DE1059770B - Process for the production of aircraft wings and tail surfaces - Google Patents
Process for the production of aircraft wings and tail surfacesInfo
- Publication number
- DE1059770B DE1059770B DER20391A DER0020391A DE1059770B DE 1059770 B DE1059770 B DE 1059770B DE R20391 A DER20391 A DE R20391A DE R0020391 A DER0020391 A DE R0020391A DE 1059770 B DE1059770 B DE 1059770B
- Authority
- DE
- Germany
- Prior art keywords
- core
- light metal
- wing
- foam
- riveted
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C44/00—Shaping by internal pressure generated in the material, e.g. swelling or foaming ; Producing porous or cellular expanded plastics articles
- B29C44/02—Shaping by internal pressure generated in the material, e.g. swelling or foaming ; Producing porous or cellular expanded plastics articles for articles of definite length, i.e. discrete articles
- B29C44/12—Incorporating or moulding on preformed parts, e.g. inserts or reinforcements
- B29C44/1228—Joining preformed parts by the expanding material
- B29C44/1242—Joining preformed parts by the expanding material the preformed parts being concentric
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
- B29C70/865—Incorporated in coherent impregnated reinforcing layers, e.g. by winding completely encapsulated
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
- B29D99/0028—Producing blades or the like, e.g. blades for turbines, propellers, or wings hollow blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2067/00—Use of polyesters or derivatives thereof, as moulding material
- B29K2067/06—Unsaturated polyesters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/04—Condition, form or state of moulded material or of the material to be shaped cellular or porous
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2309/00—Use of inorganic materials not provided for in groups B29K2303/00 - B29K2307/00, as reinforcement
- B29K2309/08—Glass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2705/00—Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Description
Die Erfindung bezieht sich auf ein Verfahren zur Herstellung eines Flugzeugtragflügels oder eines -leitwerkes.The invention relates to a method for manufacturing an aircraft wing or one - tail unit.
Bei Flugzeugtragflügeln geht das Streben dahin, Laminarprofile zu verwenden, da bei diesen der Widerstand eines Tragflügels verhältnismäßig gering ist. Um Laminarströmung zu erzielen, ist es notwendig, den Tragflügeln eine hohe Oberflächengüte zu geben und sie derart auszubilden, daß die Kontur des Profiles bei Belastung erhalten bleibt.In the case of aircraft wings, the aim is to use laminar profiles, since with these the resistance of a wing is relatively low. To achieve laminar flow it is necessary to to give the wings a high surface quality and to train them in such a way that the contour of the profile remains under load.
Bei den flugzeugen, die für verhältnismäßig geringe Beanspruchungen ausgelegt sind, ist das Gewicht von entscheidender Bedeutung. Hierdurch ist es nicht immer möglich, die Beplankungsstärke des Tragflügels so dick zu wählen, daß alle Niete versenkt werden können und daß kein Ausbeulen der dünnen Bleche vor Erreichung der Höchstgeschwindigkeit eintritt. Durch die auftretenden Ausbeulungen wird die Profilkontur erheblich gestört. Aus diesen Gründen blieb bisher der Flügel mit einem Laminarprofil nur den hochgezüchteten Hochleistungsflugzeugen, bei denen die Fertigungskosten eine untergeordnete Rolle spielen, vorbehalten. Bei diesen Flugzeugen wird die Tragfläche dauernd nachgespachtelt, um so die erforderliche Oberflächengüte zu erreichen.In the case of aircraft, which are designed for relatively low loads, the weight is vital. As a result, it is not always possible to change the thickness of the cladding To choose the wing so thick that all rivets can be countersunk and that no buckling of the thin sheet metal enters before the maximum speed is reached. Due to the bulges that occur the profile contour is significantly disturbed. For these reasons, the wing has so far remained with a laminar profile only the sophisticated high-performance aircraft, where the manufacturing costs are a subordinate Role reserved. In these aircraft, the wing is constantly re-filled, in order to achieve the required surface quality.
Die Erfindung setzt sich zur Aufgabe, eine Fertigung von Tragflächen und Leitwerksflächen zu erreichen, die die Möglichkeit gibt, Laminarflächen auch im Serienbau wirtschaftlich zu fertigen, ohne größere Gewichte in Kauf nehmen zu müssen.The invention has as its object to achieve a production of wings and tail surfaces, which gives the possibility to manufacture laminar surfaces economically in series production without larger ones Having to put up with weights.
Nach der Erfindung wird ein Herstellungsverfahren für Flugzeugtragflächen und -leitwerksflächen vorgeschlagen, das sich dadurch kennzeichnet, daß zunächst ein Leichtmetallkern, der sich aus zwei miteinander verbundenen Hohlkörpern zusammensetzt, gefertigt wird, welcher Kern in eine entsprechend dem gewünschten Profil ausgebildete Form eingelegt wird in der sich eine sehr dünne Kunststoffschicht, z. B. aus glasfaserverstärktem Polyesterharz, befindet und der Raum zwischen Leichtmetallkern und Kunststoffschicht mit Schaumstoff ausgeschäumt wird. Weitere Kennzeichen und Merkmale der Erfindung ergeben sich aus den Unteransprüchen und der folgenden Beschreibung einer vorteilhaften, beispielsweisen in den Zeichnungen dargestellten Ausführungsform.According to the invention, a manufacturing method for aircraft wings and tail surfaces is proposed, which is characterized by the fact that initially a light metal core, which is made up of two together connected hollow bodies is made up, which core in a corresponding to the desired Profile formed form is inserted in which a very thin plastic layer, z. B. off fiberglass-reinforced polyester resin, and the space between the light metal core and the plastic layer is filled with foam. Further characteristics and features of the invention result from the subclaims and the following description of an advantageous, for example in the Drawings illustrated embodiment.
Die Fig. 1 bis 8 zeigen die einzelnen Fertigungsschritte des neuen Verfahrens. FIGS. 1 to 8 show the individual manufacturing steps of the new method.
Jeder Tragflügel weist zwei Kernkörper 1 und 2 auf, die aus einem Leichtmetallblech gefertigt sind.
Nach dem Zuschneiden wird das Leichtmetallblech abgekantet und erhält die in Fig. 1 aufgezeigte Form.
Die Querschnittsfläche des Kernkörpers verjüngt sich nach außen hin, und die begrenzenden Leichtmetallbleche
sind an der Stirnseite mittels Niete 3 Verfahren
zur Fertigung von Flugzeugtragflächen
und -leitwerksflächenEach wing has two core bodies 1 and 2 , which are made from a light metal sheet. After cutting to size, the light metal sheet is folded over and given the shape shown in FIG. 1. The cross-sectional area of the core body tapers outwards, and the delimiting light metal sheets are riveted on the front side by means of 3 methods
for the production of aircraft wings
and tail surfaces
Anmelder:Applicant:
Rhein-West-Flug, Fischer & Companie,
Porz-Westhoven, Amselstr. 5Rhein-West-Flug, Fischer & Companie,
Porz-Westhoven, Amselstr. 5
Hans-Otto Fischer, Porz-Westhoven, und Bernhard Schulze-Wilmert, Münster (Westf.), sind als Erfinder genannt wordenHans-Otto Fischer, Porz-Westhoven, and Bernhard Schulze-Wilmert, Münster (Westphalia), have been named as inventors
befestigt. Es ist ein besonderer Vorteil des V erf ahrens, daß der Leichtmetallkern, der einzig und allein die statischen Beanspruchungen aufzunehmen hat, im wesentlichen ohne Rücksicht auf die endgültige Kontur des Tragflügels ausgelegt werden kann. Somit ist es auch möglich, an den zu verbindenden Stellen Halbrundniete zu verwenden, die in der Verarbeitung billig sind. Zur Bildung der Holmgurte werden auf die oberen und unteren Begrenzungskanten 4, 5, 6, 7 der Kernkörper Verstärkungswinkel 8 aufgesetzt, die über Niete 9 mit den Kernkörpern verbunden werden. Damit die über Schaumstoff mit dem Kernkörper verbundene, später aufgebrachte Kunststoffschale einen genügenden Halt auf dem Kernkörper erhält, werden auf die äußeren Begrenzungsflächen Hutprofile 10 aufgesetzt. Über ein flaches Leichtmetallband 11 werden darauf die beiden Kernkörper zu dem Leichtmetallkern, der für einen Tragflügel erforderlich ist, verbunden. Darauf wird der durch diese Verbindung entstandene Holmsteg mit Schaumstoff ausgeschäumt. Der so entstandene Kern wird dann in eine zweiteilige Negativform 12, 13, die mit einer sehr dünnen Kunststoffschicht 14, z. B. aus glasfaserverstärktem Polyesterharz, ausgekleidet -worden ist, eingelegt, die entsprechend dem gewünschten Laminarprofil ausgebildet ist. Nun werden, nachdem die Form geschlossen ist, die verbleibenden Zwischenräume mit Schaumstoff 15 ausgeschäumt. Nach Erstarren des Schaumstoffes werden die Formteile 12 und 13 entfernt.attached. It is a particular advantage of the process that the light metal core, which only has to absorb the static loads, can be designed essentially without regard to the final contour of the wing. It is thus also possible to use half-round rivets at the points to be connected, which are cheap to work with. To form the spar chords, the core body reinforcement angles 8 are placed on the upper and lower delimiting edges 4, 5, 6, 7 and are connected to the core bodies via rivets 9. So that the later applied plastic shell, which is connected to the core body via foam, has a sufficient hold on the core body, hat profiles 10 are placed on the outer boundary surfaces. The two core bodies are then connected via a flat light metal band 11 to form the light metal core which is required for an airfoil. The spar web created by this connection is then filled with foam. The resulting core is then in a two-part negative mold 12, 13, which is covered with a very thin plastic layer 14, for. B. made of glass fiber reinforced polyester resin, lined - has been inserted, which is designed according to the desired laminar profile. After the mold is closed, the remaining spaces are filled with foam 15 . After the foam has solidified, the molded parts 12 and 13 are removed.
Dieses Fertigungsverfahren erlaubt es, dünne Leichtmetallbleche für den Kernkörper zu verwenden, da die Schaumstoffschicht mit der außenliegenden Kunststoffschicht eine Sicherung gegen AusbeulungenThis manufacturing process makes it possible to use thin light metal sheets for the core body, because the foam layer with the outer plastic layer protects against bulging
909 557/64909 557/64
Claims (3)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DER20391A DE1059770B (en) | 1957-01-23 | 1957-01-23 | Process for the production of aircraft wings and tail surfaces |
GB2304/58A GB860391A (en) | 1957-01-23 | 1958-01-23 | A method of manufacturing aeroplane wings and tail units |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DER20391A DE1059770B (en) | 1957-01-23 | 1957-01-23 | Process for the production of aircraft wings and tail surfaces |
Publications (1)
Publication Number | Publication Date |
---|---|
DE1059770B true DE1059770B (en) | 1959-06-18 |
Family
ID=7400657
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DER20391A Pending DE1059770B (en) | 1957-01-23 | 1957-01-23 | Process for the production of aircraft wings and tail surfaces |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE1059770B (en) |
GB (1) | GB860391A (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1290709B (en) * | 1963-01-11 | 1969-03-13 | Bellanca August Thomas | Elongated, double-shell lightweight body with a foam material intermediate layer |
GB1089851A (en) * | 1963-11-26 | 1967-11-08 | Gen Am Transport | Railway tank cars and methods of making railway tank car bodies |
US3301926A (en) * | 1964-04-08 | 1967-01-31 | Gateway Erectors Inc | Method of fabricating a self-braced concrete form |
US3790421A (en) * | 1970-07-08 | 1974-02-05 | Plexawood Inc | Composite articles and methods of making the same |
IT1135542B (en) * | 1981-02-19 | 1986-08-27 | Mario Calcagni | EXTRUSION HEAD FOR PROFILES FOR ROLLER SHUTTERS, FIXTURES AND SIMILAR, AS WELL AS PROFILE OBTAINED |
US8043458B2 (en) * | 2007-06-21 | 2011-10-25 | Sikorsky Aircraft Corporation | Method of forming panels using an in-situ tape placement process and panels formed therefrom |
GB2523414B (en) * | 2014-02-24 | 2016-02-17 | Marine Current Turbines Ltd | Turbine blade and method of manufacture |
-
1957
- 1957-01-23 DE DER20391A patent/DE1059770B/en active Pending
-
1958
- 1958-01-23 GB GB2304/58A patent/GB860391A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
GB860391A (en) | 1961-02-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE2721651C3 (en) | Main wing connector for aircraft and spacecraft | |
DE1264266B (en) | Process for the manufacture of rotor blades from glass fiber reinforced plastic | |
DE1059770B (en) | Process for the production of aircraft wings and tail surfaces | |
AT397906B (en) | PLASTIC CONTAINER | |
DE2923463A1 (en) | Blade for wind driven turbine - has outer skin in tension to be load carrying without stiffening framework on inside of blade | |
DE2856661C2 (en) | Method and device for the production of plastic blades, in particular for wind power plants, in one form | |
DE102022124533A1 (en) | Wing or tailplane for a flying object | |
DE2639982C2 (en) | Seaplane with a boat-like hull | |
DE102005004345A1 (en) | Honeycomb sandwich core for profile-shaped aircraft-parts, like wings consists of paper, metal or plastic ribs stuck together in profile shape and is consequently not machined on full span | |
DE2718002A1 (en) | Laminated glass fibre reinforced plastics panels - with cover plates and internal corrugated support elements | |
DE723604C (en) | Air brake for multi-engine aircraft | |
DE535240C (en) | Hollow bodies for aircraft | |
DE1095131B (en) | Sewerage for fuel in fuel tanks for aircraft in honeycomb construction | |
DE574042C (en) | plane | |
DE965621C (en) | Transverse drive body or Leitflaeche, in particular tubular hydrofoil | |
DE681864C (en) | Wings, fins or rudders for aircraft | |
DE878155C (en) | Aircraft with a wing that continuously expands across the aircraft | |
DE712717C (en) | Retractable landing gear for aircraft | |
DE659324C (en) | Design for light boat bodies, especially speed boats | |
DE515645C (en) | Method for connecting metallic components by electrolytic means, in particular for manufacturing aircraft cells | |
DE515646C (en) | Airplane, the fuselage of which forms a square standing on a corner in cross section | |
AT58071B (en) | Wing-like wing for aircraft. | |
DE475230C (en) | Wing for aircraft with hollow outer walls | |
DE1781322C (en) | Hydrofoil with one or more spars extending in the direction of its span | |
DE102012002352B4 (en) | Aircraft, in particular passenger aircraft, with a hull of metal materials and fiber composite materials |