Reusable Launch Vehicle Adaptive Thrust Structure
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Solution Overview
Problem
Current space launch vehicles are not fully reusable, have limited mission capabilities, and require specific stages for different missions, leading to inefficiencies and increased costs.
Innovation Solution
The implementation of an adaptive thrust structure and a reusable, reconfigurable launch vehicle system that includes a fully reusable second stage and a modular transporter capable of carrying passengers, cargo, and satellites, with the ability to change configurations for different missions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If current space launch vehicles use solid rocket boosters and external fuel tanks that are discarded on every flight, then the vehicle can be simpler to manufacture, but the operational cost increases and reusability decreases
Solution Approach 1:
The launch vehicle is divided into separable modules including reusable first and second stages with a discarded payload fairing. The first stage includes its own propulsion system and can operate independently, while the second stage couples to it only when needed. This segmentation allows the reusable portions to be recovered and reused while simplifying the overall system architecture.
Solution Approach 2:
The first stage is designed with universal functionality to perform multiple operations: it can provide thrust during launch, perform orbital insertion maneuvers, conduct de-orbiting operations, and serve as a transport vehicle. The reusable first stage can be coupled with different second stages or payload fairings depending on mission requirements, making it a multi-purpose platform that reduces operational costs through repeated use.
2Reliability
If current space launch vehicles have reusable portions that require heat shield refurbishment after each flight, then the vehicle can be reused, but the operational complexity and cost increase
Solution Approach 1:
The vehicle separates the heat shield requirements to only the second stage and payload fairing that experience atmospheric re-entry, while the first stage uses a different re-entry method. This segmentation allows the majority of the vehicle (first stage) to be reused without heat shield refurbishment, reducing operational complexity.
Solution Approach 2:
Instead of having the entire vehicle or the main propulsion stage experience atmospheric re-entry with heat shield requirements, the invention inverts the approach by having the first stage perform de-orbiting and re-entry in a controlled manner that avoids the need for traditional heat shields, while only the payload fairing and second stage require thermal protection.
3Ease of manufacture
If current space launch vehicles are limited in the types of missions they can perform, then the vehicle design can be simpler, but the adaptability and versatility decrease
Solution Approach 1:
The reusable first stage is designed as a universal platform capable of performing multiple mission types including satellite deployment, crewed missions, cargo transport, and space station resupply. The modular coupling interface allows different second stages and payload fairings to be attached to the same first stage, providing versatility without requiring complex redesign for each mission type.
Solution Approach 2:
The vehicle configuration is dynamic and can be changed between missions by coupling and decoupling different second stages and payload fairings to the reusable first stage. This dynamic reconfigurability allows the same first stage to adapt to different mission requirements, from single-payload deployments to multi-satellite constellations and crewed missions.
4Adaptability or versatility
If current launch vehicles can be used for different missions, then the adaptability increases, but a stage must be specifically built for each particular mission
Solution Approach 1:
The vehicle is segmented into a reusable first stage with universal capabilities and mission-specific second stages or payload fairings. This segmentation allows the complex mission-specific requirements to be isolated to separate modules that can be independently designed and attached to the standardized first stage interface, reducing overall system complexity.
Solution Approach 2:
The reusable first stage acts as an intermediary platform with standardized coupling interfaces that mediate between the launch infrastructure and various mission-specific payloads. This intermediary design allows different missions to be accommodated through standardized interfaces rather than requiring custom integration for each mission type.
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 a cost-effective, efficient, and flexible space transportation system that can perform a variety of missions without the need for extensive refurbishment, thereby reducing operational costs and increasing adaptability.
Implementation Method 1
a fuel supply and an oxidizer supply fluidically coupled to the first engine assembly
Implementation Method 2
a fuel supply and an oxidizer supply fluidically coupled to the second engine assembly
Data Source
AI summary
Implementations of the disclosed subject matter may provide an adaptive thrust structure for a space launch vehicle that may include an interface block that is fluidically coupled to a fuel supply, a fuel manifold, an oxidizer supply, and an oxidizer manifold. A first adapter plate may be coupled to a first engine assembly. First adapter lines may be fluidically coupled to the first engine assembly and the interface block, via the first adapter plate. A second engine assembly, second adapter lines, and a second adapter plate are capable of replacing the first engine assembly, first adapter lines, and first adapter plate. Implementations of the disclosed subject matter may provide a reusable and reconfigurable launch vehicle that may include a reusable second stage, and a reusable and reconfigurable transporter having a plurality of zones that are configurable to transport cargo, one or more passengers, and/or one or more satellites.