A rocket stage separation guide aerodynamic push rod

Abstract

This application discloses a rocket stage separation guide aerodynamic pusher, relating to the field of aerospace technology, comprising: a first pusher assembly and a second pusher assembly; the first pusher assembly includes: a base, an outer cylinder, and an inner cylinder; one end of the base is connected to an inflation system, and the other end of the base is connected to one end of the outer cylinder; an inner retaining ring is provided on the inner side of the other end of the outer cylinder; the inner cylinder includes: an inner cylinder ring plate and an inner cylinder end face, one end of the inner cylinder ring plate is connected to the inner cylinder end face; the inner cylinder is disposed inside the outer cylinder, and the outer side of the inner cylinder ring plate is slidably connected to the inner side of the outer cylinder; the second pusher assembly includes: a guide pin, a locking nut, a connecting device, and a thrust bracket; after extension, the side of the inner cylinder end face away from the inner cylinder ring plate separates from the other end of the base, the other end of the inner cylinder ring plate is limitedly connected to the inner retaining ring of the outer cylinder, and one end of the guide pin separates from the inner cylinder and extends out of the outer cylinder. This application enables the aerodynamic pusher to have its own guidance, ensuring the stability of the attitude of the two stages after separation.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a rocket stage separation guide aerodynamic push rod. Background Technology

[0002] Pneumatic pushers are crucial components in rocket stage separation. Located on either side of the separation plane, compressed gas is introduced into the pushers before separation. During separation, the separation planes unlock and open, and the pushers, propelled by the compressed gas, rapidly extend, instantly granting the stages on either side of the separation plane kinetic energy for rapid separation.

[0003] To ensure that the two stages do not collide with other parts of the rocket after separation, the existing aerodynamic push rods need to have an additional guide mechanism added inside the rocket, which will increase the overall structural weight. Summary of the Invention

[0004] The purpose of this application is to provide a rocket stage separation guide pneumatic push rod that can provide its own guidance and ensure the stability of the attitude of the two stages after separation.

[0005] To achieve the above objectives, this application provides a rocket stage separation guide pneumatic pusher, comprising: a first pusher assembly disposed on a first separation body and a second pusher assembly disposed on a second separation body; wherein, the first pusher assembly includes at least: a base, an outer cylinder, and an inner cylinder; one end of the base is connected to an inflation system, and the other end of the base is connected to one end of the outer cylinder; an inner retaining ring is disposed on the inner side of the other end of the outer cylinder; the inner cylinder includes: an inner cylinder ring plate and an inner cylinder end face, one end of the inner cylinder ring plate is connected to the inner cylinder end face; the inner cylinder is disposed inside the outer cylinder, and the outer side of the inner cylinder ring plate is slidably connected to the inner side of the outer cylinder, and during rocket assembly, the side of the inner cylinder end face away from the inner cylinder ring plate contacts the other end of the base; the second pusher assembly includes at least: a guide The rocket consists of a guide pin, a locking nut, a connecting device, and a thrust bracket. During rocket assembly, one end of the guide pin is tightly fitted to the side of the inner cylinder end face that connects to the inner cylinder ring plate, and a portion of the outer side of the guide pin is tightly fitted to the inner side of the inner cylinder ring plate. The other end of the guide pin is located outside the other end of the outer cylinder. The other end of the guide pin is connected to one end of the connecting device, and the other end of the connecting device is connected to the thrust bracket. The locking nut is located on the connecting device and between the guide pin and the thrust bracket. After the inflation system extends, the side of the inner cylinder end face away from the inner cylinder ring plate separates from the other end of the base. The other end of the inner cylinder ring plate is connected to the inner retaining ring of the outer cylinder for limiting. One end of the guide pin separates from the inner cylinder and extends outside the outer cylinder.

[0006] As shown above, at least one dynamic sealing ring is provided on the outer side of the inner cylinder.

[0007] As shown above, the dynamic sealing ring is located on the outside of the inner cylinder ring plate.

[0008] As shown above, the outer side of the base is provided with a mating ring, and after the other end of the base is connected to one end of the outer cylinder, one end of the outer cylinder is still in contact with the mating ring.

[0009] As shown above, a static sealing ring is provided on the mating ring, and after the other end of the base is connected to one end of the outer cylinder, one end of the outer cylinder is still in contact with the static sealing ring.

[0010] As shown above, one end of the outer cylinder is also provided with a first outer cylinder outer retaining ring. After the other end of the base is connected to one end of the outer cylinder, the first outer cylinder outer retaining ring contacts the static sealing ring.

[0011] As shown above, the other end of the base is threaded to one end of the outer cylinder.

[0012] As shown above, the connecting device is a threaded device, one end of which is threadedly connected to the other end of the guide pin, and the other end of which is threadedly connected to the thrust bracket.

[0013] As shown above, the locking nut is threadedly connected to the threaded device.

[0014] As mentioned above, the gas that the inflation system fills into the first push rod assembly is nitrogen, helium, or compressed air.

[0015] The beneficial effects achieved by this application are as follows:

[0016] (1) The rocket stage separation guide pneumatic push rod of this application can make the pneumatic push rod self-guided, without the need to add an additional guide mechanism inside the rocket, reducing the overall structural weight, and ensuring the stability of the attitude of the two sub-stages after separation, without touching other parts of the rocket.

[0017] (2) The rocket stage separation guide pneumatic push rod of this application inserts the guide pin of the second push rod assembly into the first push rod assembly, and can achieve guidance by using the outer cylinder and the inner cylinder.

[0018] (3) The rocket stage separation guide aerodynamic push rod of this application can be applied not only to the two separation sub-stages of the rocket, but also to other locations of the rocket that need to be separated, such as fairing separation. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0020] Figure 1A schematic diagram of one embodiment of the rocket stage separation guide aerodynamic push rod in its retracted state;

[0021] Figure 2 This is a schematic diagram of one embodiment of the rocket stage separation guide aerodynamic pusher in the extended state. Detailed Implementation

[0022] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] like Figure 1-2 As shown, this application provides a rocket stage separation guide pneumatic pusher, including: a first pusher assembly 1 disposed on a first separation body and a second pusher assembly 2 disposed on a second separation body. The first pusher assembly 1 includes at least: a base 11, an outer cylinder 12, and an inner cylinder 13. One end of the base 11 is connected to an inflation system 3, and the other end of the base 11 is connected to one end of the outer cylinder 12; an inner retaining ring 121 is disposed on the inner side of the other end of the outer cylinder 12. The inner cylinder 13 includes: an inner cylinder ring plate 131 and an inner cylinder end face 132, one end of the inner cylinder ring plate 131 is connected to the inner cylinder end face 132; the inner cylinder 13 is disposed inside the outer cylinder 12, and the outer side of the inner cylinder ring plate 131 is slidably connected to the inner side of the outer cylinder 12. During rocket assembly, the side of the inner cylinder end face 132 away from the inner cylinder ring plate 131 contacts the other end of the base 11. The second push rod assembly 2 includes at least: a guide pin 21, a locking nut 22, a connecting device 23, and a thrust bracket 24. During rocket assembly, one end of the guide pin 21 is tightly fitted to the side of the inner cylinder end face 132 connected to the inner cylinder ring plate 131, and a portion of the outer side of the guide pin 21 is tightly fitted to the inner side of the inner cylinder ring plate 131. The other end of the guide pin 21 is located outside the other end of the outer cylinder 12. The other end of the guide pin 21 is connected to one end of the connecting device 23, and the other end of the connecting device 23 is connected to the thrust bracket 24. The locking nut 22 is disposed on the connecting device 23, and the locking nut 22 is located between the guide pin 21 and the thrust bracket 24. After the air supply system 3 extends, the side of the inner cylinder end face 132 away from the inner cylinder ring plate 131 separates from the other end of the base 11, the other end of the inner cylinder ring plate 131 is limitedly connected to the inner retaining ring 121 of the outer cylinder, and one end of the guide pin 21 separates from the inner cylinder 13 and extends outside the outer cylinder 12.

[0024] Specifically, the outer cylinder 12 has larger dimensions (e.g., diameter and length) than the inner cylinder 13. Fitting the inner cylinder 13 inside the outer cylinder 12 reduces the overall size of the aerodynamic pusher structure, which is beneficial for optimizing the rocket's structural layout. Furthermore, reducing the overall size of the outer cylinder 12 and inner cylinder 13 to a multi-section form facilitates manufacturing. Installing the second pusher assembly 2 on one side of the rocket stage and inserting its guide pin 21 into the first pusher assembly 1 installed on the other side of the rocket stage allows for guidance using the outer cylinder 12 and inner cylinder 13. This ensures that the force of the first pusher assembly 1 is transmitted to the side of the rocket stage where the second pusher assembly 2 is located, guaranteeing a smooth separation process and stable attitude of the two stages after separation, preventing contact with other parts of the rocket.

[0025] Furthermore, one side of the locking nut 22 contacts the other end of the guide pin 21, thereby increasing the structural stability through the locking nut 22.

[0026] Furthermore, the first separation body is rocket stage 1 and the second separation body is rocket stage 2, but it is not limited to the first separation body being rocket stage 1 and the second separation body being rocket stage 2. It can also be separation bodies at other locations of the rocket that need to be separated, such as fairing separation.

[0027] Furthermore, at least one dynamic sealing ring 133 is provided on the outer side of the inner cylinder 13.

[0028] Specifically, the sealing performance of the inner cylinder 13 is ensured by the dynamic sealing ring 133 when the cylinder 13 moves.

[0029] Furthermore, the specific location of the dynamic sealing ring 133 depends on the actual situation. In this application, it is preferred that the dynamic sealing ring 133 is located on the outside of the inner cylinder ring plate 131.

[0030] Furthermore, a docking ring 111 is provided on the outer side of the base 11. After the other end of the base 11 is connected to one end of the outer cylinder 12, one end of the outer cylinder 12 is also in contact with the docking ring 111.

[0031] Specifically, the docking ring 111 can limit the connection position between the outer cylinder 12 and the base 11.

[0032] Furthermore, a static sealing ring 112 is provided on the docking ring 111. After the other end of the base 11 is connected to one end of the outer cylinder 12, one end of the outer cylinder 12 is also in contact with the static sealing ring 112.

[0033] Specifically, the static sealing ring 112 ensures the sealing of the connection between the outer cylinder 12 and the base 11.

[0034] Furthermore, a first outer cylinder outer retaining ring 122 is provided at one end of the outer cylinder 12. After the other end of the base 11 is connected to one end of the outer cylinder 12, the first outer cylinder outer retaining ring 122 contacts the static sealing ring 112.

[0035] Furthermore, a second outer cylinder retaining ring 123 is provided at the other end of the outer cylinder 12 for easy installation.

[0036] Furthermore, the other end of the base 11 is threaded to one end of the outer cylinder 12, but is not limited to threaded connection. In this application, threaded connection is preferred to facilitate installation, disassembly or replacement.

[0037] Furthermore, the other end of the guide pin 21 is provided with an internal thread.

[0038] Furthermore, the thrust bracket 24 is provided with internal threads.

[0039] Furthermore, the connecting device 23 is a threaded device, one end of which is threadedly connected to the other end of the guide pin 21, and the other end of which is threadedly connected to the thrust bracket 24. However, it is not limited to threaded connection. In this application, threaded connection is preferred to facilitate installation, disassembly or replacement.

[0040] Furthermore, the locking nut 22 is threadedly connected to the threaded device, but not limited to threaded connection. In this application, threaded connection is preferred to facilitate installation, disassembly or replacement.

[0041] Furthermore, the locking nut 22 is provided with internal threads.

[0042] Furthermore, the threaded device is provided with external threads that are compatible with the internal threads of the guide pin 21, the internal threads of the thrust bracket 24, and the internal threads of the locking nut 22.

[0043] Furthermore, the inflation system 3 is used to provide compressed gas to the first push rod assembly 1 and to increase the inflation volume. The gas that the inflation system 3 fills into the first push rod assembly 1 is nitrogen, helium, or compressed air, but is not limited to nitrogen, helium, or compressed air; other working gases may also be used.

[0044] The beneficial effects achieved by this application are as follows:

[0045] (1) The rocket stage separation guide pneumatic push rod of this application can make the pneumatic push rod self-guided, without the need to add an additional guide mechanism inside the rocket, reducing the overall structural weight, and ensuring the stability of the attitude of the two sub-stages after separation, without touching other parts of the rocket.

[0046] (2) The rocket stage separation guide pneumatic push rod of this application inserts the guide pin of the second push rod assembly into the first push rod assembly, and can achieve guidance by using the outer cylinder and the inner cylinder.

[0047] (3) The rocket stage separation guide aerodynamic push rod of this application can be applied not only to the two separation sub-stages of the rocket, but also to other locations of the rocket that need to be separated, such as fairing separation.

[0048] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the scope of protection of this application is intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application. Obviously, those skilled in the art can make various alterations and variations to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of protection of this application and its equivalents, this application also intends to include these modifications and variations.

Claims

1. A rocket stage separation guide aerodynamic pusher, characterized in that, include: A first push rod assembly disposed on the first separator and a second push rod assembly disposed on the second separator; The first push rod assembly includes at least: a base, an outer cylinder, and an inner cylinder; One end of the base is connected to the inflation system, and the other end of the base is connected to one end of the outer cylinder; an inner retaining ring is provided on the inner side of the other end of the outer cylinder. The inner cylinder includes: an inner cylinder ring plate and an inner cylinder end face, with one end of the inner cylinder ring plate connected to the inner cylinder end face; The inner cylinder is set inside the outer cylinder, and the outer side of the inner cylinder ring plate is slidably connected to the inner side of the outer cylinder. During rocket assembly, the side of the inner cylinder end face away from the inner cylinder ring plate contacts the other end of the base. The second push rod assembly includes at least: a guide pin, a lock nut, a connecting device, and a thrust bracket; During rocket assembly, one end of the guide pin and the side of the inner cylinder end face that connects to the inner cylinder ring plate are tightly fitted together, and a part of the outer side of the guide pin is tightly fitted together with the inner side of the inner cylinder ring plate. The other end of the guide pin is located outside the other end of the outer cylinder; the other end of the guide pin is connected to one end of the connecting device, and the other end of the connecting device is connected to the thrust bracket; the locking nut is set on the connecting device, and the locking nut is located between the guide pin and the thrust bracket. After the air supply system extends, the side of the inner cylinder end face away from the inner cylinder ring plate separates from the other end of the base. The other end of the inner cylinder ring plate is connected to the inner retaining ring of the outer cylinder for limiting. One end of the guide pin separates from the inner cylinder and extends out of the outer cylinder.

2. The rocket stage separation guide aerodynamic pusher according to claim 1, characterized in that, At least one dynamic sealing ring is provided on the outer side of the inner cylinder.

3. The rocket stage separation guide aerodynamic pusher according to claim 2, characterized in that, The dynamic sealing ring is located on the outside of the inner cylinder ring plate.

4. The rocket stage separation guide aerodynamic pusher according to claim 1, characterized in that, The base has a mating ring on its outer side. After the other end of the base is connected to one end of the outer cylinder, the other end of the outer cylinder is still in contact with the mating ring.

5. The rocket stage separation guide aerodynamic pusher according to claim 4, characterized in that, A static sealing ring is provided on the mating ring. After the other end of the base is connected to one end of the outer cylinder, one end of the outer cylinder is still in contact with the static sealing ring.

6. The rocket stage separation guide aerodynamic pusher according to claim 5, characterized in that, One end of the outer cylinder is also provided with a first outer cylinder outer retaining ring. After the other end of the base is connected to one end of the outer cylinder, the first outer cylinder outer retaining ring contacts the static sealing ring.

7. The rocket stage separation guide aerodynamic pusher according to claim 1, characterized in that, The other end of the base is threaded to one end of the outer cylinder.

8. The rocket stage separation guide aerodynamic pusher according to claim 1, characterized in that, The connecting device is a threaded device, one end of which is threadedly connected to the other end of the guide pin, and the other end of which is threadedly connected to the thrust bracket.

9. The rocket stage separation guide aerodynamic pusher according to claim 8, characterized in that, The lock nut is threadedly connected to the threaded device.

10. The rocket stage separation guide aerodynamic pusher according to claim 1, characterized in that, The gas that the inflation system fills into the first push rod assembly is nitrogen, helium, or compressed air.

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