Deployable Wing UAV for Mid-Flight Trajectory Adjustment
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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 adjust mid-flight, making it difficult to engage defilade targets without causing civilian casualties or collateral damage.
Innovation Solution
An unmanned aerial vehicle (UAV) designed for deployment from a projectile casing, featuring a wing assembly that deploys mid-flight, equipped with a propulsion system and an inertial measurement unit (IMU) for trajectory estimation and control, allowing for autonomous loitering and targeting capabilities, including swarming features for coordinated attacks.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional small arms grenade munitions are used with parabolic trajectory, then the munition can be fired with simple mechanics, but the trajectory cannot be altered mid-flight and direct line of sight is required for accurate targeting
Solution Approach 1:
The munition is divided into two main segments: a projectile casing that follows the initial parabolic trajectory and a UAV component that deploys mid-flight. This segmentation allows the munition to benefit from both the simplicity of conventional grenade firing and the flexibility of UAV-controlled flight paths, resolving the contradiction between adaptability and complexity.
Solution Approach 2:
The UAV is pre-positioned within the projectile casing before firing, with all necessary components (propulsion system, wing assembly, payload) already in place. This preliminary preparation enables the UAV to transition from a passive projectile to an active, controllable flight platform mid-trajectory, achieving trajectory adjustment without requiring complex pre-firing setup.
2Ease of operation
If the wing assembly is deployed during transit, then the UAV can generate lift for controlled flight, but the internal components are exposed to damage during storage and handling
Solution Approach 1:
The wing assembly is designed to be dynamic rather than static, transitioning from a retracted position during storage and transit to a deployed position during flight. This dynamic configuration allows the same structure to provide both protection (when retracted) and flight capability (when deployed), eliminating the need for separate protective and functional states.
Solution Approach 2:
The wing assembly is nested within the projectile casing during storage, with the wings folded along the longitudinal axis and contained within the casing boundaries. This nesting arrangement protects the wings and internal components during handling while allowing full deployment when needed for flight, resolving the contradiction between protection and operational capability.
3Adaptability or versatility
If the wing assembly is made resilient to allow deployment, then the structure can flex between positions, but the structural strength may be compromised
Solution Approach 1:
The wing assembly utilizes materials and structures that can change their mechanical parameters dynamically. The resilient material properties allow the wings to flex during deployment while maintaining sufficient structural strength when loaded, optimizing both flexibility and strength through parameter optimization rather than compromise.
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 without direct line of sight, reduces collateral damage, and allows for dynamic adjustments in flight path, enhancing operational flexibility and safety by breaking free from conventional parabolic trajectories and enabling selective targeting with various payloads.
Implementation Method 1
a propulsion system including at least one rotor disposed on the wing assembly to generate lift
Implementation Method 2
equipped with a propulsion system and an inertial measurement unit (IMU) for trajectory estimation and control
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
The wing assembly is coupled to the projectile casing via a hinge. The hinge may include a pin associated with a mounting flange. The hinge may be configured to pivot about an axis transverse to the movement of the wing assembly
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.