Granted Patent B2

US 12,722,808 · App. 19/107,179 · Granted Sep 1, 2026

Inventor: Furkan Ahmet Tok (Kahramankazan, TR)

Assignee: Tusas—Turk Havacilik Ve Uzay Sanayii Anonim Sirketi

B64G1/58B64G1/44

Abstract

Claims (28)

1 . A thermal control system, comprising:

a body located on a space vehicle;

at least one avionics chamber on the body, avionics equipment being disposed in the at least one avionics chamber;

at least one solar panel extending outward from the body and configured to store flux from a source that generates at least one of heat and radiation;

at least one shield on the body, the at least one shield at least partially covering a surface of the body so as to protect the body from energy provided by the source; and

at least one screen barrier having a transparent form and an opaque form,

wherein, in the transparent form, the at least one screen barrier is activated by an electric field so as to allow passage of the flux in order to keep the avionics equipment on a hot side of the body, with respect to an orbital position of the space vehicle, within a temperature limit predetermined by a manufacturer,

wherein, in the opaque form, the at least one screen barrier at least partially prevents passage of the flux into the at least one avionics chamber, and

wherein the at least one shield comprises the at least one screen barrier.

2 . The thermal control system according to claim 1 , further comprising at least one actuator that actuates the at least one shield so as to open or close the at least one shield on the body.

3 . The thermal control system according to claim 2 , further comprising:

at least one spring ring having a circular form, the at least one spring ring extending outward from the body and holding the at least one shield;

at least one control unit configured to issue a command to the at least one actuator;

a first position, in which the at least one screen barrier connected with the at least one spring ring is overlapped;

a second position, in which the at least one screen barrier is rotated as a fan from the first position to the second position so as to complete one revolution together with the at least one spring ring when the at least one spring ring is released by the at least one actuator upon the command from the at least one control unit; and

at least one lock on the at least one actuator or on the at least one shield,

the at least one lock being configured to fix the at least one screen barrier in the second position.

4 . The thermal control system according to claim 1 , wherein the at least one screen barrier comprises a plurality of screen barriers located sequentially one after another on the at least one shield at radial angle intervals.

5 . The thermal control system according to claim 1 , wherein the at least one holder rotates around an axis of the at least one holder simultaneously with the at least one solar panel.

6 . The thermal control system according to claim 1 , wherein the at least one screen barrier is located on the body on a same side of the body as a side on which the at least one solar panel is attached to the body.

7 . The thermal control system according to claim 1 , wherein the at least one screen barrier comprises a plurality of screen barriers on the at least one shield, and wherein the at least one control unit is configured to operate the plurality of screen barriers in the second position simultaneously in accordance with the temperature data from the at least one sensor, or to allow the plurality of screen barriers to operate locally in accordance with external environmental conditions.

8 . The thermal control system according to claim 1 , further comprising:

at least one heater strip configured to transfer heat by radiation in accordance with the temperature data from the at least one sensor in an operational state of the thermal control system, so as to keep a heat flux within a value predetermined by a user,

wherein the at least one shield is positioned synchronously with a rotational movement of the space vehicle, and

wherein the at least one heater strip and the at least one screen barrier are located on the at least one shield at least partially in contact with one another.

9 . The thermal control system according to claim 8 , wherein the at least one heater strip and the at least one screen barrier are located one after another sequentially on the at least one shield at radial intervals.

10 . The thermal control system according to claim 8 , wherein the at least one heater strip is an infrared heater.

11 . The thermal control system according to claim 1 , wherein the body is a telecommunication satellite.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (71)