Unpowered Missile Auxiliary Device with Disposable Wing Structure
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Solution Overview
Problem
Existing auxiliary devices for unmanned missiles are complex and cost-intensive, making it difficult to adapt them to changing mission parameters and increasing production costs.
Innovation Solution
A non-powered auxiliary device with a wing structure and holding device, featuring a separation mechanism, active control elements, and a fuel tank, designed to connect and support missiles without a separate drive, allowing for cost-effective production and rapid adaptation to mission changes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If existing auxiliary devices are used to enhance UAV aerodynamic properties, then the aerodynamic performance is improved, but the production cost and complexity increase significantly
Solution Approach 1:
The patent applies the disposable principle by designing the auxiliary device as a single-use component that is attached to the UAV, performs its aerodynamic function during flight, and is then discarded. This eliminates the need for complex, expensive, reusable auxiliary devices while achieving the same aerodynamic enhancement effect during the mission.
Solution Approach 2:
The auxiliary device is segmented into separate functional components including a holding device with connection elements, a separation mechanism, and aerodynamic surfaces. This segmentation allows for simplified manufacturing of individual parts and easier attachment to the UAV, reducing overall device complexity while maintaining aerodynamic performance.
2Adaptability or versatility
If existing auxiliary devices are used to adapt UAVs to additional mission parameters, then the mission adaptability is improved, but the production cost increases
Solution Approach 1:
The auxiliary device is designed with universal connection elements and a standardized holding device that can be attached to different UAV types. The separation mechanism and aerodynamic surfaces are configured to work with various mission parameters, allowing a single auxiliary device design to serve multiple mission requirements without increasing production cost.
Solution Approach 2:
By making the auxiliary device disposable and inexpensive to produce, the system can rapidly adapt to different mission parameters by deploying different auxiliary devices for different missions, rather than investing in expensive, multi-purpose reusable auxiliary systems.
3Ease of operation
If a separate drive unit is added to the auxiliary device, then the maneuverability is improved, but the production cost and complexity increase
Solution Approach 1:
The auxiliary device uses the UAV's existing motion and aerodynamic forces to achieve maneuvering without requiring its own separate drive unit. The holding device and separation mechanism are designed to utilize the UAV's flight characteristics, allowing the auxiliary device to perform its function passively while maintaining maneuverability through aerodynamic design rather than active propulsion.
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
The solution enables cost-effective and rapid production of auxiliary devices, improving maneuverability and extending missile range, while allowing for simple take-off and landing, and enabling the auxiliary device to be designed as disposable, reducing overall costs.
Implementation Method 1
The unpowered auxiliary device (100) has a wing structure (110)
Implementation Method 2
The holding device (120) has a separation mechanism (121) designed to disconnect the connection between the unpowered auxiliary device (100) and the at least one missile (200) during operation of the at least one missile (200)
Data Source
Figure 1~2
AI summary
The present invention relates to a non-powered auxiliary device (100) for at least one missile (200), wherein the non-powered auxiliary device (100) comprises: a wing structure (110); and a holding device (120) configured to connect the non-powered auxiliary device (100) and the at least one missile (200); wherein the holding device (120) comprises a separation mechanism (121) configured to release the connection between the non-powered auxiliary device (100) and the at least one missile (200) during operation of the at least one missile (100). Furthermore, the present invention relates to a missile system (10).