Propulsion Stage Center of Mass Control via Movable Current Storage
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Solution Overview
Problem
Existing launch rockets face challenges in controlling the first propulsion stage during its return fall to Earth, which limits the ability to achieve a controlled and reusable landing.
Innovation Solution
The propulsion stage is equipped with a rocket body having a longitudinal axis, at least one recoil propulsion unit acting predominantly parallel to the longitudinal axis, and multiple rotor assemblies driven by electric rotor drives. The current storage device, which can be accumulators, capacitors, or fuel cells, is actively displaceable within the propulsion stage, allowing it to shift the center of mass and change the flight attitude during descent.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If additional control nozzles and fan motors are added to enable controlled landing, then landing control capability is improved, but device complexity and mass increase
Solution Approach 1:
The current storage device serves dual purposes: it provides electrical energy to the rotor drives for generating lift during landing, and simultaneously functions as a movable mass for controlling flight attitude during re-entry and descent. This eliminates the need for separate control nozzles and reduces overall system complexity.
Solution Approach 2:
The patent replaces traditional aerodynamic control systems (steering nozzles, control surfaces) with a mass redistribution system. By moving the current storage device to different positions within the propulsion stage, the center of mass is shifted to control flight attitude, substituting mechanical/aerodynamic control with inertial control.
2Ease of operation
If traditional aerodynamic control elements are used for steering during descent, then steering capability is improved, but mass and device complexity increase
Solution Approach 1:
The patent replaces aerodynamic control elements (steering nozzles, control surfaces) with a pure mass redistribution system. The movable current storage device shifts the center of mass to achieve attitude control during re-entry and descent, eliminating the need for additional control components and reducing overall mass.
Solution Approach 2:
The current storage device, which must be present anyway to power the rotor drives, is made to serve an additional function as a control mass. This self-service approach means the same component provides both energy storage and attitude control, eliminating the need for separate control systems.
3Ease of operation
If fuel reserves are carried for controlled landing, then landing control capability is improved, but mass to be transported increases
Solution Approach 1:
The current storage device is made multi-functional, serving both as an energy source for the rotor drives and as a movable mass for attitude control. This eliminates the need for separate fuel reserves dedicated to control operations, as the electrical energy stored in the current storage device powers the rotor drives that provide both lift and control.
Solution Approach 2:
The patent replaces chemical energy-based control (fuel consumption for thrust vectoring) with electrical energy-based control (rotor drives powered by current storage device). This substitution allows for more efficient use of mass, as electrical energy storage is more mass-efficient than carrying additional fuel reserves for control purposes.
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 solution enables the propulsion stage to be steered during re-entry and descent without the need for steering nozzles or aerodynamic elements, allowing for controlled flight paths and potentially reusable landing capabilities.
Implementation Method 1
the at least one current storage device can be moved for the purpose of displacement in a direction which lies in a plane right angled to the longitudinal axis or which has a dominant directional component which extends in the radial direction right angled to the longitudinal axis
Data Source
AI summary
A propulsion stage, in particular a reusable propulsion stage, comprising: a rocket body having a longitudinal axis; at least one recoil propulsion unit acting substantially parallel to the longitudinal axis; a plurality of rotor assemblies, each drivable by an electric rotor drive including at least one electric motor electrically connected to at least one current storage device configured to supply electrical energy to the at least one electric motor, wherein the at least one current storage device is displaceable within the propulsion stage in a direction located in a plane oriented at a right angle relative to the longitudinal axis or which has a dominant directional component which extends in the radial direction at a right angle relative to the longitudinal axis.