Editing Canadian Arrow (section)

==Design==
[[File:Canadian arrow.jpg|thumb|A rendering of a Canadian Arrow vehicle in flight]]
The Canadian Arrow was a 16.5 m tall two-stage rocket, where the second stage was a three-person space capsule. The Canadian Arrow team's somewhat conservative approach was to base the design of their rocket engine and aerodynamics on the well proven [[V-2 rocket|V-2]] design from [[World War II]].

===First stage===
The rocket's first stage was 10.2 m long and 1.7 m in diameter. It was propelled by a single liquid fuel rocket engine. It produced a thrust of 254 [[kilonewton|kN]]. Graphite jet vanes were used for stabilisation before the rocket has reached a velocity high enough for the four fins to be effective. About one minute after ignition, the fuel was depleted and the engine shut off.{{Citation needed|date=February 2011}}

===Second stage===
The rocket's second stage was 6 m long and 1.7 m in diameter at the base. It carried three astronauts and was propelled by four [[JATO]]-type solid rocket engines. These were ignited immediately after stage separation, and carried the capsule to an altitude of ~112&nbsp;km. Cold gas jets were planned to be used for attitude control.{{Citation needed|date=February 2011}}

===Crew Cabin Escape System===
The design proposed four solid rocket engines in the second stage that could be fired at any time, even when the rocket stands on its launch pad. This constituted an escape system, which could, in a case of an emergency, quickly separate the second stage from the rocket and propel it to an altitude of 1.5&nbsp;km, where its parachutes could be deployed.{{Citation needed|date=February 2011}}

===Rocket engine===
The rocket engine was to use alcohol and liquid oxygen as propellants, and produces a maximum thrust of 254 [[Kilonewton|kN]], and burns for 55s. It was constructed of low carbon steel, with propellant injectors made out of [[brass]].{{Citation needed|date=March 2016}}

===Flight profile===
The Canadian Arrow rocket was to launch vertically from the ground. Initial thrust was ~75.5&nbsp;kN, but the rocket quickly reached maximum thrust. After 55s, the propellant was depleted and stage separation occurred. The solid fuel rockets in the second stage were ignited and boosted it up to an altitude of ~112&nbsp;km, where the crew and passengers would have experienced a few minutes of "zero-G", or weightlessness.

After stage separation the first stage reached an apogee of over 80&nbsp;km before descent begun. Four parachutes slow the Canadian Arrow's first stage down before splashdown occurred at a speed of ~9&nbsp;m/s, after which recovery of the spacecraft could take place.

During descent, the crew cabin (the second stage) was planned to use a [[ballute]] to reduce its speed. When its velocity became subsonic, the second stage's ballute was to be released and pull out the three parachutes before splashdown.{{Citation needed|date=February 2011}}

===Testing===

*Summer, 2002: Single burner cup engine test.{{Citation needed|date=February 2011}}
*October 5, 2002: The rocket test stand complete.{{Citation needed|date=February 2011}}
*November 7, 2003: First engine tests conducted.{{Citation needed|date=February 2011}}
*August 14, 2004: Canadian Arrow carried out a successful drop test of the crew cabin, to test the parachutes and recovery routines.{{Citation needed|date=February 2011}}