GB1269272A - Improvements in multi-stage rockets - Google Patents

Improvements in multi-stage rockets

Info

Publication number
GB1269272A
GB1269272A GB2810269A GB2810269A GB1269272A GB 1269272 A GB1269272 A GB 1269272A GB 2810269 A GB2810269 A GB 2810269A GB 2810269 A GB2810269 A GB 2810269A GB 1269272 A GB1269272 A GB 1269272A
Authority
GB
United Kingdom
Prior art keywords
rocket
control surfaces
controls
jet
stage
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
GB2810269A
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 DE19681703534 external-priority patent/DE1703534C/en
Application filed by Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of GB1269272A publication Critical patent/GB1269272A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Abstract

1,269,272. Rockets. MESSERSCHMITTBOLKOW-BLOHM G.m.b.H. 3 June, 1969 [6 June, 1968], No. 28102/69. Heading B7G. [Also in Division F3] A multi-stage rocket 10 has a single servo unit 16 which is connected to the controls 18, 26 of first and second stages, one of the stages having jet controls 26. In a two-stage tandem arrangement, servo unit 16 controls aerodynamic control surfaces 18 on a second stage cruising rocket 13 and also, through detachable mechanical transmission elements 20, 22 and 23, jet reaction control surfaces 26 on a launching rocket 11. In a second embodiment, Fig. 2 (not shown), parallel launching rockets (34, 35) are clustered around a cruising rocket (33) and held fixed by means of a ring 37, Fig. 3. The servo unit 16 controls aerodynamic control surfaces 18 and also via transmission rods 22, jet reaction control surfaces 39 in the cruising rocket jet. When the launching rockets (34, 35) are burnt out they are separated by blowing off the ring 37 and the transmission rods 22 are also separated.
GB2810269A 1968-06-06 1969-06-03 Improvements in multi-stage rockets Expired GB1269272A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19681703534 DE1703534C (en) 1968-06-06 Missile with mechanically coupled jet and air rudders

Publications (1)

Publication Number Publication Date
GB1269272A true GB1269272A (en) 1972-04-06

Family

ID=5688462

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2810269A Expired GB1269272A (en) 1968-06-06 1969-06-03 Improvements in multi-stage rockets

Country Status (3)

Country Link
CH (1) CH480614A (en)
FR (1) FR2010278B1 (en)
GB (1) GB1269272A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2159476A (en) * 1984-06-01 1985-12-04 Messerschmitt Boelkow Blohm A control mechanism for an aircraft

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IL79864A (en) * 1985-11-25 1994-05-30 Hughes Aircraft Co Detachable vector thrust mechanism for an aeronautical vehicle
DE4300761A1 (en) * 1993-01-14 1994-07-21 Erno Raumfahrttechnik Gmbh Control device

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2159476A (en) * 1984-06-01 1985-12-04 Messerschmitt Boelkow Blohm A control mechanism for an aircraft

Also Published As

Publication number Publication date
CH480614A (en) 1969-10-31
DE1703534B1 (en) 1972-07-13
FR2010278A1 (en) 1970-02-13
FR2010278B1 (en) 1975-11-21

Similar Documents

Publication Publication Date Title
GB1085619A (en) Gas turbine engine
GB982440A (en) Rocket propelled missile
GB1009269A (en) Improvements in or relating to aircraft
GB1269272A (en) Improvements in multi-stage rockets
GB1235922A (en) Projectile with annular fin assembly
FR2367659A2 (en) Arrangement of control jets of a guided missile - uses two groups of jets for increased gain of servo control
GB961001A (en) Improvements in propulsion units having a plurality of reaction propulsion nozzles
GB1337404A (en) Solid propellant propulsion unit
CA614258A (en) Jettisonable end cone for aircraft rocket missile pods
BAUERFEIND Effects of the fuel-control system upon the thrust characteristic of a single-shaft jet engine
CLEVENSON Payload vibration of a two-stage solid-propellant launch vehicle during flight
ROUSSEL The Diamant B-P 4 launch vehicle(Program objectives and propulsive, equipment case, attitude control, interstage, separation skirt and nose cone subassemblies of French Diamant B-P 4 launch vehicle)
CONRAD et al. A control system for reducing the dispersion of multi-stage sounding rockets(Coast phase control system for reducing trajectory dispersion and shaping trajectories of Nike-Apache sounding rocket vehicle)
SMOOT Interstage pressure and separation time for solid propellant multistage rockets
STRELNITSKY et al. On the nature of high velocities of H 2 O sources in W 49(Dynamic instability of high radial velocity dispersion system for H 2 O sources in W 49)
HARWIT et al. Infrared observations of diffuse backgrounds(Rocket infrared observations of interplanetary media and submillimeter observations of night sky emission)
ES246249A1 (en) Intensive ignition rocking motor with rear and reverse front nozzles. (Machine-translation by Google Translate, not legally binding)
JAMES Flight demonstration of a nose-mounted rotating-solid-propellant rocket control system and a comparison with analog studies(Flight test of nose mounted rotating solid propellant rocket attitude control system for space vehicle second stage)
CA651423A (en) Turbo jet fuel control with emergency system
RAINE The effect of system requirements on ballistic and hardware design(System requirements effect on ballistic and hardware design of cast double-base solid propellant rocket motors)
Moehring Fuel Control System of General Electric Ge 4 Engine for the Boeing 2707 Supersonic Transport
DWORK Payload coning angle change due to stage separation of a spin-stabilized rocket
QUINN Compact thrust augmentors for V/STOL aircraft(propulsion system configuration for V/STOL and cruise flight using one engine)
SCHAFFER The load stresses on aircraft at the speed of sound and supersonic speeds investigated by flight simulation
AU289032B2 (en) Aircraft gas turbine powerplants