Modular rocket

A modular rocket is a type of multistage rocket which features components that can be interchanged for specific mission requirements. Several such rockets use similar concepts such as unified modules to minimize expenses on manufacturing, transportation and for optimization of support infrastructure for flight preparations.

A Delta IV Heavy, featuring three Common Booster Cores; one used as the first stage and two as boosters

The National Launch System study (1991-1992) looked at future launchers in a modular (cluster) fashion. This concept has existed since the creation of NASA.

Examples

Saturn C
Main articles: Saturn I, Saturn C-2, Saturn C-3, Saturn C-4, Saturn V, and Saturn C-8

A government commission, the "Saturn Vehicle Evaluation Committee" (better known as the Silverstein Committee), assembled in 1959 to recommend specific directions that NASA could take with the existing Army rocket program (Jupiter, Redstone, Sergeant). NASA's Space Exploration Program Council (1959-1963) was tasked with developing the launch architecture for the new Saturn rocket series, called Saturn C. The Saturn C architecture consisted of five different stages (S-I, S-II, S-III, S-IV, and S-V/Centaur) that could be stacked vertically for specific rockets to meet various NASA payload and mission requirements.

This work led to development of the Saturn I, Saturn IB, and Saturn V rockets.

Atlas V
Main articles: Common Core Booster and Atlas V

The Atlas V expendable launch system uses the liquid fueled Common Core Booster as its first stage. In most configurations a single CCB is used with strap-on solid rocket boosters. A proposed configuration for heavier loads strapped together three CCBs for the first stage. The Common Core Booster utilizes the Russian made RD-180 burning RP-1 fuel with liquid oxygen producing a thrust of 3.8 MN. The liquid propellant tanks use an isogrid design for strength, replacing previous Atlas tank designs which were pressure stabilized.[1]

The length of the common core booster is 89 feet (27 m), and has a diameter of 12.5 feet (3.8 m).[2]

Delta IV
Main articles: Common Booster Core and Delta IV

The Delta IV launcher family uses the liquid fuel Common Booster Core as the first stage of the various rocket configurations. One or three modules can be used as the first stage. In most configurations a single CBC is used with or without strap-on SRBs. Three CBCs together form the first stage of the Heavy configuration. The CBC uses the Rocketdyne RS-68 engine and burns liquid hydrogen with liquid oxygen producing a thrust of 2.9 meganewtons (650,000 lbf).

Angara
Main article: Angara (rocket family)

The Universal Rocket Module (URM) is the modular liquid fueled first stage of the Angara expendable launch system. Depending on the configuration, the first stage can consist of 1, 3, 5 or 8 URMs. Each URM uses a Russian-made RD-191 engine burning RP-1 fuel with liquid oxygen producing a thrust of 1.92 MN.[3]

Falcon Heavy
Main article: Falcon Heavy

The Falcon Heavy launch vehicle consists of a strengthened Falcon 9 Block 5 center core with two regular Falcon 9 Block 5 core stages acting as liquid-fuel strap-on boosters. Each core is powered by nine Merlin 1D engines burning rocket-grade kerosene fuel with liquid oxygen producing almost 7.7 meganewtons (1,700,000 lbf) of thrust, and all three cores together producing over 22MN of thrust. A first design of the Falcon Heavy included a unique propellant crossfeed capability, where fuel and oxidizer to power most of the engines on the center core would be fed from the two side cores, up until the side cores would be near empty and ready for the first separation event.[4] However, due to its extreme complexity this feature was cancelled in 2015 leaving each of the three cores to burn its own fuel. Later evaluations revealed that the propellant needed for each side booster to land (reuse) are already close to the margins so there is really no advantage to crossfeed.

Like the single stick Falcon 9, each Falcon Heavy booster core is reusable.[5] The Falcon Heavy Test Flight demonstrated the two side boosters landing simultaneously near their launch site, while the central booster attempted a landing on SpaceX's Autonomous spaceport drone ship, which resulted in a hard landing near the ship. During the second mission all three boosters landed softly.[6] A Falcon Heavy launch that succeeds in recovering all three core boosters has the same material expenditure as the Falcon 9, i.e. the upper stage and potentially the payload fairing. As such, the difference in cost between a Falcon 9 and a Falcon Heavy launch is limited, mainly to the extra fuel and refurbishing three as opposed to one booster core.

See also

References
  1. Launch Vehicles Archived 2011-11-11 at the Wayback Machine, Lockheed Martin
  2. Lockheed Martin Names New Rocket Atlas V Archived 2010-02-23 at the Wayback Machine, Lockheed Martin
  3. Rocket family «Angara», Khrunichev State Research and Production Space Center
  4. Strickland, John K., Jr. (September 2011). "The SpaceX Falcon Heavy Booster". National Space Society. Archived from the original on 2015-07-08. Retrieved 2012-11-24.
  5. Simberg, Rand (2012-02-08). "Elon Musk on SpaceX's Reusable Rocket Plans". Popular Mechanics. Retrieved 2012-02-07.
  6. "Live coverage: Falcon Heavy launches, three boosters land safely". Spaceflight Now. April 11, 2019.
  7. Universal Rocket series was a Soviet project of unified rocket systems (military and civilian); UR-700 project was supposed to use liquid fuel boosters with similar design to its first stage.
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.