Tandem Supersonic-Hypersonic Launch Vehicle for Flexible Small Satellite Deployment
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Solution Overview
Problem
The high cost and limited flexibility of launching small satellites due to the constraints of traditional launch vehicles, which are often tied to specific launch sites and have rigid launch windows, making it expensive and inflexible to place small payloads into low earth orbit.
Innovation Solution
A launch vehicle comprising a first stage supersonic aircraft and a second stage hypersonic aircraft, where the hypersonic aircraft is in tandem with the supersonic aircraft, allowing for in-flight separation and enabling the launch of a third stage rocket at high altitude and speed, reducing the size and complexity of the rocket and increasing launch flexibility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If traditional multistage rockets are used to launch small satellites, then satellites can be placed into low earth orbit, but the cost per pound is at least three times higher than for large satellites and launch flexibility is severely limited
Solution Approach 1:
The launch vehicle is divided into multiple separable stages: a first stage aircraft that can operate independently and a second stage that couples to the first stage. This segmentation allows the first stage to be reused and enables flexible launch configurations, resolving the contradiction between launch flexibility and vehicle complexity.
Solution Approach 2:
The first stage aircraft is designed to serve multiple functions: it can operate as a standalone launch vehicle for smaller payloads and can couple with a second stage for larger payloads. This multi-functionality increases adaptability without proportionally increasing overall system complexity.
2Ease of operation
If launch vehicles are tied to specific launch sites like Kennedy Space Center or Vandenberg Air Force Base, then launches can be performed from established facilities, but scheduling delays occur due to availability and weather constraints
Solution Approach 1:
The first stage aircraft can transport the second stage to optimal launch locations and altitudes before the actual launch. This preliminary action allows launches to occur from more favorable locations and conditions, reducing scheduling delays caused by weather and site availability constraints.
3Productivity
If conventional rockets are used for small satellite launches, then payloads can be delivered to orbit, but the cost is very high and launch windows are constrained to tight timeframes
Solution Approach 1:
The launch vehicle transitions from a static, ground-based system to a dynamic, air-launched system. The first stage aircraft can move to different locations and altitudes, enabling flexible launch windows and improving overall launch efficiency by selecting optimal environmental conditions.
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 configuration reduces the cost and complexity of launching small payloads by minimizing throwaway parts, allowing for flexible launch locations and windows, and achieving higher efficiency through air-breathing propulsion and reduced drag, while enabling the launch of small satellites into low earth orbit.
Implementation Method 1
At least one of the aircraft may include air-breathing engines
Implementation Method 2
achieving higher efficiency through air-breathing propulsion and reduced drag
Implementation Method 3
The arms are connected to the forward portion and configured for pivoted movement between an extended position and a retracted position. In the retracted position, the arms form a blended aerodynamic surface with the forward portion
Data Source
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AI summary
A vehicle comprises a first stage supersonic aircraft, and a second stage hypersonic aircraft. The second stage aircraft is in tandem with the first stage aircraft.