Launch Vehicle Carrier Attachment System for Bending Load Reduction
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Solution Overview
Problem
Carrying launch vehicles to high altitudes for vertical launch poses structural bending loads due to horizontal carriage, which adds unwanted weight and reduces payload performance, and existing attachment methods fail to restrict rotational and axial movement during flight.
Innovation Solution
An adaptable, flexible system using spring-loaded pins, lanyards, and stop blocks to secure launch vehicles to carrier aircraft, limiting motion during carriage and allowing unrestricted movement post-release, thereby minimizing structural modifications and weight addition.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional mechanical attachment methods (hook and pin) are used to carry launch vehicles horizontally, then the vehicle can be securely attached to the carrier aircraft, but additional structural mass must be added to the launch vehicle to resolve bending loads, reducing payload to orbit
Solution Approach 1:
The patent extracts the attachment function from traditional mechanical hook-and-pin systems and implements it through sling straps that attach to the carrier aircraft's existing structure. This eliminates the need for heavy mechanical attachment hardware on the launch vehicle itself, removing the source of additional structural mass while maintaining secure attachment through the sling configuration
Solution Approach 2:
The patent introduces sling straps as an intermediary element between the launch vehicle and carrier aircraft. These straps distribute attachment loads through the vehicle's existing structure rather than concentrating forces at specific attachment points, eliminating the need for additional reinforcing structure while maintaining secure attachment
2Ease of operation
If mechanical attachments are concentrated at the Center of Gravity area, then the vehicle can be mounted under the wing of the carrier aircraft, but additional structural bending loads are imposed on the captive vehicle due to cantilevering of the vehicle's mass
Solution Approach 1:
The patent segments the attachment system into multiple sling strap attachment points distributed along the launch vehicle's length rather than concentrating all attachments at the Center of Gravity. This distribution of attachment points creates multiple support sections that reduce the cantilevered mass at any single location, thereby reducing bending loads on the vehicle structure
Solution Approach 2:
The patent transitions from concentrated point attachments at the Center of Gravity to distributed line attachments along the vehicle's length using sling straps. This dimensional change from point to line distribution spreads the attachment loads across multiple locations, reducing the bending moment arm and associated bending loads on the vehicle structure
3Productivity
If releasable slings or straps are used to carry the vehicle, then the vehicle can be transported to altitude, but the vehicle may undesirably shift around or along the roll axis during flight
Solution Approach 1:
The patent implements a dynamic restraint system using spring-loaded pins that can adapt to vehicle movement while maintaining positional control. The springs allow controlled movement during transport but engage to prevent excessive shifting along the roll axis, providing adaptive stability that maintains vehicle position without overly restricting transport flexibility
Solution Approach 2:
The patent changes the mechanical parameters of the restraint system by incorporating spring elements that provide controlled compliance. The spring rate and preload are selected to allow normal transport movements while preventing excessive rolling or shifting, dynamically adjusting the restraint characteristics based on flight conditions
Data Source
AI summary
Disclosed are systems and methods for carrying an aeronautical or launch vehicle to altitude for release to independent flight. The system may comprise one or more mounting elements affixed to a carrier aircraft along a mounting axis and actuatable from a retention configuration to a release configuration. The retention configuration enables the mounting elements to secure the vehicle to the carrier aircraft. Actuation from retention configuration to release configuration releases the vehicle from the carrier aircraft. A detent element is configured to restrict movement of the vehicle rotationally about, and axially along, a roll axis of the vehicle with respect to the carrier aircraft when the vehicle is secured to the carrier aircraft. The system may include an adaptor beam to which each mounting element is fastened, and by which the affixing is achieved. The retention configuration may enable the mounting elements to secure the vehicle beneath the carrier aircraft.