Ram Accelerator Launching Sensitive Payloads
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Solution Overview
Problem
Traditional aerospace launch technologies using multi-stage chemical rockets are costly, inefficient, and limited in payload capacity, with high capital and operating expenses, and are not compatible with sensitive payloads or human spaceflight due to excessive acceleration loads.
Innovation Solution
The use of a distributed gas injection system in a ram accelerator for launching payloads through the atmosphere, allowing for multiple projectiles to assemble in flight and providing a low-G load launch system that tailors acceleration profiles for sensitive payloads, using systems like ram accelerators, electromagnetic mass drivers, and distributed injection gas guns to achieve rapid and cost-effective access to suborbital and orbital space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If multi-stage chemical rockets are used for launch, then payloads can be delivered to space, but the payload fraction is very small (1-10% or smaller compared with takeoff gross weight)
Solution Approach 1:
The launch system is divided into multiple independent projectiles that can be launched separately and assembled in flight. Each projectile carries only the fuel and oxidizer needed for its specific mission segment, rather than one large rocket carrying all fuel from the start. This segmentation allows each component to be optimized independently and reduces the total mass that must be accelerated from the ground.
Solution Approach 2:
Fuel and oxidizer are pre-positioned in separate projectiles on the ground before launch. The first projectile delivers fuel to a predetermined location in space, where subsequent projectiles deliver oxidizer and additional fuel. This preliminary positioning of propellants eliminates the need to carry all fuel from the ground, dramatically improving payload fraction.
2Use of energy by moving object
If conventional rockets carry all fuel and oxidizer during entire flight, then the desired energy state (delta v) can be achieved, but the system is costly and inefficient
Solution Approach 1:
The propellant delivery system is segmented into multiple specialized projectiles: some carry only fuel, others carry only oxidizer, and others carry both. This allows each projectile to be optimized for its specific cargo and mission profile, improving overall energy efficiency while reducing the complexity of any single vehicle.
Solution Approach 2:
The system changes the parameters of propellant delivery by transitioning from carrying all propellant from ground level to delivering propellants at elevated locations in space. This parameter change reduces the gravitational potential energy penalty and improves the overall energy efficiency of the launch system.
3Ease of operation
If traditional rockets provide modest acceleration loads (3-10 G's), then fragile spacecraft and human spaceflight are compatible, but the launch is slow and performs costly gravity turns
Solution Approach 1:
The system uses dynamic assembly in flight where projectiles are launched at different times and velocities, then rendezvous and combine in space. This dynamic approach allows each projectile to be optimized for its specific acceleration profile, with some capable of higher G-loads for faster acceleration, while still protecting sensitive payloads through careful timing and separation strategies.
Solution Approach 2:
Payloads are prepared and positioned in projectiles that are launched with pre-calculated trajectories to achieve rendezvous at specific locations and times. This preliminary planning allows for optimized acceleration profiles that can be faster than traditional rockets while still protecting sensitive payloads through precise control.
4Speed
If gun launch systems are used to achieve high velocity, then access to space can be rapid, but acceleration loads are extremely high and incompatible with traditional space payloads
Solution Approach 1:
The launch system segments the acceleration process across multiple projectiles launched at different times. Instead of one projectile experiencing extreme G-loads from a single gun launch, the system uses coordinated launches where each projectile experiences manageable acceleration, and the combined effect achieves the desired high velocity while protecting sensitive payloads.
Solution Approach 2:
The system uses an intermediary approach by launching projectiles with moderate acceleration loads and then combining them in flight to achieve the equivalent of high-velocity launch. This intermediary strategy avoids the harmful extreme G-loads of direct gun launch while still achieving rapid access to space through coordinated multi-projectile deployment.
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 approach enables repetitive, low-cost launches with modest acceleration loads, suitable for sensitive payloads and human spaceflight, while reducing the need for extensive fuel and oxidizer carrying, thus improving payload capacity and reducing operational costs.
Implementation Method 1
a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere
Implementation Method 2
a ram accelerator to launch multiple payloads through the atmosphere
Implementation Method 3
multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile
Data Source
AI summary
This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.