CN212125565U - Rocket recovery supporting structure - Google Patents

Abstract

The utility model provides a rocket recovery supporting structure, which comprises a hanging rack mechanism and a supporting mechanism used for fixing the hanging rack mechanism, wherein the hanging rack mechanism is positioned at the upper part of the supporting mechanism and is connected with the supporting mechanism through a rotating mechanism, the supporting mechanisms are arranged in the circumferential direction, and the hanging rack mechanism is close to each other and extends towards the central direction enclosed by the supporting mechanisms; and after the hanging rack mechanism is used for contacting with the rocket to be recovered, fixing the rocket to be recovered to finish rocket recovery. Compared with the prior art, the supporting mechanism fixes the rocket to be recovered after contacting the rocket to be recovered, so that the rocket is recovered, the posture and speed requirements on rocket recovery can be reduced in the whole process, and the success rate of rocket recovery is improved.

Description

Rocket recovery supporting structure

Technical Field

The utility model relates to a technical field is retrieved to the rocket, especially relates to a bearing structure is retrieved to rocket.

Background

The rocket recovery technology is a bright pearl in the technical field of aerospace, and is the comprehensive embodiment of the strength of the aerospace technology, so that the rocket recovery technology is also greatly concerned by all aerospace major countries. At present, no liquid rocket recovery scheme which is put into use is available in China. Rocket X, blue origin in the United states, has been used with many successful rocket recoveries. For example, the rocket recovery solution adopted by Space X company in its last few shots is: in the rocket secondary landing process, the main engine is ignited to realize deceleration, and the attitude control engine is used for adjusting the flight attitude of the rocket secondary, so that the rocket is ensured to fall in an approximately vertical attitude. As the falling rocket substage approaches the ground, the support legs, in a collapsed state, open, allowing the rocket to rest stably on a landing surface (e.g., ground or offshore platform).

Specifically, retractable supporting legs are arranged at the bottom of the rocket stage. In the process of rocket flight, the supporting legs can be always in a furled state. After the rocket substages finish working and are separated from the rocket bodies, the main engine is shut down, and the rocket substages fly to a preset landing area or fly back to a launching field. When the rocket approaches the ground, the main engine is ignited again to start, and the rocket is decelerated. Before falling to the ground, the support legs are unfolded and locked under the action of high-pressure gas. The rocket substage is controlled by the main engine to reduce the speed to 0 at the moment of final touchdown, and is stabilized on a recovery site or a recovery ship by the unfolded supporting legs.

The landing leg mechanism is complex in design and heavy (for example, the flying eagle 9 landing mechanism of SPACEX is nearly 3 tons), so that the rocket body transportation capacity is lost. The control requirements on the posture and the speed of the rocket during landing are very high in the recovery process, and if the posture or the speed of the rocket during the sublevel landing is not well controlled, the rocket is likely to topple or explode, so that the recovery of the rocket is completely failed.

Disclosure of Invention

An object of the utility model is to overcome prior art not enough, provide a supporting structure is retrieved to rocket, can be under original recovery track, the unchangeable condition of driving system, supporting mechanism through with wait to retrieve the rocket after contacting, fixed the rocket of waiting to retrieve, accomplish the rocket and retrieve, whole process can reduce gesture and the speed requirement of retrieving the rocket, improves the success rate that the rocket was retrieved.

The utility model provides a rocket recovery supporting structure, which comprises a hanging rack mechanism and a supporting mechanism used for fixing the hanging rack mechanism, wherein the hanging rack mechanism is positioned at the upper part of the supporting mechanism and is connected with the supporting mechanism through a rotating mechanism, the supporting mechanisms are arranged in the circumferential direction, and the hanging rack mechanism is close to each other and extends towards the central direction enclosed by the supporting mechanisms;

and after the hanging rack mechanism is used for contacting with the rocket to be recovered, fixing the rocket to be recovered to finish rocket recovery.

In the same embodiment, the hanging frame mechanism comprises a rotating frame, an adjusting rod and a drag hook; the rotating frame is located on the outer side of the adjusting rod and connected with the adjusting rod through the rotating mechanism, and the drag hook is located at one end, close to the center direction defined by the supporting mechanisms, of the adjusting rod.

In the same embodiment, the draw hook is provided with an anti-drop block.

In the same embodiment, the rotating mechanism is a rotating shaft structure, and the rotating shaft structure penetrates through the rotating frame and the adjusting rod.

In the same embodiment, adjust the pole and contain the shock attenuation bucket and stretch out the frame, it is located to stretch out frame one end in the shock attenuation bucket, the other end with keep away from shock attenuation bucket one side the drag hook is connected, the shock attenuation bucket is hydraulic damping shock attenuation bucket, stretch out the frame be with hydraulic damping shock attenuation bucket complex hydraulic shock-absorbing rod.

In the same embodiment, the hanger mechanism is provided with a shock absorber for protecting the hanger mechanism, the shock absorber is located at the lower part of the hanger mechanism, one end of the shock absorber is connected with the supporting mechanism through a fixing frame, and the other end of the shock absorber is connected with the hanger mechanism.

In the same embodiment, the shock absorber is a hydraulic shock absorber, and the telescopic direction of the hydraulic shock absorber is consistent with the length direction of the supporting mechanism.

In the same embodiment, the number of said support means is between 3 and 6.

In the same embodiment, the support mechanism is vertically disposed on the landing surface.

In the same embodiment, a reinforcing plate is circumferentially arranged at one end of the supporting mechanism, which is far away from the hanging rack mechanism.

The embodiment of the utility model discloses a can be under original recovery track, the unchangeable condition of driving system, supporting mechanism through with treat to retrieve the rocket after contacting, fixed treat to retrieve the rocket, accomplish the rocket and retrieve, whole process can reduce gesture and the speed requirement of retrieving the rocket, improves the success rate that the rocket was retrieved.

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 invention, as claimed.

Drawings

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

FIG. 1 is a schematic diagram of the whole arrow structure and separation of the present invention;

FIG. 2 is a schematic view of the combination of the fixing base, the supporting mechanism and the hanging rack structure of the present invention;

FIG. 3 is a schematic view of the rocket primary and secondary landing hanging rods, the main padlock and the auxiliary padlock of the present invention;

FIG. 4 is a schematic view of a hanging rack structure and a padlock mechanism when landing is completed in a first arrow body stage;

FIG. 5 is a schematic structural view of the auxiliary padlock and the hanging rod of the present invention;

FIG. 6 is a schematic structural view showing the connection between the connecting lock and the first stage of the rocket body and the hanging rod when the hanging rod of the utility model is opened;

FIG. 7 is a top view of the switch mechanism of the present invention connected to the hanging rod clamping seat;

figure 8 is a top view of the curved plate of the present invention.

Description of reference numerals:

1 two-stage rocket body structure and 2 rocket one-stage structure

3 rocket power tail cabin section 4 mounting rack

5 hanging rod and 6 hanging rod clamping seat

7 main padlock 8 posture regulating mechanism

9 fixing seat 10 supporting mechanism

11 rotating frame 12 shock-absorbing barrel

13 extending frame 14 anti-drop block

15 shock absorber 16 connecting lock

17 subsidiary padlock 18 bent plate

19 explosive bolt 20 piston

21 spring 22 groove

23 reinforcing plate

Detailed Description

Reference will now be made in detail to various exemplary embodiments of the invention, which should not be considered limiting of the invention, but rather should be understood to be a more detailed description of certain aspects, features and embodiments of the invention.

It will be apparent to those skilled in the art that various modifications and variations can be made in the 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 existing liquid rocket recovery technology needs to add 4 telescopic supporting legs on the rocket substage and is provided with a set of high-pressure gas actuating mechanism. Among them, the high-pressure gas actuation mechanism is used to deploy the support legs when the rocket substage to be recovered approaches the landing surface, increasing undoubtedly the complexity and structural weight of the rocket system.

In the takeoff stage of the rocket, the additional mechanisms are dead weights which are useless for the flight of the rocket obviously, and the carrying capacity of the rocket is reduced. In addition, with the existing rocket recovery technology, the speed and the attitude of the rocket substage must be accurately controlled during the rocket substage landing process, and the speed of the rocket substage is reduced to 0 at the moment of touchdown, and the attitude is kept vertical. Similarly, when a rocket is recovered at sea, the above-mentioned requirements for recovering a rocket on the ground and the requirements for sea conditions are also high. For example, a hull for rocket recovery cannot swing to a large extent when a substage rocket lands.

The utility model provides a supporting structure is retrieved to rocket can be under original recovery track, the unchangeable condition of driving system, and supporting mechanism is through with wait to retrieve the rocket after contacting, and fixed the rocket of waiting to retrieve accomplishes the rocket and retrieves, and whole process can reduce gesture and the speed requirement of retrieving the rocket, improves the success rate that the rocket was retrieved.

Specifically, the embodiment of the present invention provides a rocket recovery supporting structure, which comprises a hanging rack mechanism and a supporting mechanism 10 for fixing the hanging rack mechanism, wherein the hanging rack mechanism is located on the upper portion of the supporting mechanism 10 and is connected to the supporting mechanism 10 through a rotating mechanism, the supporting mechanism 10 is circumferentially arranged (for example, circumferentially arranged at equal intervals), and the hanging rack mechanism is close to each other and extends toward the central direction enclosed by the supporting mechanisms 10; after the hanging frame mechanism is used for being in contact with the rocket to be recovered, the rocket to be recovered is fixed, and the rocket is recovered.

In this embodiment, the hanging mechanism includes a rotating frame 11, an adjusting rod and a drag hook; the rotating frame 11 is located on the outer side of the adjusting rod and connected with the adjusting rod through the rotating mechanism, and the draw hook is located at one end, close to the center direction enclosed by the supporting mechanisms 10, of the adjusting rod. The rotating frame 11 is a rotating shaft structure, and the rotating shaft structure penetrates through the rotating frame 11 and the adjusting rod. The rotating frame 11 is located outside the rotating shaft, is similar to a protective cover, avoids impurities from entering the rotating shaft, ensures that the surface of the rotating shaft is clean and tidy, and can improve the stability and structural strength of the rotating shaft.

What deserves to mention is that, in order to make the stores pylon structure with wait to retrieve the rocket fixed more firm, prevent simultaneously that the unhook phenomenon from appearing in the rocket of waiting to retrieve, be equipped with anticreep piece 14 on the drag hook, guarantee that the stores pylon structure is connected closely with the rocket of waiting to retrieve, be favorable to the recovery of rocket.

It is particularly noted that in order to facilitate the extension of the adjustment lever according to the actual requirements, for example, the adjustment lever comprises a shock-absorbing barrel 12 and an extension frame 13. One end of the extending frame 13 is positioned in the damping barrel 12, and the other end is connected with the anti-dropping block 14 at one side far away from the damping barrel 12. It is further explained that, in order to make the shock absorbing barrel 12 and the extension frame 13 connect tightly and fix firmly, for example, the shock absorbing barrel 11 is a hydraulic damping shock absorbing barrel, the extension frame 13 is a hydraulic damping rod matched with the hydraulic damping shock absorbing barrel, the hydraulic damping shock absorbing barrel is matched with the hydraulic damping rod to use and is equivalent to a hydraulic structure, the two connect tightly, the extension frame 13 is prevented from separating from the shock absorbing barrel 12 in the stress stretching process, the tensile strength of the adjusting rod is improved, and the safe use of the adjusting rod is ensured. On the other hand, because hydraulic damping shock attenuation bucket and hydraulic shock attenuation pole cooperation, make things convenient for the regulation pole tensile, play the cushioning effect simultaneously.

It is particularly worth mentioning that, in order to improve the stability of the pylon structure and to buffer the force to which the pylon structure is subjected when the pylon structure is connected to the rocket stage, for example, a shock absorber 15 for protecting the pylon structure is provided on the pylon structure. The damper 15 is located at the lower portion of the hanger structure, and one end of the damper 15 is connected to the support mechanism 10 through the fixing frame, and the other end is connected to the hanger structure. In addition, in order to ensure that the shock absorber has high strength, the hanger structure is effectively supported, for example, the shock absorber 15 is a hydraulic shock absorber, and the telescopic direction of the hydraulic shock absorber coincides with the length direction of the support mechanism.

In the present embodiment, as shown in fig. 2, 4 support mechanisms 10 and 4 hanger structures are described as an example, and in actual application, the number of the support mechanisms 10 and the number of the hanger structures provided on the arrow body correspond to each other. According to a large number of simulation experiments, the number of the supporting mechanisms 10 is designed to be A, when A is not less than 3 and not more than 6, the rocket to be recovered can be uniformly stressed, in the recovery process, the rocket to be recovered is effectively prevented from inclining along the axial direction, and the rocket to be recovered is favorable for being intact after being recovered.

In this embodiment, in order to ensure that the supporting mechanism 10 is stable and to facilitate the connection of the pylon structure and the rocket to be recovered, for example, the supporting mechanism 10 is vertically disposed on the landing surface, so that the supporting mechanism 10 is uniformly stressed, and when the pylon structure is in contact with the rocket to be recovered, the supporting mechanism 10 is prevented from inclining, and the success rate of rocket recovery is improved. For example, one end of the supporting mechanism 10, which is far away from the pylon mechanism, can be fixed on the fixing seat 9, the fixing seat 9 is of a circular perforated structure, and one ends of the supporting mechanisms 10 can be embedded into the fixing seat at equal intervals along the circumferential direction, so that the force of the supporting mechanisms 10 in the circumferential direction is increased, the stability of the supporting mechanisms 10 is ensured, the phenomenon that the supporting mechanisms 10 are unevenly stressed and damaged due to the fact that the supporting mechanisms 10 are toppled over to damage the rocket to be recovered is avoided.

As shown in fig. 2 and 4, in order to make the support mechanism 10 more stable. For example, a reinforcing plate 23 is provided circumferentially at an end of the support mechanism 10 remote from the hanger mechanism, and the reinforcing plate 23 supports the bottom of the support mechanism 10, preventing the support mechanism 10 from tilting, and improving the strength of the support mechanism.

In this embodiment, in order to ensure that the action force acting on the rocket to be recovered is uniform when the pylon structure contacts the rocket to be recovered, and to avoid the rocket to be recovered from inclining, for example, the extension line of one end of the pylon structure close to the center of the fixed seat 9 is designed to coincide with the central line of the circumferential arrangement of the support mechanism 10.

The utility model discloses bearing structure is retrieved to rocket can be under original recovery track, the unchangeable condition of driving system, and bearing mechanism is through with wait to retrieve the rocket after contacting, and fixed the rocket of waiting to retrieve accomplishes the rocket and retrieves, and whole process can reduce gesture and the speed requirement of retrieving the rocket, improves the success rate that the rocket was retrieved.

As shown in fig. 1, 3, 5 and 6, the rocket recovery supporting structure of the present application can be used for recovering substage rockets provided with corresponding structures, and the following provides a specific structure of a substage rocket which can be recovered by the supporting device of the present application.

For example, one end of the rocket to be recovered, which is far away from the main engine, is provided with an attitude adjusting mechanism 8 and a padlock mechanism; the posture adjusting mechanism 8 is used for adjusting the landing posture of the substage rocket when the substage rocket returns, so that the padlock mechanism is connected with the hanging rack structure. The utility model discloses

In the same embodiment, the attitude adjusting mechanism 8 includes a grille wing and an attitude control system. Specifically, the grid wings are used for adjusting the flight attack angle and the attitude of the rocket body by changing the shape or the position to adjust the aerodynamic force on the secondary rocket in the landing process of the secondary rocket, so that the secondary rocket is ensured to land according to a preset track and attitude; the attitude control system generates a reaction force in an air injection reverse thrust mode to realize the adjustment of the flight attitude of the sublevel rocket, and ensures that the sublevel rocket contacts the pylon structure at a preset inclination angle.

In the same embodiment, in order to ensure the rocket to be recovered to be intact, the damage of the rocket to be recovered caused by the direct contact with the landing surface is avoided. For example, when the rocket padlock mechanism drives the hanging rack structure to move downwards to the maximum distance, the lower end face of the rocket does not touch the landing face, so that the rocket is ensured to be recovered in a suspended state.

In the same embodiment, as shown in fig. 1, 5 and 6, the padlock mechanism comprises a mounting frame 4, a hanging rod 5, a switch mechanism, a main padlock 7, an auxiliary padlock 17 and a hanging rod clamping seat 6. Wherein, mounting bracket 4 is fixed to be set up on the substage rocket, 5 one end of peg and mounting bracket 4 fixed connection, and the other end passes through on-off mechanism and is connected with peg cassette 6, and main padlock 7 circumference sets up on the substage rocket surface, and vice padlock 17 one end and mounting bracket 4 fixed connection, the other end runs through behind the peg 5 on the axial direction of peg 4 with main padlock 7 fixed connection. That is, the hanging rod 5 may be a hollow cylindrical structure, and the auxiliary padlock 17 is disposed inside the hollow portion of the hanging rod 5, so that the auxiliary padlock 17 may extend from both ends of the hanging rod 5 in the axial direction of the hanging rod 5 and be connected with the mounting frame 4 and the main padlock 7, respectively.

In addition, as shown in fig. 6, in order to limit the deployment angle of the hanging rod 5, for example, the connection lock 16 for connecting the hanging rod is provided on the surface of the sub-stage rocket, and one end of the connection lock 16 is fixedly connected to the sub-stage rocket, and the other end is connected to the hanging rod 5.

When the switch mechanism is opened, the hanging rod 5 is unfolded close to the end of the switch mechanism and far away from the axis direction of the substage rocket, so that the main padlock 7 is connected with the hanging rack structure. For example, during the connection process, the extension of the secondary padlock 17 along the axial direction thereof intersects with the axis of the secondary rocket.

In addition, as shown in fig. 7 and 8, the switch mechanism includes a clip for closing the hanging bar 5 and an ejector for opening the hanging bar 5. Specifically, the clamp comprises a bending plate 18 and an explosion bolt 19, the bending plate 18 is located on the outer side (the side far away from the axis of the secondary rocket) of the hanging rod 5, and the bending plate 18 is connected with the hanging rod clamping seat 6 through the explosion bolt 19. The ejector comprises a piston 20 and a spring 21, and a groove 22 matched with the piston 20 and the spring 21 to move is arranged on the region, corresponding to the bending plate 18, of the hanging rod clamping seat 6. The piston 20 and spring 21 move along the groove 22 and exert a force on the peg 5 away from the secondary rocket, thereby pushing one end of the peg 5 away from the secondary rocket axis and opening the master padlock 7 after the explosive bolt 19 is exploded apart. When the hanging rod 5 needs to be opened, the control signal is used for detonating the explosion bolt 19, so that the bent plate 18 falls off, and meanwhile, the piston 20 is pushed under the elastic force of the spring 21 to apply thrust to the hanging rod 5, so that the hanging rod 5 is unfolded towards the axis direction far away from the substage rocket near the switch mechanism end.

The embodiment of the utility model discloses an embodiment through adopting rocket recovery unit, under original recovery track, the unchangeable condition of driving system, reduces landing mechanism weight by a wide margin, improves the stability when landing, can reduce gesture and the speed requirement of retrieving the rocket, improves the success rate that the rocket retrieved.

In order to increase the strength of the main padlock, the auxiliary padlock 17 and the connecting lock 16 and avoid the breakage of the main padlock, for example, the main padlock 7, the auxiliary padlock 17 and the connecting lock 16 adopt a soft lock woven by Kevlar fibers for bearing all the mass of the arrow body. In order to reduce the weight of the cloth rail 5 and to avoid bending thereof, the cloth rail 5 is, for example, formed by a hollow, thin, hard, rigid metal shell.

The following description of the present application takes the rocket-sub-stage structure as an example, and the other sub-stages are designed in the same way when using this technology.

After the rocket primary-secondary structure 2 is separated from the rocket secondary structure 1, the overturning of the rocket primary-secondary structure 2 is completed through the attitude adjusting mechanism 8 (nitrogen attitude adjusting system). The hanging rod 5 is fixed on the hanging rod clamping seat 6 through clamping, and the arrow body primary-stage structure 2 is about 100mm away from the upper part of the fixed seat 9 through the control of the rudder and the vector engine. When the rocket primary sub-structure 2 decelerates to the speed of about 10m/s, the ejector on the hanging rod clamping seat 6 is started, so that the hanging rod 5 is opened. At the moment, the rocket body one-stage sub-structure 2 is continuously controlled to fall, the posture of the rocket body one-stage sub-structure is adjusted through the nitrogen posture adjusting system, the rocket power tail cabin section 3 is aligned with the center of the fixed seat 9, and when the speed is properly reduced to be below 5m/s, the rocket body one-stage sub-structure 2 is hung on the extending frame 13 through the main padlock 7 to drive the extending frame 13 and the shock absorber 15 to rotate downwards. Meanwhile, the damping barrel 12 and the extension frame 13 perform damping extension in two coupling modes to decelerate and damp the whole arrow body; on the other hand, the damper 15 supports the damper barrel 12 so that the descending speed of the outrigger 13 is reduced. After the main padlock of the sub-stage rocket is hung on the hanging rack in a matching mode, the anti-falling block hooks the main padlock to prevent the arrow body one-sub-stage structure 2 from falling and then being separated due to the fact that the elastic force moves towards one side far away from the center of the fixing seat 9, and finally landing of the arrow body one-sub-stage structure 2 is completed and stable hanging is carried on ground equipment.

The foregoing is only 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 principles of the present invention should fall within the protection scope of the present invention.

Claims (9)

1. A rocket recycling supporting structure is characterized in that: the hanging rack mechanism is positioned at the upper part of the supporting mechanism and is connected with the supporting mechanism through a rotating mechanism, the supporting mechanisms are circumferentially arranged, and the hanging rack mechanisms are close to each other and extend towards the central direction surrounded by the supporting mechanisms;

the hanging rack mechanism is used for fixing the rocket to be recovered after being contacted with the rocket to be recovered, so that rocket recovery is completed;

the hanging frame mechanism comprises a rotating frame, an adjusting rod and a draw hook; the rotating frame is located on the outer side of the adjusting rod and connected with the adjusting rod through the rotating mechanism, and the drag hook is located at one end, close to the center direction defined by the supporting mechanisms, of the adjusting rod.

2. A rocket retrieval support structure according to claim 1, wherein: the draw hook is provided with an anti-drop block.

3. A rocket retrieval support structure according to claim 1, wherein: the rotating mechanism is a rotating shaft structure, and the rotating shaft structure penetrates through the rotating frame and the adjusting rod.

4. A rocket retrieval support structure according to claim 1, wherein: the adjusting rod comprises a damping barrel and an extending frame, one end of the extending frame is located in the damping barrel, the other end of the extending frame is far away from one side of the damping barrel, the drag hook is connected with the damping barrel, the damping barrel is a hydraulic damping barrel, and the extending frame is a hydraulic damping rod matched with the hydraulic damping barrel.

5. A rocket retrieval support structure according to claim 1, wherein: the hanger mechanism is provided with a shock absorber for protecting the hanger mechanism, the shock absorber is positioned at the lower part of the hanger mechanism, one end of the shock absorber is connected with the supporting mechanism through a fixing frame, and the other end of the shock absorber is connected with the hanger mechanism.

6. A rocket retrieval support structure according to claim 5, wherein: the shock absorber is a hydraulic shock absorber, and the telescopic direction of the hydraulic shock absorber is consistent with the length direction of the supporting mechanism.

7. A rocket retrieval support structure according to claim 1, wherein: the number of said support means is between 3 and 6.

8. A rocket retrieval support structure according to claim 7, wherein: the support mechanism is vertically disposed on the landing surface.

9. A rocket retrieval support structure according to claim 7, wherein: one end, far away from the hanging rack mechanism, of the supporting mechanism is circumferentially provided with a reinforcing plate.

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