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 periphery of the upper middle portion of the first-stage rocket body, rocket nozzles face outwards and obliquely downwards, and the center lines of the small electric pump circulation rocket engines and the center line of the first-stage rocket body are inclined by 15-30 degrees. 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. The four or more electric pump circulation rocket engines are fixedly and obliquely installed on the periphery of the upper middle portion of the first-stage rocket body, the thrust of the electric pump circulation rocket engines in the four directions is controlled and adjusted through a computer, and stable control and accurate and stable recovery at the final stage (the altitude is 1 km) during rocket recovery are achieved.

Description

Technical Field

[0001] The invention relates to the technical field of liquid rocket recovery. Background Art

[0002] At present, rocket recovery is the main trend in the development of rocket technology. Compared with traditional disposable launch vehicles, the cost of traditional rocket launches is very high because the rocket body and rocket engine cannot be recovered. Not only that, the rocket debris will also pose a certain threat to personnel and property in the landing area. Based on the above reasons, the recoverability of rockets has become the main development trend of rockets in the future, which can greatly reduce the launch cost by 80% and accurately control the landing area. At this stage, many rocket companies are learning the recoverable launch vehicle "Falcon 9" rocket, which uses 8 rocket engines of the same type, which are installed at 360 degrees around a center engine of the same type. The power adjustment and swing of a rocket engine of the same type in the center realizes the vertical recovery of the first-stage rocket body. However, this scheme is recovered in the final stage of rocket landing (1km above sea level). Due to the large slenderness ratio of the rocket body to the sub-stage, the heavy weight, and the high center of gravity, the lateral area of ​​the rocket body is large, and the lateral wind can easily cause interference torque that exceeds the rocket's own lateral control ability. If you want to land accurately on the recovery ship or recovery site, there are very high requirements for the power adjustment and swing accuracy of the rocket engine. Summary of the invention

[0003] The present invention discloses a recoverable rocket, which can utilize the thrust of four or more small electric pump circulation rocket engines fixedly installed around the middle and upper part of the first-stage rocket body to solve the problems of insufficient power regulation ability and swing accuracy of the rocket engine in the above-mentioned existing rocket recovery methods, and realize accurate landing and recovery of the first-stage rocket in the final stage.

[0004] In order to achieve the above-mentioned object of the invention, the technical solution adopted by the present invention is: The present invention provides a recyclable rocket, comprising: Four or more small electric pump-cycle rocket engines and the necessary oxidizer tanks and fuel tanks are fixedly installed at equal intervals around the middle and upper part of the first-stage rocket body; The nozzle of the claimed electric pump-cycle rocket engine is oriented outward and obliquely downward, and the centerline of the small electric pump-cycle rocket engine is inclined by 15 to 30 degrees to the centerline of the first-stage rocket body; The claimed electric pump cycle rocket engine has a fairing fixedly mounted on the outside to reduce resistance; The oxidizer tank and fuel tank required for the claimed small electric pump cycle rocket engine are installed in the upper middle part of the first stage rocket.

[0005] The present invention installs four or more electric pump-cycle rocket engines at an angle around the upper part of the first-stage rocket body, and adjusts the thrust of the electric pump-cycle rocket engines in four directions through flight computer control, thereby achieving stable control and precise and smooth recovery in the final stage (the last 1 km) of rocket recovery. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] Figure 1 The structure and cross-sectional schematic diagram of a recoverable rocket of the present invention; Figure 2 A schematic diagram of four small electric pump cycle engines fixedly installed at equal intervals; Figure 3 This is a schematic diagram of the force analysis of a recoverable rocket during recovery; Wherein, the accompanying drawings are marked as follows: 1. Rocket body; 2. Small electric pump cycle engine; 3. Oxidant tank required for small electric pump cycle engine; 4. Fuel tank required for small electric pump cycle engine; 5. Fairing; 6. Recovery rack; 7. Main rocket engine; 8. ①, ②, ③, ④ in the figure are the numbers of four small electric pump circulation engines; 9. In the figure, F1, F2, F3, and F4 are respectively ①, ②, ③, and ④, which are the thrust directions of the four small electric pump cycle engines when they are working; 10. In the figure, Fx1, Fx2, Fx3, Fx4, Fy1, Fy2, Fy3, and Fy4 are the directions of the horizontal and vertical components of force generated by F1, F2, F3, and F4 respectively; 11. In the figure, G is the direction of gravity of the rocket. DETAILED DESCRIPTION

[0007] 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 described embodiments 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 creative work are within the scope of protection of the present invention.

[0008] One of the purposes of the present invention is to provide a new type of recoverable rocket. The present invention installs four or more electric pump circulation rocket engines in a fixed and inclined manner around the middle and upper part of the first-stage rocket body, and adjusts the thrust of the electric pump circulation rocket engines in four directions through computer control. The problems of the existing rocket recovery rocket body, such as large slenderness ratio, large weight, and too high center of gravity, large lateral area of ​​the rocket body, and lateral wind easily causing interference torque exceeding the lateral control capability of the rocket itself, have very high requirements on the power regulation and swing accuracy of the rocket engine, and realize stable control and precise and smooth recovery in the final stage (1km above sea level) of rocket recovery.

[0009] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is 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: a rocket body 1, a main rocket engine 7, a cold air RCS, a recovery rack 6, rocket oxidizer and fuel tanks, a rocket grid rudder, a navigation system, a barometric altimeter, an electric power system and other structural systems necessary for the rocket. One of the innovative focuses of the scheme of the present invention is that the overall structure of the rocket includes: a small electric pump cycle engine 2, an oxidizer tank 3 required for the small electric pump cycle engine, a fuel tank 4 required for the small electric pump cycle engine, and a fairing 5 of the small electric pump cycle engine. Four or more small electric pump cycle rocket engines 2 are fixedly installed around the middle and upper part of the first-stage rocket body 1. This design adopts four small electric pump cycle rocket engines 2. The direction of the rocket nozzle is outward and obliquely downward. The center line of the small electric pump cycle rocket engine 2 is inclined by 15 to 30 degrees with the center line of the first-stage rocket body 1. This design adopts a 30-degree inclined design. The oxidizer tank 3 and the fuel tank 4 required by the small electric pump cycle rocket engine 2 are installed in the middle and upper part of the first-stage rocket body 1. The present invention installs four or more electric pump circulation rocket engines 2 in a fixed and inclined manner around the middle and upper part of the first-stage rocket body 1. When the barometric altimeter detects that the rocket reaches an altitude of 1 km, the main rocket engine 7 and the four small electric pump circulation rocket engines 2 are ignited and decelerated at the same time. After the speed is reduced, the rocket body 1 is made as vertical as possible to the ground. When the rocket is decelerated to be relatively still with the ground, the main rocket engine 7 stops working. With the help of the navigation system and the barometric altimeter and other systems, the thrust of the electric pump circulation rocket engine in four directions is adjusted through computer control to achieve stable control and accurate and smooth recovery in the final stage (1 km above sea level) of rocket recovery. The recovery methods include landing leg recovery and recovery by recovery rack 6. The present design adopts the recovery method of recovery rack 6, which can reduce the weight of the rocket.

[0011] like Figure 2As shown, four small electric pump circulation engines 2 are numbered ①, ②, ③, and ④, and are fixedly installed around the upper and middle parts of the first-stage rocket body 1 at equal intervals, and are equipped with a fairing 5 to reduce resistance; the center lines of the four small electric pump circulation rocket engines 2 are inclined by 15 to 30 degrees to the center line of the first-stage rocket body 1. If the angle is less than 15 degrees, the tail flame of the small electric pump circulation rocket engine 2 may burn the rocket body. If the angle is greater than 30 degrees, the upward force generated by the four small electric pump circulation rocket engines 2 will become very small. This design adopts a 30-degree inclined design, and the direction of the rocket nozzle is obliquely downward outward.

[0012] like Figure 3 As shown, when the recyclable rocket reaches an altitude of 1km, the main rocket engine 7 and four small electric pump circulation rocket engines 2 are ignited at the same time to decelerate and make the rocket body 1 perpendicular to the ground. When the rocket decelerates to a relative stillness relative to the ground, the main rocket engine 7 stops working, and the four small electric pump circulation rocket engines 2 continue to work until the recovery is successful. The force analysis is as follows: 1. The rocket's gravity (G) The recoverable rocket is subject to the gravity of the earth, and the gravity direction is vertically downward; the hovering and descent of the rocket must take into account the consumption of fuel and oxidant when the four small electric pump cycle engines 2 are working; 2. The thrusts (F1, F2, F3, F4) of the four small electric pump circulation engines when they are working, and the horizontal force components (Fx1, Fx2, Fx3, Fx4) and vertical force components (Fy1, Fy2, Fy3, Fy4) generated by each of them F1 horizontal component Fx1: Fx1= F1* cos30° ; F1 vertical component Fy1: Fy1=F1*sin30°=1 / 2F1; F2 horizontal component Fx2: Fx2 = F2* cos30°; F2 vertical component Fy2: Fy2=F2*sin30°=1 / 2F2; F3 horizontal component Fx3: Fx3 = F3* cos30°; F3 vertical component Fy3: Fy3=F3*sin30°=1 / 2F3; F4 horizontal component Fx4: Fx4 = F4* cos30°; F4 vertical component Fy4: Fy4=F4*sin30°=1 / 2F4; Without considering other factors such as the consumption of rocket fuel and oxidizer, when the rocket gravity G=Fy1+Fy2+Fy3+Fy4=1 / 2(F1+F2+F3+F4), the rocket is in a relatively static state; 3. Rocket hover analysis The rocket hovering condition is that the rocket gravity G=Fy1+Fy2+Fy3+Fy4=1 / 2(F1+F2+F3+F4). In reality, considering the different air density at the hovering altitude and the consumption of the remaining rocket fuel and oxidizer, the thrust (F1, F2, F3, F4) of the four small electric pump cycle engines will also change accordingly, which needs to be analyzed according to the specific situation in reality. 4. The rocket moves horizontally When the rocket is hovering in the air, Fx1=Fx3=Fx4<Fx2, and the rocket will move in the direction of the thrust of F2; When the rocket is hovering in the air, Fx2=Fx3=Fx4<Fx1, and the rocket will move in the direction of the thrust of F1; When the rocket is hovering in the air, Fx1=Fx2=Fx4<Fx3, and the rocket will move in the direction of the thrust of F3; When the rocket is hovering in the air, Fx1=Fx2=Fx3<Fx4, and the rocket will move in the direction of the F4 thrust; They can also cooperate with each other, and need to analyze the specific situation to make the rocket move quickly and accurately to the correct position; 5. The rocket was recovered and landed The landing condition of the rocket is that the rocket gravity G>Fy1+Fy2+Fy3+Fy4=1 / 2(F1+F2+F3+F4)In reality, considering the different air density at the hovering altitude and the consumption of the remaining rocket fuel and oxidizer, the thrust (F1, F2, F3, F4) of the four small electric pump cycle engines will also change accordingly, which needs to be analyzed according to the specific situation in reality; When the rocket's gravity G=Fy1 +Fy2 +Fy3 +Fy4=1 / 2 (F1 +F2 +F3 +F4), the rocket is in a relatively static state. After a smooth landing and recovery, the four small electric pump circulation engines can stop working at the same time.

[0013] Compared with other existing rocket recovery methods, this new type of recoverable rocket technology has the following advantages: (1) Solve the problems of the existing rocket body and stage being large in slenderness ratio, heavy in weight and too high in center of gravity during recovery and landing. Since the new recoverable rocket technology scheme utilizes the thrust of four or more small electric pump circulation rocket engines fixedly installed around the middle and upper part of the first stage rocket body for recovery and landing, the center of gravity is low and the landing and recovery will be more stable; (2) Through computer control, the thrust of the electric pump cycle rocket engine in four directions is adjusted to achieve stable control and accurate and smooth recovery in the final stage of rocket recovery (1 km above sea level), solving the problem that the power adjustment and swing accuracy of the rocket main engine are very high when the rocket is recovered and landed; (3) In this new recoverable rocket technology, if the rocket tilts and lands, the thrust of the rocket engine can be increased immediately by the four-way electric pump circulation, allowing the rocket to take off again and attempt a second recovery landing.

[0014] The above are only preferred embodiments of the present invention. The protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for those skilled in the art, some improvements and modifications without departing from the principle of the present invention should also be regarded as the protection scope of the present invention.

Claims

1. A recoverable rocket, characterized in that: include: The first stage rocket body, four or more small electric pump-cycle rocket engines and the required oxidizer tanks and fuel tanks ； 2. A recoverable rocket according to claim 1, characterized in that: The four or more small electric pump-cycle rocket engines are equidistantly fixed around the upper middle part of the first-stage rocket body.

3. The recoverable rocket according to claim 1 or 2, characterized in that: The nozzle of the claimed small electric pump-cycle rocket engine is oriented obliquely downward outward.

4. The recoverable rocket according to claim 2 or 3, characterized in that: The center line of the claimed small electric pump-cycle rocket engine is inclined by 15 to 30 degrees to the center line of the first-stage rocket body; a fairing is fixedly installed on the outside of the electric pump-cycle rocket engine to reduce resistance.

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

6. A recoverable rocket and a method for recovering a recoverable rocket according to claim 1, characterized in that: By installing four or more electric pump-cycle rocket engines at a fixed angle around the upper part of the first-stage rocket body, and adjusting the thrust of the electric pump-cycle rocket engines in four directions through flight computer control, stable control of the rocket and precise and smooth recovery are achieved.

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