GB1133081A - Creation of Inventions and Patents with Artificial Intelligence

GB1133081A – An aircraft computing and director system for take-off and overshoot
– Google Patents

GB1133081A – An aircraft computing and director system for take-off and overshoot
– Google Patents
An aircraft computing and director system for take-off and overshoot

Info

Publication number
GB1133081A

GB1133081A
GB33561/64A
GB3356164A
GB1133081A
GB 1133081 A
GB1133081 A
GB 1133081A
GB 33561/64 A
GB33561/64 A
GB 33561/64A
GB 3356164 A
GB3356164 A
GB 3356164A
GB 1133081 A
GB1133081 A
GB 1133081A
Authority
GB
United Kingdom
Prior art keywords
signal
amplifier
pilot
output
adder
Prior art date
1964-08-17
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)

Expired

Application number
GB33561/64A
Inventor
Donald Edward Fry
Morrison Richard Watts
Martin Richard Green
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)

MINI OF TECHNOLOGY

Minister of Technology

Original Assignee
MINI OF TECHNOLOGY
Minister of Technology
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
1964-08-17
Filing date
1964-08-17
Publication date
1968-11-06

1964-08-17
Application filed by MINI OF TECHNOLOGY, Minister of Technology
filed
Critical
MINI OF TECHNOLOGY

1964-08-17
Priority to GB33561/64A
priority
Critical
patent/GB1133081A/en

1968-11-06
Publication of GB1133081A
publication
Critical
patent/GB1133081A/en

Status
Expired
legal-status
Critical
Current

Links

Espacenet

Global Dossier

Discuss

Classifications

G—PHYSICS

G06—COMPUTING; CALCULATING OR COUNTING

G06G—ANALOGUE COMPUTERS

G06G7/00—Devices in which the computing operation is performed by varying electric or magnetic quantities

G06G7/48—Analogue computers for specific processes, systems or devices, e.g. simulators

G06G7/78—Analogue computers for specific processes, systems or devices, e.g. simulators for direction-finding, locating, distance or velocity measuring, or navigation systems

F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING

F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL

F16H—GEARING

F16H35/00—Gearings or mechanisms with other special functional features

G—PHYSICS

G01—MEASURING; TESTING

G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES

G01S1/00—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith

G01S1/02—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith using radio waves

G—PHYSICS

G05—CONTROLLING; REGULATING

G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES

G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot

G05D1/04—Control of altitude or depth

G05D1/06—Rate of change of altitude or depth

G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft

G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing

Abstract

1,133,081. Aircraft take-off and overshoot computer. MINISTER OF TECHNOLOGY. 17 Nov., 1965 [17 Aug., 1964], No. 33561/64. Heading G4G. In apparatus for producing a display to the pilot of an aircraft during take off or overshoot, a pitch rate director signal is given by Q – QD (1) where Q is pitch rate Q D is a required pitch rate to develop the required climb path, given by Q D = K2 TV + K2V – K2 V D (2) or allowing for any loss of engine thrust where V is airspeed V is longitudinal acceleration V D is required steady climbout speed T is constant determining the ratio V/#V K 2 is an aircraft characteristic and loading constant 1 is an exponential term wherein 1 + #D # is a time constant D is a differential operator. A pressure transducer operated by a static pitot tube produces an airspeed signal connected to operational amplifier 2 with smoothing feedback path, whose output – V is connected to adder amplifier 3a direct through resistor R 2 and through a differentiating network comprising resistor R 1 and capacitor T developing longitudinal acceleration signal. Potential divider 5 is also connected over series resistors R 4 , R 5 to adder 3a to introduce a preset demanded steady climbout speed V D , and a variable capacitor T 4 is switchable at S 1 between earth and the junction of R 4 , R 5 , while a potential divider VR 5 is switohable at S 2 to the junction of S 1 and T 4 . The output of the adder is connected over potential divider 6 to operational amplifier 7 with limiter feedback, which energizes adder amplifier 9a with smoothing feedback; a smoothing network comprising resistors R 7 , R 8 and variable capacitor T 5 being connected between the input of 9a and the output of pitch rate gyro 12. Shunt resistor R 9 is switchable by S 5 while the input of 9a is also connected over series resistors R 11 , R 12 to a potential divider VR 9 ; the junction of R 11 , R 12 being earthed either direct over switch S6 or capacitatively through switch S7. Output of amplifier 7 is earthable over normally open S4, and the output of the potential divider 13 in the output adder amplifier 9a is applied to a pilot’s head-up display 15 and over a modulator 14 to an automatic pilot or head-down control display 16. The output of amplifier 2 also energizes threshold circuit 17 controlling switches S2 to S 7 , which may be transistorized, and the amplifier 18 energizing potential divider VR5. In directing take-off during acceleration to rotation speed V R , the smoothed airspeed signal (-V) at the output of 2 energizes the threshold circuit to operate first at e.g. a speed (V R – 15) slightly in defect of the rotation speed and subsequently at the rotation speed, so that initially, switches S 1 to S 7 are closed and the output of amplifier 7 is earthed. The pilot’s display then indicates at the bottom of its screen a smoothed and attenuated pitch rate signal Q. At speed (Vr – 15) switch S6 is opened and a positive voltage is applied from VR 9 to adder 9a, through warning circuit 11, and exponentially deflects the Q signal from the bottom to the centre of the pilot’s display screen in the time for the aircraft to accelerate from (V R – 15) to (V R ). At speed V R switches S 2 , S 4 , S 5 , S 6 , S 7 are open and S 1 is closed by threshold circuit 17. A (- v) signal from amplifier 2 and a V D signal from potential divider 5 produce a signal (-TV-V) at the input of adder 3a. Network 4 operates on V D to add a signal VD/1 – # D, so that the total signal at the potential divider 6 represents equation (3), but the signal V D is delayed to rise exponentially with time through the rotation manoeuvre to allow and compensate for any engine failure during take-off, by applying an instantaneously lower required climbout speed which progressively approaches the full value thereof. Limiter amplifier 7 reverses the sense of Q D and limits it so that rotation is directed at a constant rate, and a minimum value to limit any nose-down tendency. An achieved pitch rate signal Q from gyro 12 is combined with Q D in adder 9a, and the difference (Q-Q D ) operates the pilot’s display and auto pilot 16; amplifier 18 being disabled by S 2 from the instant the aircraft speed reaches VR. In directing overshoot, the apparatus operates during landing approach with switch S 1 open and switch S 2 closed. Amplifier 18 applies a (-V) signal to capacitor T4, which follows and stores the airspeed signal throughout the approach. On decision to abort landing, S 1 is closed. If airspeed exceeds V R , threshold circuit 17 opens S 2 to disconnect amplifier 18 and the instantaneous airspeed signal Vi stored on T4 is transferred exponentially to adder 3a so that the speed demand signal rises exponentially from Vi to VD. The required pitch rate signal representing demanded rate of rotation from potential divider 6 and given by equation (3), and the difference signal from (Q-QD) from potential divider 13 appears on the pilot’s display and/or at the automatic pilot to direct the pull-out. If airspeed is in defect of V R , the system operates similarly to its function for normal take-off. Azimuth and bank deflections may be superimposed on the pitch director signal in the pilot’s display, the longitudinal acceleration signal may be obtained from an accelerometer, and the pitch rate signal by differentiation of the output from an attitude gyro.

GB33561/64A
1964-08-17
1964-08-17
An aircraft computing and director system for take-off and overshoot

Expired

GB1133081A
(en)

Priority Applications (1)

Application Number
Priority Date
Filing Date
Title

GB33561/64A

GB1133081A
(en)

1964-08-17
1964-08-17
An aircraft computing and director system for take-off and overshoot

Applications Claiming Priority (1)

Application Number
Priority Date
Filing Date
Title

GB33561/64A

GB1133081A
(en)

1964-08-17
1964-08-17
An aircraft computing and director system for take-off and overshoot

Publications (1)

Publication Number
Publication Date

GB1133081A
true

GB1133081A
(en)

1968-11-06

Family
ID=10354539
Family Applications (1)

Application Number
Title
Priority Date
Filing Date

GB33561/64A
Expired

GB1133081A
(en)

1964-08-17
1964-08-17
An aircraft computing and director system for take-off and overshoot

Country Status (1)

Country
Link

GB
(1)

GB1133081A
(en)

Cited By (1)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

EP1586969A1
(en)

2004-04-15
2005-10-19
Fuji Jukogyo Kabushiki Kaisha
Automatic takeoff apparatus for aircraft, automatic landing apparatus for aircraft, automatic takeoff and landing apparatus for aircraft, automatic takeoff method for aircraft, automatic landing method for aircraft and automatic takeoff and landing method for aircraft

1964

1964-08-17
GB
GB33561/64A
patent/GB1133081A/en
not_active
Expired

Cited By (3)

* Cited by examiner, † Cited by third party

Publication number
Priority date
Publication date
Assignee
Title

EP1586969A1
(en)

US8175763B2
(en)

2004-04-15
2012-05-08
Fuji Jukogyo Kabushiki Kaisha
Automatic aircraft takeoff and landing apparatus and method for accomplishing the same

US8265807B2
(en)

2004-04-15
2012-09-11
Fuji Jukogyo Kabushiki Kaisha
Automatic takeoff and landing apparatus for aircraft, and methods for performing an automatic takeoff and an automatic landing of an aircraft

Contact information