Variable Sweep Wings for Guided Projectile Maneuvering
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Solution Overview
Problem
Existing guided projectiles face challenges in achieving accurate and efficient guidance, particularly for non-propelled projectiles, due to limitations in drag minimization, weight constraints, and compatibility with existing firing platforms.
Innovation Solution
The development of a guided projectile with a despun or spun portion featuring a plurality of deployable wings with variable wing sweep, integrated into a collar assembly that provides directional control and range extension, while being scalable for various firing platforms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a rotating nose portion with aero-surfaces is used for course correction, then directional control is improved, but drag increases
Solution Approach 1:
The patent employs dynamically adjustable canard surfaces that can change their angle of attack and deployment status during flight. The canards transition from a stowed configuration during ballistic phase to deployed configurations during guidance phase, allowing optimal performance at different flight stages while minimizing drag during high-speed flight and maximizing control during terminal phase
2Productivity
If deployable wings with variable sweep are used, then range and maneuverability are improved, but device complexity increases
Solution Approach 1:
The patent implements variable sweep wings that can dynamically adjust their sweep angle during flight. The wings transition from a swept-back configuration during ballistic flight to a unswept or partially swept configuration during terminal guidance, optimizing lift-to-drag ratio at different flight phases while providing maneuverability control through a single degree of freedom mechanism
Solution Approach 2:
The wing structure is divided into multiple segments that can independently adjust their sweep angle. Each wing half can be controlled separately, allowing differential sweep for roll control and coordinated sweep for lift management, reducing the complexity of requiring multiple independent control surfaces
3Measurement precision
If guided control mechanisms are added to non-propelled projectiles, then accuracy is improved, but weight increases
Solution Approach 1:
The patent extracts the propulsion function from the guidance system, relying entirely on aerodynamic forces generated by the deployable wings and canards to maneuver the projectile. By eliminating internal propulsion systems, batteries, and complex power supplies, the design achieves guidance capability with minimal weight addition, using only lightweight aerodynamic surfaces and simple deployment mechanisms
Data Source
AI summary
A guided projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments the projectile includes a control support portion and a collar assembly pivotally mounted to the control support portion. In various embodiments the collar assembly includes a collar having an exterior sidewall with a plurality of fixed aerodynamic surfaces thereon for spinning the collar and a plurality of variable sweep wings for directional control of the projectile. In various embodiments the plurality of variable sweep wings each have a first end coupled to a wing actuator configured to rotate a second end portion between and including a first position, where the wings are oriented generally parallel to the central axis of the projectile to a second position, where the lengthwise wing axis of the plurality of wings are oriented generally perpendicular to the central axis of the projectile.