Unmanned Aerial Vehicle Release Parachute System
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Solution Overview
Problem
Existing methods for deploying unmanned missiles from aircraft often result in uncontrolled separation from containers, potential collateral damage, and instability in flight due to lack of defined orientation, especially for asymmetrical missiles with wings.
Innovation Solution
A method involving a ready-to-deploy missile being ejected with a braking parachute, followed by a carrying parachute to stabilize the missile about its roll axis, allowing controlled free flight after release of support lines, enabling aerodynamic stabilization and propulsion activation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a braking parachute is used to pull the missile out of the aircraft, then the missile can be deployed from the aircraft, but the missile assumes an uncontrolled position around the roll axis
Solution Approach 1:
The deployment system is segmented into two functional parachutes: a braking parachute for extraction and a carrying parachute for stabilization. This segmentation allows each parachute to perform its specific function optimally without interfering with the other's performance.
Solution Approach 2:
The carrying parachute acts as an intermediary device between the braking parachute and the missile. It provides the necessary stabilization function that the braking parachute cannot provide, mediating the transition from uncontrolled extraction to controlled free flight.
2Productivity
If the missile is deployed without a container, then deployment speed is improved, but collision risk during separation increases
Solution Approach 1:
The missile is preliminarily positioned on a pallet with rollers before deployment. The rollers are prepared in advance to facilitate smooth extraction, and the carrying parachute is pre-attached to the missile, ready to deploy immediately upon extraction to prevent collisions.
3Device complexity
If only a braking parachute is used, then device complexity is reduced, but controlled free flight cannot be ensured
Solution Approach 1:
The parachute system is segmented into two distinct components with separate functions. The braking parachute handles extraction, while the carrying parachute handles stabilization. This segmentation justifies the increased complexity by providing reliable controlled free flight that a single parachute cannot achieve.
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
Ensures controlled free flight and reduces collateral damage by stabilizing the missile's orientation and enabling timely activation of aerodynamic surfaces and propulsion, enhancing deployment efficiency and safety.
Implementation Method 1
braking the missile by means of a first parachute forming a braking parachute
Implementation Method 2
Opening a second parachute forming a carrying parachute, which is attached to the upper side of the missile
Data Source
Figure 1A~1D
AI summary
A method for releasing an unmanned aerial vehicle from an aircraft comprises the following steps: a) providing a release-ready aircraft (2) at a release port (12) of the aircraft (1), b) releasing the aircraft (2) from the release port (12) of the aircraft (1). c) Braking the missile (2) by means of a first parachute forming a braking parachute (3), which is attached to the rear of the missile (1) by at least one braking line (30), d) Opening a second parachute forming a gliding parachute (4), which is attached to the top of the missile (2) by means of a front gliding line (42) and a rear gliding line (44), and releasing the braking parachute (3) from the missile (2), e) Releasing the front gliding line (42) of the gliding parachute (4), so that the nose of the missile (2) pitches downwards, and f) Releasing the rear gliding line (44) of the gliding parachute (4), so that the missile (2) enters free flight.