A rocket recovery device capable of two-stage parachute deployment

Abstract

The application discloses a rocket recovery device capable of realizing two-stage parachute opening in the field of aerospace, and relates to a rocket recovery device capable of realizing two-stage parachute opening, which comprises a parachute cabin and a parachute cover, and is characterized in that: the parachute cabin adopts a hollow structure and is divided into two layers, and a deceleration parachute is arranged in each of the two layers; the deceleration parachute is controlled to be opened through the parachute cover; the bottom of the parachute cabin is sealed, the top and the two layers are fixedly provided with the parachute cover, the upper deceleration parachute is controlled to fall off through the parachute cover between the two layers of the parachute cabin, a control line box is embeddedly arranged on the side wall of the parachute cabin, the control line box controls the connection between the parachute cabin and the parachute cover, the control line box is connected with the outside through a communication line and receives control instructions; the application is fixed through a buckle mode, and the cost is lower through a two-stage opening and one-stage automatic separation mode, and the structure is simplified.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to a rocket recovery device capable of achieving second-stage parachute deployment. Background Technology

[0002] With the rapid development of reusable spacecraft technology, the precise recovery and landing area control of rocket debris has become a research hotspot. Traditional uncontrolled descent methods result in a wide dispersion of large components such as fairings and boosters, posing safety risks and increasing recovery costs. To address this, parachute recovery technology has emerged, using a deceleration chute to stabilize attitude and provide initial deceleration, followed by the maneuverability of a large parachute to achieve a pinpoint landing. However, the high-temperature thermal environment of reentry places stringent requirements on the parachute compartment structure, hoisting point device, and deployment sequence. Existing technologies have gradually solved key challenges such as high load-bearing capacity, heat protection, and precise separation through parachute-rocket ejection deployment, high-temperature resistant material protection, and multi-stage parachute descent program control.

[0003] Current technology typically uses explosive bolts to launch the primary parachute while the secondary main parachute opens, preventing the parachute lines from tangling. This method is costly. Therefore, this invention uses a snap-fit ​​structure to allow the primary parachute lines to detach naturally. Summary of the Invention

[0004] The purpose of this invention is to provide a rocket recovery device that can achieve second-stage parachute deployment, so as to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a rocket recovery device capable of two-stage parachute deployment, comprising a parachute compartment and a parachute cover. The parachute compartment has a hollow structure and is divided into upper and lower layers. Deceleration parachutes are installed inside the upper and lower layers respectively. The deceleration parachutes are opened by the parachute cover. The bottom of the parachute compartment is sealed, and the parachute cover is fixedly installed between the top and the upper and lower layers. The upper deceleration parachute is detached by the parachute cover between the upper and lower layers of the parachute compartment. A control box is embedded in the side wall of the parachute compartment. The control box controls the connection between the parachute compartment and the parachute cover. The control box is connected to the outside via a communication line and receives control commands.

[0006] Furthermore, the parachute compartment has a cylindrical structure and is divided into upper and lower layers with different diameters, with the upper layer having a larger diameter than the lower layer.

[0007] Furthermore, the canopy consists of a primary canopy and a secondary canopy. The primary canopy is installed on the top of the canopy compartment, and the secondary canopy is installed at the bottom of the upper canopy compartment. The connection between the primary and secondary canopies and the upper canopy compartment is controlled by a control box.

[0008] Furthermore, the deceleration parachute has two parts, which are placed in the upper and lower parachute compartments respectively. They are fixed by a primary parachute suspension point and a secondary parachute suspension point, respectively. The primary parachute suspension point is located between the parachute compartment and the secondary parachute canopy, and the secondary parachute suspension point is located at the top of the side wall of the parachute compartment.

[0009] Furthermore, the primary umbrella suspension point is snapped between the umbrella compartment and the secondary umbrella canopy. The middle part of the primary umbrella suspension point is located between the umbrella compartment and the secondary umbrella canopy, the upper part is located in the upper umbrella compartment, and the lower part is located in the lower umbrella compartment. The upper part of the primary umbrella suspension point is provided with a connecting hole, and the lower part of the primary umbrella suspension point is provided with a protrusion that is installed in conjunction with the groove of the lower umbrella compartment. The upper part of the protrusion is an inclined structure.

[0010] Furthermore, the primary canopy and the secondary canopy are respectively fixed to the canopy compartment with nylon rivets.

[0011] Furthermore, it also includes a metal support component, which is fixedly mounted on the secondary canopy by screws.

[0012] Furthermore, a limiting groove is provided at the top of the side wall of the lower parachute compartment, and a metal support is installed in the limiting groove.

[0013] Furthermore, the limiting groove at the top of the side wall of the lower parachute compartment is a ring groove structure, and the metal support adopts a circular ring structure.

[0014] Furthermore, the working method is as follows: Step 1: The control box receives the command to open the upper deceleration chute, and uses electric arc ignition to detach the first-stage canopy, causing the upper chute to eject and deploy. Step 2: When the control box receives the command to open the lower deceleration chute, it uses electric arc ignition to detach the secondary canopy, causing the lower chute to launch and unfold. The secondary canopy detaches from the metal support, and the primary chute suspension point loses the pressure from the secondary canopy and the metal support, allowing it to be carried out by the upper chute, thus unfolding the lower chute.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: Compared with the traditional detachment method, the present invention uses a snap-fit ​​method for fixing and a two-stage opening and one-stage automatic detachment method, which is less costly and simplifies the structure. By detaching the second-stage canopy, the detachment of the first-stage canopy can be controlled, allowing two canopies to be assembled in one canopy compartment at the same time. The second-stage canopy acts as a separator, eliminating the need for two separate canopy compartments to stack them simultaneously. Existing parallel canopy compartments cannot control the center of gravity in practical applications. Another advantage of stacking is that the center of gravity of the two canopies after opening can be controlled to be on the central axis.

[0016] Of course, any product implementing this invention does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a cross-sectional view of the present invention; Figure 3 This is a diagram of the internal structure of the present invention; Figure 4 This is a structural diagram of the primary umbrella suspension point of the present invention.

[0019] The attached diagram lists the components represented by each number as follows: 1. Parachute compartment; 2. Primary parachute canopy; 3. Secondary parachute canopy; 4. Primary parachute hoisting point; 5. Secondary parachute hoisting point; 6. Metal support components; 7. Control box cover; 8. Communication cable. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] Please see Figures 1-4 This invention provides a technical solution: a rocket recovery device capable of two-stage parachute deployment, comprising a parachute compartment 1 and a parachute cover. The parachute compartment 1 has a hollow structure and is divided into upper and lower layers. Deceleration parachutes are installed inside the upper and lower layers respectively. The deceleration parachutes are opened by the parachute cover. The bottom of the parachute compartment 1 is sealed, and the parachute cover is fixedly installed between the top and the upper and lower layers. The upper deceleration parachute is detached by the parachute cover between the upper and lower layers of the parachute compartment 1. A control box 7 is embedded in the side wall of the parachute compartment 1. The control box 7 controls the connection between the parachute compartment 1 and the parachute cover. The control box 7 is connected to the outside via a communication line 8 and receives control commands.

[0022] The parachute compartment 1 is a cylindrical structure and is divided into two layers with different diameters, the upper layer having a larger diameter than the lower layer.

[0023] The canopy consists of a primary canopy 2 and a secondary canopy 3. The primary canopy 2 is installed on the top of the canopy compartment 1, and the secondary canopy 3 is installed at the bottom of the upper canopy compartment 1. The connection between the primary canopy 2 and the secondary canopy 3 and the upper canopy compartment 1 is controlled by the control box 7.

[0024] The deceleration parachute has two parts, which are placed in the upper and lower parachute compartments 1 respectively. They are fixed by a primary parachute suspension point 4 and a secondary parachute suspension point 5 respectively. The primary parachute suspension point 4 is located between the parachute compartment 1 and the secondary parachute cover 3, and the secondary parachute suspension point 5 is located at the top of the side wall of the parachute compartment 1.

[0025] The primary umbrella suspension point 4 is snapped between the umbrella compartment 1 and the secondary umbrella cover 3. The middle part of the primary umbrella suspension point 4 is located between the umbrella compartment 1 and the secondary umbrella cover 3, the upper part is located in the upper umbrella compartment 1, and the lower part is located in the lower umbrella compartment 1. The upper part of the primary umbrella suspension point 4 is provided with a connecting hole, and the lower part of the primary umbrella suspension point 4 is provided with a protrusion that is fitted with the groove of the lower umbrella compartment 1. The upper part of the protrusion is an inclined structure.

[0026] The primary canopy 2 and the secondary canopy 3 are respectively fixed to the canopy compartment 1 by nylon rivets.

[0027] It also includes a metal support 6, which is fixedly installed on the secondary umbrella cover 3 by screws.

[0028] The lower parachute compartment 1 has a limiting groove at the top of its side wall, and the metal support 6 is installed in the limiting groove.

[0029] The metal support 6 limits the position of the secondary canopy 3 on the canopy compartment 1.

[0030] The limiting groove at the top of the side wall of the lower parachute compartment 1 can be a ring groove structure or multiple grooves, and the metal support can adopt a circular ring structure or other structures with three-position grooves.

[0031] The working method is as follows: Step 1: When the control box 7 receives the command to open the upper deceleration parachute, it uses electric arc ignition to detach the first-stage parachute cover 2, and the upper parachute is ejected and deployed. Step 2: When the control box 7 receives the command to open the lower deceleration parachute, it uses electric arc ignition to detach the secondary parachute cover 3, and the lower parachute is ejected and unfolded; the secondary parachute cover 3 detaches from the metal support 6, and the primary parachute suspension point 4 loses the pressure of the secondary parachute cover and the metal support and is carried out by the upper parachute, and the lower parachute unfolds. The design principle adopts a compression snap-fit ​​mechanism, such as... Figure Three Figure Four As shown, the primary parachute suspension point 4 is inserted into the slot of the parachute compartment 1, and the secondary parachute canopy 3 and metal support 6 are placed into the parachute compartment 1. The side walls press against the suspension point to secure it. Then, nylon rivets are used to fix the secondary parachute canopy 3 to the parachute compartment 1. After the primary parachute compartment 2 opens, the primary parachute suspension point 4 is subjected to an upward pulling force. Due to the compression from the secondary parachute canopy 3 and metal support 6, the suspension point 4 cannot disengage from the slot of the parachute compartment 1, thus achieving the fixation of the primary parachute suspension point 4. Compared with explosive bolts, which achieve normal detachment of the primary parachute before the secondary parachute opens by causing the bolt to break through explosive force, explosive bolts are more expensive but the technology is more mature, so explosive bolts are commonly used in this field.

[0032] Another advantage is the simplification of the structure. By detaching the secondary canopy 3, the detachment of the primary canopy can be controlled, and two umbrellas can be assembled in one canopy compartment 1 at the same time. The secondary canopy 3 separates the two canopy compartments 1, eliminating the need to stack them at the same time. The existing parallel canopy compartments 1 cannot control the center of gravity in practical applications. Another advantage of stacking is that the center of gravity of the two umbrellas after opening can be controlled to be on the central axis.

[0033] The design principle of the chamfered structure: When the secondary canopy 3 is detached, the primary canopy suspension point 4 is subjected to an upward vertical pull and a rightward force, which facilitates the suspension point to quickly detach from the canopy compartment 1 slot, avoids detachment pauses due to excessive pull, prevents the secondary canopy from getting tangled with the primary canopy, and greatly improves the reliability of opening the canopy.

[0034] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0035] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A rocket recovery device capable of achieving two-stage parachute deployment, comprising a parachute compartment and a parachute canopy, characterized in that: The parachute compartment has a hollow structure and is divided into upper and lower layers. Deceleration parachutes are installed inside the upper and lower layers respectively. The deceleration parachutes are opened by a canopy. The bottom of the parachute compartment is sealed, and the canopy is fixedly installed between the top and the upper and lower layers. The upper deceleration parachute is detached by the canopy between the upper and lower layers of the parachute compartment. The control box is embedded in the side wall of the parachute compartment. The control box controls the connection between the parachute compartment and the canopy. The control box is connected to the outside through a communication line and receives control commands.

2. The rocket recovery device capable of achieving two-stage parachute opening according to claim 1, characterized in that: The parachute compartment is a cylindrical structure and is divided into upper and lower layers with different diameters, with the upper layer having a larger diameter than the lower layer.

3. The rocket recovery device capable of achieving two-stage parachute opening according to claim 1, characterized in that: The canopy consists of a primary canopy and a secondary canopy. The primary canopy is installed on the top of the canopy compartment, and the secondary canopy is installed at the bottom of the upper canopy compartment. The connection between the primary and secondary canopies and the upper canopy compartment is controlled by a control box.

4. A rocket recovery device capable of achieving two-stage parachute deployment according to claim 1, characterized in that: The deceleration parachute has two parts, which are placed in the upper and lower parachute compartments respectively. They are fixed by a primary parachute suspension point and a secondary parachute suspension point. The primary parachute suspension point is located between the parachute compartment and the secondary parachute canopy, and the secondary parachute suspension point is located at the top of the side wall of the parachute compartment.

5. A rocket recovery device capable of achieving two-stage parachute deployment according to claim 4, characterized in that: The primary umbrella suspension point is connected between the umbrella compartment and the secondary umbrella canopy. The middle part of the primary umbrella suspension point is located between the umbrella compartment and the secondary umbrella canopy, the upper part is located in the upper umbrella compartment, and the lower part is located in the lower umbrella compartment. The upper part of the primary umbrella suspension point is provided with a connecting hole, and the lower part of the primary umbrella suspension point is provided with a protrusion that is installed in conjunction with the groove of the lower umbrella compartment. The upper part of the protrusion is an inclined structure.

6. A rocket recovery device capable of achieving two-stage parachute opening according to claim 3, characterized in that: The primary and secondary canopies are fixed to the canopy using nylon rivets.

7. A rocket recovery device capable of achieving two-stage parachute opening according to claim 1, characterized in that: It also includes a metal support component, which is fixedly installed on the secondary canopy by screws.

8. A rocket recovery device capable of achieving two-stage parachute deployment according to claim 7, characterized in that: The top of the side wall of the lower parachute cabin is provided with a limiting groove, and the metal support is set in the limiting groove.

9. A rocket recovery device capable of achieving two-stage parachute deployment according to claim 7, characterized in that: The limiting groove at the top of the side wall of the lower parachute cabin is a ring groove structure, and the metal support adopts a circular ring structure.

10. A rocket recovery device capable of achieving two-stage parachute deployment according to any one of claims 1-9, wherein the working method is as follows: Step 1: The control box receives the command to open the upper deceleration chute, and uses electric arc ignition to detach the first-stage canopy, causing the upper chute to eject and deploy. Step 2: When the control box receives the command to open the lower deceleration chute, it uses electric arc ignition to detach the secondary canopy, causing the lower chute to launch and unfold. The secondary canopy detaches from the metal support, and the primary chute suspension point loses the pressure from the secondary canopy and the metal support, allowing it to be carried out by the upper chute, thus unfolding the lower chute.

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