US2694898A - Device for deflecting a high-speed jet of gas ejected through a nozzle - Google Patents
Device for deflecting a high-speed jet of gas ejected through a nozzle Download PDFInfo
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- US2694898A US2694898A US109112A US10911249A US2694898A US 2694898 A US2694898 A US 2694898A US 109112 A US109112 A US 109112A US 10911249 A US10911249 A US 10911249A US 2694898 A US2694898 A US 2694898A
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- nozzle
- interceptor
- jet
- deflecting
- supersonic
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- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 8
- 238000011144 upstream manufacturing Methods 0.000 description 6
- 230000009471 action Effects 0.000 description 5
- 229910052742 iron Inorganic materials 0.000 description 4
- 230000009189 diving Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 241001131927 Placea Species 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/90—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using deflectors
Definitions
- the present invention relates to a particularly simple and economical device Which 'is readily adaptable to any actuating member andwhich, owing to the rapidity with which it canchange its position due to-its small mass and its reduced movements, can housed-for progressively deviating a jet issuing from'the *nozzle of a jet motor with a view to producing powerful'overall torques for the piloting of an aircraft, with the minimum of power consumption and themaxirhum-of 'res'pon siveness, by the instantaneous alteration of the-,-pr'essure distribution along the wallis'of the. nozzle;
- the present invention relates to a deflecting-device that obviates the above-mentioned”drawbacks,since it enables considerable deflections, of" the orderofinagnitude of several angular degrees, to be” effected in a "highspeed jet of gas while using movable parts of only small mass and-only'employingsmallforces'compared to the result obtained
- the device according to the present invention is essentially characterized by the 'fact' that, it comprisesat least one interceptor which is made-to penetrate by means of a suitable actuating system-into the-'stream
- Figs. 1a and lb show longitudinal sections of a nozzle provided with a device according to the invention, for two different positions of the interceptor.
- Figs. 2a and 2b respectively, show a longitudinal section and an end view of another embodiment of the invention.
- Fig. 3 shows a system for actuating the interceptor.
- Fig. 4 shows another embodiment of the invention.
- Figs. 5 and 6 illustrate, respectively in longitudinal section and in end view, a device for controlling the interceptor.
- Figs. 7 and 8 illustrate, respectively in longitudinal section and in end view, another embodiment of the contrcl device for the case where two interceptors are pro- W e
- Fig. 9 illustrates diagrammatically the resultant forces where the interceptor is introduced at a small angle as heretofore proposed by others, and
- Fig. 10 illustrates diagrammatically the resultant forces where the interceptor is introduced at right angles within the supersonic jet as per the present invention.
- a nozzle 1 In the wall of a nozzle 1 an opening is provided through which is adapted to move an interceptor 2 of any suitable shape.
- This obstacle changes thedistribution of the pressure's: along the correspondin g wall of the nozzle, "thereby producing both atransverse force applied .to said nozzle and :a deflection-of the jet issuing therefrom.
- Figs. 2 show a modification wherein ;the interceptor is located outsidethe nozzle;
- the high speed of the jetof-gas which may be below or above the speed of sound, makes it :possibleto reduce considerably the response-lagof aerodynamic origin, as compared with similar control surfaces which are subjccted only to-the wind-produ'ced-by the'flight-of'the aircraft; Furthermore, the action of the device obviously depends little on the speed of :flight';
- Another advantage of the-arrangementproposed is that, so long as no defie'ction 'is required, the interceptor remains outside the jet "of gas which may be at high temperature andbe moving at very high velocity consequently; the interceptor-isless liable to damage than 'the known system of deflecting flaps which are adapted to move about an axis at right angles to that 'offthe nozzle and 'arcconstantly immersed in the fluid stream.
- the intercepting surface 2, which is-l'o'eated, in this example, behindthe nozzle 1,. is integral with an arm-6 whiclrmay rotate about the shaft 7. This arm is normally maintained'in the retracted position of the interceptor, by means of a spring 8.
- a lever 9 at the end of the shaft 7 is engaged by the rod 10 which is unitary with an iron member 11 adapted to be attracted by the electromagnet 12.
- Figs. 7 and 8 show the case where two interceptors are provided. These interceptors 2 and 2a are secured to the ends of a resilient blade 21 secured to a member integral with the nozzle 1.
- This resilient blade 21 carries an iron member 22 which can be attracted by the electromagnet 23.
- the resilient blade returns into the jet the interceptor which has previously been retracted by the action of the electromagnet.
- interceptors 2 and 2a are mechanically or electrically co-ordinated. They move in the same direction, i. e. when interceptor 2 is in the jet, interceptor 2a is outside the jet and vice-versa.
- the device according to the invention may be used (a) For the piloting of an aircraft, at any speed and at any altitude, either by a direct action of the pilot on the chosen interceptor surfaces by means of conventional mechanisms or even by an indirect action by means of a suitable pulsating device (not shown);
- an interceptor according to the present invention introduced perpendicularly into a supersonic gaseous jet, gives rise to a separate shock wave inducing an over-pressure zone upstream of the interceptor, the flow being subsonic within said zone.
- An interceptor introduced, on the contrary, like standard aerodynamic fiaps, at a small angle within a supersonic gaseous jet gives rise to a shock-wave not detached from said interceptor, so that in that case there is no over-pressure zone upstream of the interceptor, and the flow along the latter is supersonic.
- the diving moment results from the fact that the shock wave 02, which is separate, gives rise to overpressures exerted along F, upstream of the interceptor directly on the body of the nozzle.
- a nozzle subject to supersonic flow of a gaseous current therethrough, at least one movable jet-intercepting surface disposed at right angles to the gaseous current, said surface having relatively small dimensions in comparison with those of the nozzle and located adjacent the outlet orifice of the said nozzle and outside the nozzle when in the position of rest, the end of said intercepting surface adjacent said outlet orifice having a bevel shape so as to reduce frictional forces, and actuating means for introducing a single movable interception surface at a time into the supersonic gaseous current at right angles to said current, whereby the displacements of said movable surface result in an impact wave producing proportional changes in the distribution of pressure along the corresponding wall of the nozzle upstream of the intercepting surface and a proportional substantial deviation of the longitudinal axis of the supersonic jet without modifying the output of said nozzle.
- a device for deflecting a supersonic gaseous jet a nozzle subject to supersonic flow of a gaseous current therethrough, a movable interceptor located immediately adjacent the outlet orifice of said nozzle and having a deflecting surface disposed at right angles with respect to the nozzle gas flow, and actuating means moving said interceptor into the supersonic gas stream in a direction perpendicular to the flow of gas to deflect the How of gas, producing an impact wave and thereby causing a substantial deviation in the direction of flow of the supersonic jet stream, said deviation of the supersonic jet stream resulting in a side thrust applied to the wall of the nozzle upstream of the interceptor.
Description
Nov. 23, 1954 E STAUFF 2,694,898
DEVICE FOR DEFLECTING A HIGH-SPEED JET OF GAS EJECTED THROUGH A NOZZLE Filed Aug. 3, 1949 3 Sheets-Sheet 1 Nov. 23, 1954 E. STAUFF 2,694,898
DEVICE FOR DEFLECTING A HIGH-SPEED JET 0F GAS EJECTED THROUGH A NOZZLE Filed Aug. 8, 1949 3 Sheets-Sheet 2 Fiq.5. Fig.6.
Nov. 23, 1954 E. STAUFF 2,694,898
DEVICE FOR DEFLECTING A HIGH-SPEED JET 0F GAS EJECTED THROUGH A NOZZLE Filed Aug. 8, 1949 5 Sheets-Sheet 5 IN VENTOR BY ya a L LO :FLOCES ATTORNEY United States Patent DEVICE "FOR DEFLECTING..A- HIGH-SPEED JET OF .GAS EJECTEDTHROUGH A NOZZILE Emile, Stautr", Paris, :France, .assignor toThe French State, represented by the Ministere (16.1 18 ;Defense Nationale, Secretariat dEtat. 'aux...Forces. Armees. (Air), -.Paris, France Application August 8,1949, Serial No. 109,112 Claims priority, application France August 9,1948
4 Claims. -(Cl. 60.-35.54)-:
The present inventionrelates to a particularly simple and economical device Which 'is readily adaptable to any actuating member andwhich, owing to the rapidity with which it canchange its position due to-its small mass and its reduced movements, can housed-for progressively deviating a jet issuing from'the *nozzle of a jet motor with a view to producing powerful'overall torques for the piloting of an aircraft, with the minimum of power consumption and themaxirhum-of 'res'pon siveness, by the instantaneous alteration of the-,-pr'essure distribution along the wallis'of the. nozzle;
In order to varythedirection of a high-speed jet of gas, it is in general necessary to exerta considerable force or to move considerable physical masses. This fact is a drawback in certain applications such as-. the use of a deflection of the propelling jet for producing "an artificial moment about the centre'of gravity of a jetpropelled aircraftyeither the necessary mechanism tegonliles complicated, or the-consumption of power too The present invention relates to a deflecting-device that obviates the above-mentioned"drawbacks,since it enables considerable deflections, of" the orderofinagnitude of several angular degrees, to be" effected in a "highspeed jet of gas while using movable parts of only small mass and-only'employingsmallforces'compared to the result obtained The device according to the present invention is essentially characterized by the 'fact' that, it comprisesat least one interceptor which is made-to penetrate by means of a suitable actuating system-into the-'stream'of gas, either through thewall o-f-the *nozzle,'or' behind szid nozzle, in order -tovary the direction of-"the jet gas.
Other features and the chief advantages of the invention: will become apparent from -the description thereof which will be givenhereinafter'with'-reference'-to the accompanying drawing which illustrates diagrammatically and merely by way of example various embodiments of the invention.
In said drawing:
Figs. 1a and lb show longitudinal sections of a nozzle provided with a device according to the invention, for two different positions of the interceptor.
Figs. 2a and 2b, respectively, show a longitudinal section and an end view of another embodiment of the invention.
Fig. 3 shows a system for actuating the interceptor.
Fig. 4 shows another embodiment of the invention.
Figs. 5 and 6 illustrate, respectively in longitudinal section and in end view, a device for controlling the interceptor.
Figs. 7 and 8 illustrate, respectively in longitudinal section and in end view, another embodiment of the contrcl device for the case where two interceptors are pro- W e Fig. 9 illustrates diagrammatically the resultant forces where the interceptor is introduced at a small angle as heretofore proposed by others, and
Fig. 10 illustrates diagrammatically the resultant forces where the interceptor is introduced at right angles within the supersonic jet as per the present invention. I
In the wall of a nozzle 1 an opening is provided through which is adapted to move an interceptor 2 of any suitable shape. The presence of this obstacle changes thedistribution of the pressure's: along the correspondin g wall of the nozzle, "thereby producing both atransverse force applied .to said nozzle and :a deflection-of the jet issuing therefrom. These two etfects are connected with one .another by the laws of mechanics. Figs. 2 show a modification wherein ;the interceptor is located outsidethe nozzle;
The high speed of the jetof-gas, which may be below or above the speed of sound, makes it :possibleto reduce considerably the response-lagof aerodynamic origin, as compared with similar control surfaces which are subjccted only to-the wind-produ'ced-by the'flight-of'the aircraft; Furthermore, the action of the device obviously depends little on the speed of :flight';
Another advantage of the-arrangementproposed is that, so long as no defie'ction 'is required, the interceptor remains outside the jet "of gas which may be at high temperature andbe moving at very high velocity consequently; the interceptor-isless liable to damage than 'the known system of deflecting flaps which are adapted to move about an axis at right angles to that 'offthe nozzle and 'arcconstantly immersed in the fluid stream.
The small-size. of the necessary =interceptors makes it:possible to' placea wholeseries2, 2a, 2b thereof in a ring about "a nozzle-of revolution *(see Fig. 4),
tionof the jet and for producing ;a discontinuous adjustmentof said direction according to the all-or-none principle.
In the case in which theinterceptor moves between two extreme positions, since ll 5 can only assume two values, -hi and-112* (see F-ig '3), this-movementmayadvantageouslybeobtained bysecuring the interceptor 2 to the moving armature? of an electromagnet 4,10
whihcurrent-is supplied atywilljor automatically by means-of-a switch 5. In this casepthe. deflecting action,
"whichmay be very powerful, is, produced by actuating the switch 5; the currentconsumed by the electromagnet 4 may. be small'since the force-to whichthe interceptor is subjected in, the direction at right angles to the axis'of the nozzle is almost zero.
Referring to Fig. 6,, the intercepting surface 2, which is-l'o'eated, in this example, behindthe nozzle 1,. is integral with an arm-6 whiclrmay rotate about the shaft 7. This arm is normally maintained'in the retracted position of the interceptor, by means of a spring 8.
A lever 9 at the end of the shaft 7 is engaged by the rod 10 which is unitary with an iron member 11 adapted to be attracted by the electromagnet 12.
When a current passes through the electromagnet 12, the iron member 11 is attracted. The rod 10 pulls on the lever 9 and causes the shaft 7 to rotate, the spring 8 to become extended and the interceptor 2 to be introduced into the jet.
When the current ceases, the attractive force of the electromagnet on the iron member is no longer exerted so that the interceptor is brought back to its retracted position by the spring 8.
Figs. 7 and 8 show the case where two interceptors are provided. These interceptors 2 and 2a are secured to the ends of a resilient blade 21 secured to a member integral with the nozzle 1.
This resilient blade 21 carries an iron member 22 which can be attracted by the electromagnet 23.
The resilient blade returns into the jet the interceptor which has previously been retracted by the action of the electromagnet.
Both interceptors 2 and 2a are mechanically or electrically co-ordinated. They move in the same direction, i. e. when interceptor 2 is in the jet, interceptor 2a is outside the jet and vice-versa.
The device according to the invention may be used (a) For the piloting of an aircraft, at any speed and at any altitude, either by a direct action of the pilot on the chosen interceptor surfaces by means of conventional mechanisms or even by an indirect action by means of a suitable pulsating device (not shown);
(11) For deviating a gaseous jet issuing from a nozzle, whether the purpose of this deviation be (or not) the protection of a space swept by the jet or the feeding of a rotary power machine.
It is obvious that the invention has only been described and illustrated in a purely explanatory and in no wav limitative manner and that any modification of detail may be made therein in accordance with its principle without exceeding its scope.
It has been found by experience that in the case of a supersonic gaseous jet, the method of operation of an interceptor employed to produce a controlling moment on a nozzle, as well as the results obtained are totally different depending on whether the said interceptor is introduced into the gaseous jet at a right angle or not.
According to established principles, an interceptor according to the present invention, introduced perpendicularly into a supersonic gaseous jet, gives rise to a separate shock wave inducing an over-pressure zone upstream of the interceptor, the flow being subsonic within said zone.
An interceptor introduced, on the contrary, like standard aerodynamic fiaps, at a small angle within a supersonic gaseous jet gives rise to a shock-wave not detached from said interceptor, so that in that case there is no over-pressure zone upstream of the interceptor, and the flow along the latter is supersonic.
If follows from this essential difference, that:
(a) In the case where the interceptor 2 (see Fig. 9) is introduced at a small angle inside the supersonic jet, the pressures acting upon said interceptor exert a force F1 giving rise to a diving moment, it being noted that the shockwave 01 not being separate and the flow along the interceptor being as a result supersonic, considerable friction forces F2 will occur and reduce the efficiency of the interceptor which then only operates through resultant R.
(b) On the contrary, in the case where the interceptor 2 (see Fig. 10) is introduced at right angles within the supersonic jet, the force F1 acting upon the interceptor itself gives rise not to a diving moment but to a lifting moment (small in view of the short lever arm d1).
The diving moment results from the fact that the shock wave 02, which is separate, gives rise to overpressures exerted along F, upstream of the interceptor directly on the body of the nozzle.
The pressure and velocity changes within the gaseous jet caused by introducing the interceptor 2 at a right angle are bound to each other by the law of the quantity of motion.
The jet thrust that was axial before the introduction of the interceptor shows therefore a lateral component R, resultant of F and F1.
If R0 is the total thrust, the jet is accordingly deflected by an angle a such that sin R a R0 I claim:
1. In a device for deflecting a supersonic gaseous jet, a nozzle subject to supersonic flow of a gaseous current therethrough, at least one movable jet-intercepting surface disposed at right angles to the gaseous current, said surface having relatively small dimensions in comparison with those of the nozzle and located adjacent the outlet orifice of the said nozzle and outside the nozzle when in the position of rest, the end of said intercepting surface adjacent said outlet orifice having a bevel shape so as to reduce frictional forces, and actuating means for introducing a single movable interception surface at a time into the supersonic gaseous current at right angles to said current, whereby the displacements of said movable surface result in an impact wave producing proportional changes in the distribution of pressure along the corresponding wall of the nozzle upstream of the intercepting surface and a proportional substantial deviation of the longitudinal axis of the supersonic jet without modifying the output of said nozzle.
2. In a device for deflecting a supersonic gaseous jet, a nozzle subject to supersonic flow of a gaseous current therethrough, a movable interceptor located immediately adjacent the outlet orifice of said nozzle and having a deflecting surface disposed at right angles with respect to the nozzle gas flow, and actuating means moving said interceptor into the supersonic gas stream in a direction perpendicular to the flow of gas to deflect the How of gas, producing an impact wave and thereby causing a substantial deviation in the direction of flow of the supersonic jet stream, said deviation of the supersonic jet stream resulting in a side thrust applied to the wall of the nozzle upstream of the interceptor.
3. Device according to claim 2, wherein the movable intercepting surface is located downstream relatively'to the outlet orifice of the nozzle.
4. Device according to claim 2, wherein the movable intercepting surface is located upstream relatively to outlet orifice of the nozzle.
References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 1,838,984 Berkowitz Dec. 29, 1931 1,879,187 Goddard Sept. 27, 1932 2,077,471 Fink Apr. 20, 1937 2,395,809 Goddard Mar. 5, 1946 FOREIGN PATENTS Number Country Date 606,176 Great Britain Aug. 10, 1948
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR2694898X | 1948-08-09 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2694898A true US2694898A (en) | 1954-11-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US109112A Expired - Lifetime US2694898A (en) | 1948-08-09 | 1949-08-08 | Device for deflecting a high-speed jet of gas ejected through a nozzle |
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|---|---|
| US (1) | US2694898A (en) |
Cited By (34)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2875578A (en) * | 1950-06-16 | 1959-03-03 | Snecma | Device for controlling the flow direction of a reaction jet issuing from a nozzle |
| US2903851A (en) * | 1956-05-07 | 1959-09-15 | Willy A Fiedler | Jet deflector |
| US2911912A (en) * | 1957-06-27 | 1959-11-10 | United Aircraft Corp | Roll control means |
| US2943821A (en) * | 1950-12-30 | 1960-07-05 | United Aircraft Corp | Directional control means for a supersonic vehicle |
| US2967393A (en) * | 1959-12-03 | 1961-01-10 | Braun Wernher Von | Rocket-propelled missile |
| US2968149A (en) * | 1957-04-26 | 1961-01-17 | Chance Vought Aircraft Inc | Flight control means |
| US2968919A (en) * | 1957-03-25 | 1961-01-24 | Hughes Aircraft Co | Variable area nozzle |
| US3002343A (en) * | 1956-10-29 | 1961-10-03 | Aerojet General Co | Thrust-reversing mechanism for jet aircraft |
| US3013494A (en) * | 1957-08-09 | 1961-12-19 | Chanut Pierre Louis Jean | Guided missile |
| US3020714A (en) * | 1956-07-03 | 1962-02-13 | Snecma | Device for controlling the jet of a reaction propulsion motor |
| US3036430A (en) * | 1958-06-19 | 1962-05-29 | Snecma | Jet control apparatus |
| US3066485A (en) * | 1957-12-11 | 1962-12-04 | Bertin & Cie | Steering device for rocket-propelled vehicles |
| US3082666A (en) * | 1959-02-06 | 1963-03-26 | Acf Ind Inc | Method and apparatus for propulsion |
| US3091924A (en) * | 1960-12-15 | 1963-06-04 | United Aircraft Corp | Gaseous nozzle boundary |
| US3113429A (en) * | 1961-02-14 | 1963-12-10 | Cievite Corp | Steering and speed control for jet propelled vehicles |
| DE1183751B (en) * | 1958-06-19 | 1964-12-17 | Snecma | Device for influencing the direction and the cross-sectional area of a supersonic jet emerging from a Laval nozzle |
| US3163363A (en) * | 1962-12-10 | 1964-12-29 | Ralph L Travis | Combination fog, straight stream, and spray nozzle |
| US3169746A (en) * | 1959-09-11 | 1965-02-16 | Moosmann Alois | Fluid pressure operated turbines |
| DE1198145B (en) * | 1958-08-01 | 1965-08-05 | Firth Cleveland Ltd | Flow bodies, in particular transverse drive surfaces, with circulation that can be influenced by blowing out flow medium jets |
| US3279185A (en) * | 1963-07-18 | 1966-10-18 | George D Lewis | Rocket steering system |
| US3502288A (en) * | 1966-03-22 | 1970-03-24 | Cyrille Francois Pavlin | Missile-piloting system |
| US3508579A (en) * | 1965-12-29 | 1970-04-28 | United Aircraft Corp | Aerodynamic monostable valve |
| US3613996A (en) * | 1969-07-03 | 1971-10-19 | Rohr Corp | Ejector with suppressor chutes |
| US3743184A (en) * | 1972-07-07 | 1973-07-03 | Us Navy | Cylindrical throat nozzle with movable sonic blades for obtaining dual area throat and thrust vector control |
| FR2194883A1 (en) * | 1972-07-31 | 1974-03-01 | Bofors Ab | |
| US4143837A (en) * | 1976-06-08 | 1979-03-13 | Ab Bofors | Control device for missile or the like |
| EP0065529A1 (en) * | 1980-11-14 | 1982-12-01 | Commw Of Australia | A rocket vehicle. |
| US4828174A (en) * | 1984-09-28 | 1989-05-09 | Milliken Research Corporation | Method and apparatus for interrupting fluid streams |
| US5154050A (en) * | 1990-12-14 | 1992-10-13 | Herup Eric J | Thrust vector control using internal airfoils |
| US6681560B2 (en) | 2002-01-08 | 2004-01-27 | Atlantic Research Corporation | Nozzle throat area control apparatus and method |
| US20060150612A1 (en) * | 2005-01-12 | 2006-07-13 | Honeywell International Inc. | Thrust vector control |
| JP2007532826A (en) * | 2004-04-13 | 2007-11-15 | エアロジェット−ジェネラル・コーポレーション | Thrust vector control system for plug-nozzle rocket engine |
| DE102007007568B4 (en) * | 2007-02-15 | 2011-01-05 | Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh | Device for controlling the nozzle thrust direction of a rocket engine |
| US20120067976A1 (en) * | 2009-06-12 | 2012-03-22 | Laurent Carton | System for controlling the trajectory of a jet-propelled mobile |
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| US1838984A (en) * | 1931-03-20 | 1931-12-29 | Berkowitz Louis | Rocket motor aeroplane |
| US1879187A (en) * | 1931-02-07 | 1932-09-27 | Robert H Goddard | Mechanism for directing flight |
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| GB606176A (en) * | 1944-11-27 | 1948-08-10 | Power Jets Res & Dev Ltd | Variable area propelling nozzle for an aircraft jet propulsion system |
-
1949
- 1949-08-08 US US109112A patent/US2694898A/en not_active Expired - Lifetime
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| US1879187A (en) * | 1931-02-07 | 1932-09-27 | Robert H Goddard | Mechanism for directing flight |
| US1838984A (en) * | 1931-03-20 | 1931-12-29 | Berkowitz Louis | Rocket motor aeroplane |
| US2077471A (en) * | 1935-05-04 | 1937-04-20 | Aero Improvements Inc | Aircraft |
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Cited By (37)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2875578A (en) * | 1950-06-16 | 1959-03-03 | Snecma | Device for controlling the flow direction of a reaction jet issuing from a nozzle |
| US2943821A (en) * | 1950-12-30 | 1960-07-05 | United Aircraft Corp | Directional control means for a supersonic vehicle |
| US2903851A (en) * | 1956-05-07 | 1959-09-15 | Willy A Fiedler | Jet deflector |
| US3020714A (en) * | 1956-07-03 | 1962-02-13 | Snecma | Device for controlling the jet of a reaction propulsion motor |
| US3002343A (en) * | 1956-10-29 | 1961-10-03 | Aerojet General Co | Thrust-reversing mechanism for jet aircraft |
| US2968919A (en) * | 1957-03-25 | 1961-01-24 | Hughes Aircraft Co | Variable area nozzle |
| US2968149A (en) * | 1957-04-26 | 1961-01-17 | Chance Vought Aircraft Inc | Flight control means |
| US2911912A (en) * | 1957-06-27 | 1959-11-10 | United Aircraft Corp | Roll control means |
| US3013494A (en) * | 1957-08-09 | 1961-12-19 | Chanut Pierre Louis Jean | Guided missile |
| US3066485A (en) * | 1957-12-11 | 1962-12-04 | Bertin & Cie | Steering device for rocket-propelled vehicles |
| DE1183751B (en) * | 1958-06-19 | 1964-12-17 | Snecma | Device for influencing the direction and the cross-sectional area of a supersonic jet emerging from a Laval nozzle |
| US3036430A (en) * | 1958-06-19 | 1962-05-29 | Snecma | Jet control apparatus |
| DE1198145B (en) * | 1958-08-01 | 1965-08-05 | Firth Cleveland Ltd | Flow bodies, in particular transverse drive surfaces, with circulation that can be influenced by blowing out flow medium jets |
| US3082666A (en) * | 1959-02-06 | 1963-03-26 | Acf Ind Inc | Method and apparatus for propulsion |
| US3169746A (en) * | 1959-09-11 | 1965-02-16 | Moosmann Alois | Fluid pressure operated turbines |
| US2967393A (en) * | 1959-12-03 | 1961-01-10 | Braun Wernher Von | Rocket-propelled missile |
| US3091924A (en) * | 1960-12-15 | 1963-06-04 | United Aircraft Corp | Gaseous nozzle boundary |
| US3113429A (en) * | 1961-02-14 | 1963-12-10 | Cievite Corp | Steering and speed control for jet propelled vehicles |
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