Reduced-Order Flight Control for Rapid Aircraft Terrain Avoidance

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Solution Overview

Problem

Current flight control computing systems face computational complexity issues that lead to latency in calculating flight trajectories, making them unsuitable for rapid obstacle avoidance, especially at high speeds, due to the numerous steps and variables involved in full-order models.

Innovation Solution

The implementation of a reduced-order closed-loop model that approximates the behavior of existing models, combined with a fade function to attenuate command signals, allows for faster calculation of flight trajectories and automatic obstacle avoidance without operator input.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Measurement precision

If full-order models are used to calculate flight trajectories, then accuracy of trajectory prediction is improved, but computational latency increases making the system unsuitable for rapid obstacle avoidance

Engineering Contradiction:

Improvetrajectory prediction accuracyVSAvoidcomputational latency

Core Design Contradiction:

Measurement precisionVSLoss of time

Solution Approach 1:

The patent transforms the full-order model into a reduced-order model by changing the mathematical parameters and structure. The reduced-order model uses simplified dynamics equations that maintain essential flight characteristics while reducing computational complexity, enabling real-time trajectory prediction for obstacle avoidance without sacrificing excessive accuracy

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent extracts and removes unnecessary computational elements from the full-order model to create a streamlined reduced-order version. By taking out redundant calculations and simplifying the model structure while preserving core flight dynamics, the system achieves faster computation suitable for rapid obstacle avoidance scenarios

Inventive Principle:

Principle #2Taking out (Extraction)

2Reliability

If full-order models with numerous calculation steps and variables are used, then comprehensive flight dynamics are captured, but device complexity increases leading to computational delays

Engineering Contradiction:

Improveflight dynamics accuracyVSAvoidmodel computational complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent modifies the mathematical parameters of the flight dynamics model by reducing its order. This transformation simplifies the system of differential equations while retaining the essential behavior needed for obstacle avoidance, thereby reducing computational complexity without completely sacrificing reliability

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent segments the complex full-order model into a simplified reduced-order representation. By dividing the comprehensive model into essential and non-essential components, the system keeps only the critical flight dynamics needed for obstacle avoidance, reducing overall complexity while maintaining necessary reliability

Inventive Principle:

Principle #1Segmentation

3Productivity

If reduced-order models are used to reduce computational complexity, then calculation speed is improved, but model accuracy may be compromised

Engineering Contradiction:

Improvetrajectory calculation speedVSAvoidtrajectory prediction accuracy

Core Design Contradiction:

ProductivityVSMeasurement precision

Solution Approach 1:

The patent carefully adjusts the parameters of the reduced-order model to optimize the balance between speed and accuracy. By tuning the model parameters and selecting appropriate simplification levels, the system achieves sufficiently accurate trajectory predictions for obstacle avoidance while maintaining high calculation speed

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent applies partial modeling by including only the essential flight dynamics components needed for obstacle avoidance rather than modeling all aspects of flight. This partial action approach provides sufficient accuracy for the specific application while achieving the desired computational speed

Inventive Principle:

Principle #16Partial or excessive action

Data Source

PatentUS12190745B2Controlling aircraft to avoid terrain obstacles using reduced order closed loop models

Publication Date: 2025.01.07 LOCKHEED MARTIN CORP

AI summary

This disclosure relates to apparatuses, systems, and methods for controlling an aircraft. A computing system may identify a first command signal received via a flight control at a time point to control navigation of the aircraft through an environment. The computing system may attenuate the first command signal using a fade function over a time window relative to the time point to generate a second command signal. The computing system may input the second command signal to a model to generate predicted paths for the aircraft through the environment over the time window. The computing system may determine that at least one predicted path intersects with an obstacle in the environment during the time window. The computing system may generate a location to which to navigate the aircraft to avoid the obstacle. The computing system may perform an action to direct the aircraft to the location.