The MiG-9 was a cantilever mid-wing monoplane of all-metal
construction with a smooth stressed skin and a retractable tricycle undercarriage.
To simplify the process of assembly the aircraft was divided into several
semi-monocoque stressed-skin structure. Duralumin was used as the main
Technologically the fuselage was built in two sections – the
forward fuselage (frames Nos. 1 through 15a) and the rear fuselage (frames Nos.
15 through 35), which were joined together by fittings. The fuselage structure
incorporated two air ducts supplying air to the engines. The ducts had an
elliptic cross-section changing to circular at the rear and ran along the
fuselage sides, flanking the cockpit.
The forward fuselage housed the armament, the nose landing
gear unit, the cockpit with the canopy, controls and appropriate equipment, a
fuel tank and other units. The forward fuselage framework consisted of four
variable-section longerons, 15 frames, a number of stringers, two beams for the
installation of the nose gear unit and two beams for the attachment of the
armament. Attached to frame No. 1 was the front fairing which formed the
aircraft’s nose with a bifurcated air intake for the powerplant. The inlet
ducts were structurally joined to the beams of the nose gear unit and to the
armament attachment beams. Together with the floor of the cockpit, the skinning
and the longitudinal structural members they formed a structure sustaining all
the stresses of the forward fuselage.
The framework of the rear fuselage consisted of four
longerons, 20 frames, a number of stringers and two ribs to which the main
undercarriage units were attached. The aft fuselage housed equipment, wiring
and control units, as well as two bag-type fuel tanks in containers. A heat
shield protecting the fuselage undersurface from hot exhaust gases was mounted
between frames Nos. 19 and 34. Between frames Nos. 19 and 29 the fuselage was
structurally integral with the lower part of the fin. Lugs for mounting the
stabilizers and the fin were installed on frames Nos. 32, 34 and 35.
The landing gear attachment ribs together with the wing
attachment beam and engine attachment beam formed a load-bearing structure
absorbing the loads from the undercarriage, the wings and the engines.
The cockpit was placed in the forward fuselage over the
engines within the space between frame No. 5 and the sloping frame No. 11 a.
The cockpit canopy had a streamlined shape, consisting of a fixed windshield
and an aft-sliding rear portion which could be jettisoned in an emergency. Aft
of frame No. 5 the cockpit floor was partly formed by the inlet ducts. The rear
part of the floor adjoining the rear wall of the cockpit sloped in such a way
that the pilot’s seat was placed between the engines. The seat was a duralumin
pan of the usual type, designed to accommodate a parachute and attached to the
cockpit floor by brackets. The seat was provided with a harness comprising leg
belts and shoulder straps. A padded seat back was attached to the rear cockpit
wall. A padded headrest was attached to the rear bow of the sliding part of the
canopy. The cockpit armour comprised two steel armour plates 12 mm (0.47 in.)
thick and, on some machines, a 55-mm (2.16-in.) bulletproof glass plate mounted
in the front part of the windshield. An attachment unit for the
centrally-mounted cannon was installed in the cockpit on suitably stressed
elements of the structure; the cockpit also housed the control stick and rudder
wings of trapezoidal planform and all-metal two-spar riveted construction,
built as one-piece panels attached to the fuselage sides. Incidence 1°,
dihedral 2.5° and thickness-to-chord ratio 9% over the entire span.
The wings employed a combination of airfoil sections. A
low-lift TsAGI1-A-1 0 airfoil was used in the span segment between ribs Nos. 1
and 3; a high-lift TsAGI1-V-1 0 airfoil was used between rib No. 6 and the
wingtip, and the span segment in between featured a transitional airfoil
section. This combination of airfoil sections precluded the possibility of the
aircraft entering a spin at high angles of attack.
The wing framework comprised two spars, 21 ribs and a number
of stringers. The wings were equipped with Frise ailerons and TsAGI-type
slotted flap§. (modified Fowler flaps). The flaps occupied the portion of the
trailing edge between ribs Nos. 1 and 11, the ailerons being accommodated
between ribs Nos. 11 and No. 21. The ailerons’ maximum deflection angle was
+22S/-14S. The flaps were set at 20° for take-off and 50° for landing. The
trailing-edge section of the wings between ribs Nos. 1 and 6 had a cutout for
the wheel wells. The wings also housed six bag-type fuel tanks which were
placed in containers.
Tail unit: the
empennage was of all-metal construction, featuring high-set cantilever
stabilisers. The tail surfaces employed a NACA0009 symmetric airfoil section.
The fin and the stabilisers were detachable. The horizontal tail was built in
two symmetrical halves, each half having two spars and 11 ribs. The front
stabiliser attachment fittings were of a rack type, permitting the incidence of
the stabilisers to be adjusted on the ground between the angles of +1°10′ and
-4°. The starboard elevator incorporated a steerable trim tab.
The fin structure was similar to that of the stabilisers.
The fin’s frame comprised two spars and six ribs. The elevators were of
allmetal construction and were attached to the stabilisers by five brackets.
The all-metal rudder was attached by three brackets to the fin and the
pneumatically retractable tricycle type, with single wheel on each unit. The
wheel base was 3.02 m (9 ft 11 in.). All three units had levered suspension and
oleopneumatic shock absorbers, those on the main undercarriage struts being
mounted externally. The main units retracted outwards into the wings, the nose
unit aft into the fuselage. The levered-suspension main units had 660 x 160 mm
(25.74 x 6.24 in) wheels equipped with brakes and mounted on semiforks. The nose
unit had a non-braking wheel measuring 480 x 200 mm (18.72 x 7.8 in); it
featured an attachment point, an integral shock absorber, a shimmy damper, an
uplock, a downlock and a retraction jack. Each mainwheel well was closed by two
doors, the bigger one being attached to the main gear strut and the smaller one
to the wing; the nosewheel well had a forward door segment hinged to the nose
gear oleo and two lateral doors at the rear.
RD-20 Series A2 single-shaft axial-flow turbojets delivering 800 kgp (1,764 Ib
st) each. The engine had a seven-stage compressor, a single-stage turbine with
air-cooled blades and a variable nozzle with a movable centre-body. Each engine
had its own Riedel two-cylinder two-stroke starter.
The fuel (kerosene) was accommodated in ten tanks. Four
tanks (including three bagtype tanks) were housed in the aft fuselage, the
remaining six were located in the wings. The total capacity of the fuel system
was 1,595 litres (351 Imp gal), of which 1,225 litres (269.5 Imp gal) could be
carried in the four fuselage tanks. To facilitate engine start-up a special
start-up fuel system using more easily combustible petrol was provided.
production MiG-9s were equipped with one centrally-mounted 37-mm (1.45 calibre)
Nudel’man N-37 cannon with 40 rounds and two 23-mm (.90 calibre) Nudel’man/
Sooranov NS-23K cannons with 80 rpg. The N-37 weighed 103 kg (227 Ib) and
possessed a rate of fire of 400 rounds per minute, the muzzle velocity of the
shell being 700 m/sec (2,296 ft/sec). The NS-23K cannon had a rate of fire of
600 rounds per minute and a muzzle velocity of 680 m/sec (2,230 ft/sec). The
N-37 protruded 1.16 m (3 ft 9.67 in.) beyond the plane of the air intake lip,
while the NS-23K cannons protruded 0.5 m (1 ft 7.68 in.). The ammunition boxes
were accommodated in an equipment bay between fuselage frames Nos. 1 and 6.
It should be noted that some production aircraft were
provided with attachment points for a centrally-mounted cannon of a larger
calibre. Thus, the first three machines of the ‘parade’ batch (c/ns 106001
through 106003) were provided with attachment points, ammunition box and link
and case chutes for the 57-mm (2.24 calibre) Nudel’man N-57 (izdeliye 120P)
cannon. MiG-9s with c/ns 106004 through 112001 were fitted only with attachment
points for the N-57 cannon (they differed in having an increased-diameter
equipment: The basic range of equipment installed on production MiG-9s
comprised the following items: an RSI-6 CRei-VM’) short-wave transceiver; an
RPKO-10M direction finder, a single 1.5-kilowatt GSK-1500 DC generator driven
by one of the engines, a 12-A-10 DC battery and an RU-45A AC converter. The
cockpit housed flight and navigation instruments and engine control
instruments: a US-1 000 airspeed indicator, a VD-12 altimeter, an electrical
gyro horizon combined with a Horn-type turn indicator; a PDK-44 compass, a
VR-30 vertical speed indicator, a TF-15 tachometer, an MP-80 kerosene pressure
gauge, an EDMU-1 gas pressure gauge, a TVG-44 exhaust gas thermometer, a BE-296
fuel gauge and TME-45 engine oil thermometers.
A single-wire aerial was attached with one end to a strut
which was mounted on a fuselage frame, offset to starboard; the other end of
the aerial was attached to the fin.
The aircraft was fitted with a PKI-1 reflector gunsight
which was later replaced by an ASP-1 N optical sight; some machines were
provided with an S-13 gun camera in the wing/fuselage fairing.
Oxygen system: a
KP-14 breathing apparatus which ensured oxygen supply for the pilot to an
altitude of up to 12 kilometres (39,370 ft).
conventional mechanical control system comprising control stick, rudder pedals
and trim tabs. The stick was connected to the ailerons and elevators by
push-pull rods and bellcranks, while the rudder was controlled by means of
steel cables. The elevator trim tab installed on the starboard elevator was