US3401885A - Jet deflector - Google Patents

Jet deflector Download PDF

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Publication number
US3401885A
US3401885A US624271A US62427167A US3401885A US 3401885 A US3401885 A US 3401885A US 624271 A US624271 A US 624271A US 62427167 A US62427167 A US 62427167A US 3401885 A US3401885 A US 3401885A
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US
United States
Prior art keywords
jet
nozzle
chamber
walls
deflector
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 - Lifetime
Application number
US624271A
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English (en)
Inventor
Pavlin Cyrille Francois
D Albian Val
Oudin Francois Charles
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.)
Bertin Technologies SAS
Engins Matra SA
Original Assignee
Bertin et Cie SA
Engins Matra SA
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
Application filed by Bertin et Cie SA, Engins Matra SA filed Critical Bertin et Cie SA
Application granted granted Critical
Publication of US3401885A publication Critical patent/US3401885A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F02K9/82—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/38—Jet flaps

Definitions

  • the deflector according to the invention comprises mainly in combination: a nozzle delivering the propelling jet, and a deflection chamber which follows the nozzle and which terminates at its downstream end as spaced convergent walls between which the jet issues.
  • the nozzle is divergent at least in a portion near the nozzle exit orifice, and that end of the chamber via which the same is connected to the nozzle projects on either side of the nozzle exit orifice, the chamber narrowing in the vicinity of such orifice so that free spaces are left on each side of the jet in the chamber, and control passages are connected to the chamber near the ends thereof to enable the pressure in such spaces to be varied.
  • This invention relates to a jet deflector which is of use in controlling jet-propelled devices such as aircraft or rockets and which is free from moving parts in contact with the propelling jet and requiring deflection.
  • the deflector according to the invention comprises mainly in combination: a nozzle delivering the propelling jet, and a deflection chamber which follows the nozzle and which terminates at its downstream end as spaced convergent walls between which the jet issues.
  • the nozzle is divergent at least in a portion near the nozzle exit orifice, and that end of the chamber via which the same is connected to the nozzle projects on either side of the nozzle exit orifice, the chamber narrowing in the vicinity of such orifice so that free spaces are left on each side of the jet in the chamber, and control passages are connected to the chamber near the ends thereof to enable the pressure in such spaces to be varied.
  • the nozzle is adapted to deliver a flattened jet whose normal mean plane coincides with the longitudinal plane of symmetry of the convergent walls; however, the nozzle can deliver a jet of some other shape, for instance, a circular jet.
  • the jet deflector according to this invention can be used for high Mach number jets and more particularly for supersonic jets. More particularly because the chamber end projects on either side of the nozzle exit orifice, there is less tendency than previously for the jet, which bursts as it leaves the nozzle, the bursting increasing with jet velocity, to stick to the chamber walls, with resulting wall effects which disturb deflector operation. The result is, even in the case of supersonic jets, that correct deviation is maintained and that deviation is progressive and linear relatively to the actuating or control pressures used.
  • FIG. 1 shows an embodiment of the invention in elevation with partial longitudinal sectioning
  • FIG. 1a is a plan view corresponding to FIG. 1;
  • FIG. 3 is a sectioned view showing details of the control distributor
  • FIG. 4 is a plan view, with some parts removed, of a variant comprising a circular cross-section nozzle, and
  • FIG. 5 is a section on the line VV of FIG. 4.
  • a jet deflector comprises a divergent nozzle 1 comprising an exit portion 2 which is of flattened shape and which, as can be seen in FIG. 2, is connected to end 3 of a deflection chamber 4.
  • Chamber width near the chamber end 3 is appreciably greater than nozzle width and is preferably substantially twice nozzle width.
  • Chamber length is preferably approximately ten times the width of the nozzle exit orifice; it has been found by experiments that these conditions give the best results.
  • Chamber side walls 5 substantially extend corresponding walls 6 of nozzle 1, but walls 7, which are shown sectioned in FIG. 1, are further apart from one another than are corresponding walls 8 of nozzle 1 and serve merely to isolate the chamber interior from the environmental space.
  • the walls 7 terminate in plane convergent portions 9a, 9b which are symmetrical of central plane P of the nozzle 1 and of the chamber 4. Edges 10 of the walls 9 are spaced far enough apart for substantially the whole of the jet to pass between the edges 10 when the jet is not deflected.
  • the walls 7 are pierced with transverse control slots 11a, 11b which extend substantially over the whole width of the walls 7 and which passages 12a, 12b connect to a central control box 13, the same communicating via a duct 14 with an auxiliary control fluid source.
  • the box 13 comprises a distributor 15, in the form of a symmetrical double valve member 15, 15b which is adapted to be operated externally and which cooperates with symmetrical seats 16a, 16b bounding chambers 17a, 17b to which the passages 12a, 12b extend.
  • FIGS. 4 and 5 The only difference between the embodiment just described and the embodiment shown in FIGS. 4 and 5 is that in FIGS. 4 and 5 the nozzle 1 is of circular cross-section. End portion 2 is connected to chamber end 3 by means of an outer coupling sleeve or the like 18. Chamber height is substantially constant and equal to nozzle diameter, but, as the chain-dotted lines in FIG. 5 indicate, chamber width near the chamber end 3 is appreciably greater than nozzle diameter.
  • the operation of the deflector is very simple. Provided that pressures P P operative on either side of the jet are equal, the same goes through the chamber 4 without deflection and its mean plane coincides with the plane P. If, for instance, P is greater than P the jet is deflected to wards the wall 9b, strikes the same and is reflected thereby to issue from the orifice bounded by the edges 10, 10 with a deflection towards the side at the pressure P,,. The reflection produces an aerodynamic lever effect which greatly increases the final deflection as compared with the deflection experienced by the jet in the chamber 4.
  • the amplitude of the deviation depends upon the difference between the movement quantities of the control jets and/or upon the difference between the static pressures on either side of the jet in the chamber 4.
  • the latter pressure difference can be varied by means of the distributor shown in FIG. 3.
  • the same operates equally well in a dense atmosphere, in a rarified atmosphere and in vacuo; provided that like sides of the valve members experience substantially equal pressures, as is necessary if symmetrical movements of the valve member are to produce symmetrical eifects, the distributor shown in FIG. 3 has a total delivery which is constant for all the positions of the double valve member 15a, 15b.
  • the arrows refer to operation in a rarified atmosphere or in vacuo.
  • the double valve member connects, via two passages bounded by the seats 16a, 16b, both sides of the jet to the environmental rarified space.
  • the last-mentioned two passages are equal when the valve member is in a central position, and so the pressure on either side of the jet is the same and the jet is not deflected.
  • the passages, and therefore the pressures on both sides of the jet differ from one another and the jet is deflected proportionally to the pressure difference which it experiences.
  • the distributor In a dense atmosphere the distributor is connected to a pressurised fluid source. The flow is in countercurrent to the arrows, and deflection of the power jet is proportional to the difference between the movement quantities and/or the static pressures operative via the control passages.
  • the jet could be deflected by means of separate valves each associated with a control slot and not necessarily supplying the respective control slot simultaneously.
  • the embodiments hereinbefore described can be modified, inter alia by the substitution of equivalent technical means, without for that reason departing from the scope of this invention.
  • the wall portions 9a, 9b can be curved instead of plane.
  • a jet deflector of use as the downstream part of a propulsive and piloting system for a flying body comprising in combination:
  • a nozzle which is adapted to deliver a propulsive gas jet and which is divergent in at least a portion near the nozzle exit end;
  • a deflecting chamber which is connected to the last-mentioned end coaxial of the nozzle and which is bounded:
  • a jet deflector as set forth in claim 1 characterised in that the nozzle portion near the nozzle exit end has substantially the shape of a rectangle whose major sides are parallel to the partially convergent walls.
  • a jet deflector as set forth in claim 1 characterised in that the nozzle portion near the nozzle exit end has a circular crosssection.
  • a jet deflector as set forth in claim 1 characterised in that the width of the chamber end in the direction in which the same projects beyond the nozzle exit orifice is approximately twice the width thereof in the same direction, and chamber length is substantially ten times the lastmentioned width.
  • FIG. 1 It is certified that error appears in the above identified patent and that said Letters Patent are hereby corrected as shown below Column 2, line 5, "FIG. 2" should read FIG. 1

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radiation-Therapy Devices (AREA)
  • Excavating Of Shafts Or Tunnels (AREA)
  • Nozzles (AREA)
US624271A 1966-03-22 1967-03-20 Jet deflector Expired - Lifetime US3401885A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR54511A FR1481133A (fr) 1966-03-22 1966-03-22 Déviateur de jet

Publications (1)

Publication Number Publication Date
US3401885A true US3401885A (en) 1968-09-17

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Application Number Title Priority Date Filing Date
US624271A Expired - Lifetime US3401885A (en) 1966-03-22 1967-03-20 Jet deflector

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US (1) US3401885A (xx)
BE (1) BE695783A (xx)
DE (1) DE1481661A1 (xx)
FR (1) FR1481133A (xx)
GB (1) GB1185091A (xx)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5706650A (en) * 1995-08-09 1998-01-13 United Technologies Corporation Vectoring nozzle using injected high pressure air

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1493157A (en) * 1923-12-10 1924-05-06 Melot Henri Fabrice Propelling ejector
US2597253A (en) * 1945-11-13 1952-05-20 Effie B Melchior Jet-propulsion nozzle
US2914916A (en) * 1952-12-12 1959-12-01 Snecma Arrangement for controlling the flow of a fluid by means of an auxiliary flow

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1493157A (en) * 1923-12-10 1924-05-06 Melot Henri Fabrice Propelling ejector
US2597253A (en) * 1945-11-13 1952-05-20 Effie B Melchior Jet-propulsion nozzle
US2914916A (en) * 1952-12-12 1959-12-01 Snecma Arrangement for controlling the flow of a fluid by means of an auxiliary flow

Also Published As

Publication number Publication date
GB1185091A (en) 1970-03-18
DE1481661A1 (de) 1969-05-22
BE695783A (xx) 1967-09-01
FR1481133A (fr) 1967-05-19

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