Dynamic Autopilot Parameter Scheduling Across Flight Envelopes
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Solution Overview
Problem
Current guided rocket systems require separate configurations for rotary wing and fixed wing platforms, leading to inefficiencies and increased costs due to the need for multiple autopilot settings and user reconfiguration, which is undesirable for flexible and reliable performance across varying flight conditions.
Innovation Solution
A dynamic autopilot system that utilizes on-board sensors such as accelerometers, temperature sensors, and pressure sensors to calculate Mach and dynamic pressure, tailoring parameters like roll gain, pitch/yaw gains, and guidance filter frequencies to adapt to different flight conditions, enabling a single configuration to perform optimally across a wide range of platforms from low and slow to high and fast.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate guided rocket system configurations are produced for rotary wing and fixed wing platforms, then performance and stability are optimized for each specific platform, but device complexity and procurement costs increase due to maintaining multiple configurations
Solution Approach 1:
The autopilot is designed with universal functionality to operate on both rotary wing and fixed wing platforms through a single configuration. The system uses sensor data from accelerometers, pressure sensors, and temperature sensors to dynamically calculate Mach number and dynamic pressure, then automatically adjusts parameters such as roll gain, pitch/yaw gain, and guidance filter bandwidth to optimize performance for the detected platform type, eliminating the need for separate configurations.
Solution Approach 2:
The autopilot implements dynamic parameter adjustment based on real-time sensor measurements. The system continuously monitors flight conditions and automatically reconfigures control parameters during operation. The gain schedules for roll and pitch/yaw controls are dynamically modified based on calculated Mach number and dynamic pressure, allowing the single autopilot configuration to adapt to different platform characteristics and flight envelopes.
2Reliability
If users manually reconfigure autopilot settings to switch between rotary wing and fixed wing modes, then performance can be optimized for the current platform, but ease of operation deteriorates due to additional user intervention requirements
Solution Approach 1:
The autopilot system performs self-identification and self-configuration based on sensor data from the vehicle it is mounted on. The system automatically detects whether it is operating from a rotary wing or fixed wing platform by analyzing flight characteristics, Mach number, and dynamic pressure measurements, then autonomously selects and applies the appropriate parameter sets without requiring user intervention or manual reconfiguration.
Solution Approach 2:
The system continuously monitors flight parameters including acceleration, pressure, and temperature to detect platform characteristics. Based on this feedback, the autopilot automatically adjusts control parameters such as roll gain, pitch/yaw gain, and guidance filter bandwidth. The feedback loop enables the system to adapt to different platform types and flight conditions in real-time, maintaining optimal performance without user input.
3Device complexity
If a single guided rocket system configuration is used for both rotary wing and fixed wing platforms, then procurement costs and logistical complexity are reduced, but autopilot performance and stability may deteriorate due to inability to optimize for specific platform characteristics
Solution Approach 1:
The autopilot employs parameter change schedules that are automatically selected based on detected flight conditions. The system maintains multiple sets of control parameters including roll gain schedules, pitch/yaw gain schedules, and guidance filter bandwidths, and dynamically switches between them based on calculated Mach number and dynamic pressure. This allows a single physical configuration to achieve the performance characteristics of multiple specialized configurations.
Solution Approach 2:
The system applies different control parameter values tailored to specific flight conditions and platform types. Rather than using uniform parameters for all operations, the autopilot implements localized parameter optimization by selecting appropriate gain values and filter settings based on the current flight envelope and platform characteristics, ensuring optimal performance for each operating regime.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution allows for reliable and stable performance across diverse flight conditions with a single guided rocket configuration, reducing costs and logistical complexities by eliminating the need for multiple configurations and user reconfiguration, while maintaining optimal autopilot performance.
Implementation Method 1
an internal accelerometer located within the system body... capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer. The internal pressure sensor is capable of calculating Mach number via an axial acceleration
Implementation Method 2
an internal pressure sensor located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere
Data Source
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AI summary
[A system and method for dynamic autopilot control comprising providing input to a guidance and control autopilot comprising Mach and dynamic pressure; tailoring parameters of the autopilot, the parameters comprising : roll gain; a pitch/yaw gain; a pitch/yaw loop compensator frequency; a guidance filter bandwidth; a guidance filter lead compensator frequency; and a navigation gain.