CN219554029U - Space electric connector drop plug storage device - Google Patents

Abstract

The utility model provides a space electric connector drop plug storage device, which comprises a storage box (500), a pull rope assembly (600) and an elastic assembly (800), wherein a first end of the pull rope assembly (600) is connected with a plug (400), a second end of the pull rope assembly is fixed on a bracket (700), a first end of the elastic assembly (800) is pressed on the plug (400), and a second end of the elastic assembly is fixed on the storage box (500); when the plug (400) is electrically connected with the socket (300) corresponding to the plug (400), the elastic component (800) is in a tension state; after the plug (400) is separated from the socket (300) corresponding to the plug (400), the elastic component (800) is restored to a natural state or tends to the natural state, and the plug (400) is positioned in the storage box (500). The space electric connector falling plug storage device can avoid the damage to the spacecraft caused by collision between the moving part plug (400) and other stand-alone equipment or structures of the spacecraft, and reduce disturbance factors of the on-orbit stability of the spacecraft.

Description

Space electric connector drop plug storage device

Technical Field

The utility model mainly relates to the technical field of aerospace application structures, in particular to a plug containing device for an aerospace electric connector.

Background

With the continuous development of the aerospace technology and the diversification of the requirements of aerospace tasks, various spacecrafts are generated. In the field of aerospace technology, there are two main types of connection and disconnection of a spacecraft, one type is mechanical connection and disconnection, and the other type is electrical connection and disconnection, which are not necessarily accompanied by electrical connection and disconnection, but are generally accompanied by mechanical connection and disconnection. Whether electrical connection and disconnection are needed or not depends mainly on whether the initial energy source meets the power consumption requirement of the spacecraft in the earlier stage before the spacecraft solar cell array supplies energy.

The existing spacecraft electrical connection and separation is mainly applied between a carrier rocket and a satellite or between satellites, and most of the existing spacecraft electrical connection and separation is on connection of the carrier rocket and the satellite. The carrier rocket supplies power to the satellite through the umbilical cable, and the power consumption requirement of the satellite in the early stage of orbit entering is met. After the satellite is in orbit, the electrical connector in the middle of the umbilical cable is disconnected. The electric connector is widely applied to occasions needing electric connection in the aerospace field, is an important device for supplying energy between a carrier rocket and a satellite or between satellites, and even can influence the realization of functions of a spacecraft.

In the application of separating the satellite from the carrier rocket, the carrier rocket is separated from the satellite at the moment, the carrier rocket belongs to the end of life, the electric connector falling plug is arranged at the carrier end, the electric connector socket is fixed at the satellite end, and the satellite generally does not face the problem of collision or free movement of the electric connector falling plug under the condition. With the increasing complexity of space missions and the increasing diversification of mission requirements, in the application of separating satellites from satellites, the satellites are serially transmitted, particularly, under the condition that the combination of large satellites and small satellites is transferred to a high orbit, the small satellites are required to be powered by the large satellites, one of the two satellites is inevitably faced with the problem of collision or free movement of an electrical connector falling plug, the stability of the attitude of the satellites is easy to interfere, the damage of the spacecraft is also caused, and the influence on high-precision remote sensing satellites is particularly large.

Disclosure of Invention

The utility model aims to solve the technical problem of providing a space electric connector drop plug storage device, which can avoid the damage to a spacecraft caused by collision between a moving part plug and other stand-alone equipment or structures of the spacecraft and reduce disturbance factors of the on-orbit stability of the spacecraft.

In order to solve the technical problems, the utility model provides a space electric connector falling plug containing device, comprising: the device comprises a storage box, a pull rope assembly and an elastic assembly, wherein the first end of the pull rope assembly is connected with a plug, the second end of the pull rope assembly is fixed on a bracket, the first end of the elastic assembly is pressed on the plug, and the second end of the elastic assembly is fixed on the storage box; when the plug is connected with the corresponding socket, the elastic component is in a tension state; after the plug is separated from the corresponding socket, the elastic component is restored to a natural state or tends to the natural state, and the plug is positioned in the storage box.

Optionally, the storage box comprises a first member and a second member, and the first member and the second member are combined into the storage box.

Optionally, the cross section of the storage box formed by combining the first member and the second member is hexagonal, cylindrical or square.

Optionally, the side surface of the storage box is provided with a plurality of through holes.

Optionally, the elastic component is a leaf spring.

Optionally, the elastic component comprises a first leaf spring, a second leaf spring and a third leaf spring, wherein a first end of each leaf spring is fixed on the storage box, and a second end is pressed on the plug.

Optionally, the pull rope assembly comprises a steel wire rope, a first end of the steel wire rope is connected with the screw rod, and a second end of the steel wire rope is connected with the plug.

Optionally, the second end of the wire rope is connected to the plug via a cotter pin and a hole cap.

Optionally, the screw is fixed to the first structure by the bracket.

Compared with the prior art, the utility model has the following advantages: the first end of the pull rope assembly is connected with the plug, the second end of the pull rope assembly is fixed on the bracket, and the first end of the elastic assembly is connected with the plug, and the second end of the elastic assembly is fixed on the storage box; when the plug is electrically connected with the corresponding socket, the elastic component is in a tension state, after the plug is separated from the corresponding socket, the elastic component is restored to a natural state or tends to the natural state, and the plug is positioned in the storage box, so that the motion constraint after the plug is separated is realized, further, the damage to the spacecraft caused by collision of the plug of the moving part with other stand-alone equipment or structures of the spacecraft is avoided, and the disturbance factors of the on-orbit stability of the spacecraft are eliminated.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the principles of the utility model. In the accompanying drawings:

FIG. 1 is a schematic view of a space electrical connector drop-out plug receptacle according to an embodiment of the present utility model;

FIG. 2 is an internal display view of a space electrical connector drop-out plug receiving device according to one embodiment of the present utility model;

FIG. 3 is a schematic view showing bending angles of a leaf spring under different states according to an embodiment of the present utility model;

FIG. 4 is a schematic diagram of a pull cord assembly according to an embodiment of the present utility model;

FIG. 5 is a schematic diagram showing the effect of the space electric connector according to an embodiment of the present utility model after the plug and socket are separated;

fig. 6 is an internal display view of an embodiment of the present utility model with a plug and socket of the space electrical connector separated.

The reference numerals in the drawings respectively indicate:

100-a first structure;

200-a second structure;

300-socket;

400-plug;

500-a storage box; 501-a first component; 502-a second component; 503-a through hole;

600-a pull cord assembly; 601-a steel wire rope; 602-screw; 603-hole cap; 604-cotter pin;

700-bracket;

800-an elastic component; 801-a first leaf spring; 802-a second leaf spring; 803-third leaf spring.

Detailed Description

In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are used in the description of the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some examples or embodiments of the present utility model, and it is apparent to those of ordinary skill in the art that the present utility model may be applied to other similar situations according to the drawings without inventive effort. Unless otherwise apparent from the context of the language or otherwise specified, like reference numerals in the figures refer to like structures or operations.

As used in the specification and in the claims, the terms "a," "an," "the," and/or "the" are not specific to a singular, but may include a plurality, unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that the steps and elements are explicitly identified, and they do not constitute an exclusive list, as other steps or elements may be included in a method or apparatus.

The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present utility model unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.

In the description of the present utility model, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present utility model and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present utility model; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present utility model. Furthermore, although terms used in the present utility model are selected from publicly known and commonly used terms, some terms mentioned in the present specification may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Furthermore, it is required that the present utility model is understood, not simply by the actual terms used but by the meaning of each term lying within.

It will be understood that when an element is referred to as being "on," "connected to," "coupled to," or "contacting" another element, it can be directly on, connected or coupled to, or contacting the other element or intervening elements may be present. In contrast, when an element is referred to as being "directly on," "directly connected to," "directly coupled to," or "directly contacting" another element, there are no intervening elements present. Likewise, when a first element is referred to as being "electrically contacted" or "electrically coupled" to a second element, there are electrical paths between the first element and the second element that allow current to flow. The electrical path may include a capacitor, a coupled inductor, and/or other components that allow current to flow even without direct contact between conductive components.

Example 1

Fig. 1 is a schematic structural view of an embodiment of a space electric connector drop plug receiving device according to the present utility model, and fig. 2 is an internal display view of an embodiment of a space electric connector drop plug receiving device according to the present utility model, referring to fig. 1 and fig. 2, the structure of the embodiment mainly includes: the storage box 500, the pull rope assembly 600 and the elastic assembly 800, wherein the first end of the pull rope assembly 600 is connected with the plug 400, the second end of the pull rope assembly 600 is fixed on the bracket 700, the first end of the elastic assembly 800 is pressed on the plug 400, and the second end of the elastic assembly is fixed on the storage box 500. In this embodiment, the first end of the elastic member 800 is pressed against the plug 400 in a broad sense, that is, the first end of the elastic member 800 is in close contact with the plug 400. When the plug 400 is connected to the corresponding socket 300, the elastic member 800 is in a tension state, and after the plug 400 is separated from the corresponding socket 300, the elastic member 800 is restored to a natural state or is inclined to a natural state, and the plug 400 is in the storage case 500.

In the double star (double satellite) structure, the storage case 500 is fixed to the lower surface of the first structure 100 by screws, the first structure 100 generally refers to a fixing member such as a fixing surface or a fixing plate on a satellite, and the storage case 500 can be fixed thereto, the socket 300 generally refers to a fixing member such as a fixing surface or a fixing plate on a satellite, and the second structure 200 generally refers to a fixing member such as a fixing surface or a fixing plate on a satellite, and the socket 300 can be fixed thereto. When the storage box 500 is not provided, after the plug 400 is separated from the socket 300, the plug 400 flies away from the socket 300 under the action of elastic force, and the flying-away direction has uncertainty and is easy to collide with a single device or other structures near the lower surface of the first structural body 100, so that the damage of the spacecraft is caused, and even the normal function of the spacecraft is affected. In contrast, after the storage box 500 is provided, after the plug 400 is separated from the socket 300, the flying-away space is limited by the storage box 500, and the elastic component 800 needs to be restored to the natural state or inclined to the natural state, so that the plug 400 is controlled to move along with the restoration of the elastic component 800 under the action of the elastic component 800, and finally is positioned in the storage box 500. The plug 400 cannot collide with other stand-alone devices or structures under the surrounding of the storage box 500, so that the occurrence of damage to the spacecraft is reduced.

In some embodiments, the case 500 includes a first member 501 and a second member 502, the first member 501 and the second member 502 combined into the case 500. The storage box 500 may be designed as a single integral structure, which can also realize the storage function of the plug 400 in the present embodiment, but is disadvantageous for installation and maintenance of the plug 400 or the space electric connector, so in the present embodiment, the storage box 500 may be designed as a combination of two members to overcome the above-mentioned disadvantages of the integral structure. The first member 501 and the second member 502 may be combined or spliced in a manner that a clamping groove is formed on the first member 501, a corresponding buckle is formed on the second member 502, and a clamping groove buckle structure is adopted to splice the first member 501 and the second member 502, or the first member 501 and the second member 502 may be spliced in a screw-nut manner, which is not limited to the structure of the embodiment, and the splice between the first member 501 and the second member 502 may be other manners, which are not specifically listed herein. Of course, the storage box 500 may be formed by combining not only two members but also more members, such as 3 members, 4 members, etc. The storage box 500 formed by combining more components is not more prominent than the storage box 500 formed by combining only 2 components in terms of functions, but the complexity of connecting devices is additionally increased, so that the storage box 500 formed by combining 2 components is generally selected. In this embodiment, the first member 501 and the second member 502 may be combined into a hexagonal storage box 500 by screws and nuts, the storage box 500 is fixed on the lower surface of the first structural body 100 by screws, and the first structural body 100 generally refers to a fixing piece such as a fixing surface or a fixing plate on a satellite, and may be used to fix the storage box 500 thereon. More preferably, the first member 501 and the second member 502 may be arc-shaped members or polygonal members, and the cross section of the storage box 500 formed by combining them is hexagonal, cylindrical or square, etc., and may be determined according to practical requirements, and is not limited herein.

In some embodiments, the side of the case 500 has a plurality of through holes 503. Whether the side surface of the storage box 500 has the through hole 503 does not affect the storage box 500 to realize the storage function of the plug 400, but if the side surface of the storage box 500 has the through hole 503, the material consumption of the storage box 500 can be reduced on the premise that the storage function of the storage box 500 is not affected, the weight of the whole space electric connector falling-off plug storage device can be reduced, and the production cost is reduced. In addition, the through hole 503 may allow the inside of the storage case 500 to be directly observed from the outside without detaching the storage case 500. More preferably, the through hole 503 on the side of the storage case 500 is generally square or circular in shape for ease of manufacturing and molding. Further, the through holes 503 may be uniformly distributed on the surface of the receiving box 500.

In some embodiments, the resilient assembly 800 is a leaf spring (or leaf spring). Leaf springs are widely used in electrical contact devices, and the most used are straight cantilever leaf springs of the simplest shape. Leaf springs are one of the simplest springs that utilize the deformation of a resilient metal sheet to create a spring characteristic. The elastic metal sheet has rectangle, trapezoid and triangle, and can also be straight sheet or bent sheet, and is generally used in places with small load and deformation and low rigidity requirement, such as sensitive elements, elastic support or positioning devices in instruments, meters and automation mechanisms. The leaf spring is characterized by being easily bendable in one direction only and having a large tensile stiffness and bending stiffness in the other direction, and therefore, the leaf spring is well suited for use as a sensing element, elastic support, positioning means, flexible connection, etc. in a test meter or an automatic device.

Further, the elastic assembly 800 may include a first leaf spring 801, a second leaf spring 802, and a third leaf spring 803, each of which has a first end fixed to the receiving box 500 and a second end pressed against the plug 400. For example, the first leaf spring 801 is fixed to the middle of the first member 501 by a screw nut, and the second leaf spring 802 and the third leaf spring 803 are fixed to both sides of the second member 502 by screw nuts, respectively. To ensure that the leaf spring can be more securely fastened to the housing 500, the first end of the leaf spring may be designed to be elongated and two or more screws may be used to secure the leaf spring to the housing 500. The second ends of the 3 leaf springs contact and enclose the plug 400, and the first leaf spring 801, the second leaf spring 802, and the third leaf spring 803 contact and are in tension with the plug 400 when the housing 500 is mounted. Fig. 3 is a schematic diagram showing bending angles of the leaf spring in different states according to an embodiment of the present utility model, referring to fig. 3, a state S1 shows that the leaf spring is in a natural state, without tension, and has an angle of 130 °, a state S2 shows that the leaf spring is in a first compression state, and has an angle of 140 °, a state S3 shows that the leaf spring is in a second compression state, and has an angle of 130 °, wherein the leaf spring tension of the state S2 is smaller than the leaf spring tension of the state S3. It can be seen that after the plug 400 is connected to the socket 300, the leaf spring is in the state S3, where the tension of the leaf spring is relatively large, and when the plug 400 is disconnected from the socket 300, the leaf spring is necessarily restored to the natural state. Depending on the configuration of the aerospace electrical connector and the size of the interior of the housing 500, the extent to which the leaf springs return to their natural state varies. For example, if the internal space of the storage case 500 is large, the leaf spring may return to the state S1, that is, to a natural state, completely eliminating the tension; if the internal space of the storage case 500 is small, the leaf spring cannot be completely restored to the natural state, which may be restored to the state shown in state S2, and the leaf spring does not completely remove the tension at this time, but reduces the tension effect. In short, after the plug 400 is separated from the socket 300, the first leaf spring 801, the second leaf spring 802 and the third leaf spring 803 cooperate to control the plug 400 to enter the storage box 500, and the storage effect can be referred to in fig. 5 and 6.

It will be appreciated by those skilled in the art that the number of leaf springs in the present embodiment may be not limited to the form of only three leaf springs of the first leaf spring 801, the second leaf spring 802 and the third leaf spring 803, but may be 2, 4 or other leaf spring numbers, as long as the function of controlling the plug 400 to enter the storage box 500 can be achieved, and no specific limitation is made on the number of leaf springs.

In some embodiments, the plug 400 is also connected to a pull cord assembly 600, the pull cord assembly 600 being used to pull the plug 400. In general, the pull rope assembly 600 is initially in a loose state, and in the process of separating the first structural body 100 from the second structural body 200 under the condition that the electrical separation of the aerospace electrical connector fails, the tail of the plug 400 of the aerospace electrical connector can be slowly pulled by the pull rope assembly 600 until the pulling force is greater than the threshold force required by the mechanical separation of the aerospace electrical connector. After the plug 400 is separated from the socket 300, the first leaf spring 801, the second leaf spring 802 and the third leaf spring 803 are gradually bent upwards under the action of self elastic force until the plug 400 is tightly fastened, and the plug 400 moves upwards to the lower surface of the first structural body 100 under the action of elastic force and enters the storage box 500, so that other stand-alone devices or structures are prevented from being collided.

In some embodiments, as shown in fig. 4, the pull-cord assembly 600 includes a wire rope 601, a first end of the wire rope 601 being attached to a screw 602, and a second end being attached to the plug 400. Further, the second end of the cable 601 is connected to the plug 400 via cotter pin 604 and hole cap 603. Wherein, screw 602 can be a cylindrical screw, hole cap 603 can be a cylindrical cap, and the first end and the second end of wire rope 601 are respectively crimped on the cylindrical screw at the top and the cylindrical cap at the bottom.

In some embodiments, to better secure the screw 602, the screw 602 is secured to the first structure 100 by the bracket 700. The tail of the plug 400 is connected with the steel wire rope 601, the screw 602 can be fixed on the bracket 700 through a nut, and the bracket 700 can be a square bracket or other brackets, and is not particularly limited herein. In the present embodiment, the wire rope 601 of the rope assembly 600 may be replaced with a kevlar rope to improve the usability of the rope assembly 600.

According to the space electric connector drop plug storage device provided by the embodiment, the storage box 500 and the elastic component 800 are arranged, wherein the first end of the elastic component 800 is connected with the plug 400, the second end of the elastic component 800 is fixed on the storage box 500, when the plug 400 is electrically connected with the corresponding socket 300, the elastic component 800 is in a tension state, after the plug 400 is separated from the corresponding socket 300, the elastic component 800 is restored to a natural state or tends to the natural state, the plug 400 is positioned in the storage box 500, and further, the function of fixing the plug 400 dropped in the middle of an umbilical cable in the storage box 500 after separation of two spacecrafts is realized, so that damage to the spacecrafts caused by collision of single-machine equipment or other structures nearby after separation of the plug 400 is prevented, and posture disturbance to the spacecrafts can be reduced. In addition, in the present embodiment, the storage box 500 may be designed as a split type, so as to facilitate installation and maintenance of the plug 400.

While the basic concepts have been described above, it will be apparent to those skilled in the art that the foregoing disclosure is by way of example only and is not intended to be limiting. Although not explicitly described herein, various modifications, improvements and adaptations of the utility model may occur to one skilled in the art. Such modifications, improvements, and modifications are intended to be suggested within the present disclosure, and therefore, such modifications, improvements, and adaptations are intended to be within the spirit and scope of the exemplary embodiments of the present disclosure.

Meanwhile, the present utility model uses specific words to describe embodiments of the present utility model. Reference to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the utility model. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the utility model may be combined as suitable.

Similarly, it should be noted that in order to simplify the description of the present disclosure and thereby aid in understanding one or more inventive embodiments, various features are sometimes grouped together in a single embodiment, figure, or description thereof. This method of disclosure, however, is not intended to imply that more features than are required by the subject utility model. Indeed, less than all of the features of a single embodiment disclosed above.

In some embodiments, numbers describing the components, number of attributes are used, it being understood that such numbers being used in the description of embodiments are modified in some examples by the modifier "about," approximately, "or" substantially. Unless otherwise indicated, "about," "approximately," or "substantially" indicate that the number allows for a 20% variation. Accordingly, in some embodiments, numerical parameters set forth in the specification and claims are approximations that may vary depending upon the desired properties sought to be obtained by the individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and employ a method for preserving the general number of digits. Although the numerical ranges and parameters set forth herein are approximations in some embodiments for use in determining the breadth of the range, in particular embodiments, the numerical values set forth herein are as precisely as possible.

While the utility model has been described with reference to the specific embodiments presently, it will be appreciated by those skilled in the art that the foregoing embodiments are merely illustrative of the utility model, and various equivalent changes and substitutions may be made without departing from the spirit of the utility model, and therefore, all changes and modifications to the embodiments are intended to be within the scope of the appended claims.

Claims (9)

1. An electrical space connector drop-out plug receiving device, comprising: the device comprises a storage box (500), a pull rope assembly (600) and an elastic assembly (800), wherein a first end of the pull rope assembly (600) is connected with a plug (400), a second end of the pull rope assembly is fixed on a bracket (700), the first end of the elastic assembly (800) is pressed on the plug (400), and the second end of the elastic assembly is fixed on the storage box (500);

when the plug (400) is electrically connected with the corresponding socket (300), the elastic component (800) is in a tension state; after the plug (400) is separated from the corresponding socket (300), the elastic component (800) is restored to a natural state or tends to the natural state, and the plug (400) is positioned in the storage box (500).

2. The space electrical connector drop plug receiving device of claim 1, wherein the receiving box (500) comprises a first member (501) and a second member (502), the first member (501) and the second member (502) being combined into the receiving box (500).

3. The space electric connector drop plug receiving device according to claim 2, wherein the cross section of the receiving box (500) formed by combining the first member (501) and the second member (502) is hexagonal, cylindrical or square.

4. The space electrical connector drop plug receiving device according to claim 1, wherein the side of the receiving box (500) has a plurality of through holes (503).

5. The space electrical connector drop plug receiving device of claim 1, wherein the resilient member (800) is a leaf spring.

6. The space electrical connector drop plug receiving device of claim 5, wherein the resilient assembly comprises a first leaf spring (801), a second leaf spring (802) and a third leaf spring (803), each leaf spring having a first end secured to the receptacle (500) and a second end pressed against the plug (400).

7. The space electrical connector drop plug receiving device of claim 1, wherein the pull cord assembly (600) comprises a wire rope (601), a first end of the wire rope (601) being attached to a screw (602) and a second end being attached to the plug (400).

8. The space electrical connector drop plug receiving device of claim 7, wherein the second end of the wire rope (601) is connected to the plug (400) with a cap (603) via a cotter pin (604).

9. The space electrical connector drop plug receiving device of claim 7, wherein the screw (602) is secured to the first structure (100) by the bracket (700).