Spacecraft thrust assembly nozzle blanking cap

Abstract

A nozzle blanking cap of a spacecraft thrust assembly relates to the field of spacecraft thrust assemblies and comprises a silica gel body and a pressing piece, the silica gel body comprises a base body and a limiting clamping seat, the base body is cylindrical, one end of the base body is a sealing face, and the sealing face is in contact with an outer end face when the nozzle blanking cap is used; the number of the limiting clamping seats is at least three, each limiting clamping seat comprises a supporting part and a protruding part, one end of each supporting part is connected to the periphery of one side of the sealing face of the base body, the side, facing the axis of the base body, of each supporting part and the end, away from the sealing face, of each supporting part is connected with the corresponding protruding part, so that the limiting clamping seats are hook-shaped, and the protruding parts make contact with the inner end face during use; the number of the pressing pieces corresponds to the number of the limiting clamping bases in a one-to-one mode, the pressing pieces are pre-embedded into the limiting clamping bases from the end, away from the sealing face, of the base body, and opening and closing of the limiting clamping bases are controlled through the pressing pieces. The blanking cap is convenient to mount and dismount, and redundant materials can be actively controlled.

Description

Technical Field

[0001] The invention relates to a plugging cover for a nozzle of a spacecraft thrust assembly, in particular to a plugging cover used for the nozzle of a spacecraft thrust assembly. Background Art

[0002] The thrust assembly of a spacecraft is used to perform orbit and attitude control of the spacecraft. The inside of its nozzle is a smooth conical surface, and the top of the conical surface is connected to a capillary nozzle. The smoothness of the nozzle will affect the thrust of the thruster. No excess material can enter the capillary nozzle, otherwise it will affect the normal operation of the thruster. After the thruster is installed, the nozzle pointing accuracy should meet the technical requirements. After the thruster is installed, the nozzle should be prevented from being affected by external forces that affect its installation accuracy. Due to the above reasons, a nozzle plugging cover should be installed at the thruster nozzle to prevent excess material from entering the nozzle, prevent the inner cone of the nozzle from being scratched by external forces, serve as a warning, and prevent the nozzle from being knocked by external forces.

[0003] The nozzle plugging cover in the prior art is of the upper and lower split meniscus positioning type, and its components include: a fixed ring, a meniscus, a sealing ring, a cover plate and a fixing screw, a total of 8 parts, and the composition structure is complex; when installing, the various parts need to be assembled together in steps around the thruster nozzle; the operation is difficult, and only operators above the senior worker level can meet the work requirements; improper operation can easily cause parts to fall off, and there is no active prevention and control link for excess objects, resulting in excess object prevention and control risks; the sealing ring is prone to aging, resulting in poor sealing effect; the work efficiency is low, and it takes 3 minutes to install a set of nozzle plugging covers; the main parts are made of metal materials and are heavy. Summary of the invention

[0004] The technical problem solved by the present application is: to overcome the deficiencies of the prior art and to provide a spacecraft thrust assembly nozzle plugging cover having the advantages of integrated configuration, light and compact, material not prone to aging, simple and convenient operation, and providing active control of redundant links.

[0005] The technical solutions provided by this application are as follows:

[0006] A nozzle plugging cover of a spacecraft thrust assembly is used to seal the nozzle of a thruster, the side of the nozzle away from the thruster is an outer end face, and the side of the nozzle facing the thruster is an inner end face, comprising a silicone body and a pressing piece, the silicone body comprising a base and a limit card seat, the base is cylindrical, one end of the base is a sealing surface, and the sealing surface contacts the outer end face when in use; at least three limit card seats are provided, the limit card seat comprises a supporting part and a protruding part, one end of the supporting part is connected to the periphery of one side of the sealing surface of the base, and the end of the supporting part facing the side of the base axis and away from the sealing surface is connected to the protruding part, so that the limit card seat is hook-shaped, and the protruding part contacts the inner end face when in use; the number of pressing pieces corresponds to the number of limit card seats one by one, and the pressing piece is pre-buried in the limit card seat from the end of the base away from the sealing surface, so as to control the opening and closing of the limit card seat by the pressing piece.

[0007] The surface of the raised portion facing the sealing surface has an arc-shaped convex strip along the circumferential direction of the sealing surface. The position of the arc-shaped convex strip closest to the sealing surface is a compression line. When in use, the compression line of the limit clamping seat contacts the inner end surface of the nozzle.

[0008] The contact position between the clamping line and the inner end face is between the middle position -w1 of the inner end face width and the middle position +w1 of the inner end face width, wherein - means moving toward the axis of the substrate, + means moving away from the axis of the substrate, and w1 is 20-30% of the inner end face width.

[0009] The central angle corresponding to each of the compression lines in the circumferential direction of the substrate is 10°-50°.

[0010] Each of the pressing pieces includes an embedded section and a pressing section that are integrally connected. One end of the embedded section and the pressing section are connected and the angle between the two is an obtuse angle. The embedded section is embedded in the limiting socket along a direction parallel to the axis of the base body, and the pressing section is inclined away from the axis of the silicone body.

[0011] The distance from the end of the embedded section away from the sealing surface to the sealing surface is greater than the distance from the raised portion to the sealing surface.

[0012] The embedded section is provided with at least two connection holes, and the pressing section is provided with a weight-reducing hole.

[0013] The assembly method of the base body and the pressing piece comprises: firstly fixing the embedded section of the pressing piece in a mold, then pouring liquid silicone material in the mold, and obtaining a combination of the silicone body and the pressing piece after the liquid silicone is solidified.

[0014] The silicone body is made of flexible material, and the flexible material includes silicone rubber.

[0015] The silicone body also includes an anti-drop hole seat, which is located at one end of the base body away from the sealing surface. The anti-drop hole seat is provided with an anti-drop hole, through which the silicone body can be fixed to the thruster structure via an anti-drop rope.

[0016] In summary, this application at least includes the following beneficial technical effects:

[0017] (1) The main component material of the present invention is silica gel, and the overall weight is light;

[0018] (2) The present invention is an integral structure, which is a whole when in use and has a simple structure;

[0019] (3) When the present invention is used, the installation and removal of the plug cover can be completed by operating the button, which is easy to operate;

[0020] (4) The sealing surface material of the present invention is made of silicone, which is not easy to age;

[0021] (5) The present invention is provided with an anti-drop hole seat to eliminate the hidden danger of excess objects. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the present invention;

[0023] Figure 2 It is a schematic diagram of the present invention;

[0024] Figure 3 It is a schematic diagram of an example of the present invention;

[0025] Figure 4 It is a cross-sectional view of an example of the present invention.

[0026] Description of the accompanying figures: 1. Silicone body; 1.1. Base body; 1.2. Sealing surface; 1.3. Limiting seat; 1.3.1. Pressing line; 2. Pressing piece;

[0027] 3. Thruster; 3.1. Nozzle; 3.2. Outer end surface; 3.3. Inner end surface. DETAILED DESCRIPTION

[0028] 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.

[0029] The present application embodiment discloses a spacecraft thrust assembly nozzle plugging cover, such as Figure 3 and Figure 4 As shown, the nozzle 3.1 used to seal the thruster 3 has a side of the nozzle 3.1 away from the thruster 3 as an outer end surface 3.2, and a side of the nozzle 3.1 facing the thruster 3 as an inner end surface 3.3. Figure 1 and Figure 2 As shown, a nozzle plugging cover of a spacecraft thrust assembly includes a silicone body 1 and a pressing piece 2, wherein the silicone body 1 is an integrated flexible component.

[0030] like Figure 1 and Figure 2As shown, the silicone body 1 includes: a base 1.1, a sealing surface 1.2, a limit card seat 1.3 and an anti-drop hole seat 1.4; the base 1.1 is the foundation of the entire silicone body and is cylindrical; the sealing surface 1.2 is arranged at one end of the base 1.1, and when in use, the sealing surface 1.2 contacts the outer end surface 3.2 of the nozzle 3.1 to ensure that the thruster nozzle 3.1 is a closed environment; the limit card seat 1.3 includes three parts, which are arranged around the sealing surface 1.2 of the base 1.1 and are evenly distributed at 120 degrees. The limit card seat 1.3 includes a supporting part and a protruding part. One end of the supporting part is connected to the periphery of one side of the sealing surface 1.2 of the base 1.1, and the end of the supporting part facing the axis side of the base 1.1 and away from the sealing surface 1.2 is connected to the protruding part, so that the limit card seat 1.3 is hook-shaped, and the surface of the protruding part facing the sealing surface 1.2 is provided with an arc along the circumferential direction of the sealing surface 1.2 shaped convex strip, the position of the arc convex strip closest to the sealing surface 1.2 is the compression line 1.3.1, when in use, the compression line 1.3.1 of the limit clamp 1.3 contacts the inner end face 3.3 of the nozzle 3.1, to ensure that the plugging cover is firmly fixed on the nozzle 3.1, and the contact position of the compression line 1.3.1 and the inner end face 3.3 is between (the middle of the width of the inner end face 3.3 - w1) and (the middle of the width of the inner end face 3.3 + w1), wherein w1 is 20-30% of the width of the inner end face 3.3, (the middle of the width of the inner end face 3.3 - w1) is: the position after moving w1 from the middle of the width of the inner end face 3.3 to the direction close to the axis of the substrate 1.1, and (the middle of the width of the inner end face 3.3 + w1) is: the position after moving w1 from the middle of the width of the inner end face 3.3 to the direction away from the axis of the substrate 1.1, to ensure that the plugging cover can be firmly fixed. The corresponding central angle of each limit card seat 1.3 (i.e., the compression line 1.3.1) on the circumference of the base 1.1 is 10°-50°, so that the contact between the limit card seat 1.3 and the inner end surface 3.3 is sufficient to ensure that the sealing surface 1.2 and the outer end surface 3.2 of the nozzle 3.1 are relatively evenly contacted and sealed at all locations. The anti-drop hole seat 1.4 is arranged on the other end surface of the base 1.1 opposite to the sealing surface 1.2. When in use, an anti-dropping measure can be arranged on the anti-dropping hole seat 1.4, such as tying one end of the anti-dropping device to the anti-dropping hole seat 1.4 and the other end to other structures of the thruster 3.

[0031] The push pieces 2 include three parts, and the position of each push piece 2 corresponds to the position of each limit card seat 1.3 one by one. The three push pieces 2 are respectively embedded in the limit card seat 1.3 of the silicone body 1 from the side of the silicone body 1 away from the sealing surface 1.2, and the three push pieces 2 are evenly distributed at 120 degrees in the circumferential direction of the end of the base 1.1. Each push piece 2 includes an embedded section and a pressing section connected in one piece, one end of the embedded section and the pressing section are connected and the angle between the two is an obtuse angle, the embedded section is provided with at least two connecting holes, and the pressing section is provided with a weight reduction hole; the embedded section is embedded in the limit card seat 1.3 along a direction parallel to the axis of the base 1.1, and the pressing section is inclined away from the axis of the base 1.1; the distance from the end of the embedded section away from the sealing surface 1.2 to the sealing surface 1.2 is greater than the distance from the protrusion to the sealing surface 1.2, so that when the push piece 2 is pressed toward the axis of the silicone body 1, the push piece 2 can drive the limit card seat 1.3 to open better. When pre-embedded, the pre-embedded section of the pressing piece 2 is fixed in the mold, and then the flexible material is poured in the mold and solidified to obtain the silicone body 1. The setting of the connection hole ensures the stability of the connection between the silicone body 1 and the pressing piece 2. When in use, the opening and closing of the limit card seat 1.3 is controlled by pressing the pressing piece 2.

[0032] Specific installation and use methods:

[0033] 1. Check that the surface of the nozzle plug is intact and free of excess material. If necessary, clean it with a dust-free cloth dipped in anhydrous ethanol.

[0034] 2. Use three fingers to press the metal button 2 to open the limit holder 1.3 slightly.

[0035] 3. Align the axis of the nozzle plugging cover with the axis of the thruster 3; slowly fit the sealing surface 1.2 of the nozzle plugging cover with the outer end surface 3.2 of the thrust assembly nozzle 3.1, and release the metal pressing piece 2.

[0036] 4. Use three fingers to press the three limit clamps 1.3 at the same time, repeat 3-4 times, so that the limit clamps 1.3 are in good contact with the inner end surface 3.3 of the thrust assembly nozzle 3.1.

[0037] 5. Check the installation status of the plug cover: the plug cover is not skewed, and the three limit seats 1.3 are in good contact with the inner end surface 3.3 of the thrust assembly nozzle 3.1.

[0038] 6. When removing, first press the metal button 2 with three fingers to slightly open the limit holder 1.3, and then slowly move the plug cover away from the thruster 3 along its axis.

[0039] 7. When there are extra prevention and control requirements for high-altitude operations or operations in special environments, anti-falling measures can be set on the anti-falling hole seat 1.4.

[0040] The silica gel body is a flexible material. In the present invention, the silica gel body is made of silicone rubber or a material with similar performance.

[0041] The contents not described in detail in this application specification belong to the common knowledge of those skilled in the art.

[0042] The present application is described in detail above in conjunction with specific implementation methods and exemplary examples, but these descriptions cannot be understood as limiting the present application. Those skilled in the art understand that, without departing from the spirit and scope of the present application, a variety of equivalent replacements, modifications or improvements can be made to the technical solution of the present application and its implementation methods, all of which fall within the scope of the present application. The scope of protection of the present application shall be subject to the attached claims.

Claims

1. A nozzle plugging cover for a spacecraft thrust assembly, used for sealing a nozzle (3.1) of a thruster (3), wherein the side of the nozzle (3.1) away from the thruster (3) is an outer end surface (3.2), and the side of the nozzle (3.1) facing the thruster (3) is an inner end surface (3.3), characterized in that: The device comprises a silicone body (1) and a pressing sheet (2); the silicone body (1) comprises a base body (1.1) and a limit clamping seat (1.3); the base body (1.1) is cylindrical; one end of the base body (1.1) is a sealing surface (1.2); when in use, the sealing surface (1.2) contacts an outer end surface (3.2); At least three position limiting clamps (1.3) are provided, and the position limiting clamps (1.3) comprise a support portion and a protruding portion, one end of the support portion is connected to the periphery of one side of the sealing surface (1.2) of the base (1.1), and the end of the support portion facing the axis of the base (1.1) and away from the sealing surface (1.2) is connected to the protruding portion, so that the position limiting clamp (1.3) is hook-shaped, and the protruding portion contacts the inner end surface (3.3) when in use; The number of the push pieces (2) corresponds to the number of the limit clamping seats (1.3) in a one-to-one manner; the push piece (2) is pre-buried in the limit clamping seat (1.3) from one end of the base body (1.1) away from the sealing surface (1.2), so as to control the opening and closing of the limit clamping seat (1.3) through the push piece (2).

2. The spacecraft thrust assembly nozzle plugging cover according to claim 1, characterized in that: The surface of the raised portion facing the sealing surface (1.2) has an arcuate convex strip along the circumferential direction of the sealing surface (1.2), and the position of the arcuate convex strip closest to the sealing surface (1.2) is a compression line (1.3.1). When in use, the compression line (1.3.1) of the position-limiting clamp (1.3) contacts the inner end surface (3.3) of the nozzle (3.1).

3. The spacecraft thrust assembly nozzle plugging cover according to claim 2, characterized in that: The contact position between the compression line (1.3.1) and the inner end surface (3.3) is between [the middle of the width of the inner end surface (3.3) -w1] and [the middle of the width of the inner end surface (3.3) +w1], wherein - represents movement toward the axis of the substrate (1.1), + represents movement away from the axis of the substrate (1.1), and w1 represents 20-30% of the width of the inner end surface (3.3).

4. The spacecraft thrust assembly nozzle plugging cover according to claim 2, characterized in that: The central angle corresponding to each of the compression lines (1.3.1) in the circumferential direction of the base body (1.1) is 10°-50°.

5. The spacecraft thrust assembly nozzle plugging cover according to claim 1, characterized in that: Each of the pressing pieces (2) comprises an integrally connected embedded section and a pressing section, one end of the embedded section and the pressing section are connected and the angle between the two is an obtuse angle, the embedded section is embedded in the limiting clamping seat (1.3) along a direction parallel to the axis of the base body (1.1), and the pressing section is inclined in a direction away from the axis of the silicone body (1).

6. The spacecraft thrust assembly nozzle plugging cover according to claim 5, characterized in that: The distance from the end of the embedded section away from the sealing surface (1.2) to the sealing surface (1.2) is greater than the distance from the raised portion to the sealing surface (1.2).

7. The spacecraft thrust assembly nozzle plugging cover according to claim 5, characterized in that: The embedded section is provided with at least two connection holes, and the pressing section is provided with a weight-reducing hole.

8. The spacecraft thrust assembly nozzle plugging cover according to claim 1, characterized in that: The assembly method of the base body (1.1) and the pressing piece (2) comprises: fixing the embedded section of the pressing piece (2) in a mold, then pouring liquid silicone material in the mold, and obtaining a combination of the silicone body (1) and the pressing piece (2) after the liquid silicone is cured.

9. The spacecraft thrust assembly nozzle plugging cover according to claim 1, characterized in that: The silica gel body (1) is made of a flexible material, and the flexible material includes silicone rubber.

10. The spacecraft thrust assembly nozzle plugging cover according to claim 1, characterized in that: The silicone body (1) also includes an anti-drop hole seat (1.4), which is located at one end of the base body (1.1) away from the sealing surface (1.2), and an anti-drop hole is provided on the anti-drop hole seat (1.4), through which the silicone body (1) can be fixed to the thruster (3) structure via an anti-drop rope.

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