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Arboga Robotmuseum

RB 321

Robothistoriska Föreningen i Arboga

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Sidan uppdaterad: 2017-02-18 14:23

Start

Missile

Engine

Radar

Simulator

 

Missile History

 

V-1 bomb

 

Navy Test missiles

 

Air Force Test missiles

 

Saab Test missiles

 

Air-to-surface missiles

 

Ship-to-ship missiles

 

Coastal missiles

 

Surface-to-air missiles

 

Anti-tank missiles

 

Target missiles

 

Submunition dispenser

 

Missile summary table

 

                                         

RB 321 at the Technical Museum

 

RB 321 was the designation for an air-to-air missile project, intended for the J 35 aircraft. Two versions of the missile (B/C) were developed for testing that lasted from the year 1949 to 1956. The design work began in 1948. Test firings took place at the Karlsborg Missile Test Site (RFK), using a rocket launcher and 44 tests were carried out by dropping the missile from J 29 B aircraft, “The Flying Barrel”.

 

RB 321 was equipped with nose control surfaces and wings with vertical winglets and ailerons at the aft part of the wing. The control system worked with a compressed air driven guidance unit with three air-driven gyroscopes, giving fault signals to four pneumatic control servos (one each for yaw and altitude and two for the roll control) These units were developed  and manufactured at the SAAB Plant in Jönköping. The control signals were sent from an active acquisition radar. This unit was developed by FOA ( Swedish Defence Research Agency) and was manufactured by the Swedish Radio Co. (SRA) . The unit was built entirely around electronic tubes.

 

Data:

·        Wave length 10 centimeter, Pulse emitting radar with a peak power of50 kW and 50 W average power. Bearings received from a skewed, rotating parabolic disc aerial. Disc aerial reflecting diameter 10 inches  (25 centimeter).

·        Range towards an aircraft 1.9  3.7 miles    (3 - 6 kilometer).

·        Apart from the actual acquisition radar electronics there was also an analogue target calculator for a modified Pure Pursuit steering.

 

The test missiles were controlled by pre-programmed clockwork. In the 321B version electrical rudder servos were used. a film camera and a telemetering facility registered the separation phase and the following flight pattern.

 

The RB 321 project was discontinued in 1962 in favour for the Sidewinder and the Falcon missiles. The missile 321 was later on modified to a ground-to-air missile with two ram motors and one booster rocket. (Designation RB 322)

 

Main Data (RB 321 C)

 

 

Length

12 feet 5 inches

(3,790 m)

Diameter

1 foot 8 inches

(0,500 m)

Wing span

10 inches

(0,255 m)

Weight

550 lbs

(250 kg)

Nominal Velocity

M 2.5

 

Booster rocket

KR 19 C

 

Thrust

6,450 lbf during 3.1 sec

(28.700 N during 3,1 s)

 

 

 

Missile types:

 

RB 301

 

RB 302

 

RB 303

 

RB 304A

 

RB 304B

 

RB 321

 

RB 322