Airflow Plate Fins

Abstract

Curved airflow plate fins deployed upon rockets to guide the trajectory under the action of given forces. The fins are comprise relatively high gauge metal. They are located on the rocket in a triangular arrangement. When deployed. the fins contribute to deceleration and breaking. The airflow plates can be extended outwardly from their housing, and then rotated transversely with respect to the longitudinal axis of the rocket. The airflow plate fins have geometric openings to improve their performance against incoming forces given that under supersonic speed. Their curved shape increases the capabilities of friction between the forces acting against them.

Claims

1. An airflow plate fin for use with a guided rocket, comprising: (a) a curved surface plate made of relatively high gauge material with geometric openings in order to allow air to flow substantially unrestricted when said the curved plate fin is transverse of said air flow; (b) a support structure for supporting said core structure; and (c) means for mounting said support structure on a control mechanism of said rocket for relative movement between said rocket and said support structure.

2. A curved airflow plate fin as set forth in claim 1, wherein said the airflow plate fin has inner and outer curved surfaces that are curved to the same curvature of the outer periphery of a rocket upon which the airflow plate fin is mounted.

3. A curved airflow plate fin as set forth in claim 1, wherein said means for mounting at one said of said support structure is U shaped with the base of the U being adapted to be secured to said control mechanism, and projections from the base of the U shaped structure being secured to an outer surface of said support structure.

4. A curved airflow plate fin as set forth in claim 1, wherein said the airflow plate fin has geometric openings made up of one central circle, five triangles with their bases aiming towards the central circle, and five semicircular openings close to the outer perimeter of the curved airflow plate.

5. A guided rocket having a plurality of symmetrically disposed aerodynamic control airflow plate fins for decelerating and stabilizing said rocket, each of said the airflow plate fins comprising: (a) a curved plate core structure made of relatively high gauge material with geometric openings for permitting air to flow therethrough substantially unrestricted when said the curved airflow plate fin is transverse of said airflow; (b) a support structure for supporting said core structure; and (c) means for mounting said support structure on a control mechanism of said rocket for controlled movement relative to said rocket for decelerating and stabilizing said rocket during flight.

6. A guided rocket as set forth in claim 5, wherein each of said curved airflow plate fins has inner and outer curved surfaces, curved to the same curvature as the outer periphery of said rocket.

7. A guided rocket as set forth in claim 6, wherein said relatively high gauge material with geometric openings comprises the curved structure of the metal curved airflow plate.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The various features and advantages of the present invention may be more readily understood with reference to the following detailed description taken in conjunction with the accompanying drawings, in which:

[0022] FIG. 1 is a top plan view of the preferred airflow plate fin, showing the overall shape;

[0023] FIG. 2 is a side elevational view of my airflow plate fin;

[0024] FIG. 3 is a combined diagrammatic and top plan view of the airflow plate fin fully deployed;

[0025] FIG. 4 is combined diagrammatic and top plan view of the plate fin retracted position;

[0026] FIG. 5 is a combined perspective and diagrammatic view of a rocket with the airflow plate fins fully deployed;

[0027] FIG. 6 is a combined perspective and diagrammatic view of a rocket with the airflow plate fins attached to its sides.

DETAILED DESCRIPTION OF THE INVENTION

[0028] With initial reference now directed to FIGS. 1 and 2, my new control fin has been generally designated by the reference numeral (1). It comprises a shaped actuator shaft adaptor (2) adapted to be connected to the fuselage of the booster rocket via a typical movable joint or hinge mechanism (not shown) activated by the flight control system. FIG. 1 also shows the numerous specific geometric openings (3) of different shapes and sizes that can be dimensionally adjusted in the manufacturing process depending on the required necessities. Those geometric openings allow air flow through them. At the same time the surface of the curved plate that is not hollow will present a resistance to the forces acting in the opposite way, increasing drag, slowing down the aerodynamic vehicle and facilitating its control before the vehicle reaches its desired objective.

[0029] Referencing FIG. 2, which is a side view showing my curved airflow plate fin (4) and how the opposite forces, represented by the reference numeral (5), collide on the plate when deployed fully on the side of the aerodynamic vehicle traveling at great speed.

[0030] FIG. 3 shows the top of an airflow plate fin (6) fully deployed and attached to the side of the aerodynamic vehicle (7).

[0031] FIG. 4 is top plan view of the airflow plate fin (8) in a retracted position and parallel to the side of the aerodynamic vehicle (9) to diminish drag and improve the flight capabilities of the booster rocket.

[0032] FIG. 5 is a perspective view of a rocket with two airflow plate fins fully deployed (10) and one in the retracted position (15), representing a three-fin triangular arrangement articulated (rotated) on their perpendicular axis by the control flight system (11) located in the interior of the booster rocket (12) with the objective of providing stability and control with small hinge movements. The two curved airflow plate fins (10) are arranged with their plate openings to the direction of rocket or missile motion (13) and against the incoming airflow forces (14).

[0033] FIG. 6 is a side view of the curved airflow plate fins (16) attached to the sides of the booster rocket (12) and completely deployed and re-orientated to the external surface of the aerodynamic vehicle, exemplifying their rotation commanded by the control flight system (11) with sufficient strength to sustain the required aerodynamic and inertial loads. Thus, there has been disclosed an aerodynamic lifting and control surface for use with aerodynamic vehicles such as rockets, and the like, that may be stowed in the body of the vehicle to provide for compact storage of rocket (16) and completely deployed and re-orientated to the external surface of the aerodynamic vehicle, exemplifying their rotation commanded by the control flight system (17) with sufficient strength to sustain the required aerodynamic and inertial loads.

[0034] Thus, there has been disclosed an aerodynamic lifting and control surface for use with aerodynamic vehicles such as rockets, and the like, that may be stowed in the body of the vehicle to provide for compact storage. It is to be understood that the described embodiments are merely illustrative of some of the many specific embodiments which represent applications of the principles of the present invention. Clearly, numerous and other arrangements can be readily devised by those skilled in the art without departing from the scope of the invention. The intended application for use to control rockets, or particularly, reusable booster rockets, determines the specific choice of a light weight and storability of the airflow plate fin embodiment and configuration to substitute and improve the capabilities of conventional grid fins. The airflow plate fin must be sufficiently robust to withstand the loading of forces against its surface requiring effective performance at supersonic, subsonic, or transonic speeds. In some applications, minimizing drag and the ability to function at high temperatures is important, whereas in other applications those capabilities are of less concern.

[0035] The airflow plate fin produces aerodynamic lifting for stability and controls the direction of the rocket when is deployed from a parallel position to the body to which is attached with hinges and aligned perpendicular to the air flow direction.

[0036] The geometric orifices located on the circular curved airflow plates are configured to optimize the flight performance characteristics of the aeronautic vehicle shaped in the form of one central circle, five triangles with their bases aiming towards the central circle, and five semicircular openings close to the outer perimeter of the airflow plate. The sum of the areas of the openings is approximately between three quarters and one half of the total surface of the individual plate, and those can be enlarged or reduced in the manufacturing process to achieve aerodynamic stability and control in order to satisfy the needs of a variety of deployed aeronautic vehicles, consequentially increasing or decreasing the resistance that the plate's surface will encounter when moving at high flight speeds. The total surface area of the circular curved plate will depend on the size and the characteristics of the aeronautic vehicle and its specific desired performance under given circumstances. From the foregoing, it will be seen that this invention is one well adapted to obtain all the ends and objects herein set forth, together with other advantages which are inherent to the structure.

[0037] It will be understood that certain features and sub-combinations are of utility and can be employed without reference to other features and sub-combinations.

[0038] As many possible embodiments may be made of the invention without departing from the scope thereof, it is to be understood that matter herein set forth or shown in the accompanying drawings is to be interpreted as illustrative and not in a limiting sense.