GB965276A - Indicator device for vertical-landing aircraft - Google Patents
Indicator device for vertical-landing aircraftInfo
- 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
Links
- 230000001133 acceleration Effects 0.000 abstract 7
- 238000007792 addition Methods 0.000 abstract 1
- 238000010276 construction Methods 0.000 abstract 1
- 239000000446 fuel Substances 0.000 abstract 1
- 230000005484 gravity Effects 0.000 abstract 1
- 230000010354 integration Effects 0.000 abstract 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
- G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- 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
- G05D1/0676—Rate 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.
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)
| 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 |
-
1961
- 1961-06-07 GB GB20532/61A patent/GB965276A/en not_active Expired
Cited By (4)
| 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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