Patent GB-1007890-A (GB)
Title: Improvements in or relating to ground-based flight training apparatus
Inventor: CUTLER ALBERT ERNEST
IPC: G09B9/20
Filed: 1962-01-11
Abstract: 1,007,890. Grounded flight trainers. COMMUNICATIONS PATENTS Ltd. Jan. 2, 1963 [Jan. 11, 1962], No. 1034/62. Heading B7W. [Also in Division H4] This invention relates to flight simulating apparatus comprising an automatic blind landing system and a simulated autopilot providing lateral and longitudinal control and being responsive to a plurality. of alternative control signals each corresponding to a different longitudinal control mode and operative over a different altitude range, for example 1500- 200 feet, 200-50 feet and 50-0 feet. Longitndinal control.-The flight simulator described comprises (Fig. 1) a longitudinal mode computer 10, which includes pitch and rate of pitch integrators, an angle of attack and lift coefficient system, true and indicated airspeed and Mach number systems, gross weight and pitch moment of inertia systems, and a height computing system, and an autopilot 15 connected by lines 19, 19<SP>1</SP> to the computer 10 and by a line 17 to the output of a blind landing system, which computes the height error. The height error is derived from a " height above runway " signal 36 from the computer 10, and from a range computer 20, fed by northing and easting integrators 21, 22 which integrate velocity components transmitted by the computer 10 and by a windspeed resolver 29. When the height is greater than 200 feet, and the switches 37, 38 are in the positions shown, these two signals (height and range) are fed to a summing amplifier 39, and a height error (height-above-glide-path) signal is transmitted to the autopilot lines 40 and 17, the range signal being converted into a height-of-glide-path signal by a potentiometer 45. When the height is between 200 feet and 50 feet a relay 32 is operated by an amplifier 34, and the switch 37 changes from 37<SP>1</SP> to 37<SP>11</SP>, a pitch control signals passing directly from the computer 10 to the autopilot 15 via lines 25, 41<SP>1</SP>, 17. This signal preferably maintains constant pitch, but could be arranged to maintain constant rate of descent. When the height is below 50 feet, the amplifier 35 energizes the relay 33, bringing the switch 38 to the contact 3811 and connecting a summing amplifier 42 to the autopilot 15, via lines 43, 41<SP>1</SP> and 17. Into a summing amplifier 51 are fed the height-above-runway, and rate of change of this height, h and h respectively, from the computer 10 on lines 3611, 52 and the function (h g +T 1 h 9 ), where T 1  is a constant and h 0  is the local height of the terrain above the runway (a function of range), derived by a network 49 and computer 47 from the range computer 20. The output from amplifier 51 corresponds to ((h+t 1 #h) - (h g +T 1 #h g )) and hence to (h r ,+T 1 <SP>#</SP>h r ,) where h r , is the radio-altimeter height. This output signal is fed to a summing amplifier 42 directly along line 55 and through an integrator 53, into which is also fed on wire 58 a signal hd, the demand height relative to the runway, which is slightly negative to ensure the aircraft is kept on the runway after landing. The output of the integrator is and signal fed to the computer 15 via lines 43, 41<SP>1</SP>, 17 ,  is where G 1  and G 2  are constants; this is function which is stated to govern the elevator angle dnring flare-out. Lateral control.-The lateral control computer 60 (Fig. 2) includes rate of roll and roll angle integrators rate of yaw and heading angle integrator, roll of yaw moment of inertia systems and a sideslip angle computing system. Input signals 66, 66<SP>1</SP> correspond to aileron and rudder deflections. The transverse displacement of the aircraft from the runway centreline, (x cos # - y sin #) where x and y are the East-West and North-South displacements of the aircraft and # is the runway bearing, is derived from integrators 21, 22 (also shown in Fig. 1), which give x and y, and potentiometers 89, 91 which are set by a control 93 to the runway heading. The output of these potentiometers is fed through a summing amplifier 96, via lines 97, 97<SP>1</SP> to the roll and yaw computers 63, 64. The output of the integrators is fed along lines such as 78<SP>1</SP> above 200 feet and on lines 78 on which the signals are fifty times as strong below 200 feet, the necessary switches 79, 82 being operated by a relay 80 at 200 feet. The runway heading control 93 is also connected to the rotor of a synchro unit 98 and the aircraft heading is fed by a shaft 101 to the rotor of a synchro unit 99 connected to the unit 98. The difference between these headings is transmitted by wire 102 to the yaw computer 64 when the switch 103<SP>1</SP> is closed by a relay 104 at 50 feet so that the nose of the aircraft is lined up with the runway for touchdown.