Oblique IMU Orientation for Projectile Failure Detection
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Solution Overview
Problem
Conventional guided projectiles face challenges in accurately determining the functionality of inertial measurement units during launch, which can lead to incorrect measurement of motion parameters and potential deviations from intended flight paths due to faulty navigation and control systems.
Innovation Solution
The use of an oblique-oriented inertial measurement unit with sensor suites measuring acceleration and rotation along mutually orthogonal i, j, and k axes, allowing for verification of sensor performance and deployment of control surfaces only when the unit functions within predetermined tolerances, ensuring stable and guided flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional inertial measurement units are used with standard orientation, then the device complexity is reduced, but the measurement precision and reliability of motion parameters during launch deteriorate due to inability to verify sensor functionality
Solution Approach 1:
The patent applies asymmetry by orienting the inertial measurement unit's sensor axes (i, j, k) at oblique angles relative to the projectile's longitudinal axis rather than using conventional aligned or orthogonal orientations. This asymmetric configuration enables the sensors to measure motion parameters in a reference frame that is deliberately misaligned with the projectile axis, allowing verification of sensor functionality through expected motion patterns during launch while maintaining measurement precision.
2Productivity
If control surfaces are deployed without verifying inertial measurement unit functionality, then the productivity and speed of projectile deployment is improved, but the measurement precision and flight path accuracy deteriorate due to potential faulty navigation
Solution Approach 1:
The patent applies preliminary action by verifying the functionality of the inertial measurement unit and validating sensor performance before deploying the control surfaces. The system performs preliminary checks of the inertial sensors during the launch phase to ensure accurate measurement of motion parameters, and only after confirming proper sensor function does it proceed to deploy control surfaces for guided flight. This sequential approach ensures measurement precision is established before productivity-critical deployment occurs.
3Ease of operation
If the inertial measurement unit is oriented with axes aligned to the longitudinal axis, then the ease of operation is improved, but the measurement precision of motion parameters in all directions deteriorates
Solution Approach 1:
The patent applies dimensionality change by transitioning from a conventional one-dimensional alignment (sensor axes aligned with the longitudinal axis) to a three-dimensional oblique orientation configuration. The sensor axes are positioned at specific oblique angles relative to the longitudinal axis, creating a multi-dimensional measurement framework that captures motion parameters more comprehensively. This dimensional reconfiguration enables precise measurement of acceleration and rotation in all directions while the system remains operationally manageable through computational transformation.
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 approach enhances failure detection and minimizes the probability of the projectile deviating from its intended path by verifying sensor functionality and deploying control surfaces only when accurate, thereby ensuring precise targeting.
Implementation Method 1
inertial sensors, GPS positioning, and other navigation methods
Implementation Method 2
guided projectiles deploy some form of control surfaces after launch and use these control surfaces to control the trajectory
Implementation Method 3
A ballistic trajectory is a flight path that is governed by forces and conditions external to the projectile, such as the velocity provided at launch, gravity, air drag
Implementation Method 4
Guided projectiles may be programmed to navigate to specific geographic coordinates using one or more of inertial sensors
Data Source
AI summary
A guided projectile may include a projectile body, an inertial measurement unit disposed within the projectile body, one or more control surfaces extendable from the projectile body, and a controller which controls the one or more control surfaces in response, at least in part, to measurement data received from the inertial measurement unit. The inertial measurement unit may include sensors to measure motion parameters relative to first, second, and third mutually orthogonal axes, wherein each of the first, second and third mutually orthogonal axes is oblique to a longitudinal axis of the projectile body.