CN117360797A - Reusable water lifting spaceflight launching carrier and using method - Google Patents

Abstract

The invention provides a reusable water lifting spaceflight launching and carrying vehicle, which belongs to the technical field of aerospace and comprises an arrow body, an airfoil surface, a tail wing, a propulsion engine, a gesture control engine, a pontoon, a mounting bracket and a drogue release device; the arrow body adopts the shape of a pointed columnar body, and equipment such as a combustion agent, an oxidant, navigation, control, energy supply and the like is arranged in the arrow body; the wing surfaces are arranged on two sides of the arrow body in pairs; the pontoons are symmetrically mounted on the wing surfaces of the two sides; the tail wings are arranged on two sides of the tail part of the rocket body in pairs, and control surfaces rotating around the wing surfaces are arranged on the tail wings; the tail end of the rocket body is provided with a propulsion engine which is a group of rocket engines and/or aeroengines; one end of the arrow body is symmetrically provided with a group of attitude control engines; the mounting bracket is axially arranged on the upper side of the arrow body; the drogue release device is arranged on the upper side of the arrow body, and the drogue is accommodated in the device. The invention also provides a using method, and solves the problems of high space launching cost and difficult improvement of the upper limit of the effective load.

Description

Reusable water lifting spaceflight launching carrier and using method

Technical Field

The invention relates to the technical field of aerospace, in particular to a reusable water lifting aerospace launching carrier and a using method thereof.

Background

In order to effectively reduce the cost of spaceflight emission, a great deal of scientific exploration and practice are carried out by human beings, and remarkable effects are achieved in part of directions. There are two main ways in the prior art that the achievement has been achieved: firstly, a large-scale airplane is used for carrying a rocket to launch at a high-altitude of ten thousand meters; secondly, the boosting stage and the core stage of the liquid fuel carrier rocket are recycled.

The scheme that the large-scale aircraft is used for carrying the carrier rocket and launching the carrier rocket at a high altitude of ten thousand meters is adopted, the relatively low flight cost of the aircraft is utilized, the carrier rocket is endowed with a certain initial speed and a certain height, and a larger effective load is realized on the premise of the same launching quality, so that the aim of reducing the cost is fulfilled. For example, the Weizhen orbit company mounts a 'LauncherOne' two-stage liquid fuel carrier rocket by using a modified Boeing 747-400 aircraft, and sends 500kg load to the near-earth orbit with the launching mass of about 29t, and the liquid fuel carrier rocket with the same carrying capacity is launched from the ground, and the take-off mass is often more than 50t. The rocket can be carried to a low latitude area by airborne launching, the payload carrying capacity of the rocket with the same launching quality is improved by utilizing the earth rotation linear velocity and the airplane flight velocity, and the launching time is not affected by weather because the rocket is launched at the stratosphere, when the airplane flies to the open sea air to launch the rocket, the first stage of the rocket can drop into the ocean, the pressure of the safety area selection is reduced, and the rocket is more freely launched and selected. However, due to the carrying capacity of the aircraft and the limitation of the mounting space, the aerial launching is only suitable for launching rockets with the mass within tens of tons, the effective load is limited to hundreds of kilograms, and the cost per unit mass of the actual launching is not obviously reduced. In addition, in order to launch rockets of greater mass in the air, airplanes need to be made larger and airports capable of adapting to take-off and landing of such large airplanes are also constraints that limit their development and use.

By adopting a mode of recycling the boosting stage and the core stage of the liquid fuel carrier rocket, the cost of the boosting stage and the core stage of the liquid fuel carrier rocket often accounts for more than 60% of the total rocket launching cost, and the liquid fuel only accounts for less than 1% of the launching cost, so that the total launching cost can be obviously reduced if the recycling of the boosting stage and the core stage of the liquid fuel carrier rocket is realized. The SpaceX company realizes the recovery of the core stage, the boosting stage and the core stage on the falcon 9 and the heavy falcon respectively by utilizing the rocket vertical controlled landing technology, realizes the full-stage recovery on the starboard, and can reduce the effective load emission cost per unit mass to 20% -40% of the traditional rocket emission quotation by combining the recovery and the repeated use of the fairing, thereby having considerable application prospect and being tracked and simulated by countries around the world. However, the technical approach adopted by spaceX corporation also has the following disadvantages: firstly, no matter falcon, heavy falcon or starship, a special launching farm and a special launching tower are required, and in order to facilitate the land recovery boosting stage and the sea recovery core stage, a special land recovery farm apron and a sea recovery platform are also required to be built; the construction of the launching sites, the launching towers, the recovery sites and the offshore recovery platforms brings additional construction, maintenance, guarantee and other costs. Once the positions of the launching sites and the launching towers are determined, the inclination angles of the tracks suitable for launching the aircraft to run are determined, so that the requirements of different tasks such as launching forward running tracks, sun synchronous tracks, polar tracks and geostationary synchronous tracks are met, a large amount of funds are put into constructing a plurality of launching sites at different latitudes, different launching sites are selected according to the requirements of the tasks to execute the launching tasks, or the optimal carrying trajectory is difficult to match for the different launching tasks at the cost of paying more transport capacity, sacrificing the orbit transferring capacity of the upper stage and the like. Thirdly, the booster and the primary vertical recovery of the core require a gesture direct force control system and accurate control of engine power output, the technical difficulty of control system design and realization is high, the engineering reliability requirement is high, the control system cost is increased, and the recovery process is also more strictly constrained to sea conditions and wind field environments. Fourthly, in a mode of vertically loading and launching the load and the rocket in series (parallel), the gravity of the effective load is fully acted on the structure bearing area of the limited size of the rocket body in the vertical direction, the stress is too concentrated, and the mechanism quality of the rocket is required to be greatly increased to ensure the structural strength along with the increase of the effective load, so that the carrying coefficient is reduced; and fifthly, the tail flame of the engine and the ground contact reverse jet flow thereof cause high-temperature and high-speed scouring and ablation on the field apron and the rocket body in the vertical take-off and landing process, so that the design of cooling protection of the field apron and the rocket body and the maintenance cost after the fact are increased.

The world technology is strong and the aerospace is strong, the forefront of the world is overtaken in the field of aerospace emission, the situation that the world cannot follow other people to run at the back is eliminated by virtue of tracking, the situation that the world cannot follow other people is avoided, a new way must be developed, the traditional concept innovation is overtaken, a differentiated development route is adopted, and the later people are on.

The information disclosed in this background section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art that is known to a person skilled in the art.

Disclosure of Invention

The invention provides a reusable water take-off and landing spaceflight launching carrier and a using method thereof, which can be used for loading carriers such as spaceships, aerospace shuttle vehicles, other carrier rockets or aircrafts and the like to fly off the ground surface and separating the carriers after the carriers are accelerated to a preset flight speed and flight height, and autonomously return to land horizontally on water, so as to solve the problems of high spaceflight launching cost and difficult improvement of the upper limit of effective load in the prior art.

A reusable water lifting spaceflight launching carrier comprises an arrow body, an airfoil surface, a tail wing, a propulsion engine, a attitude control engine, a pontoon, a mounting bracket and a drogue release device;

the arrow body adopts the shape of a pointed columnar body, and floats on the water surface according to the water displacement generated by the volume of the arrow body; the inside of the rocket body is provided with equipment such as a combustion agent, an oxidant, navigation, control, energy supply and the like;

the wing surfaces are arranged on two sides of the arrow body in pairs; the pontoons are symmetrically mounted below the wing surfaces on two sides, are of a hollow structure, are connected with a control system of the carrying carrier, execute unlocking action according to instructions and are controlled to be separated from the carrying carrier;

the tail wings are arranged on two sides of the tail part of the rocket body in pairs, control surfaces rotating around the wing surfaces are arranged on the tail wings, and the control surfaces are used for controlling the attitude and the flight direction of the carrier;

the tail end of the rocket body is provided with a propulsion engine, and the propulsion engine is a group of rocket engines and/or aeroengines; a group of attitude control engines are symmetrically arranged at the head or tail of the rocket body;

the mounting bracket is axially arranged on the upper side of the arrow body and is used for fixing the transported load, connecting with a control system of the carrier, executing unlocking action according to the instruction and releasing the transported load;

the parachute release device is arranged on the upper side of the arrow body, a parachute is accommodated in the parachute release device and connected with the control system of the carrying carrier, and the parachute is released according to the instruction to decelerate the carrying carrier.

Further, the airfoil has two, installs in pairs in the middle part of arrow body both sides.

Further, the number of the pontoons is two, and the pontoons are symmetrically arranged on the sides, close to the wing tips, of the two wing surfaces.

Further, the pontoon is hollow structure, adopts the cylindric symmetrical appearance in middle part of both ends pointed form, can arrange boiling water and produce buoyancy to produce buoyancy with the arrow body and make carrier and load float on the surface of water together.

Further, the tail fin has two pieces, adopts the sweepback wing, and is installed in pairs in the afterbody both sides of arrow body with the V font that inclines.

Further, the attitude control engine is a group of small rocket engines, and the reaction force generated by high-speed injection of chemical reaction products acts on the rocket body to form a moment for changing the attitude and the flying speed direction of the carrier.

Further, the support has more than two, installs in the arrow body upside along the axial setting.

Based on the same technical conception, the invention also provides a method for using the reusable water lifting spaceflight launching carrier, which comprises the following steps:

s1, connecting and fixing a load required to be transmitted by an on-water lifting space launching carrier with a mounting bracket, integrally transferring to a water area with required launching latitude by means of a tugboat, and completing the horizontal alignment of the launching;

s2, the propulsion engine is ignited to drive the carrier to advance at a high speed on the water surface, and meanwhile, the control surface deflects to generate a moment for lifting the carrier, and the arrow body and the airfoil surface generate lifting force for enabling the carrier to leave the water surface under the action of high-speed airflow;

s3, increasing the thrust of the propulsion engine to lift the flying speed of the carrier, and simultaneously forming moment on the rocket body by deflecting or attitude control of the control surface to jet reactants by the engine, and increasing the pitch angle and attack angle of the carrier until the rocket body flies to the sky at a high speed at an approximately vertical angle, wherein the carrier actively releases the pontoon to reduce flying resistance;

s4, after the carrier is continuously accelerated to a preset flight speed and a preset flight height under the driving of the propulsion engine, the mounting bracket executes unlocking action and is separated from the load, the load flies according to a set program under the driving of a self-contained power system, the carrier stops the propulsion engine in a large pitch angle state, and the carrier is converted into free falling motion after flying by inertia to the highest point in a powerless state;

s5, intermittently starting a propulsion engine to reversely push the carrier to reduce the falling speed in the process of freely falling;

s6, after the carrier enters the dense atmosphere, the attitude control engine is combined with the action of the control surface to reduce the pitch angle, the yaw angle and the attack angle of the carrier, and meanwhile, the propulsion engine is gradually flamed out, and the flying height is continuously reduced by means of inertia, the flight attack angle and the wing surface lift sliding/coiling deceleration;

and S7, when the carrier approaches the water surface and the flying speed is reduced to a preset range, the drogue release device pops up the drogue, and the carrier is quickly decelerated and stably moored on the water surface under the action of the drogue, so that the launching and recycling processes are completed.

The beneficial technical effects obtained by the invention are as follows:

according to the technical scheme, the load such as a load spacecraft, an aerospace vehicle, other carrier rockets or aircrafts can fly away from the ground surface, and the load is separated from the load after being accelerated to a preset flying speed and flying height, so that the load can independently return to the horizontal water for landing. The emission and recovery do not need special ground or sea surface emission/recovery fields, emission towers and other supporting and guaranteeing facility requirements, the emission and recovery positions can be reasonably selected nearby from the angle of energy optimization according to the track inclination angle, and the recovery control system is relatively simple and reliable to realize. The loading capacity is high, the stress concentration of the effective load to the rocket body is low, and the launching and using cost is low. Compared with the mode of launching a rocket at a high-altitude of ten thousand meters by using a large-scale airplane in the prior art, the carrying capacity is greatly improved, the rocket with larger mass can be launched in the air, and the upper limit of the effective load is increased; compared with the scheme of recycling the boosting stage and the core stage vertical lifting of the liquid fuel carrier rocket, the water lifting space launching carrier is utilized to replace most of functions of the boosting stage and the core stage, the requirements on supporting and guaranteeing facilities are greatly reduced, the reliability is improved, the problems that the space launching cost is high and the upper limit of a payload is difficult to improve in the prior art are solved, and the method has outstanding substantive characteristics and remarkable progress.

Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims thereof as well as the appended drawings.

Drawings

FIG. 1 is a schematic diagram of one embodiment of the present invention;

FIG. 2 is a schematic view of another view of one embodiment of the present invention;

FIG. 3 is a front view of one embodiment of the present invention;

FIG. 4 is a left side view of FIG. 3;

FIG. 5 is a schematic view of a load carrier rocket according to one embodiment of the present invention;

FIG. 6 is a schematic view of a horizontal drop recovery configuration in accordance with one embodiment of the present invention;

FIG. 7 is a schematic diagram of a full transmit-to-recycle process in accordance with one embodiment of the present invention;

reference numerals: 1. an arrow body; 2. an airfoil; 3. a tail wing; 31. a control surface; 4. propelling the engine; 5. a gesture control engine; 6. a pontoon; 7. a mounting bracket; 8. a drogue release device; 81. a drogue.

Detailed Description

The following detailed description of the embodiments of the invention, together with the accompanying drawings, will provide further details of the invention, such as specific system configurations, models, technical parameters, etc., which are set forth in the following description, but are not limiting, as they provide a better understanding of the invention. In addition, those skilled in the art will know and understand the content, and the details will not be repeated here.

As shown in fig. 1 to 4, a specific embodiment of a reusable water lifting spaceflight launching carrier comprises an arrow body 1, an airfoil surface 2, a tail wing 3, a propulsion engine 4, a posture control engine 5, a pontoon 6, a mounting bracket 7 and a drogue release device 8.

In the specific embodiment, the arrow body 1 adopts the shape of a pointed columnar body, meets the aerodynamic shape required by air flight, has the capability of sailing on the water surface, and can float on the water surface by means of the water displacement generated by the volume of the arrow body. The rocket body 1 is used as a load bearing structure of a carrier, and is used for providing storage spaces for a propulsion engine 4, a gesture control engine 5, required combustion agents and oxidants and installation spaces required by various electromechanical equipment such as navigation, control and energy supply.

In this embodiment, the airfoil surface 2 has two pieces, and the plane shape of the plane is trapezoidal, and the plane shape is installed in the middle of two sides of the arrow body 1 in pairs, when the arrow body 1 advances at a high speed, air flows through the airfoil surface 2, and a lifting force for driving the arrow body 1 to fly upwards is generated. In the embodiment, the marine lifting space launching carrier needs to be driven by the ignition of the tug transfer or pushing engine 4 when the water surface moves, an oil tank and a landing gear are not required to be arranged in the airfoil surface 2, and the installation space of electromechanical equipment can be provided according to the requirement. The airfoil profile and mounting position of the airfoil 2 can be adapted according to actual requirements.

In this embodiment, there are two pontoons 6 symmetrically mounted on the lower sides of the two wing surfaces 2 near the tips of the wings. The pontoon 6 is hollow structure, adopts the cylindric symmetrical appearance in middle part of both ends pointed shape, produces buoyancy through the boiled water that arranges, makes carrier and load float on the surface of water with the buoyancy that arrow body 1 produced together. The pontoon 6 is connected to a control system of the carrier and can be controlled to be separated from the carrier. The shape, the number and the installation position of the pontoons 6 can be adaptively adjusted according to actual needs.

In this embodiment, the tail fin 3 has two fins, and the two fins are arranged on two sides of the tail of the arrow body 1 in pairs in an inclined V shape. The tail wing 3 is also provided with a control surface 31 which can rotate around the wing surface, and the two control surfaces 31 realize the control of the attitude and the flight direction of the carrier through the same-direction rotation or differential motion.

In this embodiment, propulsion engine 4 is a set of rocket engines or aeroengines, or a combination of both, and when the rocket engines are contained, the vehicle can perform the launching task in the atmosphere and the outer space, and when the aeroengines are contained, the vehicle can perform the launching task only in the atmosphere. The number and mounting position of the propulsion engines 4 can also be adapted according to the actual need.

In the embodiment, attitude control engines 5 are symmetrically distributed at the tail of the rocket body 1 along the circumferential direction. The attitude control engine 5 is a group of a plurality of small rocket engines, and the reaction force generated by high-speed injection of chemical reaction products acts on the rocket body 1 to form a moment for changing the attitude and the flying speed direction of the carrier, so that the pitching, yawing and rolling attitudes of the carrier are changed in the outer space, and the carrier can also work in the atmosphere, thereby accelerating the attitude adjustment speed of the carrier.

As shown in fig. 5, in this embodiment, two sets of mounting brackets 7 are axially disposed on the upper side of the rocket body 1, and are used for fixing the transported carrier rocket, and are connected with a control system of the carrier vehicle, so as to execute an unlocking action according to a command, and release the transported load.

As shown in fig. 6, in this embodiment, the tail end of the upper side of the arrow body 1 is further provided with a drag parachute release device 8, in which a drag parachute 81 is accommodated in the drag parachute release device 8, and the drag parachute release device is disposed above the propulsion engine 4, or may be symmetrically disposed on two sides according to actual needs, or adopt other schemes. The parachute release device 8 is connected with a control system of the carrier, and can release the parachute 81 according to the instruction, and the parachute 81 decelerates the carrier under the action of air resistance.

As shown in fig. 7, the launching and recovery process of the water lifting space launching and carrying vehicle in this embodiment is as follows:

s1, connecting and fixing other carrier rockets required to be launched by the water lifting spaceflight launching carrier with the mounting bracket 7, integrally transferring to a water area with required launching latitude by means of a tug, and completing the horizontal alignment of the launching direction.

S2, the propulsion engine 4 is ignited to drive the carrier to advance at a high speed on the water surface, meanwhile, the control surface 31 deflects upwards to generate a moment for lifting the carrier, and the arrow body 1 and the airfoil surface 2 generate lifting force for enabling the carrier to leave the water surface under the action of ground effect wings formed by high-speed airflow.

S3, when the thrust of the propulsion engine 4 is increased to lift the flight speed of the carrier, the control surface 31 deflects or the attitude control engine 5 sprays reactants at a high speed to form a moment on the rocket body 1, and the pitch angle and the attack angle of the carrier are increased until the rocket body 1 flies to the sky at a high speed at an angle close to the vertical angle under the combined action of aerodynamic force, the propulsion engine 4 and the attitude control engine 5, and the carrier actively releases the pontoon 6 to reduce the flight resistance.

S4, after the carrier is continuously accelerated to a preset flight speed and a preset flight height under the drive of the propulsion engine 4, the mounting bracket 7 executes unlocking action to separate from the load, the load flies according to a set program under the drive of a self-contained power system, the carrier stops the propulsion engine 4 in a large pitch angle state, and the carrier turns into free falling motion after reaching the highest point by means of inertial flight in a powerless state.

S5, in the free falling process of the carrier, the propulsion engine 4 is intermittently started to reversely push to reduce the falling speed.

S6, after the carrier enters the dense atmosphere, the attitude control engine 5 is combined with the control surface 31 to act, so that the pitch angle, yaw angle and attack angle of the carrier are reduced, meanwhile, the propulsion engine 4 is gradually extinguished, and the flying height is continuously reduced by means of inertia, flight attack angle and airfoil lift sliding/coiling deceleration.

And S7, when the carrier approaches the water surface and the flying speed is reduced to a preset range, the drogue release device 8 pops up the drogue 81, and the carrier is quickly decelerated under the action of the drogue 81 and stably moored on the water surface, so that the launching and recycling processes are completed. The predetermined range of flight speeds in this particular embodiment is around 100 m/s.

The beneficial technical effects obtained by the embodiment are as follows:

the device can launch from a wide water area, the size, the weight and the maximum load of the carrier are not limited by airports, launching plateaus and the like, and the device is more suitable for being used as a boosting stage or a core primary carrying implementation such as lunar exploration, asteroid exploration and deep space exploration, and a heavy space vehicle with the take-off weight of thousands of tons. The carrier can be optimized to a proper launching position on the sea surface according to the inclination angle of the orbit of the aircraft, so that the rotation speed of the earth is fully utilized to reduce the fuel consumption, and the optimization of the carrier coefficient of the carrier is realized; the carrier can be recycled and reused, so that the emission cost is reduced, compared with the conventional ground and offshore platform recycling, a special recycling field/recycling platform is not required to be built, the infrastructure investment is low, the carrier is recycled in a horizontal gliding mode in a wide water area, the technology is mature, the requirement on control precision is low, and the reliability is high. The thrust engine has short reverse thrust working time in the recovery process, and mainly consumes kinetic energy and potential energy by virtue of resistance generated by gliding and spiraling at a large attack angle in the atmosphere, so that less fuel for recovery consumption is needed to be reserved; the high-temperature high-speed scouring and ablation of tail flame and ground contact reverse jet flow of the engine to the apron and the rocket body in the vertical take-off and landing process are avoided, the operation of water spraying, cooling and noise reduction of a launching table implemented by a traditional launching field is not needed, the recovery, repair and use guarantee difficulty of the carrier are reduced, meanwhile, the working time of the propulsion engine in the recovery process is short, the service life of the carrier is effectively prolonged, and the launching and use cost is expected to be reduced to be within 20% of that of a traditional quotation.

The foregoing is only illustrative of the present invention and is not to be construed as limiting thereof, but rather as various modifications, equivalent arrangements, improvements, etc., within the spirit and principles of the present invention.

Claims (8)

1. The reusable water lifting spaceflight launching carrier is characterized by comprising an arrow body (1), an airfoil surface (2), a tail wing (3), a propulsion engine (4), a posture control engine (5), a pontoon (6), a mounting bracket (7) and a drogue release device (8);

the arrow body (1) adopts the shape of a pointed columnar body, and floats on the water surface according to the water displacement generated by the volume of the arrow body; the arrow body (1) is internally provided with equipment such as a combustion agent, an oxidant, navigation, control, energy supply and the like;

the wing surfaces (2) are arranged on two sides of the rocket body (1) in pairs; the pontoons (6) are symmetrically mounted below the wing surfaces (2) on two sides, the pontoons (6) are of hollow structures, are connected with a control system of the carrying carrier, execute unlocking action according to instructions and are controlled to be separated from the carrying carrier;

the tail wings (3) are arranged on two sides of the tail part of the rocket body (1) in pairs, control surfaces (31) rotating around wing surfaces are arranged on the tail wings (3), and the control surfaces (31) are used for controlling the posture and the flight direction of the carrier;

the tail end of the rocket body (1) is provided with a propulsion engine (4), and the propulsion engine (4) is a group of rocket engines and/or aeroengines; a group of attitude control engines (5) are symmetrically arranged at the head or tail of the rocket body (1);

the mounting bracket (7) is axially arranged at the upper side of the arrow body (1) and is used for fixing the transported load, connecting with a control system of the carrier, executing unlocking action according to a command and releasing the transported load;

the drag parachute release device (8) is arranged on the upper side of the arrow body (1), the drag parachute (81) is contained in the drag parachute release device (8), the drag parachute release device is connected with the control system of the carrying carrier, and the drag parachute (81) is released according to the instruction to decelerate the carrying carrier.

2. The carrier according to claim 1, wherein the wing surface (2) has two pieces, which are mounted in pairs in the middle of the two sides of the arrow body (1).

3. A carrier according to claim 2, characterized in that the pontoons (6) are two, symmetrically mounted on the two wing surfaces (2) near the wing tip side.

4. A carrier according to claim 3, wherein the pontoon (6) has a hollow structure, adopts a symmetrical shape with two sharp ends and a cylindrical middle part, and is capable of discharging boiled water to generate buoyancy and floating the carrier and the load on the water surface together with the buoyancy generated by the arrow body.

5. The carrier according to claim 1, characterized in that the tail (3) has two blades, with swept back wings, mounted in pairs on either side of the tail of the arrow body (1) in an inclined V-shape.

6. The carrier vehicle according to claims 1-5, characterized in that the attitude control engine (5) is a set of small rocket engines, and the reaction force generated by high-speed injection of chemical reaction products acts on the rocket body (1) to form a moment for changing the attitude and the flying speed direction of the carrier vehicle.

7. Carrier according to any one of claims 1-5, characterized in that more than two brackets (7) are provided, which are mounted on the upper side of the arrow body (1) in an axial arrangement.

8. The application method of the reusable water lifting spaceflight launching carrier is characterized by comprising the following steps of:

s1, connecting and fixing a load required to be emitted by an on-water lifting space launching carrier with a mounting bracket (7), integrally transferring to a water area with a required launching latitude by means of a tug, and completing the horizontal alignment of the shooting direction;

s2, a propulsion engine (4) is ignited to drive the carrier to advance at a high speed on the water surface, meanwhile, a control surface (31) deflects to generate a moment for lifting the carrier, and an arrow body (1) and an airfoil surface (2) generate a lifting force for enabling the carrier to leave the water surface under the action of high-speed airflow;

s3, increasing the thrust of a propulsion engine (4) to lift the flight speed of the carrier, and simultaneously, deflecting or controlling the engine (5) to jet reactants through a control surface (31) to form moment on an arrow body (1), increasing the pitch angle and the attack angle of the carrier until the arrow body (1) flies to the sky at a high speed at an approximately vertical angle, and actively releasing a pontoon (6) by the carrier to reduce the flight resistance;

s4, after the carrier is continuously accelerated to a preset flight speed and a preset flight height under the driving of the propulsion engine (4), the mounting bracket (7) executes unlocking action and is separated from the load, the load flies according to a set program under the driving of a self-contained power system, the carrier stops the propulsion engine (4) in a large pitch angle state, and the carrier turns into free falling body movement after flying to the highest point by inertia in a powerless state;

s5, intermittently starting a propulsion engine (4) to reversely push to reduce the falling speed of the carrier in the process of freely falling;

s6, after the carrier enters a dense atmosphere, the attitude control engine (5) is combined with the control surface (31) to act, so that the pitch angle, yaw angle and attack angle of the carrier are reduced, and meanwhile, the propulsion engine (4) is gradually flamed out, and the flying height is continuously reduced by means of inertia, flying attack angle and wing surface lift sliding/coiling deceleration;

and S7, when the carrying carrier approaches the water surface and the flying speed is reduced to a preset range, the drogue release device (8) pops up the drogue (81), and the carrying carrier is rapidly decelerated under the action of the drogue (81) and stably moored on the water surface, so that the launching and recycling process is completed.