Novel electrical interface system for a satellite and a launch vehicle

Abstract

The application provides a novel satellite-rocket electrical interface system, which comprises an interface assembly arranged on the outer surface of a satellite cabin plate, the interface assembly comprising X1F connectors, X2F connectors and X10B connectors arranged side by side; a ground test cable assembly, one end of which is provided with a first connector for connecting a satellite ground test device, and the other end of which is provided with a second connector for being connected with the X1F connectors and the X2F connectors; wherein a working port is arranged on the rocket fairing at a position corresponding to the interface assembly, and the working port is configured to allow the ground test cable assembly to be connected with the satellite connectors of the interface assembly before launch or to be manually disconnected and withdrawn. Thus, the application simplifies the satellite-rocket interface relationship, improves the reliability of satellite-rocket separation, improves the launch capacity, and reduces the system development cost.

Description

Technical Field

[0001] This invention belongs to the field of aerospace satellite assembly technology, and in particular relates to a novel satellite-rocket electrical interface system. Background Technology

[0002] According to the electrical interface requirements between the satellite and the launch vehicle, after the satellite and the rocket are docked, the satellite is connected to the ground test equipment through a cable inside the fairing to realize the pre-launch testing and battery charging functions.

[0003] Currently, the electrical interface between the satellite and the launch vehicle is achieved through an umbilical cable. The umbilical cable is divided into an onboard satellite component and a ground testing component, which are connected via an EXTC connector. The ground testing component is disconnected from the onboard satellite component at the EXTC before launch and then detaches from the rocket. The onboard satellite component cable is launched with the rocket, and before the satellite separates from the rocket, the rocket issues an electrical disconnect command, causing this cable to detach and separate from the satellite along with the launch vehicle's instrument compartment.

[0004] like Figure 2 As shown, in the existing satellite-rocket electrical interface design, a section of satellite cable located inside the mounting housing is required. One end of the cable is connected to X1F(Z) and X2F(Z) of the satellite's array, and the other end is connected to the satellite ground test equipment in the launch area of ​​the launch site via EXTC. This cable is used to provide the power supply path, satellite command path, satellite telemetry signal path, and emergency power failure command path before satellite launch.

[0005] Therefore, the existing star-rocket electrical interface uses the umbilical cable launched with the rocket, which results in complex interface, increased system weight, high reliability risk of star-rocket separation, and high cost and non-reusability of onboard cables and electric disconnect plugs. Summary of the Invention

[0006] To address the problems of complex interface relationships, cumbersome development processes, high development costs, and significant waste of system resources in the original system, this invention provides a novel electrical interface system for spacecraft and rockets, characterized by simple interface relationships, high reliability, and low development costs.

[0007] To achieve the above-mentioned technical effects, the present invention provides a novel star-rocket electrical interface system, comprising:

[0008] An interface assembly is installed on the outer surface of the satellite's cabin panel. This assembly includes X1F connectors, X2F connectors, and X10B connectors arranged side-by-side. The X1F connectors are used for centralized power supply to the entire satellite, wired control and measurement of battery access, ground charging of the batteries, wired measurement of bus voltage and north / south battery bank voltage, and emergency power-off of the batteries. The X2F connectors are used for transmitting wired remote control and telemetry signals and transmitting the enable status of pyrotechnic components at the satellite-rocket separation connector. The X10B connectors are used for the satellite's emergency power-off function.

[0009] A ground test cable assembly, one end of which is provided with a first connector for connecting to satellite ground test equipment, and the other end of which is provided with a second connector for mating with the X1F connector and the X2F connector;

[0010] The rocket fairing has an operating port at the location corresponding to the interface component. The operating port is configured to allow the ground test cable assembly to be connected to the satellite connector of the interface component before launch or to be manually disconnected and withdrawn.

[0011] Furthermore, the outer surface of the satellite cabin panel is the lower western plate of the satellite.

[0012] Furthermore, the interface component is located on the +YZ side of the satellite module.

[0013] Furthermore, the operating port is located between the first and third quadrants of the fairing column section, and its size is not less than 400mm × 400mm.

[0014] Furthermore, the first connector is an EXTC(Z) connector that connects to the EXTC(T) connector of the satellite ground test equipment; the second connector includes an X1F(T) connector and an X2F(T) connector that connect to the X1F(Z) connector and the X2F(Z) connector of the satellite respectively; and the other end of the first connector is connected to the other end of the second connector.

[0015] Furthermore, it also includes an emergency power-off cable, which comprises:

[0016] The X10B(T) connector is used to connect to the X10B(Z) connector of the satellite;

[0017] The EXB interface has one end connected to the X10B(T) connector and the other end connected to the ground emergency power-off operation equipment.

[0018] The novel satellite-rocket electrical interface system provided by this invention eliminates the original internal satellite cables and centrally arranges the X1F, X2F, and X10B connectors on the satellite module, utilizing rocket fairing openings and removable ground test cables for connection. This simplifies the satellite-rocket interface, improves separation reliability, enhances payload capacity through weight reduction, and significantly reduces development costs through reusable cables. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of the novel star-rocket electrical interface system provided in an embodiment of the present invention;

[0020] Figure 2 A schematic diagram of the existing Star-Rocket electrical interface design;

[0021] Figure 3 This is a schematic diagram of the structure of the satellite module used in the novel star-rocket electrical interface system provided in an embodiment of the present invention;

[0022] Figure 4 This is a schematic diagram of the ground test cable assembly of the novel star-rocket electrical interface system provided in an embodiment of the present invention;

[0023] Figure 5 This is a schematic diagram of the emergency power-off cable of the novel star-rocket electrical interface system provided in an embodiment of the present invention;

[0024] Figure 6 A schematic diagram of the layout of the operation port of the novel star-rocket electrical interface system on the rocket fairing according to an embodiment of the present invention;

[0025] Figure 7 This is a schematic diagram showing the layout of the interface components and the operating port of the novel star-rocket electrical interface system provided in an embodiment of the present invention on the rocket fairing. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0027] It should be noted that references to "an embodiment," "embodiment," "example embodiment," etc., in this specification refer to the described embodiment including specific features, structures, or characteristics, but not every embodiment must include these specific features, structures, or characteristics. Furthermore, such expressions do not refer to the same embodiment. Moreover, when describing specific features, structures, or characteristics in conjunction with embodiments, whether or not explicitly described, it is indicated that incorporating such features, structures, or characteristics into other embodiments is within the knowledge of those skilled in the art.

[0028] Furthermore, certain terms are used in the specification and subsequent claims to refer to specific components or parts. Those skilled in the art will understand that manufacturers may use different names or terms to refer to the same component or part. This specification and subsequent claims do not distinguish components or parts by differences in name, but rather by differences in function. The terms "comprising" and "including" used throughout the specification and subsequent claims are open-ended and should be interpreted as "including but not limited to." Additionally, the term "connection" here includes any direct and indirect electrical connection means. Indirect electrical connection means include connections made through other means.

[0029] Before describing the embodiments of the present invention in detail, the technical concept of the present invention is first briefly described: To simplify the interface relationship between the satellite and the launch vehicle, the present invention proposes a novel electrical interface design for the launch vehicle and the satellite. The new interface eliminates the original internal satellite cable and replaces it with a ground test cable to achieve the original function. After the modification, without reducing the original cable's function, the cable connector model specifications, node arrangement, and layout position are optimized and adjusted, enabling the cable to be manually removed through the fairing opening before rocket launch.

[0030] This invention is applicable to the interface design between most communication satellites and launch vehicles.

[0031] The following description, in conjunction with the accompanying drawings, provides a more detailed account of a novel star-rocket electrical interface system provided in the embodiments of this application. Figure 1 As shown, the system includes an interface assembly disposed on the outer surface of the satellite module and a ground test cable assembly, wherein:

[0032] The interface components include X1F connectors, X2F connectors, and X10B connectors arranged side by side. The X1F connectors are used to realize centralized power supply for the entire satellite, wired control and measurement of battery access, ground charging of batteries, wired measurement of bus voltage and north and south battery pack voltages, and emergency power-off of batteries. The X2F connectors are used to realize the transmission of wired remote control and telemetry signals and the transmission of the pyrotechnic enable status of the satellite-rocket separation plug. The X10B connectors are used to realize the emergency power-off function of the satellite. One end of the ground test cable assembly is provided with a first connector for connecting to the satellite ground test equipment, and the other end is provided with a second connector for docking with the X1F connectors and X2F connectors. An operation port is provided on the rocket fairing at the location corresponding to the interface components. The operation port is configured to allow the ground test cable assembly to pass through it before launch to connect to the satellite connector of the interface components or to be manually disconnected and withdrawn.

[0033] While the satellite is inside the rocket fairing on the launch tower, a ground test cable assembly is used to connect the satellite ground test equipment and the satellite-rocket interface X1F and X2F respectively, providing power supply, satellite command, satellite telemetry signal, and emergency power failure command pathways before launch. The ground test cable assembly has no interface with the rocket and is manually disconnected from the satellite interface through the fairing opening before launch. It is then pulled out and retracted from the fairing and does not ascend into space with the rocket, thus possessing a reusable function.

[0034] In this embodiment, the outer surface of the satellite module is the lower west side of the satellite; the interface components are located on the +YZ side of the satellite module. Specifically, the connectors are laid out on the satellite as follows: Figure 3 As shown, a structural opening (i.e., an operation port) is provided on the +YZ side of the satellite's lower west plate 1 for the layout of satellite catalog-related plug-ins. The X10B(Z) connector 2 of the interface component is located on the left side of the satellite catalog operation port, the X2F(Z) connector 3 is located in the middle of the operation port, and the X1F(Z) connector 4 is located on the right side of the operation port.

[0035] The first connector is an EXTC(Z) connector that connects to the EXTC(T) connector of the satellite ground test equipment; the second connector includes connectors that connect to the X1F(Z) connector and the X2F(Z) connector of the satellite respectively.

[0036] X1F(T) connector, X2F(T) connector; and the other end of the first connector is connected to the other end of the second connector. For example... Figure 4As shown, the ground test cable assembly consists of three connectors and cables. Connector X1F(T) 5 connects to satellite X1F(Z) connector 4 to enable centralized power supply for the entire satellite, wired control and measurement of battery access, ground charging of the battery, wired measurement of bus voltage and north / south battery bank voltage, and emergency power-off of the battery. Connector X2F(T) 6 connects to satellite X2F(Z) connector 3 to enable the transmission of wired remote control and telemetry signals 1 and 2, and the transmission of the pyrotechnics enable status of the satellite-launcher separation plug. Connector EXTC(Z) 7 connects to the EXTC(T) connector of the ground test equipment to connect the satellite to the ground test equipment in the launch site tower area. In this embodiment, a ground test cable assembly is used. One end is connected to the satellite ground test equipment in the launch area of ​​the launch site via EXTC, and the other end is connected to X1F(Z) and X2F(Z) of the satellite table via the fairing operation port of the rocket. This assembly is used to provide power supply path, satellite command path, satellite telemetry signal path and emergency power failure command path before satellite launch.

[0037] like Figure 5 As shown, this embodiment also includes an emergency power-off cable, consisting of two connectors and a cable, including an X10B(T) connector 8 and an EXB interface 9, wherein:

[0038] The X10B(T) connector 8 connects to the X10B(Z) connector 2 of the satellite to enable emergency power-off operation when the satellite is in wireless mode on the launch tower. One end of the EXB interface 9 connects to the X10B(T) connector 8, and the other end is used to connect the satellite to the ground emergency power-off operation equipment when it is on the tower.

[0039] In this embodiment, the operating port on the rocket fairing is as follows: Figure 6 As shown, this is used for the insertion, removal, and retraction of ground test cable assemblies when the satellite is inside the fairing; specifically, based on the satellite's position within the rocket fairing, the positions of the satellite-rocket interface connectors X1F(Z), X2F(Z), and X10B(Z) inside the fairing are determined, and the rocket fairing opening 10 is determined. The opening is located between quadrants I and IV of the fairing column, slightly off-center from quadrant I, and the opening size is not less than 400mm × 400mm.

[0040] Taking the CZ-3B / G2 rocket and a certain DFH-4E platform satellite as an example, the final satellite-rocket position relationship is as follows: Figure 7 As shown in the figure, the distance between the rocket fairing operation port and the satellite X1F(Z) and X2F(Z) connectors is approximately 0.6m. Operators can use the operation port to connect and disconnect the satellite surface connectors X1F(T) and X2F(T) and to retract the ground test cable assembly before rocket launch.

[0041] In summary, the novel satellite-rocket electrical interface system provided by this invention eliminates the original internal satellite cables, centrally arranging the X1F, X2F, and X10B connectors on the satellite module and connecting them using rocket fairing openings and removable ground test cables. This simplifies the satellite-rocket interface, improves separation reliability, increases payload capacity through weight reduction, and significantly reduces development costs through reusable cables.

[0042] Compared with the prior art, the present invention has the following beneficial effects:

[0043] (1) Simplified interface relationships. This invention can effectively simplify the interface relationships between satellites and launch vehicles, reducing cross-departmental coordination issues during the development process.

[0044] (2) Improve the reliability of satellite-rocket separation. This invention uses a ground cable to connect directly to the satellite's surface connector, and the cable is manually disconnected, pulled out, and retrieved before launch. There is no electrical interface between the satellite and the rocket, which reduces the uncertainty during the satellite-rocket separation process.

[0045] (3) Reduce the weight of the rocket system. The present invention replaces the original internal rocket cable with a test cable. This cable is manually pulled out and retracted before launch and does not go into space with the rocket. The weight saved can be directly used to improve the rocket's carrying capacity.

[0046] (4) Optimize the development process. This invention can effectively reduce the various levels of handover, testing, and experimentation between the star-rocket interface cables, reduce project workload, and shorten the development cycle.

[0047] (5) Reduce satellite development costs. The present invention adopts a manual disconnection method before launch, so the cable connector does not need to have the electric disconnection and forced disconnection functions of the original connection, and the ground test cable can be reused, which significantly reduces development costs.

[0048] (6) The changes to the design of the satellite-rocket interface in this invention only affect the satellite by altering the model, layout, hatch opening, and corresponding internal cable routing of the satellite-rocket interface connectors. It does not affect the layout of the satellite's internal equipment and has a certain degree of versatility.

[0049] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element. Furthermore, it should be noted that the scope of the methods and apparatuses in the embodiments of the present invention is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. Additionally, features described with reference to certain examples may be combined in other examples.

[0050] Of course, the present invention may have other various embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art can make various corresponding changes and modifications according to the present invention, but these corresponding changes and modifications should all fall within the protection scope of the appended claims.

Claims

1. A novel star-rocket electrical interface system, characterized in that, include: An interface assembly is installed on the outer surface of the satellite module. The interface assembly includes X1F connectors, X2F connectors and X10B connectors arranged side by side. The X1F connector is used to realize centralized power supply for the whole satellite, wired control and measurement of battery access, ground charging of batteries, wired measurement of bus voltage and north and south battery pack voltage, and emergency power outage of batteries. The X2F connector is used to transmit wired remote control and telemetry signals as well as the enable status of pyrotechnic components on the satellite-rocket separation plug; the X10B connector is used to implement the satellite's emergency power-off function. A ground test cable assembly, one end of which is provided with a first connector for connecting to satellite ground test equipment, and the other end of which is provided with a second connector for mating with the X1F connector and the X2F connector; The rocket fairing has an operating port at the location corresponding to the interface component. The operating port is configured to allow the ground test cable assembly to be connected to the satellite connector of the interface component before launch or to be manually disconnected and withdrawn.

2. The novel star-rocket electrical interface system according to claim 1, characterized in that, The outer surface of the satellite module is the lower western plate of the satellite.

3. The novel star-rocket electrical interface system according to claim 2, characterized in that, The interface component is located on the +YZ side of the satellite module.

4. The novel star-rocket electrical interface system according to claim 1, characterized in that, The operating port is located between the first and third quadrants of the fairing column section, and its size is not less than 400mm × 400mm.

5. The novel star-rocket electrical interface system according to claim 1, characterized in that, The first connector is an EXTC(Z) connector that connects to the EXTC(T) connector of the satellite ground test equipment; the second connector includes an X1F(T) connector and an X2F(T) connector that connect to the X1F(Z) connector and the X2F(Z) connector of the satellite respectively; and the other end of the first connector is connected to the other end of the second connector.

6. The novel star-rocket electrical interface system according to claim 1, characterized in that, It also includes an emergency power-off cable, which comprises: The X10B(T) connector is used to connect to the X10B(Z) connector of the satellite; The EXB interface has one end connected to the X10B(T) connector and the other end connected to the ground emergency power-off operation equipment.

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