User:Isecspace/sandbox

Independent Space Exploration Commission
Company type	Private
Industry	Aerospace and robotics
Founded	Smyrna, Georgia, United States (2011)
Founder	Luke Pilcher
Headquarters	Smyrna, Georgia, United States
Area served	worldwide
Key people	Luke Pilcher; (Flight Director) & (CEO)

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The Independent Space Exploration Commission, known as ISEC, is an independent, privately funded spaceflight and exploration organization. The organization was created by Luke Pilcher. ISEC advertises itself as the "only" open-source spaceflight company/organization in existence. ISEC's current fleet of rockets include a line of composite airframe solid fueled rockets for short-range to suborbital launches known as the CAELUS or Research Launch Vehicle(RLV) launch family as well as its multi-stage/multi-configuration Payload Transport System which has a solid fueled core stage and a liquid fueled 2^nd stage and optional solid fueled boosters in a 2 or 4 booster setup.

CAELUS / Research Launch Vehicle[edit]

The CAELUS Research Launch vehicle family are solid fueled short-range to suborbital range rockets. The core airframe, not including the Payload Fairings/Nosecone has a outside diameter of 12" and a length of about 8FT for RLV-1A & RLV-1B and a length of about 9 1/2FT for RLV-1H. They are constructed of fiberglass and carbon-fiber wrapped phenolic. The payload fairings are constructed similarly but with the addition of Kevlar^TM to its internal structure. RLV-1H, H for Heavy, also supports 2 5.5" diameter, 36" long solid fueled boosters.

Propulsion[edit]

The propellant mixture in the rockets and boosters consist of Ammonium perchlorate (oxidizer, 69.6% by weight), Aluminum (fuel, 16%), Iron oxide (a Catalyst, 0.4%), Nitrocellulose (a binder that holds the mixture together and acting as secondary fuel, 14%). This propellant is commonly referred to as Ammonium Perchlorate Composite Propellant, or simply APCP. This mixture is very similar to that used on NASA's Space Shuttle Solid Rocket Boosters except no curing agent is used and a slightly higher binder content. The propellant has a 5-point finocyl bore all the way from the forward bulkhead to aft end. Thrust vectoring is provided through 4 linear actuators controlling pitch and roll on its 2 axis nozzle support. No thrust vectoring is used on RLV-1H boosters.

Electronics/Guidance[edit]

All electronics on-board are either located or centrally controlled in the forward electronics bay which contains the Flight Dynamics Computer(FDC).

Sub-systems include:

Thrust Vectoring micro-controller
Solid State Data Recorder
GPS System
Imaging Controller(Independent of FDC)
2.4Ghz & 433Mhz communication links
Range Safety System
Recovery System
Booster Separation Control(RLV-1H)
Sat-Com communication system(RLV-1H)

RLV-1A[edit]

Artist rendering of Payload Transport System(PTS)rocket