A water surface air cushion and winged rocket combined recovery rocket system

Abstract

The present application relates to the technical field of rocket recovery, in particular to a water surface air cushion and winged rocket cooperating recovery rocket system, comprising a rocket body provided with wings for controlling the flight attitude and falling trajectory of the rocket body, a recovery air cushion arranged on water for receiving the rocket body, and the recovery air cushion being in communication with an inflation device and an exhaust control device respectively; the present application has the advantages of low fuel consumption, high reliability, reduced structural weight of the rocket, and safe recovery.

Description

Technical Field

[0001] This invention relates to the field of rocket recovery technology, specifically to a rocket recovery system that combines a water surface air cushion with a winged rocket. Background Technology

[0002] Currently, the mainstream recovery rocket solutions include the US Falcon series of reusable landing legs rocket solutions, the Starship Tower mechanical wall clamp rocket recovery solution, the Chinese Long March 10B net-system recovery rocket solution, and the Space Shuttle landing recovery solution. The reusable landing leg rocket design, the Starship Tower mechanical wall clamp rocket recovery design, and the net-system recovery design of China's Long March 10B rocket all involve the rocket falling vertically and relying on engine thrust for accurate landing and recovery. These designs have the following limitations: 1. The reverse propulsion recovery process consumes a lot of fuel. For example, the Falcon rocket needs to carry a lot of fuel during the recovery phase. This fuel must be launched into the air with the rocket, which takes up the effective payload space and reduces the overall launch efficiency. 2. During the recovery process, the engine needs to be restarted multiple times under extreme conditions, which increases the mission risk and affects the system reliability.

[0003] Furthermore, the space shuttle landing and recovery plan, although equipped with wings, requires landing on a land runway, which has three major drawbacks: 1. The space shuttle required landing gear, which introduced additional weight.

[0004] 2. Land landing lacks effective cushioning and is not suitable for the recovery of heavy rockets.

[0005] 3. Runway construction costs are high, and the choice of landing sites is limited.

[0006] Finally, the current difficulty in scaling up rocket wings is mainly due to three factors.

[0007] First, during the launch phase, wind can interfere with the rocket's flight trajectory; the larger the wing area, the more significant the impact of wind.

[0008] Secondly, the wings will generate significant air resistance during the rocket's ascent.

[0009] Furthermore, when the rocket descends into the atmosphere, the excessively large wings cannot withstand the extremely high aerodynamic loads.

[0010] Because large wings cannot be used, it is impossible to significantly reduce the rocket's descent speed. Summary of the Invention

[0011] In view of this, the present invention provides a recovery rocket system that combines a water surface air cushion with a winged rocket, aiming to solve the problems in the prior art.

[0012] To achieve the above objectives, the present invention provides the following technical solution: a recovery rocket system combining a water surface air cushion and a winged rocket, comprising, The arrow body is equipped with wings to control its flight attitude and descent trajectory. The recovery air cushion, placed on the water, is used to receive the arrow body. The recovery air cushion (8) is connected to the inflation device and the exhaust control device respectively.

[0013] A further improvement of the present invention is that the reusable air cushion is located on a ship.

[0014] A further improvement of the present invention is that the vessel is a multihull vessel or a hydrofoil vessel.

[0015] A further improvement of the present invention is that the recovery air cushion is provided with a blocking device, the blocking device is used to intercept the recovered arrow body, the blocking device includes two support rods, symmetrically arranged on both sides of the recovery air cushion or the boat, and the first end of the support rod is hinged to the recovery air cushion or the boat. Two symmetrical buffer devices are located on both sides above the recovery air cushion. The second ends of the two support rods are respectively connected to the two buffer devices. The buffer devices are connected to the drum. An arresting cable is wound on the drum. The arresting cable is adapted to the hook at the bottom of the arrow body.

[0016] A further improvement of the present invention is that the recovery air cushion is provided with a blocking device, the blocking device is used to intercept the recovered arrow body, the blocking device includes two support rods, symmetrically arranged on both sides of the recovery air cushion or the boat, and the first end of the support rod is hinged to the recovery air cushion or the boat. Two symmetrical buffer devices are located on both sides above the recovery air cushion. The second ends of the two support rods are respectively connected to the two buffer devices. The buffer devices are connected to the drum. A mesh cable is wound on the drum. A blocking member is provided between the two mesh cables. The blocking element includes: Two hanging poles are symmetrically fixed on both sides above the recovery air cushion, and a soft barrier net is installed between the two hanging poles. Two pull net cables are fixed to both sides of the soft barrier net.

[0017] A further improvement of the present invention is that the recovery air cushion is provided with a blocking device, the blocking device is used to intercept the recovered arrow body, the blocking device includes two support rods, symmetrically arranged on both sides of the recovery air cushion or the boat, and the first end of the support rod is hinged to the recovery air cushion or the boat. Two symmetrical buffer devices are located on both sides above the recovery air cushion. The second ends of the two support rods are respectively connected to the two buffer devices. The buffer devices are connected to the drum. A mesh cable is wound on the drum. A blocking member is provided between the two mesh cables. The blocking element includes: The recovery air cushion or boat is equipped with tracks on both sides, and brackets are slidably connected on the tracks; A rigid barrier net is installed on the bracket. The central barrier bar of the rigid barrier net is connected to the bracket, and the two sides of the rigid barrier net are respectively connected to two pull net cables.

[0018] A further improvement of the present invention is that the arrow body is provided with a shaft, and the rotating main wing is rotatably mounted on the arrow body through the shaft. When the arrow body rises, the rotating main wing rotates to a state parallel to the arrow body. After the arrow body decelerates, the rotating main wing rotates to a state perpendicular to the arrow body.

[0019] A further improvement of the present invention is that the rotating main wing is composed of an outer wing and an inner wing, wherein a retractable inner wing is provided inside the outer wing.

[0020] A further improvement of the present invention is that the wing is composed of a canard, a main wing, and a tail wing arranged sequentially from front to back, wherein the canard and the tail wing are control surfaces.

[0021] A further improvement of the present invention is that a padding protective plate is provided at the bottom of the arrow body.

[0022] The technological advancements achieved by this invention due to the adoption of the above technical solutions are as follows: This invention provides a recovery rocket system that combines a water surface air cushion with a winged rocket. The recovery air cushion is set on the water surface, and the rocket body slides on the water surface with the recovery air cushion when it lands. Compared with the prior art, it eliminates the need to build a dedicated runway and also saves the landing gear, thus reducing the structural weight of the rocket.

[0023] In this invention, the engine does not need to be restarted during the recovery phase, which reduces mission risk, enhances reliability, and extends the reusable service life of the engine.

[0024] In this invention, the rocket body is equipped with a canard, main wing, and tail wing, which utilizes aerodynamics for deceleration, consumes less fuel, avoids occupying the effective payload space, and significantly improves overall efficiency.

[0025] In this invention, the rocket body lands on a recovery air cushion on the water surface. With the help of the dual buffering effect of the recovery air cushion and water, the heavy rocket body can be safely recovered.

[0026] In this invention, the reusable air cushion is lightweight and easy to deploy, supports recovery in open waters without fixed ports, and is low-cost and easy to implement.

[0027] In this invention, after the rocket adopts a rotating main wing, when the rotating main wing is adjusted to be parallel to the rocket body, the rocket is less affected by wind during the launch phase and the aerodynamic drag is also smaller; the aerodynamic load is lower during the deceleration phase; and when the wing is rotated to a vertical state after deceleration, it can provide greater lift and effectively reduce the rocket's descent speed. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in the embodiments of the present invention, the 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.

[0029] Figure 1 This is a schematic diagram of the principle from below in Embodiment 1 of the recovery rocket system described in this invention; Figure 2 This is a side view schematic diagram of the recovery rocket system according to Embodiment 1 of the present invention; Figure 3 This is a rear-view schematic diagram of Embodiment 1 of the recovery rocket system described in this invention; Figure 4 This is a top-view schematic diagram of the main wing not deployed in Embodiment 2 of the recovery rocket system described in this invention; Figure 5 This is a schematic diagram of the principle of the main wing not being deployed in Embodiment 2 of the recovery rocket system of the present invention; Figure 6 This is a schematic diagram of the rear view of the main wing not deployed in Embodiment 2 of the recovery rocket system described in this invention; Figure 7 This is a top-view schematic diagram of the main wing deployment principle in Embodiment 2 of the recovery rocket system described in this invention; Figure 8 This is a schematic diagram of the main wing deployment principle in Embodiment 2 of the recovery rocket system described in this invention; Figure 9 This is a schematic diagram of the rear view principle of the main wing deployment in Embodiment 2 of the recovery rocket system described in this invention; Figure 10 This is a top-view schematic diagram of the main wing not deployed in Embodiment 3 of the recovery rocket system described in this invention; Figure 11 This is a schematic diagram of the principle of the main wing not being deployed in Embodiment 3 of the recovery rocket system of the present invention; Figure 12 This is a top-view schematic diagram of the main wing deployment principle in Embodiment 3 of the recovery rocket system described in this invention; Figure 13 This is a schematic diagram of the recovery air cushion principle in Embodiment 4 of the recovery rocket system described in this invention. Figure 14 This is a side view schematic diagram of the recovery air cushion principle in Embodiment 4 of the recovery rocket system described in this invention; Figure 15 This is a schematic diagram illustrating the landing principle of the winged rocket with a recovery cushion, as described in Embodiment 4 of the recovery rocket system of the present invention. Figure 16This is a rear-view schematic diagram of the recovery air cushion principle in Embodiment 5 of the recovery rocket system described in this invention; Figure 17 This is a side view schematic diagram of the recovery air cushion principle in Embodiment 5 of the recovery rocket system described in this invention; Figure 18 This is a schematic diagram of the recovery air cushion principle in Embodiment 6 of the recovery rocket system of the present invention; Figure 19 This is a schematic diagram illustrating the landing principle of the recovered air cushion winged rocket in Embodiment 6 of the recovered rocket system of the present invention.

[0030] Explanation of reference numerals in the attached figures: 1-Arrow body, 21-Tail fin, 22-Fixed main wing, 23-Forearm wing, 24-Folding main wing, 25-Shaft, 26-First rotating main wing, 261-Outer wing, 262-Inner wing, 27-Second rotating main wing, 3-Landing pad, 5-Pull rope, 6-Pull airbag, 7-Boat, 8-Recovery airbag, 10-Protective pad, 11-Hook, 12-Support rod, 13-Buffer device, 14-Drum, 31-Hanging rod, 32-Pull net cable, 33-Soft barrier net, 41-Bracket, 42-Railway, 43-Hard barrier net, 44-Barrier rod, 45-Spring, 46-Impact airbag, 51-Barrier cable, 70-Thruster, 71-Inflatable boat, 72-Rigid boat. Detailed Implementation

[0031] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings (the dimensions in the drawings differ significantly from the actual proportions for the purpose of illustrating the principles and do not represent the true proportions of the physical objects). Obviously, in the following description, specific details such as particular system structures and technologies are presented for illustrative purposes rather than for limiting the scope of the invention, in order to provide a thorough understanding of the embodiments of the present invention. However, those skilled in the art should understand that the present invention can also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid unnecessary details hindering the description of the present invention.

[0032] This invention provides a recovery rocket system that combines a water-based air cushion with a winged rocket. The rocket body 1 is equipped with wings to control its flight trajectory and reduce its descent speed. The rocket body 1 is also equipped with a deceleration device to slow it down as it descends. A recovery air cushion 8, positioned on the water, receives the rocket body 1. The recovery air cushion 8 is connected to both an inflation device and an exhaust control device.

[0033] The various wings on the rocket body 1 all use existing mature technologies, and the control methods are common knowledge and not the core technical points of this solution, so they will not be explained in detail.

[0034] The deceleration device can employ a rocket engine-based deceleration scheme, which is already used in existing reusable rockets. Its principle is similar to existing recovery technologies, both adjusting the rocket's velocity to a target value at a predetermined location. However, this scheme differs significantly from existing technologies: existing recovery schemes typically require multiple ignitions for deceleration, ultimately reducing the rocket's velocity to zero on the ground; while this scheme only requires a single ignition for deceleration during reentry into the upper atmosphere, reducing the rocket body's velocity to a range that the fixed wings can withstand. Alternatively, the folding wings and rotating main wings can be deployed when the rocket's velocity drops to a specific range.

[0035] Deceleration can also employ an aerodynamic deceleration scheme primarily using the wings and rocket body 1. This technology has been implemented in the Space Shuttle and Starship second-stage rockets using winglets for attitude control. Aerodynamic deceleration can be used to reduce the rocket's speed to a level suitable for landing on the air cushion. Alternatively, when the rocket's speed enters a specific range, the folding wings and rotating main wing can be deployed to glide to the recovery air cushion 8.

[0036] The rocket body 1 can also use a drag chute for further aerodynamic deceleration. Initial deceleration can be achieved using the engine or wings and rocket body 1. Once the speed drops to a specific range, the drag chute is deployed for further deceleration. Alternatively, after the rocket's speed decreases to a specific range, the drag chute is jettisoned, the folding wings and rotating main wing are deployed, and the rocket glides to the recovery air cushion 8.

[0037] An inflation device connected to the recovered air cushion 8 can be used to inflate the recovered air cushion 8 using an air pump or a blower.

[0038] The exhaust control device connected to the recovered air cushion 8 can be any existing device capable of adjusting the air cushion exhaust rate. For example, when the exhaust port size is large or the number is large, a throttle valve or other valve can be used to adjust the exhaust speed by controlling its opening; if the exhaust port size is small, a pump or fan can be used for active air extraction, and the exhaust speed can be controlled by controlling the extraction rate.

[0039] Arrow body 1 is the rocket.

[0040] Example 1

[0041] According to the instruction manual Figure 1 To be continued Figure 3 This describes a recovery rocket system that combines a water-based air cushion with a winged rocket. The rocket engine on the rocket body 1 acts as a deceleration device. When the rocket body 1 descends, it only needs one high-altitude reentry ignition to reduce its speed to within the range that the fixed wings can withstand in the dense atmosphere. The rocket body 1 is equipped with wings to reduce its descent speed and control its gliding to the recovery air cushion 8 positioned on the water surface for recovery.

[0042] This embodiment is a small winged rocket stage with a relatively low maximum speed. The rocket body 1 has, from front to back, a canard wing 23, a fixed main wing 22, and a tail wing 21. The tail wing 21 and canard wing 23 are V-shaped canard wing 23 and V-shaped tail wing 21, similar to the all-moving V-tail of the J-20 fighter jet, providing yaw and pitch control. The fixed main wing 22 adopts a fixed-wing design, primarily providing lift to the rocket body 1 and reducing descent speed.

[0043] The rocket body 1 has a protective airbag 6 and a landing pad 3 at its bottom. The upper end of the protective airbag 6 is fixed to the bottom of the rocket body 1. After being inflated with a certain amount of gas, the protective airbag 6 is elastic and can effectively absorb impact energy, playing a cushioning role, while also having the advantage of being lightweight. The lower end of the upper protective airbag 6 is fixed to the landing pad 3. The rigid landing pad 3 is made of titanium alloy or carbon fiber material and reinforced with ribs to enhance its rigidity and withstand lateral bending loads. When the rocket body 1 lands on the recovery air cushion 8, the protective airbag 6 and the landing pad 3 work together to provide protection.

[0044] The fixed main wing 22 is connected to the landing pad 3 by multiple ropes 5. Given that the rocket wing needs to strictly control its weight, a lightweight structural design can be adopted, and any insufficient structural strength is reinforced by the ropes 5.

[0045] Since the complex structure of the recovery air cushion 8 will be described in detail in the embodiment of the recovery air cushion 8, the complete and detailed process of the rocket body 1 landing on the recovery air cushion 8 will be described in the embodiment of the recovery air cushion 8.

[0046] Example 2

[0047] According to the instruction manual Figure 4 To be continued Figure 9 It is known that the folding main wing 24 is hinged to the arrow body 1 on the side closest to the arrow body 1. A shaft 25 is rotatably mounted on the arrow body 1 at the upper center of the arrow body 1, and the first rotating main wing 26 is rotatably mounted on the arrow body 1 via the shaft 25, with the shaft 25 located at the center of the first rotating main wing 26. The first rotating main wing 26 consists of an outer wing 261 and an inner wing 262, wherein a retractable inner wing 262 is provided inside the outer wing 261. A horizontal forewing wing 23 is provided at the rear of the arrow body 1. A tail wing 21 is provided at the rear of the arrow body 1, which includes both a horizontal tail wing and a vertical tail wing. The width of both the forewing wing 23 and the tail wing 21 is smaller than that of the arrow body 1.

[0048] This embodiment is a relatively large winged rocket first stage. The folding main wing 24 can fold upwards or unfold horizontally, and a thermal protection layer is provided underneath the folding main wing 24. In this embodiment, the folding main wing 24 is thin, mainly suitable for providing a thermal protection barrier for other wing surfaces during atmospheric reentry and reducing descent speed. The structure of the folding main wing 24 can refer to the folding wings of the Starship second stage or the folding structure of carrier-based aircraft. The folding main wing 24 can also be connected to the landing pad 3 by multiple ropes 5, which makes the folding main wing 24 more stress-bearing.

[0049] The first rotating main wing 26 is similar to that of a cruise missile equipped with a rotating wing. In this embodiment, the shaft 25 is located in the middle, and the first rotating main wing 26 is installed in the middle of the missile body 1. The inner wing 262 can extend and retract inside the outer wing 261. When the inner wing 262 is retracted inside the outer wing 261, the first rotating main wing 26 has a small volume and high structural strength. When the speed is further reduced, the inner wing 262 extends from the outer wing 261 to increase the lift area.

[0050] During the ascent and descent deceleration of the rocket body 1, the first rotating main wing 26 rotates to be parallel to the rocket body 1, and the inner wing 262 retracts into the outer wing 261. The folding main wing 24 is in an upward folded state. Due to the thermal protection layer below it, the folding main wing 24 can shield the forewing wing 23, tail wing 21, and the first rotating main wing 26, providing them with protection. The protective airbag 6 is not inflated.

[0051] Once the rocket's speed decreases to a specific range, the angle of attack is adjusted to position the wings fully upwind. The folding main wing 24 then unfolds, and the first rotating main wing 26 rotates to a position perpendicular to the rocket body 1. Upwind, the folding main wing 24 is unaffected by updrafts and unfolds easily, while the first rotating main wing 26 unfolds smoothly due to balanced forces on both sides. As the rocket body 1's speed further decreases, the inner wing 262 extends from the outer wing 261. The canard wing 23 and tail wing 21 provide yaw and pitch control. Once the folding main wing 24 and the first rotating main wing 26 are fully deployed, the rocket body 1 can achieve gliding deceleration and maneuvering flight. The protective airbag 6 inflates.

[0052] In this embodiment, the slenderness ratio is small; in practical applications, the length and position of the rotating main wing need to be adjusted according to the specific rocket.

[0053] Specifically, the folding main wing 24 and the first rotating main wing 26 can both be connected to the padding guard plate 3 via the pull rope 5. The padding guard plate 3 can also employ a separate heat protection solution, such as coating with an ablation material. The pull rope 5 must also possess high-temperature resistance properties, or be protected by a special protective tube.

[0054] Example 3

[0055] According to the instruction manual Figure 10 To be continued Figure 12It can be seen that this embodiment is an improvement on the basis of Embodiment 2. The main difference from Embodiment 2 is that the projectile body 1 is not provided with the folded main wing 24. Therefore, its rotating main wings are narrower than the projectile body 1. The positions of the front wing 23 and the tail wing 21 are interchanged, and the tail wing 21 is located at the end of the projectile body 1 close to the engine. The rear part of the projectile body 1 is also provided with a shaft 25. Two layers of second rotating main wings 27 are rotatably mounted on the projectile body 1 through the shaft 25; the shaft 25 is located on one side of the second rotating main wings 27, and both layers of the second rotating main wings 27 are located above the first rotating main wing 26. When the projectile body 1 decelerates, the second rotating main wings 7 can also be automatically deployed by means of air flow. After the first rotating main wing 26 and the second rotating main wings 27 are fully deployed, the overall structure presents a shape of the Chinese character "tu".

[0056] Since three layers of rotating main wings are equipped, the wings can provide greater lift, so that the projectile body 1 can carry heavier loads. It should be noted that, since the tail wing 21 in this solution is located on the engine side at the tail of the projectile body 1, it is necessary to structurally reinforce the front part of the projectile body 1.

[0057] In order to show the structure of the three layers of rotating main wings more clearly, this solution is not provided with the folded main wing 24. In actual specific implementation, adding the folded main wing 24 is a better choice. In addition, in specific implementation, more layers of rotating main wings can also be provided, for example, a four-layer wing structure in the shape of the Chinese character "gong" can be formed.

[0058] Embodiment 4

[0059] According to the accompanying drawings of the specification Figure 13 to the accompanying drawings Figure 14 it can be seen that the upper end of the recovery air cushion 8 is provided with a protective pad 10. The recovery air cushion 8 is arranged on the ship 7, the arresting device comprises two support rods 12 symmetrically arranged on both sides of the ship 7, and the first end of each support rod 12 is hinged with the ship 7; two symmetrical buffer devices 13 are arranged on both sides above the protective pad 10, the second ends of the two support rods 12 are respectively connected with the two buffer devices 13, the buffer devices 13 are connected with the reel 14, the reel 14 is wound with a net pulling cable 32, and an arresting member is arranged between the two net pulling cables 32.

[0060] The recovery air cushion 8 is connected to both the inflation device and the exhaust control device. In this embodiment, the inflation device is a blower, and the recovery air cushion 8 is inflated by the blower. The exhaust control device is a computer-controlled large valve that controls the exhaust speed by controlling the opening of the exhaust port, thereby controlling the air pressure inside the recovery air cushion 8 and adjusting the buffering strength and duration. This allows for flexible control of the buffering strength and duration to adapt to the recovery requirements of different rocket models. The recovery air cushion 8 can adopt a multi-chamber structure for independent control. This design allows the air chamber corresponding to the landing point of the rocket body 1 to accelerate exhaust, creating a depression and effectively preventing the rocket body 1 from rolling randomly. The recovery air cushion 8 can also be in a multi-layered stacked form; for example, this solution uses a two-layer structure. Multi-layered recovery air cushion 8 can achieve a faster exhaust response, and the height of the recovery air cushion 8 can be set by adjusting the number of inflation layers according to different rocket bodies 1. Since the bottom of the recovery air cushion 8 may enter water, the equipment needs to be waterproofed; for example, the exhaust outlet can be extended to the upper part via an air pipe. The protective pad 10 is designed to reduce damage to the recovery air cushion 8 from the rocket body 1, and is easy to replace if damaged. It is made of wear-resistant, highly lubricating, and high-temperature resistant materials. The recovery air cushion 8 also includes various technologies used in existing air cushions, such as air cushion stabilization nets. The boat 7 is used to transport the recovery air cushion 8 and the rocket. In this embodiment, the boat 7 is an inflatable boat 71, which has the advantage of being lightweight and can be towed. In this embodiment, the inflatable boat 71 is equipped with a propeller 70, and the navigation route can be changed by adjusting the direction of the propeller 70. This allows for high-speed navigation to reduce the speed difference with the rocket during descent and can actively adjust its direction to align with the rocket's landing point. The bottom of the inflatable boat 71 is a trimaran with a curved bottom, which facilitates rapid submersion in water after the rocket lands on the cushion.

[0061] The recovery air cushion 8 is also equipped with an arresting device, which functions similarly to the arresting cables on an aircraft carrier. This device ensures that the rocket body 1 lands reliably on the cushion and gently synchronizes the speeds of the rocket body 1 and the recovery air cushion 8. The arresting device consists of a support rod 12, a buffer device 13, a drum 14, and arresting components.

[0062] The inflatable boat 71 is equipped with support rods 12 mounted on a shaft. The support rods 12 on both sides of the recoverable air cushion 8 are connected to the protective pad 10 by a crossbeam. The support rods 12 can rotate around the shaft, thereby adjusting their tilt angle according to the height of the recoverable air cushion 8. After adjustment, the position of the support rods 12 can be locked.

[0063] A buffer device 13 is installed behind the support rod 12. The buffer device 13 can be a hydraulic buffer device similar to that used in aircraft carrier arresting gear, a new type of electric buffer device, or a brake similar to that used in automobile brakes (such as disc or block brakes). In this example, the buffer device 13 adopts a computer-controlled brake disc structure. The buffer device 13 is connected to the drum 14, and the rotation speed of the drum 14 can be precisely controlled by adjusting the braking pressure.

[0064] The barrier components include a pull net cable 32, hanging poles 31, and a flexible barrier net 33. The pull net cable 32 is wound around a drum 14. Two hanging poles 31 are symmetrically fixed on both sides above the protective pad 10, with a detachable flexible barrier net 33 suspended between them. The hanging poles 31 can be made of highly elastic carbon fiber material and designed to be detachable; when the flexible barrier net 33 comes into contact with the arrow body 1, the net can detach from the hanging poles 31 and be easily removed upon impact. The hanging poles 31 can also be highly elastic and fixed to the protective pad 10. The two pull net cables 32 are fixedly connected to both sides of the flexible barrier net 33.

[0065] Based on the instruction manual Figure 15 This paper describes the complete rocket recovery process in Recovery Scheme 2 using the recovery cushion 8. At launch, the folding main wings 24 on the rocket body 1 are folded upwards. The first rotating main wing 26 rotates to be parallel to the rocket body 1, with its inner wing 262 retracting inside the outer wing 261. Simultaneously, the ship 7 carrying the recovery cushion 8 is pre-deployed to the designated sea landing point of the rocket body 1. The recovery cushion 8's blower is activated in advance for inflation, and the arresting gear enters standby mode.

[0066] After completing its mission, the first-stage rocket body 1 enters the descent phase. When rocket body 1 decelerates to a specific range, it deploys the folding main wings 24 and the first rotating main wings 26. These primarily provide lift for rocket body 1, assisting its gliding flight; the tail fin 21 and canard fin 23 act as control surfaces, used to precisely control the flight attitude and gliding trajectory of rocket body 1. Rocket body 1 then glides horizontally towards the location of the sea-based recovery air cushion 8, and its bottom protective plate airbag 6 inflates to enter the cushioning state.

[0067] As the rocket body 1 continues to glide and approaches the sea surface to recover the air cushion 8, the computer, through coupling control of the propeller 70 of the ship 7 and the various wing surfaces of the rocket body 1, generates the optimal contact strategy. By coordinating the movement of the ship 7 and the rocket body 1, the ship 7 uses its own propeller 70 to adjust its course and speed, aligning itself in advance with the gliding trajectory of the rocket body 1, and completing the recovery posture for standby.

[0068] When the rocket body 1 lands on the recovery air cushion 8, it first impacts the soft barrier net 33, pulling the net 33 off the support pole 31 and causing it to detach from the pole. The computer-controlled buffer device 13 automatically matches the optimal buffering scheme according to the speed and model of the rocket body 1. It adjusts the rotation speed of the drum 14 by regulating the braking pressure, thereby controlling the release speed of the net cable 32, achieving a gradual buffering from gentle to strong, so that the speed of the rocket body 1 and the ship 7 tend to be synchronized.

[0069] As the rocket body 1 continuously presses down onto the recovery air cushion 8, its impact force is transmitted downwards to the landing pad 3, and then to the protective airbag 6. The inflated protective airbag 6 absorbs the vertical impact a second time through compression deformation. Simultaneously, the computer-controlled exhaust control device of the recovery air cushion 8 is activated, using the load-bearing range of the rocket body 1 as the control parameter for isobaric exhaust of the recovery air cushion 8. Furthermore, the computer precisely controls the dynamic distribution of air pressure in each air chamber and forms a closed-loop feedback system with the real-time attitude data of the rocket body 1, thereby achieving a seamless transition from deceleration to landing pad cushioning. At the same time, due to the transfer of gravity to the water surface, the boat 7 and the recovery air cushion 8 begin to immerse in the water and generate upward lift, forming a water surface cushioning effect. The recovery air cushion 8 and the water together form a double buffer, ultimately ensuring the structural integrity of the rocket body 1 and the safety of its internal load.

[0070] As the descent velocity of rocket body 1 approaches zero, the exhaust valve closes with high precision, forming a stable support plane to prevent rocket body 1 from tilting or bouncing. Under the combined effect of multiple buffering layers, rocket body 1 finally comes to a smooth stop on the surface of the recovery cushion 8. Subsequently, the air inlet and exhaust outlet are closed, forming a sealed airbag. Finally, a tugboat tows the recovery cushion 8, which carries the rocket, back to the launch site.

[0071] The above represents the optimal solution achievable under current technological conditions. However, in actual operation, the complexity can be appropriately simplified depending on the specific circumstances. For example, for winged rockets, the autonomous landing mode of the Soviet Buran space shuttle can be referenced, or the current method of manually controlling drones can be imitated to allow for manual landing. For the recovery air cushion 8, it can be placed on the ship 7 or directly positioned on the water surface, with support rods 12 and other arresting devices hinged to both sides of the air cushion 8 to await the landing of the winged rocket. The simplest solution could even be to simply place the recovery air cushion and wait for the winged rocket to land.

[0072] Example 5

[0073] According to the instruction manual Figure 16 To be continued Figure 17 As can be seen, this embodiment is an improvement on Embodiment 4. Unlike Embodiment 4, the vessel 7 is a rigid hull vessel 72, and the rigid hull vessel 72 has a rudder at its stern. The rigid hull vessel 72 replaces the inflatable vessel 71, thereby improving the durability of the vessel 7. Furthermore, the rigid hull vessel 72 is equipped with a rudder, which makes directional control more efficient than using only the propeller 70.

[0074] The barrier device has been changed to a rigid barrier net system. In this embodiment, the barrier consists of a bracket 41, a track 42, a rigid barrier net 43, and a mesh cable 32.

[0075] The recovery air cushion 8 has two tracks 42 on both sides, and the tracks 42 are connected by crossbeams at the front and rear. Two brackets 41 are set on the protective pad 10 and are slidably connected to the tracks 42. The rigid barrier net 43 is set on the brackets 41. The lower part of the middle of the rigid barrier net 43 has a notch, and a barrier bar 44 is set on the notch. The two sides of the rigid barrier net 43 are respectively connected to two pull net cables 32. A trigger-type impact airbag 46 is fixed at the upper end of the rigid barrier net 43. The spring 45 is sleeved on the barrier bar 44, and the lower end of the spring 45 is fixed on the bracket 41.

[0076] In this embodiment, the rigid barrier net 43 is made of rigid material. The rigid barrier net 43 is mounted on the bracket 41. A spring 45 is installed in the middle of the bracket 41, and the barrier bar 44 in the middle of the rigid barrier net 43 is inserted into the spring 45. This ensures that the rigid barrier net 43 remains upright under normal conditions. However, when the arrow body 1 contacts the rigid barrier net 43, the rigid barrier net 43 has a certain range of swinging ability. The spring 45 also ensures that the rigid barrier net 43 and the bracket 41 move together. The bracket 41 supports the rigid barrier net 43 and can slide along the track 42. An impact airbag 46 is also installed on the upper part of the rigid barrier net 43. The impact airbag 46 is similar to a safety airbag. It is normally in an uninflated state. When the arrow body 1 is about to contact the rigid barrier net 43, the impact airbag 46 quickly inflates and deploys to buffer the impact of the arrow body 1. The impact airbag 46 does not affect the forward movement of the ship 7 and can provide protection when the arrow body 1 contacts the rigid barrier net 43.

[0077] In practical use, the barrier bar 44 can be directly fixed to the bracket 41, or it can be connected to the bracket 41 through other flexible devices, such as a flexible bar.

[0078] Example 6, according to the appendix to the instruction manual Figure 18 To be continued Figure 19 It can be seen that this embodiment is a further improvement on Embodiment 5. Unlike Embodiment 5, an arresting cable 51 is wound around the drum 14. After being guided by a steering device, the arresting cable 51 is placed horizontally above the protective pad 10. In this design, the arresting cable 51 is adapted to the hook 11 structure at the lower part of the rocket body 1, and its working principle is similar to the landing mechanism of a carrier-based aircraft on an aircraft carrier. The hook 11 is installed at the lower part of the rocket body 1, and the hook 11 is connected to the bottom of the rocket body 1 by multiple ropes. This design takes into account both lightweighting and a better stress-bearing structure. The arresting cable 51 is adapted to the hook 11 at the lower part of the rocket body 1.

[0079] Appendix Figure 12This embodiment describes the process of recovering the rocket of Embodiment 2 using the rocket body 1 and the arresting cable 51. First, the support rod 12 is adjusted to raise the arresting cable 51 to the optimal height, and then the position of the support rod 12 is locked. Similar to the process of a carrier-based aircraft landing on an aircraft carrier, the hook 11 of the rocket body 1 will hook the horizontally placed arresting cable 51. Next, the buffer device 13 controls the rotation speed of the drum 14 by adjusting the braking pressure, thereby precisely managing the release speed of the arresting cable 51, realizing a gradual buffer control of the rocket body 1 from gentle to forceful, and finally synchronizing the speed of the rocket body 1 with that of the recovery platform.

[0080] Specifically, the super-large recovery air cushion 8 can also be composed of multiple hulls carrying the recovery air cushion 8, with each hull connected by steel beams to ensure synchronization during vertical movement.

[0081] Specifically, in certain situations, such as when the rocket body 1 is small and close to the launch site, its wings can be used solely to reduce the vertical descent speed, resulting in extremely low horizontal speed. However, in other situations, if the rocket's horizontal speed is too high or the rocket body 1 is heavy, a drag chute can be used to assist in deceleration. If the timing of the drag chute's deployment can be precisely controlled, a relatively ideal deceleration effect can be achieved. Furthermore, solid rocket motors can be installed on the rocket body 1. Activating these motors as it approaches the recovery cushion 8 can effectively slow down the descent and forward speed of the rocket body 1, ensuring that the final speed remains within the safe operating range of the recovery cushion 8. High-temperature resistant materials can be laid on the surface of the recovery cushion 8, or the area where the motors are located can be cooled by water spray.

[0082] Ship 7 can adopt high-speed ship design schemes such as multihull ships and hydrofoils.

[0083] The landing pad 3 can also be designed as a two-piece structure, which is fixed to multiple support rods hinged to the rocket body 1, and uses mechanisms such as springs or rotational damping devices to control torque for cushioning. Of course, if the rocket body 1 structure itself is strong enough, or if it has been specifically reinforced internally, the landing pad 3 may not be required.

[0084] In this invention, the winged rocket can take on various other forms, such as a space shuttle configuration. This space shuttle-style winged rocket can also land in water and recover on the air cushion 8. Its corresponding wings and deceleration mechanisms can draw upon various wing and deceleration mechanisms used in the space shuttle, all of which fall within the scope of this invention.

[0085] The main wing in this invention includes a fixed main wing 22, a folding main wing 24, and a rotating main wing, as well as various other forms of main wings or combinations of main wings that primarily generate lift. The rotating main wing can be a first rotating main wing 26 or a second rotating main wing 27.

[0086] The wing design in this invention is also applicable to the upper stage of a rocket, especially the folding main wing and the rotating main wing, which have shown excellent results in the upper stage. The canard wing 23 and tail wing 21 design can also be used in the upper stage of a rocket, and the canard wing 23 and tail wing 21 can also be designed to be foldable.

[0087] It should be noted that in this patent application, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, the phrase "comprising an element defined as..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0088] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be included within the protection scope of the present invention.

Claims

1. A recovery rocket system combining a water-based air cushion and a winged rocket, characterized in that, include: The arrow body (1) is equipped with wings to control the flight attitude and descent trajectory of the arrow body (1). A recovery air cushion (8) is placed on the water to receive the arrow body (1). The recovery air cushion (8) is connected to an inflation device and an exhaust control device.

2. The recovery rocket system combining a water surface air cushion and a winged rocket according to claim 1, characterized in that, The recovery air cushion (8) is located on the ship (7).

3. The recovery rocket system combining a water surface air cushion and a winged rocket according to claim 2, characterized in that, The vessel (7) is a multihull vessel or a hydrofoil vessel.

4. A recovery rocket system combining a water-based air cushion and a winged rocket according to any one of claims 1-3, characterized in that, The recovery air cushion (8) is equipped with a blocking device, which is used to intercept the recovered rocket body (1). The blocking device includes: Two support rods (12) are symmetrically arranged on both sides of the recovery air cushion (8) or the boat (7), and the first end of the support rod (12) is hinged to the recovery air cushion (8) or the boat (7); Two symmetrical buffer devices (13) are provided on both sides above the recovery air cushion (8). The second ends of the two support rods (12) are respectively connected to the two buffer devices (13). The buffer devices (13) are connected to the drum (14). The drum (14) is wound with a blocking cable (51). The blocking cable (51) is adapted to the hook (11) at the bottom of the arrow body (1).

5. A recovery rocket system combining a water-based air cushion and a winged rocket according to any one of claims 1-3, characterized in that, The recovery air cushion (8) is equipped with a blocking device, which is used to intercept the recovered rocket body (1). The blocking device includes: Two support rods (12) are symmetrically arranged on both sides of the recovery air cushion (8) or the boat (7), and the first end of the support rod (12) is hinged to the recovery air cushion (8) or the boat (7); Two symmetrical buffer devices (13) are provided on both sides above the recovery air cushion (8). The second ends of the two support rods (12) are respectively connected to the two buffer devices (13). The buffer devices (13) are connected to the drum (14). A pull net cable (32) is wound on the drum (14). A blocking member is provided between the two pull net cables (32). The blocking element includes: Two hanging poles (31) are symmetrically fixed on both sides above the recovery air cushion (8), and a soft barrier net (33) is provided between the two hanging poles (31). Two pull net cables (32) are fixed to both sides of the soft barrier net (33).

6. A recovery rocket system combining a water-based air cushion and a winged rocket according to any one of claims 1-3, characterized in that, The recovery air cushion (8) is equipped with a blocking device, which is used to intercept the recovered rocket body (1). The blocking device includes: Two support rods (12) are symmetrically arranged on both sides of the recovery air cushion (8) or the boat (7), and the first end of the support rod (12) is hinged to the recovery air cushion (8) or the boat (7); Two symmetrical buffer devices (13) are provided on both sides above the recovery air cushion (8). The second ends of the two support rods (12) are respectively connected to the two buffer devices (13). The buffer devices (13) are connected to the drum (14). A pull net cable (32) is wound on the drum (14). A blocking member is provided between the two pull net cables (32). The blocking element includes: The recovery air cushion (8) or boat (7) is provided with rails (42) on both sides, and the rails (42) are slidably connected to brackets (41). A rigid barrier net (43) is installed on the bracket (41). The middle barrier bar (44) of the rigid barrier net (43) is connected to the bracket (41), and the two sides of the rigid barrier net (43) are respectively connected to two pull net cables (32).

7. A recovery rocket system combining a water surface air cushion and a winged rocket according to claim 1, characterized in that... The arrow body (1) is provided with a shaft (25). The rotating main wing is rotatably mounted on the arrow body (1) through the shaft (25). When the arrow body (1) rises, the rotating main wing rotates to a state parallel to the arrow body (1). After the arrow body (1) decelerates, the rotating main wing rotates to a state perpendicular to the arrow body (1).

8. A recovery rocket system combining a water surface air cushion and a winged rocket according to claim 7, characterized in that... The rotating main wing consists of an outer wing (261) and an inner wing (262), wherein the outer wing (251) has a retractable inner wing (252) inside.

9. A recovery rocket system combining a water surface air cushion and a winged rocket according to any one of claims 1-3, characterized in that, The wing consists of a canard (23), a main wing, and a tail (21) arranged sequentially from front to back. The canard (23) and the tail (21) are control surfaces.

10. A recovery rocket system combining a water surface air cushion and a winged rocket according to any one of claims 1-3, characterized in that, The bottom of the arrow body (1) is provided with a padding protective plate (3).

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