DE202019103684U1 - Missile for transport and traffic - Google Patents

Abstract

A missile for transport and traffic, characterized in that the missile is designed as a flying disc, which consists of an annular and thus aerodynamically infinitely stretched wing and contains the drive unit in its center.

Description

The main distinguishing feature of current missiles is their basic lift generation principle. The fixed-wing principle is today known as the aircraft, the rotary-wing principle mainly as a helicopter. Missiles of both genera or hybrids are heavier than air and generate their buoyancy dynamically - regardless of the number and arrangement of their engines and wings or supporting elements. Exemplary here are the variants called multi-engine aircraft, canards, multicopters or autogyros.

As a dynamic buoyancy force is called acting perpendicular to the direction of flow force component to a body flow around. Directs the body from a technical point of view, for. via its wings from a horizontal flow downwards and thus changes the momentum of the flow, it induces impulse-sustaining upward acting buoyancy. As a result, at sufficiently high relative speeds, this body can completely divert and fly the entire momentum of its weight to the ambient air.

Fixed-wing aircraft generate the necessary feed via their engines or by sliding. The feed force only needs to be a fraction of its own weight. However, fixed-wing aircraft rely on long runways according to this operating principle.

Rotorcraft, on the other hand, generate the flow around their engines by directly or indirectly setting the wings in motion via feed. Functionally, this requires a much higher engine performance compared to the fixed-wing aircraft. However, the rotary wing principle allows vertical take-off and landing, which allows the abandonment of runways.

• - Die Tragflächen sind endlich lang. Darum sind Auftriebsverluste und Induktion von Widerstandskräften durch unkontrollierten Druckausgleich zwischen Ober- und Unterseite der Tragfläche über ihre Randbögen unvermeidlich. Eine strömungstechnisch unendlich lang gestreckte Tragfläche würde diese Effekte verhindern.
• - Die Tragflächen sind zum übrigen Flugkörper hin prinzipbedingt auskragend angebunden; ihre Höhe, genannt Profildicke, ist im Vergleich zur Länge sehr klein. Folglich stützt sich das resultierende Hebelmoment der Auftriebskräfte nur über einen niedrigen Flächenquerschnitt ab. Der Kraftfluss ist an der Tragflächenwurzel konzentriert, beim Drehflügler wirken zudem grundsätzlich die Fliehkräfte aus der Rotation ein. Die Festigkeitswerte des Strukturmaterials begrenzen demnach die Gestaltungs- und Skalierungsmöglichkeiten solcher Flugkörper; auch bei Verwendung von High-Tech-Materialien. Eine nicht-kragende Tragflächenkonfiguration schüfe hier neue Möglichkeiten und ließe auch wieder den Einsatz natürlicher Materialien zu.
• - Charakteristisch für konventionell geartete Flugkörper ist ihre große Außenoberfläche bei vergleichsweise kleinem Volumen. Dieses unsinnig kleine Volumen schränkt natürlich die Möglichkeiten, sperrige Güter zu transportieren, erheblich ein.
• - Die enormen Außenabmessungen der Flugkörper erfordern einen erheblichen logistischen, verkehrstechnischen, sowie Ressourcen- und Raum-verschlingenden Aufwand zu ihrem Betrieb. Eine Reduzierung dieser Aufwände ist erstrebenswert.

Both principles of flight contain further defects:

• - The wings are finally long. Therefore, lift losses and induction of drag forces by uncontrolled pressure equalization between the top and bottom of the wing over their margins are inevitable. An aerodynamically infinitely elongated wing would prevent these effects.
• - The wings are connected to the rest of the missile in principle projecting overhanging; their height, called profile thickness, is very small in comparison to the length. Consequently, the resulting momentum of the buoyancy forces only supported over a low area cross-section. The power flow is concentrated at the root of the wing, while the rotorcraft basically also has the centrifugal forces from the rotation. The strength values of the structural material therefore limit the design and scaling possibilities of such missiles; even when using high-tech materials. A non-cantilevered wing configuration creates new possibilities here and allows the use of natural materials again.
• - Characteristic of conventionally shaped missiles is their large outer surface with a comparatively small volume. Of course, this nonsensical small volume considerably limits the possibilities of transporting bulky goods.
• - The enormous outer dimensions of the missile require a significant logistical, traffic engineering, as well as resource and space-consuming effort to their operation. A reduction of these efforts is desirable.

The purpose of the invention is therefore a vertical launch capable missile, which combines the exclusive advantages of both flight principles in itself and can compensate for the consequent common disadvantages of both flight principles.

According to the invention, this object is achieved in that the missile is designed as a flying disc, which consists of an annular and thus aerodynamically infinitely stretched wing and contains the drive unit in its center. Directly at the top of the annular support surface, a thin air film accelerated from the drive assembly is blown radially outward over at least one concentrically arranged annular gap, so that the arrangement generates lift in accordance with the Bernoulli effect. Obeying the Coanda effect, the air film follows the downwardly curved airfoil contour as the ambient air pushes the high velocity air film over its boundary layer onto the airfoil. As a result of flow technology, the air film loses speed and becomes thicker. At the outer edge of the disc, so the end edge of the annular support surface, the air film rolls under the wing finally to a vortex torus and is deflected by this torus lossless center, sucked by the drive unit and in turn accelerated blown through the annular gap. The vortex torus thus flows radially apart, generating lift on the underside of the wing.

The airfoil, together with the closed air film, which flows rapidly relative to the environment, forms a pressure sink in the direction of which the quiescent air is accelerated from all sides. This air is, given by the predetermined outside of the flying disc flow direction of the air film, deflected downward, where it jams under the closed air film and thus forms a pressure source. The resulting pressure difference between the top and bottom of the flying disc in total forms a downwardly directed flow field over which the flying disc derives the momentum of its weight force to the ambient air and thus generates its buoyancy.

The control can be carried out by way of example by way of a plurality of control fins arranged on and / or under the support surface, which distribute the air film differently to the circumference of the annular support surface and thus control the missile via a controlled conditional displacement of the lift center-analogous to the rotary vane principle. At the same time, such fins are also suitable for generating or preventing rotation about the vertical axis.

Likewise, the buoyancy center of gravity can be effected, for example, by an asymmetrical widening of the mentioned air gap, which is then activated in a manner completely analogous to the swashplate of a helicopter. In this case, the fins only serve to regulate the movement about the vertical axis.

The design as an annular wing also reduces the burden of the missile structure, since compared to the fixed-wing and rotorcraft, the power flow is not angled and the power flow routes are both short and field-like distributed, which also favors uncomplicated lightweight construction of the missile. The thick profile design also contributes to this. Furthermore, the volume of this missile is inscribed on a smaller surface, which allows significantly more payload per friction-generating, and thus energy-consuming surface.

• Zeichnung 1 zeigt die Flugscheibe im Schnitt, sowie das vom Antriebsaggregat erzeugte Strömungsfeld
• Zeichnung 2 zeigt die Flugscheibe von oben
• Zeichnung 3 zeigt die Flugscheibe von unten

The invention will be explained in more detail with reference to drawings

• drawing 1 shows the flying disk in section, and the flow field generated by the drive unit
• drawing 2 shows the flying disc from above
• drawing 3 shows the flying disc from below

To drawing 1 : It shows the flying disk on average with the appropriate nomenclature drive unit 1 , Annular gap 2 , Wing 3 , Tax fins 4 and flow field 5 , which is composed of air film and vortex torus.

The drive is here as a single drive unit 1 represented, which over the annular gap 2 generates a high relative to the ambient air accelerated air film and this on the annular support surface 3 and the vortex to a flow field 5 formed. Turning the steering fins 4 generates a shift of the lift center of gravity and / or moment about the vertical axis, which accelerate the flying disc horizontally translationally or rotationally about the vertical axis.

drawing 2 shows a perspective view of the flying disc from above

drawing 3 shows a perspective view of the flying disc from below

LIST OF REFERENCE NUMBERS

power unit 1 annular gap 2 wing 3 control fins 4 flow field 5

Claims (6)

A missile for transport and traffic, characterized in that the missile is designed as a flying disc, which consists of an annular and thus aerodynamically infinitely stretched wing and contains the drive unit in its center. to Claim 1 : characterized in that directly at the top of the annular support surface from the inside over at least one annular gap, a thin, highly accelerated by the drive unit air film is blown radially outward, so that the arrangement generates a buoyancy according to the Bernoulli effect. to Claim 1 and 2 characterized in that, following the Coanda effect, the air film follows the downwardly curved airfoil contour by the ambient air pushing the high velocity air film over its boundary layer onto the airfoil. to Claim 1 - 3 : characterized in that at the outer edge of the disc, so the end edge of the annular support surface, the air film finally curls under the wing and so, at a distance below the wing again radially inward and along the axis of symmetry of the flying disc back up through the central drive unit in the airfoil flows, accelerated again through the annular gap is blown out. The flow of the air film is thus closed in itself. to Claim 1 - 4 : characterized in that this closed air film forms the inscribed to the wing underside inscribed air to a closed vertebrae and these drives with the same direction of rotation. The vortex torus thus flows radially apart, generating lift on the underside of the wing. to Claim 1 - 5 : characterized in that the control takes place via a controlled conditional displacement of the center of lift or torque generation about the vertical axis and thus controls the missile. This can be carried out by way of example by way of a multiplicity of control fins arranged on and / or under the support surface or can take place via an asymmetrical widening of the air gap.

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