Separable Missile Hanger Prevents Rail Contact
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Solution Overview
Problem
Missiles with sensitive rear parts risk damage during launch due to contact with the launch rail, and existing hanger designs either fail to absorb tensile forces during flight or cause jamming and increased air resistance when attempting to prevent such contact.
Innovation Solution
The rearmost hanger is designed with two separable main parts connected by a dovetail joint, allowing separation during launch to prevent contact with the launch rail while maintaining the ability to absorb both compressive and tensile forces during flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the rearmost hanger includes lateral flanges to take up tensile forces during flight, then the hanger can absorb tensile loads, but the lateral flanges create an undesired hinge action during launch causing the missile rear to hit the rail
Solution Approach 1:
The hanger is divided into two separable parts: a body portion that remains attached to the rail and provides guidance, and lateral flanges that can detach during launch. This segmentation allows the flanges to perform their tensile force absorption function during flight while preventing hinge action during launch when they separate from the missile body.
Solution Approach 2:
The hanger transitions from a static, integral structure to a dynamic, separable structure. The lateral flanges are designed to detach automatically under specific launch conditions, transforming the hanger from a rigid connection to a separable mechanism that adapts to different operational phases (flight vs. launch).
2Object-affected harmful factors
If lateral flanges are removed to prevent hinge action during launch, then rear contact with rail is prevented, but the hanger cannot take up tensile forces during ordinary flight time
Solution Approach 1:
The hanger body and lateral flanges are segmented into separate detachable components. The body portion remains on the rail to provide continuous guidance and support, while the flanges detach during launch to prevent hinge action, yet remain attached during flight to absorb tensile forces.
Solution Approach 2:
The hanger structure dynamically changes configuration based on operational phase. During flight, the flanges are attached to provide tensile strength; during launch, they separate to eliminate hinge action, creating a dynamic adaptation to different operational requirements.
3Object-affected harmful factors
If supplementary laterally extending collars are added to prevent rear contact during launch, then compressive forces are protected, but the hanger cannot take up tensile forces and front hangers are subjected to higher loads
Solution Approach 1:
The collar protection feature is merged with the detachable flange structure. The collars are integrated into the flange assembly, so that when the flanges detach during launch, the collars remain attached to the hanger body to provide compressive protection, while the flange portion provides tensile force absorption when attached during flight.
Solution Approach 2:
The hanger structure achieves multi-functionality by combining multiple features: the body provides guidance and support, the collars provide compressive protection, and the detachable flanges provide tensile force absorption during flight while preventing hinge action during launch. This universal design handles both compressive and tensile loads appropriately in different operational phases.
4Reliability
If the rearmost hanger is modified to prevent contact during launch, then missile safety is improved, but the hanger structure becomes more complex and may cause jamming problems
Solution Approach 1:
The hanger is segmented into simple, geometrically straightforward components (body and flanges) that separate through basic mechanical detachment. This segmentation achieves safety without requiring complex control systems, sensors, or actuation mechanisms, maintaining structural simplicity while improving reliability.
Data Source
Figure 1~2
Figure 3~4c
AI summary
A missile launching system, comprising a launch rail (34) for attachment to an aircraft and having a longitudinal slot (32, 36), and at least two hangers for attachment to the missile at longitudinally spaced locations thereof and having a cross-section configured to be received in said longitudinal slot in the launch rail (34). The rearmost hanger (10) includes two separable main parts, i.e. a first main part (12) for engagement with a respective lateral, first groove section (32) of the slot, and a second main part (14) configured to be attached to the missile and be slidably guided in a second groove section (36) of the slot normal to the first groove section (32) and opening towards the missile (24), said second main part (14) having laterally extending collars (26) configured to interact in close proximity with respective rail sections (40) facing the missile. The second main part (14) is configured to separate from the first part (12) when launching the missile.