Nose Cone Divert Control System for Rocket Propulsion
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Solution Overview
Problem
Conventional rocket propelled payloads require large and redundant booster attitude control systems (ACS) due to the proximity of solid rocket fuel to the center of mass, leading to increased weight and limited nozzle optimization, as well as inefficient propellant usage and aerodynamic constraints.
Innovation Solution
A rocket design with a divert control system housed entirely in the nose cone, utilizing a perforated nose cone nozzle extension assembly to eliminate booster ACS, allowing for high impulse liquid propellant and optimized nozzles with high slew angles, reducing weight and redundant hardware.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If solid rocket fuel is contained in the fuselage with propulsion elements arrayed along the sides of booster stages, then the booster attitude control system can be implemented, but the system becomes large, redundant, and heavy
Solution Approach 1:
The divert control system is extracted from the booster fuselage and relocated entirely into the nose cone. This separation removes the need for large, redundant booster ACS elements, directly reducing the weight of the moving object while maintaining attitude control capability through the compact nose cone housing.
Solution Approach 2:
The divert control system components (propulsion elements, nozzles, propellant) are merged and integrated within the nose cone structure. This consolidation eliminates redundant hardware between booster ACS and divert control, reducing overall system weight while achieving the desired attitude control function.
2Ease of operation
If propulsion elements are arrayed along the sides of booster stages, then attitude control is provided, but nozzle optimization is limited and slew angles are constrained
Solution Approach 1:
The divert control system transitions from a lateral array configuration along booster sides to a three-dimensional arrangement within the nose cone. This dimensional change allows nozzles to be positioned at optimized angles and locations, achieving high slew angles and superior nozzle optimization that were previously constrained by aerodynamic requirements of side-mounted elements.
3Force
If solid rocket fuel with low impulse capability is used, then propulsion is achieved, but a relatively large amount of fuel is needed increasing overall weight
Solution Approach 1:
The propellant type is changed from solid rocket fuel with low impulse capability to high impulse liquid propellant. This parameter change in propellant properties increases the impulse capability, allowing a relatively small amount of propellant to be used while still achieving the required propulsion force, thereby reducing overall system weight.
4Weight of moving object
If divert control system is housed in the nose cone, then redundant hardware is eliminated and weight is reduced, but space constraints increase
Solution Approach 1:
The divert control system components are nested within the nose cone structure, with propulsion elements, nozzles, and propellant storage arranged in a compact, space-efficient configuration. This nesting approach accommodates all necessary components within the limited nose cone volume while eliminating redundant hardware and reducing overall system weight.
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 configuration enhances divert control moment, reduces propellant loading, and eliminates redundant hardware, resulting in a lighter, more efficient, and less complex rocket system with improved aerodynamics and reduced program risks.
Implementation Method 1
high impulse liquid propellant and provides space for nozzles with high slew angles that are optimized with high expansion ratios
Data Source
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AI summary
A rocket is provided and includes booster stages at a rear of the nose cone, the booster stages being configured for propelling the nose cone in a propulsion direction and a divert control system housed entirely in the nose cone for controlling an orientation of the propulsion direction.