Missile Control Rudder with Movable Blade Segments
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Solution Overview
Problem
Existing directional control systems for supersonic unmanned aerial vehicles face limitations in aerodynamic controllability and structural integrity at high Mach numbers, requiring additional control systems and continuous thrust vector control, which complicates roll stabilization and increases mechanical stress.
Innovation Solution
The implementation of rotatable control rudders with movable blade segments that can change their cross-sectional profile by spreading or folding, allowing for independent adjustment of the rudder's angle and thickness, enhancing aerodynamic control and load distribution through aero-thermoelastic effects.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional control surfaces are used for supersonic flight, then aerodynamic controllability is maintained at low Mach numbers, but effectiveness is limited at high Mach numbers due to airfoil characteristics and structural stiffness
Solution Approach 1:
The control surfaces incorporate movable blade segments that can dynamically change the cross-sectional profile from a closed airfoil shape to an open spoiler-like configuration. This dynamic transformation allows the control surface to adapt its aerodynamic characteristics to different flight regimes, maintaining effectiveness from subsonic through supersonic ranges without requiring separate control systems for different Mach numbers.
Solution Approach 2:
The invention changes the geometric parameters of the control surface by pivoting blade segments relative to each other about a pivot point. This alters the cross-sectional area, thickness, and camber of the control surface, enabling optimization of aerodynamic performance across varying Mach numbers and flight conditions.
2Ease of operation
If thrust vectoring is used to supplement aerodynamic control systems, then agility is increased, but device complexity increases and continuous thrust is required
Solution Approach 1:
The control surface is divided into multiple independently movable blade segments that can be actuated separately. This segmentation provides additional control degrees of freedom, enabling complex maneuvering and enhanced agility without requiring a thrust vectoring system. The segmented design allows for differential movement of blade segments to generate rolling, pitching, and yawing moments.
3Reliability
If additional control systems are added for roll stabilization, then roll control is achieved, but device complexity and mechanical stress increase
Solution Approach 1:
The movable blade segments serve multiple control functions simultaneously. By coordinating the movement of blade segments on opposite control surfaces, the system can generate rolling moments for roll stabilization while the same segments contribute to pitching and yawing control. This multi-functionality eliminates the need for separate roll control actuators.
4Power
If blade segments are spread to increase drag for steering, then additional steering torque is generated in supersonic range, but device complexity increases
Solution Approach 1:
The control surface integrates both the primary control surface structure and the movable blade segments into a single unified component. The blade segments are directly mounted on the control surface and share common mounting structures and drive mechanisms, eliminating the need for separate spoiler systems and reducing overall device complexity while providing enhanced steering capability.
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 solution provides efficient aerodynamic control and additional steering torques in the supersonic range, simplifies roll stabilization, and optimizes load distribution across rudders, enabling compact and reliable directional control without the need for continuous thrust vector control.
Implementation Method 1
The effectiveness of the drag resulting from the blade segment position increases in the supersonic range due to aero-thermoelastic effects, thereby enabling the efficient generation of additional steering torque even at supersonic speeds.
Data Source
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AI summary
The present invention describes a flying object (100), in particular an unmanned flying object, with at least two control surfaces (1), each of which is rotatable about a rotation axis (A) extending transversely to a longitudinal axis (L100) of the flying object by means of a first drive device (2), wherein the control surfaces (1) each have a first blade segment (10) and a second blade segment (20), wherein the blade segments (10; 20) form at least partially opposite flow surfaces (1a; 1b) of a cross-sectional profile of the respective control surface (1), and wherein the blade segments (10; 20) are movable about a pivot point (P) relative to each other by means of a second drive device (3) to change the cross-sectional profile.