GB952333A - Improvements in and relating to the linking of twin-component aviation systems - Google Patents

Improvements in and relating to the linking of twin-component aviation systems

Info

Publication number
GB952333A
GB952333A GB13030/60A GB1303060A GB952333A GB 952333 A GB952333 A GB 952333A GB 13030/60 A GB13030/60 A GB 13030/60A GB 1303060 A GB1303060 A GB 1303060A GB 952333 A GB952333 A GB 952333A
Authority
GB
United Kingdom
Prior art keywords
aeroplane
platform
pitch
roll
demand signals
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
GB13030/60A
Inventor
Anthony Thomas Frederi Simmons
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.)
English Electric Co Ltd
Original Assignee
English Electric Co Ltd
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
Application filed by English Electric Co Ltd filed Critical English Electric Co Ltd
Priority to GB13030/60A priority Critical patent/GB952333A/en
Priority to FR10647A priority patent/FR1286237A/en
Publication of GB952333A publication Critical patent/GB952333A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D3/00—Aircraft adaptations to facilitate towing or being towed
    • B64D3/02—Aircraft adaptations to facilitate towing or being towed for towing targets
    • 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
    • G05D1/10—Simultaneous control of position or course in three dimensions
    • G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
    • G05D1/104—Simultaneous control of position or course in three dimensions specially adapted for aircraft involving a plurality of aircrafts, e.g. formation flying

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

952,333. Controlling composite aircraft. ENGLISH ELECTRIC CO. Ltd. April 5, 1961 [April 12, 1960], No. 13030/60. Headings B7G and B7W. [Also in Division H4] Relates to a system for landing a conventional aeroplane 1 with the aid of a piloted flying platform 2 capable of vertical take-off and landing and of horizontal flight at a speed exceeding the normal stalling speed of the aeroplane 1 in which the platform 2 is flown upwards towards the aeroplane 1 from a position below and astern thereof to a position in which contact is made with the wheels of the aeroplane 1, sufficient force is applied thereto to take the full weight of the aeroplane, an automatically or manually controlled lock-on gear secures the aeroplane to the platform and the platform carrying the aeroplane is then landed vertically. According to the present invention an optical or near optical radiation source A is mounted underneath the aeroplane 1, two transversely spaced directional sensing heads B1 and B2, Figs. 1 and 2, on the platform 2 are directed at the source A and means are provided for deriving from the longitudinal component # 1 , Fig. 1, and the lateral components # 1 , # 2 of the sighting angles of the heads B 1 and B 2 the pitch, roll and thrust demand signals required to fly the platform 2 to the aeroplane 1, the pitch and roll demand signals # and # being applied to an automatic pilot and the incremental forward thrust demand signal #T being applied to a flight director display. As described with respect to Figs. 4, 5 and 6 (not shown), the demand signals are computed in accordance with the equations where A, B ... G are constants, the pitch and roll ratio d#/dt and d#/dt are measured by rate gyros and a is the forward acceleration. Each sensing head may comprise an auxiliary reflector near the focus of a main parabolic reflector and a radiation sensitive cell at the centre of the main reflector, Fig. 3 (not shown).
GB13030/60A 1960-04-12 1960-04-12 Improvements in and relating to the linking of twin-component aviation systems Expired GB952333A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB13030/60A GB952333A (en) 1960-04-12 1960-04-12 Improvements in and relating to the linking of twin-component aviation systems
FR10647A FR1286237A (en) 1960-04-12 1961-04-11 Connection device for composite aircraft installations

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB13030/60A GB952333A (en) 1960-04-12 1960-04-12 Improvements in and relating to the linking of twin-component aviation systems

Publications (1)

Publication Number Publication Date
GB952333A true GB952333A (en) 1964-03-18

Family

ID=10015532

Family Applications (1)

Application Number Title Priority Date Filing Date
GB13030/60A Expired GB952333A (en) 1960-04-12 1960-04-12 Improvements in and relating to the linking of twin-component aviation systems

Country Status (2)

Country Link
FR (1) FR1286237A (en)
GB (1) GB952333A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5465923A (en) * 1992-07-25 1995-11-14 British Aerospace Plc Vertical take-off/landing of aircraft

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1028676A (en) * 1963-06-24 1966-05-04 British Aircraft Corp Ltd Improvements in and relating to the aligning of twin-component aviation systems in flight
US3285544A (en) * 1964-02-26 1966-11-15 Industrial Nucleonics Corp Mid-air refueling system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5465923A (en) * 1992-07-25 1995-11-14 British Aerospace Plc Vertical take-off/landing of aircraft

Also Published As

Publication number Publication date
FR1286237A (en) 1962-03-02

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