Variable Hinge Moment Test Apparatus for Flight Control Systems
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Solution Overview
Problem
Traditional flight control system loading methods apply a constant hinge moment, leading to excessive overload on primary flight control system components due to varying hinge moments throughout their travel positions, which can damage the components.
Innovation Solution
A flight control system loading test apparatus and method that uses a surface-mounted sector, a cam profile sector, and a cable with a dummy weight to simulate a variable hinge moment, allowing the hinge moment to vary with the flight control system angles, thereby avoiding excessive overload.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a constant hinge moment is applied using traditional loading methods, then the loading test is simple to implement, but excessive overload is provided to the flight control system components causing potential damage
Solution Approach 1:
The patent applies the dynamics principle by replacing the static constant hinge moment with a dynamic variable hinge moment that changes throughout the flight control component's travel position. The cam profile mechanism dynamically adjusts the moment arm length based on the component's angular position, ensuring the hinge moment varies to match actual operational conditions and preventing excessive overload while maintaining test simplicity.
Solution Approach 2:
The patent implements parameter changes by varying the hinge moment parameter throughout the travel position rather than maintaining a constant value. The cam profile sector changes the effective moment arm length parameter as the flight control component moves through different angles, allowing the hinge moment to adapt to different operational phases and prevent damage while remaining easy to implement.
2Object-affected harmful factors
If a variable hinge moment is simulated using a cam profile sector and dummy weight, then excessive overload is avoided, but the device complexity increases
Solution Approach 1:
The patent applies the intermediary principle by introducing a cam profile sector as a mediating mechanism between the dummy weight and the flight control system. This intermediary component translates the constant gravitational force of the dummy weight into a variable hinge moment through its cam profile geometry, achieving variable loading without requiring complex active control systems.
Solution Approach 2:
The cam profile sector mechanism is self-regulating and automatically adjusts the hinge moment based on the flight control component's position without external control. The geometry of the cam profile inherently provides the variable moment characteristic, making the system self-service and reducing the need for additional complex control mechanisms.
3Measurement precision
If the hinge moment varies throughout the travel position, then the loading test accurately reflects actual operational conditions, but the traditional constant loading method becomes insufficient
Solution Approach 1:
The patent applies dynamics to achieve accurate hinge moment simulation by making the loading characteristic dynamic rather than static. The cam profile mechanism ensures the hinge moment varies in sync with the flight control component's angular position, providing measurement precision that reflects actual operational conditions across the entire travel range.
Solution Approach 2:
The patent implements parameter changes to enhance adaptability and measurement precision. The hinge moment parameter is continuously adjusted throughout the travel position through the cam profile mechanism, allowing the loading test to accurately simulate varying operational conditions at different angles without requiring multiple separate test configurations.
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
The solution effectively simulates the actual hinge moment required by the flight control system at each angle, preventing damage and ensuring compliance with regulatory pilot force limits without overloading the components.
Implementation Method 1
The cam profile sector is configured to rotate about a rotational axis among a plurality of loading positions as the flight control system body pivots among the plurality of flight control system angles. The cam profile sector includes a profile surface including a plurality of successive curves.
Implementation Method 2
The cable is configured to contact to the cam profile sector along the profile surface. A hinge moment applied to the flight control system body using the dummy weight varies among the plurality of loading positions to approximate a pre-calculated actual hinge moment associated with the flight control system at each of the flight control system angles.
Implementation Method 3
The surface-mounted sector attaches to the flight control system body of the aircraft such that the surface-mounted sector pivots along with the flight control system body about a pivot axis as the flight control system body pivots about the pivot axis among a plurality of flight control system angles.
Data Source
AI summary
A flight control system loading test apparatus includes a surface-mounted sector, a cam profile sector, a dummy weight, and a cable. The surface-mounted sector attaches to an aircraft flight control system body such that the surface-mounted sector pivots along with the body about a pivot axis. The cam profile sector is configured to rotate about a rotational axis among a plurality of loading positions. The cam profile sector includes a profile surface having a plurality of curves. Each curve follows a different radius emanating from a respective axis substantially parallel to the rotational axis of the cam profile sector. The cable contacts the cam profile sector along the profile surface. An applied hinge moment using the dummy weight varies as the cam profile sector rotates about the rotational axis.