GB2080429A - Articulated propellant feed system - Google Patents

Abstract

A propellant feed system for propellant tanks in a missile body 1 to a jet propulsion unit 6 which is mounted by a universal joint, includes a joint wherein the four limbs mounted between respective yokes 2, 3 and 7, 8 have sockets providing a seal and affording angular displacement between fuel or oxydiser pipes 9, 10 from tanks and pipes 14, 15 to the propulsion unit 6. The joint core structure has internal channels connecting each feed pipe 9, 10 with respective outlet pipes 14, 15. The construction avoids flexible hose connections. <IMAGE>

Description

SPECIFICATION Propellant feed system for missiles with angularly adjustable propulsion unit This invention relates to feed of propellant or propellants from a propellant tank in a missile, for example to a propulsion unit, particularly a rocket propulsion unit, which is carried on the missile by means of a universal swivel joint so as to be angularly movable.

Known directional control systems for missiles include those in which the propulsion units is swivel mounted on the missile in an angularly movable manner and by means of a ball-andsocket type joint or a universal joint. Owing to the articulated connection provided between the missile and the propulsion unit the operation of feeding the propellants to the unit from tanks in the missile is not without its problems, particularly when large swivel angles are required. To balance out the relative movements accompanying these adjustments or the changes caused in the spacings between the injection head of the combustion chamber of the propulsion unit and the fixed propellant connections on the missile, flexible propellant transfer hoses of adequate length are installed in order to couple to the missile body to the propulsion unit across the articulated connection.Although these hoses provide the necessary angular mobility they also have a number of drawbacks. Since high specific performances are usually required in rocket propulsion units the operating system uses high combustion chamber pressures. This necessitates even higher injection pressures and therefore the use of comparatively heavy thick-walled and consequently less flexible hoses for the propellant.

This disadvantage, in its turn, calls for considerable adjustment forces to be used for the operation of pivoting the propulsion unit. Cardanic suspension rocket propulsion units with hose connections serving to convey the propellants between the missile and the propulsion units are described, for example, in DE Patent 1,153,657.

The object of this invention is to provide, for the zone of the articulated connection between the missile and the propulsion unit which is suspended in an angularly movable manner, a propellant feed in which the disadvantages of known constructions will be reduced or avoided and which will provide a saving both in over-all weight and components, in addition to which it will not require such large adjustment forces and will have a longer service life.

According to this invention there is provided propellant feed system for a propulsion unit which is carried by an angularly adjustable mount comprising a universal swivel joint wherein the or each propellant component is fed to the propulsion unit through channels in the universal joint structure.

Preferably a propellant flow channel extends from each limb forming the universal joint yoke which are fixed, to one of the two limbs of the joint forming the yoke which are secured to the propulsion unit, the channels extending inside the joint structure.

This invention provides the particular advantage that no flexible connecting hoses are required for connection across the articulated joint. The construction according to the invention is therefore lighter in weight and more reliable in operation as flexible hoses are as general principle more subject to failures and breakdowns and last for a shorter time. The elimination of flexible hoses makes it possible to derive benefit from the moderate over-all length made possible by the universal joint as it is no longer necessary to provide sufficient lengths of hose in order to allow for the considerable angular deflections, which necessitate a certain number of bends in the hose.

In a preferred embodiment the four limbs of the joint have coupling sockets, the sockets of one pair of limbs connecting with the fuel and oxidiser feed pipes from respective tanks, the sockets of the other pair of limbs connecting with the respective fuel and oxidiser feed pipes to. the propulsion unit, each socket incorporating an annular sealing means and affording relative angular movement of the feed pipes and joint structure, the joint structure including passageways connecting pairs of sockets for fuel and oxidiser feed.

The accompanying drawings show an embodiment of the invention by way of example only, and in the drawings:~ Figure 1 shows the rear end of a missile with a rocket propulsion unit pivotally mounted thereon in an angularly adjustable manner, and shown partly in longitudinal section, Figure 2 shows a section through the universal joint structure, and Figure 3 shows a view, of the rear end, of the missile shown in Figure 1 from a different angle with the propulsion unit pivoted from the longitudinal axis.

Referring to the drawings, the missile 1 houses tanks for the two propellants, fuel and oxygen and is provided with support arms 2 and 3 forming a yoke with bearings 2a and 3a, in which two mutually opposite limbs 4a and 4b of a universal joint structure 4 are rotatably mounted by means of needle bearings 5.

For the angularly movable connection between the rocket propulsion unit 6 with the missile 1 the unit 6 also has two support arms 7 and 8 (Figure 3) forming a yoke with bearing lugs 7a and 8a, which are offset in relation to the arms 2 and 3 by an angle of 900. The limbs 4c and 4d of the joint structure 4 are also rotatably mounted in the bearing lugs 7a and 8a by means of needle bearings 5.

From the propellant tank containing fuel a fixed fuel pipe 9 feeds the limb arm 4a, while a fixed oxygen pipe 10 feeds from the oxygen tank to the limb 4b of the structure 4. The end of the fuel pipe 9 of the missile which is nearer to the universal joint is rotatably mounted within a sealing ring 11 in a coupling socket 4a1 of the structure 4. The end of the oxygen pipe 10 which is nearer to the universal joint is likewise rotatably mounted within a sealing ring 11 in a connecting socket 4b1 of the structure 4.

Two angled flow channels 12 and 13 are provided inside the universal joint structure. The flow channel 12 for fuel extends from the limb 4a to the limb 4c, while the flow channel 13 extends from the limb 4b to the limb 4d of the joint structure 4. The limbs 4c and 4dare likewise provided with radial connecting sockets 4c1 and 4d1 . The end of a fuel pipe 14 on the propulsion unit which is nearer to the universal joint is rotatably coupled with the connection socket 4c1, and the end of the oxygen pipe 1 5 of the propulsion unit which is nearer to the universal joint is rotatably coupled with the connecting socket 4d1 with radial sealing rings 11.

Claims (5)

1. Propellant feed system for a propulsion unit which is carried by an angularly adjustable mount comprising a universal swivel joint wherein the or each propellant component is fed to the propulsion unit through channels in the universal joint structure.

2. Propellant feed system in accordance with Claim 1, wherein a propellant flow channel extends from each limb forming the universal joint yoke which are fixed, to one of the two limbs of the joint forming the yoke which are secured to the propulsion unit, the channels extending inside the joint structure.

3. Propellant feed system in accordance with Claim 2, wherein the four limbs of the joint have coupling sockets, the sockets of one pair of limbs connecting with the fuel and oxidiser feed pipes from respective tanks, the sockets of the other pair of limbs connecting with the respective fuel and oxidiser feed pipes to the propulsion unit, each socket incorporating an annular sea#ling means and affording relative angular movement of the feed pipes and joint structure, the joint structure including passageways connecting pair of sockets for fuel and oxidiser feed.

4. A propellant feed system substantially as herein described and with reference to the accompanying drawings.

5. A missile including a propellant feed system in accordance with any preceding claim for supply of fuel and oxidiser to a propulsion unit which is secured to the missile body through a universal swivel joint.