CN118548757A

CN118548757A - Carrier rocket adopting flexible parachute wing water sliding recovery and use method

Info

Publication number: CN118548757A
Application number: CN202410305865.2A
Authority: CN
Inventors: 李沈军
Original assignee: China Changfeng Electromechanical Technology Research And Design Institute
Current assignee: China Changfeng Electromechanical Technology Research And Design Institute
Priority date: 2024-03-18
Filing date: 2024-03-18
Publication date: 2024-08-27

Abstract

The invention provides a carrier rocket adopting flexible parachute wings to slide on water for recycling, which belongs to the technical field of carrier rockets and comprises a rocket body, a rocket engine, a attitude control engine, a rudder, a parachute wing cabin, a parachute wing, an air bag cabin and an air bag; the attitude control engine and the rudder are arranged at the position of the arrow body axially far away from the mass center; umbrella wing cabins and airbag cabins are symmetrically arranged on two sides of the middle section of the arrow body and are used for accommodating umbrella wings and airbags; the air bag is connected with a pressurized gas storage container in the rocket body through an air duct, and the air bag is restrained with the rocket body through a cable; the umbrella wing comprises an umbrella wing support arm, stay ropes, a piece of cloth and wing ribs; the root of the umbrella wing support arm is hinged with the arrow body through a mounting shaft, the cover cloth is triangular after being unfolded, one side of the cover cloth is fixed on the umbrella wing support arm, the other side of the cover cloth is fixed in the umbrella wing cabin, and the long side of the cover cloth is overlapped and fixed with the stay cable; the ribs are radially distributed between the wing arms and the inner wall of the wing cabin. The invention also provides a using method, and solves the problems of low load coefficient and poor economical efficiency of the existing recovery mode.

Description

Carrier rocket adopting flexible parachute wing water sliding recovery and use method

Technical Field

The invention relates to a recoverable carrier rocket, in particular to a carrier rocket recovered by adopting flexible hydrofoil sliding on water and a use method thereof, and belongs to the technical field of carrier rockets.

Background

In order to reduce the launching cost of the spacecraft, a mode of recovering the boosting stage and/or the core stage of the carrier rocket is mainly adopted at present, for example, a falcon No. 9 recovers a first-stage rocket, and a heavy falcon No. 9 can recover two boosting stages and core stages. From the analysis of the cost ratio, the first-stage rocket accounts for about 60% of the falcon No. 9 rocket cost, and the second-stage rocket accounts for about 20% of the falcon No. 9 rocket cost, but because the second-stage rocket has a long flight distance and a large flight speed, if a vertical recovery mode of a water recovery platform/a land launching field is adopted, the load coefficient of the second-stage rocket is too low due to the overlarge fuel consumed by return field flight and stable deceleration, and finally the maximum load is greatly reduced and is irreparable, so that SpaceX company abandons the recovery of the second-stage rocket on the falcon No. 9 and heavy falcon.

In addition, secondary rocket recovery has various constraints on technical pathway selection: firstly, the additional structural dry weight constraint of the recovery device is further enhanced, the mass of the secondary rocket is far lower than that of a boosting stage and a primary rocket, for example, the dry weight of a falcon No. 9 primary rocket structure is 22 tons, the designed recovery device is 5 tons, the structural dry weight of the secondary rocket is only 4.5 tons, and in order to ensure a higher load coefficient, the structural dry weight of the recovery device allowed by the secondary rocket must be controlled within hundreds of kilograms; the design of drag reduction and high temperature resistance ablation prevention required by severe working conditions is that the maximum speed of the first-stage rocket is usually 2.5km/s, the maximum speed of the second-stage rocket is usually more than 7km/s, the huge speed leads to remarkable flying resistance and pneumatic heating effect of the second-stage rocket in an atmosphere, the recovery modes such as exposed hard folding wings and the like have large structural quality, and the second-stage rocket recovery device is easy to be subjected to pneumatic heating ablation in an ultra-high-speed environment, and the second-stage rocket recovery device needs to be considered to be completely embedded to reduce the pneumatic resistance and the pneumatic heating ablation aggravation caused by a non-streamline structure, so that the design difficulty of structural quality control is further improved.

Considering that the cost of the secondary rocket is relatively high, the secondary rocket recovery can be realized in a more economical way without obviously losing the load coefficient, and the further reduction of the launching cost is brought. The invention provides a flexible parachute wing water recovery carrier rocket with a recovery device which is light in weight, low in pneumatic resistance and good in heat protection capability, and is mainly used for recovering a rocket with a maximum flight speed exceeding 7km/s, and can also be used for recovering a light rocket with a speed lower than the maximum flight speed.

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

In order to solve the technical problems in the prior art, the invention provides a carrier rocket adopting flexible parachute wings to slide on water for recycling and a use method thereof.

A carrier rocket adopting flexible parachute wing water sliding recovery comprises a rocket body, a gesture control engine, a rudder, a rocket engine, a parachute wing cabin, a parachute wing, an air bag cabin and an air bag;

The rocket engine is arranged at the tail part of the rocket body and adopts a liquid rocket engine with a plurality of start and stop functions; the attitude control engine and the rudder are arranged at the position of the arrow body axially far from the mass center, and are distributed and arranged radially outwards for controlling the attitude and the flight direction of the arrow body;

Two umbrella wing cabins are symmetrically arranged on two sides of the upper part of the middle section of the arrow body, two air bag cabins are symmetrically arranged on two sides of the abdomen of the middle section of the arrow body, each umbrella wing cabin accommodates a folded umbrella wing, and each air bag cabin accommodates an air bag in a folded and uninflated state; the air bag is connected with a pressurized gas storage container in the rocket body through an air duct, and is restrained by a cable between the air bag and the rocket body and used for restraining the air bag on two sides of the rocket body;

The umbrella wing comprises an umbrella wing support arm, stay ropes, a piece of cloth and wing ribs; the root of the umbrella wing support arm is hinged with the arrow body through a mounting shaft, and the hinge point is close to the tail side or the head side; the cloth is in a triangle shape after being unfolded, one short edge of the cloth is fixed on the wing support arm in parallel along the extending direction of the wing support arm, the other short edge of the cloth is fixed in the wing cabin in parallel with the longitudinal axis of the arrow body, and the long edge of the cloth is overlapped and fixed with the stay cable; the ribs are radially distributed between the wing arms and the inner wall of the wing cabin; the starting end of the wing rib and the root of the umbrella wing support arm are coaxially hinged in the umbrella wing cabin through the installation shaft and the arrow body, the tail end of the wing rib is fixedly connected with the stay cable, and the wing rib is covered by the cloth and fixedly connected with the wing rib; the starting end of the stay cable is fixed in the parachute wing cabin and is sequentially connected with the tail ends of all the wing ribs, and the tail ends of the stay cable are fixedly connected with the tail ends of the parachute wing support arms;

The parachute wing cabin and the airbag cabin are provided with sealed heat-insulating cabin doors for bearing the temperature and pressure of the rocket in the rocket launching and recovering stage; the sealed heat-insulating cabin door is in a closed state in the launching flight stage, is timely opened according to instructions in the rocket recovery stage, and is unfolded to release the air bag.

Based on the same technical conception, the invention also provides a carrier rocket using method for water sliding recovery by adopting the flexible parachute, which comprises the following steps:

s1, a parachute wing, an air bag and a rudder of a carrier rocket are in a folded and contained state, are ignited and launched from a launching field to lift off, a rocket engine pushes the carrier rocket to bear a load to fly away from the ground/the water surface, and in the flying process, the attitude control engine adjusts the attitude and the flying direction of the carrier rocket;

s2, when the load reaches a preset flying height and speed, the carrier rocket is separated from the load, if the carrier rocket has residual fuel, and the follow-up conventional gliding pneumatic deceleration is difficult to ensure that the pneumatic friction heating does not cause serious ablation on the carrier rocket according to the speed of the carrier rocket entering the atmosphere, the attitude control engine is used for controlling the carrier rocket to adjust the pitch angle, the rocket body head is directed opposite to the current flying speed, the carrier rocket is decelerated by the reverse thrust of the rocket engine until the fuel distributed to the rocket engine is exhausted or the carrier rocket reaches below a controllable speed, and the rocket engine is flamed out;

S3, when the carrier rocket is in a rarefied atmosphere with the height of more than 20km, adjusting the posture and the flight direction of the carrier rocket through a posture control engine, so that the carrier rocket spirals and glides in the rarefied atmosphere, and decelerating the carrier rocket by means of air resistance and gradually reducing the height;

s4, when the speed and pneumatic heating of the carrier rocket are reduced to the conditions that the parachute wings can bear, the attack angle of the carrier rocket is reduced through control of the attitude control engine, the sealed heat-insulating cabin door of the parachute wing cabin is opened according to the instruction, and the parachute wings are unfolded;

S5, when the flying height of the carrier rocket is reduced below 20km, the rudder is unfolded, the attitude and the flying direction of the carrier rocket are controlled by using a rudder deflection or/and attitude control engine control mode, the carrier rocket flies to a wide water surface or sea surface in the deceleration process, and continues to spiral and glide above the water surface or sea surface, and the height is gradually reduced until the minimum stall speed is approached;

s6, when the carrier rocket approaches the water surface/sea surface, selecting an upwind approach direction according to the on-site wind direction and wind speed, and controlling the carrier rocket to slide and land on the water surface or the sea surface through a rudder or/and a gesture control engine;

s7, when the sliding speed of the carrier rocket on the water surface or the sea surface is reduced to be within 10m/S, the air bag cabin opens the sealed heat-insulation cabin door, ejects the air bag, and inflates the air bag through the pressurized gas storage container in the rocket body until the air bag is completely filled;

S8, hoisting the carrier rocket from the water surface or the sea surface to a deck by utilizing a large ship, maintaining and repairing the carrier rocket after returning, inflating and loading fuel, restoring the parachute wings, the air bags and the rudder to a folded state, and re-closing the sealed heat-insulating cabin doors of the parachute wing cabin and the air bag cabin to prepare for the next launching.

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

the carrier rocket adopts a flexible parachute wing structure and a water sliding recovery mode, the recovery device is light in weight, low aerodynamic resistance and good thermal protection performance of the carrier rocket can be kept in an ultra-high speed launching flight stage, the height can be reduced slowly through aerodynamic resistance and lifting force in the recovery stage, the carrier rocket can return to slide down on the water surface independently, reserved fuel is effectively reduced, the complexity of a control system is reduced on the premise of keeping a higher load coefficient, proper landing heading is reasonably selected by utilizing a wide water surface, the safety and reliability of rocket recovery in various complex meteorological environments are enhanced, the comprehensive cost performance is improved, and the carrier rocket 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 view of the overall structure of one embodiment of the present invention in a fully extended state;

FIG. 2 is a schematic view of the overall structure of a folded storage and launching flying state according to one embodiment of the present invention;

FIG. 3 is a schematic view of the overall structure of one embodiment of the invention deployed in a recovery flight configuration;

Reference numerals: 1. an arrow body; 2. an umbrella wing cabin; 3. a wing; 31. a wing arm; 32. stay cables; 33. covering cloth; 34. ribs; 4. an airbag module; 5. an air bag; 6. a gesture control engine; 7. a rudder; 8. rocket engine.

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. 1-3, a specific embodiment of a carrier rocket adopting flexible parachute wing water sliding recovery comprises an rocket body 1, a attitude control engine 6, a rudder 7, a rocket engine 8, a parachute wing cabin 2, a parachute wing 3, an air bag cabin 4 and an air bag 5.

The rocket body 1 is designed according to the aerodynamic shape required by water surface navigation and air flight, not only is a load bearing structure of a carrier rocket, but also provides storage spaces for rocket engines 8, attitude control engines 6 and required combustibles and oxidants, and provides installation spaces for various electromechanical equipment such as navigation, control and energy supply, and installation spaces for a pressurized gas storage container. In this embodiment, the arrow body 1 is a solid of revolution, the head is conical, and the main body is a column.

The rocket engine 8 is arranged at the tail part of the rocket body 1, the rocket engine 8 adopts a liquid fuel engine, the prior art or the new development can be adopted, and the model which can be started and stopped for a plurality of times is adopted to realize intermittent work.

In the specific embodiment, the rudders 7 are in a grid rudder form, 4 parts are uniformly distributed at the tail part of the arrow body 1 along the circumferential direction, the rudders are far away from the mass center, and the corresponding positions of the outer wall surface of the arrow body 1 are provided with avoidance grooves. The grid rudder can be folded close to the outer wall surface of the rocket body 1, so that the air resistance born by the rocket body in the launching flight stage is reduced, and the rudder 7 is unfolded and controlled to deflect when the carrier rocket is recovered, so that the rocket body is used for controlling the attitude and the flight direction of the rocket body 1.

In this embodiment, the attitude control engine 6 is disposed between the rudder 7 and the wing cabin 2, away from the center of mass, and can be implemented by adaptively modifying the technology in the prior art, which is not described in detail.

Two umbrella wing cabins 2 are symmetrically arranged on two sides of the upper part of the middle section of the arrow body 1, two air bag cabins 4 are symmetrically arranged on two sides of the abdomen of the middle section of the arrow body 1, a folded umbrella wing 3 is accommodated in each umbrella wing cabin 2, and an air bag 5 in a folded and uninflated state is accommodated in each air bag cabin 4.

The air bag 5 has good airtight and watertight characteristics, is connected with a pressurized gas storage container in the rocket body 1 through an air duct, is closed through a cabin door during storage, is in a closed state during the launching and flying stage of the carrier rocket, is opened according to instructions during the recovery stage, and is inflated into the air bag 5 after the air bag 5 is ejected out of the air bag cabin 4, the air bag 5 and the rocket body 1 are restrained by a cable, and the air bag 5 is fixed at two sides of the rocket body 1 after the air bag 5 is inflated. The buoyancy generated by the rocket body 1 and the inflated air bag 5 can meet the requirement that the carrier rocket floats on the water surface for a long time, and enough time is reserved for salvaging the ship.

The umbrella wing 3 in the present embodiment comprises an umbrella wing arm 31, a stay cable 32, a cover 33 and a wing rib 34.

The umbrella wing support arm 31 is of a strip-shaped structure, the root is hinged with the arrow body 1 through a mounting shaft, and the hinge point is close to the tail side. The wing arms 31 are made of high-strength, high-rigidity, high-temperature-resistant and light materials, and in the embodiment are carbon fiber composite materials with ceramic materials coated on the surfaces. The function of the parachute wing support arm 31 is controlled to be unfolded, the parachute wing support arm is driven by spring force to rotate around the installation shaft relative to the rocket body 1, other structures of the parachute wing 3 are driven to be unfolded and locked from front to back, a stable bearing structure is formed, main lifting force and resistance required by slow deceleration and height reduction in the carrier rocket recovery stage are generated, and high temperature and dynamic pressure impact during carrier rocket return can be borne.

The lift force and the resistance generated by the wing 3 mainly depend on the area after being unfolded, and the hinge point can be arranged at a position close to the head side of the arrow body 1 according to actual needs, so that the unfolding mode of the wing 3 is changed from front to back and front.

The cover cloth 33 is in a triangle shape after being unfolded, one short side is fixed on the umbrella wing support arm 31 in parallel along the extending direction of the umbrella wing support arm 31, the other short side is fixed in the umbrella wing cabin 2 in parallel with the longitudinal axis of the arrow body 1, and the long side is overlapped and fixed with the stay cable 32. The cloth 33 is made of a high-strength, high-temperature-resistant, flexible and light composite material, and in this embodiment is a carbon fiber cloth with a ceramic material coated on the surface.

The ribs 34 are a plurality of, and the specific number is determined according to the actual needs, and are radially distributed between the wing arms 31 and the inner wall of the wing cabin 2. The starting end of the rib 34 and the root of the wing arm 31 are coaxially hinged with the arrow body 1 through a mounting shaft, the tail end of the rib 34 is fixedly connected with the stay cable 32, and the cover 33 wraps the rib 34 and is fixedly connected with the rib 34 to form a structure like a rib supporting umbrella cloth. The ribs 34 are made of a high strength, high stiffness, high temperature resistant, lightweight material, in this embodiment carbon fiber reinforced aluminum alloy rods.

The starting end of the stay cable 32 is fixed in the wing cabin 2, one end far away from the hinging point of the wing arm 31 is sequentially connected with the tail ends of the ribs 34, and the tail end of the stay cable 32 is fixedly connected with the tail end of the wing arm 31. The stay cable 32 is made of a high strength, high temperature resistant, flexible, lightweight material, in this embodiment a high strength steel cable.

In the carrier rocket launching flight stage, the parachute wings 3 are folded and stored in the parachute wing cabins 2 along the axial direction of the rocket body 1, so that the requirements of reducing air resistance and preventing the damage to the parachute wings 3 caused by high-speed air flow and pneumatic heating in the launching stage are met.

When the carrier rocket is recovered, the parachute wing support arms 31 rotate around the installation shaft under the driving of spring force, the wing ribs 34, the cloth 33 and the stay ropes 32 are driven to synchronously rotate, so that the 2 parachute wings 3 are symmetrically unfolded and locked along the longitudinal symmetrical plane of the rocket body 1 like folding fans, lift force and resistance required by maintaining the carrier rocket to slow speed down in a stagnant air manner and reducing the height are generated, the requirements of slow landing in a gliding manner are realized by virtue of the lift force and the resistance generated by the parachute wings 3 and the rocket body 1, and the low-impact landing and long-time floating on the carrier rocket are realized by combining the storage and inflation of the airbag cabin 3 and the inflation release of the airbag 4, so that the complexity of a fuel reservation, a landing gear system dead load and a vertical lifting control system is effectively reduced.

The parachute wing cabin 2 and the airbag cabin 4 are both provided with sealed heat-insulating cabin doors capable of bearing the temperature and the pressure in the rocket launching and recovering stage, the sealed heat-insulating cabin doors are in a closed state in the carrier rocket launching and flying stage, the high-speed airflow and the high temperature are ensured not to damage the parachute wing 3 and the airbag 5, and the sealed heat-insulating cabin doors are timely opened according to instructions in the rocket recovering stage to release the parachute wing 3 and the airbag 5.

The specific embodiment of the carrier rocket using method adopting the flexible parachute wing water sliding recovery method adopts the carrier rocket, and the launching recovery flow is as follows:

S1, as shown in FIG. 2, the parachute wings 3, the air bags 5 and the rudders 7 of the carrier rocket are in a folded and contained state and are used as boosting rockets, core-level rocket load spaceship, aerospace craft, other carrier rockets or aircrafts and the like to be ignited, launched and lifted off from a land launching field on the sea and close to a wide water surface, the rocket engine 8 pushes the carrier rocket to bear the load to fly away from the ground/the water surface, and in the flying process, the attitude control engine 6 is controlled to jet working medium to form moment on the mass center of the rocket body 1 so as to adjust the attitude and the flying direction of the carrier rocket.

S2, when the load reaches a preset flying height and speed, the carrier rocket is separated from the load, if the carrier rocket has residual fuel, the carrier rocket reenters the atmosphere at a high speed, and the subsequent conventional gliding pneumatic deceleration is difficult to ensure that the pneumatic friction heating does not cause serious ablation on the carrier rocket, the attitude control engine 6 is used for controlling the carrier rocket to adjust the pitch angle at a large angle, so that the head of the rocket body 1 points to the direction opposite to the current flying speed, the rocket engine 8 is used for reversely pushing, the carrier rocket is decelerated until the fuel distributed to the rocket engine 8 is exhausted or the carrier rocket reaches below the controllable speed, and the rocket engine 8 is flamed out.

S3, when the carrier rocket is in the thin atmosphere with the height of more than 20km, the attitude and the flight direction of the carrier rocket are adjusted through the attitude control engine 6, so that the carrier rocket spirals and glides in the thin atmosphere at a larger attack angle, and the carrier rocket is decelerated by virtue of air resistance and gradually reduced in height.

And S4, after the speed of the carrier rocket and the external pneumatic heating are reduced to the condition that the parachute wings 3 can bear, the attack angle of the carrier rocket is moderately reduced by controlling the attitude control engine 6, and the sealed heat-insulating cabin door of the parachute wing cabin 2 is opened according to the instruction, so that the parachute wings 3 are unfolded.

And S5, when the flying height of the carrier rocket is reduced below 20km, the rudder 7 is unfolded, the attitude and the flying direction of the carrier rocket are controlled by using the control mode of the rudder 7 deflection or/and the attitude control engine 6, the carrier rocket flies to the wide water surface or the sea surface in the deceleration process, and continues to spiral and glide above the water surface or the sea surface, and the height is gradually reduced until the minimum stall speed is approached.

S6, when the carrier rocket approaches the water surface/sea surface, selecting the upwind approach direction according to the on-site wind direction and wind speed, and controlling the carrier rocket to slide and land on the water surface or the sea surface at a small attack angle through the rudder 7 or/and the attitude control engine 6.

S7, as shown in figure 1, when the sliding speed of the carrier rocket on the water surface or the sea surface is reduced to be within 10m/S, the air bag cabin 4 opens the sealed heat-insulation cabin door, ejects the air bag 5 in a folded state, and inflates the air bag 5 through the pressurized gas storage container in the rocket body 1 until the air bag 5 is completely filled, so that the carrier rocket is separated from long-time contact with the water surface or the sea surface by the buoyancy of the air bag 5.

S8, hoisting the carrier rocket from the water surface or the sea surface to a deck by utilizing a large ship, maintaining and repairing the carrier rocket after returning, inflating and loading fuel, recovering the parachute wings 3, the air bags 5 and the rudders 7 to a folded state, and re-closing the sealed heat-insulating cabin doors of the parachute wing cabin 2 and the air bag cabin 4 to prepare for the next launching.

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

The carrier rocket combines the advantages of winged recovery and water surface sliding recovery, so that the energy consumption in the recovery process is small, the recovery control mode is simple, the influence of strong crosswind on safe landing is small, the structural quality of the recovery device is effectively reduced by utilizing the parachute wings, the aerodynamic resistance of the carrier rocket in high-speed flight in the launching stage is reduced by designing a sealed parachute wing cabin and folding and containing the parachute wings, the high-temperature ablation of the parachute wings by pneumatic heating is avoided, the carrier rocket can be applied to carrier rockets and recovery and reuse of the upper level of the carrier rockets, and compared with the existing main stream carrier rocket recovery mode, the high load coefficient can be ensured, and the recovery device is low in design complexity, low in price, high in reliability and safety.

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

1. The carrier rocket adopting the flexible parachute wing water sliding recovery comprises a rocket body (1), a gesture control engine (6) and a rudder (7) rocket engine (8), and is characterized by further comprising a parachute wing cabin (2), a parachute wing (3), an air bag cabin (4) and an air bag (5);

The rocket engine (8) is arranged at the tail part of the rocket body (1) and adopts a liquid rocket engine with a plurality of start and stop functions; the attitude control engine (6) and the rudder (7) are arranged at the position of the arrow body (1) axially far away from the mass center, and are distributed and installed along the radial outer side of the arrow body (1) for controlling the attitude and the flight direction of the arrow body (1);

two umbrella wing cabins (2) are symmetrically arranged on two sides of the upper part of the middle section of the arrow body (1), two airbag cabins (4) are symmetrically arranged on two sides of the abdomen of the middle section of the arrow body (1), each umbrella wing cabin (2) accommodates one umbrella wing (3) in a folded state, and each airbag cabin (4) accommodates one airbag (5) in a folded and uninflated state; the air bag (5) is connected with a pressurized gas storage container in the rocket body (1) through an air duct, and the air bag (5) is restrained with the rocket body (1) through a cable for restraining the air bag (5) at two sides of the rocket body (1);

The umbrella wing (3) comprises an umbrella wing support arm (31), stay ropes (32), a cloth (33) and wing ribs (34); the root of the umbrella wing support arm (31) is hinged with the arrow body (1) through a mounting shaft; the cloth (33) is in a triangle shape after being unfolded, one short edge of the cloth is fixed on the umbrella wing support arm (31) in parallel along the extending direction of the umbrella wing support arm (31), the other short edge of the cloth is fixed in the umbrella wing cabin (2) in parallel with the longitudinal axis of the arrow body (1), and the long edge of the cloth is overlapped and fixed with the stay cable (32); the ribs (34) are radially distributed between the wing support arms (31) and the inner wall of the wing cabin (2); the starting end of the wing rib (34) and the root of the umbrella wing support arm (31) are coaxially hinged in the umbrella wing cabin (2) through the installation shaft and the arrow body (1), the tail end of the wing rib (34) is fixedly connected with the stay cable (32), and the wing rib (34) is covered by the cloth (33) and fixedly connected with the wing rib (34); the starting end of the stay cable (32) is fixed in the umbrella wing cabin (2) and is sequentially connected with the tail ends of the wing ribs (34), and the tail end of the stay cable (32) is fixedly connected with the tail end of the umbrella wing support arm (31);

The parachute wing cabin (2) and the airbag cabin (4) are both provided with sealed heat-insulating cabin doors for bearing the temperature and pressure of the rocket in the rocket launching and recovering stage; the sealed heat-insulating cabin door is in a closed state in the launching flight stage, is timely opened according to instructions in the rocket recovery stage, and is used for unfolding the parachute wings (3) and releasing the air bags (5).

2. The carrier rocket according to claim 1, wherein the rudders (7) are grid rudders, at least three rudders are uniformly distributed at the tail part of the rocket body (1) along the circumferential direction, and are arranged far away from the mass center.

3. A launch vehicle according to claim 1, characterized in that the outer wall surface of the rocket body (1) is provided with a avoidance groove for avoiding the rudder (7) in the folded state.

4. A carrier rocket according to claim 1, wherein the wing arms (31) rotate around the mounting shaft to drive the ribs (34), the cloth (33) and the stay cables (32) to synchronously rotate, so that the wings (3) are unfolded or folded, and the wings (3) are completely contained in the wing tanks (2) when folded.

5. A carrier rocket according to claim 1, wherein two parachute wings (3) are symmetrically arranged along the longitudinal symmetry plane of the rocket body (1), the parachute wings (3) are folded and accommodated in the parachute wing cabin (2) along the axial direction of the rocket body (1) in the launching and flying stage of the carrier rocket, and when the carrier rocket is recovered, the two parachute wings (3) are driven by the parachute wing support arms (31) to rotate around respective mounting shafts, and are symmetrically unfolded and locked along the longitudinal symmetry plane of the rocket body (1).

6. A method for using a carrier rocket for water planing recovery by using flexible parachute wings, which is characterized by adopting the carrier rocket according to any one of claims 1 to 5, comprising the following steps:

S1, a parachute wing (3), an air bag (5) and a rudder (7) of a carrier rocket are in a folded and contained state, the carrier rocket is ignited, launched and lifted from a launching field, a rocket engine (8) pushes the carrier rocket to bear a load to fly away from the ground or the water surface, and in the flying process, a posture control engine (6) adjusts the posture and the flying direction of the carrier rocket;

S2, when the load reaches a preset flying height and speed, the carrier rocket is separated from the load, if the carrier rocket has residual fuel, and the follow-up conventional gliding pneumatic deceleration is difficult to ensure that the pneumatic friction heating does not cause serious ablation on the carrier rocket according to the speed of the carrier rocket entering the atmosphere, the attitude control engine (6) is used for controlling the carrier rocket to adjust the pitch angle, so that the head direction of the rocket body (1) is opposite to the current flying speed direction, the carrier rocket is decelerated by the reverse thrust of the rocket engine (8) until the fuel distributed to the rocket engine (8) is exhausted or the carrier rocket reaches below a controllable speed, and the rocket engine (8) is flamed;

S3, when the carrier rocket is in a rarefied atmosphere with the height of more than 20km, adjusting the posture and the flight direction of the carrier rocket through a posture control engine (6) to enable the carrier rocket to spiral and glide in the rarefied atmosphere, and decelerating the carrier rocket by means of air resistance and gradually reducing the height;

S4, when the speed and the pneumatic heating temperature of the carrier rocket are reduced to the conditions that the parachute wings (3) can bear, the attack angle of the carrier rocket is controlled to be reduced through the attitude control engine (6), the sealed heat-insulating cabin door of the parachute wing cabin (2) is opened according to the instruction, and the parachute wings (3) are unfolded;

S5, when the flying height of the carrier rocket is reduced below 20km, the rudder (7) is unfolded, the attitude and the flying direction of the carrier rocket are controlled by using a control mode of deflecting the rudder (7) or/and an attitude control engine (6), the carrier rocket flies to a wide water surface or sea surface in the deceleration process, and continues to spiral and glide above the water surface or the sea surface, and the height is gradually reduced until the minimum stall speed is approached;

S6, when the carrier rocket approaches the water surface/sea surface, selecting the upwind approach direction according to the on-site wind direction and wind speed, and controlling the carrier rocket to slide and land on the water surface or the sea surface through a rudder (7) or/and a gesture control engine (6);

S7, when the sliding speed of the carrier rocket on the water surface or the sea surface is reduced to be within 10m/S, the air bag cabin (4) opens the sealed heat-insulation cabin door, ejects the air bag (5), and inflates the air bag (5) through the pressurized gas storage container in the rocket body (1) until the air bag (5) is completely filled;

S8, hoisting the carrier rocket from the water surface or the sea surface to a deck by utilizing a large ship, maintaining and repairing the carrier rocket after returning, inflating and loading fuel, recovering the parachute wings (3), the air bags (5) and the rudders (7) to a folding state, and re-closing the sealed heat-insulating cabin doors of the parachute wing cabin (2) and the air bag cabin (4) to prepare for the next launching.