US3150486A

US3150486A - Cooled reaction control device

Info

Publication number: US3150486A
Application number: US264004A
Authority: US
Inventors: Heinrich J Hollstein; Raymond J Novotny
Original assignee: Individual
Current assignee: Individual
Priority date: 1963-03-08
Filing date: 1963-03-08
Publication date: 1964-09-29
Anticipated expiration: 1981-09-29

Description

Sept. 29, 1964 H. J. HOLLSTEIN ETAL 3,150,486

COOLED REACTION comm. DEVICE Fi led March 8, 1963 2 Sheets-Sheet 1 p 'IIIII/L INVENTORS HEINRICH J. HOLLSTEIN RAYMOND J. NOVOTNY A 7' TOR/VE Y Sept. 29, 1964 H. J. HOLLSTEIN ETAL 3,150,486

coouan REACTION CONTROL DEVICE INVENTORS HEINRICH J. HOLLSTEIN RAYMOND J. NOVOTNY Fig. 3 9: r2 1 )4 A7 TOR/VE;

United States Patent 3,150,486 UGQLED REACTION CONTROL DEVICE Heinrich J. Hollstein, Los Altos, Calif., and Raymond J.

Novotny, Uwehland, Pa., assignors, by mesne assignrnents, to the United States of America as represented by the ecretaryof the Navy Filed Mar. 8, 19%, 'Ser. No. 264,004 8 Claims. (Cl. elk-35.54)

This invention relates to reaction control devices, and more particularly to a cooled reaction control device for rocket engines which can sustain higher nozzle exhaust temperature conditions.

It is well established that missiles requiring low gs or operating in altitudes above 300,000 feet are unable to utilize aerodynamic forces for fiightcontrol. Instead, auxiliary reaction control devices have been devised to deflect the primary rocket thrust. Such reaction control devices have taken the form of gimbaled motors and.

nozzles, fluid injection devices, jetevators, and jet vanes. The present invention is an improvement in the vane-type of reaction control devices, sometimes referred to as jetetabs.

While the vane-type reaction control device is generally suitable for most applications, with the advent of newly developed propellants, such as the aluminized base type, the need became apparent for a vane construction permitting operation in higher temperature environments, for example 6200 F. or more. Uncooled jetevators made of presently known and available refractory metals have not been found capable of withstanding nozzle temperatures above 5600 F. for any appreciable time.

The present invention provides a thrust control device capable of withstanding higher temperature rocket chamber conditions by means of a novel concept of cooling the critical impinged surfaces. This is achieved by using a hollow control surface having vent openings adjacent the criticalsurfaces. Within the hollow control surface is a source of a coolant having a high heat-absorption capability, which when heated vaporizes and is gradually discharged through the vent openings thereby cooling the surfaces.

One object of this invention is to provide a control surface capable of withstanding higher jet exhaust temperatures.

Another object is to provide in such a control surface an improved radiation mode of heat transfer.

Still a further object is to cool a control surface through a metal coolant capable of vaporizing and being exhausted from the surface to be cooled.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

FIG. 1 is a cross-sectional view of a conventional jet nozzle showing the typical shock pattern created; by a jet vane type ofcontrol;

FIG. 2 is a perspective View of a multiple nozzle end of one type of missile on which the jet vane of this invention may be employed;

FIG. 3 is an end view of the jet vane showing the vapor exhaust openings;

FIG. 4- is a longitudinal sectional View of the jet vane taken along line lV-IV of FIG. 3;

FIG. 5 is a cross-sectional view of the jet vane cap taken along V-V of FIG. 4; and

I FIG. 6 is a partial sectional view of a modified sectional jet vane cap.

Referring to the drawing where like reference numerals refer to similar parts throughout the drawing there is shown in FIG. 1 an exhaust nozzle ltl having a typical 3,150,486 Patented Sept. 29, 1%64 configuration for a rocket engine, not shown. A jet vane 12, sometimes referred to as a jetetab, is mounted on the nozzle or associated structure, being arranged to project into, and deflect, the nozzle exhaust flow to achieve thrust vector control. The jet vane configuration illustrated in the drawing is of the type that lies in the nozzle exit plane, although, depending on the required performance, it could be positioned beyond said plane, such as in a jetevator type, or it may be positioned within, or protrude through the wall of the nozzle, such as in the sector type of jet vane. The illustrated arrangement of the jet vane creates two shockwaves within the nozzle, a normal shock wave represented by line A and a oblique shock represented by line B, and the values of pressure and Mach number will vary in each of the three areas created in the nozzle. v

The improved jet vane of this invention is illustrated at 14 in FIG. 2 as bein applied to a missile it; of a type having four exhaust nozzles 1'7, each vane being located between adjacent nozzles. For this application, each jet vane-14 is designed to be rotatable in and out of the exhaust path of adjacent nozzles, but this feature forms no part of this invention nor should it be construedas a limitation to the use of the present invention.

Referring to FIGS. 3 to 6 inclusive, jet vane 14 comprises four basic parts, namely, an L-shaped support structure 18, a shoe 20, a heat sink 22, and a cap 24.

, Support structure 18 consists of a mounting shaft portion 26, having a longitudinal axis parallel to the longitudinal axis of the nozzle by which the jet vane is threadly or otherwise secured, either rotatably or fixed, to the nozzle or surrounding structure 27 such as a flame guard in a suitable manner. A transversely extending portion 28 of the support structure forms a base for shoe 20. Support structure 13 is suitably fabricated of a nickel or cobalt base steel alloy (lnconel X etc). Shaft portion 26 is constructed hollow to form a cylinder 30 to serve as a storage reservoir for a suitable coolant 32 having a high heat-absorption quality, such as lithium, lithium hydride and other similar alkali metals and coolants, for a purpose later to be described. An amount in the order of 10 cubic inches of coolant can be stored in the jet vane. Cylinder Bil is filled through access plug 33 with molten coolant which solidifies at room temperature. When cap 24 is heated by the rocket nozzle exhaust flow, the coolant melts in a flowable condition. Slidably disposed within the cylinder 30 at one end is a piston 34 which is capable of applying a pressure on the coolant in the cylinder when actuated by gas pressure from a gas generator 36 located on the side of the piston opposite the coolant. Generator 34 can be electrically energized by conductors 38 through a remote control, not shown.

Shoe 20 forms the back portion of the jet vane when supported in the nozzle exhaust stream. The shoe is preferably constructed with tapered side walls 39 which have been found to decrease aerodynamic hinge moments. The shoe is recessed at 46 to seat transverse portion 28 of the supporting structure, a portion of the shoe extending around the shaft portion 26. Shoe 20 can be fabricated of a chopped Fiberite or Astrolite-type material since it is in an area not subject to critical temperatures and may be bonded to the support structure.

Cap 24- is supported to shoe 20 through heat sink 22, the latter being constructed of pyrolytic graphite or the like, for example, in the order of one or more inchesthe increased thicknesses decreasing substantially the surface temperature of the cap while reducing the overall weight of the jet vane. Heat sink 22 has a high thermal capacity to supplement heat absorption of the coolant system. The heat sink is recessed at 42 to accommodate anchored in bosses 47 formed integral with the cap. The washers 4d permit structural and thermal distortion of the parts. The face portion 49 of cap 24, being directly in the path of the hot impinging exhaust flow, represents the most critical surface of the jet vane subjected to the high temperatures and edge erosion effects. Cap 24- has an extending portion which forms a protective sleeve 48 surrounding the shaft structure, sleeve 43 terminating in a flange 51 which is adapted to abut nozzle supporting structure 27. The most satisfactory material for the cap in the temperature ranges to be encountered has been found to be tungsten, particularly when infiltrated with copper; the latter decreasing thermal shock sensitivity, increasing mechanical strength and acting as a coolant.

It has been observed that the heat sink 22 in itself cannot dissipate suflicient heat to which the jet vane is subjected to prevent destruction by the high temperature encountered. In accordance with the present invention an additional heat dissipating means is provided which utilizes the stored coolant 32. Cap 24 is provided with a coolant passage t) along the hollow rim portion 5111, the latter provided with a plurality of laterally directed spaced ports 52 around the rim for the escape of the vaporized coolant in a manner to be described. Like shoe 2d and heat sink 22, the outer side wall of the rim portion is tapered at 53. Coolant passage 59' is connected to cylinder 39 through sealed passages 54 and 56 in the heat sink and supporting structure 23, respectively. An orifice 58 is positioned between passage 56 and cylinder 3t). As is cylinder 30, the interconnecting passages may also be filled with molten coolant 32 which solidifies at room temperatures. Cap 24 can be fabricated as a onepiece construction as illustrated in FIGS. 3-5 inclusive, or a two-piece construction as illustrated in FIG. 6 wherein the rim is in a U-shaped construction of) separate from the fiat cap surface 62 and is secured together in overlapping relation.

The novel cooling concept for the jet vane is carried out in the following manner. Immersion of the jet vane into the exhaust stream of the rocket motor heats the cap and surrounding structure causing coolant 32 contained therein to melt. The cap soon reaches a temperature that causes the coolant in rim passage 5% to vaporize and be discharged through ports 52. Simultaneously gas generator 36 pressurizes piston 34 which is forced against the coolant 31; in the cylinder now in a liquid condition. Movement of piston 34 gradually extrudes the reserve coolant in cylinder 36 through orifice 58, which meters the flow, into the passages 55 and 54, and into rim passage Sii to replace the coolant that is released in the form of vapor through ports 52. Sufficient coolant can be provided throughout the period that the jet vane is designed to function.

According to the present invention an increased heat absorption quality of the conventional jet vane is accomplished by allowing the vaporizing of a coolant at a critical temperature surface. A supply of the coolant is stored in the jet vane with means provided for replacing the coolant that is so dissipated. This novel cooling concept enables the jet vane to withstand higher jet e1.- haust gas temperatures without a sacrifice of Weight or size. This design permits the jet vane to be of the rotatable or fixed-position type and usable on many different applications.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise that as specifically described.

We claim:

1. A jet vane for deflecting rocket motor exhaust flow to achieve thrust vector control comprising:

(a) a face member having a plurality of openings extending therethrough into the exhaust flow; a heat sink member secured to the face member;

(b) means at one end of the vane for supporting the face member in the exhaust flow to be impinged thereby;

(c) said support means provided with means for storing a source of a coolant having a high heat-absorption capability; and

(:1) means for discharging vaporized coolant from said source through said openings to dissipate the heat load on the face member.

2. A jet vane for deflecting rocket motor exhaust flow to achieve thrust vector control comprising:

(a) a face member; a heat sink member secured to the face member;

(12) means at one end of the vane for supporting the face member in the exhaust flow to be impinged thereby;

(c) said face member having a coolant passage provided with vent apertures open to outside the vane;

(d) said jet vane provided with means for storing a source of a coolant for said passage having a high heat-absorption capability; conduit means extending from the coolant source to said passage; and

(e) whereby vaporized coolant can be discharged from said passage vents to dissipate the heat load on the face member.

3. A jet vane for deflecting rocket motor exhaust flow to achieve thrust vector control comprising:

(a) a face member;

(b) means for supporting the face member in the exhaust flow to be impinged thereby; said jet vane provided with means for storing a source of coolant having a high heat-absorption capability;

(c) said face member having a coolant passage around the rim provided with vent apertures open to outside the vane;

((1) means for applying a pressure on said coolant in the source to replace the vaporized coolant discharged from said passage vents to dissipate the heat load on the face member; and

4. A jet vane for deflecting rocket motor exhaust flow to achieve thrust vector control comprising:

(a) a face member; a heat sink member secured to the face member;

(b) means at one end of the vane including a hollow shaft for supporting the face member in the exhaust flow to be impinged thereby;

(d) said hollow shaft filled with a sourcc of a coolant having a high heat-absorption capability;

(e) conduit means between said hollow shaft and the coolant passage and extending through the heat sink member for the flow of the coolant; and

(f) whereby vaporized coolant can be discharged from said passage vents to dissipate the heat load on the face member.

5. A jet vane for deflecting rocket motor exhaust flow to achieve thrust vector control comprising:

(a) a face member;

(b) means including a hollow shaft for supporting the face member in the exhaust flow to be impinged thereby;

(c) said face member having a coolant passage provided with vent apertures open to outside the vane; (d) means for metering the coolant flow from the hollow shaft to the passage;

(e) said hollow shaft filled with a source of a coolant having a high heat-absorption capability; and

(1) whereby vaporized coolant can be discharged from said passage vents to dissipate the heat load on the face member.

6. A jet vane for deflecting rocket motor exhaust flow to achieve thrust vector control comprising:

(a) a face member;

(c) said face member having a coolant passage along a rim portion provided with vent apertures open to outside the vane;

(d) said hollow shaft filled with a source of a coolant having a high heat-absorption capability;

(e) conduit means connecting said hollow shaft and the coolant passage for the flow of the coolant;

(f) a piston located in the hollow shaft;

(g) gas generating means located behind said piston for applying a pressure through said piston on the coolant stored in the hollow shaft; and

(h) whereby vaporized coolant can be discharged from said passage vents to dissipate the heat load on the face member.

7. A jet vane for deflecting rocket motor exhaust flow to achieve thrust vector control comprising:

(a) a cap member adopted to face said exhaust flow;

(b) a shoe member;

(c) a heat sink member secured between said cap member and the shoe member;

(:1) means for supporting said members in the ex haust flow;

(e) said support means including a hollow shaft having a longitudinal axis parallel to the longitudinal axis of said nozzle;

(f) said cap member having a coolant passage along a rim portion provided with vent apertures open to outside the vane;

(g) conduit means connecting said hollow shaft and the coolant passage for the how of the coolant; (It) said hollow shaft, conduit means and coolant passage all being filled with a coolant having a high heat-absorption capability and being in a solid form at room temperature; and

(1') means for pressurizing said coolant supply in the hollow shaft for replacing the vaporized coolant dis charged from said vents dissipate the heat load on the cap member.

8. A jet vane for deflecting rocket motor exhaust flow to achieve thrust vector control comprising:

(a) a cap member adapted to lie in the exit plane of said nozzle and face said exhaust flow;

(17) a shoe member;

(c) a heat sink secured between said cap member and the shoe member;

(d) L-shaped means for supporting said members in the exhaust flow including one portion lying between said shoe member and the sink member, and another portion being a hollow shaft;

(e) said cap member having a coolant passage formed along the rim portion provided with laterally directed vent apertures open to outside the vane;

(1) conduit means connecting said hollow shaft and the coolant passage and extending through said one portion of the support means and said heat sink;

(g) a valve in said conduit means for metering the flow of coolant;

(h) a piston positioned in said hollow shaft;

(i) gas generating means for applying a force on said piston;

(j) said hollow shaft, conduit means, and coolant passage all being filled with a coolant having a high heat-absorption capability and being in a solid form at room temperature; and

(k) whereby the vaporized coolant discharged from said vents to dissipate the heat load on the cap member is replaced by coolant from said hollow shaft.

References Cited in the file of this patent UNITED STATES PATENTS 2,692,475 Hull Oct. 26, 1954 2,919,546 David Jan. 5, 1960 3,026,806 Runton et al Mar. 27, 1962

Claims

1. A JET VANE FOR DEFLECTING ROCKET MOTOR EXHAUST FLOW TO ACHIEVE THRUST VECTOR CONTROL COMPRISING: (A) A FACE MEMBER HAVING A PLURALITY OF OPENINGS EXTENDING THERETHROUGH INTO THE EXHAUST FLOW; A HEAT SINK MEMBER SECURED TO THE FACE MEMBER; (B) MEANS AT ONE END OF THE VANE FOR SUPPORTING THE FACE MEMBER IN THE EXHAUST FLOW TO BE IMPINGED THEREBY; (C) SAID SUPPORT MEANS PROVIDED WITH MEANS FOR STORING A SOURCE OF A COOLANT HAVING A HIGH HEAT-ABSORPTION CAPABILITY; AND (D) MEANS FOR DISCHARGING VAPORIZED COOLANT FROM SAID SOURCE THROUGH SAID OPENINGS TO DISSIPATE THE HEAT LOAD ON THE FACE MEMBER.