Reusable Launch Vehicle Trajectory Correction via Wind Maps
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Solution Overview
Problem
Conventional launch vehicles are expendable, leading to high costs due to the need for extensive reconditioning and ground-based infrastructure, which is time-consuming and costly, especially for partially reusable vehicles like the NASA space shuttle.
Innovation Solution
A reusable launch vehicle system that continuously monitors its position and environment to make course corrections during ascent and descent, employing wind maps and aerodynamic control surfaces to predict and adjust its trajectory for precise landing, minimizing the use of propulsion sources and reducing reconditioning needs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional expendable launch vehicles are used, then high costs are incurred due to extensive reconditioning and ground-based infrastructure, but the vehicles can be used only once
Solution Approach 1:
The launch vehicle performs self-correction of trajectory during flight using onboard sensors and control systems. The system autonomously monitors its position, predicts drift caused by winds aloft, and commands aerodynamic control surfaces to correct the trajectory without requiring extensive ground-based intervention or reconditioning infrastructure.
Solution Approach 2:
The system continuously monitors the launch vehicle's position using sensors and compares it with the desired trajectory. Based on this feedback, the system predicts future position and commands corrections to aerodynamic control surfaces to maintain accurate trajectory, enabling precise landing without extensive ground infrastructure.
2Measurement precision
If trajectory correction is made during ascent, then precise landing is achieved, but propulsion sources must be used efficiently
Solution Approach 1:
The system predicts the launch vehicle's future position based on current trajectory and wind conditions during ascent. By making trajectory corrections in advance during the powered ascent phase, the system ensures the vehicle will land at the desired location without requiring additional propellant during the descent phase.
Solution Approach 2:
The system replaces reliance on propulsion sources for trajectory correction with aerodynamic control surfaces. By using aerodynamic forces generated by control surfaces during ascent, the system achieves precise trajectory control without consuming additional propellant.
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
Enables significant cost reduction by allowing for multiple uses of launch vehicle components, reducing reconditioning requirements and infrastructure needs, while ensuring precise landing at specified sites with minimal propellant usage.
Implementation Method 1
employing wind maps and aerodynamic control surfaces to predict and adjust its trajectory for precise landing
Implementation Method 2
After MECO, gravity will eventually overcome the RLV's momentum and the RLV will then begin an un-powered descent because of gravity's downward force
Data Source
AI summary
Technology for predicting and correcting a trajectory is described. The technology can create a model to predict a position of the reusable launch vehicle at a time in the future; observe a wind condition during ascent of the reusable launch vehicle; store the observed wind condition in a wind map; predict during ascent a position and a terminal lateral velocity of the reusable launch vehicle at a terminal altitude; and correct a flight trajectory of the reusable launch vehicle based on the wind map.