NO150416B - SLIDE CONSTRUCTION FOR SURFACE EFFECTS - Google Patents
SLIDE CONSTRUCTION FOR SURFACE EFFECTS Download PDFInfo
- Publication number
- NO150416B NO150416B NO821786A NO821786A NO150416B NO 150416 B NO150416 B NO 150416B NO 821786 A NO821786 A NO 821786A NO 821786 A NO821786 A NO 821786A NO 150416 B NO150416 B NO 150416B
- Authority
- NO
- Norway
- Prior art keywords
- tail
- capsule
- hulls
- construction
- vessel
- Prior art date
Links
- 238000010276 construction Methods 0.000 title claims description 7
- 230000000694 effects Effects 0.000 title claims description 4
- 239000002775 capsule Substances 0.000 claims description 14
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 241000272517 Anseriformes Species 0.000 description 1
- 241000251730 Chondrichthyes Species 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangements of rocket launchers or releasing means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60V—AIR-CUSHION VEHICLES
- B60V1/00—Air-cushion
- B60V1/08—Air-cushion wherein the cushion is created during forward movement of the vehicle by ram effect
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Radar Systems Or Details Thereof (AREA)
- Fluid-Damping Devices (AREA)
- Details Of Aerials (AREA)
- Casting Support Devices, Ladles, And Melt Control Thereby (AREA)
Description
Oppfinnelsen.angår en halekonstruksjon for overflate-effektfartøy eller luftvingebåt med to parallelle skrog og en midtvinge som forbinder de to skrog, samt en halekonstruksjon som xorbinder skrogene bak midtvingen og omfatter en fra hvert skrog oppragende halefinne og en haleflate som forbinder halefinnene. The invention relates to a tail structure for a surface effect vessel or hydrofoil with two parallel hulls and a center wing that connects the two hulls, as well as a tail structure that connects the hulls behind the center wing and includes a tail fin projecting from each hull and a tail surface that connects the tail fins.
Det medfører et problem å utstyre hurtiggående, lavtflyvende fartøyer av denne art med radar. For oppnåelse av størst mulig rekkevidde på en radar i lav høyde eller på havoyerflaten må man nemlig operere med stråler med stor bølgelengde, idet disse,følger jordens krumning bedre enn stråler med kort,bølgelengde. Imidlertid krever langbølgede stråler stor diameter på antennen, noe som er et problem for et. meget hurtiggående fartøy, fordi antennekapselen vil lage stor luftmotstand. Equipping fast-moving, low-flying vessels of this kind with radar entails a problem. In order to achieve the greatest possible range on a radar at low altitude or on the havoy surface, one must operate with beams of long wavelength, as these follow the curvature of the earth better than beams with short wavelength. However, long-wavelength beams require a large diameter antenna, which is a problem for a. very fast-moving craft, because the aerial capsule will create a lot of air resistance.
Ved flyangrep mot slike lavtflyvende, hurtiggående fartøyer er det rimelig å tenke seg at flyene fortrinnsvis vil angripe bakfra. Det er derfor ønskelig å anordne ut-skytningsrør for antiflymissiler som kan avfyres skrått oppover og bakover. Avfyringsbanen for slike missiler kan imidlertid lett komme i veien for en høytliggende radarantennekapsel. Samtidig er det i slike fartøyer viktig å unngå tunge konstruksjoner som reduserer fartøyets nyttelast og/eller gir ekstra luftmotstand. In the case of air attacks against such low-flying, fast-moving vessels, it is reasonable to imagine that the planes will preferably attack from behind. It is therefore desirable to arrange launch tubes for anti-aircraft missiles that can be fired obliquely upwards and backwards. However, the launch path of such missiles can easily get in the way of a high-altitude radar antenna capsule. At the same time, in such vessels it is important to avoid heavy structures that reduce the vessel's payload and/or provide extra air resistance.
Den foreliggende oppfinnelse tar sikte på å skaffe en halekonstruksjon for et fartøy av den ovennevnte art som er slik utformet at den i stor utstrekning løser de foran nevnte problemer. The present invention aims to provide a tail structure for a vessel of the above-mentioned type which is designed in such a way that it largely solves the aforementioned problems.
Ifølge oppfinnelsen er utskytningsrør for antiflymissiler innlemmet som en del av den bærende konstruksjon av hver halefinne, samtidig som en radarantennekapsel er innlemmet som en del av den bærende konstruksjon av haleflaten. According to the invention, launch tubes for anti-aircraft missiles are incorporated as part of the supporting structure of each tail fin, at the same time as a radar antenna capsule is incorporated as part of the supporting structure of the tail surface.
Radarantennekapselen, som er diskosformet, utgjør fortrinnsvis haleflatens midtparti, samtidig som haleflatens sidepartier på hver side av kapselen skråner svakt nedover fra kapselen mot halefinnene» Utskytningsrørene i haie-finnene kan ha tilnærmet samme helning^ som disse» forkanta Videre kan utskytningsrørene fortrinnsvis strekke seg ned gjennom skrogene og være åpne mot fartøyets underside. The radar antenna capsule, which is disc-shaped, preferably forms the middle part of the tail surface, while the side parts of the tail surface on each side of the capsule slope slightly downwards from the capsule towards the tail fins" The launch tubes in the shark fins can have approximately the same slope^ as these" leading edge Furthermore, the launch tubes can preferably extend down through the hulls and be open to the underside of the vessel.
Den sentrale diskosformede radarantennekapsel kan romme en roterende radarantenne med drivverk etc. Dé to side— partier av halef laten er festet 1 underkant av deri sentrale kapsel og^ skråner nedover for at deres masse ikke unødig skal hindre radarens effektivitet. The central disc-shaped radar antenna capsule can accommodate a rotating radar antenna with drive etc. The two side parts of the tail surface are attached to the underside of the central capsule and slope downwards so that their mass does not unnecessarily hinder the radar's effectiveness.
I hver halefinne kan der være innlemmet flere utskyt-ningsrør for henholdsvis målsøkende missiler og avledende varmekilder. Missilene kan f.eks. være av type Bofors Robot Several launch tubes for target-seeking missiles and diverting heat sources can be incorporated into each tail fin. The missiles can e.g. be of the Bofors Robot type
.70 • Utskytningsrørene er åpne mot fartøyets underside for unngåelse av for store reaksjonskrefter og varroepåkjenninger på fartøyet» .70 • The launch tubes are open towards the underside of the vessel to avoid excessive reaction forces and varro stress on the vessel"
Tegningen viser et eksempel, på et overflateeffektfartøy med erv halekonstruks jon ifølge oppfinnelsen» The drawing shows an example of a surface effect vessel with a erv tail construction according to the invention"
Fig. 1 er et grunnriss av fartøyet. Fig. 1 is a floor plan of the vessel.
Fig. 2 er et snitt etter linjen II-II på fig. 1. Fig. 2 is a section along the line II-II in fig. 1.
Fig. 3 viser fartøyet sett forfra. Fig. 3 shows the vessel seen from the front.
Som vist på tegningen kan fartøyet bestå av to skrog 1 og 2, en midtvinge 3, to sidevinger 4 og 5, en halekonstruksjon 6 og en canardvinge 7 som bærer turboviftemotorer 8 og 9. As shown in the drawing, the vessel can consist of two hulls 1 and 2, a central wing 3, two side wings 4 and 5, a tail structure 6 and a canard wing 7 which carries turbofan engines 8 and 9.
Fartøyet er beregnet på å operere ved lave hastigheter i en så lav høyde at skarpe kjølpartier på skrogene 1 og 2 rager ned i vannet, og ved høye hastigheter (opptil 200- The vessel is intended to operate at low speeds at such a low altitude that sharp keel sections on hulls 1 and 2 protrude into the water, and at high speeds (up to 200-
300 km/h) i en høyde over vannflaten på et par meter med muligheter for kortvarig å gå opp i høyder på 20-30 m. 300 km/h) at a height above the water surface of a couple of metres, with the possibility of briefly going up to heights of 20-30 m.
Halekonstruksjonen 6 ifølge oppfinnelsen består av to halefinner 11 og 12 og en haleflate 13 bestående av en sentral diskosformet kapsel 13a og sidepartier 13b og 13c som skråner svakt nedover fra undersiden av den diskosformede kapsel 13a mot og fortrinnsvis noe forbi halefinnene 11 og 12 som sidepartiene av haleflaten er forbundet med. Haleflaten av halekonstruksjonen ifølge oppfinnelsen har således to funksjoner, idet den dels virker som en innkapsling for rada.rantennen, dels utfører den vanlige funksjon av en haleflate, nemlig å virke som stabilisator i vertikalplanet. The tail structure 6 according to the invention consists of two tail fins 11 and 12 and a tail surface 13 consisting of a central disc-shaped capsule 13a and side parts 13b and 13c which slope slightly downwards from the underside of the disc-shaped capsule 13a towards and preferably somewhat past the tail fins 11 and 12 as the side parts of the tail surface is connected to. The tail surface of the tail construction according to the invention thus has two functions, as it partly acts as an enclosure for the radar antenna, and partly performs the usual function of a tail surface, namely to act as a stabilizer in the vertical plane.
Som vist på fig. 2 er der i halefinnene 11 og 12 an-ordnet utskytningsrør 14 og^ 15 for henholdsvis målsøkende antif lymissiler og avledende varmekilder-. Disse utskytnings-rør 14 og 15 utgjør en integrert del av halefinnens bærende konstruksjon. As shown in fig. 2, launch tubes 14 and 15 are arranged in the tail fins 11 and 12 for homing anti-aircraft missiles and diverting heat sources, respectively. These launch tubes 14 and 15 form an integral part of the supporting structure of the tail fin.
På denne måte kan utskytningsrørene gis en hensikts-messig helning uten overhodet å bidra til økt luftmotstand-eller vekt. In this way, the launch tubes can be given an appropriate slope without contributing to increased air resistance or weight at all.
Claims (4)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NO821786A NO150416C (en) | 1982-05-28 | 1982-05-28 | SLIDE CONSTRUCTION FOR SURFACE EFFECTS |
GB08314095A GB2120991B (en) | 1982-05-28 | 1983-05-20 | Tail structure for ground effect vehicle |
DE19833319129 DE3319129A1 (en) | 1982-05-28 | 1983-05-26 | REAR ARRANGEMENT FOR A AIR CUSHION VEHICLE |
JP58093907A JPS58218500A (en) | 1982-05-28 | 1983-05-27 | Tail structure of air cushion vehicle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NO821786A NO150416C (en) | 1982-05-28 | 1982-05-28 | SLIDE CONSTRUCTION FOR SURFACE EFFECTS |
Publications (3)
Publication Number | Publication Date |
---|---|
NO821786L NO821786L (en) | 1983-11-29 |
NO150416B true NO150416B (en) | 1984-07-02 |
NO150416C NO150416C (en) | 1984-10-10 |
Family
ID=19886591
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
NO821786A NO150416C (en) | 1982-05-28 | 1982-05-28 | SLIDE CONSTRUCTION FOR SURFACE EFFECTS |
Country Status (4)
Country | Link |
---|---|
JP (1) | JPS58218500A (en) |
DE (1) | DE3319129A1 (en) |
GB (1) | GB2120991B (en) |
NO (1) | NO150416C (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN1104352C (en) * | 1998-04-08 | 2003-04-02 | 任清海 | Ultrahigh speed marine air cushion vehicle installed with whole airplane |
ES2190869B1 (en) * | 2001-04-06 | 2005-02-01 | Gamesa Desarrollos Aeronauticos, S.A. (Soc. Unip) | COMBINED VEHICLE OF SOIL EFFECT AND CONVENTIONAL FLIGHT. |
AUPR880101A0 (en) | 2001-11-12 | 2001-12-06 | Metal Storm Limited | Weapons platform construction |
CN109131867B (en) * | 2018-07-18 | 2023-10-27 | 深圳筋斗云智能科技有限公司 | Aircraft with a plurality of aircraft body |
CN109018341A (en) * | 2018-09-30 | 2018-12-18 | 中国特种飞行器研究所 | It is a kind of can launch mission load land and water landing unmanned plane |
-
1982
- 1982-05-28 NO NO821786A patent/NO150416C/en unknown
-
1983
- 1983-05-20 GB GB08314095A patent/GB2120991B/en not_active Expired
- 1983-05-26 DE DE19833319129 patent/DE3319129A1/en not_active Withdrawn
- 1983-05-27 JP JP58093907A patent/JPS58218500A/en active Pending
Also Published As
Publication number | Publication date |
---|---|
NO150416C (en) | 1984-10-10 |
GB2120991B (en) | 1985-09-04 |
JPS58218500A (en) | 1983-12-19 |
DE3319129A1 (en) | 1983-12-01 |
GB2120991A (en) | 1983-12-14 |
GB8314095D0 (en) | 1983-06-29 |
NO821786L (en) | 1983-11-29 |
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