FIELD: rocketry; production of guided missiles steering engines.
SUBSTANCE: the invention is dealt with the field of rocketry and may be used in the field of assembly of electropneumatic (gas) steering engines for the guided missiles and in the method to check leakage of the pneumoshutter of the steering engines gas-distributing devices in the process of their series production. In the process of assembly of a steering engine, that consists of an air engine and a electromagnet with a spring-loaded retractable armature interacting through a pusher with the pneumoshutter valve located between input and output saddles. At that besides progressive installation in the master body of component parts of the air engine of the pneumoshutter and the electromagnet they perform a number of padding operations. Using compression by the valve of edges of holes of the pneumoshutter input and output saddles up to the preset sizes at provision of the valve self-positioning in the holes of the input and output saddles of the pneumoshutter they make seats for electromagnet in the pneumoshutter and before mounting a spring in the electromagnet at feeding to its coil of a constant electrical signal they using motion of a pusher in the armature make the size of the pusher output from the electromagnet and exercise locking of the pusher in the armature. Then after installation of the electromagnet they check the leakproofness of the pneumoshutter and set the spring of the electro magnet. At that the necessary effort of a preliminary contraction of the spring in the electromagnet is adjusted after installation of the steering engine into the steering gear of the guided missile, controlling and setting up dynamic characteristics of the steering engine at feeding a control electrical signal and a pneumatic power from external sources. The method of leak check of the pneumoshutter with the valve spring-loaded to the saddle includes the air delivery into the checked sample from a pneumatic power source and the control over the air pressure variation in the container coupled to the pneumoshutter. At that the air is delivered into the steering engine from the source of the pneumatic power through a technological buffer container, which may be disconnected from the source of the pneumatic power with the help of a valve at the moment the air pressure in it reaches the initial level. Control of hermiticity of the pneumoshutter is conduct by a time required for a drop of the air pressure in the technological buffer container from its initial level to the given minimum level at blanking the saddle by the valve, that is applied mechanically on the valve with the effort equal to computational effort of the preliminary contraction of the spring. The invention increases stability of the dynamic characteristics of the guided missile steering engine in the process of operation and at the series production.
EFFECT: the invention allows to improve stability of the dynamic characteristics of the guided missile steering engines in operation and at the series production.
2 cl, 4 dwg
