CN115854830A - Manned spacecraft cabin section butt joint surface gap measuring tool and method - Google Patents

Abstract

The invention provides a manned spacecraft cabin section butt joint surface gap measuring tool, which comprises: the shape of the special base is adapted to the size and the shape of a reference surface of a measurement target position, and the contact area of the special base and the reference surface can be increased; and the lever dial indicator is arranged on the special base. The height of the special base meets the following conditions: after the lever dial indicator is installed on the special base, when a measuring swing rod of the lever dial indicator is placed on a measuring surface, an included angle between the axis of the measuring swing rod and the measuring surface is smaller than 15 degrees. By using the tool, the gap of the butt joint surface of the manned spacecraft cabin section can be measured in a narrow space, and the measuring method is simple and high in precision.

Description

Manned spacecraft cabin section butt joint surface gap measuring tool and method

Technical Field

The invention relates to the field of design for spacecraft assembly measurement, in particular to a tool and a method for measuring gaps of butt joint surfaces of cabin sections of manned spacecraft.

Background

The manned spacecraft is composed of a plurality of cabin sections, and the cabin sections are butted to form the whole spacecraft after the final assembly of each cabin section is finished in an independent state in the actual final assembly process. For each cabin section connecting and separating surface, in the final assembly process, in order to achieve the product design performance, a series of strict requirements are provided. Taking the butt joint face of the re-entry capsule and the service capsule as an example, the butt joint process is to hoist the body of the re-entry capsule, a plurality of groups of titanium pipes below the re-entry capsule are in butt joint fit with the bottom face of the groove on the service capsule, and the titanium pipes and the service capsule connecting piece are installed after the re-entry capsule is placed.

The lower end face of the titanium pipe below the returning capsule and the upper end face of the service capsule are connected and separated faces, the connection is completed through a plurality of groups of titanium pipes which are uniformly distributed on the circumference with the diameter of 3.8m, and the lower structure of the returning capsule is made of composite materials and is easy to deform, so that the lower end faces of the plurality of groups of titanium pipes have height difference, and a gap exists between the lower end faces of the titanium pipes and the upper end face of the service capsule after butt joint. The titanium tube is made of titanium alloy material and is fixed on the heat-proof large bottom in a cementing way. If the clearance exceeds the design allowable value, the cementation strength of the titanium pipe is damaged when the connection between the cabins is carried out, the titanium pipe is possibly pulled off forcibly, and the product is seriously damaged.

The titanium pipe and the cabin body butt joint face are matched in a mode that the titanium pipe protrudes and falls into the groove, the actual titanium pipe and the cabin body butt joint face are located in the groove, and a gap cannot be measured. In the final assembly process, the gap between the lower end face of the titanium pipe and the butt joint face of the service cabin is required to be measured and controlled to be less than 0.1mm.

Disclosure of Invention

Aiming at the defects of the effective measurement means of the gap size of the butt joint surface of the titanium pipe of the returning capsule and the service capsule at present, the size of the connecting piece, the peripheral structure of the butt joint surface and the use characteristics of various measurement tools are analyzed, and a simple, safe and feasible measurement method is explored to complete the measurement work of the gap between the titanium pipe of the returning capsule and the butt joint surface of the service capsule.

In order to achieve the purpose, the invention adopts the following technical scheme:

the invention provides a manned spacecraft cabin section butt joint surface gap measuring tool, which comprises:

the shape of the special base is adapted to the size and the shape of a reference surface of a measurement target position, and the contact area of the special base and the reference surface can be increased;

and the lever dial indicator is arranged on the special base.

Further, the height of the dedicated base satisfies the following condition:

after the lever dial indicator is installed on the special base, when a measuring swing rod of the lever dial indicator is placed on a measuring surface, an included angle between the axis of the measuring swing rod and the measuring surface is smaller than 15 degrees.

The invention also provides a method for measuring the gap between the butt joint surfaces of the cabin sections of the manned spacecraft, which comprises the following steps:

s1: establishing a reference, and placing the manned spacecraft cabin section butt joint surface gap measuring tool near a titanium pipe of a returning cabin to enable a measuring swing rod of the lever dial indicator to be in contact with the upper end face of a service cabin;

s2: and setting a zero position, namely placing the measuring oscillating bar on the upper end surface of the service cabin, resetting the lever dial indicator to zero, repeatedly measuring the same position and the nearby position of the upper end surface of the service cabin, checking whether the display number of the lever dial indicator is zero, entering the next step after zero setting, and resetting the zero again if the display number of the lever dial indicator is not zero.

S3: moving the measuring point, lifting the measuring swing rod, and moving a measuring head of the measuring swing rod to the upper end surface of the titanium pipe of the returning cabin to enable the measuring head to be in contact with the upper end surface of the titanium pipe of the returning cabin;

s4: recording the height difference, and recording the height difference according to the dial display of the lever dial indicator;

s5: and symmetrically measuring, replacing a measuring point, and repeating the steps S1 to S4 on the other side of the titanium tube.

Further, the method also comprises the step S6: and further measuring, setting more measuring points, and repeating the steps S1-S4.

Further, in step S2, the zeroing operation is specifically to adjust the bezel to align the 0 line of the index plate with the pointer.

Further, when moving the measuring pendulum rod, the measuring pendulum rod needs to be slowly and lightly moved and cannot be suddenly loosened or lifted.

Further, in step S2, an included angle between the axis of the measuring swing rod and the upper end surface of the service compartment is less than 25 °.

Further, in step S2, when the measuring swing link contacts the measured surface, the lever dial indicator is compressed by a certain amount in advance, so as to ensure that an initial measuring pressing force is formed between the measuring head of the measuring swing link and the measured surface.

The invention has the beneficial effects that:

the invention solves the problem that the gap between the butt joint surfaces of the manned spacecraft cabin sections cannot be measured by providing the measuring tool and the matching method, meets the technical control of the measurement of the key dimension of the butt joint of the manned spacecraft cabin sections, and ensures the smooth operation of the final assembly;

the measuring tool can be used for measuring the height difference under the narrow working condition in the similar space, and the measuring precision can reach 0.01mm.

Drawings

FIG. 1 is a sectional view of a mechanical connection between a return module and a service module according to an embodiment of the present invention;

FIG. 2 is a schematic diagram of a special base according to an embodiment of the present invention;

FIG. 3 is a schematic diagram of a special base according to an embodiment of the present invention;

FIG. 4 is a schematic view of a connecting screw of a special base and a lever dial indicator according to an embodiment of the present invention;

FIG. 5 is a schematic view of a measurement tool according to an embodiment of the present invention;

FIG. 6 is a diagram illustrating a zero position of a dial indicator according to an embodiment of the present invention;

FIG. 7 is a schematic view of a datum level measurement in an embodiment of the present invention;

FIG. 8 is a schematic view of a measurement area in an embodiment of the present invention;

FIG. 9 is a schematic view of measurement of a replacement measurement point according to an embodiment of the present invention;

FIG. 10 is a diagram illustrating an exemplary embodiment of a correct measurement procedure;

FIG. 11 is a schematic diagram illustrating an error measurement method according to an embodiment of the present invention;

FIG. 12 is a schematic diagram of a principle of measurement error in an embodiment of the present invention;

in the figure, 1-returning cabin titanium pipe, 2-first upper end face, 3-service cabin upper end frame and 4-second upper end face.

Detailed Description

In order to make the technical solutions and advantages of the present invention clearer, the technical solutions of the embodiments of the present invention will be fully described below with reference to the accompanying drawings in the present application. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention and are not to be construed as limiting the present invention.

According to the original measuring method, a standard measuring block is used, as shown in figure 1, the surface flatness of the measuring block is attached to the first upper end surface 2 of the titanium pipe 1 of the returning cabin, then a clearance between the measuring block and the second upper end surface 4 of the upper end frame 3 of the service cabin is measured by using a clearance gauge, and the height difference is obtained. Because titanium pipe up end is the annular plane, and the ring width is less than 5mm, and standard gauge block is mostly the rectangle, and is narrow again short with annular plane laminating position when using the gauge block, can't keep stable laminating, needs many times repetition and try, influences and measures the accuracy.

Aiming at the problems, a lever dial indicator is selected to carry out relevant measurement due to the narrow space of a measurement target.

Generally, the lever dial indicator is used for a workpiece on an inspection bench, a special clamping magnetic gauge stand is used, the flatness of a measuring bench is utilized to move the gauge stand, and meanwhile, the workpiece may be ensured to be in a parallel relation with a measuring bench by using a special clamp.

In the assembly process of the large-scale spacecraft, the size, height, measurement position and the like of the spacecraft are not allowed to be carried out by using a special measurement platform. Therefore, in the above situation, the measurement can be performed only by using the structure near the measurement point of the spacecraft as a reference, the plane position size provided by the structure near the measurement point is not standardized, and meanwhile, the protrusion such as a screw and the like which needs to be avoided is required, and the base design is specially performed.

When measuring a plane, the stylus axis should be as parallel as possible to the plane, as shown in FIG. 10; if the approach shown in fig. 11 occurs, a measurement error occurs. Because of the measurement error Δ = a (1-cos a), where a is the reading of the table and a is the angle between the axis of the spindle and the measurement plane; the error is relatively small if the a-angle is small. Therefore, in the case of low requirements, the measurement results at a.ltoreq.15 are considered permissible.

The error generation principle is shown in fig. 12, when the angle exists between the axis of the measuring rod and the surface of the workpiece, the measurement result should be corrected, and it can be known from the figure that when the plane ascending distance is a, the swinging distance of the dial indicator is b, that is, the reading of the dial indicator is b, and since b > a, the indication reading is larger.

Therefore, in order to realize the measurement feasibility and guarantee the precision, the height difference delta h between the upper end surface of the tail end of the titanium pipe and the upper end surface of the service cabin is measured by designing a special base and utilizing the same reference surface near a measurement target, the gap size between the lower end surface of the titanium pipe and the bottom surface of the groove of the butt joint surface of the service cabin is obtained by comparing the height size with the thickness size h1 of the tail end of the titanium pipe and the depth size h2 of the groove of the butt joint surface of the service cabin, and the gap size is judged according to the design requirement value of 0.1mm to make a decision.

The shape of the base may be designed differently in consideration of the size and shape of the reference surface near the measurement target position, and as shown in fig. 2 and 3, the base may have a circular shape, a square shape, a rectangular shape, or the like, and the usable reference surface may be maximized as much as possible. The base and the dial indicator are connected through the connecting mechanism shown in the figure 5, the lever dial indicator is limited in self movement stroke, different heights H are designed for the base in order to guarantee the measurement accuracy of the lever dial indicator, the height difference between a reference surface and a measurement surface, which are attached to the base, on the cabin body is comprehensively analyzed through the height of the base and the size of the dial indicator, the height of the base is obtained, through the design of the height, the fact that the axial line of a measuring swing rod and the measurement surface of the dial indicator are smaller than 15 degrees and are as small as possible is guaranteed, and the measurement accuracy is improved. By means of the shape and height design, the adaptive working condition of the measuring tool is expanded, and the measuring precision is kept.

An example of a specific measurement is as follows:

1. and (5) interface confirmation. The butt joint interface matching is confirmed according to the process design file, and measurement can be implemented;

2. and establishing a benchmark. As shown in fig. 7, the assembled measurement module is placed near the titanium pipe of the return capsule to establish a reference with the upper end face of the service capsule. The measuring rod is slightly pulled, the spherical measuring head is moved to the upper end face, and then the measuring rod is slowly released, so that the measuring head is in contact with the upper end face. The measuring rod is not allowed to be suddenly loosened after being lifted, so that instant impact is easy to generate, and errors are introduced to measurement. The included angle between the measuring rod and the upper end face is smaller than 25 degrees, so that the flexible movement of the measuring head is facilitated, and the indicating value error is reduced. When the measuring head contacts with the step surface, the lever dial indicator is enabled to have a compression amount of 0.4-0.8 mm (namely the pointer has a swinging amount of 0.5-1 circle), initial measuring pressing force between the measuring head and the measured surface is guaranteed, and the stability of indicating value is improved;

3. and setting a zero position. The lever dial indicator is symmetrically graduated, in order to facilitate reading, as shown in fig. 6, a dial ring is adjusted to enable a '0' line of the graduated dial to be aligned with the pointer, then the vicinity of the same position is repeatedly measured for 2-3 times, whether the pointer is still aligned with the '0' line is checked, and if the pointer is not aligned, the pointer is zeroed again;

4. and moving the measuring point. As shown in fig. 8, the lifting measuring rod is slightly pulled, and the spherical measuring head is moved to the upper end surface of the titanium pipe of the returning cabin, so that the side head is contacted with the upper end surface of the titanium pipe. .

5. And recording the step height difference. Reading the value of the lever percentage, for example, the index value of the meter is 0.01mm,1 index is 0.01mm, and if the pointers are aligned 10, the height difference between the end faces is 0.1mm. The co-design validates the data and records the data in the corresponding table.

6. And (4) measuring symmetry. And (4) repeating the steps b, c, d and e to measure the height difference between the end surfaces on the other side of the step surface of the titanium tube as shown in FIG. 9. The height difference measurement between the end surfaces of the other titanium pipe parts is completed by using the same measurement steps;

in the description herein, references to the terms "one embodiment" and "an example" or the like mean that a particular feature, structure, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to be combined in any suitable manner in the relative embodiments or examples.

It should be noted that the above-mentioned embodiments are not intended to limit but only to help understand the core idea of the present invention, and it is obvious for those skilled in the art that any modifications of the present invention and alternatives equivalent to the present product without departing from the principle of the present invention also belong to the protection scope of the present claims.

Claims (8)

1. The utility model provides a manned spacecraft cabin section butt joint face clearance measures frock which characterized in that includes:

the shape of the special base is adapted to the size and the shape of a reference surface of a measurement target position, and the contact area of the special base and the reference surface can be increased;

and the lever dial indicator is arranged on the special base.

2. The tool according to claim 1, wherein the height of the special base meets the following conditions:

after the lever dial indicator is installed on the special base, when a measuring swing rod of the lever dial indicator is placed on a measuring surface, an included angle between the axis of the measuring swing rod and the measuring surface is smaller than 15 degrees.

3. A manned spacecraft cabin section butt joint surface gap measuring method is characterized by comprising the following steps:

s1: establishing a reference, and placing the manned spacecraft cabin section butt joint surface gap measuring tool according to any one of claims 1-2 near a titanium pipe of a return cabin, so that a measuring swing rod of the lever dial indicator can contact the upper end surface of a service cabin;

s2: setting a zero position, namely placing the measuring swing rod on the upper end face of the service cabin, resetting the lever dial indicator to zero, repeatedly measuring the same position and the nearby position of the upper end face of the service cabin, checking whether the display number of the lever dial indicator is zero, entering the next step after zero setting, and resetting the zero again if the display number is not zero;

s3: moving the measuring point, lifting the measuring swing rod, and moving a measuring head of the measuring swing rod to the upper end surface of the titanium pipe of the returning cabin to enable the measuring head to be in contact with the upper end surface of the titanium pipe of the returning cabin;

s4: recording the height difference, and recording the height difference according to the dial display of the lever dial indicator;

s5: and (4) symmetrically measuring, replacing a measuring point, and repeating the steps S1 to S4 on the other side of the titanium tube.

4. The method according to claim 3, further comprising step S6: and (5) further measuring, setting more measuring points and repeating the steps S1-S4.

5. A method according to claim 3, characterized in that in step S2 the zeroing operation is carried out by adjusting the bezel so that the 0 line of the graduated disk is aligned with the pointer.

6. A method according to claim 3, characterized in that the measuring pendulum is moved slowly without sudden release or lifting.

7. A method according to claim 3, characterized in that in step S2 the angle of the measuring pendulum axis to the upper end surface of the service bay is less than 25 °.

8. The method according to claim 3, characterized in that in step S2, when the measuring swing rod is contacted with the surface to be measured, the lever dial indicator is compressed in advance by a certain amount, so that an initial measuring pressing force is ensured between a measuring head of the measuring swing rod and the surface to be measured.

Images