A reusable waterborne takeoff and landing space launch vehicle and its usage method

Abstract

This invention proposes a reusable waterborne takeoff and landing space launch vehicle, belonging to the field of aerospace technology. It includes a rocket body, wing surfaces, tail fins, propulsion engines, attitude control engines, floats, mounting brackets, and a deceleration parachute release device. The rocket body has a pointed cylindrical shape and houses propellant, oxidizer, navigation, control, and energy supply equipment. Wing surfaces are mounted in pairs on both sides of the rocket body. Floats are symmetrically mounted on the wing surfaces on both sides. Tail fins are mounted in pairs on both sides of the tail section of the rocket body, and control surfaces rotating around the wing surfaces are mounted on the tail fins. A propulsion engine, consisting of a set of rocket engines and / or aero engines, is mounted at the end of the rocket body. A set of attitude control engines is symmetrically arranged at one end of the rocket body. The mounting bracket is axially positioned on the upper side of the rocket body. The deceleration parachute release device is mounted on the upper side of the rocket body and houses the deceleration parachute. This invention also proposes a method of use, solving the problems of high space launch costs and difficulty in increasing the maximum payload capacity.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to a reusable waterborne takeoff and landing space launch vehicle and its usage method. Background Technology

[0002] To effectively reduce the cost of space launches, humanity has conducted extensive scientific exploration and practice, achieving significant results in some areas. Existing technologies that have yielded results mainly fall into two categories: one is using large aircraft to carry launch vehicles for launch at altitudes of tens of thousands of meters; the other is retrieving and reusing the booster stages and core stages of liquid-fueled launch vehicles.

[0003] The strategy of launching rockets from large aircraft at altitudes of tens of thousands of meters leverages the relatively low cost of aircraft to provide the rocket with a certain initial velocity and altitude, achieving a larger payload with the same launch mass, thereby reducing costs. For example, Virgin Orbit uses a modified Boeing 747-400 to launch its LauncherOne two-stage liquid-fueled rocket, sending a 500kg payload into low Earth orbit with a launch mass of approximately 29 tons. In contrast, a liquid-fueled rocket with the same payload capacity launched from the ground often has a launch mass exceeding 50 tons. Northrop Grumman uses an L-1011 aircraft to launch its Pegasus three-stage solid-fueled rocket, sending a 440kg payload into low Earth orbit with a launch mass of 18.5 tons, reducing the number of solid rocket boosters by nearly 8 tons compared to ground launches. Airborne launches can carry rockets to low-latitude regions, utilizing the Earth's rotational velocity combined with aircraft speed to increase the payload capacity of rockets with the same launch mass. Furthermore, since rockets are mostly launched from the stratosphere, launch timing is unaffected by weather. When launching rockets over international waters, the first stage can crash into the ocean, reducing the pressure of choosing a safe launch zone and allowing for greater freedom in rocket trajectory selection. However, due to limitations in aircraft carrying capacity and payload space, air launches are often only suitable for rockets with a launch mass of tens of tons or less, limiting the effective payload to several hundred kilograms, and the actual unit mass cost of launch has not been significantly reduced. In addition, to launch larger rockets in the air, larger aircraft need to be manufactured, and airports suitable for the takeoff and landing of such large aircraft become a constraint on its development and use.

[0004] The reuse of booster stages and core stages of liquid-fueled launch vehicles is a significant solution. Since the cost of booster stages and core stages often accounts for over 60% of the total launch cost, while liquid fuel accounts for less than 1%, achieving this reuse would substantially reduce overall launch costs. SpaceX has successfully implemented vertical landing technology on its Falcon 9 and Falcon Heavy rockets, recovering the core stage, booster stage, and core stage, respectively, and on its Starship platform, achieving full-stage recovery. Combined with fairing reuse, this reduces the launch cost per unit mass of payload to 20%-40% of traditional rocket launch costs, demonstrating considerable potential and prompting widespread adoption and emulation by other countries. However, SpaceX's approach also has the following shortcomings: First, regardless of whether it's the Falcon, Falcon Heavy, or Starship, dedicated launch sites and launch towers are required. To facilitate the recovery of the booster stage on land and the core stage at sea, dedicated land-based recovery pads and sea-based recovery platforms also need to be constructed. The construction of launch sites, launch towers, recovery pads, and sea-based recovery platforms incurs additional construction, maintenance, and support costs. Second, once the location of the launch site and launch tower is determined, the suitable orbital inclination for launching the spacecraft is also determined. To meet the needs of different missions such as prograde orbits, sun-synchronous orbits, polar orbits, and geostationary orbits, either a large amount of money must be invested in building multiple launch sites at different latitudes, selecting different launch sites according to mission requirements, or greater payload capacity and sacrificed upper-stage orbital maneuvering capabilities are required, making it difficult to match the optimal launch trajectory for different launch missions. Third, the vertical recovery of the boosters and core stage requires a direct force control system for attitude control and precise control of engine power output. This poses significant technical challenges to the design and implementation of the control system, demanding high engineering reliability and increasing control system costs. Furthermore, it imposes strict constraints on sea conditions and wind conditions during the recovery process. Fourth, the vertical loading and launch method, where the payload is connected in series (or parallel) with the rocket, concentrates the entire weight of the payload on a limited vertical structural load-bearing area of ​​the rocket body. This leads to excessive stress concentration. As the payload increases, the rocket's structural mass must be significantly increased to ensure structural strength, resulting in a decrease in the payload capacity. Fifth, during vertical takeoff and landing, the engine exhaust and its reverse jet upon impact cause high-temperature, high-speed erosion and ablation of the launch pad and rocket body, increasing the costs of cooling and protection design for the launch pad and rocket body, as well as subsequent maintenance and repair. Summary of the Invention

[0005] This invention provides a reusable water-based takeoff and landing space launch vehicle and its usage method. It can carry spacecraft, space shuttles, other launch vehicles or aircraft, etc., to take off from the ground and accelerate to a predetermined flight speed and altitude before separating from the payload and autonomously returning to land horizontally on the water. The purpose is to solve the problems of high space launch costs and difficulty in increasing the upper limit of effective payload in the existing technology.

[0006] A reusable waterborne takeoff and landing space launch vehicle includes a rocket body, wings, tail fins, propulsion engine, attitude control engine, floats, mounting brackets, and a deceleration parachute release device.

[0007] The rocket body has a pointed cylindrical shape and floats on the water surface by the displacement generated by its own volume. The rocket body is equipped with a propellant, an oxidizer, and navigation, control, and energy supply equipment.

[0008] The wing surfaces are installed in pairs on both sides of the rocket body; the floats are symmetrically mounted below the wing surfaces on both sides. The floats are hollow and connected to the control system of the launch vehicle. They perform unlocking actions according to instructions and are controlled to separate from the launch vehicle.

[0009] The tail fins are mounted in pairs on both sides of the tail of the rocket body. The tail fins are equipped with control surfaces that rotate around the fin surfaces. The control surfaces are used to control the attitude and flight direction of the carrier vehicle.

[0010] The rocket body is equipped with a propulsion engine at the end of the rocket body, which is a set of rocket engines and / or aircraft engines; a set of attitude control engines is symmetrically arranged at the head or tail of the rocket body.

[0011] The mounting bracket is installed axially on the upper side of the rocket body to fix the transported load. It is connected to the control system of the transport vehicle and performs an unlocking action according to the command to release the transported load.

[0012] The deceleration parachute release device is installed on the upper side of the rocket body. The deceleration parachute is housed inside the device and is connected to the control system of the transport vehicle. The deceleration parachute is released according to the command to decelerate the transport vehicle.

[0013] Furthermore, there are two wing surfaces, which are installed in pairs on the middle of both sides of the rocket body.

[0014] Furthermore, there are two floats, symmetrically mounted on the two wing surfaces near the wingtips.

[0015] Furthermore, the pontoon is a hollow structure with a symmetrical shape of pointed ends and a cylindrical middle section, which can displace water to generate buoyancy and, together with the rocket body, generate buoyancy, enabling the carrier and load to float on the water surface.

[0016] Furthermore, the tail fin has two swept wings, which are mounted on both sides of the tail of the arrow body in an inclined V-shape.

[0017] Furthermore, the attitude control engine is a set of small rocket engines that generate a reaction force through high-speed jetting of chemical reaction products, which acts on the rocket body to form a torque that changes the attitude and flight speed direction of the launch vehicle.

[0018] Furthermore, there are two or more supports, which are installed axially on the upper side of the arrow body.

[0019] Based on the same technical concept, this invention also proposes a method for using a reusable waterborne takeoff and landing space launch vehicle, comprising the following steps:

[0020] S1. Connect and fix the payload that needs to be launched by the water-based space launch vehicle to the mounting bracket, transfer it as a whole to the water area of ​​the required launch latitude by tugboat, and complete the horizontal alignment of the launch direction;

[0021] S2. The propulsion engine ignites and drives the vehicle forward at high speed on the water surface. At the same time, the deflection of the control surface generates a torque that makes the vehicle pitch up. The rocket body and wing surfaces generate lift force that makes the vehicle leave the water surface under the action of high-speed airflow.

[0022] S3. While increasing the thrust of the propulsion engine to improve the flight speed of the launch vehicle, the torque on the rocket body is generated by deflecting the control surfaces or ejecting reactants from the attitude control engine, increasing the pitch angle and angle of attack of the launch vehicle until the rocket body flies into the sky at a near-vertical angle at high speed. The launch vehicle actively releases the floats to reduce flight drag.

[0023] S4. After the transport vehicle accelerates to the predetermined flight speed and altitude under the drive of the propulsion engine, the mounting bracket performs the unlocking action to separate from the load. The load flies according to the set program under the drive of its own power system. The transport vehicle shuts off the propulsion engine at a high pitch angle and, in a powerless state, relies on inertial flight to reach the highest point before switching to free fall motion.

[0024] S5. During the free fall of the transport vehicle, the propulsion engine is intermittently activated to reverse the thrust and reduce the falling speed.

[0025] S6. After the vehicle enters the dense atmosphere, the attitude control engine, combined with the control surface action, reduces the vehicle's pitch angle, yaw angle and angle of attack. At the same time, the propulsion engine is gradually shut down, and the vehicle relies on inertia, flight angle of attack and wing lift to glide / turn and decelerate, continuously reducing the flight altitude.

[0026] S7. When the launch vehicle approaches the water surface and its flight speed drops to the predetermined range, the deceleration parachute release device deploys the deceleration parachute. Under the action of the deceleration parachute, the launch vehicle decelerates rapidly and comes to a smooth stop on the water surface, completing the launch and recovery process.

[0027] The beneficial technical effects achieved by this invention are:

[0028] The technical solution described in this invention can carry spacecraft, aerospace vehicles, other launch vehicles, or other aircraft to lift off the Earth's surface and accelerate to a predetermined speed and altitude before separating from the payload and autonomously returning to a horizontal water landing. Launch and recovery do not require dedicated ground or sea-based launch / recovery sites, launch towers, or other support and maintenance facilities. The launch and recovery locations can be rationally selected based on the orbital inclination from an energy optimization perspective, and the recovery control system is relatively simple and reliable. It has a large load-bearing capacity, low stress concentration of the payload on the rocket body, and low launch and operating costs. Compared to existing technologies that use large aircraft to carry launch vehicles for launch at altitudes of tens of thousands of meters, the carrying capacity is significantly increased, allowing for the launch of larger mass rockets in the air, thus raising the upper limit of the effective payload. Compared to the scheme of vertically taking off and landing and reusing the booster stage and core stage of liquid-fueled launch vehicles, using a water-based launch vehicle to replace most of the functions of the booster stage and core stage significantly reduces the need for support and maintenance facilities, improves reliability, and solves the problems of high launch costs and difficulty in raising the upper limit of the effective payload in existing technologies. It has outstanding substantive features and significant progress.

[0029] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures particularly pointed out in the written description, claims, and drawings. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the structure of one specific embodiment of the present invention;

[0031] Figure 2 This is a structural schematic diagram from another perspective of one specific embodiment of the present invention;

[0032] Figure 3 This is a front view of one specific embodiment of the present invention;

[0033] Figure 4 yes Figure 3 The left view;

[0034] Figure 5 This is a structural schematic diagram of a specific embodiment of the present invention, showing the launch vehicle in its loaded state;

[0035] Figure 6 This is a schematic diagram of the structure of a specific embodiment of the present invention in a horizontal landing and recovery state;

[0036] Figure 7 This is a schematic diagram of the entire launch-to-recovery process according to one specific embodiment of the present invention;

[0037] Reference numerals: 1. Arrow body; 2. Wing surface; 3. Tail fin; 31. Control surface; 4. Propulsion engine; 5. Attitude control engine; 6. Float; 7. Mounting bracket; 8. Deceleration parachute release device; 81. Deceleration parachute. Detailed Implementation

[0038] The specific embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Specific details such as particular system structures, models, and technical parameters mentioned in the following description are merely illustrative of the specific embodiments and not intended to limit the scope of protection of the present invention. Furthermore, content that should be known and understood by those skilled in the art will not be repeated here.

[0039] like Figures 1-4 As shown, a specific embodiment of a reusable waterborne takeoff and landing space launch vehicle includes a rocket body 1, wing surfaces 2, tail fins 3, propulsion engine 4, attitude control engine 5, floats 6, mounting brackets 7, and a deceleration parachute release device 8.

[0040] In this specific embodiment, the rocket body 1 adopts a pointed cylindrical shape to meet the aerodynamic requirements for aerial flight, while also possessing the ability to navigate on water, floating on the surface due to the displacement generated by its own volume. The rocket body 1 serves as the load-bearing structure of the launch vehicle, and also provides storage space for the propulsion engine 4, the attitude control engine 5, and the required propellant and oxidizer. It also provides installation space for various navigation, control, and energy supply electromechanical equipment.

[0041] In this specific embodiment, the wing surface 2 consists of two trapezoidal wings in plan view, mounted in pairs on the middle of both sides of the rocket body 1. When the rocket body 1 moves forward at high speed, air flows over the wing surface 2, generating lift that propels the rocket body 1 upward. In this specific embodiment, the water-based takeoff and landing space launch vehicle needs to be moved on the water surface by tugboats or driven by the ignition of the propulsion engine 4. The wing surface 2 does not require fuel tanks or landing gear, and can provide space for the installation of electromechanical equipment as needed. The airfoil and installation position of the wing surface 2 can be adaptively adjusted according to actual needs.

[0042] In this specific embodiment, there are two pontoons 6, symmetrically mounted on the underside of the two wing surfaces 2 near the wingtips. The pontoons 6 are hollow structures with a symmetrical shape, pointed at both ends and cylindrical in the middle. They generate buoyancy by displacing water, which, together with the buoyancy generated by the rocket body 1, allows the transport vehicle and its load to float on the water surface. The pontoons 6 are connected to the control system of the transport vehicle and can be controlled to separate from it. The shape, number, and installation position of the pontoons 6 can be adaptively adjusted according to actual needs.

[0043] In this specific embodiment, the tail fin 3 has two swept wings, which are mounted on both sides of the tail of the rocket body 1 in an inclined V-shape. The tail fin 3 is also equipped with a control surface 31 that can rotate around the wing surface. The two control surfaces 31 can control the attitude and flight direction of the vehicle by rotating in the same direction or differentially.

[0044] In this specific embodiment, the propulsion engine 4 is a group of rocket engines or aircraft engines, or a combination of both. When it includes rocket engines, the launch vehicle can perform launch missions in the atmosphere and outer space. When it only includes aircraft engines, the launch vehicle can only perform launch missions within the atmosphere. The number and installation position of the propulsion engines 4 can also be adjusted according to actual needs.

[0045] In this specific embodiment, attitude control engines 5 are symmetrically distributed circumferentially at the tail of the rocket body 1. The attitude control engines 5 are a group of multiple small rocket engines. The reaction force generated by the high-speed ejection of chemical reaction products acts on the rocket body 1 to form a torque that changes the attitude and flight speed direction of the launch vehicle. In outer space, it changes the pitch, yaw, and roll attitude of the launch vehicle. It can also work in the atmosphere to accelerate the attitude adjustment speed of the launch vehicle.

[0046] like Figure 5 As shown, in this specific embodiment, two sets of mounting brackets 7 are provided on the upper side of the rocket body 1 along the axial direction for fixing the transported launch vehicle. They are connected to the control system of the launch vehicle and can perform unlocking actions according to instructions to release the transported payload.

[0047] like Figure 6 As shown, in this specific embodiment, a deceleration parachute release device 8 is also installed at the upper end of the rocket body 1. The deceleration parachute release device 8 houses a deceleration parachute 81 and is positioned above the propulsion engine 4. Depending on actual needs, two devices can be symmetrically positioned on both sides, or other solutions can be adopted. The deceleration parachute release device 8 is connected to the control system of the transport vehicle and can release the deceleration parachute 81 according to the command. The deceleration parachute 81 decelerates the transport vehicle under the action of air resistance.

[0048] like Figure 7 As shown in this specific embodiment, the launch and recovery process of the water-based takeoff and landing space launch vehicle is as follows:

[0049] S1. Connect and fix other launch vehicles that need to be launched by water-based space launch vehicles to the mounting bracket 7, and transfer them as a whole to the required launch latitude water area by tugboat, and complete the horizontal alignment of the launch direction.

[0050] S2, the propulsion engine 4 ignites to drive the vehicle forward at high speed on the water surface, while the control surface 31 deflects upward to generate a torque that makes the vehicle lift off the water surface. The rocket body 1 and the wing surface 2 generate lift under the action of the "ground effect" formed by the high-speed airflow, which makes the vehicle leave the water surface.

[0051] S3. While increasing the thrust of the propulsion engine 4 to improve the flight speed of the launch vehicle, the torque on the rocket body 1 is generated by the deflection of the control surface 31 or the high-speed ejection of reactants by the attitude control engine 5, thereby increasing the pitch angle and angle of attack of the launch vehicle. Until, under the combined action of aerodynamic force and the propulsion engine 4 and attitude control engine 5, the rocket body 1 flies into the sky at a near-vertical angle at high speed, and the launch vehicle actively releases the floats 6 to reduce flight drag.

[0052] S4. After the transport vehicle accelerates to the predetermined flight speed and altitude under the drive of the propulsion engine 4, the mounting bracket 7 performs the unlocking action to separate from the load. The load flies according to the set program under the drive of its own power system. The transport vehicle shuts down the propulsion engine 4 at a high pitch angle and, in a powerless state, relies on inertial flight to reach the highest point before switching to free fall motion.

[0053] S5. During the free fall of the transport vehicle, the propulsion engine 4 is intermittently activated to reduce the descent speed.

[0054] S6. After the vehicle enters the dense atmosphere, the attitude control engine 5, in conjunction with the control surface 31, reduces the vehicle's pitch angle, yaw angle, and angle of attack. At the same time, the propulsion engine 4 is gradually shut down, and the vehicle continuously reduces its altitude by relying on inertia, flight angle of attack, and wing lift to glide / hover.

[0055] S7. When the launch vehicle approaches the water surface and its flight speed decreases to a predetermined range, the deceleration parachute release device 8 deploys the deceleration parachute 81. Under the action of the deceleration parachute 81, the launch vehicle rapidly decelerates and smoothly comes to a stop on the water surface, completing the launch and recovery process. In this specific embodiment, the predetermined range of flight speed is approximately 100 m / s.

[0056] The beneficial technical effects achieved by this specific embodiment are:

[0057] Capable of launching from vast bodies of water, the size, weight, and maximum payload of the launch vehicle are not limited by airports or launch pads, making it more suitable as a booster or core stage launch vehicle for heavy spacecraft such as lunar, asteroid, and deep space exploration missions, with takeoff weights often reaching thousands of tons. The launch vehicle can select a suitable launch location on the sea surface based on the spacecraft's orbital inclination, fully utilizing the Earth's rotation speed to reduce fuel consumption and optimize the launch vehicle's payload coefficient. The launch vehicle can be recovered and reused, reducing launch costs. Compared to traditional ground and sea platform recovery, it eliminates the need for dedicated recovery sites / platforms, resulting in lower infrastructure investment. Furthermore, recovery via horizontal gliding over vast waters is a mature technology with low requirements for control precision and high reliability. The propulsion engine has a short reverse thrust time during recovery, mainly relying on the drag generated by gliding and hovering at high angles of attack within the atmosphere to consume kinetic and potential energy, requiring less fuel to be retained for recovery. It avoids the high-temperature, high-speed erosion and burning of the launch pad and rocket body caused by the engine exhaust and reverse jet upon ground contact during vertical takeoff and landing, and eliminates the need for traditional launch pad water spraying for cooling and noise reduction. This reduces the difficulty of recovery, repair, and maintenance of the launch vehicle. At the same time, the short working time of the propulsion engine during recovery effectively extends the service life of the launch vehicle, and is expected to reduce the launch and usage costs to less than 20% of the traditional price.

[0058] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A reusable water-based launch space vehicle, characterized by, The waterborne launch space launch vehicle comprises a body (1), a wing surface (2), a tail fin (3), a propulsion engine (4), an attitude control engine (5), a float (6), a mounting bracket (7), and a deceleration parachute release device (8). The body (1) is in the shape of a pointed column, and is floated on the water surface by the displacement generated by its volume; the body (1) is internally provided with combustion agents, oxidizing agents, and navigation, control, and energy supply equipment; The wing surfaces (2) are installed in pairs on both sides of the body (1); the floats (6) are symmetrically hung below the wing surfaces (2) on both sides, the floats (6) are hollow structures, are connected with the control system of the launch vehicle, and perform unlocking actions according to instructions to be controlled to be separated from the launch vehicle; The tail fins (3) are installed in pairs on both sides of the tail of the body (1), and the tail fins (3) are provided with rudder surfaces (31) rotating around the wing surfaces (2), the rudder surfaces (31) are used for controlling the attitude and flight direction of the launch vehicle; The body (1) is provided with the propulsion engine (4) at the tail end, the propulsion engine (4) is a group of rocket engines and / or aircraft engines; a group of attitude control engines (5) are symmetrically arranged on the head or tail of the body (1); The mounting bracket (7) is arranged on the upper side of the body (1) in the axial direction, is used for fixing the transported load, is connected with the control system of the launch vehicle, performs unlocking actions according to instructions, and releases the transported load; The deceleration parachute release device (8) is arranged on the upper side of the body (1), the deceleration parachute release device (8) internally accommodates a deceleration parachute (81), is connected with the control system of the launch vehicle, and releases the deceleration parachute (81) according to instructions to decelerate the launch vehicle; The use method of the waterborne launch space launch vehicle comprises the following steps: S1, connecting and fixing the load to be launched by the waterborne launch space launch vehicle with the mounting bracket (7), transferring the whole to the water area at the required launch latitude by means of a tugboat, and completing the horizontal alignment of the launch direction; S2, igniting the propulsion engine (4) to drive the launch vehicle to advance at a high speed on the water surface, at the same time, deflecting the rudder surface (31) to generate a moment to make the launch vehicle lift its head, and under the action of high-speed airflow, the body (1) and the wing surface (2) generate lift to make the launch vehicle leave the water surface; S3, increasing the thrust of the propulsion engine (4) to increase the flight speed of the launch vehicle, at the same time, deflecting the rudder surface (31) or spraying reaction substances by the attitude control engine (5) to form a moment to the body (1), to increase the pitch angle and attack angle of the launch vehicle, until the body (1) flies to the sky at a high speed at a nearly vertical angle, and the launch vehicle actively releases the float (6) to reduce the flight resistance; S4, after the launch vehicle is continuously accelerated to the predetermined flight speed and flight height under the driving of the propulsion engine (4), the mounting bracket (7) performs the unlocking action to separate from the load, the load is driven by the power system to fly according to the set program, the launch vehicle stops the propulsion engine (4) at a large pitch angle, and after flying to the highest point in the state of inertia, the launch vehicle becomes a free falling body; S5, during the free falling process of the launch vehicle, the propulsion engine (4) is intermittently started to reduce the falling speed. S6, after the carrier enters the dense atmosphere, the pitch angle, yaw angle and attack angle of the carrier are reduced by the action of the attitude control engine (5) combined with the rudder surface (31), and the propulsion engine (4) is gradually turned off, relying on inertia, flight attack angle, wing surface lift sliding / circling deceleration to continuously reduce the flight height; S7, when the carrier approaches the water surface and the flight speed decreases to a predetermined range, the deceleration parachute release device (8) pops out the deceleration parachute (81), and the carrier is quickly decelerated and smoothly parked on the water surface under the action of the deceleration parachute (81), completing the launch and recovery process.

2. The carrier vehicle of claim 1, wherein, The wing surface (2) has two pieces, which are installed in pairs on both sides of the middle part of the arrow body (1).

3. The carrier vehicle of claim 2, wherein, The float (6) has two, which are symmetrically hung on the two wing surfaces (2) near the wing tip side.

4. The carrier vehicle of claim 3, wherein, The float (6) is a hollow structure, which adopts a symmetric shape of two-end sharp and middle cylindrical shape, can disperse water to generate buoyancy, and generate buoyancy with the arrow body to make the carrier and the load float on the water surface.

5. The carrier vehicle of claim 1, wherein, The tail wing (3) has two pieces, which are installed on both sides of the tail of the arrow body (1) in the form of a backward swept wing and an inclined V-shaped pair.

6. The carrier vehicle of any of claims 1-5, wherein, The attitude control engine (5) is a group of small rocket engines, which generate a reaction force by high-speed injection of chemical reaction products to act on the arrow body (1) to form a moment that changes the attitude of the carrier and the direction of flight speed.

7. The carrier vehicle of any of claims 1-5, wherein, The bracket (7) has two or more, which are installed on the upper side of the arrow body (1) in the axial direction.

Images