Missile Nose Cone Shell Ejection via Curved Support Element
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Solution Overview
Problem
Existing missile nose cone ejection systems fail to effectively control the ejection angle of shells at high speeds and low altitudes, leading to potential re-attachment and increased residual mass due to articulation hinges, which compromises performance and structural integrity.
Innovation Solution
A nose cone design featuring a support element with a circular arc shape and edge assembly that allows shells to pivot from a parallel to an angled position, enabling controlled ejection by maintaining contact until a predetermined angle is reached, eliminating the need for hinges and reducing residual mass.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If articulation hinges are used to enable shell ejection, then the shells can be ejected from the nose cone, but the residual mass on the terminal vehicle increases due to the mass of hinges
Solution Approach 1:
The patent removes the articulation hinges from the system entirely. Instead of using hinges to enable shell ejection, the invention uses a fixed support element with a specific geometric configuration (circular arc shape with edge assembly and crown element) that allows shells to be ejected through aerodynamic forces alone, eliminating the need for mechanical articulation mechanisms and their associated mass.
Solution Approach 2:
The patent replaces the mechanical hinge-based articulation system with an aerodynamic solution. The support element's geometry is designed so that aerodynamic forces during flight naturally enable shell ejection at the appropriate moment, substituting a mechanical system with one based on fluid dynamics and aerodynamic principles.
2Ease of operation
If shells are designed to pivot at high speeds, then ejection can be achieved, but the shells risk rotating too quickly and falling back on the missile body
Solution Approach 1:
The support element features a circular arc shape with specific curvature radii (R1 for the edge assembly, R2 for the crown element). This curved geometry is designed to control the shell ejection trajectory by guiding the shells along a predetermined path that prevents excessive rotation and ensures they do not fall back on the missile body during high-speed flight.
Solution Approach 2:
The patent optimizes geometric parameters of the support element, including the circular arc radii (R1, R2), the angle alpha between the edge assembly and crown element, and the position of the rear end of the shell. These parameter changes are specifically tuned to control shell rotation speed and trajectory during ejection at high velocities.
3Strength
If the nose cone is designed to withstand important loading factors, then structural integrity is maintained, but usual articulation solutions cannot maintain the base of the nose cone
Solution Approach 1:
The support element is designed as a integrated structural component that is segmented into functional zones: the edge assembly, the crown element, and the housing formation. This segmentation allows each zone to be optimized for its specific function while collectively maintaining the nose cone base structure under important loading factors during flight and transport.
4Reliability
If minimum opening angle is guaranteed for subsonic flight, then shells do not close under aerodynamic flow, but this is incompatible with low-altitude high-speed separation
Solution Approach 1:
The support element geometry is designed to dynamically adapt to different flight regimes. The circular arc configuration with specific radii and the angle alpha between components create a system that automatically provides appropriate shell separation characteristics for both subsonic flight (maintaining minimum opening angle) and low-altitude high-speed separation (enabling controlled ejection), eliminating the need for different design configurations.
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 solution ensures controlled and reliable ejection of nose cone shells at high speeds and low altitudes, maintaining structural integrity and enhancing missile performance by minimizing residual mass and avoiding re-attachment risks.
Implementation Method 1
on subsonic missile flying in a low atmosphere, simply, generally, it is ensured that the shells of the nose cone do not close under the effect of the aerodynamic flow
Implementation Method 2
At these high speeds, the surface temperature of the missile can reach several hundred degrees Celsius under the effect of the aerothermal flow
Data Source
AI summary
A missile includes a separable nose cone having an ejectable shell cooperating with a support element. The missile has a body with a main longitudinal axis and a nose cone having a shell connected by a rear end thereof to a support element of the missile and defined around a secondary longitudinal axis. The support element has a housing, and the rear end of the shell has a thickness adapted to be received in the housing in a contacting manner. The housing is configured to allow the shell to pivot and to maintain contact while the orientation of the shell is such that the secondary longitudinal axis is at an angle smaller than an ejection angle in relation to said main longitudinal axis, and to end the contact when the secondary longitudinal axis is at an angle higher than or equal to the ejection angle in such a way as to eject the shell from the missile.