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GB965276A - Indicator device for vertical-landing aircraft - Google Patents

Indicator device for vertical-landing aircraft

Info

Publication number
GB965276A
GB965276A GB20532/61A GB2053261A GB965276A GB 965276 A GB965276 A GB 965276A GB 20532/61 A GB20532/61 A GB 20532/61A GB 2053261 A GB2053261 A GB 2053261A GB 965276 A GB965276 A GB 965276A
Authority
GB
United Kingdom
Prior art keywords
given
acceleration
amplifier
input
maximum
Prior art date
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
GB20532/61A
Inventor
Jacques Desire Deschamps
Jean Paul Vesigot
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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.)
Filing date
Publication date
Priority claimed from FR829474A external-priority patent/FR1267275A/en
Priority claimed from FR851941A external-priority patent/FR79188E/en
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB965276A publication Critical patent/GB965276A/en
Expired legal-status Critical Current

Links

Classifications

    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05DSYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/08Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05DSYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/04Control of altitude or depth
    • G05D1/06Rate of change of altitude or depth
    • G05D1/0607Rate of change of altitude or depth specially adapted for aircraft
    • G05D1/0653Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
    • G05D1/0676Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for landing

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Navigation (AREA)

Abstract

965,276. Electric analogue calculating. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. June 7,1961 [June 9, 1960; Feb. 7, 1961], No. 20532/61. Heading G4G. [Also in Division B7] In a vertical landing aircraft, the measured values of altitude h rate of climb v, and vertical acceleration γ t , and the assumed values of the maximum lift engine thrust P and total mass m are used to compute the values of the following variables by electric anologue means:- (a) the maximum vertical acceleration obtainable, given by γ m = P/m-g, where g is the acceleration due to gravity; (b) the vertical acceleration γ, required to achieve touch down at zero rate of descent, given by γ1 = v<SP>2</SP>/2h; (c) the altitude h (γt) at which # would become zero if the instantaneous acceleration γt were maintained, given by h (γt) = - #<SP>2</SP>/2γt + h (d) the altitude h (γ m ) at which v would become zero if the maximum acceleration γ m were attained and maintained, given by h (γ m ) = v<SP>2</SP>/2γ m + h and (e) the time interval t after which h (γ m ) will no longer be positive if the instantaneous acceleration γt is maintained. A square generator supplies a signal representing v<SP>2</SP> from an input representing v,when required, and where division is necessary, it is performed as in Fig. 6. In this Figure the maximum available lift engine thrust P is computed in a device 17,from inputs representing the nominal maximum thrust, ambient temperature and pressure, and v. The output representing P is fed as one input to a high gain amplifier 19. The total mass m is computed from the take-off mass,fuel consumed, and mass of articles dropped in an amplifier 20a, the output of which forms one input of a multiplier 18. The other multiplier input is the output of amplifier 19. The high gain of the amplifier requires that the total input be very small, and thus the output is P/m = γ m + g. A signal representing -g is added in amplifier 20, to derive γ m . Other additions, multiplications, and divisions are affected similarly, except that the term v<SP>2</SP>/2γ m required for h (γ m ) is derived by controlling a potentiometer, energized by a signal representing #<SP>2</SP>,by a device computing ¢ γ m . An explicit formula for t is given, but it is computed as shown in Fig. 7, where an electronic switch feeds a sampled value of γ t to two integrators in series, which have simultaneously sampled values of v and h as initial values for the integrations, to produce outputs v (#) and h (#) where # is "accelerated" time. v<SP>2</SP>(#) is generated from #(#), and divided by 2γ m , and the result subtracted from h (#), to give h (γ m ) (#), the predicted value of h (γ m ), and the value of # is registered when h (γ m ) goes negative. This computation is repeated, say, 50 times per second,fresh samples of γ t , v, and b, being taken for each computation.
GB20532/61A 1960-06-09 1961-06-07 Indicator device for vertical-landing aircraft Expired GB965276A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR829474A FR1267275A (en) 1960-06-09 1960-06-09 Vertical landing indicator device
FR851941A FR79188E (en) 1961-02-07 1961-02-07 Vertical landing indicator device

Publications (1)

Publication Number Publication Date
GB965276A true GB965276A (en) 1964-07-29

Family

ID=26186322

Family Applications (1)

Application Number Title Priority Date Filing Date
GB20532/61A Expired GB965276A (en) 1960-06-09 1961-06-07 Indicator device for vertical-landing aircraft

Country Status (1)

Country Link
GB (1) GB965276A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2450209A (en) * 2007-06-15 2008-12-17 Boeing Co Displaying automatically controlled engine thrust information
RU207467U1 (en) * 2021-04-22 2021-10-28 Максим Владимирович Окороков The device for evaluating the reliability of technical systems with the distribution of Weibull uptime

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2450209A (en) * 2007-06-15 2008-12-17 Boeing Co Displaying automatically controlled engine thrust information
GB2450209B (en) * 2007-06-15 2009-10-14 Boeing Co Quiet climb crew interface
US8131410B2 (en) 2007-06-15 2012-03-06 The Boeing Company Quiet climb crew interface
RU207467U1 (en) * 2021-04-22 2021-10-28 Максим Владимирович Окороков The device for evaluating the reliability of technical systems with the distribution of Weibull uptime

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