FIELD: military equipment, measuring elements of control and stabilization systems of rocket missiles, rocket missiles of salvo fire, for example. SUBSTANCE: hydrodynamic gyroscope has case, rotor with adjustable space rotated by outside motor and partially filled with liquid. Space is made of left and right parts made fast one to another through adjustable element of cups with internal spherical surface. Centers of spheres are displaced from center of space of rotor by value L≤0,004Rc. Space of rotor houses spherical float with axial through hole, device for axial centering of float in the form of ball fixed in center of float and two axial bearings. Ball is placed in center of axial hole of float with the aid of left and right bushings with axial through holes and internal conical surface to ensure clearance δ = δ0+L, between it and axial bearings. Mass of liquid is chosen with due account of value and direction of displacement of centers of spheres of cups in accordance with relationship mf.l = ma.d+Δmf.l where δ0 and ma.d are axial clearance and rated computed mass of liquid found when L=0; Δmf.l is additional adjustable mass of liquid established from relationship 
where Rc is radius of sphere of cups; Rf.s is radius of free surface of liquid; ρ- is specific weight of liquid; π = 3,14.= 3.14. EFFECT: reduced error and raised functional reliability of gyroscope, improved precision characteristics and operational reliability of control and stabilization systems. 4 dwg
