Ram Accelerator Launching Multiple Payloads
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Solution Overview
Problem
Traditional aerospace launch technologies using multi-stage chemical rockets are costly, inefficient, and limited in re-usability, with high G-load acceleration incompatible with sensitive payloads and human spaceflight, and offer only a small payload fraction to space.
Innovation Solution
The development of a distributed gas injection system and ram accelerator technology for rapid, low-cost access to suborbital and orbital space, allowing multiple payloads to assemble in flight and achieve customized acceleration profiles with lower G-loads, using systems like electromagnetic rail guns, coil guns, and vented or unvented light gas guns.
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 launched at different times. Each projectile carries a portion of the total payload, eliminating the need for a single massive rocket. This segmentation allows each individual launch to have a higher effective payload fraction while the system as a whole delivers the total required mass to space.
Solution Approach 2:
Multiple projectiles are launched in sequence rather than all at once. The first projectile is launched, then subsequent projectiles follow. This preliminary action approach allows each projectile to be optimized for its specific payload while collectively achieving the total mission requirement, improving overall payload fraction.
2Object-affected harmful factors
If conventional rockets are used, then payloads experience modest quasi-static acceleration loads (3-10 G's), but the launch cost is very high and re-usability is limited
Solution Approach 1:
The system uses multiple disposable projectiles rather than expensive reusable rockets. Each projectile is a simple, low-cost vehicle designed for single use, eliminating the high manufacturing and maintenance costs associated with reusable rocket systems while still delivering payloads to space.
Solution Approach 2:
The acceleration profile is modified by launching multiple smaller projectiles at different times rather than one large payload on a conventional rocket. This parameter change in the launch strategy reduces peak acceleration demands on any single vehicle while lowering overall system cost.
3Speed
If conventional rockets launch from surface with zero relative velocity, then payloads can be accelerated to orbital velocity, but the first stages depart slowly and perform gravity turns that are very costly from performance standpoint
Solution Approach 1:
The system provides preliminary action by launching projectiles with initial velocity from a moving platform (aircraft or vehicle) rather than from stationary ground. This preliminary velocity reduces the delta-v requirement for orbital insertion and eliminates the need for energy-intensive gravity turns in the first stage.
Solution Approach 2:
The launch approach transitions from vertical ground-based launch to horizontal or angled launch from a moving platform. This dimensional change in the launch trajectory allows the system to exploit the motion of the launching platform and avoid the inefficient gravity turn maneuver required by conventional vertical launches.
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
Enables repetitive, low-cost launches with modest acceleration loads, accommodating sensitive payloads and human spaceflight, while increasing payload fraction and reducing operational expenses through efficient energy use and re-usability of launch systems.
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
using systems like electromagnetic rail guns
Implementation Method 3
coil guns
Implementation Method 4
vented or unvented light gas guns
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.