KS-41 (2P24) launcher

Пусковая установка КС-41 (2П24)

The self-propelled launcher (PU) KS-41 (2P24) is located on the tracked chassis "object 123" developed by the Sverdlovsk plant of transport engineering (see diagram). The prototype for it was the light armored chassis "Object 105" of self-propelled artillery unit SU-100P developed in the first postwar years. Very successful chassis of this self-propelled gun, formally adopted for service, but never entered mass production, was considered as a base for the launchers of many missiles designed, but never completed development in the late fifties - early sixties. Later it was used for self-propelled artillery and mortars "Acacia", "Hyacinth", "Tulip", self-propelled tracked minefence GMZ.

The artillery part of the launcher included a support beam with an arrow hinged in its tail part, lifted by two hydraulic cylinders. Brackets with "zero length" supports were mounted on the sides of the boom to accommodate two missiles. When the missile was launched, the front support freed the way for the lower stabilizer arm of the missile. On the march, the missiles were held by additional underwater supports, also fixed to the boom. One support of the truss structure was brought in from the front and provided for the fixation of both missiles at once. Another support was moved on the sides opposite to the arrow. The height of the launcher with the assembled rockets on the march was more than 4 m, so if it was necessary to pass under the viaducts, the upper stabilizer console was removed.

The rockets were launched by lifting the boom with the guides at an angle from 10 to 60° to the horizon. Soundproofing made it possible to carry out the launch when the personnel were inside the PU 2P24.

The appearance of the rocket and the launcher was not formed immediately. At an early stage of design was considered a version of the rocket with a "+"-shaped arrangement of the wings and "x"-shaped tail fins, with the launch of the missile was made with beam guides launcher. At the beginning of the flight tests it was planned to switch from a circular air intake to a sector air intake. The wingspan and plumage were slightly reduced during the test.