Rotating Payload Launcher for Protected, Low-Drag Release
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Solution Overview
Problem
Existing payload release systems from aircraft expose payloads to environmental conditions, affecting flight characteristics and increasing the risk of foreign object damage, particularly for drones and munitions with deployable control surfaces.
Innovation Solution
A rotating release launching system with a tubular body and a rotating door mechanism that retains the payload, providing a rolling or rotating release through angular momentum, using biasing and fastening mechanisms to ensure proper orientation and separation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the payload is exposed externally on the aircraft, then the payload can be easily attached and accessed, but the payload is exposed to environmental conditions affecting flight characteristics and increasing risk of foreign object damage
Solution Approach 1:
The payload is housed within a launcher body that forms a protective enclosure, nesting the payload inside the launcher structure. This allows the payload to be protected from environmental conditions while maintaining easy access through the launch mechanism.
Solution Approach 2:
The payload is pre-positioned within the launcher body before flight, with control surfaces in a retracted position. This preliminary arrangement protects the payload during transport while enabling quick deployment when needed.
2Stability of the object's composition
If the payload has deployable control surfaces that extend outwardly, then the payload can achieve stable flight, but the control surfaces may extend undesirably while the payload is still attached to the aircraft causing drag and potential damage
Solution Approach 1:
The control surfaces are designed to be dynamically adjustable between retracted and extended positions. They remain retracted while the payload is attached to the aircraft to minimize drag, and extend only after separation to provide flight stability.
Solution Approach 2:
The control surfaces are pre-positioned in a retracted state within the launcher body before payload release. This preliminary configuration eliminates aerodynamic interference during transport, with deployment occurring automatically after separation.
3Object-affected harmful factors
If the payload is retained within a protected launcher body, then the payload is protected from environmental factors, but the release mechanism becomes more complex
Solution Approach 1:
The launcher is divided into distinct functional segments: a protective body portion, a separable door portion, and a payload retention mechanism. This segmentation allows each component to perform its specific function independently while maintaining overall system protection.
Solution Approach 2:
The payload retention mechanism uses pre-positioned brackets and fastening structures that automatically engage and disengage during the launch sequence. This preliminary arrangement simplifies the release action while maintaining secure retention during transport.
4Speed
If the door portion rotates to expose the bay area for payload release, then the payload can be deployed with angular momentum, but the mechanism requires precise control to ensure proper orientation
Solution Approach 1:
The door portion follows a substantially elliptical rotational path that naturally generates consistent angular momentum. This curved trajectory ensures uniform force application and predictable payload orientation during deployment.
Solution Approach 2:
The brackets are pre-configured with specific geometric features that guide the payload orientation during rotation. This preliminary setup ensures proper alignment is maintained throughout the rotational launch sequence without requiring active control adjustments.
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
The system protects payloads from environmental factors, reduces drag, and minimizes foreign object damage by ensuring controlled and efficient release, enhancing the safety and functionality of aircraft operations.
Implementation Method 1
a biasing portion configured to transfer an angular momentum of the rotating door portion to the payload arranged within the door portion
Data Source
AI summary
The present disclosure provides a payload deployment system that is operative to receive and retain a configurable payload. The payload deployment mechanism helps to reduce the drag of the payload and to protect the payload from environmental factors. The payload may be released using a hinge mechanism to ensure the payload does not contact the payload deployment mechanism when the payload is deployed. A vent may be utilized to equalize pressure between the external environment and a body portion of the payload deployment mechanism. The vent may generate an additional force to assist in separating the payload from the launcher.