Wikipedia:WikiProject Rocketry
Title
WikiProject Launch vehicles
Scope
This WikiProject aims primarily to provide information on the information that should be included in articles about rockets, missiles and other launch vehicles, with an emphasis on space launch vehicles. Although it is impossible to have complete standardisation across ever single type of rocket that had ever been designed, this project aims to make sure that a user of Wikipedia can guarantee to see roughly the same thing across the board.
Parentage
The parent of this WikiProject is the WikiProject Transport.
Descendant Wikiprojects
No descendant WikiProjects have been defined.
Similar Wikiprojects
The similar WikiProjects are WikiProject Space Missions, WikiProject Ships and WikiProject Aircraft.
Participants
Article title
Articles should be titled like Saturn V (rocket).
Structure
There are basically three types of rockets and missiles that would probably be written about in wikipedia. They are: Intermediate Range Ballistic Missiles (IRBM), Intercontinental Ballistic Missiles (ICBM) and space launch vehicles.
IRBM
ICBM
| Minuteman I | ||
|---|---|---|
| Saturn V launch Minuteman I missile | ||
| Stages | ||
| 1 | Engines | 1 * Thiokol M55A1 |
| Thrust | 901 kN | |
| ISP | sec | |
| Burn time | ~ sec | |
| Fuels | PBAA polymer binder AP oxidant aluminum powder | |
| 2 | Engines | Aerojet General M56 |
| Thrust | 267 kN | |
| Burn time | ~ sec | |
| Fuels | PU/AP | |
| 3 | Engines | Hercules M57 |
| Thrust | 156 kN | |
| Burn time | ~ sec | |
| Fuels | Nc/Ng/AP | |
| Payload | A: 1.2 MT W59 B: 2 MT W56 | |
| Deployment | ||
| First Operational | December 1962 | |
| Launches | 380 | |
| Retired | September 27, 1974 | |
| Specifications | ||
| Maximum Speed | 6700 m/s | |
| Maximum Range | 10,100 km | |
| Maximum Alitude | 1,100 km | |
| Accuracy | 2.4 km | |
Space Launchers
At the moment the basic table looks like this:
| Saturn V | ||
|---|---|---|
| Saturn V launch Saturn V launching Apollo 15. | ||
| Stages | ||
| 1 - S-IC | Engines | |
| Thrust | N | |
| ISP | sec | |
| Burn time | ~ sec | |
| Fuels | RP-1/LOX | |
| 2 - S-II | Engines | |
| Thrust | N | |
| Burn time | ~ sec | |
| Fuels | LH2/LOX | |
| 3 - S-IVB | Engines | |
| Thrust | N | |
| Burn time | ~ sec | |
| Fuels | LH2/LOX | |
| Three stage version | ||
| Payload to LEO | 118,000 kg | |
| Payload to TLI | 47,000 kg | |
This is the basic table for the Saturn V launch vehicle. Each stage is named as well as the number and types of main engines on each stage. It also has the average thrust, burn time and fuel (which could be linked if an article exists).