Vertical Stabilizer Side Force and Auxiliary Yaw Control
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Solution Overview
Problem
Air vehicles face challenges in maintaining directional stability and generating controllable side forces during sideslipping flight, as conventional configurations result in significant loss of side force and reduced directional stability.
Innovation Solution
The method involves generating a controllable side force by selectively causing the vertical stabilizer arrangement to produce a first side force and a corresponding yaw moment, while applying an auxiliary force component that induces a second yaw moment in a direction opposed to the first, using differential drag or thrust between the port and starboard sides, independent of rudder deflection or pitch control surfaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If conventional rudder deflection is used to trim sideslip flight, then directional stability is maintained, but side force is significantly reduced
Solution Approach 1:
The invention divides the yaw moment generation function into two independent components: the vertical stabilizer arrangement generates side force, while a separate auxiliary system (drag-inducing devices or differential thrust) generates the counteracting yaw moment. This segmentation allows each component to perform its function without compromising the other, resolving the contradiction between maintaining directional stability and preserving side force.
Solution Approach 2:
The invention extracts the yaw moment generation function from the rudder/vertical stabilizer system and places it in a separate auxiliary system. By taking out this function, the vertical stabilizer can focus on generating side force without being counteracted by trim-induced yaw moments, thereby resolving the contradiction between directional stability and side force generation.
2Force
If tandem vertical stabilizer arrangement is used to trim yaw moments, then side force is increased, but directional stability is reduced
Solution Approach 1:
The invention extracts the yaw moment generation function from the vertical stabilizer arrangement and places it in a separate auxiliary system. This allows the vertical stabilizer to be optimized for side force generation without compromising directional stability, as the auxiliary system independently handles yaw moment control.
Solution Approach 2:
The auxiliary system (drag-inducing devices or differential thrust) serves multiple functions: it generates the necessary yaw moment to counteract the vertical stabilizer's yaw moment, and it does so without interfering with the vertical stabilizer's side force generation or the aircraft's directional stability. This multi-functionality resolves the contradiction by providing a versatile solution that addresses both side force and stability requirements.
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 allows for trimmed side force generation at zero sideslip angle and improved directional stability, enabling enhanced maneuverability and control during sideslipping flight without diminishing the original side force.
Implementation Method 1
selectively causing said vertical stabilizer arrangement to generate a first side force in a first side direction to provide said controllable side force, said first side force inducing a corresponding first yaw moment in a first yaw direction
Implementation Method 2
said second yaw moment being induced by a force component of an auxiliary force applied to said air vehicle, said force component being in a force direction that is non-parallel with respect to said first side direction
Implementation Method 3
said force component being spaced from a center of gravity of the air vehicle
Data Source
AI summary
A method for providing a controllable side force to an air vehicle having a vertical stabilizer arrangement includes (a) selectively causing the vertical stabilizer arrangement to generate a first side force in a first side direction to provide the controllable side force, the first side force inducing a corresponding first yaw moment in a first yaw direction; and (b) selectively providing to the air vehicle a second yaw moment in a second yaw direction, the second yaw moment being induced by a force component of an auxiliary force applied to the air vehicle, the force component being in a force direction that is non-parallel with respect to the first side direction and the force component being spaced from a center of gravity of the air vehicle; wherein the second yaw direction is opposed to the first yaw direction. Also disclosed is a corresponding auxiliary yaw generating system.