Method for determining length of flexible rope of forced releasing device of spacecraft electric connector and measuring tool

Abstract

The invention relates to the technical field of spacecraft general assembly, in particular to a spacecraft electric connector forced release device flexible rope length determination method and a measurement tool, the measurement tool comprises a base and a distance measurement rod, and the base is provided with a reference plane; one end of the distance measuring rod is connected with the base, the other end of the distance measuring rod is used for being connected with the separating plug, and the distance measuring rod is perpendicular to the reference plane and can stretch in the length direction of the distance measuring rod to enable the reference plane to abut against the lander platform. During measurement, the other end of the distance measuring rod is connected with the separation plug, the distance measuring rod stretches out and draws back in the length direction of the distance measuring rod so that the reference plane can abut against the lander platform, and the sum of the measured length of the distance measuring rod and the height of the base is the distance between the separation plug and the lander platform at the moment. The measuring tool is easy to operate and high in reliability, the measuring difficulty is greatly simplified, and the accuracy of a measuring result is improved. Measurement can be completed only once, time loss caused by multiple times and multiple items of satellite measurement is avoided, and the inspection efficiency is improved.

Description

Technical Field

[0001] This application relates to the technical field of spacecraft general assembly, and particularly to a method for determining the length of a flexible rope of a strong detachment device for a spacecraft electrical connector and a measuring tooling. Background Art

[0002] The function of the electrical connector is to achieve electrical connection between the ascender and other spacecraft components (such as the lander, etc.), including transmitting electric energy, signals, etc., to ensure normal communication and collaborative work between components. For example, transmitting the control signal on the lander to the ascender, or feeding back the status information of the ascender to the lander, etc.

[0003] The pin puller is mainly used to unlock and separate the connection parts between the lander and other related components (such as the ascender, etc.). For example, after completing the lunar mission, the lander and the ascender need to be separated, and the pin puller will play a role in pulling out the pin connecting the two to achieve mechanical unlocking and create conditions for the takeoff of the ascender.

[0004] The puller is connected to the separation plug of the electrical connector by a rope assembly, and the spacecraft inter - connector strong detachment device usually has very high precision requirements for the length of the rope. A tiny length error may affect the normal separation and docking of the electrical connector, and further affect the success or failure of the entire spacecraft mission. Summary of the Invention

[0005] This application provides a method for determining the length of a flexible rope of a strong detachment device for a spacecraft electrical connector and a measuring tooling, aiming to solve the problem that it is difficult to determine the length of the rope in the strong detachment device of the spacecraft inter - connector in the prior art.

[0006] On the one hand, this application provides a measuring tooling, including:

[0007] A base with a reference plane;

[0008] A ranging rod, one end of which is connected to the base, and the other end is used to connect to the separation plug. The ranging rod is perpendicular to the reference plane, and the ranging rod can make the reference plane abut against the lander platform by telescoping along its own length direction.

[0009] In a possible design, a positioning groove is provided at the end of the ranging rod far from the base. The inner wall of the positioning groove is in clearance fit with the outer wall of the pin rod of the separation plug, and a positioning hole is provided on the side wall of the positioning groove. The tooling further includes a positioning shaft that can pass through the positioning hole and the pin hole of the pin rod of the separation plug.

[0010] In a possible design, an equal - height plane is formed on the outer surface of the positioning groove. The equal - height plane is perpendicular to the ranging rod, and the axis of the positioning hole is within the equal - height plane.

[0011] In a possible design, the distance between the inner bottom wall of the positioning groove and the axis of the positioning hole is equal to the distance between the end face of the pin rod and the axis of the pin hole.

[0012] In a possible design, the ranging rod and the base are coaxially connected through a telescopic structure.

[0013] In a possible design, the ranging rod and the base are coaxially connected through a threaded structure.

[0014] In a possible design, the ranging rod includes a first vertical rod and a second vertical rod. The first vertical rod is connected to the base, and the second vertical rod is used to connect to the separating plug. The first vertical rod and the second vertical rod are coaxially connected through a telescopic structure.

[0015] In a possible design, the first vertical rod and the second vertical rod are coaxially connected through a threaded structure.

[0016] In a possible design, scales are arranged along the length direction of the ranging rod.

[0017] In a possible design, the end of the positioning shaft is formed with a tip with a gradually decreasing diameter.

[0018] In a possible design, the base is in a plate-like structure, and the plane where the lower end face of the base is located is the reference plane.

[0019] In a possible design, a notch is formed in the side wall of the positioning groove.

[0020] On the other hand, the present application also provides a method for determining the length of the flexible rope of the strong disconnection device of the spacecraft electrical connector. Using the measuring tooling described above, the method includes:

[0021] Obtain the distance between the lander platform and the separating plug through the measuring tooling;

[0022] Obtain the length of the flexible rope according to the distance.

[0023] The beneficial effects of the present application are as follows:

[0024] The measuring tooling of the present application is provided with a base and a ranging rod. One end of the ranging rod is connected to the base, and the length direction of the ranging rod is perpendicular to the reference plane of the base. During measurement, the other end of the ranging rod is connected to the separation plug. By telescoping the ranging rod along its own length direction, the reference plane is made to abut against the lander platform. At this time, the sum of the length of the ranging rod and the height of the base is the distance between the separation plug and the lander platform. This measuring tooling is easy to operate and has strong reliability, greatly simplifying the measurement difficulty and improving the accuracy of the measurement results. In particular, after using this tooling for measurement, the measurement can be completed only once, avoiding the time loss caused by multiple on-orbit measurements, and improving the inspection efficiency. At the same time, the application of this tooling reduces the measurement errors caused by on-orbit operations and inappropriate tools, ensures the accuracy and effectiveness of the measurement results, makes up for the deficiency of this key quality control measure due to the lack of measurement means, and thus ensures the smooth progress of the satellite assembly work.

[0025] The method for determining the length of the flexible rope of the strong disconnection device of the spacecraft electrical connector provided by the present application includes the above-mentioned all advantages of the measuring tooling because it includes the measuring tooling of the present application. Brief Description of the Drawings

[0026] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings required to be used in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0027] Figure 1 It is a schematic structural diagram of the measuring tooling provided by the embodiment of the present application;

[0028] Figure 2 It is a side view of the measuring tooling provided by the embodiment of the present application;

[0029] Figure 3 It is a schematic structural diagram of the upper end part of the measuring tooling provided by the embodiment of the present application;

[0030] Figure 4 It is a schematic diagram of the installation position of the ascender electrical connector relative to the lander platform;

[0031] Figure 5 It is a principle illustration diagram of the method for determining the length of the flexible rope of the strong disconnection device of the spacecraft electrical connector provided by the embodiment of the present application.

[0032] Reference Signs:

[0033] 100. Base; 110. Reference plane; 120. Adjusting nut; 200. Distance measuring rod; 210. Positioning groove; 220. Positioning hole; 230. Equal height plane; 240. Notch; 300. Positioning shaft; 400. Lander platform; 500. Pin extractor; 600. Sleeve; 700. Flexible rope; 800. Adapter ring; 900. Separation plug; 910. Pin rod; 920. Pin hole. Detailed implementation mode

[0034] The technical solutions of the present application will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts belong to the scope of protection of the present application.

[0035] The following combines Figures 1 - 5 to describe the measuring tool provided in the embodiments of the present application.

[0036] Refer to Figure 4 As shown, the structure and layout of the spacecraft are complex, and the installation position of the ascender electrical connector relative to the lander platform 400 is in a narrow and inaccessible space position, which brings great inconvenience to the measurement operation of the height of the ascender electrical connector relative to the lander platform 400. To solve the above problems, the embodiments of the present application provide a measuring tool for measuring the height of the ascender electrical connector relative to the lander platform 400.

[0037] Refer to Figure 1 , Figure 2 , Figure 3 As shown, the measuring tool provided in the embodiments of the present application includes a base 100 and a distance measuring rod 200. The base 100 has a plate-like structure with an upper end face and a lower end face arranged opposite to each other. The lower end face is a reference plane 110, and the reference plane 110 is used to abut against the lander platform 400.

[0038] The lower end of the distance measuring rod 200 is connected to the base 100. The distance measuring rod 200 is perpendicular to the reference plane 110. During measurement, the upper end of the distance measuring rod 200 is connected to the separation plug 900. The distance measuring rod 200 can be telescoped along its own length direction to make the reference plane 110 abut against the lander platform 400, and keep the length of the distance measuring rod 200 unchanged after telescoping. Disconnect the connection between the distance measuring rod 200 and the separation plug 900, and measure the length of the distance measuring rod 200 at this time. The sum of the length of the distance measuring rod 200 at this time and the thickness of the base 100 is the height of the ascender electrical connector relative to the lander platform 400.

[0039] In some embodiments provided by the present application, a positioning groove 210 is formed at one end of the ranging rod 200 away from the base 100. The notch of the positioning groove 210 faces the end face of the ranging rod 200. During measurement, the notch of the positioning groove 210 faces the separating plug 900, so that the pin rod 910 of the separating plug 900 enters the positioning groove 210, and the inner wall of the positioning groove 210 is in clearance fit with the outer wall of the pin rod 910 of the separating plug 900. Two positioning holes 220 are symmetrically formed in the left and right side walls of the positioning groove 210. The tooling further includes a positioning shaft 300. During measurement, the positioning shaft 300 is sequentially passed through the left positioning hole 220, the pin hole 920 of the pin rod 910 of the separating plug 900, and the right positioning hole 220. The outer wall of the positioning shaft 300 is in clearance fit with the inner walls of the pin hole 920 and the positioning hole 220 respectively, so that the axis of the positioning shaft 300 is collinear with the center line of the pin hole 920 of the pin rod 910. In this way, the positioning shaft 300 can prevent relative rotation in the horizontal direction between the ranging rod 200 and the pin rod 910, and improve the measurement accuracy. In some of these embodiments, an equal-height plane 230 is formed on the outer surface of the positioning groove 210. The equal-height plane 230 is perpendicular to the ranging rod 200, and the axis of the positioning hole 220 is within the equal-height plane 230. By measuring the distance between the equal-height plane 230 and the reference plane 110, the height of the center line of the pin hole 920 of the pin rod 910 relative to the lander platform 400 can be obtained.

[0040] In some specific embodiments, the end of the positioning shaft 300 is formed with a tip with a gradually decreasing diameter. This is beneficial to enable the positioning shaft 300 to pass through the pin hole 920 of the pin rod 910.

[0041] In some specific embodiments, a notch 240 is formed in the side wall of the positioning groove 210. By forming the notch 240 in the side wall of the positioning groove 210, the internal pin rod 910 can be visualized, which is beneficial to align the pin hole 920 with the positioning hole 220 and facilitate the positioning shaft 300 to quickly pass through the pin hole 920 of the pin rod 910.

[0042] In some specific embodiments, the distance between the inner bottom wall of the positioning groove 210 and the axis of the positioning hole 220 is equal to the distance between the end face of the pin rod 910 and the axis of the pin hole 920. In this way, during measurement, the end face of the pin rod 910 can abut against the inner bottom wall of the positioning groove 210, which can prevent relative rotation in the vertical direction between the ranging rod 200 and the pin rod 910, and improve the measurement accuracy.

[0043] In some of the specific embodiments, the ranging rod 200 is coaxially connected to the base 100 through a threaded structure. Specifically, an internal threaded hole is provided in the base 100, and an adjusting nut 120 is coaxially welded to the end face of the internal threaded hole. The lower end of the ranging rod 200 is provided with an external thread, and the ranging rod 200 is threadedly connected to the internal threaded hole. By rotating the base 100, the length of the ranging rod 200 located outside the base 100 can be adjusted.

[0044] In some of the specific embodiments, the ranging rod 200 includes a first vertical rod and a second vertical rod. The first vertical rod is connected to the base 100, and the first vertical rod and the second vertical rod are coaxially connected through a telescopic structure. In some embodiments, the first vertical rod and the second vertical rod are coaxially connected through a threaded structure. For example, an external thread is provided at the upper end of the first vertical rod, and a cylindrical groove is provided at the lower end of the second vertical rod. The inner wall of the cylindrical groove is provided with an internal thread that cooperates with the external thread. By rotating the first vertical rod, the total length of the first vertical rod and the second vertical rod can be adjusted. In other embodiments, the telescopic structure can also adopt a sliding sleeve type telescopic structure or a pneumatic type telescopic structure, etc. During measurement, the positioning groove 210 at the upper end of the second vertical rod is connected to the pin rod 910 of the separation plug 900 through the positioning shaft 300. By rotating the first vertical rod, the total length of the first vertical rod and the second vertical rod can be adjusted until the reference plane 110 of the base 100 abuts against the lander platform 400. Keep the lengths of the first vertical rod and the second vertical rod unchanged after adjustment, and disconnect the first vertical rod from the separation plug 900. At this time, the sum of the total length of the first vertical rod and the second vertical rod and the thickness of the base 100 is the height of the ascender electrical connector relative to the lander platform 400.

[0045] In some of the specific embodiments, scales are provided on the ranging rod 200 along its length direction. After adjusting the length of the ranging rod 200 so that the reference plane 110 abuts against the lander platform 400, the length of the ranging rod 200 located outside the base 100 can be obtained through the scale reading of the ranging rod 200. In some of the specific embodiments, a first scale is provided on the first vertical rod along its length direction, and the position of the zero graduation line of the first scale corresponds to the position of the equal height plane 230. A second scale is provided on the second vertical rod along its length direction, and the position of the zero graduation line of the second scale corresponds to the upper end face position of the base 100. Thus, after adjusting the total length of the first vertical rod and the second vertical rod so that the reference plane 110 abuts against the lander platform 400, the total length of the first vertical rod and the second vertical rod can be directly obtained through the first scale and the second scale.

[0046] In the embodiments of the present application, a method for determining the length of the flexible rope 700 of a strong disconnection device for a spacecraft electrical connector is also provided. Using the measuring tooling provided in the above embodiments, the method includes:

[0047] The distance between the lander platform 400 and the separation plug 900 is obtained through a measuring tooling, specifically as follows: The positioning groove 210 at the upper end of the ranging rod 200 is sleeved on the pin rod 910 of the separation plug 900, and the positioning shaft 300 passes through the positioning hole 220 and the pin hole 920 of the pin rod 910, so that the ranging rod 200 is connected to the pin rod 910 of the separation plug 900. Rotate the base 100 to adjust the length of the ranging rod 200 outside the base 100 until the reference plane 110 of the base 100 abuts against the lander platform 400. Keep the length of the ranging rod 200 after adjustment unchanged. The actual length of the ranging rod 200 outside the base 100 can be obtained through the scale reading of the ranging rod 200. Finally, the sum of the actual length of the ranging rod 200 outside the base 100 and the thickness of the base 100 is the height of the center of the pin hole 920 of the pin rod 910 of the ascender electrical connector relative to the lander platform 400.

[0048] The length of the flexible rope 700 is obtained according to the distance. Specifically, the length of the flexible rope 700 is obtained according to the distance between the center of the pin hole 920 and the lander platform 400.

[0049] Refer to Figure 5 As shown, the pin puller 500 is installed on the landing platform, and the pin puller 500 is connected to the screw sleeve 600. The electrical connector is installed on the ascender. The electrical connector includes a separation plug 900 and a socket. The screw rod of the separation plug 900 is connected to the adapter ring 800 through a pin shaft, and the adapter ring 800 and the screw sleeve 600 are connected through a flexible rope 700.

[0050] The distance from the center of the pin hole 920 at the tail of the pin rod 910 to the lander platform 400 is L1, the length of the flexible rope 700 is L2, and the slack of the flexible rope 700 is designed as a constant a according to the spacing of the forced disconnection device and the characteristics of the flexible rope 700. Specifically, a is equal to 12 mm; the distance from the end of the screw sleeve 600 to the lander platform 400 is a constant b. Specifically, b is equal to 86.5 mm; the length of the adapter ring 800 is a constant c. Specifically, the length of the adapter ring 800 is 19 mm. Then, the length of the flexible rope 700 can be calculated by the following formula:

[0051] L2 = L1 + a - b - c;

[0052] In some specific embodiments, L2 = (L1 + 12 - 86.5 - 19) mm.

[0053] It should be noted that the method for determining the length of the flexible rope 700 of the forced disconnection device of the spacecraft electrical connector includes the measuring tooling, and thus includes all the above advantages of the measuring tooling, which will not be elaborated here.

[0054] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0055] In addition, the terms "first" and "second" are only used for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present application, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically and clearly defined.

[0056] In the present application, unless otherwise clearly specified and limited, the terms "mounted", "connected", "coupled", "fixed", etc. shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0057] In the present application, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0058] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as a limitation to the present application. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present application.

Claims

1. A measuring tooling, characterized in that, Comprising: A base with a reference plane; A ranging rod, one end of which is connected to the base and the other end is used to connect to a separation plug. The ranging rod is perpendicular to the reference plane, and the ranging rod can make the reference plane abut against the lander platform by telescoping along its own length direction.

2. The measuring tooling according to claim 1, characterized in that: A positioning groove is formed at one end of the ranging rod away from the base. The inner wall of the positioning groove is used for clearance fit with the outer wall of the pin rod of the separation plug. A positioning hole is formed in the side wall of the positioning groove. The tooling further includes a positioning shaft, and the positioning shaft can pass through the positioning hole and the pin hole of the pin rod of the separation plug.

3. The measuring tooling according to claim 2, wherein: An equal-height plane is formed on the outer surface of the positioning groove. The equal-height plane is perpendicular to the ranging rod, and the axis of the positioning hole is within the equal-height plane.

4. The measuring tooling according to claim 3, wherein: The distance between the inner bottom wall of the positioning groove and the axis of the positioning hole is equal to the distance between the end face of the pin rod and the axis of the pin hole.

5. The measuring tooling according to any one of claims 1-4, characterized in that: The ranging rod and the base are coaxially connected through a telescopic structure.

6. The measuring tooling according to claim 5, characterized in that: The ranging rod and the base are coaxially connected through a threaded structure.

7. The measuring tooling according to claim 6, wherein: Scales are arranged on the ranging rod along its length direction.

8. The measuring tooling according to claim 2, wherein: The end of the positioning shaft is formed with a tip with a gradually decreasing diameter.

9. The measuring tooling according to claim 2, wherein: A notch is formed in the side wall of the positioning groove.

10. A method for determining the length of a flexible rope of a strong disconnection device for a spacecraft electrical connector, characterized in that, Using the measuring tooling according to any one of claims 1-9, the method includes: Obtaining the distance between the lander platform and the separation plug through the measuring tooling; Obtaining the length of the flexible rope according to the distance.

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