A modular star cover assembly structure without a transfer frame

Abstract

A modular star cover assembly structure without an adapter frame belongs to the field of space technology, and includes a fairing, a satellite bracket, an instrument cabin and connecting screws; the fairing is located at the top of a rocket; the satellite bracket is located in the fairing, and the end frame of the satellite bracket is clamped between the fairing and the instrument cabin, which is used to connect the satellite and the rocket, and plays a force transmission role, transferring the load formed by the satellite to the rocket control cabin; the fairing, the satellite bracket and the satellite together constitute a star cover assembly; the instrument cabin is installed under the fairing, forming a mounting base of the star cover assembly, and bearing the load transmitted from the star cover assembly; the connecting screws are used to connect and fix the star cover assembly. The present invention eliminates the adapter frame through the end frame stacking load-bearing structure to achieve structural weight reduction; the present invention realizes the double docking of the fairing-satellite bracket and the star cover assembly-instrument cabin under the stacking structure through the group installation of connecting bolts, and the star cover assembly can be transported independently, and the fairing can be separated during flight.

Description

Technical Field

[0001] The invention relates to a modular star cover assembly structure without a switching frame, belonging to the field of space technology. Background Art

[0002] The star cover assembly refers to the use of a fairing to encapsulate the satellite and the satellite bracket into a whole, so as to facilitate the transfer and transportation of the satellite and simplify the docking operation with the rocket. The star cover assembly structure needs to connect the fairing, the satellite bracket and the rocket body instrument cabin into one. At present, the docking structure design of the star cover assembly is realized by an adapter frame structure, such as Figure 1 shown.

[0003] The adapter frame type star cover assembly uses the adapter frame as a connecting structure, but due to the overall size constraints, the height of the adapter frame is usually very low. When the load of the satellite bracket needs to be transmitted through the adapter frame, a large bending moment is formed, which makes the adapter frame bear a poor load-bearing state, heavy weight, and loses some carrying capacity. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide a modular star cover assembly structure without an adapter frame, to change the Y-shaped load-bearing structure of the adapter frame into a stacked load-bearing structure of the fairing-satellite bracket-instrument cabin end frame, and to realize the double docking of the fairing-satellite bracket and the star cover assembly-instrument cabin under the stacked structure by group installation of connecting bolts.

[0005] The technical solution of the present invention is: a modular satellite cover assembly structure without an adapter frame, including a fairing, a satellite bracket, an instrument cabin and connecting screws;

[0006] The fairing is located at the top of the rocket;

[0007] The satellite bracket is located in the fairing, and the end frame of the satellite bracket is clamped between the fairing and the instrument cabin, and is used to connect the satellite and the rocket, and plays a force transmission role, transmitting the load formed by the satellite to the rocket control cabin; the fairing, the satellite bracket and the satellite together constitute a satellite cover assembly;

[0008] The instrument cabin is installed below the fairing, forming a mounting base for the star cover assembly, and bearing the load transmitted from the star cover assembly;

[0009] The connecting screws are used to connect and fix the star cover assembly.

[0010] Furthermore, the connecting screws include fairing separation explosive bolts; the fairing separation explosive bolts connect the fairing with the satellite bracket and the instrument cabin as a whole, and are installed when the satellite cover assembly is docked with the instrument cabin. When the fairing is separated, the separation explosive bolts are unlocked to release the fairing.

[0011] Furthermore, the fairing separation explosion bolts connect the fairing, the satellite bracket and the three-layer docking frame of the instrument cabin.

[0012] Furthermore, the connecting screws include a first docking bolt, which is used for docking the star cover assembly with the instrument cabin; the docking bolt connects the satellite bracket and the instrument cabin as one, and is installed when the star cover assembly and the instrument cabin are docked. After the fairing is separated, the docking bolt becomes the only connecting structure between the satellite bracket and the instrument.

[0013] Furthermore, the first docking bolts connect the two docking frames of the satellite bracket and the instrument cabin.

[0014] Furthermore, the connecting screws include a second docking bolt, which is used for docking the fairing with the satellite bracket; the second docking bolt is a process bolt, which is only used during the preparation process for rocket launch and is removed before launch; the second docking bolt is installed when the fairing is docked with the satellite bracket, connecting the fairing and the satellite bracket as one to form a star cover assembly, and the star cover assembly is transported independently; after the star cover assembly is docked with the instrument cabin, the second docking bolt is removed from one side of the instrument cabin through the screw hole on the instrument cabin to prevent it from affecting the separation of the fairing.

[0015] Furthermore, the second docking bolts connect the two-layer docking frames of the fairing and the satellite bracket.

[0016] Furthermore, the fairing, the satellite bracket, and the docking frame of the instrument cabin are directly connected by docking bolts without providing an adapter frame.

[0017] Furthermore, the docking frames of the fairing, satellite bracket and instrument cabin are stacked and connected in the order of fairing docking frame, satellite bracket docking frame and instrument cabin docking frame from top to bottom.

[0018] Furthermore, the instrument cabin docking frame is provided with a hole for removing the second docking bolt from one side of the instrument cabin, so that after the star cover assembly is docked with the instrument cabin, the second docking bolt can be removed from one side of the instrument cabin to avoid affecting the function of separating the fairing.

[0019] The advantages of the present invention compared with the prior art are:

[0020] (1) The present invention uses an end frame stacking bearing structure to eliminate the adapter frame, thereby achieving structural weight reduction;

[0021] (2) The present invention realizes two dockings of the fairing-satellite bracket and the satellite cover assembly-instrument cabin under the stacked structure by installing the connecting bolts in groups. The satellite cover assembly can be transported independently and the fairing can be separated during flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1Design of docking structure for traditional star cover assembly;

[0023] Figure 2 It is a stacked load-bearing structure of fairing-satellite bracket-instrument cabin end frame of the present invention;

[0024] Figure 3 The fairing and satellite bracket docking structure of the present invention;

[0025] Figure 4 It is a docking structure between the star cover assembly and the rocket instrument cabin of the present invention;

[0026] Figure 5 The fairing and the satellite bracket of the present invention are respectively connected to the instrument cabin. DETAILED DESCRIPTION

[0027] In order to better understand the above technical scheme, the technical scheme of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical scheme of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other.

[0028] The following is a further detailed description of a modular star cover assembly structure without a transfer frame provided by an embodiment of the present application in conjunction with the accompanying drawings of the specification. The specific implementation method may include (such as Figures 1 to 5 shown):

[0029] The docking bolts between the fairing, satellite bracket and instrument compartment are divided into three groups. Figure 2 As shown, the first group is the explosion bolts for fairing separation, the second group is the bolts for docking the star cover assembly (fairing and satellite bracket) with the instrument cabin, and the third group is the bolts for docking the fairing with the satellite bracket. The first and third groups of bolts are installed when the star cover assembly is docked with the control cabin, and the second group of bolts is installed when the fairing is docked with the satellite bracket to form the star cover assembly. The first group of bolts is detonated and disconnected when the fairing is separated, and the second group of bolts is removed when the star cover assembly is docked with the control cabin.

[0030] Specifically, a modular satellite cover assembly structure without an adapter frame includes a fairing, a satellite bracket, an instrument cabin and connecting screws; the fairing is located at the top of the rocket, the instrument cabin is below the fairing, the satellite bracket is located inside the fairing, and the end frame of the satellite bracket is clamped between the fairing and the instrument cabin.

[0031] The docking frames of the fairing, satellite bracket and instrument cabin are directly connected with docking bolts without setting up an adapter frame.

[0032] The docking frames of the fairing, the satellite bracket and the instrument cabin are stacked and connected in the order of the fairing docking frame, the satellite bracket docking frame and the instrument cabin docking frame from top to bottom.

[0033] The instrument cabin docking frame is provided with a hole for removing the second docking bolt from one side of the instrument cabin, so that after the star cover assembly is docked with the instrument cabin, the second docking bolt can be removed from one side of the instrument cabin to avoid affecting the function of separating the fairing.

[0034] The main function of the fairing is to protect the satellite and satellite bracket installed in the fairing. After the rocket flies out of the atmosphere, the fairing completes its mission and separates from the rocket.

[0035] The satellite bracket is a connecting structure between the satellite and the rocket, which plays a connecting and force transmission role, and transmits the load formed by the satellite to the control cabin;

[0036] The fairing and the satellite bracket (including the satellite) together constitute the satellite cover assembly;

[0037] The instrument cabin constitutes a mounting base for the fairing and the satellite bracket, and bears the loads transmitted from the fairing and the satellite bracket.

[0038] The connecting screws play a role of connecting and fixing, and connect the fairing, the satellite bracket and the instrument cabin into one.

[0039] The docking frames of the fairing, satellite bracket and instrument cabin are directly stacked and connected in the order of fairing docking frame, satellite bracket docking frame and instrument cabin docking frame from top to bottom. That is, there is no gap between the three layers of docking frames, and the transfer frame structure is cancelled.

[0040] Furthermore, the connecting screws include fairing separation explosion bolts, star cover assembly (fairing and satellite bracket) and instrument cabin docking bolts, and fairing and satellite bracket docking bolts.

[0041] The fairing separation explosive bolts connect the fairing, the satellite bracket and the instrument cabin as a whole, and are installed when the satellite cover assembly is docked with the instrument cabin. When the fairing is separated, the separation explosive bolts are unlocked to release the fairing; the fairing separation explosive bolts connect the three-layer docking frame of the fairing, the satellite bracket and the instrument cabin.

[0042] The star cover assembly and the instrument cabin docking bolts connect the satellite bracket and the instrument cabin as a whole, and are installed when the star cover assembly and the instrument cabin are docked. After the fairing is separated, the star cover assembly and the instrument cabin docking bolts become the only connection structure between the satellite bracket and the instrument; the star cover assembly and the instrument cabin docking bolts connect the two-layer docking frames of the satellite bracket and the instrument cabin.

[0043] The fairing and satellite bracket docking bolts are process bolts, which are only used during the preparation process of rocket launch and are removed before launch. The fairing and satellite bracket docking bolts are installed when the fairing and satellite bracket are docked, connecting the fairing and the satellite bracket into one body to form a star cover assembly, and the star cover assembly can be transported independently. After the star cover assembly is docked with the instrument cabin, the fairing and satellite bracket docking bolts are removed from one side of the instrument cabin through the screw holes on the instrument cabin to prevent them from affecting the separation of the fairing. The fairing and satellite bracket docking bolts connect the two-layer docking frames of the fairing and the satellite bracket.

[0044] In the solution provided in the embodiment of the present application, Figure 3 , the fairing is docked with the satellite bracket, and only the third set of bolts is installed. At this time, the star cover assembly is formed and can be transported to the site for docking with the rocket.

[0045] like Figure 4 , the star cover assembly docks with the rocket instrument cabin, the first and second sets of bolts are installed, and the third set of bolts is removed. This is the launch state.

[0046] like Figure 5 During the flight, the fairing separation explosive bolts unlocked and the fairing separated. After that, only the second set of bolts remained to connect the instrument cabin and the satellite bracket.

[0047] When the satellite cover assembly is not used, and the fairing and the satellite bracket are docked with the instrument cabin respectively, the satellite bracket end frame is cancelled between the docking surface of the fairing and the instrument cabin, and the satellite bracket is connected to other parts of the instrument cabin. In order to keep the connection thickness and the overall appearance consistent, a gasket with the same thickness as the satellite bracket end frame is added below the lower end frame of the fairing. The gasket is connected to the fairing and separated together. The second and third sets of bolts are not installed, and the structure of the fairing and the instrument cabin does not need to be changed.

[0048] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

[0049] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A modular star cover assembly structure without an adapter frame, characterized in that: Includes fairing, satellite bracket, instrument compartment and connecting screws; The fairing is located at the top of the rocket; The satellite bracket is located in the fairing, and the end frame of the satellite bracket is clamped between the fairing and the instrument cabin, and is used to connect the satellite and the rocket, and plays a force transmission role, transmitting the load formed by the satellite to the rocket control cabin; the fairing, the satellite bracket and the satellite together constitute a satellite cover assembly; The instrument cabin is installed below the fairing, forming a mounting base for the star cover assembly, and bearing the load transmitted from the star cover assembly; The connecting screws are used to connect and fix the star cover assembly; The connecting screws include fairing separation explosive bolts; the fairing separation explosive bolts connect the fairing with the satellite bracket and the instrument cabin as a whole, are installed when the satellite cover assembly is docked with the instrument cabin, and when the fairing is separated, the separation explosive bolts are unlocked to release the fairing; The connecting screws include a first docking bolt, which is used for docking the satellite cover assembly with the instrument cabin; the first docking bolt connects the satellite bracket with the instrument cabin as a whole, and is installed when the satellite cover assembly is docked with the instrument cabin. After the fairing is separated, the first docking bolt becomes the only connection structure between the satellite bracket and the instrument cabin; The connecting screws include a second docking bolt, which is used for docking the fairing with the satellite bracket; the second docking bolt is a process bolt, which is only used in the rocket launch preparation process and is removed before launch; the second docking bolt is installed when the fairing is docked with the satellite bracket, and the fairing and the satellite bracket are connected as a whole to form a star cover assembly, and the star cover assembly is transported independently; after the star cover assembly is docked with the instrument cabin, the second docking bolt is removed from one side of the instrument cabin through the screw hole on the instrument cabin to prevent it from affecting the separation of the fairing; The fairing, satellite bracket and instrument cabin docking frame are directly connected by docking bolts without providing an adapter frame; The docking frames of the fairing, the satellite bracket and the instrument cabin are stacked and connected in the order of the fairing docking frame, the satellite bracket docking frame and the instrument cabin docking frame from top to bottom.

2. According to claim 1, a modular star cover assembly structure without an adapter frame is characterized in that: The fairing separation explosion bolts connect the fairing, the satellite bracket and the three-layer docking frame of the instrument cabin.

3. According to claim 1, a modular star cover assembly structure without an adapter frame is characterized in that: The first docking bolts connect the satellite bracket and the two-layer docking frame of the instrument cabin.

4. The modular star cover assembly structure without an adapter frame according to claim 1, characterized in that: The second docking bolts connect the fairing and the two-layer docking frames of the satellite bracket.

5. The modular star cover assembly structure without an adapter frame according to claim 1, characterized in that: The instrument cabin docking frame is provided with a hole for removing the second docking bolt from one side of the instrument cabin, so that after the star cover assembly is docked with the instrument cabin, the second docking bolt can be removed from one side of the instrument cabin to avoid affecting the function of separating the fairing.

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