Electric UAV Launcher with Motor-Driven Tape
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Solution Overview
Problem
Current UAV launching systems rely on hydraulic-pneumatic systems, which are heavy, complex, and prone to leaks, require pre-charging with nitrogen, and impose high g-load spikes, making them environmentally unfriendly and inefficient for mobile and expeditionary use.
Innovation Solution
An electrically powered launcher system using a motor-driven tape mechanism to propel a shuttle along a launcher rail, eliminating hydraulic fluids and nitrogen, with a detachable shuttle and secondary arrestment strap to control g-loads and enhance mobility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a pneumatic or hydraulic system is used as the prime propulsion system, then the UAV can be launched with sufficient force and speed, but the system becomes heavy and complex
Solution Approach 1:
The patent extracts and eliminates the heavy hydraulic-pneumatic system components (accumulators, hydraulic fluids, compressed gas bottles) while retaining the essential launch function through a simplified electric motor-driven cable reel mechanism. This removes the disturbing heavy components while preserving the core launch capability.
Solution Approach 2:
The patent replaces the complex hydraulic-pneumatic mechanical system with an electric motor-driven system. The electric motor converts electrical energy to mechanical motion, driving the cable reel to pull the UAV along the guide rail, thereby substituting the heavy fluid-based mechanical system with a lighter electric-based system.
2Force
If a pneumatic or hydraulic system is used, then the UAV can be launched, but the system requires pre-charging with compressed gases and has leak concerns
Solution Approach 1:
The patent removes the compressed gas accumulators and hydraulic fluid reservoirs from the system, eliminating the sources of potential leaks. The launch force is generated on-demand by the electric motor without requiring pre-stored pressurized fluids or gases.
Solution Approach 2:
The electric motor-driven system generates launch force self-sufficiently without requiring external gas bottles or hydraulic fluid replenishment. The system serves itself by converting electrical energy directly to mechanical launch force, eliminating the need for external pressurization systems.
3Speed
If a launcher allows shorter distance to achieve flight, then the launch velocity is achieved faster, but higher g-loads are imparted to the UAV
Solution Approach 1:
The patent employs dynamic control of the cable tension through the electric motor's variable speed capability. The motor can adjust the acceleration profile in real-time, increasing force application at the beginning of the launch stroke and reducing it as the UAV approaches launch velocity, thereby controlling g-loads dynamically throughout the launch sequence.
Solution Approach 2:
The system changes the acceleration parameter dynamically during the launch process. By varying the electric motor's torque output and rotational speed, the system optimizes the balance between launch velocity achievement and g-load management, allowing shorter launch distances while protecting sensitive UAV electronics.
4Reliability
If a hydraulic-pneumatic system is used, then the system can provide reliable launch, but the reset time is lengthy due to fluid recovery
Solution Approach 1:
The patent replaces the hydraulic fluid recovery process with an electric motor-driven cable retraction mechanism. After launch, the electric motor simply winds the cable back onto the reel, a much faster process than pumping hydraulic fluid back through the system. This substitution eliminates the time-consuming fluid recovery phase.
Solution Approach 2:
The electric motor can immediately begin retracting the cable after launch without waiting for fluid pressure equalization or system depressurization. The continuous electrical power supply enables uninterrupted operation, allowing the motor to quickly reset the system for the next launch without the delays inherent in hydraulic-pneumatic systems.
5Force
If a pneumatic launcher is used, then the system can launch the UAV, but the system complexity increases due to control valves and pressure regulation
Solution Approach 1:
The patent removes the complex network of control valves, pressure regulators, and flow control devices from the hydraulic-pneumatic system. The electric motor's inherent ability to precisely control torque and speed eliminates the need for these additional mechanical control components, significantly simplifying the overall system architecture.
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 achieves efficient and controlled launch with reduced weight, complexity, and environmental impact, allowing for faster launch and reset times, and improved g-load management, while eliminating the need for nitrogen pre-charging and reducing the risk of leaks.
Implementation Method 1
a drive mechanism including a DC motor
Data Source
Figure 1~2
Figure 3A~3B
Figure 3C~4
AI summary
Embodiments of the present invention provide improvements to UAV launching systems. The disclosed launching system eliminates the use of hydraulic fluid and compressed nitrogen or air by providing an electric motor-driven tape that causes movement of a shuttle along a launcher rail. The shuttle is detachable from the motor-driven tape, such that stoppage of the tape can be separate from stoppage of the shuttle. Embodiments further provide a secondary arrestment strap. Further embodiments provide an anti-rollback latch system.