Segmented Aircraft Control Surfaces with Centrifugal Deployment
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Solution Overview
Problem
Existing deployment systems for control surfaces in projectiles and missiles often rely on centrifugal forces, which may not be sufficient for reliable and efficient deployment, particularly in terms of stability and compactness during launch and deployment.
Innovation Solution
The design features hingedly coupled segmented control surfaces that pivot relative to each other and the aircraft's fuselage, with locking mechanisms like sleeves to secure the segments in a deployed state, utilizing centrifugal forces from spinning for deployment without complex mechanisms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If control surfaces are kept compact during launch, then launch stability and compactness are improved, but deployment reliability and efficiency deteriorate
Solution Approach 1:
The control surface is divided into multiple segments that can be independently positioned. During launch, segments are folded along hinge connections to achieve compact stowage. During deployment, segments pivot outward from the fuselage while maintaining hinge connections, enabling reliable transition from compact to functional state without compromising launch stability or deployment reliability
2Device complexity
If centrifugal forces are used for deployment, then deployment simplicity is improved, but deployment stability deteriorates
Solution Approach 1:
The system utilizes changes in rotational parameters (spin rate) to control deployment. During launch, the projectile spins at high rate providing centrifugal forces that drive segment deployment outward. After deployment, spin rate is reduced or stabilized, allowing locks to engage and maintain the deployed configuration. This parameter change enables simple centrifugal deployment while achieving deployment stability through controlled transition to a locked state
3Stability of the object's composition
If locks are added to secure segments, then deployment stability is improved, but device complexity increases
Solution Approach 1:
The lock mechanism is designed to automatically engage and disengage based on the deployment state. During centrifugal deployment, centrifugal forces automatically drive the locks into the engaged position to secure segments. For disengagement, reduction of spin rate allows automatic unlocking without complex actuation systems. This self-service approach provides deployed state stability while minimizing structural complexity by eliminating the need for powered lock actuation
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 compact stowed control surfaces to deploy efficiently during flight, providing stability and eliminating the need for expensive or complicated deployment systems, with segments locking into place using centrifugal forces and sliding locks.
Implementation Method 1
spinning the aircraft during and/or after the launching; utilizing centrifugal forces from spinning for deployment
Implementation Method 2
control surface segments that are hingedly coupled together; allowing one segment to pivot relative to an adjacent segment
Implementation Method 3
locks to hold the control surface segments in a deployed state of the control surface; sliding locks of the control surfaces in place over the hinged connections
Data Source
AI summary
An aircraft, such as a missile, has control surfaces that have segments that are hinged together. The control surfaces deploy from a closed position, for example with the segments folded against a fuselage, so as to allow for launching from a launch tube. Once the aircraft is launched the control surfaces deploy from the closed position to an open position, with the segments opening up farther from the body or fuselage. In the open position or deployed state the segments may be substantially planar. Locks of the control surfaces may be used to lock the segments in place in the open position. The locks may include hollow sleeves that slide over the control surface segments. The sleeves and the segments may include a protrusions and depressions that engage each other to hold the segments in the open configuration.