Center-Mounted Rocket Engine for Horizontal Launch Aerospace Vehicle
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Solution Overview
Problem
Current space launch vehicles require extensive infrastructure and are not cost-effective due to their vertical launch and expendable nature, limiting payload capacity and reusability, especially for horizontal takeoff and landing designs which face challenges with wing loading and reentry heating.
Innovation Solution
A twin-hull aerospace vehicle with a center-mounted rocket engine that can pivot for horizontal launch and vertical thrust, allowing for horizontal takeoff and landing, and featuring a catamaran design for stability and hydrodynamic lift, enabling efficient payload delivery to orbit and return, with a piggyback second stage and air-augmented rocket engines for thrust augmentation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If vertical launch is used, then thrust greater than gross weight can be achieved, but extensive infrastructure and high costs are required
Solution Approach 1:
The patent inverts the conventional vertical launch approach by implementing horizontal launch capability. The vehicle can accelerate horizontally along a track or runway and then transition to vertical flight, eliminating the need for extensive launch pad infrastructure, gantries, and support systems while maintaining the ability to generate sufficient thrust for orbital insertion.
Solution Approach 2:
The launch system employs dynamic transition from horizontal to vertical flight. The vehicle accelerates horizontally to gain velocity, then performs a gravity turn or powered maneuver to transition to vertical ascent. This dynamic approach allows flexible launch profiles and reduces infrastructure requirements compared to fixed vertical launch systems.
2Device complexity
If horizontal takeoff with aerodynamic lift is used, then infrastructure needs are reduced, but payload capacity decreases due to large wing area requirements
Solution Approach 1:
The vehicle uses dynamic wing deployment where wings are extended during horizontal acceleration and transition phases, then retracted or folded during vertical ascent and orbital insertion. This allows the vehicle to benefit from aerodynamic lift during ground operations without the permanent weight penalty of large fixed wings, thereby preserving payload capacity.
Solution Approach 2:
The propulsion and lift systems are segmented into separate functional phases. Rocket engines provide thrust during vertical ascent while wings provide aerodynamic lift during horizontal acceleration and landing. This segmentation allows optimization of each system for its specific phase without compromising overall payload capacity.
3Ease of manufacture
If expendable booster sections are used, then simple design is achieved, but cost per flight increases
Solution Approach 1:
The patent implements recoverable first stage boosters that return to the launch site or designated recovery areas after stage separation. The boosters are retrieved, refurbished, and reused for subsequent missions, dramatically reducing the cost per flight while maintaining design simplicity through modular architecture and standardized recovery procedures.
4Adaptability or versatility
If sea launch is used, then geographical location flexibility is improved, but infrastructure investment and recovery complexity increase
Solution Approach 1:
Instead of launching vertically from sea platforms with all associated infrastructure, the patent enables horizontal launch from conventional runways or tracks near coastal areas, then transition to vertical flight. This approach provides geographical flexibility without requiring specialized sea launch infrastructure, floating platforms, or complex water recovery systems.
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 design reduces infrastructure needs, enhances payload capacity, and allows for reusable systems with controlled landing and reentry, minimizing costs and environmental impact while enabling larger payloads and flexible launch locations.
Implementation Method 1
redirect exhaust gases to provide thrust vector control
Implementation Method 2
intake of air to augment thrust
Implementation Method 3
twin-hull aerospace vehicle... featuring a catamaran design for stability and hydrodynamic lift
Data Source
Figure 1A
Figure 1B~1C
Figure 2~3
AI summary
An aerospace vehicle that permits horizontal launch and subsequent orbital deployment of a second stage. The vehicle can be returned to Earth for subsequent re-use. Both land-based and water-based launch is disclosed. A rocket propulsion engine is located at the center of gravity of the vehicle and rotates to provide vertical and horizontal thrust.