Recyclable rocket

Abstract

The invention discloses a recoverable rocket, and belongs to the technical field of liquid rocket recovery. Four or more small electric pump circulation rocket engines are fixedly installed on the upper middle portion of the first-stage rocket body in the circumferential direction at equal intervals, rocket nozzles face the right lower portion, and the center lines of the small electric pump circulation rocket engines are parallel to the center line of the first-stage rocket body. An oxidizing agent storage tank and a fuel storage tank which are needed by the small electric pump circulation rocket engine are installed on the upper middle portion of the first-stage rocket. Four or more small electric pump circulation rocket engines are fixedly installed on the upper middle portion of a first-stage rocket body in the circumferential direction at equal intervals; the flight computer obtains the real-time attitude and position information of the rocket body, the thrust of the four or more small electric pump circulation rocket engines is adjusted, and the rocket body is controlled to obliquely fly to a designated recovery area through the thrust difference; and the thrust of each small electric pump circulation rocket engine is continuously adjusted, so that the attitude of the rocket body is stable, and accurate and stable recovery is realized.

Description

Technical Field

[0001] This invention relates to the field of liquid rocket recovery technology. Background Technology

[0002] This invention relates to the field of liquid rocket recovery technology. Currently, rocket recovery is a major trend in rocket technology development. Compared to traditional expendable launch vehicles, which cannot be recovered due to the non-recoverable rocket body and engines, traditional rocket launches are extremely costly. Furthermore, rocket debris poses a threat to personnel and property in the landing area. For these reasons, rocket reusability has become a major future development trend, potentially reducing launch costs by up to 80% and allowing for precise control of the landing area. Currently, many rocket companies are studying the reusable launch vehicle "Falcon 9," which uses eight identical rocket engines, evenly spaced around a central engine at 360-degree intervals. Vertical recovery of the first stage is achieved through the power adjustment and oscillation of this central engine. However, this method faces challenges in the final stage of landing (at an altitude of 2km). Due to the large aspect ratio, weight, and high center of gravity of the first stage rocket, the large lateral area of ​​the rocket body makes it susceptible to interference torques from crosswinds exceeding the rocket's lateral control capabilities. Precise landing on the recovery ship or landing site requires extremely high precision in the power adjustment and oscillation of the rocket engines. Summary of the Invention

[0003] This invention discloses a reusable rocket, which uses four or more small electric pump circulating rocket engines fixedly installed at equal intervals along the circumference of the upper middle part of the first-stage rocket body to increase the thrust of the rocket engines. This addresses the problem of insufficient oscillation accuracy of rocket engines in existing rocket recovery methods, thereby achieving precise landing and recovery of the first-stage rocket in the final stage.

[0004] To achieve the above-mentioned objectives, the technical solution adopted by this invention is as follows: This invention provides a reusable rocket, comprising: The upper middle part of the first-stage rocket body is equipped with four or more small electric pump cycle rocket engines, as well as the required oxidizer tank and fuel tank, which are fixedly installed at equal intervals along the circumference. The centerline of the small electric pump-cycle rocket engine is parallel to the centerline of the first stage rocket body, and the nozzle of the electric pump-cycle rocket engine is oriented directly downwards. The four or more small electric pump-cycle rocket engines mentioned above are fixedly installed at a certain distance from the rocket body to avoid burning the rocket body when the electric pump-cycle rocket engines are working; The electric pump-cycle rocket engine in question has a fairing fixedly mounted on its exterior to reduce drag; The oxidizer tank and fuel tank required for the small electric pump cycle rocket engine are installed in the upper part of the first stage rocket.

[0005] This invention involves fixing four or more small electric pump-cycle rocket engines at equal intervals along the circumference of the upper middle part of the first-stage rocket body. By controlling the flight computer, the thrust of the electric pump-cycle rocket engines in the four directions is adjusted, allowing the rocket body to tilt and fly to the designated position. This achieves stable control and precise and smooth recovery during the final stage of rocket recovery (at an altitude of 2km).

[0006] Figure 1 This is a structural and cross-sectional schematic diagram of a reusable rocket according to the present invention; Figure 2 A schematic diagram showing the equidistant fixed installation of four small electric pump circulating engines; Figure 3 A schematic diagram showing the operation of a four-small electric pump circulating engine; Figure 4 A schematic diagram showing the directions of the X and Z coordinate axes; Figure 5 A schematic diagram illustrating the force analysis of a reusable rocket during tilted flight and recovery. The attached figures are labeled as follows: 1. Rocket body; 2. Small electric pump cycle engine; 3. Oxidant tank for the small electric pump cycle engine; 4. Fuel tank for the small electric pump cycle engine; 5. Fairing; 6. Main rocket engine; 7. Grid fins; 21, 22, 23, and 24 are the numbers of the four small electric pump cycle engines. 8. In the diagram, F21, F22, F23, and F24 represent the thrust directions of the four small electric pump circulating engines during operation, respectively. 9. In the diagram, Fx21, Fx24, Fy21, and Fy24 represent the directions of the horizontal and vertical components of the forces generated by F21 and F24, respectively. 10. In the diagram, G represents the direction of gravity of the rocket. Detailed Implementation

[0007] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0008] One objective of this invention is to provide a novel reusable rocket. This invention involves the fixed installation of four or more small electric pump-driven recirculation rocket engines at equal intervals along the circumference of the upper middle part of the first-stage rocket body. Through computer control, the thrust of the electric pump-driven recirculation rocket engines in the four directions is adjusted. This addresses the problems of existing reusable rockets, such as the large aspect ratio, heavy weight, and high center of gravity of the first stage, the large lateral area of ​​the rocket body, and the tendency for lateral winds to cause interference torques exceeding the rocket's lateral control capabilities. It also addresses the extremely high requirements for the power adjustment and oscillation precision of the rocket engines. This invention achieves stable control and precise, smooth recovery during the final stage of rocket recovery (at an altitude of 2km).

[0009] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0010] like Figure 1 As shown, the first-stage recovery rocket includes: rocket body 1, main rocket engine 6, coolant RCS, rocket oxidizer and fuel tank, rocket grid fins, navigation system, altimeter, power system, and other necessary structural systems. One of the key innovations of this invention is that the overall rocket structure includes: a small electric pump cycle engine 2, an oxidizer tank 3 for the small electric pump cycle engine, a fuel tank 4 for the small electric pump cycle engine, and a fairing 5 for the small electric pump cycle engine. Four or more small electric pump cycle rocket engines 2 are fixedly installed at equal intervals along the circumference of the upper middle part of the first-stage rocket body 1. These four or more small electric pump cycle rocket engines 2 are fixedly installed at a certain distance from the rocket body 1. This design uses four small electric pump cycle rocket engines 2. The nozzles of the small electric pump cycle rocket engines 2 face directly downwards, and the centerline of the small electric pump cycle rocket engines 2 is parallel to the centerline of the first-stage rocket body 1. The oxidizer tank 3 and fuel tank 4 required for the small electric pump cycle rocket engines 2 are installed in the upper middle part of the first-stage rocket body 1. This invention involves fixing four or more small electric pump-cycle rocket engines 2 at equal intervals along the circumference of the upper middle part of the first-stage rocket body 1. This design uses four small electric pump-cycle rocket engines 2. When the altimeter detects that the rocket has reached an altitude of 2km, the main rocket engine 7 and the four small electric pump-cycle rocket engines 2 ignite simultaneously to decelerate. After the speed decreases, the rocket body 1 is made as perpendicular to the ground as possible. When the rocket decelerates to a relatively stationary position relative to the ground, the main rocket engine 6 stops working. With the help of the navigation system and altimeter system, the thrust of the four electric pump-cycle rocket engines 2 is adjusted by computer control to tilt the rocket body 1 to the designated position. This design uses a 10-degree tilt of the rocket body 1 to achieve stable control and precise and smooth recovery in the final stage (at an altitude of 2km) during rocket recovery.

[0011] like Figure 2 and Figure 3 As shown, four small electric pump-cycle engines 2, numbered 21, 22, 23, and 24, are fixedly installed at equal intervals around the upper part of the first-stage rocket body 1, and are equipped with fairings 5 ​​to reduce drag. The centerlines of the four small electric pump-cycle rocket engines 2 are parallel to the centerline of the first-stage rocket body 1, and the rocket nozzles face directly downwards. The four or more small electric pump-cycle rocket engines are fixedly installed at a certain distance from the rocket body to avoid burning the rocket body when the electric pump-cycle rocket engines are working.

[0012] like Figure 3 and Figure 4 As shown, when the barometric altimeter detects that the reusable rocket has reached an altitude of 1 km, the main rocket engine 6 and four small electric pump cycle rocket engines 2 ignite to decelerate and bring the rocket body 1 perpendicular to the ground. Once the rocket has decelerated to a relatively stationary position relative to the ground, the main rocket engine 6 stops operating, while the four small electric pump cycle rocket engines 2 continue operating, tilting the rocket body 1 to the designated location until successful recovery. This design uses a 10-degree tilt for the rocket body 1, and the force analysis is as follows: 1. The rocket's gravity (G) Reusable rockets are subject to Earth's gravity, with the direction of gravity pointing vertically downwards; the effects of fuel and oxidizer consumption during rocket hovering and descent must be taken into account when the four small electric pump cycle engines are working. 2. Analysis of the rocket's hovering motion The rocket hovering condition is given by the rocket's gravity G = F21 + F22 + F23 + F24. In reality, considering the different air densities at hovering altitudes and the consumption of remaining rocket fuel and oxidizer, the thrust (F21, F22, F23, F24) of the four small electric pump cycle engines will also change accordingly, requiring specific analysis based on the actual situation. 3. Analysis of the rocket's horizontal movement When the rocket is hovering in the air, if F21+F22>F23+F24, the rocket body 1 will tilt in the -X direction. F21, F22, F23, and F24 will generate component forces Fx21, Fy21, Fx22, Fy22, Fx23, Fy23, Fx24, and Fy24, respectively. The rocket will then generate a thrust in the -X direction equal to Fx21+Fx22+Fx23+Fx24, causing the rocket to move in the -X direction. When the rocket is hovering in the air, if F21+F22<F23+F24, the rocket body 1 will tilt in the X direction. F21, F22, F23, and F24 will generate component forces Fx21, Fy21, Fx22, Fy22, Fx23, Fy23, Fx24, and Fy24, respectively. The rocket will then generate a thrust in the X direction equal to Fx21+Fx22+Fx23+Fx24, causing the rocket to move in the X direction. When the rocket is hovering in the air, if F21+F24>F22+F23, the rocket body 1 will tilt in the -Z direction. F21, F22, F23, and F24 will generate component forces Fz21, Fy21, Fz22, Fy22, Fz23, Fy23, Fz24, and Fy24, respectively. The rocket will then generate a thrust in the -Z direction of Fz21+Fz22+Fz23+Fz24, causing the rocket to move in the -Z direction. When the rocket is hovering in the air, if F21+F24 < F22+F23, the rocket body 1 will tilt in the Z direction. F21, F22, F23, and F24 will generate component forces Fz21, Fy21, Fz22, Fy22, Fz23, Fy23, Fz24, and Fy24, respectively. The rocket will then generate a thrust in the Z direction equal to Fz21+Fz22+Fz23+Fz24, causing the rocket to move in the Z direction. F21, F22, F23, and F24 can also be analyzed according to specific circumstances. The flight computer obtains the real-time attitude and position information of the rocket body, adjusts the thrust of the four or more small electric pump cycle rocket engines, controls the rocket body to tilt and fly to the designated recovery area through thrust difference, and continues to adjust the thrust of each small electric pump cycle rocket engine to stabilize the attitude of the rocket body and achieve a precise and smooth landing. 4. The rocket was recovered and landed. The rocket landing conditions are: rocket gravity G > F21 + F22 + F23 + F24. In reality, considering the different air densities at hovering altitudes and the consumption of remaining rocket fuel and oxidizer, the thrust (F1, F2, F3, F4) of the four small electric pump cycle engines will also change accordingly, and specific analysis is needed based on the actual situation. When the rocket's gravity G = F21 + F22 + F23 + F24, the rocket is in a relatively stationary state. After a smooth landing and recovery, the four small electric pump cycle engines can stop working simultaneously.

[0013] Compared with other existing rocket recovery methods, this novel reusable rocket technology has the following advantages: (1) To solve the problems of large slenderness ratio, heavy weight and high center of gravity of the first stage of the rocket body during the recovery and landing of the existing rocket, the new reusable rocket technology scheme utilizes the thrust of four or more small electric pump circulating rocket engines fixedly installed around the upper part of the first stage rocket body for recovery and landing, with a low center of gravity and a more stable landing and recovery. (2) By controlling the electric pump cycle rocket engine in four directions through computer control, the thrust of the electric pump cycle rocket engine was adjusted to achieve stable control and precise and smooth recovery in the final stage (2km above sea level) of rocket recovery, which solved the problem that the requirements for the power adjustment and swing accuracy of the main rocket engine during the landing of the current recovered rocket are very high. (3) In this new type of reusable rocket technology, if the rocket lands at an angle, the thrust of the electric pump circulating rocket engine in four directions can be increased immediately to allow the rocket to take off again and attempt a second recovery landing.

[0014] The above are merely preferred embodiments of the present invention, and the scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of this invention are protected by this invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of this invention should also be considered within the scope of protection of this invention.

Claims

1. A reusable rocket, characterized in that, include: The first-stage rocket body, four or more small electric pump cycle rocket engines, and the required oxidizer and fuel tanks.

2. A reusable rocket according to claim 1, characterized in that, The four or more small electric pump-cycle rocket engines are fixedly installed at equal intervals along the circumference in the upper middle part of the first-stage rocket body.

3. A reusable rocket according to claims 1 and 2, characterized in that, The nozzle of the small electric pump-cycle rocket engine is oriented directly downwards.

4. A reusable rocket according to claims 2 and 3, characterized in that, The centerline of the small electric pump-cycle rocket engine is parallel to the centerline of the first-stage rocket body.

5. The reusable rocket according to claim 1, characterized in that, The oxidizer tank and fuel tank required for the small electric pump cycle rocket engine are installed in the upper part of the first stage rocket.

6. A method for recovering a reusable rocket based on any one of claims 1-5, characterized in that, include: During the final stage of recovery and landing of the first-stage rocket body, the flight computer acquires the real-time attitude and position information of the rocket body; adjusts the thrust of the four or more small electric pump cycle rocket engines, and controls the rocket body to tilt and fly to the designated recovery area through thrust difference; continuously adjusts the thrust of each small electric pump cycle rocket engine to stabilize the rocket body attitude and achieve precise and stable recovery.

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