GB908570A - Improved system for guiding and landing aircraft - Google Patents
Improved system for guiding and landing aircraftInfo
- Publication number
- GB908570A GB908570A GB32096/60A GB3209660A GB908570A GB 908570 A GB908570 A GB 908570A GB 32096/60 A GB32096/60 A GB 32096/60A GB 3209660 A GB3209660 A GB 3209660A GB 908570 A GB908570 A GB 908570A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- vector
- centre
- horizontal
- spot
- 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
- 238000013459 approach Methods 0.000 abstract 2
- 230000007423 decrease Effects 0.000 abstract 1
- 230000011664 signaling Effects 0.000 abstract 1
Classifications
-
- 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, 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Computer Networks & Wireless Communication (AREA)
- Traffic Control Systems (AREA)
Abstract
908,570. Signalling apparatus for aerial navigation. MESSERSCHMITT A.G. Sept. 19, 1960 [Sept. 19, 1959], No. 32096/60. Class 118. [Also in Group XL (c)] In a system for guiding a vertical take-off and landing aircraft on to a landing area during the final phase of a blind approach from any direction, a rotationally symmetrical magnetic field is produced by feeding a circular or cylindrical coil (Fig. 1) under the surface of the airfield with direct or alternating current (up to 400 c.p.s.), and means is provided in the aircraft for evoluating the field intensity vector at the existing location of the aircraft above the landing area. If the aircraft is outside the axially symmetrical funnel shown in Fig. 1, the vector will have an upwardly directed component which changes continuously to a down; ward component as the aircraft penetrates the funnel and becomes progressively larger as it approaches the axis of the field until, on the axis, the vector points vertically downward. A voltage proportional to the angle of inclination of the field vector to the horizontal may be applied to the deflection coils of a cathode-ray tube so that the light spot will be exactly in the centre of the screen when the vector points vertically downwards and progressively further from the centre as the angle of inclination decreases, until when the vector is horizontal, the spot will be at a well-defined distance from the centre. If the direction of movement of the light spot is also arranged to indicate the direction of the aircraft's movement, then the line joining all points at which the vector is horizontal will be a circle (Fig. 3) and if the light spot is outside this circle, as at A, the pilot will know that he is outside the funnel (of Fig. 1) and will continue to manoeuvre the aircraft until the spot is at B. A precision altimeter (of any known type) is necessary in the aircraft to permit the pilot to bring the aircraft down at a rate appropriate to its altitude at any time.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM42792A DE1110020B (en) | 1959-09-19 | 1959-09-19 | Landing aid procedure for aircraft taking off and landing perpendicularly in the final phase of a blind landing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB908570A true GB908570A (en) | 1962-10-17 |
Family
ID=7304472
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB32096/60A Expired GB908570A (en) | 1959-09-19 | 1960-09-19 | Improved system for guiding and landing aircraft |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE1110020B (en) |
| GB (1) | GB908570A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109782791A (en) * | 2017-11-14 | 2019-05-21 | 长城汽车股份有限公司 | A kind of landing method and device of unmanned plane |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1276456B (en) * | 1964-06-22 | 1968-08-29 | Guiseppe Panerai | Optical landing aid for helicopters |
-
1959
- 1959-09-19 DE DEM42792A patent/DE1110020B/en active Pending
-
1960
- 1960-09-19 GB GB32096/60A patent/GB908570A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109782791A (en) * | 2017-11-14 | 2019-05-21 | 长城汽车股份有限公司 | A kind of landing method and device of unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| DE1110020B (en) | 1961-06-29 |
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