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EP0078921B1 - Empennage avec sensibilité au vent du sol réduite - Google Patents

Empennage avec sensibilité au vent du sol réduite Download PDF

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Publication number
EP0078921B1
EP0078921B1 EP82109279A EP82109279A EP0078921B1 EP 0078921 B1 EP0078921 B1 EP 0078921B1 EP 82109279 A EP82109279 A EP 82109279A EP 82109279 A EP82109279 A EP 82109279A EP 0078921 B1 EP0078921 B1 EP 0078921B1
Authority
EP
European Patent Office
Prior art keywords
tail
fins
tail unit
flight
flight body
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
Application number
EP82109279A
Other languages
German (de)
English (en)
Other versions
EP0078921A2 (fr
EP0078921A3 (en
Inventor
Walter Prof. Dr. Diesinger
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.)
Dynamit Nobel AG
Original Assignee
Dynamit Nobel AG
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 Dynamit Nobel AG filed Critical Dynamit Nobel AG
Publication of EP0078921A2 publication Critical patent/EP0078921A2/fr
Publication of EP0078921A3 publication Critical patent/EP0078921A3/de
Application granted granted Critical
Publication of EP0078921B1 publication Critical patent/EP0078921B1/fr
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • the invention relates to an empennage of the type specified in the preamble of claim 1.
  • Tail units cause the longitudinal stability of unguided missiles.
  • guided missiles generally only a low level of longitudinal stability is sought in order to facilitate longitudinal control.
  • controller built into the control there is also the possibility of artificially stabilizing an unstable guided missile using a controller built into the control.
  • the stabilizing effect of an empennage arises from the fact that when the missile rotates out of the direction of flight, the empennage generates a turning moment that continues until the missile is turned back in the direction of flight.
  • This turning back eliminating the disturbance moment about the center of gravity of the missile comes about because the tail unit is attached behind the center of gravity of the missile and acts as a wing due to the deflection from the flight direction.
  • the buoyancy i.e. If the stability is high, the disturbance is eliminated quickly; if it is small, the disturbance is only slowly compensated for. If the tail lift is insufficient, the deviation from the flight direction increases until the missile "breaks out" after a certain time and the missile longitudinal axis is rotated by 90 ° to the flight direction.
  • the tail unit must therefore be at least large enough that it is also sufficient for stabilization at the maximum speed, which then results in a high sensitivity to ground wind in the known tail units.
  • the invention has for its object to design a tail so that it is particularly effective at the highest airspeed in comparison to the take-off speed in order to be able to use a fixed tailplane or a tailplane that opens immediately after takeoff.
  • the fins of the tail unit can be provided with openings or recesses in their fully flowed area outside the contour of the missile.
  • these can be designed as perforations which are arranged in the region of the end of the fins facing the missile fuselage.
  • This pressure equalization has the consequence that the lift and thus the stabilizing effect of the tail are reduced. Since the pressure equalization is stronger for aerodynamic reasons at low airspeed after takeoff than at supersonic speed, the measure according to the invention has the consequence that such an empennage also works worse at high airspeeds than a conventional one, but particularly poorly at low airspeeds works. However, this means that it is less sensitive to cross winds.
  • tail units with a small extension can be difficult with conventional construction, since this leads to tail units whose depth or axial extension is large compared to their wingspan. This requires a correspondingly long tail of the missile or results in tail units, the wingspan of which would disappear within the caliber and can therefore no longer be implemented.
  • the formation of the tail unit according to claim 2 can be provided in these but also other cases.
  • the tail unit is then broken up into individual wings, each of which can easily be designed as a wing with a small extension.
  • the individual wings are not attached to the fuselage as usual, but at such a lateral distance from it that their inner ends facing the fuselage are also fully exposed to the air flow. This not only results in pressure equalization over the outer ends, but also over the inner ends of the wings.
  • the latter is, however, reduced by the web-shaped mounting of the wings and the certain width of the intermediate space compared to the theoretical value, so that the effective extension of the individual wings is greater than their geometric, which must be taken into account in their design.
  • Fig. 1 shows the tail 1 of a missile with a conventional empennage of great extent.
  • the aspect ratio is small in contrast to this.
  • the fins 2 are designed as single wings with a small extension, which are connected to the fuselage 1 via a web 3 in each case.
  • the fins 2 are arranged at a distance a from the fuselage 1 and thus outside the contour of the missile in the region of its tail so that they extend in their entire extent, i.e. are also fully exposed to the flow according to arrow A with their inner end 2 '.
  • the tail unit otherwise corresponds to the conventional structure, i.e. it consists of at least three, preferably four but also more than four fins 2, which are firmly connected to the fuselage 1 in flight.
  • the trailing edge of the fin and the trailing edge of the fuselage do not have to lie in one plane.
  • the holder 3 can be fastened to the fuselage 1 in a known manner so that it can be rotated and locked.
  • a corresponding mechanism can also be present at the interface of the holder 3 and fin 2.
  • Fig. 3b which, like the other figures for the sake of simplicity, only shows a partial view of the tail units, shows one with two retaining webs 3 on the fuselage 1 at a distance a, i.e. fin 2 fastened while leaving the gap or space 4.
  • the pressure compensation is achieved by an axially extending perforation 5, which is preferably arranged in the area of the fin-fuselage transition, but also in other areas of the fin plan, albeit with a reduced effect can be.
  • This perforation which extends over the entire depth of the fins, advantageously advantageously approximately divides the entire tail unit into individual wings with a small extension. In this way, existing conventional tail units can also be modified with relatively little effort.
  • FIG. 4b shows a version in which instead of the perforation according to FIG. 4a, a longitudinal slot 6 open at the rear is provided, which instead could also be open at the front or, according to FIG. 4c, can also be designed as a slot 6 'closed at both ends .
  • a longitudinal slot 6 open at the rear is provided, which instead could also be open at the front or, according to FIG. 4c, can also be designed as a slot 6 'closed at both ends .
  • an approximate division into single wings with a small extension is achieved, which can also be applied to existing conventional tail units.
  • FIGS. 5a and b The various possibilities of pressure equalization can also be combined with one another, as shown in FIGS. 5a and b with individual wings 2, webs 3 and perforations 5, if e.g. in the course of the design of a tail unit should show that the brackets 3 hinder the lateral pressure compensation too much.
  • FIG. 6 finally shows a tail unit with fins 2 turned forward, in which these can be rigidly attached to the fuselage 1 with their one corner 8.
  • the fins shown in Figs. 2 to 6 have a rectangular plan, but this is not a requirement. In the case of folding stabilizers in particular, other layouts may also arise for structural reasons.
  • the effect of the tail units according to the invention, the reduction in ground wind sensitivity, does not change as a result.
  • the rigid tail units according to the invention that are shown or that open up at the start do not change their configuration during the flight.
  • more complicated tail assemblies are also possible with an effort comparable to the known late-opening tail assemblies, which enable a further reduction in the sensitivity to ground wind.
  • the fin 2 is mounted so as to be resiliently rotatable about the axis of the web 3.
  • the position of this fulcrum - viewed in the direction of flight - before the point of application of the lift force on the fin 2, its angle of attack is smaller than that of the fuselage, which means an effective reduction in the effectiveness of the tail unit.
  • Non-guided missiles are designed to rotate to compensate for asymmetries.
  • the speed of rotation around the longitudinal axis increases with the airspeed.
  • the centrifugal force or the dynamic pressure can be used to to lock.
  • perforations can be sealed or tail fins e.g. 6 are rotated on the fuselage in order to reduce the stability-reducing influence of the small aspect ratio or to eliminate it, if necessary, with increasing flight speed.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (3)

1. Empennage fixe ou déployable, pour engins volants supersoniques guidés ou non-guidés, caractérisé en ce que les ailerons (2) de l'empennage, pour réduire leur effet, notamment au début de la phase de vol, sont réalisés de façon qu'un équilibre de pression renforcé, entre leur côté supérieur et leur côté inférieur, soit rendu possible, cela par le fait que ces ailerons (2) présentent un petit allongement, notamment un allongement inférieur à 1, et/ou que ces ailerons (2) sont munis, en dehors du contour de l'engin volant, dans la région de leur extrémité tournée vers cet engin, de fentes ou de perforations (5, 6, 6'), ou analogues, s'étendant dans la direction longitudinale.
2.- Empennage selon revendication 1, caractérisé en ce que les ailerons (2) sont réalisés en tant qu'ailes séparées agissant indépendamment les unes des autres, lesquelles sont agencées à distance du fuselage (1) de l'engin volant, en laissant subsister un intervalle (4) situé à l'extérieur du contour de l'engin, et sont liées au fuselage par au moins une âme (3) franchissant cet intervalle (4).
3. Empennage selon revendication 1, caractérisé en ce que les ailerons (2) ont une disposition oblique et ne sont rattachés qu'en un coin (8) au fuselage (1) de l'engin volant.
EP82109279A 1981-11-06 1982-10-07 Empennage avec sensibilité au vent du sol réduite Expired EP0078921B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19813144073 DE3144073A1 (de) 1981-11-06 1981-11-06 Leitwerk mit reduzierter bodenwindempfindlichkeit
DE3144073 1981-11-06

Publications (3)

Publication Number Publication Date
EP0078921A2 EP0078921A2 (fr) 1983-05-18
EP0078921A3 EP0078921A3 (en) 1984-06-06
EP0078921B1 true EP0078921B1 (fr) 1987-05-27

Family

ID=6145752

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82109279A Expired EP0078921B1 (fr) 1981-11-06 1982-10-07 Empennage avec sensibilité au vent du sol réduite

Country Status (3)

Country Link
EP (1) EP0078921B1 (fr)
DE (2) DE3144073A1 (fr)
MX (1) MX163263B (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3927918A1 (de) * 1989-08-24 1991-02-28 Rheinmetall Gmbh Fluegelstabilisiertes geschoss
FR2721701B1 (fr) * 1994-06-28 1996-08-14 Giat Ind Sa Empennage pour projectile, notamment pour projectile sous-calibré supersonique.
CN115371501B (zh) * 2022-09-19 2023-04-28 山西华洋吉禄科技股份有限公司 一种精确制导组件的舵翼联动结构及控制方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2045687A1 (de) * 1970-09-16 1972-03-23 Dynamit Nobel Ag Thermische Auslösung von Flugkörperfunktionen

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE373811A (fr) * 1929-11-09
CA466940A (fr) * 1945-12-14 1950-08-01 Anzalone Ralph Fusee
FR2070389A5 (fr) * 1969-12-03 1971-09-10 Serat
US3690595A (en) * 1970-11-19 1972-09-12 Sarmac Sa Self-propelled, vaned missile
US4004514A (en) * 1976-01-20 1977-01-25 The United States Of America As Represented By The Secretary Of The Navy Roll rate stabilized wrap around missile fins

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2045687A1 (de) * 1970-09-16 1972-03-23 Dynamit Nobel Ag Thermische Auslösung von Flugkörperfunktionen

Also Published As

Publication number Publication date
EP0078921A2 (fr) 1983-05-18
DE3276446D1 (en) 1987-07-02
MX163263B (es) 1992-03-30
DE3144073A1 (de) 1983-05-19
EP0078921A3 (en) 1984-06-06

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