WO2017134689A2

WO2017134689A2 - Adaptable satellite bus

Info

Publication number: WO2017134689A2
Application number: PCT/IN2017/050053
Authority: WO
Inventors: Priyank PUNTAMBEKAR
Original assignee: Axiom Research Labs Private Limited
Priority date: 2016-02-06
Filing date: 2017-02-06
Publication date: 2017-08-10
Also published as: WO2017134689A3

Abstract

An adaptable satellite bus (100, 300) is provided. The adaptable satellite bus (100, 300) includes a plurality of coupling brackets. The adaptable satellite bus (100, 300) further includes a plurality of structural panels (106-116) configured to be coupled to each other via the plurality of coupling brackets (104), wherein at least one structural panel of the plurality of structural panels (106-116) includes mounting provisions (118) for supporting one or more different types of payloads, and one or more structural panels include mounting provisions for one or more supporting sub-systems, and wherein configuration of the mounting provisions (118) for supporting one or more different types of payloads and configuration of the mounting provisions (126) for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus (100). A method (400) for making the adaptable satellite bus (100) also provided.

Description

TITLE

"ADAPTABLE SATELLITE BUS"

ADAPTABLE SATELLITE BUS

EARLIEST PRIORITY

This Complete specification claims priority from a provisional application filed in India having Patent Application No. 201641004296.

BACKGROUND

[0001] Embodiments of the present invention relate to a spacecraft, and more particularly, to a satellite bus.

[0002] Nowadays, different types of spacecraft are available in the market which are used for various purposes. One such spacecraft includes a satellite bus, which is used for applications such as imaging, telecommunication, and sensing. The satellite buses include one or more payloads, which are used to perform the imaging, telecommunication, and the sensing. For example, a star sensor with gyros and actuators may be used for precision pointing capabilities and a high data rate transmitter such as an X-band transmitter for transmitting high data rate payload data.

[0003] Conventionally, different satellite buses are designed for accommodating different payloads. Therefore, satellite manufacturers have a corresponding satellite bus design for each payload configuration. Moreover, in some situations, the satellite manufacturer may need to design a new satellite bus based on the customer's requirement. Such an approach leads to high lead and delivery times as the satellite manufacturer is required to manufacture an all new satellite bus based on the customer's requirement.

[0004] In another approach, the satellite manufacturers design one satellite bus including different types of payloads and based on customer's requirement, the satellite manufacturer configures one or more payloads in the satellite bus to serve the applications requested by the client. However, such an approach leads to higher costs of manufacturing and launch as the satellite bus becomes costlier and heavier to launch. Hence, there is a need for an improved satellite bus which can address the aforementioned issues. BRIEF DESCRIPTION

[0005] In accordance with some embodiments of the present specification, an adaptable satellite bus is provided. The adaptable satellite bus includes a plurality of coupling brackets. The adaptable satellite bus further includes a plurality of structural panels configured to be coupled to each other via the plurality of coupling brackets, wherein at least one structural panel of the plurality of structural panels includes mounting provisions for supporting one or more different types of payloads, and one or more structural panels include mounting provisions for one or more supporting sub-systems, and wherein configuration of the mounting provisions for supporting one or more different types of payloads and configuration of the mounting provisions for one or more supporting subsystems are independent of an intended use of the adaptable satellite bus.

[0006] In accordance with some embodiments of the present specification, a method for making an adaptable satellite bus is provided. The method includes providing a plurality of coupling brackets. The method further includes coupling a plurality of structural panels to each other via the plurality of coupling brackets, wherein at least one structural panel of the plurality of structural panels includes mounting provisions for supporting one or more different types of payloads, and one or more structural panels include mounting provisions for one or more supporting sub-systems, and wherein configuration of the mounting provisions for supporting one or more different types of payloads and configuration of the mounting provisions for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus.

BRIEF DESCRIPTION OF DRAWINGS

[0007] These and other features, aspects, and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:

[0008] FIG. 1 is a diagrammatical representation showing an expanded view of an adaptable satellite bus, in accordance with one embodiment of the present specification; [0009] FIG. 2 is a diagrammatical representation showing a perspective view of the adaptable satellite bus of FIG. 1, in accordance with one embodiment of the present specification;

[0010] FIG. 3 is a diagrammatical representation showing perspective view of another adaptable satellite bus, in accordance with one embodiment of the present specification; and

[0011] FIG. 4 is a flow-diagram showing a method for making an adaptable satellite, in accordance with one embodiment of the present specification.

DETAILED DESCRIPTION

[0012] Before the present invention is described in further detail, it is to be understood that the invention is not limited to the particular embodiments described, as such may, of course, vary. It is also to be understood that the terminology used herein is for the purpose of describing particular embodiments only, and is not intended to be limiting, since the scope of the present invention will be limited only by the appended claims.

[0013] References to "one embodiment", "an embodiment", "at least one embodiment", "one example", "an example", "for example" and so on, indicate that the embodiment(s) or example(s) so described may include a particular feature, structure, characteristic, property, element, or limitation, but that not every embodiment or example necessarily includes that particular feature, structure, characteristic, property, element or limitation. Furthermore, repeated use of the phrase "in one embodiment" does not necessarily refer to the same embodiment, though it may.

[0014] In accordance with some embodiments, an adaptable satellite bus is provided. The adaptable satellite bus includes a plurality of coupling brackets. The adaptable satellite bus further includes a plurality of structural panels configured to be coupled to each other via the plurality of coupling brackets, wherein at least one structural panel of the plurality of structural panels includes mounting provisions for supporting one or more different types of payloads, and one or more structural panels include mounting provisions for one or more supporting sub-systems, and wherein configuration of the mounting provisions for supporting one or more different types of payloads and configuration of the mounting provisions for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus. The adaptable satellite bus, in accordance with some embodiments, has a universal design which can be used to couple different payloads in the satellite bus without changing the bus structure and design. The proposed satellite bus configuration enhances the level of adaptability of the bus to the mission requirements such that all the required features and only the required features are a part of the flight configuration leading to a solution which is cost optimal and quickly deliverable.

[0015] FIG. 1 is a diagrammatical representation showing an expanded view of an adaptable satellite bus (100), in accordance with one embodiment of the present specification. In some embodiments, the adaptable satellite bus (100) may include a plurality of coupling brackets such as the coupling brackets (104) and a plurality of structural panels such as the structural panels (106, 108, 110, 112, 114, and 116) (hereinafter collectively referred to as structural panels (106-116)). In some embodiments, the plurality of coupling brackets 104 is L-shaped.

[0016] The structural panels (106-116) are configured to be coupled to each other via the plurality of coupling brackets (104). In some embodiments, the plurality of structural panels (106-116) may be coupled to the coupling brackets (104) via one or more fasteners, adhesives, or a combination thereof. In some embodiments, the structural panels (106- 116) may be coupled to the coupling brackets (104) such that a resultant satellite bus body having a cubical shape is formed (see FIGs. 2 and 3). As depicted in FIGs. 1-3, the structural panels (106-112) are disposed on sides of the cubical shape and also referred to as side structural panels (106-112). The structural panel 114 is disposed on bottom side of the cubical shape and also referred to as a bottom structural panel 114. The structural panel 116 is disposed on a top side of the cubical shape and also referred to as a top structural panel 116.

[0017] In the embodiment of FIG. 1, sixteen (16) coupling brackets (104) and six (6) structural panels (106-116) are shown. Greater or fewer number of the coupling brackets and the structural panels may be employed without limiting the scope of the present specification. Moreover, although in the embodiment of FIG. 1, one or more the structural panels (106-116) having rectangular shapes are used, a satellite bus configuration with structural panels of different shapes is also envisioned.

[0018] In some embodiments, at least one structural panel, such as the top structural panel (116) of the plurality of structural panels (106-116) includes mounting provisions (118) for supporting one or more different types of payloads. In some embodiments, the structural panel (116) that includes the mounting provisions (118) for supporting payloads may also be referred to as a payload deck. The mounting provisions (118) for supporting one or more different types of payloads may include but are not limited to one or more of holes, clamps, fastening means, or combinations thereof. Non-limiting examples of the different types of payloads include an imaging payload (120), a global positioning system (GPS) antenna (122), a star sensor (124), or combinations thereof. The mounting provisions (118) may be designed such that any type of payloads can be mounted on the structural panel (116). More particularly, a configuration of the mounting provisions (118) for supporting the different types of payloads is independent of an intended use of the adaptable satellite bus (100).

[0019] Furthermore, in some embodiments, one or more structural panels (106-116) may include mounting provisions (126) for one or more supporting sub- systems. The mounting provisions (126) for supporting sub-systems may include but are not limited to one or more of holes, clamps, fastening means, or combinations thereof. Non-limiting examples of the supporting sub-systems include a thermal control sub-system (TCS), an electrical power sub-system (EPS), an altitude and orbit determination and control subsystem (AOCS), a communication sub-system, a command and data handling sub-system (C&DH) disposed in an avionics box (127), flight software (FS), a propulsion sub-system, and an integrated tank assembly, or combinations thereof. The mounting provisions (126) may be designed such that any type of supporting sub-systems can be mounted on the structural panels (106-116). More particularly, a configuration of the mounting provisions (126) for supporting the different supporting sub-systems is independent of an intended use of the adaptable satellite bus (100). [0020] In some embodiments, EPS may include power generation apparatus such as solar panels (128), an energy storage device such as a battery (130), and a power conditioning and distribution unit (PCDU) (132). The solar panels (128) may be body mounted, deployed in-orbit without sun-tracking or deployed in-orbit with sun-tracking. An actual size and configuration of the solar panels (128) may be a function of a mission power requirements and orbit geometry. The battery ( 130) is configured to store the power and supply the power to the supporting sub-systems and/or the payloads when the solar power is not sufficient to meet their power requirements. The battery (130) may have a baseline configuration irrespective of the configuration of the other systems such as the supporting sub-systems and the payloads. The PCDU (132) may be configured to distribute power among the supporting sub-systems and/or the payloads. The PCDU (132) may be a modular unit designed such that it would have interface cards with each sub-system baseline design and a provision to add cards for the add-on packages of each system. In some embodiments, components of the EPS may be located on a single structural panel. In some embodiments, the components of the EPS may be distributed over one or more of the plurality of structural panels (106-116).

[0021] The communication sub-system may be configured to provide a communication link between the satellite bus (100) and the ground station (not shown) for downlink of telemetry and housekeeping data along uplink of tele -commands and to facilitate the downlink of payload data. The communication system may include a low data rate transceiver (or S-band transceiver) (134) for facilitating a low data rate communication link with the ground station via an S-band monopole (136). In some embodiments, low data rate transceiver (134) may be configured to facilitate a single communication link with the ground station which would be used for tele-command uplink, housekeeping and payload data. In some embodiments, the communication system may include a high data rate transmitter (or X-band transmitter) (138) for facilitating an independent transmit link via an X-band antenna (140). In some embodiments, the X-band transmitter (138) may be utilized dedicatedly for payload data downlink in addition to the communication link facilitated by the S-band transceiver (134). In some embodiments, components of the communication sub-system may be located on a single structural panel. In some embodiments, the components of the communication sub-system may be distributed over one or more of the plurality of structural panels (106-116).

[0022] The C&DH sub-system (not shown) may be disposed in the avionics box (127) may include an on-board computer. The C&DH sub-system interfaces with all the payloads and/or supporting sub-systems of the satellite bus (100) and configured to run AOCS algorithms and manages the payload data storage, command and telemetry and basic fault detection isolation and recovery. Various configurations in C&DH are defined based on the data interface, processing, storage and mission life time requirements. The basic configuration of the C&DH sub-system meets the requirements of the low data rate payload operating for short mission life. The intermediate configuration of the C&DH sub-system is capable of supporting higher data rate payloads and longer mission life. The data storage is an order of magnitude higher than the basic configuration. The highest configuration of the C&DH sub-system is capable of supporting very high data rate payloads and storing data an order of magnitude higher than the intermediate level. All the configurations are capable of meeting the interface and processing requirements of all other supporting subsystems.

[0023] The AOCS sub-system is configured to manage the altitude and orbit of the satellite bus (100) to ensure that the satellite bus (100) is pointing in the desired direction such that either the payload is pointing at the object of interest, or the communication antenna are pointing towards the ground station or the solar panels are generating power or any other operational pointing requirement. Orbit control may be desirable at lower operating altitude to compensate for the decay in the orbit due to atmospheric drag. The AOCS sub-system has two configurations based on the pointing accuracy of the system, a coarse altitude pointing (CAP) and a precision altitude pointing (PAP). The CAP is based on the most basic set of hardware such as magnetometers (142), GPS (not shown), sun sensors (not shown) and magnetorquers (144). These sensors may provide a coarse attitude knowledge and the actuators combine to give full 3-axis pointing capability. The PAP may include precision attitude determination sensors like a star sensor (124) and gyros (not shown) and actuators like the reaction wheels (146) which augment the performance of the hardware in CAP to provide 3-axis precision pointing capability. The altitude pointing modes are configurable through flight software implementation as per the specific mission requirement. In some embodiments, components of the AOCS sub-system may be located on a single structural panel. In some embodiments, the components of the AOCS subsystem may be distributed over one or more of the plurality of structural panels (106-116).

[0024] In some embodiments, the satellite bus (100) may optionally include the propulsion sub-system (not shown). The propulsion sub-system is designed to provide orbit maintenance capability at very low orbit altitude and de-orbit capability at high operating orbit altitudes.

[0025] The integrated tank assembly (148) may include one or more of a propellant tank (150), reaction wheels (146), a thruster (not shown), and an integrated mount (152) for the propellant tank (150), the reaction wheels (146), the thruster. The integrated tank assembly (148) may be mounted to the bottom deck (for example, the bottom structural panel (114)), which also acts as the interface with a launch vehicle (not shown). Components of the integrated tank assembly (148) may be optional. For example, the reaction wheels (146) are only used if there is a need for precision pointing (see FIG. 2). The propellant tank (150) and the thruster are mounted only if there is a need for the propulsion sub-system. The integrated mount (152) may be used even if the is a need for only one of the two systems.

[0026] FIG. 2 is a diagrammatical representation showing a perspective view (200) of the adaptable satellite bus (100) of FIG. 1, in accordance with one embodiment of the present specification. More particularly, the perspective view (200) of FIG. 2 includes all elements of FIG. 1 except the front structural panel (108) for facilitating enhanced view of internal components. FIG. 3 is a diagrammatical representation showing a perspective view 300 of another adaptable satellite bus (302), in accordance with one embodiment of the present specification. More particularly, the perspective view (300) of FIG. 3 shows another satellite bus (302) which does not include a payload such as a star sensor, and a reaction wheel as the star sensor is not required. In fact, FIGs. 2 and 3 represent different embodiments of a satellite bus having different payloads and different supporting subsystems, in accordance with the aspects of the present specification. [0027] FIG. 4 is a flow-diagram (400) showing a method for making an adaptable satellite, in accordance with one embodiment of the present specification. For ease of illustration, FIG. 4 is described in conjunction with the adaptable satellite (100) of FIG. 1. In some embodiments, the method of making the adaptable satellite (100) includes steps (402) and (404). At step (402), a plurality of coupling brackets (104) are provided. In some embodiments the plurality of coupling brackets (104) of L- shape are provided. Further, in some embodiments, at step (404), a plurality of structural panels such as the structural panels (106-116) may be coupled to each other via the plurality of coupling brackets. More particularly, at least one structural panel (e.g., the structural panel (116) of the plurality of structural panels (106-116) includes mounting provisions (118) for supporting one or more different types of payloads, and one or more structural panels (e.g., the structural panels (106-114)) may include mounting provisions (126) for one or more supporting subsystems, and wherein configuration of the mounting provisions (118) for supporting one or more different types of payloads and configuration of the mounting provisions (126) for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus (100).

[0028] The adaptable satellite bus, in accordance with some embodiments, has a universal design which can be used to couple different payloads in the satellite bus without changing structure and design and design of the satellite bus. In a non-limiting example, as shown in FIGs. 1-3, the top structural panel (116) may be used primarily as the payload deck and the mounting provisions are provided such that any type of payloads can be mounted on the payload deck. The proposed satellite bus configuration enhances the level of adaptability of the bus to the mission requirements such that all the required features and only the required features are a part of the flight configuration leading to a solution which is cost optimal and quickly deliverable.

[0029] The embodiments described herein are examples of structures, systems and methods having elements corresponding to the elements of the invention recited in the claims. This written description enables one of ordinary skill in the art to make and use embodiments having alternative elements that likewise correspond to the elements of the invention recited in the claims. The scope thus includes structures, systems and methods that do not differ from the literal language of the claims, and further includes other structures, systems and methods with insubstantial differences from the literal language of the claims. While only certain features and embodiments have been illustrated and described herein, many modifications and changes may occur to one of ordinary skill in the relevant art. The appended claims are intended to cover all such modifications and changes.

Claims

1. An adaptable satellite bus (100, 300), comprising:

a plurality of coupling brackets (104), and

a plurality of structural panels (106, 116) configured to be coupled to each other via the plurality of coupling brackets (104), wherein at least one structural panel of the plurality of structural panels (106-116) comprises mounting provisions (118) for supporting one or more different types of payloads, and one or more structural panels comprise mounting provisions (126) for one or more supporting sub-systems, and wherein configuration of the mounting provisions (118) for supporting one or more different types of payloads and configuration of the mounting provisions (126) for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus (100, 300).

2. The adaptable satellite bus (100, 300) of claim 1, wherein the plurality of coupling brackets (104) is L- shaped.

3. The adaptable satellite bus (100, 300) of claim 1, wherein the mounting provisions (118) for supporting the one or more different types of payloads and the mounting provisions (126) for the one or more supporting sub-systems comprise one or more of holes, clamps, fastening means, or combinations thereof.

4. The adaptable satellite bus (100, 300) of claim 1, wherein the plurality of structural panels (106-116) that are coupled via the plurality of coupling brackets (104) forms a cubical shape, wherein the plurality of structural panels (106-116) are disposed as side structural panels (106-112), a top structural panel (116), and a bottom structural panel (114) of the cubical shape.

5. The adaptable satellite bus (100, 300) of claim 1, wherein the mounting provisions (118) for the one or more different types of payloads are provided on the top structural panel (116).

6. The adaptable satellite bus (100, 300) of claim 1, wherein the one or more supporting sub-systems comprise a thermal control sub-system (TCS), an electrical power sub-system (EPS), an altitude and orbit determination and control sub-system (AOCS), a communication sub-system, a command and data handling sub-system (C&DH), flight software (FS), a propulsion sub-system, and an integrated tank assembly, or combinations thereof.

7. The adaptable satellite bus (100, 300) of claim 7, wherein the integrated tank assembly (148) comprises a plurality of reaction wheels for precision pointing.

8. The adaptable satellite bus (100, 300) of claim 7, wherein the integrated tank assembly (148) comprises a propellant tank (150), a thruster, or a combination thereof.

9. The adaptable satellite bus (100, 300) of claim 1, wherein the one or more different types of payloads comprise an imaging payload (120), a global positioning system (GPS) antenna (122), a star sensor (124), or combinations thereof.

10. A method (400) for making an adaptable satellite bus (100, 300), the method (400) comprising:

providing a plurality of coupling brackets (104); and

coupling a plurality of structural panels (106-116) to each other via the plurality of coupling brackets (104), wherein at least one structural panel of the plurality of structural panels (106-116) comprises mounting provisions (118) for supporting one or more different types of payloads, and one or more structural panels comprise mounting provisions (126) for one or more supporting sub-systems, and wherein configuration of the mounting provisions (118) for supporting one or more different types of payloads and configuration of the mounting provisions (126) for one or more supporting sub-systems are independent of an intended use of the adaptable satellite bus (100, 300).