Miloch
February 4th 20, 03:11 PM
https://en.wikipedia.org/wiki/Mikoyan-Gurevich_I-270
The Mikoyan-Gurevich I-270 (Design ? ("Zh") under Mikoyan-Gurevich's in-house
designation sequence, USAF/DoD designation: Type 12) was a response to a Soviet
Air Forces requirement in 1945 for a rocket-powered interceptor aircraft for the
point-defence role. In concept and basic configuration, it was related to the
early Korolyov RP-318 rocket-powered aircraft which was developed in 1936 and
first flew February 20, 1940, and the more recent Bereznyak-Isayev BI-1 Soviet
design. Only two prototypes were built, both of which were destroyed in crashes,
leading to the cancellation of the project.
Role
Interceptor aircraft
National origin
Soviet Union
Manufacturer
Mikoyan-Gurevich
First flight
December 1946 (unpowered)
Status
Cancelled
Primary user
Soviet Air Forces
Number built
2
In the early stages of World War II (1942), a complete prototype BI-1 (also
known as The Devil's Broomstick), made its first several flights. The I-270
shared the BI-1's simple, tapered fuselage, bubble canopy, wing design, and
dual-chambered bipropellant rocket motor. On the other hand, it was considerably
larger than the BI-1 and featured short, reinforced wings (from the RP-218) and
a raised T-tail which aircraft such as the Tupolev ANT-8 proved, offered better
landing control than the BI-1's more traditional fighter layout. While there
seems little doubt that the BI-1 influenced the design of the I-270, the latter
appears far from a direct descendant of the former, and much closer to being a
Soviet version of the Me 263, sharing very similar fuselage, canopy and landing
gear layouts, while adding a conventional stabilizer surface atop the vertical
tail, absent on the German design.
Soviet tradition of rocketry, starting from the early work of Konstantin
Tsiolkovsky and carried through by men like Sergei Korolev, made rocket fighters
a reality. The RD-2M engine, designed by Leonid Dushkin was the dual-combustion
chamber version of the engine used for the 1941 BI-1 rocket plane. That in turn
had followed from a tradition dating back to Sergey Korolev's work on project
"06" in the early 1930s and the RP-318 rocket plane designed in 1936.
The first gliding trials commenced in December 1946, with the first prototype
towed into the air behind a Tupolev Tu-2, ballast-loaded in place of an engine.
The second prototype began powered tests early in 1947, but was damaged beyond
repair making a hard landing. Shortly afterwards, the first prototype was also
destroyed in a landing accident. By this stage, turbojet technology was at a far
more advanced stage than it had been at the outset of the project, and
surface-to-air missiles had replaced the need for point-defence interceptors.
Under these circumstances, the Air Force decided to cancel the project.
Specifications (I-270)
General characteristics
Crew: 1
Length: 8.915 m (29 ft 3 in)
Wingspan: 7.75 m (25 ft 5 in)
Height: 2.8 m (9 ft 2 in)
Wing area: 12 m2 (130 sq ft)
Airfoil: root: TsAGI-12145; tip: TsAGI-1S012
Empty weight: 1,564 kg (3,448 lb)
Gross weight: 2,556 kg (5,635 lb)
Max takeoff weight: 4,121 kg (9,085 lb)
Fuel capacity: 2,120 kg (4,670 lb) (also quoted as 2,150 kg (4,740 lb)) - 1,620
kg (3,570 lb) RFNA oxidiser in four tanks, 440 kg (970 lb) kerosene fuel in a
single tank with seven tanks for 80% hydrogen peroxide (H2O2) to generate steam
to run turbopumps.
Powerplant: 1 × Dushkin-Glushko RD-2M-3V liquid-fuelled rocket engine, 14.22 kN
(3,197 lbf) thrust for take-off
15.06 kN (3,385 lbf) at 5,000 m (16,000 ft)15.50 kN (3,484 lbf) at 10,000 m
(33,000 ft)15.60 kN (3,506 lbf) at 15,000 m (49,000 ft)
Performance
Maximum speed: 1,000 km/h (620 mph, 540 kn) , Mach0.815 at sea level
990 km/h (620 mph; 530 kn), Mach0.86 at 5,000 m (16,000 ft)928 km/h (577 mph;
501 kn), Mach0.87 at 10,000 m (33,000 ft)925 km/h (575 mph; 499 kn), Mach0.87 at
11,000 m (36,000 ft)936 km/h (582 mph; 505 kn), Mach0.88 at 15,000 m (49,000
ft)Landing speed: 137 km/h (85 mph; 74 kn) flaps extended
156.5 km/h (97.2 mph; 84.5 kn) flaps retractedEndurance: at 15,000 m (49,000 ft)
with both chambers ignited 4 minutes 8.4 secondswith one chamber ignited 4
minutes 53.4 secondsService ceiling: 17,970 m (58,960 ft) (some sources 17,000 m
(56,000 ft)
Time to altitude: 5,000 m (16,000 ft) in 88.5 seconds
10,000 m (33,000 ft) in 144 seconds11,000 m (36,000 ft) in 150.4 seconds15,000 m
(49,000 ft) in 181.25 secondsWing loading: 344 kg/m2 (70 lb/sq ft)
Take-off run: 895 m (2,936 ft)
Landing run: 493 m (1,617 ft) (some sources 956 m (3,136 ft))
Armament
Guns: 2 × 23 mm (0.906 in) Nudelman-Suranov NS-23 autocannon with 40 rpg (some
sources 50 rpg)
Avionics
PKI-1 collimator gunsight
RPKO-10 (or RPKO-10M) ADF
RSI-6 radio
IFF
KP14 Oxygen unit
FSI-6M
*
The Mikoyan-Gurevich I-270 (Design ? ("Zh") under Mikoyan-Gurevich's in-house
designation sequence, USAF/DoD designation: Type 12) was a response to a Soviet
Air Forces requirement in 1945 for a rocket-powered interceptor aircraft for the
point-defence role. In concept and basic configuration, it was related to the
early Korolyov RP-318 rocket-powered aircraft which was developed in 1936 and
first flew February 20, 1940, and the more recent Bereznyak-Isayev BI-1 Soviet
design. Only two prototypes were built, both of which were destroyed in crashes,
leading to the cancellation of the project.
Role
Interceptor aircraft
National origin
Soviet Union
Manufacturer
Mikoyan-Gurevich
First flight
December 1946 (unpowered)
Status
Cancelled
Primary user
Soviet Air Forces
Number built
2
In the early stages of World War II (1942), a complete prototype BI-1 (also
known as The Devil's Broomstick), made its first several flights. The I-270
shared the BI-1's simple, tapered fuselage, bubble canopy, wing design, and
dual-chambered bipropellant rocket motor. On the other hand, it was considerably
larger than the BI-1 and featured short, reinforced wings (from the RP-218) and
a raised T-tail which aircraft such as the Tupolev ANT-8 proved, offered better
landing control than the BI-1's more traditional fighter layout. While there
seems little doubt that the BI-1 influenced the design of the I-270, the latter
appears far from a direct descendant of the former, and much closer to being a
Soviet version of the Me 263, sharing very similar fuselage, canopy and landing
gear layouts, while adding a conventional stabilizer surface atop the vertical
tail, absent on the German design.
Soviet tradition of rocketry, starting from the early work of Konstantin
Tsiolkovsky and carried through by men like Sergei Korolev, made rocket fighters
a reality. The RD-2M engine, designed by Leonid Dushkin was the dual-combustion
chamber version of the engine used for the 1941 BI-1 rocket plane. That in turn
had followed from a tradition dating back to Sergey Korolev's work on project
"06" in the early 1930s and the RP-318 rocket plane designed in 1936.
The first gliding trials commenced in December 1946, with the first prototype
towed into the air behind a Tupolev Tu-2, ballast-loaded in place of an engine.
The second prototype began powered tests early in 1947, but was damaged beyond
repair making a hard landing. Shortly afterwards, the first prototype was also
destroyed in a landing accident. By this stage, turbojet technology was at a far
more advanced stage than it had been at the outset of the project, and
surface-to-air missiles had replaced the need for point-defence interceptors.
Under these circumstances, the Air Force decided to cancel the project.
Specifications (I-270)
General characteristics
Crew: 1
Length: 8.915 m (29 ft 3 in)
Wingspan: 7.75 m (25 ft 5 in)
Height: 2.8 m (9 ft 2 in)
Wing area: 12 m2 (130 sq ft)
Airfoil: root: TsAGI-12145; tip: TsAGI-1S012
Empty weight: 1,564 kg (3,448 lb)
Gross weight: 2,556 kg (5,635 lb)
Max takeoff weight: 4,121 kg (9,085 lb)
Fuel capacity: 2,120 kg (4,670 lb) (also quoted as 2,150 kg (4,740 lb)) - 1,620
kg (3,570 lb) RFNA oxidiser in four tanks, 440 kg (970 lb) kerosene fuel in a
single tank with seven tanks for 80% hydrogen peroxide (H2O2) to generate steam
to run turbopumps.
Powerplant: 1 × Dushkin-Glushko RD-2M-3V liquid-fuelled rocket engine, 14.22 kN
(3,197 lbf) thrust for take-off
15.06 kN (3,385 lbf) at 5,000 m (16,000 ft)15.50 kN (3,484 lbf) at 10,000 m
(33,000 ft)15.60 kN (3,506 lbf) at 15,000 m (49,000 ft)
Performance
Maximum speed: 1,000 km/h (620 mph, 540 kn) , Mach0.815 at sea level
990 km/h (620 mph; 530 kn), Mach0.86 at 5,000 m (16,000 ft)928 km/h (577 mph;
501 kn), Mach0.87 at 10,000 m (33,000 ft)925 km/h (575 mph; 499 kn), Mach0.87 at
11,000 m (36,000 ft)936 km/h (582 mph; 505 kn), Mach0.88 at 15,000 m (49,000
ft)Landing speed: 137 km/h (85 mph; 74 kn) flaps extended
156.5 km/h (97.2 mph; 84.5 kn) flaps retractedEndurance: at 15,000 m (49,000 ft)
with both chambers ignited 4 minutes 8.4 secondswith one chamber ignited 4
minutes 53.4 secondsService ceiling: 17,970 m (58,960 ft) (some sources 17,000 m
(56,000 ft)
Time to altitude: 5,000 m (16,000 ft) in 88.5 seconds
10,000 m (33,000 ft) in 144 seconds11,000 m (36,000 ft) in 150.4 seconds15,000 m
(49,000 ft) in 181.25 secondsWing loading: 344 kg/m2 (70 lb/sq ft)
Take-off run: 895 m (2,936 ft)
Landing run: 493 m (1,617 ft) (some sources 956 m (3,136 ft))
Armament
Guns: 2 × 23 mm (0.906 in) Nudelman-Suranov NS-23 autocannon with 40 rpg (some
sources 50 rpg)
Avionics
PKI-1 collimator gunsight
RPKO-10 (or RPKO-10M) ADF
RSI-6 radio
IFF
KP14 Oxygen unit
FSI-6M
*