Hypersonic Payload Separation via Negative Angle of Attack
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Solution Overview
Problem
Reusable launch systems face challenges in efficiently separating payloads at hypersonic speeds due to high energy requirements and complex landing procedures, especially when operating at sub-orbital altitudes, which increase costs and operational complexity.
Innovation Solution
A reusable atmospheric re-entry launch system with a booster and upper stage rocket configuration, utilizing a pitch control system and mounting system to adjust the angle of attack to a negative angle during hypersonic flight, allowing for controlled payload separation at low dynamic pressures, and enabling unpowered landing and reusability of the booster.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If payload separation occurs at sub-orbital altitudes with vertically stacked rockets, then orbit insertion capability is achieved, but energy requirements increase roughly 30 times compared to hypersonic separation
Solution Approach 1:
The patent changes the separation parameters from sub-orbital vertical configuration to hypersonic horizontal configuration. By separating at hypersonic speeds (Mach 5+) in a horizontal orientation with negative angle of attack, the system reduces energy requirements by approximately 30 times while maintaining separation reliability through aerodynamic force utilization.
2Productivity
If vertically stacked rockets are used for orbit insertion, then payload deployment capability is achieved, but operational complexity and costs increase
Solution Approach 1:
The patent inverts the conventional approach by using horizontal stacking instead of vertical stacking, and hypersonic separation instead of sub-orbital separation. This inversion simplifies the system by eliminating the need for complex vertical landing procedures, engine assistance, and flip maneuvers, thereby reducing operational complexity and costs while maintaining productivity.
3Ease of operation
If booster landing is performed vertically in upright position, then booster reusability is achieved, but landing complexity requires engine assistance, complex control systems, and flip maneuvers
Solution Approach 1:
The patent inverts the landing approach from vertical upright landing to horizontal landing. By maintaining a horizontal orientation throughout flight and separating at hypersonic speeds, the booster can land horizontally without requiring complex vertical landing procedures, engine assistance, or flip maneuvers, thereby simplifying operations and reducing control system complexity.
4Force
If separation occurs at positive angle of attack with high dynamic pressure, then separation force is sufficient, but forces required are extremely high and separation control becomes difficult
Solution Approach 1:
The patent changes the separation parameters from positive angle of attack to negative angle of attack at hypersonic speeds. This parameter change reduces the separation forces required while improving separation control, as the negative angle of attack creates favorable aerodynamic conditions for controlled separation without the extreme forces and control difficulties associated with positive angle of attack separation.
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 approach simplifies payload separation and booster recovery by reducing energy requirements and operational complexity, enabling efficient and cost-effective hypersonic payload deployment and booster reusability.
Implementation Method 1
commanding the at least one pitch control system to adjust an angle of attack of the body to a negative angle of attack
Implementation Method 2
a rocket engine coupled to the body and configured to accelerate the body to a hypersonic speed
Implementation Method 3
a rocket engine coupled to the body and configured to accelerate the body to a hypersonic speed
Implementation Method 4
commanding the mounting system to release the payload while the body is moving at the hypersonic speed and at the negative angle of attack
Data Source
AI summary
An apparatus includes a body having at least one pitch control system and a mounting system, the mounting system configured to couple to a payload. The apparatus also includes a rocket engine coupled to the body and configured to accelerate the body to a hypersonic speed. The apparatus further includes a control system configured to release the payload while the body moves at the hypersonic speed by commanding the at least one pitch control system to adjust an angle of attack of the body to a negative angle of attack and commanding the mounting system to release the payload while the body is moving at the hypersonic speed and at the negative angle of attack.