Integrated Wing and Covering Unit for Flying Object Drag Reduction
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Solution Overview
Problem
Existing flying objects, such as missiles, face challenges in maintaining stability and reducing weight and drag due to the installation of tail wings, which require additional components and increased fabrication costs, and often compromise on aerodynamics and heat resistance.
Innovation Solution
A flying object design featuring a covering unit integrated with a wing unit, where the wing is protruded from the outer surface of the covering unit, and a fixing member is used to secure the covering unit to the nozzle assembly, minimizing drag and weight by eliminating the need for a coupling structure and reducing heat transmission.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a foldable tail wing is installed in the nozzle structure, then flying stability is maintained, but additional drag is generated due to bending the free surface of the nozzle structure
Solution Approach 1:
The tail wing is integrated with the covering unit to form a unified structure. The covering unit that already surrounds the nozzle assembly now also incorporates the tail wing functionality, eliminating the need for separate fastening structures and reducing drag by avoiding bending of the nozzle structure's free surface.
2Temperature
If the nozzle assembly is fabricated with improved heat resistance characteristics, then heat resistance is improved, but the weight of the nozzle assembly is inevitably increased
Solution Approach 1:
The covering unit acts as a thermal barrier between the hot nozzle assembly and the tail wing. By positioning the covering unit (which can be made of lighter materials) between the heat source and the tail wing, heat transmission is reduced without requiring the nozzle assembly itself to be made of heavy heat-resistant materials.
3Stability of the object's composition
If a fixed tail wing is bolt-fastened to a cylindrical covering, then aerodynamics requirements are met, but the covering unit and fastening unit are required to have rigidity, making it difficult to reduce weight
Solution Approach 1:
The tail wing and covering unit are formed as a single integrated structure through extrusion molding. This eliminates the need for separate fastening components and reduces the overall weight by removing the covering unit's structural reinforcement requirements, while still meeting aerodynamic requirements through precise integral forming.
4Stability of the object's composition
If components for fastening or assembling are increased to support aerodynamics, then aerodynamic stability is improved, but fabrication costs are high and number of assembly processes is increased
Solution Approach 1:
The covering unit and tail wing are formed as a single integrated component using extrusion molding, eliminating the need for multiple fastening components and assembly steps. This reduces fabrication cost and simplifies manufacturing while maintaining aerodynamic stability through the integral structure.
5Stability of the object's composition
If the wing is insertedly fixed to the covering and the covering is bolt-fastened with a skirt, then the wing is securely attached, but it is difficult to precisely form tolerance of the structure
Solution Approach 1:
The tail wing and covering unit are formed as a single integrated structure through extrusion molding, eliminating multiple fastening interfaces and their associated tolerance accumulation problems. The integral forming process ensures precise geometric tolerances are achieved in one step rather than through multiple assembly operations.
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 design enhances stability and reduces the weight and drag of the flying object while maintaining aerodynamic performance and heat resistance, and allows for precise processing of the wing unit without increasing assembly complexity or costs.
Implementation Method 1
a nozzle assembly (410) formed to discharge a burnt propellant in one direction in order to provide propulsion to the flying object body
Implementation Method 2
a combustion tube formed to burn the propellant by the nozzle assembly
Implementation Method 3
the combustion tube and the nozzle assembly are in contact to allow heat generated from the combustion pipe to be transmitted to the nozzle assembly
Implementation Method 4
a wing unit protruded from an outer surface of the covering unit in a direction crossing the one direction
Data Source
AI summary
Disclosed is a flying object in which a covering unit and a wing unit installed in a nozzle assembly are integrally formed to form a smooth outer surface of the flying object, thus minimizing drag, and the covering unit and the nozzle assembly are fastened by using a fastening member having one end fastened to a slit, thereby preventing the flying object from being damaged by thermal deformation.