Adjustable Simulated Payload Apparatus for Flight Motion Testing
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Solution Overview
Problem
Conventional dummy loads for flight motion systems are labor and cost intensive, require design and fabrication for each specific payload, and fail to accurately simulate the mass and placement of ancillary components, necessitating separate alignment and calibration procedures.
Innovation Solution
A simulated payload apparatus with adjustable weights and onboard electronics for real-time data measurement and communication, along with enhanced alignment features, allowing for customizable simulation of various payloads and reducing the need for multiple dummy loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If conventional dummy loads are used for each specific payload, then the simulation accuracy for that specific payload is improved, but the design, review, fabrication and test labor and cost increase significantly
Solution Approach 1:
The patent applies universality by creating a single base dummy load structure that can simulate multiple different payloads through adjustable weights. The base structure serves as a universal platform that can be configured for various payload types by changing weight arrangements, eliminating the need to design and fabricate separate dummy loads for each payload type while maintaining simulation accuracy.
Solution Approach 2:
The patent applies dynamics by making the dummy load adjustable rather than fixed. The weights can be repositioned along the body to change the center of gravity and mass distribution, allowing the same physical structure to dynamically adapt to different payload simulation requirements without requiring physical redesign.
2Manufacturing precision
If application-specific dummy loads are fabricated for each payload, then the mass and center of gravity simulation is improved, but the fabrication cost and time increase
Solution Approach 1:
The patent applies segmentation by dividing the dummy load into a base structure and separate adjustable weights. This segmentation allows the base structure to be manufactured once as a universal component, while the weights can be independently positioned or replaced to achieve different mass and center of gravity configurations, reducing fabrication costs and time compared to manufacturing complete custom dummy loads for each application.
Solution Approach 2:
The patent applies parameter changes by allowing the mass and center of gravity parameters to be adjusted through repositioning weights rather than changing the physical structure. This enables precise control over simulation parameters (mass, center of gravity, moment of inertia) while using the same manufactured components, eliminating the need for expensive and time-consuming re-fabrication when parameters need to change.
3Device complexity
If dummy loads are used without ancillary components, then the simplicity of the dummy load is improved, but the simulation accuracy of the actual payload decreases
Solution Approach 1:
The patent applies the nested doll principle by placing ancillary components (cables, bolts, spacers, and other small parts) inside or attached to the dummy load body in a nested arrangement. This allows the dummy load to maintain a relatively simple external structure while containing the necessary ancillary components internally to accurately simulate the actual payload's mass distribution and characteristics, thus achieving both simplicity and accuracy.
4Measurement precision
If separate alignment and calibration procedures are performed for each dummy load, then the alignment precision is improved, but the labor intensity and time required increase
Solution Approach 1:
The patent applies preliminary action by incorporating alignment features directly into the dummy load structure during its initial setup. These features (such as alignment marks, sensors, or mechanical indicators) are pre-installed and configured to facilitate quick and accurate alignment with the flight motion system, eliminating the need for time-consuming separate alignment procedures for each test setup.
Data Source
AI summary
A simulated payload apparatus (SPA) for testing in a flight motion system (FMS), which has a body for mounting in the FMS, and which simulates an actual payload during the FMS test. The SPA may include a plurality of adjustable weights that are mountable on and/or removable from the body to vary the mass and/or center of gravity of the SPA. The SPA may include an adjustable bracket for interfacing with a motion drive of the FMS, in which the bracket is positionable along the body to vary the moment of inertia of the SPA. The SPA may include an onboard electronic measurement device that is configured to measure a motion characteristic of the SPA and/or communicate information about the measured motion characteristic in real-time during the FMS test. The SPA may include a laser alignment for aligning the SPA relative to test equipment of the FMS.