Orbital Launch Trajectory via Gravity Turn Descent
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Solution Overview
Problem
Current orbital launch methods require high propellant consumption and strain on rocket engines, limiting the ability to achieve stable orbits with specific inclination angles and restricting launch site flexibility, as they necessitate large thrust-to-weight ratios and specific launch azimuths.
Innovation Solution
The method involves converting inverse square law gravitational potential energy into kinetic energy through a rocket-assisted descent from a higher radius to a desired orbital radius, allowing for any orbital inclination and reducing propellant demand, enabling smaller, less stressed rocket engines and flexible launch site usage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional launch methods with high thrust-to-weight ratio are used, then stable orbit can be achieved, but propellant consumption is high and rocket engine strain is excessive
Solution Approach 1:
The patent inverts the conventional launch approach by first launching the payload vertically to a high altitude (apogee) and then using a gravity turn to convert gravitational potential energy into kinetic energy during the descent phase. This reverse sequence allows the payload to achieve orbital velocity through gravitational acceleration rather than continuous rocket thrust, significantly reducing propellant consumption while maintaining reliable orbit insertion
Solution Approach 2:
The patent performs preliminary vertical launch to reach a high apogee altitude where the payload will later perform the gravity turn maneuver. This preliminary action positions the payload optimally to exploit gravitational potential energy conversion, preparing the system in advance for the energy-efficient orbital insertion phase
2Reliability
If conventional launch methods with specific launch azimuths are used, then stable orbit can be achieved, but launch site flexibility is restricted
Solution Approach 1:
The patent employs a dynamic gravity turn maneuver that can be executed from any launch azimuth after reaching apogee. Unlike conventional methods that require precise initial azimuth alignment, this approach allows the payload to dynamically adjust its trajectory during the descent phase, enabling launches from any site with any desired inclination angle while maintaining reliable orbit achievement
3Speed
If high thrust-to-weight ratio rocket engines are used, then orbital velocity can be achieved, but rocket engine lifespan is reduced
Solution Approach 1:
The patent extracts the orbital velocity achievement function from the rocket engine by using gravitational potential energy conversion. The rocket engine only needs to provide initial thrust to reach apogee, while the gravity turn maneuver extracts kinetic energy from the gravitational field to achieve the required orbital velocity, thereby preserving rocket engine lifespan
Solution Approach 2:
The patent employs the Earth's gravitational field to accelerate the payload to orbital velocity during the gravity turn descent. The gravitational field essentially serves itself by converting its own potential energy into kinetic energy, eliminating the need for continuous rocket engine operation and reducing engine wear and lifespan limitations
Data Source
AI summary
A method is provided for efficient orbital launch trajectories. A payload (e.g., satellite) is launched as high as a first radius with respect to the center of the Earth. The method decreases the payload altitude in response to a gravitational pull of the Earth, and ultimately the payload attains a stable orbit around the Earth at a second radius with respect to the center of the Earth. If the first radius is twice the second radius, the payload acquires a gravitational first potential energy at the first radius, and in the stable orbit the payload has a second (potential and kinetic) energy equal to the gravitational first potential energy, with the second kinetic energy being equal to the energy required to maintain a stable orbital velocity. Advantageously, the stable orbit can potentially be at any orbital inclination angle in the range between 0 and 360 degrees.