A segmented high-temperature resistant oil-based deceleration parachute device

Abstract

This invention discloses a segmented high-temperature resistant oil-based deceleration parachute device, belonging to the category of rocket first-stage recovery deceleration and heat insulation equipment. It includes a housing cylinder, segmented two-stage parachutes, a timing deployment controller, a 1200℃ high-temperature resistant oil-based protective coating, and a multi-parallel base. The timing controller controls the parachute to open segment by segment in a step-by-step manner, reducing the impact of instantaneous parachute opening. The second-stage parachute is coated with an oil-based heat-insulating coating to isolate the supersonic re-entry high-temperature airflow and prevent parachute ablation. Multiple parachutes can be assembled in parallel, with a load-bearing capacity suitable for recovering medium-sized propulsion modules weighing 22 to 25 tons. This device features a time-sharing activation logic; the parachute opens only after the rocket body completes lateral separation of the modules and establishes a safe distance of 1.2 times the outer diameter. The propulsion module, due to its large inertia, falls forward, while the separated modules, due to wind resistance, naturally lag behind, utilizing the natural speed difference to completely eliminate the risk of module collision and entanglement. This invention can completely replace the grid fin and vertical thrust reverser deceleration system, with a simple structure, low maintenance cost, and high recovery safety, making it suitable for the non-destructive recovery of large and medium-sized civilian reusable rockets at sea.

Description

Technical Field

[0001] This invention belongs to the field of rocket recovery deceleration equipment technology, and is suitable for deceleration and heat insulation of the first stage of various reusable launch vehicles. The basic configuration of the device is used for small civilian rockets, and the overall parachute structure can be connected in parallel and scaled up proportionally, suitable for the recovery of the propulsion module of medium-sized launch vehicles with a capacity of 22 to 25 tons (dry weight range of the first stage of SpaceX Falcon 9). Background Technology

[0002] The Falcon 9 relies on grid fins and whole-engine reverse thrust for deceleration, which is complex and consumes a lot of fuel. Traditional aerospace deceleration parachutes are single-section integrated structures without high-temperature protection. When a heavy rocket body re-enters at supersonic speeds, the high-temperature airflow directly ablates the parachute fabric. The single parachute has a low load-bearing capacity and cannot support a heavy propulsion module of more than 20 tons, making it prone to tearing and failure.

[0003] Existing deceleration chutes lack segmented, step-by-step deployment structures, resulting in large instantaneous impact loads during deployment. Under heavy-duty rocket conditions, the rocket body structure is prone to deformation and damage. Summary of the Invention Purpose of the invention

[0004] Overcoming the shortcomings of traditional deceleration parachutes, such as poor high-temperature resistance, limited load-bearing capacity, large opening impact, and easy entanglement and collision with rocket body separation components, we provide a segmented oil-insulated deceleration parachute that can be enlarged and connected in parallel with multiple parachutes to adapt to heavy rockets. Technical solution

[0005] A segmented high-temperature resistant oily deceleration parachute device, characterized in that: it includes a storage cylinder ①, a first-stage low-speed deceleration parachute ②, a second-stage heat-insulating oily parachute ③, a parachute body timing deployment controller ④, a high-temperature resistant oily protective coating ⑤, and a multi-parallel connection base ⑥. The first-stage deceleration parachute and the second-stage heat-insulating oil-based parachute are stored in layers inside the storage cylinder. The timing unfolding controller controls the two parachute sections to open sequentially. The inner and outer surfaces of the second-stage heat-insulating oil-based parachute are coated with a high-temperature resistant oil-based protective coating, which can withstand re-entry aerodynamic high temperatures above 1200℃. The multi-parallel connection base can simultaneously assemble multiple sets of parachute units. A single parachute unit is suitable for small rockets, and the load-bearing capacity of multiple sets of parallel combinations meets the deceleration requirements of a 22-25 ton heavy propulsion module. This parachute device is equipped with a time-sharing start control logic. The parachute will only deploy in sections after the rocket body separation components have drifted to a safe area, thus avoiding the risk of falling components colliding with or entangled in the parachute fabric. Beneficial effects

[0006] 1. Segmented and step-by-step deployment: Reduces the instantaneous impact of parachute opening, protecting the 22-25 ton heavy rocket body structure from deformation; 2. Oil-based high-temperature resistant coating: Withstands high temperature of 1200℃, completely solves the problem of high-speed reentry ablation of medium-sized rockets, and does not require an additional heat insulation shell; 3. Modular parallel design: The core umbrella structure is unified, and the load limit can be increased by increasing the number of umbrellas, directly comparable to the Falcon 9 heavy-duty first-stage recovery operation. 4. Time-sharing start-up protection design: Matching the actual descent attitude of the rocket, it utilizes the natural physical characteristics of the heavy rocket body's inertial rapid dive and the separation capsule's large drag and delayed descent. The parachute is only deployed after the rocket body and capsule have completely separated and a safe distance has been created, thus eliminating interference failures between the capsule and the parachute from the root and significantly reducing the recovery failure rate. Attached Figure Description

[0007] Figure 1 Cross-sectional view of the overall structure of a single segmented oil-based deceleration chute Attached reference numerals: ① Storage cylinder ② First-stage low-speed deceleration parachute ③ Second-stage heat-insulating oily parachute ④ Timing deployment controller ⑤ Oily protective coating; Drawing description: The cylinder is arranged vertically, with two umbrella sections for layered storage. Arrows indicating the order of unfolding are marked, and the diagonal lines on the umbrella surface represent the high-temperature resistant oil film coating.

[0008] Figure 2 Schematic diagram of parallel assembly of multiple parachutes for 22-25 ton heavy-lift rocket Attached reference numeral: ⑥ Multi-umbrella parallel connection base; Drawing description: 3 to 4 sets of segmented deceleration parachute units are evenly arranged on the base to adapt to the recovery conditions of the 22 to 25-ton propulsion compartment of the Falcon 9. Specific Implementation

[0009] Example (Adaptation Example for 22-25 ton medium launch vehicle) This segmented high-temperature resistant oily deceleration parachute uses a multi-parallel base to assemble four independent canopy units. The overall size of the canopy is proportionally widened and thickened, and the oily protective coating is thickened. After the first and second stages of the rocket separate and the attitude is reversed, it enters a stable diving attitude: the heavy propulsion module has a large mass, strong inertia, and low wind resistance, and falls at a high speed, always facing the ground from the front; the rocket body separation components are lightweight and have a large wind-receiving area, and are naturally located above and behind the propulsion module.

[0010] The rocket completes the lateral separation of its components at an altitude of 3-8 km, and the lateral ejection outputs horizontal thrust, giving the separated components a lateral safety distance of not less than 1.2 times the outer diameter of the propulsion module. After separation, the components fall further due to the drag of their own shells, while the front propulsion module continues to dive rapidly due to its huge inertia. The two automatically form a stable speed difference and distance difference, and the separated components fall further and further back, never catching up with the main rocket body.

[0011] This device strictly adopts a time-sharing operation logic: at an altitude of 3km to 8km, only the rocket body components are separated without initiating the parachute deployment procedure. After the separated components have completely drifted to a safe area and their trajectories have completely diverged, the rocket body will then sequentially deploy the first and second stage parachutes at an altitude of 3km to 10km. The segmented parachutes buffer the supersonic airflow, and the 1200℃ high-temperature resistant oil film isolates the rocket from re-entry into high temperatures. Multiple parachutes are connected in parallel to distribute the 22-25 ton heavy propulsion compartment load, preventing tearing and overloading, and achieving complete and undamaged sea recovery.

[0012] Compared to the Falcon 9 vertical thrust recovery system, this invention eliminates the complex vector braking engine and saves huge amounts of braking fuel consumption, significantly reducing rocket manufacturing and reuse maintenance costs.

Claims

1. A segmented high-temperature resistant oil-based deceleration parachute device, characterized in that: It includes a storage cylinder, a primary low-speed deceleration parachute, a secondary heat-insulating oil-based parachute, a timing deployment controller, a high-temperature resistant oil-based protective coating, and a multi-parallel connection base; the primary deceleration parachute and the secondary heat-insulating oil-based parachute are stored in layers and opened in stages through the timing deployment controller; the surface of the secondary heat-insulating oil-based parachute is coated with a high-temperature resistant oil-based protective coating to achieve heat insulation and deceleration for supersonic reentry.

2. The segmented high-temperature resistant oil-based deceleration chute device according to claim 1, characterized in that: The timing deployment controller first deploys a low-speed parachute to buffer the airflow, then deploys a large-diameter oil-filled main parachute, gradually removing the supersonic impact load.

3. The segmented high-temperature resistant oil-based deceleration parachute device according to claim 1, characterized in that: The high-temperature resistant oil-based protective coating can withstand temperatures greater than 1200℃, isolating the rocket from the high-temperature airflow during reentry and preventing the parachute from being ablated and damaged.

4. The segmented high-temperature resistant oil-based deceleration chute device according to claim 1, characterized in that: The multi-umbrella parallel connection base can simultaneously assemble multiple groups of segmented umbrella units, and adapt to the recovery of large-tonnage rocket bodies by sharing the load among multiple umbrellas.

5. The segmented high-temperature resistant oil-based deceleration chute device according to claim 1, characterized in that: The umbrella body and high-temperature resistant oil-based protective coating can be proportionally thickened and strengthened to accommodate the deceleration load of a 22-25 ton heavy rocket propulsion module.

6. The segmented high-temperature resistant oil-based deceleration chute device according to claim 1, characterized in that: The storage cylinder has a sealed, heat-proof storage structure that will not bulge or delaminate under high-altitude, low-temperature, or high-speed airflow environments.

7. The segmented high-temperature resistant oil-based deceleration parachute device according to claim 1, characterized in that: The segmented, step-by-step deployment structure significantly reduces instantaneous parachute overload and prevents deformation and cracking of the heavy rocket body structure.

8. The segmented high-temperature resistant oil-based deceleration chute device according to claim 1, characterized in that: The Class II oil-resistant umbrella is made of high-toughness flame-retardant umbrella fabric, which is resistant to tearing by high-speed airflow and abrasion.

9. The segmented high-temperature resistant oil-based deceleration chute device according to claim 1, characterized in that: The entire device can be modularly scaled up and assembled in parallel with multiple units, adapting to the 22-25 ton dry weight recovery conditions of the first stage of the Falcon 9. It relies on a segmented heat-insulated deceleration structure to replace the traditional grid fins and vertical reverse thrust recovery scheme, reducing the manufacturing and maintenance costs of rocket recovery.

Images