Falcon Heavy: ArabSat-6A
Mission: ArabSat-6A
Vehicle: Falcon Heavy Block V
Launch Location: LC-39A
Viewing Location: Port Canaveral
Date: 4/11/2018
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Falcon Heavy: ArabSat-6A
Mission: ArabSat-6A
Vehicle: Falcon Heavy Block V
Launch Location: LC-39A
Viewing Location: Port Canaveral
Date: 4/11/2018
Delta IV: WGS-10
Mission: WGS-10
Vehicle: Delta IV
Launch Location: LC-37
Viewing Location: Port Canaveral
Date: 3/15/2019
SpaceX: DM-1
Mission: Dragon 2 Demo Mission 1
Vehicle: Falcon 9 Block V
Launch Location: LC-39
Viewing Location: Port Canaveral
Date: 3/2/2019
Falcon 9: PSN-6
Mission: PSN-6
Vehicle: Falcon 9 Block V
Launch Location: LC-40
Viewing Location: Port Canaveral
Date: 2/21/2019
Falcon 9: Telstar 18 V
Mission: Telstar 18V
Vehicle: Falcon 9 Block V
Launch Location: LC-40
Viewing Location: Port Canaveral
Date: 9/10/2018
SpaceX Falcon 9: Telstar 19V
Mission: Telstar 19V
Vehicle: Falcon 9 Block V
Launch Location: LC-40
Viewing Location: Melbourne Beach
Date: 7/22/2018
SpaceX Falcon 9 CRS 15
Mission: CRS-15
Vehicle: Falcon 9 ( Final Block 4 first stage, Block V upper stage)
Launch Location: LC-40
Viewing Location: Melbourne Beach
Date: 6/29/2018
SpaceX Falcon 9: SES-12
Mission: SES-12
Vehicle: Falcon 9 (Reused Block 4 first stage, Block V upper stage)
Launch Location: LC-40
Viewing Location: Port Canaveral
Date: 6/4/2018
SpaceX Falcon 9: Bangabandu-1
Mission: Bangabandu-1
Vehicle: Falcon 9 Block V
Launch Location: LC-39A
Viewing Location: Playalinda Beach
Date: 5/11/2018
For the full album, please visit: https://flic.kr/s/aHsmfD3Cu7
Mission: Falcon Heavy Demo
Vehicle: Falcon Heavy
Launch Location: LC-39A
Viewing Location: Port Canaveral
Date: 2/6/2018
Mission: AFSPC-11
Vehicle: Atlas V 551
Launch Location: Cape Canaveral
Viewing Location: Playalinda Beach
Date: 4/14/2018
Soyuz 2
The Soyuz 2 is a Russian built launch vehicle, a member of the Soyuz family of rockets, a derivative of the R-7, the oldest launch vehicle in history. The Soyuz family of rockets all have the same basic architecture: a core stage surrounded by four liquid fueled boosters, with a second stage mounted on top. The Soyuz 2 also has the option for a upper stage.
Boosters
The Soyuz 2 uses four boosters, each powered by a single RD-107A, each producing 839 kilo-Newtons of thrust per booster. The boosters ignite at liftoff, and continue to burn until booster separation about 118 seconds into flight. The booster separation on a Soyuz is unique. The booster is attached at two points, a forward and a rear attachment, like any booster. However, at separation, initially only the rear attachment separates. The booster begins to pivot around the forward attachment, at which point the forward attachment separates, at the same moment that the first stage opens a valve, releasing any remaining liquid oxidizer. This produces a thrust that pushes the booster away from the core stage. A view of this separation sequence can be seen here.
Core Stage
The Soyuz 2 core stage, known as a Blok-A, is powered by a single liquid fueled RD-108A, producing 792 kilo-Newtons of thrust at liftoff. The core star ignites at liftoff and burns until stage separation at 286 seconds into flight.
Second Stage
The Soyuz 2 second stage, known as the Blok-I, is powered by a single liquid fueled engine, producing between 294 and 298, depending on which Soyuz 2 variant is used. Using a hot staging technique, the second stage ignites moments before the core stage actually separates. The second stage continues to burn until the payload is in the intended orbit. In the case of an upper stage, the second stage would place the payload and upper stage into a preliminary orbit before separating from them.
Upper Stage
The Soyuz 2 can launch with an optional Fregat-MT upper stage. The Fregat-MT is powered by a liquid fueled single S5.92 engine, producing 19.85 kilo-Newtons of thrust. The Fregat-MT ignites after second stage separation, and burns until the payload is in the intended orbit.
Variants
Soyuz 2.1a
The Soyuz 2.1a features a second stage powered by a single liquid fueled RD-0110 engine, producing a total thrust of 298 kilo-Newtons of thrust.
Soyuz 2.1b
The Soyuz 2.1b features a second stage powered by a single liquid fueled RD-0124 engine, producing a total thrust of 294.3 kilo-Newtons of thrust.
Soyuz 2.1v
The 2.1v is a fairly interesting breed of Soyuz. Unlike every other Soyuz, the 2.1v lacks the four liquid fueled boosters. The 2.1v features an upgraded blok A first stage, powered by a single liquid fueled RD-193 engine. The 2.1v uses the same RD-0124 powered second stage as the 2.1b. For an optional upper stage, the 2.1v will use a Volga upper stage, instead of the typical Fregat-MT.
GPS IIF-12
Tomorrow’s launch of GPS IIF-12 is a routine launch of a Global Positioning System satellite for the United States Air Force, a mission fairly common on a United Launch Alliance rocket.
The Launch window for tomorrow’s launch is 1338-1357 GMT (8:38-8:57am EST). The mission will launch from SCL-41 in Cape Canaveral, Florida, aboard an 401 configuration Atlas V. (More on Atlas V)
You can watch the launch live on the Unites Launch Alliance website.
-By Michael Kalenty
Atlas V
The Atlas V is the newest member of the Atlas family of rockets, which began with the Atlas ICMB. The modern iteration of Atlas, the Atlas V is manufactured and operated by the American company United Launch Alliance, a joint venture between the launch vehicle divisions of Boeing and Lockheed Martin: Boeing Integrated Defense Systems, and Lockheed Martin Space Systems. The Atlas V consists of four main components, a first stage, optional solid fueled boosters, a second stage, and fairings.
First Stage
The Atlas V first stage, known as the Atlas Common Core Booster, is powered by a single liquid fueled RD-180 engine. At liftoff, the RD-180 produces 3,827 kilo-Newtons of thrust. The Common Core Booster ignites at liftoff and burns until BECO, Booster Engine Cut Off, at 253 seconds. Seconds after BECO, the Atlas CCB simultaneously separates from the second stage, and ignites a series of retro rockets, small rocket motors that act against the stages forward motion. The retro’s slow the spent first stage, pulling it away from the second stage, providing adequate clearance for second stage ignition.
Boosters
Some missions require the use of solid rocket boosters on the Atlas V. Depending on the mission, the Atlas V uses between 0-5 AJ-60A boosters. Each booster produces 1,688 kilo-Newtons of thrust, burning for 94 seconds before burnout and separation. In 2015, ULA announced the decision to replace the AJ-60As with GEM-63s on future Atlas V missions.
Second Stage
For the upper stage, the Atlas V uses Centaur, an upper stage originally developed in the 1960′s. Centaur was first flown atop the original Atlas ICBM, a configuration known as the Atlas-Centaur. An iteration of Centaur has been flown on every Atlas rocket since, as well as the now retired Titan IIIE and Titan IV. Centaur is powered by either one or two RL-10 engines, each producing 99.2 kilo-Newtons of thrust. Centaur ignites shortly after first stage separation, and burns until the payload is in the intended orbit. Centaur is capable of performing engine restarts, allowing Centaur to enter a coast phase before execute additional orbital maneuvers, such as Trans-Mars injection. Since it was introduced, some iteration of Centaur has successful sent payloads to every planet in our solar system.
Fairings
Like any fairing on any rocket, the Atlas V fairings are intended to protect the payload during initial accent.Depending on the mission, the Atlas will use either a 4 meter diameter fairing, or a 5 meter diameter fairing. Not only are the fairings different in size, but also how they are mounted to the rocket, and when the separate. The 4 meter fairings are mounted to the second stage, encapsulating the payload, and separate shortly after Centaur ignition. The 5 meter fairings mount to the first stage, encapsulating the both Centaur and payload, and separate shortly before BECO. In the case of the 5 meter fairing, the Atlas carries a component called the Forward Load Reactor. the FLR is a structural component that braces the Centaur against the fairings, providing structural support to the larger payload fairing. The FLR is jettisoned six seconds after fairing separation.
Variants
The variant of the Atlas V is denoted by a three digit number. The first digit denotes which size fairing is used, either a 4 or a 5. The second digit denotes the number of boosters used on the rocket. While the Atlas can accommodate anywhere from 0 to 5 boosters, the 400 series variants only use 0 to 3 boosters. The 500 series are the only variants to use 4 or 5 boosters. The last digit denotes whether the Centaur is a single or double engine variant. Therefor an Atlas V 401 is an Atlas with a 4 meter fairing, no boosters, and a dual engine Centaur, and a 552 would have a 5 meter fairing, 5 boosters, and a dual engine Centaur.
-By Michael Kalenty
Long March 3C
The Long March 3C is an orbital launch vehicle operated by the Chinese Government. The Long March 3C is a member of the Long March 3 family of launch vehicles. The 3C consists of four main components: Liquid Fueled Boosters, First Stage, Second Stage, and Third Stage.
Liquid Boosters
The Liquid Fueled boosters are each powered by a single YF-25 liquid engine, producing 740 kilo-Newtons of thrust each. They ignite at liftoff, and burn 127 seconds, at which point the boosters separate from the first stage.
First Stage
The First Stage is powered by four YF-21C liquid fueled engines, producing a total of 2961.6 kilo-Newtons of thrust. The first stage ignites at liftoff and burns for 145 seconds until first stage separation.
Second Stage
The Second Stage is powered by a single YF-24E liquid fueled main engines, with four YF-23C liquid fueled vernier engines for guidance. The main engine produces a total thrust of 742 kilo-Newtons of thrust, and the vernier engines produce a total thrust of 47.1 kilo-Newtons. The second stage starts up after first stage separation, and burns for 185 seconds until second stage separation.
Third Stage
The third stage is powered by a single YF-75 liquid fueled engine, producing 167 kilo-Newtons of thrust. The third stag ignites after second stage separation, and burns until the payload is placed in it’s desired orbit.
3C Extended Variant.
The Long March 3C has a single Extended variant. The Extended Variant has an extended first stage and boosters, allowing more fuel to be loaded, and allowing the stages and boosters to burn longer. The extended boosters burn for 140 seconds, 10 percent longer than the basic variant. The extended First Stage burns for 158 seconds, 8 percent longer than the basic variant.
-By Michael Kalenty
Remembering Tragedy
It’s that time of year again: January 28th, NASA’s official Day of Remembrance. Today we look back on all three of NASA’s worst tragedies: Apollo 1, Challenger, and Colombia. This Day of Remembrance is a particularly hard one, as it falls on the 30th anniversary of the Challenger disaster, which occurred on January 28th 1986. Today we remember all those who have given their lives in the pursuit of exploration.
-By Michael Kalenty
The Proton-M
The Proton-M is a heavy lift launch vehicle, and the newest member of the Proton family of rockets. The Proton rocket was originally designed as a Inter-Continental Ballistic Missile, but never entered service as an ICMB. The Proton was eventually replaced by the Proton 8K82K, later renamed the Proton-K. The Proton K launched notable payloads such as all the components of the Mir space station, as well as the Zarya (Russia: Sunrise) and Zvesta (Russian: Star) modules of the International Space Station. In March 2012, the Proton-K was retired and replaced with the Proton-M.
The Proton family of rockets launch from Baikonur Cosmodrome, in Kazakhstan.
The Proton has five major components: the First Stage, Second Stage, Third Stage, Payload Fairings, and an optional Fourth Stage.
First Stage
The First Stage is powered by six liquid fueled RD-253-14D14 engines, producing a total liftoff thrust of 10532 kilo-Newtons. The First Stage ignites at liftoff and burns until first stage separation at 108 seconds into flight. The design of the first stage is unique. Most rocket stages consist of a both an oxidizer tank and a fuel tank, staked on top of each other, giving the stage as a whole a roughly cylindrical shape. The design first stage of the Proton consists of a central oxidizer tank that runs the length of the stage, surrounded by six fuel tanks. This design is what gives the first stage a unique look that distinguishes it from the rest of the rocket.
Second Stage
The Second Stage is powered by four liquid fueled RD-0210 engines, producing a total thrust of 2399 kilo-Newtons. The second stage uses a “Hot Staging” technique, igniting the second stage engines before the first stage has separated. After first stage separation, the second stage continue firing until second stage separation, about 206 seconds after first stage separation, or 314 seconds into flight.
Third Stage
The Third Stage is powered by a single liquid fueled RD-0212 engine, producing a total thrust of 613.8 kilo-Newtons. The third stage ignites after second stage separation, and usually burns until the payload has reached the desired orbit. However, some missions require the use of a forth stage. If that is the case, the third stage will place the payload and the fourth stage into a slightly suborbital trajectory. The third stage then separates, and coasts along a suborbital trajectory until it crashes back to earth, landing in the ocean.
Payload Fairings
Like any set of payload fairings, the Proton’s payload fairings protect the payload from aerodynamic forces during the initial ascent. The payload fairings separate once the vehicle has reached a sufficient altitude,
Fourth Stage
While some missions can be accomplished with only three stages, others require a forth stage. If that is the case, there are three options for the for an upper stage. In all cases, the fourth stage will separate from the third stage and coast for a period, and then perform a burn to place the payload in a temporary orbit, known as a parking orbit. The forth stage will often perform multiple maneuvers until the payload has reached the desired orbit.
Forth Stage Options
Briz-M
The Briz-M is the most common forth stage on a Proton-M launch. The Briz-M is powered by a single liquid fueled S5.98M engine, producing a total thrust of 19.6 kilo-Newtons.
Blok DM-2
The Blok DM-2 is a less common forth stage. The Blok DM-2 is powered by a single liquid fueled RD-58M engine, producing a total thrust of 85 kilo-Newtons.
Blok DM-03
The Blok DM-03 is another uncommon forth stage. The Blok DM-03 is powered by a single liquid fueled RD-58MF, producing a total thrust of 49.3 kilo-Newtons. The Blok DM-03 has a serious case of bad luck. Of the three missions the Blok DM-03 has flown, only one has been successful. The first failure was due to the ground crews accidentally adding too much fuel to the stage; as a result, the sage was too heavy to reach orbit. The second failure was due a guidance failure in the first stage, causing the rocket to crash almost immediately after liftoff. Due to the failure occurring early in the flight, there are numerous videos of the failure: Real Speed | Slow Motion
-By Michael Kalenty