Deployable Wing UAV for Beyond-Line-of-Sight Targeting
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Solution Overview
Problem
Modern small arms grenade munitions face challenges in accurately targeting enemy positions, especially when operatives lack a direct line of sight due to their parabolic trajectory limitations and inability to alter flight paths, leading to potential civilian casualties and collateral damage.
Innovation Solution
An unmanned aerial vehicle (UAV) designed for deployment from a projectile casing, featuring a wing assembly that deploys after reaching apogee, equipped with rotors for lift generation and an inertial measurement unit for trajectory estimation, allowing for autonomous flight and targeting adjustments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If small arms grenade munitions are used to engage targets, then operatives can attack enemy positions, but they require direct line of sight and cannot target enemies in defilade positions or behind cover
Solution Approach 1:
The patent transitions from ground-level grenade throwing to aerial drone delivery, changing the dimension of attack from horizontal to vertical. The drone can fly over hills, trees, and other obstacles to deliver munitions to targets in defilade positions, eliminating the line of sight requirement while maintaining target engagement capability
Solution Approach 2:
The unmanned aerial vehicle serves as an intermediary between the operative and the target. The drone carries the munition through the air to a location near or on the target, allowing the operative to engage enemies behind cover without exposing themselves or requiring direct line of sight
2Productivity
If conventional grenade munitions are used, then the projectile follows a parabolic trajectory, but the trajectory cannot be altered once fired
Solution Approach 1:
The patent replaces the static, fixed parabolic trajectory of conventional grenades with a dynamic, controllable flight path. The drone can adjust its trajectory in real-time based on target location, environmental conditions, and mission requirements, providing both speed and flexibility by flying directly to the target area rather than following a predetermined arc
3Speed
If the wing assembly is deployed during transit, then lift can be generated, but the internal components are exposed and aerodynamic flight is disrupted
Solution Approach 1:
The patent divides the operational sequence into distinct phases: a transit phase where the wing assembly is retracted and integrated with the projectile casing for protection and aerodynamics, and a deployment phase where the wing assembly is extended for lift generation. This temporal segmentation allows the system to optimize for both component protection and aerodynamic flight capability at different times
Solution Approach 2:
The wing assembly transitions from a static, integrated state during transit to a dynamic, deployed state during flight operations. This dynamic reconfiguration allows the system to maintain aerodynamic integrity and protect components during transit while enabling lift generation when needed, resolving the contradiction between protection and flight capability
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 precise engagement of enemy targets, including those in defilade positions, by breaking from the parabolic trajectory and providing flexible, dynamic flight paths, reducing collateral damage and enhancing operational safety.
Implementation Method 1
a propulsion system including at least one rotor disposed on the wing assembly to generate lift
Implementation Method 2
the wing assembly in the closed position may be substantially integral with the projectile casing to effect aerodynamic flight when the projectile casing is projected into an airborne trajectory
Implementation Method 3
The wing assembly may include a spring return means used to bias the wing assembly towards the closed position
Implementation Method 4
equipped with rotors for lift generation and an inertial measurement unit for trajectory estimation
Data Source
AI summary
An unmanned aerial vehicle (UAV) adapted for transit in and deployment from a projectile casing is provided. The UAV includes a wing assembly coupled to the projectile casing and the wing assembly moveable between a closed position and a deployed position. The UAV further includes a propulsion system including at least one rotor disposed on the wing assembly to generate lift, wherein in the closed position, the wing assembly is substantially integral with the projectile casing and in the deployed position, the wing assembly is extended outwards from the projectile casing.