[go: up one dir, main page]

WO2024049384A1 - Système de protection thermique - Google Patents

Système de protection thermique Download PDF

Info

Publication number
WO2024049384A1
WO2024049384A1 PCT/TR2023/050836 TR2023050836W WO2024049384A1 WO 2024049384 A1 WO2024049384 A1 WO 2024049384A1 TR 2023050836 W TR2023050836 W TR 2023050836W WO 2024049384 A1 WO2024049384 A1 WO 2024049384A1
Authority
WO
WIPO (PCT)
Prior art keywords
shield
heater
control system
thermal control
heaters
Prior art date
Application number
PCT/TR2023/050836
Other languages
English (en)
Inventor
Furkan Ahmet TOK
Original Assignee
Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from TR2022/013585 external-priority patent/TR2022013585A1/tr
Application filed by Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi filed Critical Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi
Publication of WO2024049384A1 publication Critical patent/WO2024049384A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
    • B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/54—Protection against radiation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/58—Thermal protection, e.g. heat shields

Definitions

  • the present invention relates to a thermal protection system suitable for use in air and/or space vehicles.
  • US8196869B2 which is included in the known-state of the art, discloses a sunshield for satellites. Said shield is located on or adjacent to the equipment deck. After the depot enters orbit, the sunshield is deployed around the cryogenic tank to minimize the heat from the sun and earth, and the shield deflects the heat emitted from these sources into deep space. It is mentioned that the shield is actuated by an actuator to minimize the boiling of the liquid in the tank.
  • US20220048650A1 which is included in the known-state of the art, discloses an attitude control module that allows a space vehicle to control its direction relative to an inertial frame of reference or another entity such as a celestial sphere, specific areas, and nearby objects.
  • the module located outside the space vehicle can be opened and folded. It comprises a system actuated by an actuator, which can be opened and closed circularly.
  • KR20100034501 A which is included in the known-state of the art, discloses a plate positioned outside a satellite body. Said structure comprises a satellite body with a cooling plate system for indirect heating of the satellite body.
  • a horizontal posture maintenance device is fixed on one end of the satellite body. It comprises a heat sink to provide radiant heat energy to the surface of the satellite body.
  • the heat sink is the satellite body supporting the heat sink with one end separate from the surface, and the other end fixed to the horizontal position support device.
  • US9815576B2 which is included in the known-state of the art, discloses a sun shield designed to protect optical sensors on space vehicles from exposure to radiation.
  • Said sun shield comprises a flat panel rotatable in two directions.
  • the azimuth adjustment is provided by a large bearing to which the shield is hinged.
  • the azimuth bearing extends around the opening in the enclosure.
  • An azimuth axis around which the bearing rotates can be aligned with the sensor's field of view.
  • a motor or another suitable device is used to rotate a part of the sun shield and bearing relative to the enclosure.
  • US7837154B2 which is included in the known-state of the art, discloses that a temperature in the part of the space vehicle that is exposed to the sun can reach up to 1700 °C, and a sun shield is used to prevent this.
  • the sun shield is locked using springs and bearings when it reaches a desired position in open and closed positions.
  • thermal protection system according to the present invention, more durable and more reliable thermal protection is provided.
  • Another object of the present invention is to provide a lightweight thermal protection system for air and/or space vehicles.
  • Another object of the present invention is to provide thermal protection in a practical, effective and easy way.
  • the thermal protection system realized to achieve the object of the present invention, which is defined in the first claim and other claims dependent thereon, comprises a source, such as the sun, that produces heat and/or radiation.
  • the thermal protection system comprises a body provided on a space vehicle; and an avionics chamber in the body, with avionic equipment therein.
  • the thermal protection system comprises a plurality of panels located on the outer side of the body facing deep space to store flux from a source such as the sun.
  • the thermal protection system comprises at least one heater which is heated for the equipment in which the panels overheat due to the solar flux reaching the satellite at different angles while the satellite is cruising on the orbit and the heat loads of the equipment placed on the panels, or in which the panels that are not exposed to any solar flux experience supercooling, so that they are kept within temperature limits predetermined by the manufacturer, wherein the heater is located on the body, close to the avionics chamber, between the avionics chamber and the panel, on the surface of the avionics chamber facing the panel.
  • It comprises at least one heater which is heated for the equipment on the farthest side from the heat flux by the source with respect to the orbital position of the space vehicle, wherein the equipment is not exposed to any heat flux and remains on the relatively cold side, wherein the heater enables the equipment to be kept within the temperature adequacy limits.
  • the thermal protection system comprises at least one shield located on a surface of the body interacting with the space environment, wherein the shield at least partially covers the body surface to protect the body from the energy provided by the source. It comprises at least one actuator that enables the shield to be opened and closed on the body.
  • the actuator is positioned on the body.
  • the heaters may be located on the body or on the shield.
  • the thermal protection system comprises the heaters in the form of strips and/or rods.
  • the thermal protection system comprises at least one holder extending outward from the body, allowing the shield to be held thereon. It comprises at least one sensor located in connection with the body for detecting temperature data of external environment of the space vehicle. It comprises at least one control unit that allows the execution of various commands according to the data from the sensor. By means of the thermistor data on the body, the control unit detects condition and location of the need, and the system activates to provide opening. It comprises at least one spring on the holder, which is compressed in the actuator.
  • It comprises a first position (I) in which the heater strips are overlapped when the spring is in the compressed position; and a second position (II), wherein at least one of the heater strips are rotated as an accordion from the first position (I) to the second position (II) to complete one revolution around the holder when the spring, which is compressed in the actuator triggered by a command from the control unit, is released. It comprises at least one lock on the actuator, which allows the heater strips in the second position (II) to remain fixed in the second position (II).
  • the system performs the first opening movement almost 90° sideways upon the command received from the control unit, and then, as a result of the release of the compressed spring system in the actuator, the heaters will be opened as an accordion by rotating around the body axis to complete one revolution.
  • the first heater reaching the actuator by completing the revolution will be locked by the lock structure on the actuator.
  • the heaters are activated to provide heat.
  • the lock structure will be released and the actuator will be activated, and with the release of the spring, the heaters will rotate in the opposite direction and fold back to the first position (I).
  • the thermal protection system comprises at least one spring ring, which has a circular form extending outward from the body, allowing the shield to be held thereon. It comprises the first position (I) in which the heaters connected with the spring ring are overlapped; the second position (II), wherein at least one heater is rotated as a fan from the first position (I) to the second position (II) to complete one revolution together with the spring ring when the spring ring, which is triggered by the actuator upon a command from the control unit, is released; the lock on the actuator or the shield, which allows the heaters in the second position (II) to remain fixed in the second position (II).
  • the system performs the first opening movement almost 90° sideways upon the command received from the control unit, and then, as a result of the release of the spring system compressed inside the spring ring, the heaters will be folded open like a fan by rotating around the body axis to complete one revolution.
  • the first heater to reach the folding motor-gear system by completing the revolution will be locked by the lock structure on the folding motor-gear system or on the main heater.
  • the heaters are activated to provide heat.
  • the lock structure will be released and the actuator, which is a folding motor-gear system, will be activated, and with the release of the spring, the heaters will rotate in the opposite direction and will be folded back to their initial state, which is in the first position (I).
  • the rotation axes of two reverse gears in the actuator, which is a folding motor-gear system, are positioned to be 90° to each other.
  • the gear connected to the actuator and receiving the first driving force is fixed on the solar panel structure, while the second gear is positioned in the spring-loaded opening ring or on the first heater.
  • the dimensions of the gears can be changed according to the design.
  • the sizes and levels of the screen barriers opened in the form of a fan can be different from each other.
  • the thermal protection system comprises the heaters made of infrared strips.
  • the thermal protection system comprises heaters with solar cells positioned on their surfaces facing space. It comprises that the infrared heater strips with solar cells positioned on their surfaces facing deep space support the power consumption apart from the main panels.
  • the thermal protection system comprises the holder that rotates around an axis to which it is connected by the panel, synchronously and concentric with the panel. During all this operation, the thermal protection system comprises the synchronous rotation or stop of the holder and the panel structure.
  • the thermal protection system comprises heaters positioned one behind the other sequentially on the shield with radial angle intervals, on the point where they are supported by the panel.
  • the thermal protection system comprises a control unit, which operates each of the heaters on the shield in the second position (II) simultaneously according to the data from the sensors, or allows them to operate locally according to external environmental conditions.
  • the heaters can operate at the same time or can be activated separately and locally.
  • the thermal protection system comprises at least one screen barrier that transfers heat by radiation according to the external environment data from the sensors in the operational state, in order to keep the heat flux within the value predetermined by the user. It comprises the shield which is positioned synchronously with the rotational movement of the space vehicle, and on which the heater and the screen barrier are located at least partially in contact with each other.
  • the thermal protection system comprises screen barriers made of a liquid - crystal flexible material. Screen barriers can form the main structure of the shield.
  • the thermal protection system comprises positioning the heater and screen barriers, respectively, one after the other sequentially at radial intervals on the shield.
  • the thermal protection system comprises the body, which is a telecommunication satellite.
  • Figure 1 is a perspective view of the thermal protection system.
  • Figure 2 is a perspective view of the spring ring, heater, screen barrier and actuator.
  • Figure 3 is a perspective view of the shield, screen barrier and heater.
  • Figure 4 is a perspective view of the shield, screen barrier and heater.
  • Figure 5 is a perspective view of the first position (I).
  • Figure 6 is a perspective view of the second position (II).
  • Figure 7 is a perspective view of the holder, lock and actuator.
  • the thermal protection system (1) comprises a source (S) generating heat and/or radiation; a body (2) located on a space vehicle; at least one avionics chamber (A) on the body (2), in which the avionics equipment is provided; at least one panel (P) outside the body (2), which extends outward from the body (2) and stores the flux from the source (S).
  • S source
  • A avionics chamber
  • P panel
  • the thermal protection system (1) comprises at least one heater (3) which is heated for the equipment on the colder side relative to the orbital position of the space vehicle, so that the equipment is kept within the temperature limits predetermined by the manufacturer, wherein the heater (3) is located on the body (2) close to the avionics chamber (A), between the avionics chamber (A) and the panel (P), and on the surface of the avionics chamber (A) facing the panel (P).
  • the thermal protection system comprises a source (S) generating heat and/or radiation.
  • (1) comprises a body (2) on the space vehicle; and an avionics chamber (A) in the body
  • the thermal protection system (1) comprises at least one panel (P) on the body (2).
  • the panel (P) provides storage of the flux from the source (S).
  • It comprises at least one heater (3) which is heated for the equipment in which the panels (P) overheat due to the flux from the orbit of the space vehicle and to the heat loads of the equipment placed over the panels (P), or in which the panels (P) that are not exposed to any flux experience supercooling, so that the equipment is kept within temperature limits predetermined by the manufacturer, wherein the heater (3) is located on the body (2), close to the avionics chamber (A), between the avionics chamber (A) and the panel (P), on the surface of the avionics chamber (A) facing the panel (P).
  • the heater (3) is heated for the equipment on the farthest side from the heat flux by the source (S) with respect to the orbital position of the space vehicle, wherein the equipment is not exposed to any heat flux and remains on the relatively cold side, wherein the heater enables the equipment to be kept within the temperature adequacy limits.
  • the thermal protection system (1) comprises at least one shield (4) located on and/or close to the outer surface of the body (2) that interacts with the space environment, wherein the shield (4) at least partially covers the surface of the body (2) to protect the body (2) from the energy provided by the source (S); at least one actuator (5) that actuates the shield (4) to be opened or closed on the body (2); the heater (3) located on the shield (4). Since the shield (4) is located on the wall of the body
  • the shield (4) can be used by the user according to external environmental conditions thanks to its retractable opening mechanism.
  • the thermal protection system (1) comprises the heater
  • the thermal protection system (1) comprises at least one holder (6) extending outward from the body (2) and allowing the shield (4) to be held thereon; at least one sensor (7) connected with the body (2) for detecting temperature data of external environment of the space vehicle; at least one control unit (8) that allows the execution of various commands according to the data from the sensor (7); a first position (I) in which the heaters (3) are overlapped so as to be in connection with the holder (6); a second position (II), wherein at least one heater (3) is triggered by the actuator (5) upon a command received from the control unit (8), such that is rotated as an accordion from the first position (I) to the second position (II) to complete one revolution around the holder (6); at least one lock (9) on the actuator (5), which allows the heaters (3) in second position (II) to remain fixed in the second position (II).
  • the system is activated to provide opening. It comprises a first position (I) in which the heaters (3) are overlapped in a position where the spring is compressed in the actuator (5) positioned on the holder (6); a second position (II), wherein at least one of the heater (3) strips are rotated as an accordion from the first position (I) to the second position (II) to complete one revolution around the holder (6) when the spring, which is compressed in the actuator (5) triggered by a command from the control unit (8), is released. Thanks to the lock (9), the heaters (3) are enabled to be remain fixed in the first position (I) or the second position (II).
  • the thermal protection system (1) comprises at least one spring ring (10) which has a circular form extending outward from the body (2), allowing the shield (4) to be held thereon; the first position (I) in which the heaters (3) connected with the spring ring (10) are overlapped; the second position (II), wherein at least one heater (3) is rotated as a fan from the first position (I) to the second position (II) to complete one revolution together with the spring ring (10) when the spring ring (10), which is triggered by the actuator (5) upon a command from the control unit (8), is released; the lock (9) on the actuator (5) or the shield (4), which allows the heaters (3) in the second position (II) to remain fixed in the second position (II). Thanks to the lock (9), the heaters (3) can remain fixed in the first position (I) or the second position (II).
  • the thermal protection system (1) comprises the heater (3) which is an infrared strip.
  • the capacities of the heaters (3) can be revised according to the design, so that the panel (P) in need of heating becomes active and provides heat transfer to the panel (P) area by radiation.
  • the thermal protection system (1) comprises the heater (3) with solar cells that are positioned on surfaces thereof facing the space.
  • the power consumption can be supported by the solar cells, apart from the main solar panels (P).
  • the thermal protection system (1) comprises the holder (6) which rotates around the axis it is supported by the panel (P), in synchronization with the panel (P).
  • the holder (6) provides a synchronous rotation or stop state with the solar panel (P) structure.
  • the thermal protection system (1) comprises heaters (3) located sequentially one after the other on the shield (4) at radial intervals, at the point where they are supported by the panel (P). Thanks to the heaters (3) positioned with radial angle intervals on the shield (4), wide-angle heating is provided on the body (2) surface.
  • the thermal protection system (1) comprises the control unit (8), which operates each of the heaters (3) on the shield (4) in the second position (II) simultaneously according to the data from the sensors (7), or allows them to operate locally according to external environmental conditions.
  • the heaters (3) can operate at the same time or can be activated separately and locally. In this way, the space vehicle is heated locally, depending on the region of need.
  • the thermal protection system (1) comprises at least one screen barrier (11) that transfers heat by radiation according to the external environment data from the sensors (7) in the operational state, in order to keep the heat flux within the value predetermined by the user; the shield (4) which is positioned synchronously with the rotational movement of the space vehicle, and on which the heater (3) and the screen barrier (11) are located at least partially in contact with each other.
  • the heat flux transmission or prevention is ensured by the screen barriers (11), which have the function of preventing radiation. It does not affect other systems since it transfers heat only by radiation during its heating function and the interior of the body (2) is isolated from the environment.
  • the thermal protection system (1) comprises screen barriers (11) made of a liquid - crystal flexible material. Thanks to the screen barriers (11) made of a liquid-crystal material, they can be activated or deactivated by electric current, so that heat flux transfer to the body (2) is provided or prevented.
  • the necessary heat flux prevention or heating functions are fulfilled by means of heaters (3) and liquid crystal anti- radiation screen barriers (11), thus contributing to keeping the temperatures of equipment and structural parts at desired levels.
  • the thermal protection system (1) comprises the heater (3) and the screen barrier (11), which are each located one after the other sequentially on the shield at radial intervals. This provides a wide-angle heating on the body (2) surface.
  • the thermal protection system (1) comprises the body (2), which is a telecommunication satellite. It comprises the shield (4) comprising the heater (3), the heater (3) being connected to the body (2) or located on the side of North-

Landscapes

  • Engineering & Computer Science (AREA)
  • General Health & Medical Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Health & Medical Sciences (AREA)
  • Toxicology (AREA)
  • Critical Care (AREA)
  • Emergency Medicine (AREA)
  • Environmental Sciences (AREA)
  • Environmental & Geological Engineering (AREA)
  • Biodiversity & Conservation Biology (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Air-Conditioning For Vehicles (AREA)

Abstract

La présente invention concerne une source (S) générant de la chaleur et/ou un rayonnement ; un corps (2) situé sur un véhicule spatial ; au moins une chambre avionique (A) sur le corps (2), dans laquelle est disposé l'équipement avionique ; au moins un panneau (P) à l'extérieur du corps (2), qui s'étend vers l'extérieur à partir du corps (2) et stocke le flux provenant de la source (S).
PCT/TR2023/050836 2022-08-31 2023-08-21 Système de protection thermique WO2024049384A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2022013585 2022-08-31
TR2022/013585 TR2022013585A1 (tr) 2022-08-31 Bir termal koruma sistemi.

Publications (1)

Publication Number Publication Date
WO2024049384A1 true WO2024049384A1 (fr) 2024-03-07

Family

ID=90098383

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2023/050836 WO2024049384A1 (fr) 2022-08-31 2023-08-21 Système de protection thermique

Country Status (1)

Country Link
WO (1) WO2024049384A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE8120156U1 (de) * 1981-07-10 1983-03-10 Dornier System Gmbh, 7990 Friedrichshafen Behaelter mit an den behaelterwaenden angeordneten heizkoerpern und/oder blenden
US6003817A (en) * 1996-11-12 1999-12-21 Motorola, Inc. Actively controlled thermal panel and method therefor
JP2020001654A (ja) * 2018-07-02 2020-01-09 三菱電機株式会社 宇宙機構体

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE8120156U1 (de) * 1981-07-10 1983-03-10 Dornier System Gmbh, 7990 Friedrichshafen Behaelter mit an den behaelterwaenden angeordneten heizkoerpern und/oder blenden
US6003817A (en) * 1996-11-12 1999-12-21 Motorola, Inc. Actively controlled thermal panel and method therefor
JP2020001654A (ja) * 2018-07-02 2020-01-09 三菱電機株式会社 宇宙機構体

Similar Documents

Publication Publication Date Title
Tachikawa et al. Advanced passive thermal control materials and devices for spacecraft: a review
JP2008265522A (ja) 熱制御装置
JP5126854B2 (ja) 宇宙探査装置
EP0780304B1 (fr) Radiateur déployable à double fonction et couverture pour radiateur
KR101575920B1 (ko) 위성 자세 제어 방법 및 자세-제어 위성
EP1135292A2 (fr) Engin spatial
US5653407A (en) Geocentric pointing three-axis stabilised satellite in low orbit with single-axis steerable solar generator
JP2002308199A (ja) 展開可能な宇宙船用放熱器
EP1999023A2 (fr) Satellite comportant des radiateurs thermiques pouvant etre articules et deployes
US9708081B2 (en) Radiator with reduced insolation for satellite and satellite provided with such a radiator
EP2983992A2 (fr) Bouclier d'orbite de transfert de génération thermique
US9828116B1 (en) Spacecraft
WO2024049384A1 (fr) Système de protection thermique
WO2024049385A1 (fr) Système de protection thermique
Novak et al. Development of a thermal control architecture for the Mars Exploration Rovers
TR2022013588A1 (tr) Bir termal koruma sistemi.
TR2022013585A1 (tr) Bir termal koruma sistemi.
US11926442B2 (en) Multiple function spacecraft sunshade systems and methods
Novak et al. Mars exploration rover surface mission flight thermal performance
US10618677B1 (en) Articulating sunshield
US20190337646A1 (en) Spacecraft
US20240384947A1 (en) Thermal radiator shutter and system and method for thermal control using a thermal radiator shutter
Ferrero et al. The Challenges of the Thermal Design of BepiColombo Mercury Planetary Orbiter
Choi Using paraffin with-10 C to 10 C melting point for payload thermal energy storage in SpaceX dragon trunk
Schor Passive thermal control with passive sun shield for low-temperature sensors

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 23802345

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 2023802345

Country of ref document: EP

ENP Entry into the national phase

Ref document number: 2023802345

Country of ref document: EP

Effective date: 20250331