CN210036456U - Supporting leg and power tail cabin section for rocket landing - Google Patents

Abstract

The utility model discloses a landing leg and power tail cabin section for rocket landing. The landing leg is used for supporting the power tail cabin section when the power tail cabin section lands, and comprises a supporting seat, a connecting rotating shaft and a touch floor. Supporting seat one side is equipped with first bellying, and the opposite side is used for connecting engine installation frame, is equipped with the through-hole on the first bellying, is equipped with the second bellying on contacting the floor, is equipped with the open channel of cooperation through-hole on the second bellying, connects the pivot and will touch the floor and be connected with the supporting seat through running through-hole and open channel to contact the floor configuration and realize drawing in and expanding for the supporting seat through rotating around connecting the pivot. Landing leg is used for being connected and setting up in engine mounting bracket's keeping away from engine nozzle side through engine installation frame and power tail cabin section, compares with prior art, and this structure has reasonable in design, stable in structure, advantages such as the operation of being convenient for.

Description

Supporting leg and power tail cabin section for rocket landing

Technical Field

The utility model relates to a liquid rocket engine field, in particular to landing leg and power tail cabin section for rocket landing.

Background

With the rapid development of the aerospace industry, various technologies related to rockets also realize the rapid advance. Currently, the continuous reduction of rocket manufacturing and launch costs as the only vehicle currently launching satellites into space is a pursuit goal of large commercial space companies.

The rocket recovery is an important means for reducing the launching cost of the rocket, so that the landing leg of the rocket, which is reasonable in design, stable in structure, convenient to operate, safe and reliable, is provided, and the problem to be solved at present is solved.

Disclosure of Invention

The utility model aims at providing a landing leg for rocket has reasonable in design, stable in structure, the operation of being convenient for, advantages such as safe and reliable.

In order to achieve the above object, the utility model provides a following technical scheme: a supporting leg for rocket landing is used for supporting a power tail cabin section when the power tail cabin section lands and comprises a supporting seat, a connecting rotating shaft and a contact floor; the engine mounting support comprises a support seat, a connecting rotating shaft and a supporting seat, wherein a first protruding part is arranged on one side of the support seat, the other side of the support seat is used for being connected with an engine mounting frame, a through hole is formed in the first protruding part, a second protruding part is arranged on the contact floor, an opening channel matched with the through hole is formed in the second protruding part, the connecting rotating shaft penetrates through the through hole and the opening channel to connect the contact floor with the support seat, and therefore the contact floor is configured to be folded and unfolded relative to the support seat through rotating around; the landing support leg is used for being connected with the power tail cabin section through an engine mounting frame, and the landing support leg is used for being arranged on the side, far away from the engine spray pipe, of the engine mounting frame.

Preferably, the connecting shaft is sleeved with a spring, and the spring is tightly attached to the inner side of the second protruding part.

Preferably, the thickness of the end, far away from the connecting rotating shaft, of the touch floor is larger than the thickness of the end, close to the connecting rotating shaft, of the touch floor.

Preferably, the supporting seat comprises a first supporting body, a second supporting body and a telescopic spring body; the one end of first supporter is used for connecting the engine mounting bracket, the flexible spring body both ends respectively with first supporter with the second supporter is connected, first bellying is located one side of second supporter.

Preferably, the power tail cabin section is provided with a groove matched with the floor contact plate, and after the floor contact plate is opened, the part of the ground contact plate is positioned on the inner side of the groove and is tightly attached to the inner side of the groove.

Preferably, first supporter is one end opening, one end confined cavity structure, the second supporter includes the outside matching the cooperation part of cavity structure, the one end fixed connection of the extension spring body in the inboard of blind end, just the other end of the extension spring body is connected the cooperation part.

Preferably, one side of the touch floor, which is far away from the connecting rotating shaft, is an inclined surface which is close to the supporting seat and far away from the supporting seat.

Preferably, the landing leg surface is provided with a layer structure, the layer structure and the landing leg are tightly attached to each other and are in adhesive connection, and the layer structure comprises a flame retardant layer and a waterproof layer.

Preferably, the flame-retardant layer is positioned on the lower surface of the waterproof layer, and the flame-retardant layer and the waterproof layer are in adhesive connection.

The utility model also provides a power tail cabin section contains the landing leg of above arbitrary one.

Compared with the prior art, the beneficial effects of the utility model are that: a landing leg for a rocket is used for supporting a power tail cabin section during landing of the power tail cabin section and mainly comprises a supporting seat, a connecting rotating shaft and a contact floor; because supporting seat one side is equipped with first bellying, and the opposite side is used for connecting the engine mount frame, is equipped with the through-hole on the first bellying, is equipped with the second bellying on the board to touch, is equipped with the cooperation on the second bellying the open passage of through-hole, connect the pivot through running through-hole and open passage will touch the floor and be connected with the supporting seat, thereby touch the floor configuration and be through centering on the rotation of connecting the pivot realizes for drawing in and expanding of supporting seat, when many parallelly connected engines are vertical upwards in the power tail cabin section, expand the landing leg, rotate along connecting the pivot as the center through the board to touch promptly for touch the floor and expand, finally accomplish the support to power tail cabin. In the whole landing process, the stability of the whole power tail cabin section can be ensured, the inclination is avoided, further, the completeness of internal devices is ensured, the recovery of the power tail cabin section is completed, and the whole landing support leg has the advantages of reasonable design, stable structure, convenience in operation, safety and reliability.

Drawings

FIG. 1 is a front view of the landing leg of the present invention;

figure 2 is a left side view of the landing leg of the present invention;

FIG. 3 is a left side view of the supporting seat of the present invention;

FIG. 4 is a front view of the supporting seat of the present invention;

FIG. 5 is a front view of the floor panel of the present invention;

FIG. 6 is a left side view of the floor panel according to the first embodiment of the present invention;

FIG. 7 is a left side view of the touch panel according to the second embodiment of the present invention;

FIG. 8 is a schematic structural view of the connecting shaft and the spring of the present invention;

FIG. 9 is a top view of the fixing hole of the present invention;

FIG. 10 is a front view of the landing platform of the present invention connected to a colloid layer;

fig. 11 is a schematic structural view of the power compartment section of the present invention;

FIG. 12 is a schematic view of the power tail section of the present invention showing the opening of the brake parachute and the turning thereof;

FIG. 13 is a schematic view of the power tail compartment section of the present invention with the main umbrella opened and the air vane adjusted;

figure 14 is a schematic diagram of the landing leg ejected from the power tail capsule section and landing,

fig. 15 is a perspective view of the first support of the present invention;

fig. 16 is a schematic structural view of the first support body, the support seat and the telescopic spring body of the present invention.

Description of reference numerals:

1 rocket one-sub-stage 2 power tail cabin section

3 separation explosion device 4 adjustable tail wing device

5 second controller 6 multiple parallel engines

7 parachute bag 8 parachute fixing bracket

9 engine mounting frame 10 landing leg

11 oxidant main pipeline separating valve 12 fuel main pipeline separating valve

13 deceleration parachute 14 main parachute

15 landing platform 16 support base

17 connecting rotating shaft 18 spring

19 open channel touching floor 20

21 first projection 22 through hole

23 glue layer 24 fixing hole

25 raised post 26 second raised portion

27 first support 28 Telescopic spring body

Detailed Description

To make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the spirit of the present invention will be described in detail with reference to the accompanying drawings, and any person skilled in the art can change or modify the techniques taught by the present invention without departing from the spirit and scope of the present invention after understanding the embodiments of the present invention.

The exemplary embodiments and descriptions of the present invention are provided to explain the present invention, but not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.

As used herein, the terms "first," "second," …, etc. do not denote any order or sequential importance, nor are they used to limit the invention, but rather are used to distinguish one element from another or from another element or operation described in the same technical language.

With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.

As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.

As used herein, "and/or" includes any and all combinations of the described items.

As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. Generally, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.

Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.

Taking rocket recovery as an example, in order to reduce cost, only the power tail section can be recovered. For example, a parachute pack is arranged in the power tail cabin section, and when the power tail cabin section is separated from the rocket primary-secondary stage, the parachute pack is opened to ensure the safe landing of the power tail cabin section, and then the recovery of the power tail cabin section is completed. In order to make the landing of the power tail cabin section more stable and ensure the integrity of internal devices, landing support legs can be designed in the power tail cabin section. By unfolding the landing support legs when the power tail cabin section is recovered, the direct contact between the power tail cabin section and a landing point can be avoided, so that the internal devices are ensured to be intact, and the recovery of the power tail cabin section is completed. Can be reused after being cleaned, maintained and tested. In order to effectively utilize the space, the landing leg can be designed into a folding structure, and in order to support the power tail cabin section, the leg in the folding state needs to be unfolded to ensure the stable landing of the power tail cabin section.

Referring to fig. 1, 2, 3, 4, 5, 7, 8 and 11, an embodiment of the present invention provides a landing leg for rocket landing, which includes a landing leg 10 located at the power tail section 2, the landing leg is connected to the power tail section 2 through an engine mount frame 9, and the landing leg 10 is located at an upper portion of the engine mount frame 9 (i.e., an opposite side of the engine mount frame from the side where the engine is mounted). Wherein: the landing leg 10 comprises a support base 16, a connecting rotating shaft 17, a spring 18 and a ground contact plate 19; the supporting seat 16 is provided with a first protruding portion 21 on one side, a protruding column 25 on the other side (the protruding column can be used for connecting with the engine mounting bracket 9), a through hole 22 is formed in the first protruding portion 21, a second protruding portion 26 is connected to the ground contact plate 19, an opening channel 20 is formed in the second protruding portion 26, and the connecting rotating shaft 17 penetrates through the through hole 22 and the opening channel 20, so that the ground contact plate 19 can rotate relative to the supporting seat 16 around the connecting rotating shaft 19, and opening and closing are achieved. For example, both ends of the connecting rotation shaft 17 may be fixed by fixing nuts. When the landing leg 10 is in the closed state, the surface of the ground contact plate 19 abuts the support base 16. The landing leg 10 may have its end in contact with the ground, acting as a buffer for the power pod section, in the fully open position, i.e. after the ground contact plate 19 has been rotated outwards, for example 180 degrees, about the connecting shaft 17 under the influence of gravity. For example, the spring 18 may be sleeved on the connecting rotating shaft 17, and two ends of the spring may be tightly attached to the inner side of the second protruding portion 26, so as to improve the reliability of the landing leg in opening and supporting, the landing leg 10 is used for being connected with the power tail cabin section 2 through the engine mounting frame 9, and the landing leg 10 is used for being disposed on the side of the engine mounting frame 9 away from the engine nozzle.

Specifically, the method comprises the following steps: the landing leg 10 is composed of a support base 16, a connecting rotating shaft 17, a spring 18 and a floor contact plate 19. Since the connecting rotary shaft 17 penetrates the through hole 22 and the opening passage 20, and both ends are provided with fixing nuts. The effective fixed connection pivot 17 of fixation nut prevents to connect pivot 17 and appears rocking, avoids first bellying 21 and second bellying 21 to drop from connecting pivot 17 simultaneously. Since the open channel 20 is located on the second protruding portion 26, the second protruding portion 26 can rotate freely around the connecting rotation shaft 17, which is convenient for opening by touching the floor. Meanwhile, the spring 18 is positioned on the outer side of the connecting rotating shaft 17, two ends of the spring are tightly attached to the inner side of the second protruding portion 26, the power tail cabin section 2 is connected with the rocket primary sub-stage 1 through the explosion separation device 3, the explosion separation surface is positioned between the bottom of the storage tank of the rocket primary sub-stage 1 and the power tail cabin section 2, and when the power tail cabin section is not separated, the explosion separation surface can extrude the ground contact plate, so that the ground contact plate is compressed and is in a furled state. When the power tail cabin section 2 is separated from the rocket first substage 1, namely the rocket first substage 1 is separated from the upper part of the power tail cabin section 2 along the explosion separation surface, the ground contact plate is unfolded under the action of the spring 18. Namely, on one hand, the spring 18 can assist the supporting seat 16 and the ground contact plate 19 to bounce off, so that the ground contact plate 19 can conveniently rotate around the connecting rotating shaft 17; on the other hand, the touch floor 19 can be surely and stably touched to the landing surface. Meanwhile, the spring 18 can be effectively fixed by the mutual close contact between the spring and the inner side of the second bulge 26, and the displacement movement of the spring 18 is avoided. For example, when a plurality of parallel engines 7 in the power pod 2 are vertically upward through the parachute kit 7, the landing legs 10 are unfolded, that is, the landing legs are rotated by the floor contact 19 around the connecting rotating shaft 19, so that the floor contact is unfolded, and finally the support of the power pod is completed. In whole landing process, can guarantee that whole power tail cabin section 2 is stable, avoid taking place the slope, and then guarantee that inside device is intact, accomplish the recovery of power tail cabin section 2, whole landing leg 10 has reasonable in design, stable in structure, the operation of being convenient for, safe and reliable, explosion separation device 3 contains explosion bolt and circular stationary blade in addition, makes rocket one grade 1 and power tail cabin 2 section separation through detonating explosion bolt.

In the first embodiment of the present invention, as shown in fig. 7 and 12, the thickness of the touch panel 19 away from the end of the connection shaft 17 is larger than the thickness of the connection shaft 19. Because the thickness of the end, far away from the connecting rotating shaft 17, of the touch floor 19 is greater than the thickness of the end, close to the connecting rotating shaft 17, of the touch floor 19, the center of gravity of the touch floor 19 is not on the same straight line with the center of the supporting seat, and the center of gravity is located on the side, far away from the power tail cabin section 2. When the power tail cabin section is turned over (the nozzle of the engine is upward), the floor 19 rotates downwards by taking the connecting rotating shaft 17 as the center under the action of gravity in the vertical direction, and forms a certain included angle with the supporting seat 16. According to the stress analysis, the structure decomposes the gravity of the whole power tail cabin section, reduces the force of the power tail cabin section 2 in the vertical direction, and is favorable for enabling the power tail cabin section 2 to land stably.

The present invention also relates to a second embodiment, which is further improved from the first embodiment, as shown in fig. 7, fig. 11, fig. 15 and fig. 16. Specifically, the supporting base 16 further includes a first supporting body 27 and a telescopic spring body 28, and two ends of the telescopic spring body 28 are respectively connected to the first supporting body 27 and the protruding column 25 disposed on the supporting base 16. Also, one end of the support base 16 may be fixed to the engine mount. The power pod section 2 may be correspondingly grooved. When the touch floor 19 is rotated around the connecting shaft 17 to be opened, the part of the touch floor 19 is positioned inside the groove and is tightly attached to the inside of the groove. During the whole falling process of the power tail cabin section, when one end of the floor contact plate 19 is in contact with the ground, the telescopic spring body 28 is gradually compressed, so that the floor contact plate 19 drives the supporting seat 16 to move upwards until the shell of the power tail cabin section 2 is in direct contact with the ground. Touch floor 19 on the one hand and play cushioning effect, on the other hand, expand the back, owing to touch floor 19 one end and be located and keep away from power tail cabin section 2 shell one side, increased the support area, and then make more steady from power tail cabin section 2, avoid it to take place to rock and produce and empty the phenomenon.

Specifically, the first support 27 may have a hollow structure and one end is closed. The outer side of the support base 16 may comprise a shape that fits inside the cavity of the first support 27, i.e. a portion of the support base 16 is arranged inside the cavity structure in a matching manner (the protruding stud 25 is arranged at the end of the portion of the support base 16) and another portion is used for fitting against the floor 19 and for fixed connection with the engine mounting bracket. When the support base 16 is subjected to a force in the vertical direction, it can move relative to the first support body 27, i.e. the part of the support base 16 located in the cavity moves relative to the cavity structure. For example, when the ground contact plate 19 is subjected to a vertical upward force after contacting the ground, the support base 16 can be driven to move in the first support body 27 (i.e., retract toward the interior of the power tail section 2) until the end of the housing of the power tail section 2 contacts the ground.

It should be noted that, as shown in fig. 3 and 4, in the present embodiment, in order to make the connection between the first protruding portion 21 and the supporting seat 16 more tight, the two portions may be welded. In the present embodiment, the first protruding portion 21 and the support seat 16 are independent components, but in the practical application, in order to make the connection between the first protruding portion 21 and the support seat 16 more tight and firm, the two portions may be designed to be integrally formed, and the process will not be described here.

It is worth mentioning that, as shown in fig. 3 and 7, in order to facilitate the fixing of the protruding column 25, the outer shape of the protruding column 25 is designed to be a cylindrical structure. Meanwhile, in order to ensure the structural stability of the first boss 21, the shape thereof is similar to a rectangular parallelepiped structure. In order to ensure the stability of the touch floor 19 and to facilitate the unfolding, the shape thereof is shaped like a trapezoid. Meanwhile, in order to facilitate the free rotation of the second boss 26, the outer shape of the second boss 26 is designed to be a semicircular structure.

In this embodiment, as shown in fig. 11, the entire rocket may contain a rocket stage 1, a power pod section 2 and a separate explosive device 3. The power pod section 2 may comprise a housing, a plurality of parallel engines 6, an engine mount 9 and an adjustable tail device. The multiple parallel engines 6 and the engine mounting frame 9 are all positioned in the shell, the engine mounting frame 9 is positioned at the upper parts of the parachute pack 7, the parachute fixing support 8 and the multiple parallel engines 6 (under the condition that the rocket is upright in the forward direction). Namely, the parachute pack 7, the parachute fixing bracket 8 and the plurality of parallel engines 6 are all arranged on the same side of the engine mounting frame 9. The two ends of the parachute fixing support 8 are respectively connected with the parachute bag 7 and the engine mounting support 9. For example, the parachute mounting bracket 8 may be located on a centerline of the engine mount frame 9 and near one side of the plurality of parallel engines 6, one end of the plurality of parallel engines 6 being connected to the engine mount frame 9 and the nozzle opening facing the other end away from the engine mount frame 9. The adjustable tail device comprises an adjustable tail device 4 and a second controller 5, wherein the second controller 5 is used for controlling the adjustable tail device 4 to rotate.

It should be noted that, as shown in fig. 11, the parachute package 7 is fixed to the power trunk section 2 by the parachute fixing bracket 8.

It should be particularly noted that, as shown in fig. 2, 9, 11 and 13, in order to facilitate adjustment of the position of the landing leg 10 and to facilitate fixing, a plurality of fixing holes 24 are provided in the engine mount frame 9. The raised posts 25 may be disposed within the securing holes 24 to facilitate securing the raised posts 25, thereby allowing the landing leg 10 to be securely secured.

As shown in fig. 11, in order to reduce the cost, an oxidant main line separation valve 11 and a fuel main line separation valve 12 are provided in the casing of the power tail section, so that the oxidant main line separation valve and the fuel main line separation valve are collectively recovered when the power tail section is recovered, thereby realizing the reuse and reducing the cost. For example, the oxidant line and the fuel line may be separable bayonet lines.

The present invention also relates to a third embodiment, as shown in fig. 6, 8 and 11, which is an alternative to the first embodiment, and is a floor panel 19. Specifically, in the present embodiment, when the floor contact plate 19 is in the collapsed state, the side of the floor contact plate 19 away from the connecting rotation shaft 17 is an inclined surface that is inclined from the side close to the support base 16 toward the side away from the support base 16. The inclined surface directly engages the landing surface when the ground engaging plate 19 is in contact with the ground. According to the embodiment of the invention, one side of the floor contact plate 19, which is far away from the connecting rotating shaft 17, is arranged to be the inclined surface, so that the area of the floor contact plate 19 and the contact surface can be increased, a supporting inclined angle towards the outer side of the power tail cabin section is provided, friction is increased, the support stability of the floor contact plate 19 is facilitated, the safety and stability of the power cabin section 2 are ensured, and the inclination of the power cabin section is avoided.

It should be noted that, as shown in fig. 11, the landing leg 10 may be changed according to the landing environment, and when the power tail section 2 lands on the sea, the landing leg 10 may be changed into a floating valve, and the process is not described.

In particular, as shown in fig. 11, in the recovery process of the power tail section 2, in order to position the position of the power tail section 2 conveniently, a navigation positioner may be disposed in the casing, so that the position change of the power tail section 2 is monitored in real time through communication between the navigation positioner and a ground signal receiver.

In this embodiment, as shown in fig. 12 and 13, the parachute package 7 includes a speed reducer 13 and a main parachute 14, the speed reducer 13 may be located outside the main parachute 14, and the two may not interfere with each other when opened, the speed reducer 13 is used to adjust the attitude of the power pod 2 and perform a speed reduction function, so as to make the power pod 2 in a vertical state, the first controller is used to control the opening of the parachute package, when the engine of the power pod 2 faces away from the ground and is vertical to the ground, the first controller controls the opening of the main parachute 14, and the main parachute 14 is used to decelerate the power pod 2, thereby ensuring the recovery of the whole device.

As shown in fig. 10 and 14, in order to ensure safe recovery of the power tail section 2, a landing platform 15 may be installed at the landing of the power tail section 2. In the present embodiment, the landing platform 15 may have a square structure in its outer shape. In practical applications, the landing platform 15 may also be rectangular, circular, diamond-shaped, etc., and will not be described herein. It should be noted that, in order to reduce the pressure between the power pod 2 and the landing platform 15, a glue layer 25 may be provided on the upper surface of the landing platform 15. The colloid layer 25 plays a role of buffering when the power tail cabin section descends, and further the landing safety of the power tail cabin section 2 is guaranteed. Further, in order to prevent the colloid layer 25 from moving, the colloid 25 and the landing platform 15 are closely attached to each other and are adhesively connected.

It should be noted that, as shown in fig. 11, the power nacelle section 2 includes an engine frame 9 and a parachute fixing bracket 8, one end of the parachute fixing bracket 8 is fixedly connected to the engine frame 9 near the engine nozzle side, and the other end is used for installing the parachute pack 7.

As shown in fig. 1, in order to facilitate the connection of the connecting shaft 17 with the through hole 22 and the open channel 20, the through hole 22 and the open channel 20 have the same opening direction and the same inner diameter.

The utility model also provides a power tail cabin section contains the landing leg that is used for the rocket above.

In the present embodiment, it is worth mentioning that the connection means includes a screw connection, welding, riveting, etc., and will not be described in detail herein.

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 (10)

1. A landing leg for a rocket is used for supporting a power tail cabin section when the power tail cabin section lands and is characterized in that the landing leg comprises a supporting leg body, a supporting leg body and a supporting leg;

comprises a supporting seat, a rotating shaft and a floor; the engine mounting support comprises a support seat, a connecting rotating shaft and a supporting seat, wherein a first protruding part is arranged on one side of the support seat, the other side of the support seat is used for being connected with an engine mounting frame, a through hole is formed in the first protruding part, a second protruding part is arranged on the contact floor, an opening channel matched with the through hole is formed in the second protruding part, the connecting rotating shaft penetrates through the through hole and the opening channel to connect the contact floor with the support seat, and therefore the contact floor is configured to be folded and unfolded relative to the support seat through rotating around;

the landing support leg is used for being connected with the power tail cabin section through an engine mounting frame, and the landing support leg is used for being arranged on the side, far away from the engine spray pipe, of the engine mounting frame.

2. A leg for rocket landing according to claim 1, wherein; the connecting shaft is sleeved with the spring, and the spring is tightly attached to the inner side of the second boss.

3. A leg for rocket landing according to claim 1, wherein; the touch floor is far away from the thickness of one end of the connecting rotating shaft is larger than the thickness of one end of the connecting rotating shaft.

4. A leg for rocket landing according to claim 1, wherein; the supporting seat comprises a first supporting body, a second supporting body and a telescopic spring body; the one end of first supporter is used for connecting the engine mounting bracket, the flexible spring body both ends respectively with first supporter with the second supporter is connected, first bellying is located one side of second supporter.

5. A leg for rocket landing according to claim 1, wherein; the power tail cabin section is provided with a groove matched with the touch floor, and when the touch floor is opened, the part of the ground contact plate is positioned on the inner side of the groove and is tightly attached to the inner side of the groove.

6. A leg for rocket landing according to claim 4, wherein; first supporter is one end opening, one end confined cavity structure, the second supporter includes the outside matches the cooperation part of cavity structure, the one end fixed connection of the extension spring body in the inboard of blind end, just the other end of the extension spring body is connected the cooperation part.

7. A leg for rocket landing according to claim 1, wherein; in a furled state, one side of the touch floor, which is far away from the connecting rotating shaft, is an inclined plane which is close to the supporting seat and far away from the supporting seat.

8. A leg for rocket landing according to claim 1, wherein; the landing leg comprises a landing leg body and a landing leg body, wherein the landing leg body is provided with a layer body structure on the surface, the layer body structure is tightly attached to the landing leg body, the landing leg body and the layer body structure are in adhesive connection, and the layer body structure comprises a flame-retardant layer and a waterproof layer.

9. A leg for rocket landing according to claim 8, wherein; the flame-retardant layer is positioned on the lower surface of the waterproof layer, and the flame-retardant layer and the waterproof layer are in adhesive connection.

10. A power pod section comprising a leg for rocket landing according to any one of claims 1-9.

Images