CRC is developing the R-series orbital launch architecture and E-1 liquid-oxygen/methane gas-generator propulsion. Its current website presents reusable R-2 medium lift with nine E-1 engines and a target above 12,500 kilograms to sun-synchronous orbit. The E-1 thrust label is 725 kN+, without rating conditions or a completed test result.
The September development plan centres on propulsion components before the assembled engine. Aerospace America reports a planned gas-generator hot-fire in December 2026, a complete engine with its turbopump around 2028, and launch around 2032. It gives an R-2 objective of up to 15,000 kilograms to low Earth orbit. Both payload figures are design targets with different orbit bases.
Earlier material described a one-engine R-1 pathfinder and shared propulsion, structures, avionics and ground systems. The current medium-lift emphasis differs from earlier seven-engine R-2 descriptions, while DND agreement CO5-023 remains publicly scoped to R1. A common dated baseline is needed to connect configuration, test evidence and funded milestones.
Technical detail
Core features
Current company-stated R-2 configuration with nine E-1 engines
Liquid-oxygen/methane gas-generator propulsion
E-1 thrust label of 725 kN+, with rating conditions unspecified
Reusable medium-lift target above 12,500 kg to sun-synchronous orbit
Separately reported September target of up to 15,000 kg to low Earth orbit
Earlier R-series architecture with R-1 pathfinder and shared propulsion, structures, avionics and ground systems
Orbital launch vehicles
Methalox propulsion
Responsive launch
Reusable launch vehicle
Use & integration
Recorded applications
Sovereign and responsive orbital launch
Defence, civil and commercial satellite deployment
These describe the reviewed application scope, not confirmed deployments, released requirements or procurement eligibility.
Evidence of maturity
Pre-flight development. September 21 reporting describes a planned December 2026 gas-generator hot-fire, full-engine testing around 2028 and launch around 2032, updating an earlier late-2027 engine forecast. No completed hot-fire or orbital flight is established.
Commercial availability
Development discussions through CRC’s public contact route. Vehicle performance and launch timing remain targets; no reviewed source establishes an operational service, manifested customer payload or accepted payload flight.
Integration and verification
Readiness
A technology readiness level is not established by the reviewed public sources.
Reviewed connections
No reviewed Mission area or released Defence need connection is currently published.
Original sources 7 linked records
These records support this capability and its published Mission area and Defence need connections. A source count is not a count of independent confirmations.
Canada Rocket Company currently presents R-series responsive launch vehicles and E-1 methalox engine through its official public capability surface.
Supports: Capability · technical tags
Derived taxonomy tag: reusable launch vehicle.
Supports: Capability · core features
The official site describes R-1 as mobile and states an intended call-up time under 96 hours.
Supports: Capability · technology readiness level
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · commercial availability
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · defence applications
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · core features
The official site describes R-2 as a medium-lift concept powered by seven E-1 engines.
Supports: Capability · technical tags
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · maturity
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · capability type
Derived capability type: development-stage orbital launch vehicles and methalox propulsion.
Supports: Capability · defence applications
Sovereign and responsive orbital launch
Supports: Capability · technical tags
Derived taxonomy tag: responsive launch.
Supports: Capability · capability type
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · defence applications
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · technical tags
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · technical tags
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · core features
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · summary
The company describes an R-1 technical pathfinder using one E-1 engine and an R-2 reusable medium-lift concept using seven engines. Payload, response-time, reuse, and schedule figures are engineering targets rather than flight-proven performance.
Supports: Capability · technical tags
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · core features
Mobile light-lift and reusable medium-lift vehicle concepts
Supports: Capability · technical tags
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · technicaldomainslugs
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · core features
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · summary
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · technical tags
Derived taxonomy tag: methalox propulsion.
Supports: Capability · technical tags
True North Map applies the launch-vehicles tag from Canada Rocket Company's documented capability functions.
Supports: Capability · technical tags
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · technical tags
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · technology readiness level
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · capability type
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · capability type
Source-bounded strategic technology capability
Supports: Capability · technicaldomainslugs
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · name
The official site names the R-series launch vehicles and E-1 methalox engine as CRC's core launch architecture.
Supports: Capability · summary
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · technical tags
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · core features
The official site says the R-series shares propulsion, structures, avionics and ground-system architecture.
Supports: Capability · defence applications
Defence, civil, and commercial satellite deployment
Supports: Capability · technical tags
Derived taxonomy tag: orbital launch vehicles.
Supports: Capability · core features
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · technicaldomainslugs
True North Map maps R-series responsive launch vehicles and E-1 methalox engine to space and earth observation from its documented technology functions.
Supports: Capability · core features
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · name
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · core features
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · core features
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · defence applications
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · name
Current company website describes R-2 with nine E-1 methalox gas-generator engines, 725 kN+ E-1 thrust and a target above 12,500 kg to sun-synchronous orbit. These are company design claims, not demonstrated performance.
Supports: Capability · name
R-series responsive launch vehicles and E-1 methalox engine
Supports: Capability · core features
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · defence applications
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · core features
The official site describes R-1 as a technical pathfinder powered by one E-1 engine.
Supports: Capability · core features
The current CRC website presents R-2 as reusable medium-lift with nine E-1 engines, methane/liquid-oxygen propellant and gas-generator cycle, targeting more than 12,500 kg to sun-synchronous orbit. The E-1 thrust label says 725 kN+ without specifying test conditions or an explicit per-engine qualifier. Do not multiply it by nine. The page gives 38 Racine Road, Etobicoke as headquarters.
Supports: Capability · defence applications
CRC presents the R-series for defence, civil and commercial satellite deployment.
Supports: Capability · technical tags
True North Map applies the methalox-propulsion tag from Canada Rocket Company's documented capability functions.
Aerospace America reported on September 21 that CRC planned a gas-generator hot-fire in December 2026 for turbine ignition. CEO Hugh Kolias expected a fully assembled engine with turbopump ready for hot-fire around 2028 and a first launch attempt around 2032. These are forecasts, not completed tests; they are later reporting than the August IEEE engine-static-fire expectation.
Supports: Capability · maturity
Aerospace America reported on September 21 that CRC planned a gas-generator hot-fire in December 2026 for turbine ignition. CEO Hugh Kolias expected a fully assembled engine with turbopump ready for hot-fire around 2028 and a first launch attempt around 2032. These are forecasts, not completed tests; they are later reporting than the August IEEE engine-static-fire expectation.
In the September 3 Canadian Explorers interview, Hugh Kolias discussed a 500,000-square-foot manufacturing facility, a proposed government/private financing mix and a search for anchor launch contracts. These are company intentions; the interview does not establish acquired premises, committed project finance or customer orders.
Department of National Defence's public evidence confirms a company-specific project, award, program or operating context, while configuration-specific acceptance and scale remain bounded by the reviewer warning.
Supports: Capability · defence applications
DND's Launch the North challenge targets sovereign Canadian light-lift launch capability.
IEEE Spectrum reports CRC shifting from R-1 toward an R-2 using seven E-1 engines, projected at 12,000–15,000 kg to LEO. CRC anticipated a fully assembled engine for static-fire testing in late 2027; orbital testing was years away. These are reported plans, not achieved results. IEEE Spectrum reports that orbital testing remains several years away and a fully assembled engine static fire is anticipated for late 2027. IEEE Spectrum reports that a fully assembled engine static fire is expected in late 2027 and orbital testing remains years away. IEEE Spectrum reported on August 20, 2026 that CRC had shifted toward R-2, projected 12,000 to 15,000 kilograms to LEO, expected a full-engine static fire in late 2027 and remained years from orbital testing. IEEE Spectrum published its Canada Rocket Company report on August 20, 2026. IEEE Spectrum reported that the company hired approximately 30 people in its first six months.
Public sources cited · Facts and assessments kept separate · Human review
Aerospace America describes a nine-engine methalox R-2 with a target of up to 15,000 kg to low Earth orbit. Its CEO said the structure would likely be mostly aluminum-lithium. These are reported design intentions, not tested performance or a frozen configuration.
Supports: Capability · commercial availability
Aerospace America reported on September 21 that CRC planned a gas-generator hot-fire in December 2026 for turbine ignition. CEO Hugh Kolias expected a fully assembled engine with turbopump ready for hot-fire around 2028 and a first launch attempt around 2032. These are forecasts, not completed tests; they are later reporting than the August IEEE engine-static-fire expectation.
Supports: Capability · summary
Aerospace America describes a nine-engine methalox R-2 with a target of up to 15,000 kg to low Earth orbit. Its CEO said the structure would likely be mostly aluminum-lithium. These are reported design intentions, not tested performance or a frozen configuration.
Supports:
Retain space and earth observation as the reviewed domain because the funded project concerns sovereign orbital launch for space capability.
Supports: Capability · summary
IEEE Spectrum reports CRC shifting from R-1 toward an R-2 using seven E-1 engines, projected at 12,000–15,000 kg to LEO. CRC anticipated a fully assembled engine for static-fire testing in late 2027; orbital testing was years away. These are reported plans, not achieved results.
Supports: Capability · commercial availability
IEEE Spectrum reports CRC shifting from R-1 toward an R-2 using seven E-1 engines, projected at 12,000–15,000 kg to LEO. CRC anticipated a fully assembled engine for static-fire testing in late 2027; orbital testing was years away. These are reported plans, not achieved results.
Supports: Capability · summary
Derived capability summary: CRC's one-engine R-1, seven-engine R-2 and E-1 architecture remains pre-flight, with changing payload and thrust targets and no completed full-engine hot-fire or flight.
Supports: Capability · maturity
IEEE Spectrum reports CRC shifting from R-1 toward an R-2 using seven E-1 engines, projected at 12,000–15,000 kg to LEO. CRC anticipated a fully assembled engine for static-fire testing in late 2027; orbital testing was years away. These are reported plans, not achieved results.
The public grant record names Canada Rocket Company and legal recipient 17457693 Canada Inc., Toronto, with CAD 8,333,333 under CO5-023 from March 6, 2026 through September 30, 2027. It funds research and development, not flight acceptance.
Supports: Capability · summary
DND agreement CO5-023 records C$8,333,333 for legal recipient 17457693 Canada Inc., operating as Canada Rocket Company, from March 6, 2026 to September 30, 2027. The public award describes research and development toward Canadian launch capability. DND’s March announcement identifies the project as R1 light-lift; neither source proves accepted prototype or flight deliverables.
SpaceQ reported access to an undisclosed medium-lift-capable test site and did not disclose its location. Derived availability: launch-site arrangements were discussions and no reviewed customer contract, manifested payload, licensed site, accepted delivery or operational service was located. SpaceQ reported launch-site partnership discussions rather than a selected launch site or completed launch-service agreement. SpaceQ reported preliminary turbomachinery and turbopump test-article work but no completed engine hot-fire or flight. SpaceQ reported approximately C$22.5 million in funding as of July 8, 2026. SpaceQ reported that Canada Rocket Company had 22 staff as of July 8, 2026. Derived maturity: SpaceQ reported preliminary turbopump test-article work and no completed hot-fire or flight, while IEEE Spectrum places a full-engine static fire in late 2027.
Supports: Capability · maturity
Derived maturity: SpaceQ reported preliminary turbopump test-article work and no completed hot-fire or flight, while IEEE Spectrum places a full-engine static fire in late 2027.
Supports: Capability · commercial availability
Derived availability: launch-site arrangements were discussions and no reviewed customer contract, manifested payload, licensed site, accepted delivery or operational service was located.
Supports: Capability · core features
SpaceQ reported access to an undisclosed medium-lift-capable test site and did not disclose its location. Derived availability: launch-site arrangements were discussions and no reviewed customer contract, manifested payload, licensed site, accepted delivery or operational service was located. SpaceQ reported launch-site partnership discussions rather than a selected launch site or completed launch-service agreement. SpaceQ reported preliminary turbomachinery and turbopump test-article work but no completed engine hot-fire or flight. SpaceQ reported approximately C$22.5 million in funding as of July 8, 2026. SpaceQ reported that Canada Rocket Company had 22 staff as of July 8, 2026. Derived maturity: SpaceQ reported preliminary turbopump test-article work and no completed hot-fire or flight, while IEEE Spectrum places a full-engine static fire in late 2027.
