DE2334295A1 - STEERABLE MISSILE - Google Patents

Description

British Aircraft Corporation Limited, London, England,

Dirigible missile

The invention relates to a steerable plug body that by Jet propulsion is moved, and in particular, a device for pivoting a nozzle at the end of the jet pipe of the jet-driven Plug body for the purpose of controlling the missile.

In accordance with one feature of the invention, a jet-propelled steerable missile includes a pivotable exhaust nozzle and a plurality of gas-actuated ones Pistons, which are connected to the nozzle and both sides of which exhaust gases can be fed continuously, whereby A gas collection chamber is assigned to each jyiroTben to keep it against a to keep enclosed Qae ^ volume, and with a valve provided which provides the ability to withdraw gas from selected gas chambers in order to make the pistons relative to the gas chambers move and swivel the nozzle.

Preferably, each gas collection chamber consists of a cylinder in which a piston is slidable and can be vented to the atmosphere via a valve which can be closed and opened upon request can.

Preferably, the nozzle has a part-spherical shell with its outer surface against a bearing near the rear end of the jet pipe is supported.

An exemplary embodiment of the invention is described below with reference to FIG Drawing described. In the drawing show:

309884/0569

ORIGINAL INSPECTED

1 shows a schematic sectional view of the missile with Swivel nozzle and the swivel drive; the nozzle is shown in the new, extral middle position,

Fig. 2 is a sectional view corresponding to Fig.l with a pivoted Jet,

Fig. 3 is a section along the line X-X according to Fig.l.

A jet pipe 1 extends from the combustion chamber (not shown) of the steerable missile 2 to the rear and carries on its outer surface an annular body 3, the four cylindrical bores 4,5,6,7, which are arranged at an angular distance of 90 ° are. On the outer surface of the part 3 is means Screws 8 fastened the front end of a casing 9, the rear end of which is pulled inwards at 10, and a carbon P gasket and a bearing ring 11 within an annular groove 12 carries.

A swivel nozzle 13 with a constriction 14 with a diameter which is smaller than the inner diameter of the jet pipe 1 is with a diverging rear section I5 and a spherical front shell shape! gen section 16 equipped. The outer surface of the shell part 16 bears against the carbon ring 11. An annular collar I7 protrudes from the shell part 16 in front and carries one end of four piston rods 18, 19, 20 and 21. Located between the jet pipe 1 and the inner wall of the casing 9 is a space 40. The four piston rods 18,19,20 and 21 are each connected to a piston 22,23,24 and 25, the inside of holes 4.5 * 6 and 7 are slidable and each of the holes is connected to the room 40 via channels 41. A part-spherical sleeve 26 is attached to the end of the jet pipe 1 so that a Annular gap 27 remains between the sleeve 26 and the inner surface of the shell part l6.

In the base of each bore 4, 5, 6 and 7 there is a channel 28, 29, 30 and 31 and on the annular body 3 are electromagnetic

309884/0569

ORIGINAL INSPECTED

te 32,33,34 and 35 so arranged that their anchors 36,37,38 and 39 are aligned with channels 28,29,30 and 3I, which terminate them, when the anchors are advanced. The electromagnets are electric connected to a control device, not shown and channels 28,29,30 and 3I can be energized and de-energized, respectively the electromagnet. opened or closed.

If the missile moves in a straight plug, then most of the exhaust gases leaving the jet pipe 1 flows to the atmosphere through the divergent section 15 of the nozzle I3. The remaining part of the gas flow is diverted through the space 27 into the space 40, so that the gas flow acts uniformly everywhere on the pistons 22, 23, 24 and 25. The channels 31 are all open and the pressures in the BohrUngej ^ jiepPBnd 7, which are fed with gas from the space 40 ^^ jjeBP ^^ easy, so that the nozzle I3 is a middle positioneüMejjjHpiJ ^^ pressure in these holes is half as great ^the nozzle I3 gaflj ^ ^ ^r i HBPW ^läGhen | wi ^ jjeBpWnRaum ^4o · At the same time, the gas also acts au. Therefore, there is niflgjjflj ^^^^ HPBrcnwise low total load according to ^^^^ BP ^ * 6 on the sealing ring 11

To change the flight direction of the missile, the openings of the channels 28,29,30,31 through the magnet 32,33,34,35 controlled, whereby the pressure in the bores 4,5,6 and 7 is changed. The combined effect of the pistons. 22, 23, 24 and 25 causes that the nozzle 13 is pivoted and the direction of flight of the missile is changed accordingly.

The force exerted by the shell section 16 on the ring 11 is due to the force on the back surfaces of the colon 22, 23, 24 and 25 acting gas pressure and constantly weakened as a result of the balancing effect of the load on the inner surfaces of the nozzle I3 gas. Accordingly, only a very small force is required to

309884/0569

ORlQfNAt INSPECTED

to swivel the nozzle. Only a very small flow of the exhaust gases through the gap 27 and into the space 40 is required, the carbon ring 11 preventing gas from escaping past the nozzle.

Instead of the electromagnets, other control devices can also be used for the gas flow through the channels 28,29,30 * 31 can be used. For example, servomotors could be used.

The invention provides a swivel control nozzle for a jet-driven Guided missiles created, wherein the frictional forces are low and only a low performance is already a satisfactory Working method guaranteed.

Claims

309884/0569

Claims (1)

. 5 - claims: 1. ^ Beam-driven steered plug body with a swiveling ^ "^^ exhaust nozzle, characterized in that a plurality of gas operated pistons are connected to the nozzle, the are continuously exposed to exhaust gases on both sides, that gas collection chambers are assigned to each piston, whereby each piston is held against an enclosed gas volume, and in that a valve is provided for each piston for selectively venting gas from a gas chamber, whereby the pistons be caused to move relative to the gas chambers, whereby a pivoting movement of the nozzle begins. . 2. plug body according to claim 1, characterized gekennzeichne t, _v that each vapor collection chamber from eijjg p ^^ Linder consists, in which the pistons slide Karin ^ jpiArci it is feaiifffidftbar cylinder through a valve according to the Atmosphay ^ and the valves odgp ^ can be esch lossen selectively opened. ;}. Plug body according to claims 1 or 2, characterized, that the nozzle has a part-spherical shell portion, the outer surface of which against a bearing adjacent to the rear End of the missile is supported. 4. Missile according to claim 5, characterized in that the nozzle is fed via a jet pipe which has a partially spherical shape Has section which, together with the part-spherical shell section, has a channel for the passage of the Exhaust gases form after the piston. 309884/0563 ORIGINAL INSPECTED Blank page ORIGINAL INSPECTED