Wedge Outlet Fairing for Combined Axial and Lateral Thrust
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing thrust flow powered vehicles, such as missiles, require complex control systems and significant redesigns to achieve axial thrust components, making them costly, unreliable, and difficult to maintain, especially in retrofitting existing systems.
Innovation Solution
A thrust flow powered vehicle design featuring a wedge-shaped outlet fairing with a short angled portion and a tapered portion, allowing independent control of thrust flows from two nozzles to generate both lateral and axial thrust components without a separate control system, and a fixed deflector surface that deflects thrust flows at an angle, reducing complexity and increasing aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a jetavator is used to deflect lateral flow to provide axial thrust, then the missile moves horizontally away from the launch site, but the control system becomes complex and sealing is required
Solution Approach 1:
The patent combines the lateral flow deflection function and axial thrust generation function into a single integrated outlet fairing structure. The fixed deflector surface within the fairing simultaneously redirects both lateral flows to produce axial thrust, eliminating the need for separate jetavators and their complex control systems while maintaining missile safety
2Reliability
If a jetavator is used to provide axial thrust, then the missile moves away from the launch site, but sealing is required over the nozzle
Solution Approach 1:
The outlet fairing integrates the deflection function and thrust generation into a single structure where the fixed deflector surface redirects lateral flows. This unified approach eliminates the need for separate jetavators that would require sealing mechanisms, thereby maintaining safety while reducing structural complexity
Solution Approach 2:
Instead of using a movable jetavator that rotates to deflect flow, the patent uses a fixed fairing structure with a stationary deflector surface. This inverts the approach from active mechanical deflection to passive geometric redirection, eliminating sealing requirements while achieving the same thrust generation
3Reliability
If a jetavator is used to deflect lateral flow, then axial thrust is provided, but it requires significant space and redesign for retrofitting
Solution Approach 1:
The outlet fairing combines multiple functions (flow deflection, thrust generation, and structural support) into a single integrated component that can be attached to existing missile configurations. This modular design requires minimal space and allows retrofitting without significant redesign of the original missile structure
Solution Approach 2:
The outlet fairing is designed as a universal component that can be applied to various missile configurations. Its multi-functional design (providing both flow deflection and thrust generation) allows it to serve multiple purposes simultaneously, making it suitable for retrofitting existing missiles without requiring extensive modifications
4Measurement precision
If separate control systems are used for each thrust flow, then precise thrust control is achieved, but device complexity increases
Solution Approach 1:
The patent merges the control of both lateral flows into a single control system that independently regulates the magnitude of each flow. By controlling the flow rates from the two lateral nozzles, the system achieves precise control over the resultant axial thrust without requiring separate control mechanisms for each flow path
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 simplifies the control of thrust direction, reduces costs, enhances reliability, and minimizes drag and turbulence, allowing for efficient lateral and axial movement without the need for complex control systems, and can be retrofitted to existing vehicles.
Implementation Method 1
a thrust flow deflector surface comprising a portion at an angle to the plane of the first and second directions, and an outlet portion through which an output thrust flow is to be expelled, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow
Data Source
Figure 1
Figure 2
Figure 3
AI summary
Thrust flow powered vehicle (100) comprising a first thrust flow expeller (130) for expelling a first thrust flow in a first direction, a second thrust flow expeller (131) for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface (124) at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.