Spin-Stabilized Flare Ballute and Spin Brake Design
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Solution Overview
Problem
Existing artillery flares with 2-stage ejection systems are inefficient due to environmental influences affecting pyrotechnic delay elements, leading to inconsistent deployment and requiring more space within the projectile, which limits the size of the illuminant and burn time.
Innovation Solution
A 1-stage ejection system is integrated into the projectile, utilizing a spin brake and a ballute for spin stabilization, with a single ejection charge pushing the internal structure out, and a separating device for the parachute line, allowing for a compact design and longer burn time.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a 2-stage ejection system with pyrotechnic delay elements is used, then the flare can be deployed from the projectile, but the space required in the projectile increases and the delay times become inconsistent due to environmental influences
Solution Approach 1:
The patent combines the two separate ejection stages into a single ejection event. The flare is ejected from the projectile in one stage, and the parachute is deployed in the same ejection event, eliminating the need for pyrotechnic delay elements and multiple ejection charges. This merging reduces the internal space required in the projectile while improving reliability by removing the inconsistent pyrotechnic timing mechanism.
Solution Approach 2:
The patent extracts and removes the pyrotechnic delay elements from the ejection system. By eliminating these unreliable timing components, the system achieves consistent deployment without requiring additional space for delay mechanisms, directly resolving the contradiction between reliability and space requirements.
2Volume of moving object
If a compact projectile structure is used, then the space for illuminant is reduced, but the burn time decreases
Solution Approach 1:
By merging the ejection and parachute deployment into a single stage, the patent eliminates the need for complex multi-stage mechanisms that consume internal space. This freed space is then allocated to increase the illuminant size, directly enabling longer burn time while maintaining a compact projectile structure.
Solution Approach 2:
The parachute is pre-positioned within the projectile and deployed simultaneously with the flare ejection. This preliminary arrangement eliminates the need for additional deployment mechanisms and space, allowing the compact structure to accommodate a larger illuminant for extended burn time.
3Extent of automation
If pyrotechnic delay elements are used for timing, then the deployment can be controlled, but the delay times scatter due to environmental influences
Solution Approach 1:
The patent completely removes pyrotechnic delay elements from the system, replacing them with a mechanical timing mechanism based on the fixed geometry of the packing sleeve and separator. This extraction of unreliable pyrotechnic components eliminates environmental sensitivity while maintaining automated deployment timing control.
Solution Approach 2:
The patent replaces the chemical/pyrotechnic timing system with a purely mechanical timing mechanism. The fixed-length packing sleeve and separator create a predetermined delay through mechanical motion, providing consistent timing control that is immune to environmental influences while maintaining automation.
4Ease of operation
If multiple ejection charges are used for 2-stage ejection, then the deployment sequence is controlled, but the cost and complexity increase
Solution Approach 1:
The patent merges two separate ejection charges and their associated control mechanisms into a single ejection charge system. This single charge simultaneously ejects the flare and triggers the parachute deployment sequence, reducing device complexity and cost while maintaining controlled deployment sequencing through the integrated mechanical timing mechanism.
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
This compact design enables a larger illuminant with a longer burn time, reducing space requirements and costs, while ensuring consistent descent speed and stability of the flare.
Implementation Method 1
The ejection charge 10 pushes the luminous element(s) 8 as well as the parachute carrier 4 with the spin brake 6 and the descent parachute 5 out of the projectile casing 7
Implementation Method 2
The spin of the spin-stabilized flares is reduced via a corresponding spin brake
Implementation Method 3
The spin of the spin-stabilized flares is reduced via a corresponding spin brake and additionally only by a ballute for the/the flare
Implementation Method 4
The flare then descends on the main parachute at a constant speed to the ground
Data Source
Figure 1~3
AI summary
The invention relates to a spin-stabilized flare (1), comprising a flare bottom (2), a flare shell (7), at least one luminous body (8), a parachute (5) connected to the at least one luminous body, a spin brake (6), and an ejection charge (10). Said flare (1) is characterized in that now a ballute (3) is integrated, which together with the spin brake (6) reduces the spin of the at least one luminous body (8).