CN101381003A - A New Type of Spacecraft Main Bearing Structure - Google Patents

Abstract

The invention discloses a novel spacecraft main load-bearing structure, which comprises a propulsion cabin structure, a star-shaped truss structure (6) and an electronic cabin main frame structure; the upper part of the propulsion cabin structure is connected with the electronic cabin main frame structure, and the lower part serves as The star precision detection reference plane and the installation surface for providing propulsion cabin instruments and equipment; the star truss structure (6) is a load installation frame supported by struts, located in the main frame structure of the electronic cabin, and used for installing payloads. The lower ends of the struts are fixedly connected to the upper part of the propulsion cabin structure. Since the present invention adopts the outer frame side plate structure and the inner star-shaped truss structure to form a hybrid main structure with internal and external double load-bearing paths to transmit the load of the whole satellite, the force transmission path is short and continuous, the structure is compact, and the center of mass is low, which meets the requirements of the entire satellite. High stiffness and small inertia requirements.

Description

A New Type of Spacecraft Main Bearing Structure

technical field

The invention relates to a main load-bearing structure of a spacecraft, in particular to a novel small-satellite main load-bearing structure for improving the adaptability of a small satellite platform.

Background technique

The main load-bearing structure of the spacecraft is mainly used to bear the static and dynamic loads acting on the spacecraft, provide a fixed installation interface for the instruments and equipment on board, maintain stable accuracy, and ensure the overall geometry.

Taking satellites as an example, the main functions of the satellite’s main force-bearing structure are: to withstand the static and dynamic loads acting on the satellite, to provide a fixed installation interface for spaceborne instruments and equipment and to maintain stable accuracy, and to ensure the geometry of the entire satellite.

Some of the instruments and equipment of satellite subsystems are directly installed on the main load-bearing components, and most of the instruments and equipment are connected to the main load-bearing components through secondary components such as partitions and wall panels. The overall layout and mass characteristics of the main load-bearing components should adapt to the mechanical environment of the launch vehicle. The force-bearing direction of the main load-bearing components of the satellite structure system should be consistent with the thrust direction of the launch vehicle.

The main load-bearing structure is the backbone of the satellite. It bears axial, bending, shearing and torsional loads. Due to the different forms of the main load-bearing components selected by the satellite, its configuration will also vary greatly. At present, the main load-bearing structure can be generally divided into four types: box-shaped plate type, central load-bearing cylinder type, truss type, and shell type.

Box-shaped plate structure: the main load-bearing structure is mainly a box-shaped structure composed of honeycomb sandwich panels. For example, the main load-bearing structure of my country's CAST968 small satellite platform and CAST2000 small satellite platform is a box-shaped plate structure, and the typical one is the A2100 satellite platform of Lockheed Martin Corporation of the United States. If the main load-bearing structure of the box-plate type is selected, because the payload camera is relatively large and occupies a large space, it is not convenient for the final assembly operation whether it is installed vertically or horizontally.

Central load-bearing cylinder structure: The main load-bearing member of this type of satellite is located in the center of the satellite body. For example, my country's Dongfanghong No. 3 satellite platform is composed of a central load-bearing tube and a structural plate to form the main load-bearing structure. The solar wings, antennas, and instruments are connected to the load-bearing components through connection interfaces, brackets, etc., and the load is transferred to the main force transmission path. Its characteristic is that the load is mainly transmitted through the internal force transmission path, and the plate frame structures such as star-arrow docking rings and partitions also transmit loads through the internal force transmission path.

For small satellites, if the central load-bearing cylinder is to play the main load-bearing role, its diameter must be equivalent to the size of the docking ring. In this case, the external space is very small, and the equipment installation space provided is not much. The internal space is limited due to the installation and disassembly space requirements of the camera. The utilization rate is low and it is inconvenient to operate. There is no way to install equipment in the form of side plates or adding platforms. Even if the instruments and equipment are arranged on the periphery, the large moment of inertia of the whole star is not conducive to the overall small inertia requirement. And because the engine of the propulsion system needs to extend out of the star body, it is necessary to open holes in the corresponding parts of the load-bearing tube, which also affects the rigidity of the load-bearing tube.

Truss structure: Its main load-bearing member is a truss composed of rods. Such as the HS702 satellite platform of Hughes Corporation of the United States. The truss can have many forms, therefore, the configuration of the truss load-bearing satellite is also diversified. Triangular trusses or polygonal trusses can be used. The configuration of the truss-type main load-bearing member is different, and the configuration of the satellite is also different. The truss structure has high requirements on materials and structures, and there are few examples of it as the main load-bearing structure in China, and the technical difficulty is relatively large.

Outer shell structure: The cabin is used as the main load-bearing component, and the load is mainly transmitted through the external force path. This type of satellite is often connected by multiple cabins, the cabins are connected by the cabin flange, and the lowest cabin connected to the launch vehicle bears the load of the entire spacecraft. For example, most of my country's returnable satellites and manned spacecraft of various countries adopt this structure. However, when there is a heavy payload at the center of the satellite, it is not convenient to select only the shell as the main force transmission structure.

The above-mentioned structures all adopt a single force transmission route, which results in a large moment of inertia on the longitudinal axis and cannot satisfy the mobility of the payload. At present, a single main load-bearing structure can no longer meet the needs of agile maneuvering of small satellites, but it is difficult to realize the main load-bearing structure in multiple ways in terms of design and structure, and there are no relevant reports in the literature.

Contents of the invention

The technical problem of the present invention is: to overcome the deficiencies of the prior art, to provide a new type of spacecraft main load-bearing structure with small vertical axis inertia, easy rolling and pitching maneuvers for the payload, and adopting internal and external dual load-bearing paths.

The technical solution of the present invention is: a new type of spacecraft main load-bearing structure, including a propulsion cabin structure, a star truss structure and an electronic cabin main frame structure; the upper part of the propulsion cabin structure is connected to the electronic cabin main frame structure, and the lower part serves as The reference plane for whole-star precision detection and the installation surface for propulsion cabin instruments and equipment are provided; the star-shaped truss structure is a load installation frame supported by struts, which is located in the main frame structure of the electronic cabin and is used for installing payloads. The lower end is fixedly connected to the upper part of the propulsion cabin structure.

The structure of the propulsion cabin is in the shape of a truncated cone, including the lower end frame of the propulsion cabin, the shell of the propulsion cabin, the reinforcement stringers of the thrust cabin and the upper end frame of the thrust cabin; The lower end frame of the propulsion compartment and the upper end frame of the propulsion compartment, the upper end surface of the upper end frame of the propulsion compartment is connected to the main frame structure of the electronic compartment, and the conical surface at the lower part of the upper end frame of the propulsion compartment is the connection surface of the propulsion compartment shell.

The lower end frame of the propulsion cabin is provided with an inner flange, which is used as a reference plane for whole-star precision testing and provides a mounting surface for propulsion cabin instruments and equipment.

The number of struts in the star-shaped truss structure is an even number of no less than six, and the tops of every two struts share a connecting joint, the upper end of the joint is connected to the load installation frame, and the lower end of the joint is connected to the propulsion cabin structure.

The main frame structure of the electronic cabin includes the lower corner bar of the main frame, the main frame column, the upper corner bar of the main frame and the reinforcement support. Install reinforced supports at the corner strips.

The main frame structure of the electronic cabin also includes a T-shaped corner bar, which is located between the lower corner bar of the main frame and the upper corner bar of the main frame to support the main frame column.

The beneficial effect of the present invention compared with prior art is:

1. The main load-bearing structure of the satellite of the present invention is docked with the launch vehicle, and the outer frame side plate structure and the inner star-shaped truss structure are used to form a hybrid main structure with internal and external double load-bearing paths to transmit the entire satellite load. The force transmission path is short and continuous. Its main force transmission path is:

Inside: payload camera→payload star truss support structure→lower end frame of propulsion module→carrying docking frame;

Outside: top plate and side plate→main frame structure→upper frame of propulsion cabin→shell of propulsion cabin→lower frame of propulsion cabin→carrying docking frame.

Therefore, the invention has a compact structure and a low center of mass, and meets the requirements of high rigidity and small inertia of the entire satellite.

2. The structure of the satellite body has broken through the box-plate structure configuration that was often used in the past. The plate shell structure, truss structure and load-bearing conical cylinder with reinforced stringers are rationally used. The star-shaped truss structure used for the docking of the payload and the platform is the largest. Maximize installation accuracy. A star-shaped truss structure and a dual-path load-bearing structure combining the inside and outside of the main frame of the outer plate are formed, so that the overall rigidity of the satellite is better guaranteed.

Description of drawings

Fig. 1 is the general view of main bearing structure of the present invention;

Fig. 2 is the general view of propulsion cabin structure of the present invention;

Fig. 3 is the general view of star truss structure of the present invention;

Fig. 4 is a general view of the main frame structure of the present invention.

Detailed ways

As shown in Figure 1, a novel satellite main load-bearing structure of the present invention includes a propulsion cabin structure, a star truss structure and an electronic cabin main frame structure; the upper part of the propulsion cabin structure is connected to the electronic cabin main frame structure, and the lower part serves as Accuracy detection reference plane and installation surface for propulsion cabin instruments and equipment; the star truss structure is located in the main frame structure of the electronic cabin, which is a load installation frame supported by struts for installing payloads, and the lower ends of the struts are fixedly connected In the upper part of the propulsion compartment structure.

As shown in Figure 2, the structure of the propulsion cabin is in the shape of a truncated cone, including the lower end frame 1 of the propulsion cabin, the casing 2 of the propulsion cabin, the reinforcement stringers 3 of the thrust cabin, and the upper end frame 4 of the thrust cabin; the reinforcement stringers 3 of the thrust cabin are distributed in the Around the cabin shell 2, its two ends are respectively fixedly connected to the lower end frame 1 of the propulsion cabin and the upper end frame 4 of the propulsion cabin. The lower conical surface is the connecting surface of the propulsion cabin shell 2 .

The frame 1 at the lower end of the propulsion cabin is provided with an inner flange, which serves as a datum surface for whole-star precision testing and provides a mounting surface for propulsion cabin instruments and equipment.

As shown in FIG. 3 , the star truss structure 6 is a load mounting frame supported by struts, which is used to install the payload camera and related loads, and provides the basic rigidity of the camera. There are eight struts in this embodiment, and the tops of every two struts share a joint. The upper end of the joint is connected to the load installation frame, and the lower end of the joint is connected to the lower end frame 1 of the propulsion compartment structure.

As shown in FIG. 4 , the main frame structure of the electronic cabin in this embodiment includes six main frame lower corner bars 5 , six main frame upright columns 7 , six main frame upper corner bars 9 and six reinforcement supports 10 . The main frame column 7 is connected with the main frame lower angle bar 5 and the main frame upper angle bar 9, and the reinforcement support 10 is installed near the main frame upper angle bar 9 on the main frame column 7.

Between the lower corner bar 5 of the main frame and the upper corner bar 9 of the main frame, there are six T-shaped corner bars 8 for supporting the column 7 of the main frame.

The main frame structure is the central part of the electronic cabin, and its main function is to connect the structural plates into a whole closed structure and ensure the strength of the connection between the electronic cabin and the propulsion cabin.

The main assembly sequence of the main load-bearing structure of this small satellite is as follows:

(1) The lower end frame 1 of the propulsion compartment, the shell 2 of the propulsion compartment, the reinforcing stringer 3 of the propulsion compartment, and the upper frame 4 of the propulsion compartment of the propulsion compartment structure are mainly connected into a whole by riveting. , Replaced by screw connection to prevent peeling.

(2) Considering the installation accuracy of the payload and the convenience of the assembly operation, a star-shaped truss structure 6 is adopted to realize the docking of the payload and the platform. Bolt the bottom of the star-shaped truss structure 6 to the inner flange of the lower end frame 1 of the propulsion cabin.

(3) Connect the lower corner strips 5 of the six main frames that have been riveted to the upper end frame 4 of the propulsion cabin by screwing or riveting.

(4) Connect the six main frame columns 7, six main frame T-shaped corner strips 8, six main frame upper corner strips 9, and six reinforcement supports 10 through transition corner boxes to form a whole main frame structure and have been connected with The lower angle bar 5 of the main frame connected to the structure of the propulsion cabin is connected by bolts.

Claims (6)

1. A novel spacecraft main load-bearing structure is characterized in that it comprises a propulsion cabin structure, a star-shaped truss structure (6) and an electronic cabin main frame structure; the top of the said propulsion cabin structure connects the electronic cabin main frame structure, and the bottom serves as Whole-star precision detection datum plane and providing installation surface for propulsion cabin equipment; said star-shaped truss structure (6) is a load installation frame supported by struts, located in the main frame structure of electronic cabin, for installing payload, The lower ends of the struts are fixedly connected to the upper part of the propulsion cabin structure. 2. The main load-bearing structure of a novel spacecraft according to claim 1, characterized in that: the propulsion cabin structure is in the shape of a truncated cone, comprising a lower end frame (1), a propulsion cabin shell (2), and a propulsion cabin Reinforced stringers (3) and the upper end frame (4) of the propulsion cabin; the reinforced stringers (3) of the propulsion compartment are distributed around the shell (2) of the propulsion compartment, and the two ends are respectively fixedly connected to the lower end frame (1) of the propulsion compartment and the upper end of the propulsion compartment Frame (4), the upper end surface of the upper end frame (4) of the propulsion cabin is connected to the main frame structure of the electronic cabin, and the conical surface at the lower part of the upper end frame (4) of the propulsion cabin is the connecting surface of the shell of the propulsion cabin. 3, according to claim 1 or 2 a kind of novel spacecraft main load-bearing structure, it is characterized in that: the lower end frame (1) of described propulsion cabin is provided with inner flange, as whole satellite accuracy detection reference plane and provides propulsion cabin instrument The mounting surface of the device. 4. The main load-bearing structure of a novel spacecraft according to claim 1, characterized in that: the number of struts of the star-shaped truss structure (6) is an even number not less than six, and the tops of every two struts Share a connecting joint, the upper end of the joint is connected with the load installation frame, and the lower end of the joint is connected with the structure of the propulsion cabin. 5. The main load-bearing structure of a novel spacecraft according to claim 1, characterized in that: said electronic cabin main frame structure comprises a main frame lower corner bar (5), a main frame column (7), a main frame upper corner bar ( 9) and reinforced support (10), the main frame column (7) connects the main frame lower corner bar (5) and the main frame upper corner bar (9), and is close to the main frame upper corner bar (9) on the main frame column (7) Install reinforcement support (10). 6. The main load-bearing structure of a novel spacecraft according to claim 5, characterized in that: the main frame structure of the electronic cabin also includes a T-shaped corner bar (8), which is located on the lower corner bar (5) of the main frame and the main frame The main frame columns (7) are supported between the corner bars (9).

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