Add to ORKGOur goal is to design a 15,000 pound Small Launch Vehicle (SLV) which can carry a 250 kg payload into Low Earth Orbit (LEO). The objective is to develop a system to provide the SLV capability at a low cost. A preliminary analysis established for further refinement of the design. The SLV is a two state liquid oxygen/liquid hydrogen booster. Alternative fuels and engines are being investigated
This paper presents the conceptual design and performance analysis of a partially reusuable space l...
This paper presents the conceptual design and performance analysis of a partially reusuable space l...
A NASA study of the propulsion systems for possible low-risk replacements for the Space Shuttle is p...
Our goal IS to design a 15.!100 pound Small Launch Vehicle (SLV) which c~n carry a 2~0 kg payload in...
The Advanced Concepts Office at NASA's George C. Marshall Space Flight Center conducted a study of t...
Recent years have seen a drastic increase in the number of small satellites launched per year, as th...
The Advanced Concepts Office at NASA's George C. Marshall Space Flight Center conducted a study of t...
The small satellite industry faces a special challenge when it comes to the selection of a launch ve...
Low thrust chemical (hydrogen-oxygen) propulsion systems configured specifically for low acceleratio...
Low cost satellites require low cost access to space. Today, several companies are attempting to pro...
The space transportation system (STS) will be the principal means of launching USAF spacecraft begin...
The growing number of Small Launch Vehicles (SLV) will lower the cost of space access in the coming ...
Small rockets have the potential to play an important role in the changes that are now occurring in ...
Rocket Propulsion Engineering (RPe) is developing the first in a family of two low-cost, two stage, ...
This paper presents the conceptual design and performance analysis of a partially reusable space lau...
This paper presents the conceptual design and performance analysis of a partially reusuable space l...
This paper presents the conceptual design and performance analysis of a partially reusuable space l...
A NASA study of the propulsion systems for possible low-risk replacements for the Space Shuttle is p...
Our goal IS to design a 15.!100 pound Small Launch Vehicle (SLV) which c~n carry a 2~0 kg payload in...
The Advanced Concepts Office at NASA's George C. Marshall Space Flight Center conducted a study of t...
Recent years have seen a drastic increase in the number of small satellites launched per year, as th...
The Advanced Concepts Office at NASA's George C. Marshall Space Flight Center conducted a study of t...
The small satellite industry faces a special challenge when it comes to the selection of a launch ve...
Low thrust chemical (hydrogen-oxygen) propulsion systems configured specifically for low acceleratio...
Low cost satellites require low cost access to space. Today, several companies are attempting to pro...
The space transportation system (STS) will be the principal means of launching USAF spacecraft begin...
The growing number of Small Launch Vehicles (SLV) will lower the cost of space access in the coming ...
Small rockets have the potential to play an important role in the changes that are now occurring in ...
Rocket Propulsion Engineering (RPe) is developing the first in a family of two low-cost, two stage, ...
This paper presents the conceptual design and performance analysis of a partially reusable space lau...
This paper presents the conceptual design and performance analysis of a partially reusuable space l...
This paper presents the conceptual design and performance analysis of a partially reusuable space l...
A NASA study of the propulsion systems for possible low-risk replacements for the Space Shuttle is p...