Gimbal-Based Missile Component Testing System
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Solution Overview
Problem
Existing methods for testing missile components, such as accelerometers, are often inaccurate due to side-loading, which is uncharacteristic of a true missile launch, as they do not accurately simulate the combination of centripetal, tangential, and gravitational accelerations experienced during a launch.
Innovation Solution
A system comprising a centrifuge, a support arm, an orientation assembly, and a controller that reorients the sense axis of a missile component to align with the vector sum of acceleration vectors, including centripetal, tangential, and gravitational accelerations, using gimbal motors and resolvers to simulate a missile launch by rotating the component about multiple axes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional centrifuge testing methods are used, then the testing process is simple, but side-loading occurs that is uncharacteristic of true missile launch conditions
Solution Approach 1:
The testing system is segmented into multiple independent rotational stages: an outer gimbal that rotates about a vertical axis and an inner gimbal that rotates about a horizontal axis perpendicular to the vertical axis. This segmentation allows each gimbal to independently control a specific component of acceleration, enabling precise replication of missile launch conditions without side-loading.
Solution Approach 2:
The system transitions from traditional single-axis centrifuge testing to multi-axis rotational testing by adding the inner gimbal rotation dimension. This dimensional expansion allows the sense axis to be oriented in three-dimensional space, aligning it with the vector sum of centripetal, tangential, and gravitational accelerations to eliminate side-loading effects.
2Reliability
If the sense axis is not aligned with the resultant acceleration vector, then the testing setup is simpler, but side-loading occurs on the missile component
Solution Approach 1:
Resolvers are installed on both the outer and inner gimbals to provide real-time feedback on the orientation of the sense axis. The controller receives this feedback and automatically adjusts the rotation angles of both gimbals to ensure the sense axis aligns precisely with the vector sum of acceleration vectors, eliminating the need for manual alignment and preventing side-loading.
Solution Approach 2:
The system replaces manual mechanical alignment with an automated control system that uses electrical signals from resolvers to drive the gimbal motors. This substitution of mechanical alignment procedures with an automated feedback control system improves both precision and ease of operation.
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 provides a more accurate simulation of a missile launch, mitigating side-loading and allowing for the precise testing of missile components by aligning the sense axis with the resultant acceleration vector, thereby improving the reliability of the testing process.
Implementation Method 1
a centrifuge motor for rotating the centrifuge shaft about a vertical axis
Implementation Method 2
The first motor is mounted to the floor and has a first rotatable shaft defining a yaw axis that is parallel to the vertical axis of the centrifuge shaft. The outer gimbal is coupled with the first rotatable shaft so as to rotate about the yaw axis.
Implementation Method 3
The second motor is mounted to the outer gimbal and has a second rotatable shaft defining a pitch axis that is perpendicular to both the vertical axis of the centrifuge shaft and the longitudinal axis of the support arm. The inner gimbal is coupled with the second rotatable shaft so as to rotate about the pitch axis.
Implementation Method 4
The controller is configured to reorient the missile component by operating the first and second motors such that the sense axis of the missile component will align with a vector sum of acceleration vectors experienced by the missile component while the missile component is rotated about the vertical axis of the centrifuge shaft, the acceleration vectors including centripetal acceleration, tangential acceleration, and gravitational acceleration.
Data Source
AI summary
A testing system for testing a missile component having a sense axis includes a centrifuge, a support arm, an orientation assembly, and a controller. The centrifuge rotates the orientation assembly about a vertical axis in a substantially horizontal plane. The orientation assembly includes a first motor, a first gimbal, and a gimballed support. The first motor has a first rotatable shaft defining a first gimbal axis. The first gimbal is coupled with the first rotatable shaft to rotate about the first gimbal axis while the centrifuge rotates the orientation assembly about the vertical axis such that missile component is simultaneously rotated about both the vertical axis and the first gimbal axis to simulate a missile launch of the missile component. The gimballed support is coupled with the first gimbal for supporting the missile component such that the sense axis of the missile component is not parallel to the substantially horizontal plane. The orientation assembly may also include a second gimbal that is rotated about a second gimbals axis by a second motor.