Marine reusable carrier rocket system

Abstract

The utility model discloses an offshore reusable carrier rocket system which comprises an offshore rocket platform, a rocket protection cylinder is installed in the offshore rocket platform, a rocket film bag is installed in the rocket protection cylinder, a reusable rocket is arranged in the rocket film bag, and the reusable rocket comprises a first-stage rocket and a second-stage rocket. The first-stage rocket is located below the second-stage rocket, a fuel storage tank and an oxidizing agent storage tank are arranged in the second-stage rocket and the first-stage rocket respectively, and the submerged or semi-submerged rocket can effectively enable the rocket and matched equipment to avoid severe weather on the sea and is suitable for long-distance and long-term continuous launching activities; according to the recovery scheme that a rocket engine is sleeved with a film bag and a parachute is used, the rocket is effectively recovered in the marine environment, and it is not needed that many propellants need to be reserved for reverse thrust like a power reverse thrust recovery mode.

Description

Technical Field

[0001] The utility model relates to the field of launch vehicle systems, in particular to a launch vehicle system that can be reused at sea. Background Art

[0002] A reusable rocket is a vehicle that can be used multiple times. By employing advanced technology and design, it allows the rocket to safely return to Earth and be reused after completing its mission, significantly reducing the cost of space exploration. The realization of reusable rockets relies on a number of key technologies, including but not limited to vertical take-off and landing technology, parachute recovery technology, and winged horizontal recovery technology.

[0003] Existing reusable rockets are primarily launched from space launch sites or bases. However, due to the fixed location, the farther from the equator, the more energy is consumed to launch satellites, resulting in lower efficiency. Some existing rockets are launched from ships, but are still manufactured and stored on land. These launches can only be carried out in good weather, and are prone to inclement weather at sea when far from land. Furthermore, existing technologies require extensive repairs before re-use of recovered rockets (or boosters), limiting their reuse value. Utility Model Content

[0004] In response to the problems in the related technologies, the present invention proposes a reusable launch vehicle system at sea to overcome the above-mentioned technical problems existing in the existing related technologies.

[0005] To this end, the specific technical solutions adopted in this utility model are as follows:

[0006] The reusable marine launch vehicle system includes an offshore rocket platform, a rocket protection tube is installed inside the offshore rocket platform, a rocket film bag is installed inside the rocket protection tube, a reusable rocket is arranged inside the rocket film bag, the reusable rocket includes a first-stage rocket and a second-stage rocket, the first-stage rocket is located below the second-stage rocket, the second-stage rocket and the first-stage rocket are respectively provided with a fuel tank and an oxidizer tank, the fuel tank and the oxidizer tank are respectively provided with a tank film bag, and a liquid inlet is provided on one side of the fuel tank and the oxidizer tank.

[0007] Furthermore, the film bag or film bag is a device made of a flexible film material with a thickness of ≤50mm and ≥0.1mm.

[0008] Furthermore, fixed measurement and control equipment is installed above the offshore rocket platform.

[0009] Furthermore, an external measurement and control device is installed on the outside of the offshore rocket platform.

[0010] Furthermore, a traction mechanism is provided at the bottom of the second-stage rocket and the first-stage rocket, which is composed of a driver, a bow-shaped traction rod, and a bow-shaped traction rod sealing groove. It is used to drag one end of the film bag to cover the rocket engine and seal it, and the other end of the film bag is fixed on the rocket body.

[0011] Furthermore, an oxidant exhaust hole and a fuel exhaust hole are respectively provided inside the oxidant storage tank and the fuel storage tank.

[0012] Furthermore, check valves are installed inside the oxidant exhaust hole and the fuel exhaust hole respectively.

[0013] The beneficial effects of the utility model are:

[0014] 1. Long-range sea-based rocket platforms can launch from most oceanic areas. Launching eastward from the equator can conserve propellant, or, for the same weight of propellant, achieve a greater payload capacity.

[0015] 2. The sea-based rocket platform has multiple functions, including assembly, testing, maintenance, launch, and storage.

[0016] 3. Using submersible or semi-submersible rockets can effectively protect the rockets and supporting equipment from severe weather at sea, making them suitable for long-distance, long-term continuous launch activities.

[0017] 4. Better recovery effect, using film bags to cover the rocket engine and parachute recovery method, effectively recovering the rocket in the marine environment, without the need to reserve a lot of propellant for reverse thrust like the power reverse thrust recovery method. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 This is a schematic diagram of the main structure of a reusable launch vehicle system at sea according to an embodiment of the present utility model;

[0020] Figure 2 This is a partial structural diagram of a first-stage rocket in a marine reusable carrier rocket system according to an embodiment of the present utility model.

[0021] Figure 3 This is a structural diagram of a traction mechanism in a marine reusable launch vehicle system according to an embodiment of the present utility model;

[0022] Figure 4This is a schematic structural diagram of an engine protective film bag in a marine reusable launch vehicle system according to an embodiment of the present utility model.

[0023] In the picture:

[0024] 1. Offshore rocket platform; 2. Rocket protection tube; 3. Reusable rocket; 4. First-stage rocket; 5. Second-stage rocket; 6. Fixed measurement and control equipment; 7. External measurement and control device; 8. Rocket film bag; 9. Tank film bag; 10. Engine protection film bag; 11. Oxidizer exhaust hole; 12. Fuel exhaust hole; 13. Traction mechanism; 131. Fixed seal of film bag; 132. Bow-shaped traction rod; 133. Drive; 134. Bow-shaped traction rod sealing groove; 14. Fuel storage tank; 15. Oxidizer storage tank; 16. Liquid inlet. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0026] According to an embodiment of the present invention, a launch vehicle system that is reusable at sea is provided.

[0027] like Figure 1-4 As shown, according to an embodiment of the utility model, a reusable marine launch vehicle system includes a marine rocket platform 1, a rocket protection tube 2 is installed inside the marine rocket platform 1, a rocket film bag 8 is installed inside the rocket protection tube 2, a reusable rocket 3 is arranged inside the rocket film bag 8, the reusable rocket 3 includes a first-stage rocket 4 and a second-stage rocket 5, the first-stage rocket 4 is located below the second-stage rocket 5, a fuel storage tank 14 and an oxidizer storage tank 15 are respectively provided inside the second-stage rocket 5 and the first-stage rocket 4, a tank film bag 9 is respectively provided inside the fuel storage tank 14 and the oxidizer storage tank 15, a liquid inlet 16 is provided on one side of the fuel storage tank 14 and the oxidizer storage tank 15, a fixed measurement and control device 6 is installed above the marine rocket platform 1, and an external measurement and control device 7 is provided outside the marine rocket platform 1.

[0028] Through the above technical solution, the utility model is composed of three major parts: the offshore rocket platform 1, the carrier rocket system, and the measurement and control system.

[0029] The offshore rocket platform 1 is modified from an unmanned vessel and is used for the assembly, testing, maintenance, launch and storage of reusable rockets 3. There is a corresponding launch hole in the operating platform with a diameter of 12 meters.

[0030] The launch vehicle system is designed as a three-stage launch vehicle with a diameter of 9 meters and uses methane and liquid oxygen propellants. The rocket's fuel tank 14 is made of titanium alloy, and the oxidizer tank 15 is made of 304L material. After the rocket body is assembled, it awaits a possible launch mission at any time. If encountering inclement weather at sea during non-launch missions, the rocket body dives to avoid inclement weather. Before diving, the rocket body is filled with seawater to balance the internal and external water pressure and buoyancy. The method for filling the fuel tank 14 and oxidizer tank 15 with seawater is as follows: First, the reusable rocket 3, the second stage 5, the first stage 4, and the rocket film bag 8 are wrapped and sealed to prevent seawater from entering the engine and causing corrosion. Then, a tank film bag 9 is placed inside the fuel tank 14 or oxidizer tank 15. Seawater enters the tank film bag 9 through the liquid inlet 16, preventing direct contact between the seawater and the inner wall of the fuel tank 14 or oxidizer tank 15. Since titanium alloy is not susceptible to seawater corrosion, seawater can be directly poured into the fuel tank 14 without the need for a film bag for isolation. When the launch mission was in progress and encountered bad weather at sea, the rocket was not injected with seawater, but dived with propellant to avoid the bad weather at sea.

[0031] The measurement and control system consists of fixed measurement and control equipment 6 installed on the offshore rocket platform 1 and an external measurement and control device 7. The fixed measurement and control equipment 6 contains at least a gyroscope and a laser sensor, transmitting measurement and control data in real time. The external measurement and control device 7 is operated by a measurement and control vessel. The fixed measurement and control equipment 6 installed on the offshore rocket platform 1 uses inertial devices and a GNSS system to provide accurate position, direction, and time measurement and control information during the initial launch phase. The external measurement and control device 7 provides measurement and control information during the rocket's flight.

[0032] The tank film bag 9 and the rocket film bag 8 are polytetrafluoroethylene film bags. The fixed seal 131 of the film bag, the bow traction rod 132, the driver 133 and the bow traction rod sealing groove 134 are all made of high temperature resistant materials, and the driver 133 is hydraulic or electric.

[0033] like Figure 1-4 As shown, according to the marine reusable launch vehicle system of an embodiment of the present invention, a traction mechanism 13 is provided at the bottom of the second-stage rocket 5 and the first-stage rocket 4, and the traction mechanism 13 includes a fixed seal 131 of the film bag, and a bow-shaped traction rod 132 is provided on one side of the fixed seal 131 of the film bag, and a driver 133 is connected between the two ends of the fixed sealing plate 131 of the film bag and the two ends of the bow-shaped traction rod 132, a pressure or electric driver is connected, and the engine protection film bag 10 is connected to the periphery of the fixed sealing plate 131 of the film bag and the bow-shaped traction rod 132, which is folded and placed between the two during installation, and a bow-shaped traction rod sealing groove 134 is opened inside the first-stage rocket 4 and the second-stage rocket 5, and an oxidizer exhaust hole 11 and a fuel exhaust hole 12 are respectively provided inside the oxidizer storage tank 15 and the fuel storage tank 14, and a check valve is respectively installed inside the oxidizer exhaust hole 11 and the fuel exhaust hole 12.

[0034] Through the above technical solution, the core content of the rocket launch and recovery method is: the rocket is launched from the offshore rocket platform 1, and the pre-landing area of the first-stage rocket 4 is the ocean. After completing the mission, the first-stage rocket 4 separates from the second-stage rocket 5 and enters the recovery program. The attitude is adjusted in the air, the engine side faces the wind, and the engine of the first-stage rocket 4 is completely shut down. The atmosphere and a small amount of remaining low-temperature propellant are used to cool the rocket engine in a high-temperature state. When it reaches a predetermined height, the first-stage rocket 4 opens the parachute, and a visual control system is used to control the parachute away from the pre-landing area ship on the ocean. After the rocket engine drops to a predetermined temperature, the driver 133 is started to drive the bow traction rod 132 to move. The bow traction rod 132 drags the engine protection film bag 10 to move and wrap the rocket engine. Then the bow traction rod is embedded in the bow traction rod sealing groove and sealed, so that the carbon fiber / aramid fiber mixed woven engine protection film bag 10 wraps and seals the rocket engine to prevent seawater from entering the engine and causing corrosion. The first-stage rocket 4 lands in a controlled manner on the sea surface, and then the recovered first-stage rocket 4 is towed back to the offshore rocket platform 1 or land by a ship for inspection and reuse.

[0035] The second stage rocket 5 uses the same recovery method as the first stage rocket 4.

[0036] If necessary, the booster can be recovered in the same way as the first stage rocket.

[0037] After the rocket engine is sealed with a film bag, a small amount of volatile gas is still released from the rocket through the oxidizer exhaust hole 11 and the fuel exhaust hole 12 with a check valve function provided on the rocket body.

[0038] In order to facilitate understanding of the above technical solutions of the present invention, the working principle or operation method of the present invention in actual process is described in detail below.

[0039] In summary, with the aid of the above technical solution of the present invention, the recovery method of a reusable launch vehicle system at sea includes the following steps:

[0040] Step 1: The rocket is launched from the offshore rocket platform 1. The first-stage rocket 4 is pre-landed in the ocean. After completing its mission, the first-stage rocket 4 separates from the second-stage rocket 5 and enters the recovery process.

[0041] Step 2: Adjust the attitude in the air, with the engine side facing the wind, completely shut down the engine of the first-stage rocket, and use the atmosphere and a small amount of remaining cryogenic propellant to cool the high-temperature rocket engine;

[0042] Step 2: When reaching the predetermined height, the first stage rocket 4 opens the parachute and uses a visual control system to control the parachute away from the pre-landing area ship on the ocean;

[0043] Step 3: After the rocket engine cools down to a predetermined temperature, the driver 133 is activated, driving the bow-shaped traction rod 132 to move. The bow-shaped traction rod 132 drags the engine protection film bag 10 to move and wrap the rocket engine. The bow-shaped traction rod is then inserted into the bow-shaped traction rod sealing groove and sealed. The carbon fiber / aramid fiber hybrid woven engine protection film bag 10 wraps and seals the rocket engine to prevent seawater from entering the engine and causing corrosion.

[0044] Step 4: The first-stage rocket 4 makes a controlled landing on the sea surface, and then the recovered first-stage rocket 4 is towed back to the offshore rocket platform 1 or land by a ship for inspection and reuse.

[0045] The second stage rocket 5 uses the same recovery method as the first stage rocket 4.

[0046] If necessary, the booster can be recovered in the same way as the first stage rocket.

[0047] After the rocket engine is sealed with a film bag, a small amount of volatile gas is still released from the rocket through the oxidizer exhaust hole 11 and the fuel exhaust hole 12 with a check valve function provided on the rocket body.

[0048] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A sea-based reusable launch vehicle system, characterized in that: The invention comprises an offshore rocket platform (1), wherein a rocket protection tube (2) is installed inside the offshore rocket platform (1), a rocket film bag (8) is installed inside the rocket protection tube (2), a reusable rocket (3) is arranged inside the rocket film bag (8), and the reusable rocket (3) comprises a first-stage rocket (4) and a second-stage rocket (5), wherein the first-stage rocket (4) is located below the second-stage rocket (5), a fuel storage tank (14) and an oxidizer storage tank (15) are respectively arranged inside the second-stage rocket (5) and the first-stage rocket (4), wherein tank film bags (9) are respectively arranged inside the fuel storage tank (14) and the oxidizer storage tank (15), and a liquid inlet (16) is provided on one side of the fuel storage tank (14) and the oxidizer storage tank (15).

2. The marine reusable launch vehicle system according to claim 1, characterized in that: A fixed measurement and control device (6) is installed above the offshore rocket platform (1).

3. The marine reusable launch vehicle system according to claim 2, characterized in that: An external measurement and control device (7) is provided outside the offshore rocket platform (1).

4. The marine reusable launch vehicle system according to claim 3, characterized in that: The bottom of the second-stage rocket (5) and the first-stage rocket (4) is provided with a traction mechanism (13), the traction mechanism (13) includes a fixed seal (131) of a film bag, a bow-shaped traction rod (132) is provided on one side of the fixed seal (131) of the film bag, a driver (133) is connected between the two ends of the fixed seal (131) of the film bag and the two ends of the bow-shaped traction rod (132), the fixed seal (131) of the film bag and the bow-shaped traction rod (132) are connected to the engine protection film bag (10) at the periphery, and are folded and placed between the two during installation, and the first-stage rocket (4) and the second-stage rocket (5) are provided with a bow-shaped traction rod sealing groove (134).

5. The marine reusable launch vehicle system according to claim 4, characterized in that: The oxidant storage tank (15) and the fuel storage tank (14) are respectively provided with an oxidant exhaust hole (11) and a fuel exhaust hole (12).

6. The marine reusable launch vehicle system according to claim 5, characterized in that: Check valves are respectively installed inside the oxidant exhaust hole (11) and the fuel exhaust hole (12).

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