Title of Invention: An Apparatus for Controlling a Spacecraft's Atmospheric

Reentry

[0001] The apparatus consists of an opening in the wing or body of the spacecraft, the opening has multiple actuating fins which form a louver system. This louver system actuates to control the aerodynamic forces acting on the body of the spacecraft.

Technical Field

[0002] The opening would ideally be on a fixed wing. But it can also be on a moving wing, the body, or airframe of the spacecraft. The fins would ideally move in unison but can move independently from each other. They can be actuated with an electric motor system, a hydraulic system, or any other type of system. They can be actuated to control the aerodynamic forces acting on the body of the spacecraft, by adjusting the surface area distribution of the spacecraft.

Background Art

[0003] This invention is similar to how aircrafts' manufacturers are utilizing a main wing with multiple flaps connected to it, in order to control the airflow around the body of the aircraft. Instead of using a one-piece wing, which is not precise enough to correct for small fast turbulences upon landing.

Summary of Invention

[0004] An aerodynamic louver system used in one or more of the following operations: control, adjust, or stabilize, aid in controlling, adjusting or stabilizing a spacecraft's orientation, angle of attack, lift, or position. There could be multiple of these systems on the spacecraft's body, working together to control the aerodynamic forces acting on the body of the spacecraft.

Technical Problem

[0005] Exiting aerospace companies are utilizing bulky wings or flaps in order to control a spacecraft's orientation as it descends into an atmosphere. This method is not precise enough to correct for fast turbulences, furthermore these systems require an extremely high torque to actuate, requiring high power actuation systems and larger heavier parts, due to higher induced strain on the system's parts.

Solution to Problem

[0006] Utilizing multiple smaller fins or flaps reduces the torque required to actuate each fin and reduces the strain on the actuation system's parts, therefore smaller lighter parts can be used, allowing the entire louver system to be faster, more precise and able to correct for smaller faster turbulences. Advantageous Effects of Invention

[0007] Due to this system dividing its aerodynamic control surfaces to smaller lighter parts, it reduces the strain on the aerodynamic system's parts, therefore reducing the chances of a system failure. In addition to making it easier and faster to actuate, allowing it to correct for smaller faster turbulences.

Brief Description of Drawings

[0008] Part [101] of Figure 1 through 8 is a fin of a multiple of fins that form part of the louver system according to an embodiment of the present invention.

Part [102] of Figure 1 through 8 is a section of the wing or body of the spacecraft according to an embodiment of the present invention.

Fig. 1

[0009] [Fig. 1] Is a top view of the louver system according to an embodiment of the present invention.

Fig. 2

[0010] [Fig. 2] Is a bottom view of the louver system of Fig. 1.

Fig. 3

[0011] [Fig. 3] Is a side view of the louver system of Fig. 1.

Fig. 4

[0012] [Fig. 4] Is an opposite side view of the louver system of Fig. 3.

Fig. 5

[0013] [Fig. 5] Is a front view of the louver system of Fig. 1.

Fig. 6

[0014] [Fig. 6] Is a back view of the louver system of Fig. 1.

Fig. 7

[0015] [Fig. 7] Is an isometric view of the louver system of Fig. 1.

Fig. 8 [0016] [Fig. 8] Is a perspective view of the louver system of Fig. 1.