Carrier Vehicle Launch System for High Altitude UAV Deployment
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Solution Overview
Problem
Current UAV systems face challenges in rapidly deploying payload vehicles to high altitudes, especially above 3 km, as existing systems are inefficient and require payload vehicles to possess their own propulsion systems or have limited climb rates.
Innovation Solution
A launch system comprising a carrier vehicle with a solid rocket propulsion system and a payload vehicle designed for subsonic cruise speed, where the carrier vehicle propels the payload vehicle to the desired altitude and releases it at a correlated forward speed, enabling faster deployment and higher altitudes than the payload vehicle could achieve alone.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If high lift-to-drag ratio aircraft configurations are used to optimize subsonic cruise performance at high altitude, then cruise efficiency is improved, but climb rate to such altitudes deteriorates
Solution Approach 1:
The system divides the mission into two distinct phases: a launch phase using a carrier vehicle with rocket propulsion to rapidly reach high altitude, and a cruise phase using the payload vehicle's aerodynamic propulsion system. This segmentation allows each subsystem to be optimized for its specific function, resolving the contradiction between climb rate and cruise efficiency.
Solution Approach 2:
The carrier vehicle acts as an intermediary that provides the payload vehicle with initial altitude and velocity. The carrier vehicle's solid rocket propulsion system serves as a mediator to transfer the payload vehicle to the desired flight conditions, enabling the payload vehicle to operate in its optimal subsonic cruise regime without needing high climb rate capabilities.
2Adaptability or versatility
If payload vehicles use their own propulsion systems to reach high altitudes, then deployment independence is improved, but deployment speed and efficiency deteriorate
Solution Approach 1:
The system segments the propulsion function between the carrier vehicle (solid rocket propulsion for rapid ascent) and the payload vehicle (aerodynamic propulsion for sustained cruise). This allows the payload vehicle to be deployed rapidly to high altitude by the carrier while maintaining its own propulsion system for independent sustained operation.
Solution Approach 2:
The carrier vehicle performs preliminary action by propelling the payload vehicle to the desired high altitude and forward speed before release. This preliminary propulsion action enables the payload vehicle to be deployed rapidly to operational altitude without relying on its own slower propulsion system for the ascent phase.
3Device complexity
If conventional propulsion systems are used to reach high altitudes, then system simplicity is improved, but deployment capability above 3 km deteriorates
Solution Approach 1:
The system merges two different propulsion technologies: solid rocket propulsion in the carrier vehicle for rapid altitude gain, and aerodynamic propulsion in the payload vehicle for sustained flight. This combination enables deployment above 3 km while maintaining operational simplicity through clear functional separation.
Solution Approach 2:
The carrier vehicle with solid rocket propulsion serves as an intermediary that bridges the gap between ground level and high altitude operations. This intermediary system enables the payload vehicle to access altitudes above 3 km that would be difficult to reach with conventional propulsion alone, while the overall system remains relatively simple through functional specialization.
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
Enables rapid and efficient deployment of payload vehicles to high altitudes, exceeding the capabilities of conventional systems, allowing for emergency situations and extended cruise or loiter times at subsonic speeds.
Implementation Method 1
the carrier vehicle configured for carrying the at least one payload vehicle at least up to said desired altitude, and further comprising a solid rocket propulsion system for propelling said launch system to said desired altitude
Implementation Method 2
the payload vehicle comprising a payload propulsion system and aerodynamic lift surfaces designed for providing the payload vehicle with aerodynamic powered flight at a design subsonic cruise speed
Data Source
AI summary
According to at least one example a launch system is provided, including a carrier vehicle and at least one payload vehicle. The payload vehicle includes a payload propulsion system and aerodynamic lift surfaces designed for providing the payload vehicle with aerodynamic powered flight at a design subsonic cruise speed at a desired altitude. The carrier vehicle is configured for carrying the at least one payload vehicle at least up to the desired altitude, and further includes a solid rocket propulsion system for propelling the launch system to the desired altitude. The carrier vehicle is configured for providing a predetermined forward speed at the desired altitude, correlated to the design subsonic cruise speed. The carrier vehicle is configured for releasing the payload vehicle with respect to the carrier vehicle at the desired altitude and the predetermined forward speed. The design subsonic cruise speed is less than 0.7 Mach number, and, the desired altitude is greater than 3 km.