit based at least in part on the initial aircraft (IA) and initial mission (IM) data.

An objective module operatively coupled with the optimizer circuit generates objective data (OD) reflecting an objective function based at least in part on the aircraft (A) data, the mission (M) data, the mission history (MH) data, and the model output (MO) data received from the optimizer circuit. The optimizer circuit outputs the aircraft (A) data, the mission (M) data, and the mission history (MH) data to a post-processing circuit based at least in part on the objective data (OD).

The design optimization convergence loop employs a residual convergence loop that uses residual data (RD) value generated by a residual calculation circuit to gate convergence. A non-linear solver circuit iteratively adjusts modified aircraft (A) data and mission (M) data based on a residual data (RD) value so that processing continues until the residual data (RD) value becomes zero.

The system further employs a mission integration circuit and named abstractions such as drag abstraction, atmosphere abstraction, and propulsion abstraction, and can generate mission history (MH) based at least in part on a fuel requirement or range requirement through a weight definition circuit.

Claims Coverage

Two independent claims define the system and the corresponding method, each centered on the same inventive architecture of an optimizer circuit coupled with vehicle sizing and a secondary model, producing mission history and model output, then computing objective data for post-processing. Four inventive features are captured in the consolidated coverage.

Across both independent claims, the core claim coverage centers on an optimizer circuit that iteratively generates modified aircraft and mission data via a processor-controlled design optimization convergence loop using a vehicle sizing circuit and a secondary model circuit, generates mission history and model output for the optimizer, computes objective data reflecting an objective function, and outputs aircraft, mission, and mission history to a post-processing circuit based on the objective data.

Stated Advantages

Documented Applications

No documented applications found