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WO2024123270A1 - A protector for nano satellites - Google Patents

A protector for nano satellites Download PDF

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Publication number
WO2024123270A1
WO2024123270A1 PCT/TR2022/051709 TR2022051709W WO2024123270A1 WO 2024123270 A1 WO2024123270 A1 WO 2024123270A1 TR 2022051709 W TR2022051709 W TR 2022051709W WO 2024123270 A1 WO2024123270 A1 WO 2024123270A1
Authority
WO
WIPO (PCT)
Prior art keywords
nano
nano satellite
satellite
satellites
protective equipment
Prior art date
Application number
PCT/TR2022/051709
Other languages
French (fr)
Inventor
Ayse Meric YAZICI
Original Assignee
Yazici Ayse Meric
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 TR2022/018707 external-priority patent/TR2022018707A2/en
Application filed by Yazici Ayse Meric filed Critical Yazici Ayse Meric
Publication of WO2024123270A1 publication Critical patent/WO2024123270A1/en

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
    • 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
    • B64G1/56—Protection against meteoroids or space debris
    • 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
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • B64G1/68—Arrangements or adaptations of apparatus or instruments, not otherwise provided for of meteoroid or space debris detectors

Definitions

  • the patent application regrads a design for protecting nano-satellites from extreme temperature fluctuations. It features a a cone shaped design that protects the equipment on board the satellite from low and high temperatures and a GPS that detects space debris and reports its coordinates.
  • Satellites travelling at various altitudes around the Earth move in and out of the Earth's shadow, and are therefore exposed to extreme temperature differences. Cyclically repeated temperature changes can cause damage to satellite structural subsystems.
  • Satellites are exposed to heat from both the sun and the earth. There must be heat dissipation between the parts of each element in the satellite. Miniaturised satellites are densely packed within the smaller satellite volume due to high- power components and payloads, causing thermal problems as the available radiative surface area decreases. Solving thermal challenges is imperative for high-power, scientific and cryogenic small satellite missions.
  • nano satellites One of the main challenges of nano satellites is low-temperature operation. In orbit, the spacecraft surface experiences extreme temperature fluctuations that can reach up to ⁇ 100 °C. Various materials such as aluminium, titanium, graphene composites and composite sandwich panels are used in the production of nano satellites. These materials differ in cost, manufacturing process, mass, strength, durability and required labour. The main objective of the thermal design of a nano satellite is to keep all elements of the satellite within specified temperature ranges.
  • a simple thermal strap containing a thermal switch that can be retrospectively attached to a nanosatellite can achieve a significant temperature reduction.
  • Aluminium shielding to be placed on the structure surrounding the satellite subsystems or under the solar panels and thermal blanket, radiator or cooling block designs to be placed in critical subsystems such as batteries.
  • the advantage of our invention over existing techniques is the multilayered internal equipment protective funnel, which is additionally placed inside the nano satellites.
  • This multi-layered internal equipment protective funnel prevents heat from entering the interior and prevents damage to the internal equipment.
  • the multilayer internal equipment protective funnel will keep the thermal balance at a stable level at all times.
  • the invention is a nano satellite in which the state of the art is exceeded, disadvantages are eliminated and additional advantages are included.
  • the purpose of the invention is to ensure the thermal stability of the equipment in the nano satellite.
  • Another purpose of the invention is to detect and report space debris that may endanger the satellite.
  • the design of the inventive protector was inspired by an annelid worm known as the Pompeii worm (Alvinella Pompejana), which lives in deep-sea hydrothermal vents in the Pacific Ocean.
  • Pompeii worms live in the ocean at a depth of about 2600 metres. In this environment, pressures often reach 260 bar and temperatures reach 350°C.
  • the Pompeii worm is resistant to extreme environmental conditions, including high temperatures and pressures, as well as high levels of sulphur and heavy metals.
  • the Pompeii worm has developed adaptations for heat reversal in a protective tube made of positively and negatively twisted polymer layers containing a stable glycoprotein matrix, elemental sulphur, a number of heat shock proteins and stress oxidative enzymes.
  • Pompeii worm can withstand temperatures as high as 105°C.
  • Pompeii worms live in tubes, which are the exoskeleton of the body against extreme temperatures and allow the worm to settle on the chimney walls.
  • the material forming the tubes of Pompeii worms is an antero-ventral granular shield. Most of the material forming this shield is homogeneous granules secreted by the deep mother cells. Although the organic matter of the tube is granules, the other 7% is composed of hexose sugar, an oligosaccharide.
  • the tube consists of a concentric multilayered fibrous structure in which overlapping parallel layers of fibrils change direction from one leaf to another.
  • the inner surface of the tubes is covered with multilayered filamentous bacteria of successive material.
  • the zinc-iron sulphide nanocrystals grouped in sub- micrometre-sized clusters, consist of layers of tubes with proteins. These minerals show a special zinc-iron signature and, unlike mineral deposits found outside the tubes, have a protected dimension. This acts as an effective barrier against the external environment of the tube.
  • Pompeii worm tubes react very little to disulphide bond-breaking agents, although a cycle of concentrated hydrochloric acid and potassium hydroxide treatments causes delamination, swelling and some dissolution. Thermal stability is also excellent with little swelling or shrinkage in the temperature range 0 to 100°C.
  • Pompeii worms live in funnel-shaped multilayered proteinaceous tubes on the surface of zinc sulphide diffusers.
  • the anterior ends of the tubes have a radial appearance.
  • the tube has a maximum diameter of 2 cm.
  • the anterior end and outer surface of the tube are usually scaly.
  • the tube opening is either cylindrical or funnel-shaped, sometimes with a transverse septum separating two connected tubes.
  • Figure - 1 Illustrates the deisign fitted to a nano satellite from a top cover view.
  • Figure - 2 Illustrates the design fitted to a nano satellite from a side cover view.
  • Figure - 3 lllustrtes the design fitted to a nano satellite from a bottom cover view.
  • Figure - 4 This is an open view of the nano satellite covers.
  • Figure - 6 Illustrates protector used in the invention in the nanosatellite.
  • FIG - 7 View of the GPS module used in the invention in the nanosatellite.
  • Figure - 8 Solar panels used on the surface of a nanosatellite.
  • nano satellite (A) is described by way of nonlimiting examples only for a better understanding of the subject matter.
  • the nano satellite (A) subject to the invention has a body comprising a top cover (1 ), side covers (2) and a bottom cover (3).
  • Figure 1 shows a view of the top cover (1).
  • the protective equipment (10) is placed in the centre of the top cover (1 ).
  • Figure 2 shows the side covers (2). On the side covers (2), there are cavities (7) for saving, channel stabiliser (5) to fix all covers together, electronic card slots (8) and screw holes (9) to fix electronic cards. There are also ventilation holes (6) on the side covers (2) to provide air circulation.
  • Figure 3 shows the back cover (3), which is a flat plate.
  • the protective equipment (10) is placed with the base part on the inner surface of the back cover (3) and the roof part on the mouth (4) in the centre of the top cover (1 ), so as to protrude outwards. In this way, it protects the electronic equipment inside the body from cold and hot ambient conditions.
  • the protective equipment (10) is designed in the form of a funnel, inspired by the Pompeii worm, narrowing towards the top cover (1 ). But alternatively it can also be produced in cylinder form.
  • the multilayer protective equipment (10) placed inside the nano satellite (A) provides thermal stability to prevent damage to the equipment inside the nano satellite (A).
  • Internal protective equipment (10) inspired by the protective funnel shape of the Pompeii worm's multi-layered internal equipment, is placed inside the nano satellite (A). However, the tube does not completely enter the nano satellite (A). The end remains outside. The aim here is to stabilise the thermal heat between the layers.
  • the main purpose of the multilayer protective equipment (10) is to keep the external heat outside the nano satellite (A) and prevent the heat from passing into the layers.
  • the protective equipment (10) is of multilayer construction.
  • the multilayer protective equipment (10) consists of three to six layers and is a concentrically multilayered fibrous structure. Between two successive layers is an intermediate layer of zinc-iron sulphide particles.
  • the multi-layered funnel form prevents each of the nano satellite's internal equipment from being exposed to heat.
  • Another feature of the inventive nano satellite (A) is that it has a GPS (11 ) which detects space debris and inactive satellites, and notifies in The International Space Station.
  • This GPS (11 ) is placed in a GPS chamber (13) located in the body.
  • nano satellite (A) subject to the invention is that at least one surface is covered with solar panels (12). In this way, it can obtain its electricity requirement from sun rays.

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • Critical Care (AREA)
  • Emergency Medicine (AREA)
  • General Health & Medical Sciences (AREA)
  • Details Of Aerials (AREA)

Abstract

The invention relates to a nano satellite (A) comprising a protective equipment 5 (10) which protects the equipment on board from low and high temperatures, and a GPS (11) which detects space debris and notifies in The International Space Station centre.

Description

A PROTECTOR FOR NANO SATELLITES
Technical field:
The patent application regrads a design for protecting nano-satellites from extreme temperature fluctuations. It features a a cone shaped design that protects the equipment on board the satellite from low and high temperatures and a GPS that detects space debris and reports its coordinates.
Background art:
Satellites travelling at various altitudes around the Earth move in and out of the Earth's shadow, and are therefore exposed to extreme temperature differences. Cyclically repeated temperature changes can cause damage to satellite structural subsystems.
Satellites are exposed to heat from both the sun and the earth. There must be heat dissipation between the parts of each element in the satellite. Miniaturised satellites are densely packed within the smaller satellite volume due to high- power components and payloads, causing thermal problems as the available radiative surface area decreases. Solving thermal challenges is imperative for high-power, scientific and cryogenic small satellite missions.
In recent years, there has been an increasing growth in the small satellite sector, especially in nano satellites (1 kg - 10 kg). The widespread use of nanosatellites with their low cost has encouraged commercialisation.
One of the main challenges of nano satellites is low-temperature operation. In orbit, the spacecraft surface experiences extreme temperature fluctuations that can reach up to ±100 °C. Various materials such as aluminium, titanium, graphene composites and composite sandwich panels are used in the production of nano satellites. These materials differ in cost, manufacturing process, mass, strength, durability and required labour. The main objective of the thermal design of a nano satellite is to keep all elements of the satellite within specified temperature ranges.
Some of the existing applications to control the heat in nano satellites are as follows:
• The entire surface of the nano satellites is covered with solar cells.
• A simple thermal strap containing a thermal switch that can be retrospectively attached to a nanosatellite can achieve a significant temperature reduction.
• Optical coatings on nanosatellites.
• Heaters placed in the subsystems of nano satellites.
• Anodised coating of materials to increase the temperature resistance of the nano satellite.
• Aluminium shielding to be placed on the structure surrounding the satellite subsystems or under the solar panels and thermal blanket, radiator or cooling block designs to be placed in critical subsystems such as batteries.
Conventional solutions are insufficient to provide thermal insulation of nano satellites. The advantage of our invention over existing techniques is the multilayered internal equipment protective funnel, which is additionally placed inside the nano satellites. This multi-layered internal equipment protective funnel prevents heat from entering the interior and prevents damage to the internal equipment. The multilayer internal equipment protective funnel will keep the thermal balance at a stable level at all times.
In the Chinese patent document CN113911400A numbered CN113911400A, which was encountered in the literature search, a nano satellite containing thermal insulation boards on the outer wall is described. In the said document, the funnel or cylinder-shaped multi-layer protector in the present invention was not encountered. There is also no GPS for space junk detection.
As a result, there is a need for a new nanosatellite in which the known state of the technique is overcome and its disadvantages are eliminated.
Summary of the invention:
The invention is a nano satellite in which the state of the art is exceeded, disadvantages are eliminated and additional advantages are included.
The purpose of the invention is to ensure the thermal stability of the equipment in the nano satellite.
Another purpose of the invention is to detect and report space debris that may endanger the satellite.
The design of the inventive protector was inspired by an annelid worm known as the Pompeii worm (Alvinella Pompejana), which lives in deep-sea hydrothermal vents in the Pacific Ocean. Pompeii worms live in the ocean at a depth of about 2600 metres. In this environment, pressures often reach 260 bar and temperatures reach 350°C. The Pompeii worm is resistant to extreme environmental conditions, including high temperatures and pressures, as well as high levels of sulphur and heavy metals. To cope with high temperatures, the Pompeii worm has developed adaptations for heat reversal in a protective tube made of positively and negatively twisted polymer layers containing a stable glycoprotein matrix, elemental sulphur, a number of heat shock proteins and stress oxidative enzymes. These worms remain stable and active at temperatures above 50°C and these tubes insulate the worms from high temperatures. A Pompeii worm can withstand temperatures as high as 105°C. Pompeii worms live in tubes, which are the exoskeleton of the body against extreme temperatures and allow the worm to settle on the chimney walls. The material forming the tubes of Pompeii worms is an antero-ventral granular shield. Most of the material forming this shield is homogeneous granules secreted by the deep mother cells. Although the organic matter of the tube is granules, the other 7% is composed of hexose sugar, an oligosaccharide. The tube consists of a concentric multilayered fibrous structure in which overlapping parallel layers of fibrils change direction from one leaf to another.
The inner surface of the tubes is covered with multilayered filamentous bacteria of successive material. The zinc-iron sulphide nanocrystals, grouped in sub- micrometre-sized clusters, consist of layers of tubes with proteins. These minerals show a special zinc-iron signature and, unlike mineral deposits found outside the tubes, have a protected dimension. This acts as an effective barrier against the external environment of the tube. Pompeii worm tubes react very little to disulphide bond-breaking agents, although a cycle of concentrated hydrochloric acid and potassium hydroxide treatments causes delamination, swelling and some dissolution. Thermal stability is also excellent with little swelling or shrinkage in the temperature range 0 to 100°C.
Pompeii worms live in funnel-shaped multilayered proteinaceous tubes on the surface of zinc sulphide diffusers. The anterior ends of the tubes have a radial appearance. The tube has a maximum diameter of 2 cm. The anterior end and outer surface of the tube are usually scaly. The tube opening is either cylindrical or funnel-shaped, sometimes with a transverse septum separating two connected tubes.
Brief description of figures:
The invention will be described with reference to the accompanying figures, so that the features of the invention will be more clearly understood. However, it is not intended to limit the invention to these particular embodiments. On the contrary, it is also intended to cover all alternatives, modifications and equivalents of the invention which may be included within the field defined by the appended claims. It is to be understood that the details shown are shown solely for the purpose of illustrating preferred embodiments of the present invention and are presented for the purpose of providing the most useful and easily understood description of both the embodiment of the methods and the rules and conceptual features of the invention. In these figures;
Figure - 1 Illustrates the deisign fitted to a nano satellite from a top cover view.
Figure - 2 Illustrates the design fitted to a nano satellite from a side cover view.
Figure - 3 lllustrtes the design fitted to a nano satellite from a bottom cover view.
Figure - 4 This is an open view of the nano satellite covers.
Figure - 5 Side view of the protector used in the invention.
Figure - 6 Illustrates protector used in the invention in the nanosatellite.
Figure - 7 View of the GPS module used in the invention in the nanosatellite. Figure - 8 Solar panels used on the surface of a nanosatellite.
The figures which will assist in the understanding of the present invention are numbered as indicated in the accompanying drawing and are given below with their names.
List of reference numerals:
1. Top cover
2. Side cover
3. Bottom cover
4. Mouth
5. Channel stabiliser
6. Ventilation hole 7. Gap
8. Electronic card slot
9. Screw hole
10. Protective equipment
11. GPS
12.Solar panel
13.GPS hopper
A. Nano Satellite
Detailed description of the invention:
In this detailed description, the nano satellite (A) is described by way of nonlimiting examples only for a better understanding of the subject matter.
The nano satellite (A) subject to the invention has a body comprising a top cover (1 ), side covers (2) and a bottom cover (3). Figure 1 shows a view of the top cover (1). In the centre of the top cover (1 ), there is an mouth (4) where the protective equipment (10) is placed. There are also material-saving gaps (7) to reduce cost.
Figure 2 shows the side covers (2). On the side covers (2), there are cavities (7) for saving, channel stabiliser (5) to fix all covers together, electronic card slots (8) and screw holes (9) to fix electronic cards. There are also ventilation holes (6) on the side covers (2) to provide air circulation. Figure 3 shows the back cover (3), which is a flat plate.
One of the distinguishing features of the nano satellite (A) is the protective equipment (10). This protective equipment (10) is placed with the base part on the inner surface of the back cover (3) and the roof part on the mouth (4) in the centre of the top cover (1 ), so as to protrude outwards. In this way, it protects the electronic equipment inside the body from cold and hot ambient conditions. The protective equipment (10) is designed in the form of a funnel, inspired by the Pompeii worm, narrowing towards the top cover (1 ). But alternatively it can also be produced in cylinder form.
The multilayer protective equipment (10) placed inside the nano satellite (A) provides thermal stability to prevent damage to the equipment inside the nano satellite (A). Internal protective equipment (10), inspired by the protective funnel shape of the Pompeii worm's multi-layered internal equipment, is placed inside the nano satellite (A). However, the tube does not completely enter the nano satellite (A). The end remains outside. The aim here is to stabilise the thermal heat between the layers. The main purpose of the multilayer protective equipment (10) is to keep the external heat outside the nano satellite (A) and prevent the heat from passing into the layers.
The protective equipment (10) is of multilayer construction. The multilayer protective equipment (10) consists of three to six layers and is a concentrically multilayered fibrous structure. Between two successive layers is an intermediate layer of zinc-iron sulphide particles. Inspired by the layered structure of the Pompeii Worm tube, the multi-layered funnel form prevents each of the nano satellite's internal equipment from being exposed to heat.
Another feature of the inventive nano satellite (A) is that it has a GPS (11 ) which detects space debris and inactive satellites, and notifies in The International Space Station. This GPS (11 ) is placed in a GPS chamber (13) located in the body.
Another feature of the nano satellite (A) subject to the invention is that at least one surface is covered with solar panels (12). In this way, it can obtain its electricity requirement from sun rays.

Claims

1. The invention relates to nano satellites (A) having a body comprising a bottom cover (3), a top cover (1 ) and side covers (2), characterised in that it is provided with at least one protective device consisting of a plurality of layers, the bottom part of which is disposed on the inner surface of the back cover (3) and the roof part of which is disposed in such a way that it protrudes into the mouth (4) in the centre of the top cover (1 ).
2. A nano satellite (A) according to claim 1 , characterised in that the protective equipment (10) has 3 to 6 layers.
3. A nano satellite (A) according to claim 1 , characterised in that the protective equipment (10) comprises an intermediate layer of zinc-iron sulphide particles between two successive layers.
4. A nano satellite (A) according to claim 1 , characterised in that the protective equipment (10) is in the form of a funnel narrowing towards the upper cover
(I )-
5. A nano satellite (A) according to claim 1 , characterised in that the protective equipment (10) is in the form of a cylinder.
6. A nano satellite (A) according to claim 1 , characterised in that it has a GPS
(I I ) which detects space debris, inactive satellites and notifies in The International Space Station centre.
7. A nano satellite (A) according to claim 1 , characterised in that it comprises a GPS receptacle (13) on the housing in which the GPS (11 ) is located. A nano satellite (A) according to claim 1 , characterised in that at least one surface of the body comprises solar panels (12) generating electricity from solar radiation.
PCT/TR2022/051709 2022-12-06 2022-12-30 A protector for nano satellites WO2024123270A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2022/018707 TR2022018707A2 (en) 2022-12-06 A PROTECTOR FOR NANO SATELLITES
TR2022018707 2022-12-06

Publications (1)

Publication Number Publication Date
WO2024123270A1 true WO2024123270A1 (en) 2024-06-13

Family

ID=91379927

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2022/051709 WO2024123270A1 (en) 2022-12-06 2022-12-30 A protector for nano satellites

Country Status (1)

Country Link
WO (1) WO2024123270A1 (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6215458B1 (en) * 1996-03-20 2001-04-10 Centre National D'etudes Spatiales Observation or telecommunication satellites
US9567110B1 (en) * 2013-06-17 2017-02-14 Sierra Lobo, Inc. Satellite testbed for evaluating cryogenic-liquid behavior in microgravity
CN106516161A (en) * 2016-10-28 2017-03-22 深圳航天东方红海特卫星有限公司 Magic cube type modularization satellite
CN109606746A (en) * 2018-11-19 2019-04-12 北京宇航系统工程研究所 A gas cylinder thermal protection structure and gas cylinder against the influence of large plume of attitude control engine
EP4015397A1 (en) * 2020-12-17 2022-06-22 The Boeing Company Satellite thermal enclosure
CN115285383A (en) * 2022-08-17 2022-11-04 上海卫星工程研究所 Conical cylinder structure multi-star adapter thermal design device and method

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6215458B1 (en) * 1996-03-20 2001-04-10 Centre National D'etudes Spatiales Observation or telecommunication satellites
US9567110B1 (en) * 2013-06-17 2017-02-14 Sierra Lobo, Inc. Satellite testbed for evaluating cryogenic-liquid behavior in microgravity
CN106516161A (en) * 2016-10-28 2017-03-22 深圳航天东方红海特卫星有限公司 Magic cube type modularization satellite
CN109606746A (en) * 2018-11-19 2019-04-12 北京宇航系统工程研究所 A gas cylinder thermal protection structure and gas cylinder against the influence of large plume of attitude control engine
EP4015397A1 (en) * 2020-12-17 2022-06-22 The Boeing Company Satellite thermal enclosure
CN115285383A (en) * 2022-08-17 2022-11-04 上海卫星工程研究所 Conical cylinder structure multi-star adapter thermal design device and method

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