CN215399393U

CN215399393U - Carrier rocket reverse-thrust device and carrier rocket

Info

Publication number: CN215399393U
Application number: CN202120742569.0U
Authority: CN
Inventors: 袁野; 宋晓伟
Original assignee: Landspace Technology Co Ltd; Zhejiang Landspace Technology Co Ltd
Current assignee: Landspace Technology Co Ltd; Zhejiang Landspace Technology Co Ltd
Priority date: 2021-04-13
Filing date: 2021-04-13
Publication date: 2022-01-04
Anticipated expiration: 2031-04-13

Abstract

The utility model provides a carrier rocket reverse thrust device and a carrier rocket, which comprise a plurality of reverse thrust structures uniformly arranged along a sub-stage circumferential surface of the rocket, wherein each reverse thrust structure comprises a reverse thrust small rocket and a cover body arranged outside the reverse thrust small rocket; the reverse thrust small rocket is fixed with the surface of the first sub-stage of the rocket, and the nozzle is close to the second sub-stage of the rocket in the axial direction of the rocket; the cover body comprises an end socket with a clamping piece and a body part with a matching piece, the end socket is matched with the matching piece through the clamping piece, so that the end socket is tightly connected with the body part, the body part is used for being fixedly connected with the surface of the first substage of the rocket, and the body part, the end socket and the surface of the first substage of the rocket which are clamped with each other form a space for limiting a reverse thrust small rocket; after the first rocket substage and the second rocket substage are connected and unlocked, the small reverse-thrust rocket is ignited, the seal head is pushed away from the body by the pressure generated in the space, and the small reverse-thrust rocket enables the first rocket substage to obtain the reverse thrust so that the first rocket substage and the second rocket substage are separated from each other.

Description

Carrier rocket reverse-thrust device and carrier rocket

Technical Field

The utility model relates to the technical field of rocket separation, in particular to a carrier rocket thrust reverser and a carrier rocket.

Background

With the rapid development of the aerospace industry, all the technologies related to the rocket field also realize the rapid advance.

The reverse thrust small rockets of the existing carrier are mostly installed in a primary box interval section and externally installed. The biggest difficulty of external installation is that the reverse thrust small rocket needs to be protected by a fairing before the first stage separation and the second stage separation so as to avoid pneumatic heating interference. At the instant of the second stage separation, the thrust reverser cowling needs to be able to open quickly to enable the small rocket to work effectively.

It is urgently needed to provide a carrier rocket reverse thrust device which is reasonable in design and stable in structure, can enable a rocket to be rapidly separated in a first-level and a second-level, and improves the separation reliability.

Disclosure of Invention

The utility model aims to overcome the defects of the prior art and provides a carrier rocket reverse thrust device and a carrier rocket structure, which have the advantages of reasonable design and stable structure, can quickly separate a rocket in a first stage and a second stage, and improve the separation reliability.

The utility model provides a carrier rocket thrust reverser, which comprises a plurality of thrust reversers uniformly arranged along the circumferential surface of a sub-stage of a rocket, wherein,

the reverse-thrust structure comprises a reverse-thrust small rocket and a cover body arranged outside the reverse-thrust small rocket; the reverse thrust small rocket is fixed with the surface of a first sub-stage of the rocket through a fixing frame; in the axial direction of the rocket, the nozzle is close to the second sub-stage of the rocket; the cover body comprises an end socket with a clamping piece and a body part with a matching piece, the end socket is matched with the matching piece through the clamping piece, so that the end socket is tightly connected with the body part, and the other end of the end socket, which is far away from the clamping piece, is used for being fixed on the surface of a first-stage rocket through a supporting piece; the body part is fixedly connected with the surface of the first-stage rocket, and the body part, the end socket and the surface of the first-stage rocket, which are clamped with each other, form a space for limiting the reverse thrust small rocket;

after the first rocket secondary stage and the second rocket secondary stage are unlocked, the reverse thrust small rocket is ignited, the seal head is pushed away from the body by pressure generated in the space, and the reverse thrust small rocket enables the first rocket secondary stage to obtain reverse thrust so as to be convenient for the quick separation of the first rocket secondary stage and the second rocket secondary stage.

Further, the nozzle rocket of the reverse thrust small rocket extends towards the outer side far away from a sub-stage of the rocket.

Further, the joint spare is for setting up the head is close to the fixed strip hole of body position, the fitting piece is for setting up the elastic component of body corresponding position, the elastic component is in body inboard for body internal surface protrusion sets up body inboard, the head passes through fixed strip hole articulate the elastic component realize with the joint of body.

Furthermore, the elastic component comprises an extending portion and a U-shaped portion, wherein the extending portion is symmetrically arranged on two sides of the opening of the U-shaped portion and is a structure formed by extending towards two sides far away from the center of the U-shaped portion.

Further, the bottom of the U-shaped part is convex towards one side close to a first sub-stage of the rocket.

Furthermore, the transition part of the bottom of the U-shaped part and the connection of the side wall of the U-shaped part is of an arc structure.

Further, the end socket comprises a flat plate with a radian and a bent arc part; one side of the flat plate, which is close to the outer surface of the first sub-stage of the rocket, is attached to the outer surface of the first sub-stage of the rocket, the outer side of the flat plate is connected with one end of the bent arc part, the other end of the bent arc part is clamped with the body part, and the bent arc part is matched with the outer surface of the first sub-stage of the rocket in shape.

Further, the side of the flat plate close to the outer surface of the rocket primary sub-stage is connected with the outer surface of the rocket primary sub-stage through an adhesive.

Furthermore, the outer surface of one end of the curved part, which is far away from the flat plate, is closely attached to the inner side surface of the body part.

In addition, the utility model also provides a carrier rocket comprising the characteristics of any one carrier rocket thrust reverser.

The carrier rocket reverse thrust device provided by the embodiment of the utility model comprises a plurality of reverse thrust structures which are uniformly arranged along the circumferential surface of a sub-stage of a rocket, and each reverse thrust structure consists of a reverse thrust small rocket and a cover body arranged outside the reverse thrust small rocket. Wherein the cover body comprises the head that has the joint spare and the body portion that has the fitting piece, through the head passes through joint spare and fitting piece cooperation. After the first rocket secondary and the second rocket secondary are unlocked, the reverse thrust small rocket is ignited, and the end socket can be quickly pushed away by high-pressure gas generated by the reverse thrust small rocket due to the fact that the end socket is connected with the body in a clamping mode. After the end socket is pushed away from the cover body, the nozzle of the reverse thrust small rocket is directly arranged outside, so that the first sub-stage of the rocket can quickly obtain the reverse thrust, and the first sub-stage of the rocket and the second sub-stage of the rocket can be quickly separated.

In addition, because the body part is fixedly connected with the surface of the first sub-stage of the rocket, the body part can be prevented from moving in a displacement mode, and further the body part is prevented from being damaged due to the fact that the body part is in contact with the small reverse-thrust rocket, and therefore the safe use of the small reverse-thrust rocket is guaranteed. The whole structure has reasonable design and stable structure, can quickly separate the rocket into two stages, and improves the separation reliability.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the utility model, as claimed.

Drawings

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

FIG. 1 is a schematic structural view of a launch vehicle thrust reverser in an embodiment of the utility model;

FIG. 2 is a front view of a closure in an embodiment of the utility model;

FIG. 3 is a left side view of the closure in an embodiment of the present invention;

FIG. 4 is a perspective view of a closure in an embodiment of the utility model;

FIG. 5 is a front view of a body portion in an embodiment of the present invention;

FIG. 6 is a left side view of a body part in an embodiment of the present invention;

FIG. 7 is a bottom view of the body portion of an embodiment of the present invention;

FIG. 8 is a front view of an elastic member according to an embodiment of the present invention;

FIG. 9 is a partial structure view of the connection between the head and the body in the embodiment of the present invention;

FIG. 10 is a top view of a support member in an embodiment of the present invention;

FIG. 11 is a left side view of a support member in an embodiment of the present invention;

FIG. 12 is a perspective view of a support member in an embodiment of the present invention;

FIG. 13 is a perspective view of the connection of the closure head to the body in the embodiment of the present invention;

fig. 14 is a schematic view of the connection between the support body and the end socket in the embodiment of the present invention.

Description of reference numerals:

1 rocket one-sub-stage 2 reverse thrust small rocket

3 end socket 4 body part

5 fixing strip hole 6 elastic piece

7 rocket secondary stage 8 nozzle

9 flat plate 10 curved part

11 first support 12 second support

13 recess 14 extension

15U-shaped part 16 support piece

Detailed Description

Reference will now be made in detail to various exemplary embodiments of the utility model, the detailed description should not be construed as limiting the utility model but as a more detailed description of certain aspects, features and embodiments of the utility model.

It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments will be apparent to those skilled in the art from consideration of the specification. The specification and examples are exemplary only.

The applicant has found that the high-pressure gas generated by the small reverse-thrust rocket after ignition can be pushed to open the end cover on the reverse-thrust fairing so as to discharge the flame of the small reverse-thrust rocket from the through hole. Through the research on the open end cover of the fairing, the design of the reverse thrust fairing is considered to have great potential safety hazard and even can cause the failure of rocket separation. On the one hand, the high-pressure gas that the little rocket of backstepping produced after the ignition can only be followed the through-hole and discharged for high-pressure gas can not be fast followed the backstepping radome fairing and discharged, and the backstepping efficiency is by serious loss, and then can influence a second grade quick separation. On the other hand, part of high-pressure gas can impact the inside of the reverse thrust fairing, so that the reverse thrust fairing deforms, the reverse thrust small rocket is fixed and infirm to incline, a thrust line deviates, and primary and secondary collision accidents are caused.

In some embodiments of the utility model, a combined external throwing cover structure is adopted, a double-engine single-cover mode is adopted, and a separation structure mode of a fairing end socket is optimized. The structure has the advantages of compact structure, no occupation of the outer wall space of the shell section, especially great improvement of the separation efficiency of the reverse rocket, and high separation reliability.

The present application is described above for the sub-stage separation of rockets, but it can be seen from the technical solutions of the present application that the separation of multi-stage solid rockets and missiles can also be implemented by using the structure of the present application, and still fall within the scope of the protection of the present application.

One aspect of the utility model provides a launch vehicle thrust reverser. As shown in fig. 1, fig. 2, fig. 3, fig. 4, fig. 5, fig. 6, fig. 7, fig. 8, fig. 9, fig. 12, and fig. 13, the thrust reverser includes a plurality of thrust reverser structures for being uniformly disposed along the circumferential surface of the rocket-stage 1. Wherein, the reverse structure comprises a reverse small rocket 2 and a cover body arranged outside the reverse small rocket 2. The reverse thrust small rocket 2 is fixed with the surface of the first rocket secondary stage 1 through a fixing frame, and the nozzle is close to the second rocket secondary stage in the axial direction of the rocket. The cover body contains the head 3 that has the joint spare and the body portion 4 that has the fitting piece, and head 3 cooperates with the fitting piece through the joint spare for head 3 and body portion 4 zonulae occludens, and the other end that the joint spare was kept away from to head 3 is used for fixing the surface at rocket first substage 1 through support piece 16. The body part 4 is used for being fixedly connected with the surface of the rocket primary sub-stage 1, and the body part 4, the end socket 3 and the surface of the rocket primary sub-stage 1 which are clamped with each other form a space for limiting the reverse thrust small rocket 2.

After the joint lock between the joint sections of the first rocket substage 1 and the second rocket substage 7 (for example, the joint lock mode triggered by an explosive bolt), the small reverse rocket 2 is ignited, the seal head 3 is pushed away from the body part 4 by the pressure generated in the space, and the small reverse rocket 2 makes the first rocket substage 1 obtain the reverse thrust so as to rapidly separate the first rocket substage 1 from the second rocket substage 7.

Concretely speaking, this kind of carrier rocket thrust reverser contains and is used for along a plurality of thrust reverser structures that rocket one-sub 1 circumference surface evenly set up, and thrust reverser structure is by thrust reverser rocket 2 and set up at the outside cover body of thrust reverser rocket 2 and constitute. And the cover body comprises head 3 that has the joint spare and the body portion that has fitting piece 4, and through joint spare and fitting piece cooperation, convenient each other fixed and separation are passed through to head 3.

After the explosion bolt between the connecting sections of the first rocket secondary stage 1 and the second rocket secondary stage 7 is detonated, after the reverse thrust small rocket 2 is ignited, the end socket 3 can be quickly pushed open by high-pressure gas generated by the reverse thrust small rocket 2 due to the clamping connection of the end socket 3 and the body part 4, so that the end socket 3 integrally falls off from the body part. In one embodiment of the utility model, after the end socket 2 falls off, the nozzle of the reverse thrust small rocket 2 is arranged outside, the reverse thrust flame of the reverse thrust small rocket is fully converted into separating force between the first-stage rocket and the second-stage rocket, namely, the first-stage rocket 1 can quickly obtain the reverse thrust, and the first-stage rocket 1 and the second-stage rocket 7 can realize quick separation. Because the body part 4 is fixedly connected with the surface of the first-stage rocket 1, the body part 4 can be prevented from moving when the reverse thrust small rocket applies reverse thrust, and further the body part 4 is prevented from being damaged by the reverse thrust small rocket 2 due to the contact with the reverse thrust small rocket 2, so that the safe use of the reverse thrust small rocket 2 is ensured. The whole structure has reasonable design, particularly the whole sealing head falls off, the efficiency of the reverse thrust of the small reverse thrust rocket can be ensured, the structure is kept stable in the separation process, the first-stage and second-stage quick separation of the rocket is realized, and the separation reliability is improved.

It should be noted that, as shown in fig. 1, fig. 2, fig. 3 and fig. 4, in order to facilitate the rapid opening of the cover body, the arrangement of the cover body is reduced (if each small rocket corresponds to one cover body, the increase of the cover body can cause the reduction of the surface space of the first stage of the rocket, and at the same time, because the cover body occupies a large space, when the rocket is launched, resistance is increased), so that the first stage and the second stage of the rocket can be rapidly separated, for example, each thrust-back structure at least comprises two thrust-back small rockets 2, and the two thrust-back small rockets are arranged side by side along the circumferential surface of the first stage of the rocket 1, and are arranged in one cover body. In practical application, the end socket can be pushed away by high-pressure gas generated by igniting one reverse thrust small rocket 2, and the two reverse thrust small rockets 2 can avoid single-point failure, so that the first stage 1 of the rocket obtains larger thrust, and reliable separation of the first stage and the second stage of the rocket is further ensured.

In order to prevent the high-temperature flame generated from the nozzle when the thrust-back small rocket 2 is ignited from burning on the surface of the rocket second substage 7, for example, the nozzle of the thrust-back small rocket 2 is close to one side of the rocket second substage 7 and extends to the outer side far away from the rocket first substage 1.

In addition, when the included angle between the axis of the nozzle and the axis of the first rocket secondary stage 1 is 15 degrees, after the small rocket 2 is ignited, the uniform stress of the first rocket secondary stage 1 can be ensured, so that the separation from the second rocket stage 7 is accelerated. Through a large amount of simulation experiments, the included angle between the axis of the nozzle and the axis of the first-stage and second-stage rocket 1 is A, when the condition that A is more than or equal to 10 degrees and less than or equal to 20 degrees is met, the condition that the first-stage and second-stage rockets are subjected to uniform thrust is guaranteed, sufficient and appropriate separation thrust can be provided, the seal heads 3 are separated from the body part 4, collision or separation failure of the first-stage and second-stage rockets is effectively avoided, and accelerated separation between the first-stage and second-stage rockets is further guaranteed.

In addition, as shown in fig. 1, fig. 2, fig. 3, fig. 4, fig. 8, fig. 9, fig. 10 and fig. 11, in order to facilitate the connection and separation of the closing head 3 with the body 4, for example, the snap-in member is a fixing strip hole 5 provided at a position of the closing head near the body, and the mating member is an elastic member 6 provided at a corresponding position of the body. For example, the elastic member 6 is provided to protrude from the inner surface of the body 4 inside the body, and the sealing head 3 is hooked to the elastic member 6 through the fixing strip hole 5 inside the body 4 to be clamped with the body 4.

Further, in the present embodiment, as shown in fig. 8 and 9, in order to facilitate the fixing and expansion of the elastic member 6, for example, the elastic member 6 includes the extension portion 14 and the U-shaped portion 15. The extending portions 14 are symmetrically arranged at two ends of the opening side of the U-shaped portion 15, extend towards one side far away from the center of the U-shaped portion 15 (extend towards two sides far away from the center of the U-shaped portion to form a structure), and the bottom of the U-shaped portion protrudes towards one side close to a first secondary stage of the rocket. In addition, the extension portion 14 may be fixed to the body portion by bolts. The elastic part 6 is arranged on the inner side of the body part in a protruding mode relative to the inner surface of the body part 4, and the seal head 3 is hung on the elastic part 6 through the fixing strip hole 5 to be clamped with the body part 4 on the inner side of the body part 4.

In order to facilitate installation, the transition part which is convenient for the connection of the bottom of the U-shaped part and the side wall of the U-shaped part is of an arc structure.

When one end of the end socket 3 enters the body part 4, the end entering the body part 4 moves downwards along the inner side of the body part (the side far away from the second sub-stage). When the fixing strip contacts with the U-shaped portion 15, the fixing strip enters the U-shaped opening of the U-shaped portion to press the protruding portion of the U-shaped portion 15 to the side away from the primary-secondary axis. When the fixing strip hole 5 and the U-shaped portion 15 are just matched in place, the U-shaped portion 15 is restored (i.e., bounced to the side close to the primary axis) so that the U-shaped portion 15 and the fixing strip hole 5 are clamped together. And the U-shaped portion 15 is designed to be easily deformed (to be retractable). In addition, in order to ensure the structure stability of the elastic member 6, the extension portion 14 and the U-shaped portion 15 are tightly connected, for example, they may be integrally formed. In addition, as shown in fig. 1, 2, 3, 4 and 5, in order to facilitate the space of the head enough to accommodate the thrust-back small rocket 2, for example, the head 3 includes a flat plate 9 with a curvature and a curved portion 10. The inner side of the flat plate 9 is arranged on the outer surface of the first rocket secondary stage 1 in a fitting mode through a supporting piece, the outer side of the flat plate 9 is connected with one end of the bent arc portion 10, the other end of the bent arc portion 10 is connected with the body portion 4 in a clamping mode, and the bent arc portion 10 is matched with the outer surface of the first rocket secondary stage 1 in shape. In order to connect the plate 9 to the rocket-stage 1 tightly, for example, the side of the plate 9 close to the outer surface of the rocket-stage 1 is connected to the outer surface of the rocket-stage 1 by an adhesive. In order to reduce the gap between the curved part 10 and the body part 4, for example, the outer surface of the curved part 10 at the end away from the flat plate 9 and the inner surface of the body part 4 are closely attached to each other.

In order to facilitate the detachment of the head 3, for example, the side of the plate 9 abutting the surface of the rocket-stage 1 is inclined toward the side connected to the curved portion 10. For example, the inclined plane is mutually perpendicular to the axis of the nozzle of the reverse thrust small rocket 2, the contact area between high-pressure gas sprayed by the nozzle and the inclined plane can be increased, and further the stress of the flat plate is increased, so that the end socket can fall off quickly, and the separation of the first stage and the second stage of the rocket is facilitated.

It should be noted that, as shown in fig. 1, 3, 4, 5, 6, 7, 8, 9, 12, 13 and 14, in order to avoid deformation of the upper part of the head 3 (near the end of the second rocket stage 7) and to avoid displacement movement of the head 3, the head 3 may be supported by a support 16, for example. In the present embodiment, for example, the cross section of the support 16 is L-shaped, and the support 16 includes the first support 11 and the second support 12 which are integrally formed. The upper surface of the first support body 11 is in close contact with the lower surface of the plate 9 (the first support body and the plate can be fixed together by bolts), one side of the second support body 12 is in close contact with the surface of the rocket first sub-stage 1, and one end of the second support body 12, which is far away from the first support body 11, is provided with at least two concave parts 13 which are concave towards the first support body 11. The concave part 13 is used for being fixed on the surface of the first rocket substage 1 through bolts (the concave part 13 is inserted into a stud of the bolt, one end of the stud is in threaded connection with the first substage, and the stud is used for supporting the second supporting body 12), so that the fixing of the supporting piece 16 can be realized, the seal head can be firmly fixed, and the radial movement of the seal head is avoided, namely the opening end of the concave part 13 moves downwards to penetrate through the stud, and a nut which is positioned on the bolt far away from the first rocket substage 1 is used for limiting the radial movement of the concave part (the second supporting body 12 is positioned between the first rocket substage 1 and the nut and can freely move along the axial direction, so that the seal head can be separated).

In addition, in order to ensure the tight connection between the upper part of the end socket 3 and the rocket primary stage surface 1, for example, the gap between the two parts can be bonded by an adhesive.

The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.

Claims

1. A carrier rocket thrust reverser comprising a plurality of thrust reversers arranged uniformly along a circumferential surface of a sub-stage of a rocket, wherein,

the reverse-thrust structure comprises a reverse-thrust small rocket and a cover body arranged outside the reverse-thrust small rocket; the reverse thrust small rocket is fixed with the surface of the first rocket secondary stage, and the nozzle is close to the second rocket secondary stage in the axial direction of the rocket; the cover body comprises an end socket with a clamping piece and a body part with a matching piece, the end socket is matched with the matching piece through the clamping piece, so that the end socket is tightly connected with the body part, the body part is used for being fixedly connected with the surface of a first rocket secondary, and the body part, the end socket and the surface of the first rocket secondary which are clamped with each other form a space for limiting the reverse thrust small rocket;

after the connection of the first rocket substage and the second rocket substage is unlocked, the small reverse-thrust rocket is ignited, the seal head is pushed away from the body by the pressure generated in the space, and the small reverse-thrust rocket enables the first rocket substage to obtain reverse thrust so that the first rocket substage and the second rocket substage are separated from each other.

2. A launch vehicle thrust reverser according to claim 1, wherein the jet rockets of the thrust rocket extend outboard away from a substage of the rocket.

3. A carrier rocket thrust reverser according to claim 1, wherein the locking member is a fixing strip hole provided at a position of the seal head near the body, the engaging member is an elastic member provided at a corresponding position of the body, the elastic member is arranged at the inner side of the body to protrude relative to the inner surface of the body, and the seal head is hung on the elastic member through the fixing strip hole at the inner side of the body to realize locking with the body.

4. A launch vehicle thrust reverser according to claim 3, wherein said elastic member comprises an outward extending portion and a U-shaped portion, said outward extending portion being symmetrically disposed on both sides of the opening of said U-shaped portion and being a structure formed to extend away from both sides of the center of said U-shaped portion.

5. A launch vehicle thrust reverser according to claim 4, wherein the bottom of the U-shaped section is convex to a side adjacent to a sub-stage of the rocket.

6. A launch vehicle thrust reverser according to claim 5, wherein the transition between the bottom of the U-shaped section and the side walls of the U-shaped section is of a circular arc configuration.

7. A launch vehicle thrust reverser according to claim 1, wherein the head comprises a flat plate with a curvature and a curved portion; one side of the flat plate, which is close to the outer surface of the first sub-stage of the rocket, is attached to the outer surface of the first sub-stage of the rocket, the outer side of the flat plate is connected with one end of the bent arc part, the other end of the bent arc part is clamped with the body part, and the bent arc part is matched with the outer surface of the first sub-stage of the rocket in shape.

8. A launch vehicle thrust reverser according to claim 7, wherein the side of the plate adjacent to the outer surface of the rocket stage one is joined to the outer surface of the rocket stage one by an adhesive.

9. A launch vehicle thrust reverser according to claim 7, wherein the outer surface of the curved section at the end remote from the flat plate and the inner surface of the body section abut against each other.

10. A launch vehicle comprising a launch vehicle thrust reverser according to any one of claims 1 to 9.