MODULAR AND PASSIVE FIBER OPTIC LIGHT TRANSMISSION SYSTEM FOR SPACECRAFT

Abstract

The invention is a modular system that enables the passive collection of natural light in spacecraft and its transmission to the Spacecraft's Internal Structure (1) via Fiber Optic Cables (4) and Structural Embedded Channels or Guides (5). The system consists of a Light Entry Aperture (2), Optical Collector Elements (3), Fiber Optic Cable (4), Optical Connector (6) and Sensor Unit (7). This structure, which does not create electromagnetic interference, is resistant to space conditions and offers flexibility and structural integration in sensor placement.

Description

1 TARIFF MODULAR AND PASSIVE FIBER OPTIC LIGHTING FOR SPACECRAFT TRANSMISSION SYSTEM The technical field to which the invention relates The invention is a system designed for use in spacecraft that utilizes natural light from the external environment. It relates to a fiber optic light transmission system that enables light to be transmitted to the interior structure of a spacecraft. State of the art 10 The sun has many applications, particularly in spacecraft attitude control systems. These sensors are used. Solar sensors determine the direction of the sun based on the sensor's position. These are optoelectronic systems used for the purpose of determination. These sensors are located outside the satellite structure. They are integrated. Solar position sensors, depending on the data transmission method, are either digital or analog, 15 Based on their accuracy levels, they are classified as Coarse and Fine sensors. They are classified. The transmission of light rays to the sensor is also associated with these classifications. Analog solar sensors typically consist of four identical sensors placed under slit or hole openings. It is structured with arrays of light-sensitive sensors in a segmented square arrangement. The Sun's off-axis A direction is determined by the difference in signals obtained from silicon cells relative to each other, depending on their position. 20 Determination is made. These systems operate with a relatively small number of electronic components and have low error rates. It offers a simple solution with its ratios. In analog sensors, the output depends on the angle of the sun's rays. In contrast, in crude oils, the output signal in digital sensors is a continuous function, with discrete and binary values. Although the sensors operate with lower accuracy, they have the advantages of simple structure and low cost. is preferred. However, thinner sensors offer higher accuracy, but are still 25 It requires complex electronic components and processing units. Perforated digital solar sensors, on the other hand, detect light entering through a small hole. It works by the object falling onto a positioned image sensor. This structure is suitable for both horizontal and horizontal orientations. It allows for angular measurement along the vertical axis and offers a wide field of view (FOV). Additionally, Due to its simple optical geometry and stationary part structure, it is suitable for 30 space missions. It provides high reliability. However, due to the small diameter of the hole, the light intensity is low. It is falling, which can lead to a loss of performance in low light conditions. Digital solar Two common types of sensors are slotted and pin-hole systems. Slotted digital solar sensors... sensors, a mask with a narrow opening, and a CMOS image sensor located behind this mask. It consists of a sensor. When sunlight passes through the slit and falls on the sensor surface, a light trail is created. 35 This trace is converted into a multi-channel digital output based on threshold values, and these outputs are analyzed. By doing this, the angular position of the Sun is calculated. Such systems are generally uniaxial measurement systems. Used in applications requiring (horizontal or vertical) viewing only. Finally, all of these traditional systems involve mounting the sensors directly onto the exterior surface. 40 While requiring; fiber optic transmission systems allow sensors to be delivered more flexibly, securely, and safely within the spacecraft. This allows for placement in critical areas. Thus, both design and assembly are easier. Great convenience and freedom of settlement are provided during this phase. 2 Technical problems that the invention aims to solve. Solar sensors and similar light-based sensing systems used in spacecraft For them to function effectively, they are usually placed in a location that faces directly to the outside environment. This is necessary. This situation requires the sensors to withstand external environmental conditions (vacuum, temperature changes, 5 exposure to radiation, micrometeorite impacts, etc., and structural integration This leads to increased complexity and risks of electromagnetic interference. Furthermore, the sensors... Direct mounting to the outer surface of the spacecraft; additional mechanical tasks such as drilling, fastening, and alignment. This can make the processes mandatory and reduce the overall reliability of the system. However, in current systems, light needs to be directed directly to the sensor, 10 The placement of the sensors is a limitation in terms of spacecraft design and assembly flexibility. This reduces the risk of damage. Since it is not possible to isolate the sensors from the external environment, both environmental factors and other factors are addressed. Protecting them from the effects becomes difficult, and operations such as maintenance and repair become almost impossible. This is becoming the case. Moreover, current solutions are mostly limited to a small number of sensor locations and fixed positions. Because it has orientations, it can be configured and extended according to task requirements. 15 It falls short in this respect. Explanation of the Figures Figure 1: View of the Spacecraft Structure and Fiber Optic Light Transmission System Figure 2: View of Spacecraft Structure and Fiber Optic Light Transmission System Figure 3: Detailed Top View of the Sensor Unit 20 Figure 4: Top view of the spacecraft structure and fiber optic light transmission system. Figure 5: Front view of the sensor unit and fiber optic light transmission system. Figure 6: Sensor Unit and Detailed Front View Figure 7: Front view of the spacecraft structure and fiber optic light transmission system. Figure 8: Front View of Sensor Unit 25 Figure 9: Left View of the Sensor Unit Figure 10: Top View of the Sensor Unit Figure 11: Right View of the Sensor Unit Explanation of References in Figures 30 1: Spacecraft Structure 2: Optical Light Inlet Aperture 3: Optical Gathering Elements (Lens / Mirror) 4: Fiber Optic Cable 5: Structural Embedded Channels or Guides 35 6: Optical Connectors 7: Sensor Unit 40 45 3 Description of the Invention The invention is designed specifically for use in spacecraft, utilizing external environmental radiation. enabling natural light to be transmitted to the interior structure of the spacecraft (1) via fiber optic cables (4). It relates to a fiber optic light transmission system. This system uses solar sensors or light rays to transmit light. This eliminates the need for other sensors used to be mounted on the outer surface of the spacecraft. and allows sensors to be removed and positioned more securely inside. It provides. The system developed within the scope of the invention consists of three main components: • An optical light entry aperture (2) mounted on the outer surface of the spacecraft, 10 • At least one fiber optic cable (4) is optically connected to this unit. • At least one sensor unit (7) where the fiber optic cable (4) terminates in the internal structure. The system receives light through an optical light entry aperture (2) located on the outer surface of the spacecraft. It collects natural light (such as sunlight). The light passes through at least one optically aligned fiber optic cable. (4) are carried to the interior of the spacecraft (1). These cables (4) are carried to the structural interior or 15 of the spacecraft. Fiber optic cables are laid with a minimum bending radius, oriented towards the outer sections. In order for cables (4) to work safely in space missions, vacuum environment, radiation, It is essential to insulate it with coating materials that can withstand external conditions such as high temperatures. Fiber The sensor unit (7), located at the point where the optical cable (4) terminates in the indoor environment, transmits the optical signals It performs orientation determination or other optical measurement operations by sensing. This unit contains 20 Optional optical collecting devices, such as lenses or mirrors. (3) elements can be used. These optical collecting elements (3) can collect light at higher intensity and By ensuring that the system is transferred to the fiber optic cable (4) in a directed manner, the efficiency of the system is improved. It increases. One of the most important advantages of the system described in the invention is that it operates entirely passively. 25 In other words, it uses only light from the outside environment, without needing any electrical power source. It is transmitted. In addition, the system is modular and will include multiple fiber optic cables (4). It can be configured. Thus, from different surfaces of the spacecraft (1) in different orientations and It is possible to collect light in the spectra. Each fiber cable (4) has its own optical light input. The aperture (2) and sensor unit (7) can operate independently. This situation is specific to the space mission 30 It facilitates the customization of the system according to requirements. Fiber optic transmission system can be integrated with the structural components of the spacecraft (1) It is designed in such a way that the system uses channels embedded within the structural material or It can be routed within the guides (5). Thus, the fiber cable (4) is better protected from external environmental conditions. It is protected and the need for exposed cabling is eliminated. 35 In terms of modularity, the system has optical connectors (6) at its ends and fiber optic cable (4) sections or sensor units (7) can be changed or upgraded as needed. This structure, the sustainability of the system in terms of maintenance, repair or post-commissioning restructuring It increases. One of the most important features is that, unlike traditional systems, the sensors are not directly connected. These sensors (7) can be placed on the outer surface of the spacecraft structure (1) without needing to be placed on the outer surface of the spacecraft 40 It is possible to position the sensor in any desired area within the structure (1). The units (7) are made more protected against environmental damage and the assembly 4 No mechanical processing (drilling, alignment, etc.) is required on the outer surface during the operations. It does not remain. In conclusion, this innovative system is particularly useful in space missions, especially in attitude determination. It can be used in all sensor applications based on light transmission, both structural and operational. It offers significant advantages in this respect. 5 How the invention can be applied to industry. The invention has potential, particularly in the aerospace industry, for attitude determination systems. It has been developed for use in light-based sensing and measurement systems. Sun 10 sensors or other light-sensing components mounted directly on the outer surface of the spacecraft Instead of being dismantled, this makes it possible to integrate it into the internal structure via fiber optic cables. The system facilitates production, integration, and testing processes for spacecraft. It starts with an optical light entry aperture on the outer surface and continues inside via fiber optic cables. The light entering the building is detected by sensors that can be placed at appropriate points within the interior space. This structure is perceived, especially in miniature satellites (CubeSat, microsat, nanosat, etc.), orbit. low-volume, modular, and electromagnetically compatible systems on platforms and stations It meets the need. The invention can be configured for mass production and adapted to different task profiles. It is scalable. Thanks to its passive operation, it does not generate energy consumption. 20 Its high reliability is due to its lack of electromagnetic interference and its long lifespan. It is suitable for use in space missions requiring such capabilities. In addition, maintenance and It offers ease of updating. The production and assembly of fiber optic components, existing industry This can be achieved with technologies, and the system is used in both commercial and public space projects. It is applicable in projects. In this respect, the invention is suitable for activities in the field of space technologies. demonstrating an innovative approach directly applicable to industry for companies and research institutions. It offers a solution.

Claims

REQUESTS 1) The invention utilizes a solar sensor or other method of detecting light rays from the spacecraft's external environment. a fiber optic light transmission system configured to provide optical light transmission to the sensors It is a system, and its feature is; - The spacecraft includes an optical light input unit mounted on its outer surface, 5 - Light enters through at least one fiber optic cable that is optically connected to this unit. moving to the building, - At least one sensor unit where the fiber optic cable terminates in the spacecraft's interior. It includes. 2) According to claim 1, it is a fiber optic light transmission system, characterized by its ability to convert sunlight into 10 watts at the light input unit. The collecting mechanism includes an optically aligned lens or mirror collecting assembly. 3) According to Claim 1, it is a fiber optic light transmission system, characterized by its passive operation. and it operates in an optical medium that does not generate electromagnetic interference. 4) According to Claim 1, it is a fiber optic light transmission system, characterized by the fiber optic cable passing through the satellite. 15 oriented along the structural surfaces and maintaining a minimum bending radius It is the way in which it is placed. 5) According to Claim 1, it is a fiber optic light transmission system, characterized by the fact that the light output unit is located indoors. It contains a diffusing lens, optical prism, or diffuser that will spread the light. 6) According to Claim 1, it is a fiber optic light transmission system, characterized by the fact that the fiber optic cable transmits radio waves. insulated with a coating material resistant to frequencies, high temperatures and vacuum environments 20 It is the fact that it has been done. 7) According to Claim 1, it is a fiber optic light transmission system, characterized by having multiple fiber optic cables. It can include cables and each one can emit light from different regions in different spectrum ranges. It is structured to carry the load. 8) According to Claim 1, it is a fiber optic light transmission system, characterized by its ability to integrate seamlessly into the spacecraft structure. Structural material designed for embedded integration and protection from external influences. This means it is contained within channels or guides. 9) According to Claim 1, it is a fiber optic light transmission system, characterized by its fibers carrying the optical signal. Thanks to the optical connectors located at its ends, the system has a modular and interchangeable structure. That is. 30 10) Fiber optic light transmission system according to claim 1, its feature is; sun sensor or light This allows other sensors that use its rays to be positioned inside the satellite. 35

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