Rocket Configuration Determination via Acceleration and Temperature
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Solution Overview
Problem
Existing rocket guidance and control systems face challenges in determining the configuration of attached warheads without manual intervention, as external switches are prone to operator error and require manual operation, which is undesirable, especially in combat situations.
Innovation Solution
A processor-implemented method and system that measures rocket acceleration and internal temperature during the burn-out phase to calculate a delta acceleration threshold, allowing for automated determination of the rocket configuration without external switches, using an accelerometer, temperature sensor, and processing circuitry to estimate the warhead type based on consistent deceleration patterns.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If external switches are added to identify warhead type, then rocket configuration identification is enabled, but device complexity and operator error risk increase
Solution Approach 1:
The patent replaces the mechanical switch system with a sensor-based detection system using accelerometers and temperature sensors. The system automatically detects warhead type by measuring physical parameters (acceleration, temperature) during rocket motor burnout, eliminating the need for manual switch operation and reducing device complexity.
Solution Approach 2:
The system enables self-service by automatically identifying the warhead type without requiring operator intervention. The onboard sensors and processing circuitry autonomously determine the rocket configuration by analyzing measured parameters, allowing the guidance system to adapt without manual input.
2Adaptability or versatility
If manual switch operation is required, then configuration identification is achieved, but ease of operation deteriorates in combat situations
Solution Approach 1:
The system performs self-service by automatically detecting and identifying the warhead type through sensor measurements during flight. The processing circuitry autonomously analyzes acceleration and temperature data to determine configuration, completely eliminating the need for manual switch operation by personnel.
Solution Approach 2:
The system performs preliminary action by pre-programming multiple warhead type configurations and their corresponding parameter signatures. During flight, the system automatically compares measured parameters against these pre-stored profiles to rapidly identify the attached warhead type without requiring manual configuration.
3Measurement precision
If temperature compensation is implemented, then measurement precision improves, but device complexity increases
Solution Approach 1:
The patent merges the temperature measurement function with the acceleration measurement system by using the same onboard temperature sensor to compensate for thermal effects on acceleration data. The processing circuitry integrates both temperature and acceleration measurements to calculate compensated values, eliminating the need for separate compensation hardware.
Solution Approach 2:
The system applies parameter changes by using measured temperature values to dynamically adjust the acceleration measurement interpretation. The processing circuitry modifies the acceleration data based on temperature-dependent parameters stored in memory, compensating for thermal expansion and other temperature-induced measurement errors.
Data Source
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AI summary
Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.