Self-adaptive deformation gas cylinder transverse supporting structure

Abstract

The invention discloses a self-adaptive deformation gas cylinder transverse supporting structure which is used for installing a gas cylinder on a spacecraft structure. The gas cylinder transverse supporting structure comprises a structure body, a support, a cover plate, a lining and a hoop. The structure body is of a triangular structure, and three vertexes of the triangular structure are respectively marked as a point A, a point B and a point C; the two supports are installed at the position of a point A and the position of a point B of the structure body respectively. The lining is limited at the position of a point C of the structure body through the hoop; and the cover plate is connected with a combined body of the structure body and the hoop through a screw. According to the gas cylinder transverse supporting structure, the problem that the gas cylinder is clamped relative to the gas cylinder transverse supporting structure due to the fact that the vertical state of the axis of the gas cylinder and the gas cylinder transverse supporting structure is changed in the gas cylinder inflation and deflation process is solved.

Description

Technical Field

[0001] The invention belongs to the technical field of spacecraft design, and in particular relates to a gas cylinder lateral support structure with adaptive deformation. Background Art

[0002] Spacecraft propulsion systems are usually equipped with gas cylinders, and the maximum pressure of the gas cylinders can reach 30MPa. After the gas cylinders are pressurized, the volume of the gas cylinders will expand, and after expansion, the elongation of the gas cylinders along the axis direction can reach 10mm.

[0003] The installation state of the gas cylinder is usually that one end is fixed on the spacecraft structure, and the other end is free along the axis direction to meet the axial extension requirements of the gas cylinder after pressurization. Therefore, a transverse support structure needs to be designed on the top of the gas cylinder to limit the lateral shaking of the gas cylinder during mechanical testing and launch, while meeting the requirements of free extension along the axis of the gas cylinder during inflation and retraction after exhaust. Due to factors such as spacecraft structural processing errors, gas cylinder installation errors, the axis of the gas cylinder that does not change along a straight line, and structural deformation caused by the filling and discharge of tank propellants, the maximum change can reach 0.2mm. The accumulated deformation usually causes a slight change in the angle between the axis of the gas cylinder and the transverse support structure of the gas cylinder when the gas cylinder is inflated and extended or when the gas cylinder is exhausted and retracted, and no longer maintains a vertical state, causing the gas cylinder to become stuck relative to the transverse support structure. Summary of the invention

[0004] The technology of the present invention solves the problem: Overcoming the shortcomings of the prior art, providing an adaptively deformable gas cylinder lateral support structure, aiming to solve the problem that the vertical state of the gas cylinder axis and the gas cylinder lateral support structure changes during the gas cylinder filling and exhaust process, resulting in the gas cylinder getting stuck relative to the gas cylinder lateral support structure.

[0005] In order to solve the above technical problems, the present invention discloses an adaptively deformable gas cylinder lateral support structure, comprising: a structural body, a support, a cover plate, a bushing and a clamp;

[0006] The structure is a triangular structure, and the three vertices of the triangular structure are respectively recorded as point A, point B and point C;

[0007] The two supports are respectively installed at point A and point B of the structure body;

[0008] The bushing is limited at point C of the structural body by a clamp;

[0009] The cover plate is connected to the combination of the structural body and the clamp through screws.

[0010] In the above-mentioned adaptively deformable gas cylinder lateral support structure, the gas cylinder is installed on the spacecraft structure through the gas cylinder lateral support structure.

[0011] In the above-mentioned adaptively deformable gas cylinder lateral support structure, there are two bushings and the structure is semicircular.

[0012] In the above-mentioned adaptively deformable gas cylinder lateral support structure, during assembly:

[0013] Put two semicircular bushings on the top cylindrical surface of the gas cylinder, and limit the bushings at point C of the structure body through clamps;

[0014] Installing the cover plate on the combination of the structural body and the clamp;

[0015] Mounting two supports on the spacecraft structure;

[0016] Connect the two supports to point A and point B of the structure respectively.

[0017] In the above-mentioned adaptively deformable gas cylinder transverse support structure, the clamp and the structure body, the cover plate and the combination of the structure body and the clamp, the support and the spacecraft structure, and the support and the structure body are all connected by screws.

[0018] In the above-mentioned adaptively deformable gas cylinder transverse support structure, the matching surfaces of the bushing and the gas cylinder are cylindrical surfaces, and a clearance fit is adopted, and the matching clearance is 0.02mm~0.04mm, so as to realize the axial movement of the gas cylinder relative to the gas cylinder transverse support structure when the gas cylinder is pressurized and expanded.

[0019] In the above-mentioned adaptively deformable gas cylinder transverse support structure, the bushing and the combination of the structural body and the clamp are matched with a spherical clearance of 0.01mm to 0.03mm to adapt to the inclination of the cylinder axis caused by the inflation of the cylinder or the structural deformation.

[0020] In the above-mentioned adaptively deformable gas cylinder transverse support structure, a gap is left between the structural body, the clamp and the cover plate and the cylindrical surface of the gas cylinder. The gap size is k, so that the gas cylinder does not interfere with the structural body, the clamp and the cover plate when the angle between the gas cylinder axis and the gas cylinder transverse support structure changes.

[0021] In the above-mentioned adaptively deformable gas cylinder lateral support structure, the lining material is polytetrafluoroethylene.

[0022] In the above-mentioned adaptively deformable gas cylinder transverse support structure, the two bushings are obtained by cutting the circular ring part processed at one time.

[0023] The present invention has the following advantages:

[0024] (1) The present invention discloses an adaptively deformable gas cylinder transverse support structure, which can adapt to the change in the vertical state between the axis of the gas cylinder and the transverse support structure of the gas cylinder when the gas cylinder is filled or exhausted, and effectively avoid the occurrence of jamming.

[0025] (2) The present invention discloses an adaptively deformable gas cylinder lateral support structure, which can adapt to structural deformation caused by factors such as spacecraft processing errors, assembly errors, and tank filling when the gas cylinder is installed.

[0026] (3) The present invention discloses an adaptively deformable gas cylinder lateral support structure, which has a split structure with the gas cylinder connection part, so that the installation of the gas cylinder lateral support structure is not affected by the pipeline welding state, which is flexible and convenient.

[0027] (4) The present invention discloses a gas cylinder transverse support structure with adaptive deformation. The structure body and the support are connected by screws. The structural processing error and assembly error can be adapted by filing the screw connection holes between the structure body and the support, and the adaptability is strong.

[0028] (5) The present invention discloses a gas cylinder lateral support structure with adaptive deformation, which can be extended to other support structure designs with assembly errors and deformation during product use. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a schematic diagram of a gas cylinder installation state in an embodiment of the present invention;

[0030] Figure 2 is a structural schematic diagram of a gas cylinder lateral support structure with adaptive deformation in an embodiment of the present invention;

[0031] Figure 3 is a schematic diagram of an explosion state of a gas cylinder lateral support structure with adaptive deformation in an embodiment of the present invention;

[0032] Figure 4 Schematic diagram of the coordination between a gas cylinder transverse support structure and a gas cylinder in an embodiment of the present invention DETAILED DESCRIPTION

[0033] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0034] One of the core ideas of the present invention is: disclosing an adaptively deformable gas cylinder lateral support structure, which is composed of a structural body, a support, a cover plate, a bushing and a clamp; the structural body, the cover plate and the clamp constitute the main load-bearing structure of the support structure; the bushing is installed between the main load-bearing structure and the gas cylinder.

[0035] In this embodiment, if Figures 1 to 4As shown, the gas cylinder 3 is installed on the spacecraft structure 2 through the gas cylinder transverse support structure 1. The adaptively deformable gas cylinder transverse support structure mainly includes: a structural body 4, a support 5, a cover plate 6, a bushing 7 and a clamp 8. Among them, the structural body 4 is a triangular structure, and the three vertices of the triangular structure are respectively recorded as point A, point B and point C; the two supports 5 are respectively installed at the point A and point B positions of the structural body 4; the bushing 7 is limited at the point C position of the structural body 4 by the clamp 8; the cover plate 6 is connected to the combination of the structural body 4 and the clamp 8 by screws.

[0036] In this embodiment, there are two bushings 7, and the structure is semicircular. The bushing 7 is made of polytetrafluoroethylene, which has good self-lubricating properties. When the gas cylinder 3 is inflated and expanded, there is less friction with the gas cylinder 3, the structural body 4, and the clamp 8. The bushing 7 can also be made of other materials, which is not limited by the embodiment of the present invention. The two bushings 7 can be obtained by cutting the circular ring part processed once, that is, the circular ring part processed once is cut symmetrically along the center line to obtain two semicircular bushings to ensure the spherical processing accuracy, and the two cut bushings are required to be uniquely matched and used together in one gas cylinder transverse support structure 1.

[0037] In this embodiment, the assembly process of the gas cylinder transverse support structure and the gas cylinder is as follows: two semicircular structure bushings 7 are sleeved on the top cylindrical surface of the gas cylinder 3, and the bushings 7 are limited at the point C position of the structure body 4 by the clamp 8; the cover plate 6 is installed on the combination of the structure body 4 and the clamp 8; the two supports 5 are installed on the spacecraft structure 2; the two supports 5 are respectively connected to the points A and B positions of the structure body 4. Among them, the clamp 8 and the structure body 4, the cover plate 6 and the combination of the structure body 4 and the clamp 8, the support 5 and the spacecraft structure 2, and the support 5 and the structure body 4 are all connected by screws.

[0038] Preferably, the matching surfaces of the bushing 7 and the gas cylinder 3 are cylindrical surfaces, and a clearance fit is adopted, and the matching clearance is 0.02mm-0.04mm, so as to realize the axial movement of the gas cylinder 3 relative to the gas cylinder transverse support structure 1 along the gas cylinder when the gas cylinder 3 is pressurized and expanded.

[0039] Preferably, there is a spherical clearance fit between the bushing 7 and the combination of the structural body 4 and the clamp 8, and the fit clearance is 0.01mm-0.03mm to accommodate the inclination of the cylinder axis caused by the inflation of the cylinder 3 or the structural deformation.

[0040] Preferably, a gap is left between the structural body 4, the clamp 8 and the cover plate 6 and the cylindrical surface of the gas cylinder 3, and the gap size is k (k is required to be larger than the lateral deformation of the gas cylinder when inflated, generally k>0.3mm), so as to adapt to the gas cylinder 3 not interfering with the structural body 4, the clamp 8 and the cover plate 6 when the angle between the gas cylinder axis and the gas cylinder lateral support structure 1 changes.

[0041] Preferably, during the specific structural design, the cover plate 6 can be integrated into the combination of the structural body 4 and the clamp 8 as required.

[0042] Preferably, after the structural body 4 and the clamp 8 are combined, spherical surface SRr (SR is the method of expressing the radius of the sphere, r is the value of the sphere radius, usually the value of r is greater than D+10mm, D represents the diameter of the matching section between the gas cylinder and the gas cylinder transverse support structure) processing is performed to ensure the matching spherical surface processing accuracy. When the structural body 4 and the clamp 8 are combined, it is ensured that the contact surface with the cover plate 6 is coplanar, and the structural body 4 and the clamp 8 processed at one time are uniquely paired and used together in a gas cylinder transverse support structure 1.

[0043] Preferably, the structural body 4 and the clamp 8 are positioned by a "concave-convex" matching method, and other positioning methods, such as pin positioning, etc., can also be used, which is not limited in the embodiment of the present invention. .

[0044] Preferably, when installing the gas cylinder transverse support structure 1 on the spacecraft, the screws are tightened after the contact surfaces of the structural body 4, the clamp 8 and the cover plate 6 are coplanar; when using screws to connect the structural body 4 and the support 5, if the threaded hole and the through hole are not aligned, the through hole can be filed to adapt.

[0045] Based on the above embodiment, a specific example is given below for explanation.

[0046] 1) According to the diameter D of the matching section between the gas cylinder 3 and the gas cylinder transverse support structure 1, considering the stress conditions such as gas cylinder installation, mechanical testing, and launching, as well as factors such as the material strength and elastic modulus of the bushing 7, determine the spherical radius SRr of the bushing 7, the structural body 4, and the clamp 8.

[0047] 2) According to the influence of factors such as the change in the filling and exhaust axis of the gas cylinder 3, the processing error of the spacecraft structure 2, the assembly error, the structural deformation caused by the filling of the tank with propellant, and the structural deformation caused by the installation of equipment on the axial angle of the gas cylinder 3 relative to the gas cylinder transverse support structure 1, determine the gap h (generally 1mm>h>0.5mm) between the bushing 7 and the structural body 4, the clamp 8, and the cover plate 6 along the axial direction of the gas cylinder 3.

[0048] 3) The clearance k between the structural body 4, the clamp 8, the cover plate 6 and the cylindrical surface of the gas cylinder 3 is determined according to the clearance h between the bushing 7 and the structural body 4, the clamp 8 and the cover plate 6 along the axial direction of the gas cylinder 3.

[0049] 4) According to the stress state of the gas cylinder 3 during the mechanical test and the launch process, and the spatial position of the gas cylinder 3 in the spacecraft structure 2, the characteristic dimensions such as the cross-sectional dimensions and the external shape of each structural component are determined.

[0050] 5) Determine the matching tolerance between the bushing 7 and the cylindrical surface of the gas cylinder 3, and the matching spherical surface tolerance between the bushing 7 and the structural body 4 and the clamp 8.

[0051] 6) Determine the spherical tolerance of the structural body 4, the clamp 8 and the bushing 7.

[0052] 7) The two bushings 7 are processed at one time, and the structural body 4 and the clamp 8 are combined and then the spherical surface SRr is processed.

[0053] 8) When installing the gas cylinder transverse support structure 1 on the spacecraft, the contact surfaces of the structure body 4, the clamp 8 and the cover plate 6 are required to be coplanar and then the screws are tightened; when using screws to connect the structure body 4 and the support 5, if the threaded hole and the through hole are not aligned, the through hole can be filed to adapt.

[0054] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0055] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. An adaptively deformable gas cylinder lateral support structure, characterized in that: include: A structural body (4), a support (5), a cover plate (6), a bushing (7) and a clamp (8); The structural body (4) is a triangular structure, and the three vertices of the triangular structure are respectively recorded as point A, point B and point C; The two supports (5) are respectively installed at point A and point B of the structural body (4); The bushing (7) is limited at point C of the structural body (4) by a clamp (8); The cover plate (6) is connected to the assembly of the structural body (4) and the clamp (8) by means of screws.

2. The gas cylinder lateral support structure with adaptive deformation according to claim 1, characterized in that: The gas cylinder (3) is mounted on the spacecraft structure (2) via a gas cylinder transverse support structure (1).

3. The gas cylinder lateral support structure with adaptive deformation according to claim 2, characterized in that: There are two bushings (7) with a semicircular structure.

4. The gas cylinder lateral support structure with adaptive deformation according to claim 3 is characterized in that: During assembly: Two semicircular bushings (7) are placed on the top cylindrical surface of the gas cylinder (3), and the bushings (7) are limited at point C of the structure body (4) by means of a clamp (8); Installing the cover plate (6) on the assembly of the structural body (4) and the clamp (8); Mounting two supports (5) on the spacecraft structure (2); The two supports (5) are respectively connected to the structure body (4) at point A and point B.

5. The gas cylinder lateral support structure with adaptive deformation according to claim 4, characterized in that: The clamp (8) and the structural body (4), the cover plate (6) and the assembly of the structural body (4) and the clamp (8), the support (5) and the spacecraft structure (2), and the support (5) and the structural body (4) are all connected by screws.

6. The gas cylinder lateral support structure with adaptive deformation according to claim 4, characterized in that: The matching surfaces of the bushing (7) and the gas cylinder (3) are cylindrical surfaces, and a clearance fit is adopted, wherein the matching clearance is 0.02 mm to 0.04 mm, so as to enable the gas cylinder (3) to move along the axial direction of the gas cylinder relative to the gas cylinder transverse support structure (1) when the gas cylinder (3) is pressurized and expanded.

7. The gas cylinder lateral support structure with adaptive deformation according to claim 4, characterized in that: The bushing (7) and the assembly of the structural body (4) and the clamp (8) are matched with a spherical clearance of 0.01 mm to 0.03 mm to accommodate the inclination of the cylinder axis caused by the inflation of the cylinder (3) or structural deformation.

8. The gas cylinder lateral support structure with adaptive deformation according to claim 4, characterized in that: A gap is left between the structural body (4), the clamp (8) and the cover plate (6) and the cylindrical surface of the gas cylinder (3), and the size of the gap is k, so that when the angle between the axis of the gas cylinder and the gas cylinder transverse support structure (1) changes, the gas cylinder (3) does not interfere with the structural body (4), the clamp (8) and the cover plate (6).

9. The gas cylinder lateral support structure with adaptive deformation according to claim 4, characterized in that: The material of the bushing (7) is polytetrafluoroethylene.

10. The gas cylinder lateral support structure with adaptive deformation according to claim 4, characterized in that: The two bushings (7) are obtained by cutting the circular ring piece processed once.

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