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- ...lar systems of existing rocket engines can be found in the [[RocketEngines|rocket engines]] page. =First mass approximation for our rocket= ...29 KB (4,729 words) - 01:08, 29 December 2012
- =Rocket aerodynamics= ...tage air-to-orbit configuration, when aerodynamic effects are ignored. The rocket engine has to be larger to compensate the gravity. ...5 KB (815 words) - 00:16, 12 March 2013
- =Rocket Fuel tanks= ...nd one for the oxidizer, but it has not always been the case. The Redstone rocket for example used a single tank with an internal separation, as we can see b ...8 KB (1,251 words) - 01:13, 29 December 2012
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- (Single-Spent-to-orbit), like a rocket, and thus using the £1,000 for the full rocket or a Helium balloon. Everything that is recovered and reusable doesn't ...1 KB (194 words) - 00:06, 20 November 2010
- Wings will have to sustain the mass of the rocket at accelerations from -2g to +4g. They will have to support heavy curving, ===Rocket body=== ...5 KB (843 words) - 11:52, 23 October 2010
- ...lift-off operation. An additional disposable tank could be mounted on the rocket or on the aircraft, jettisoned after this burn. The engine may allow thrott * push-on boosters, either with propellers or miniature solid rocket engines, that would stay on the ground when the plane lifts-off. ...6 KB (982 words) - 19:23, 5 November 2012
- ...lable documentation on the numerous subjects linked the project, including rocket science, turbofans, aerodynamics, amateur rocketry and SSTO. ...m/ Opennautics] (European project) develops a hybrid engine for an amateur rocket, all open source. ...6 KB (923 words) - 14:04, 31 December 2013
- =Rocket aerodynamics= ...tage air-to-orbit configuration, when aerodynamic effects are ignored. The rocket engine has to be larger to compensate the gravity. ...5 KB (815 words) - 00:16, 12 March 2013
- The stoichiometric ratio is not the optimal ratio for rocket applications. The density and exhaust speeds are more important than maximu [[Category:Rocket|Propellants]] ...3 KB (416 words) - 01:12, 29 December 2012
- =Rocket Fuel tanks= ...nd one for the oxidizer, but it has not always been the case. The Redstone rocket for example used a single tank with an internal separation, as we can see b ...8 KB (1,251 words) - 01:13, 29 December 2012
- ...and comparing some of its subsystems. Our rocket will be based on regular rocket technology, as explained on this page. ...ges about the rocket and its flight can be found in the [[:Category:Rocket|Rocket category]]. ...13 KB (1,998 words) - 23:47, 19 January 2015
- [[Category:Rocket|LOX]] ...1 KB (170 words) - 22:49, 5 January 2013
- ...ing on which the research is based. A 3D rendering or drawing of the plane/rocket system would help visitors to understand the project at the first look to t ...1 KB (211 words) - 15:59, 27 May 2012
- ...g the other part. Other teams have for example been developing satellites, rocket engines, and so on. ...aunches (air-to-orbit), the body of the plane being the rocket itself. The rocket, or a part of it, as in any other orbital launch system, would achieve orbi ...22 KB (3,681 words) - 00:55, 6 November 2017
- ...lar systems of existing rocket engines can be found in the [[RocketEngines|rocket engines]] page. =First mass approximation for our rocket= ...29 KB (4,729 words) - 01:08, 29 December 2012
- ...appeared. For example, the [https://github.com/zortness/rocket-mega-shield Rocket Mega shield] features a fast GPS chip, XBee telemetry, MicroSD card, pressu ...eter could be used for thrust confirmation, collinear to the length of the rocket. It would also be a nice telemetry feature, and provide a feedback on the s ...12 KB (1,936 words) - 14:01, 26 September 2013
- ...aporization of cryogenic propellant on the ground and during the ascent to rocket ignition altitude. The latter could however be easily used to calculate the ...:First_approximations#Minimum_mass_evaluation|first approximation]] of the rocket mass program, the climb rates and flight profile (currently based on [https ...14 KB (2,254 words) - 21:16, 26 June 2013
- ...e|use]] this model to estimate the heat transfer to cryogenic tanks during rocket ascension to ignition altitude. Our implementation can be found here: [[Fil ...4 KB (672 words) - 04:03, 19 November 2012
