FLIGHT SIMULATION COMPLEX FOR INVESTIGATION OF LANDING SYSTEMS OF SHIP-BASED FLYING VEHICLES Russian patent published in 1995 - IPC

FIELD: aeronautical engineering. SUBSTANCE: introduced into ground portion of flight simulation complex are: landing radar 12 with computer 13, control command computer 10, computer of disturbance and motions model, ship's motions computer-extrapolator 18, computer 24 of vertical velocity of ship's motions, trajectory criterion computer unit 29, logic device 25, external trajectory optical meter 6 with computer 7, optical landing system 8, localizer beacon 16 and glide-path beacon 17, TV measurement information system 15, meteorological parameter meter 11 and air camera recorder 5. First output of computer 13 of landing radar 12 is connected with control signal transmission line 3 through control command computer 10 and its second output is connected with respective inputs of control command computer 10 which are connected in series by means of ship's motions computer-extrapolator 18, motions vertical velocity computer 24 and logic device 25; third output is connected with first input of first adder 21 whose second input is connected with programmed trajectory computer 19 trajectory criterion computer unit 29 whose first output is connected with second input of logic device and second output is connected with first input of second adder whose second input is connected via computer of flying vehicle model and automatic control system model with second output of motions vertical velocity computer which is also connected to respective inputs of programmed trajectory computer and criterion computer unit. Output of second adder is connected with first input of disturbance and motions model computer whose second input is connected with meteorological parameter meter; first output is connected with second inputs of control command computer and optical landing system; second output is connected with landing radar, third output is connected with second input of motions computer-extrapolator whose third input is connected with landing radar; first output is connected to logic device, second output is connected with first input of programmed trajectory computer whose second outputs are connected with computer of external optical trajectory meter, and then with air camera recorder 5 and with display system which is connected to respective inputs of computers of disturbance and motions models, flying vehicle model and automatic control system model, to calculated criterion computer unit, to expert system computer connected to calculated criterion unit. EFFECT: enhanced reliability. 3 dwg