XCOR Aerospace Lynx
The Lynx rocketplane is developed by the California-based company XCOR to compete in the emerging suborbital space flight market. Beginning in January, 2014 the Lynx is expected to be flying suborbital space tourism flights and scientific research missions by SXC (KLM-Space Expedition Curaçao) from a new spaceport on the Caribbean island of Curaçao.
Developing nation: United States of America.
Manufacturer/designer: XCOR Aerospace.
Production line: Mojave California.
Type aircraft: suborbital horizontal-takeoff, horizontal-landing (HTHL), rocket-powered spaceplane.
First flight: end 2012.
The Lynx is not dependable on a mothership that takes time to get it a to a high altitude launch environment. The Lynx has several major systems including: propulsion, aerodynamic shape, pressure vessel, cockpit, fuselage, wing strakes, wings, avionics, life support, and other related subsystems such as landing gear, doors. The propulsion system contains the engines with nozzle extensions, the pumps that drive fuel and liquid oxygen (LOX) into the engine, and various valves, regulators, piping, controllers, etc. The engine and nozzle design has been tested and demonstrated proper operation.
The Lynx will offer several multi-mission primary and secondary payload capabilities including: in-cockpit experiments, externally mounted experiments, test pilot/astronaut training, upper atmospheric sampling, microsatellite launch / ballistic trajectory research (Mk. III / US capability only), and personal spaceflight (space tourism).
Mark I Prototype
The Lynx Mark I is the initial flight test vehicle now under development at XCOR’s Mojave, CA facilities. This prototype vehicle will be used to characterize and flight test the various sub-systems of the craft including life support, propulsion, tanks, structure, aeroshell, aerodynamics, re-entry heating and other design elements. It will undergo a flight test program beginning in late 2012 and continuing into 2013.
- Maximum Altitude: 62 km (203,000 ft)
- Primary Internal Payload: 120 kg (260 lb)
- External Dorsal Mounted Pod: 280 kg (620 lb)
- Secondary payload spaces include a small area inside the cockpit behind the pilot or outside the vehicle in two areas in the aft fuselage fairing.
Mark II Production Model
The Lynx Mark II will begin construction and assembly during the Lynx Mark I development program . The Mark II is the production version of the Lynx, servicing both the suborbital tourism market and ll markets that make use of the Lynx’s internal payload volumes, such as microgravity and biotechnology experiments. The Lynx Mark II uses the same propulsion and avionics systems as the Lynx Mark I, but has a lower dry weight and hence higher performance than the Mark I. The Lynx Mark II is scheduled to enter flight service beginning in 2014.
- Maximum Altitude: +100 km (330,000 ft)
- Primary Internal Payload: 120 kg (260 lb)
- External Dorsal Mounted Pod: 650 kg (1,400 lb) and is large enough to hold a two stage carrier to launch a microsatellite or multiple nanosatellites into low Earth orbit.
- Secondary payload spaces include the same as the Mark I.
- Non-toxic (non-hydrazine) reaction control system (RCS) thrusters, type 3N22
Lynx XR-5K18 engine
The Lynx will have four liquid rocket engines at the rear of the fuselage burning a mixture of LOX-Kerosene and each of them will produce 2,900 pounds-force (13,000 N) of thrust.
All pictures courtesy of Zijde Aviation Photo and Publishing, Rob Vogelaar
Learjet C-21A
The Learjet C-21A is an military variant of the Learjet 35 business jet. The C-21A is a twin turbofan engine aircraft used for cargo and passenger airlift, and can transport litters during medical evacuations.
Developing nation: United States of America.
Manufacturer/designer: Bombardier/Learjet
Production line: Wichita, Kansas.
Type aircraft: twin turbofan engine business jet.
First flight: 22 August 1973 civil prototype.
First delivery: April 1984 to USAF.
Produced: April 1984 – October 1985.
Built: 38 Air Force active duty aircraft, and 18 Air National Guard aircraft in the C-21A fleet
The C-21A’s turbofan engines are pod-mounted on the sides of the rear fuselage. The swept-back wings have hydraulically actuated, single-slotted flaps. The aircraft has a retractable tricycle landing gear, single steerable nose gear and multiple-disc hydraulic brakes. The aircraft has a crew of two and may be flown from either cockpit seat. It is equipped with an automatic navigation system to enhance crew efficiency. Four cathode ray tubes display essential information to the pilots.
On April 1, 1997, all continental U.S.-based C-21s were realigned under Air Mobility Command, with the 375th Airlift Wing at Scott Air Force Base, Ill., as the lead command. C-21s stationed outside the continental United States are assigned to the theater commanders.
General characteristics
- Crew: two (pilot and co-pilot)
- Capacity: 8 passengers and 1,433 kg (3,153 lb) of cargo
- Length: 14.71 m (48 ft 7 in)
- Wingspan: 11.97 m (39 ft 6 in)
- Height: 3.71 m (12 ft 3 in)
- Wing area: 23.53m² (253.3ft²)
- Empty weight: 4,590kg (10,119 lb)
- Max takeoff weight: 8,235 kg (18,300 lb)
- Powerplant: 2 × Garrett TFE731-2-2B turbofan, 3,500 lbf (16kN) each
Performance
- Never exceed speed: 648 km/h (403 mph, 0.81M)
- Maximum speed: 853 km/h (530 mph, Mach 0.81) at 12,500 m (41,000 ft)
- Range: 3,690 km (2,004 nm, 2,306 mi)
- Service ceiling: 13,700 m (45,000 ft)
All pictures courtesy of Zijde Aviation Photo and Publishing, Rob Vogelaar and Marcel van Leeuwen.
Stratolaunch System
Stratolaunch Systems, a Paul G. Allen project, is developing an air-launch system that will revolutionize space transportation by providing orbital access to space at lower costs, with greater safety and more
flexibility. Delivering payloads in the 10,000lbm class into low earth orbit, the system allows for maximum operational flexibility and payload delivery from several possible operational sites, while inimizing mission constraints such as range availability and weather.
Developing nation: United States of America.
Manufacturer/designer: Scaled Composites/Burt Rutan.
Type aircraft: Six-engine carrier aircraft.
First flight: 2016.
Stratolaunch Systems is a space transportation venture specializing in air launch to orbit, with its corporate headquarters located in Huntsville, Alabama. It was founded in 2011 by Microsoft co-founder Paul G. Allen and Scaled Composites founder Burt Rutan, who had previously collaborated on the creation of SpaceShipOne.
The air-launch system is made up of four primary elements: a carrier aircraft, a multi-stage booster, a mating and integration system, and an orbital payload. Initial efforts will focus on unmanned payloads; however, human flights will follow as safety, reliability, and operability are demonstrated.
Stratolaunch Systems has assembled a team of innovative aerospace leaders to build and deliver a commercial air launch system.
Scaled Composites will build the carrier aircraft; SpaceX will provide the booster and space launch mission design and mission integration services; Dynetics will provide program management and systems engineering and integration, as well as test and operations support to Stratolaunch; Dynetics will also build the mating and integration system hardware. Stratolaunch Systems headquarters are in Huntsville, Alabama, and its aircraft hangar is in Mojave, California.
Carrier Aircraft
The carrier aircraft, built by Scaled Composites, weighs more than 1.2 million pounds and has a wingspan of 117 m (385 feet) – greater than the length of a football field. The carrier aircraft will be the largest aircraft ever constructed.and will weigh in at over 540,000 kg (1,200,000 pounds). The aircraft will be powered by 6 × 46,000-66,500lb thrust range Turbine Engines planned to be sourced from Boeing 747 engines and other components (flight deck, landing gear) from the 400-series The air-launch system requires a takeoff and landing runway that is, at minimum, 3,700 m (2,000 feet) long. The carrier aircraft can fly over 2,100 km (1,300 nautical miles) to reach an optimal launch point.
Multi-Stage Booster
SpaceX’s multi-stage booster is derived from the company’s Falcon 9 rocket. At approximately 36.57 m (120 feet) long, The launch vehicle will have a launch mass of approximately 220,000 kilograms (490,000 lb) and will have the goal of inserting a 6,100 kilograms (13,000 lb) payload into low Earth orbit. After release of the booster from the aircraft at approximately 30,000 feet, the first stage engines ignite and the spacecraft begins its journey into space. After the first stage burn and a short coast period, the second stage ignites and the orbital payload proceeds to its planned mission. The booster’s health and status during flight is monitored from the carrier aircraft and on the ground.
Mating and Integration System
Built by Dynetics, the mating and integration system (MIS) provides the single interface between the carrier aircraft and the booster. The MIS includes all systems required for the booster to interface with the carrier aircraft, including mechanical, electrical, thermal, fluids, and gases. The MIS is designed to safely and securely carry a booster weighing up to roughly 500,000 pounds. The MIS will secure the booster to the carrier aircraft, from taxiing to flight maneuvers to release of booster. In the case of a mission abort, the MIS will keep the booster secure during return to base and landing.
General characteristics
- Wingspan: 117 m (385 ft)
- Gross weight: 544,311 kg (1,200,000 lb)
- Powerplant: 6 × 46,000-66,500lb thrust rangeTurbine Engines planned to be sourced from a Boeing 747
Source and image Stratolaunch Systems.