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My 2nd SSTO. How can I give it more delta V when it reaches ...
A Single-Stage-To-Orbit (SSTO) vehicle's payload fraction, the ratio of payload mass to initial mass at liftoff, is a critical factor for its viability. While SSTOs aim for a high payload fraction, achieving a truly competitive one is challenging, often requiring advanced technologies. Typical payload fractions for SSTO vehicles range from 1% to 5%, with some advanced designs potentially reaching 10% or even higher.
Factors Influencing SSTO Payload Fraction:
Propellant Fraction:
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A large portion of an SSTO's mass is dedicated to propellant. High specific impulse (Isp) engines are crucial for reducing the required propellant mass, but even with high Isp, the propellant fraction can still be significant.
Inert Mass Fraction:
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This refers to the mass of the vehicle structure, engines, and other non-propellant components. Reducing the inert mass fraction is vital for increasing the payload fraction.
Engine Technology:
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Advanced engine technologies, like air-breathing engines, offer potential for higher Isp and reduced propellant needs, but they also come with their own set of engineering challenges.
Launch Altitude:
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Launching from a high altitude can significantly improve performance, reducing atmospheric drag and allowing for higher engine performance, which can translate to a higher payload fraction.
Vehicle Design:
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The overall design of the SSTO vehicle, including its aerodynamics and structure, plays a crucial role in maximizing payload fraction.
Examples and Considerations:
Reusable SSTOs:
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Reusable SSTOs face the challenge of balancing reusability with low inert mass. The need for robust structures to withstand multiple flights can make it difficult to achieve high payload fractions.
Expendable SSTOs:
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Expendable SSTOs, where the vehicle is not recovered, can achieve higher payload fractions due to lower structural requirements, but at the cost of reusability.
Air-Breathing Engines:
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Air-breathing engines, which utilize atmospheric oxygen, offer the potential for significant performance gains, but they are complex and require significant technological development.
Nuclear Propulsion:
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Nuclear thermal or nuclear electric propulsion systems offer the potential for very high Isp, which could drastically improve SSTO payload fractions, but they present their own set of challenges and safety concerns.
In essence, while achieving a high payload fraction for an SSTO vehicle is difficult, it is a key factor in determining its economic viability. Advanced technologies and careful design are necessary to push the payload fraction to levels that make SSTOs truly competitive with traditional multi-stage rockets
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