阅读说明：本技术 液体火箭推力控制系统、液体火箭 (Liquid rocket thrust control system and liquid rocket ) 是由 彭小波 张玺 魏一 于 2019-12-27 设计创作，主要内容包括：本发明中提供了一种液体火箭推力控制系统、液体火箭,一种液体火箭推力控制系统包括：泵送装置,所述泵送装置的进口与燃料供给系统或氧化剂供给系统连通,出口处并联设置有若干调节支路；所述调节支路上设置有：计量阀；串联在所述计量阀两端的恒压差节流阀；以及开闭阀,用以控制所述调节支路的通断；其中若干所述调节支路作用于至少一个动力装置。本发明中的液体火箭推力控制系统可有效提高火箭的推重比的同时,也可实现对火箭推力的精确调节。(The invention provides a liquid rocket thrust control system and a liquid rocket, wherein the liquid rocket thrust control system comprises: the inlet of the pumping device is communicated with the fuel supply system or the oxidant supply system, and the outlet of the pumping device is provided with a plurality of regulating branches in parallel; the adjusting branch is provided with: a metering valve; the constant pressure difference throttling valve is connected in series with the two ends of the metering valve; and the open-close valve is used for controlling the on-off of the regulating branch; wherein a plurality of said regulating branches act on at least one power unit. The liquid rocket thrust control system can effectively improve the thrust-weight ratio of the rocket and can also realize the accurate regulation of the rocket thrust.)

1. A liquid rocket thrust control system, comprising:

the inlet of the pumping device (1) is communicated with a fuel supply system or an oxidant supply system (2), and the outlet of the pumping device (1) is provided with a plurality of regulating branches (3) in parallel;

the adjusting branch (3) is provided with:

a metering valve (31) to detect the flow in the regulating branch (3);

a constant pressure difference throttle valve (32) connected in series across the metering valve (31);

and an on-off valve (33) for controlling the on-off of the regulating branch (3);

wherein a plurality of said regulating branches (3) act on at least one power means (4).

2. Liquid rocket thrust control system according to claim 1, characterized in that said metering valve (31) is provided with an adjusting actuator (34), said adjusting actuator (34) being adapted to control the opening of said metering valve (31).

3. Liquid rocket thrust control system according to claim 1 or 2, characterized in that said opening and closing valve (33) is arranged after said constant pressure difference throttle valve (32), defined in the fluid flow direction.

4. The liquid rocket thrust control system of claim 3, further comprising:

the booster valve (5) is connected in parallel at two ends of the pumping device (1) and is communicated with the adjusting branch (3);

and the pressure comparison device (6) is connected in parallel among the regulating branches (3) to detect the maximum pressure among the regulating branches (3) and feed back the maximum pressure to the pressure increasing valve (5).

5. Liquid rocket thrust control system according to claim 4, characterized in that said pressure comparison means (6) are connected after said constant pressure difference throttle valve (32), defined in the fluid flow direction.

6. Liquid rocket thrust control system according to any one of claims 4 or 5, characterized in that said power plant (4) is configured as an engine.

7. Liquid rocket thrust control system according to claim 6, characterized in that said regulating branches (3) are connected respectively in combustion chambers of the same engine.

8. Liquid rocket thrust control system according to claim 6, characterized in that several said regulating branches (3) are connected respectively in the combustion chambers of different said engines.

9. A liquid rocket, comprising:

the liquid rocket thrust control system of any one of claims 1-8.

Technical Field

The invention relates to the technical field of aerospace, in particular to a liquid rocket thrust control system and a liquid rocket.

Background

With the increasing competition of commercial aerospace, the requirements on the reliability and economy of the launch vehicle engine are getting tighter and tighter. To reduce the cost of a single launch, the rocket permits reuse. Therefore, the rocket needs to be recovered, and the thrust of the engine needs to be accurately adjusted in the rocket recovery process so as to ensure that the carrier rocket can stably land on the ground and be recycled.

On the other hand, the existing launch vehicle usually needs to carry a plurality of engines, the existing falcon heavy rocket only carries 27 Meilin engines at one stage, and each engine needs to be matched with a turbine pump, thus seriously compromising the thrust-weight ratio of the engine.

Disclosure of Invention

Accordingly, the present invention has been made to solve the above-mentioned problems, and an object of the present invention is to provide a liquid rocket thrust control system and a liquid rocket.

In order to solve the above problems, the present invention provides a liquid rocket thrust control system comprising: the inlet of the pumping device is communicated with the fuel supply system or the oxidant supply system, and the outlet of the pumping device is provided with a plurality of regulating branches in parallel; the adjusting branch is provided with: a metering valve to sense flow in the regulating branch; the constant pressure difference throttling valve is connected in series with the two ends of the metering valve; and the open-close valve is used for controlling the on-off of the regulating branch; wherein a plurality of said regulating branches act on at least one power unit.

Further, an adjusting and executing structure is arranged on the metering valve and used for controlling the opening degree of the metering valve.

Further, the opening and closing valve is disposed after the constant pressure difference throttle valve, defined in the fluid flow direction.

Further, still include: the booster valve is connected in parallel at two ends of the pumping device and is communicated with the adjusting branch; and the pressure comparison device is connected in parallel between the regulating branches to detect the maximum pressure between the regulating branches and feed back the maximum pressure to the pressure increasing valve.

Further, the pressure comparison device is connected after the constant pressure difference throttle valve, defined in the fluid flow direction.

Further, the power plant is configured as an engine.

Furthermore, a plurality of the adjusting branches are respectively connected in a plurality of combustion chambers of the same engine.

Furthermore, a plurality of the adjusting branches are respectively connected in combustion chambers of different engines.

The invention also provides a liquid rocket comprising the liquid rocket thrust control system.

The technical scheme of the invention has the following advantages:

1. the liquid rocket thrust control system comprises: the inlet of the pumping device is communicated with the fuel supply system or the oxidant supply system, and the outlet of the pumping device is provided with a plurality of regulating branches in parallel; the adjusting branch is provided with: a metering valve; the constant pressure difference throttling valve is connected in series with the two ends of the metering valve; and the open-close valve is used for controlling the on-off of the regulating branch; wherein a plurality of said regulating branches act on at least one power unit.

Firstly, the liquid rocket thrust control system pumps fuel or oxidant to a plurality of regulating branches through a single pumping device respectively, and the regulating branches can act on a power device respectively, such as a combustion chamber of an engine, so that the problem that each engine needs to be provided with a turbopump can be avoided, the number of the turbopumps on the rocket is reduced, and the thrust-weight ratio of the rocket is improved;

furthermore, each regulating branch is also provided with a metering valve and a constant pressure difference throttle valve, and the constant pressure difference throttle valve is used for keeping the stability of the front and back pressure difference of the metering valve, so that the accuracy of flow statistics of the metering valve in unit time is ensured, the accurate control of the flow of the oxidant or the fuel provided by the power device is realized, the accuracy of the flow control of the oxidant or the fuel is realized, and according to the reaction ratio of the metering valve and the fuel, the preset thrust can be accurately provided for the rocket during combustion, so that the accurate regulation of the thrust of the rocket is realized, and the success rate is improved for the recovery of the rocket.

2. The liquid rocket thrust control system is characterized in that the metering valve is provided with an adjusting execution structure, the adjusting execution structure is used for controlling the opening of the metering valve, the thrust of the rocket is required to be adjusted in real time due to different thrust required by the rocket at different stages, and the adjustment of the rocket thrust is realized by controlling the flow of the oxidant and the combustion agent provided for the rocket.

3. The liquid rocket thrust control system in the invention is defined by the opening and closing valve arranged behind the constant pressure difference throttle valve along the fluid flow direction. The open-close valve is arranged behind the constant pressure difference throttling valve, and the open-close valve is arranged on each adjusting branch, so that the design can ensure that under some conditions, when some adjusting branches are required to be closed, the adjusting branches can be directly closed through the open-close valve, and the adjustment is simple and convenient.

4. The liquid rocket thrust control system of the invention also comprises: the booster valve is connected in parallel at two ends of the pumping device and is communicated with the adjusting branch; and the pressure comparison device is connected in parallel between the regulating branches to detect the maximum pressure between the regulating branches and feed back the maximum pressure to the pressure increasing valve. The method comprises the steps that firstly, a booster valve can improve the pumping pressure of a pumping device to meet the pumping pressure requirement of each adjusting branch, secondly, the reaction pressure of an oxidant and a fuel is preset, and therefore the pressure of each adjusting branch introduced into a power device finally needs to reach a preset value, a pressure comparison unit can detect the pressure condition of fluid on each adjusting branch, when adjustment is carried out, the required pressure possibly changes, the pressure condition on each adjusting branch needs to be monitored in real time, when the compared highest pressure is larger than the preset pressure value, the highest pressure is fed back to the booster valve to reduce the pressure behind a pump, and meanwhile, redundant fluid can flow back to the front of the pump again, so that the reasonable utilization of the fuel or the oxidant is achieved.

5. The liquid rocket thrust control system is defined along the flow direction of fluid, the pressure comparison device is connected behind the constant differential pressure throttle valve, the pressure comparison unit is arranged behind the constant differential pressure throttle valve according to the pressure required by the reaction of the power device, and the measured pressure condition is closest to the reaction pressure of the power device, so that the influence of the metering valve and the pipeline wall resistance on the pressure measurement result is avoided, and the accuracy of the pressure comparison result is ensured.

6. The liquid rocket thrust control system comprises a plurality of adjusting branches, a plurality of engines and a plurality of engines, wherein the adjusting branches are connected with the plurality of combustion chambers of the same engine respectively, and the adjusting branches are used as some implementation modes of the liquid rocket thrust control system.

7. The liquid rocket thrust control system comprises a plurality of regulating branches, a plurality of engines, a plurality of pumping devices and a plurality of turbo pumps, wherein the regulating branches are connected with combustion chambers of different engines respectively.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

Fig. 1 is a schematic structural diagram of a liquid rocket thrust control system in embodiment 1 provided by the present invention.

Description of reference numerals:

1-a pumping device;

2-a fuel supply system or an oxidant supply system;

3-regulating the branch; 31-a metering valve; 32-constant differential pressure throttle valve; 33-an opening and closing valve; 34-adjusting the execution structure;

4-a power plant;

5-a pressure increasing valve;

6-pressure comparison means.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

Example 1

As shown in fig. 1, a schematic diagram of a thrust control system of a liquid rocket provided in this embodiment includes a pumping device 1, an inlet of the pumping device 1 is communicated with a fuel supply system or an oxidant supply system, and a plurality of adjusting branches 3 are arranged in parallel at an outlet; the regulating branch 3 is provided with a metering valve 31; a constant pressure difference throttle valve 32 connected in series across the metering valve 31; and an on-off valve 33 for controlling the on-off of the regulating branch 3; wherein several regulating branches 3 act on at least one power means 4.

It should be noted that the rocket thrust control system in this embodiment is a liquid rocket, the liquid rocket is a rocket using a liquid rocket engine as a power device, and generally comprises a power device, a rocket body structure, a control system and other components, and the chemical propellant usually used by the liquid rocket engine is composed of a fuel and an oxidizer, and this embodiment is a liquid oxygen methane liquid rocket, but this system is also applicable to other types of liquid rockets. In view of the above, the fuel supply system in the present embodiment is a methane supply system, and the oxidizer supply system is a liquid oxygen supply system, which will not be explained in the following explanation.

The pumping device in this embodiment is a turbo pump, which pumps liquid oxygen and methane within the power plant.

It should be noted that, during the pumping of liquid oxygen and methane, two sets of systems in this embodiment are required to perform pumping adjustment respectively, and for simplicity of illustration and reduction of description repeatability, the illustration in this embodiment is given by taking the pumping of methane as an example.

The power device in this embodiment is the engine, and is the different combustion chambers of same engine, uses the thrust governing system in this embodiment it can realize adjusting the thrust production condition of the different combustion chambers of same engine, because of what thrust needs to be adjusted except the angle of the final synthetic thrust of size, especially in the accommodation process of rocket gesture, the detail adjustment of thrust angle needs to carry out reasonable fine setting to the thrust angle of every engine to realize the accurate adjustment of final thrust.

In other embodiments, a plurality of adjusting branches are respectively connected in combustion chambers of different engines, so that thrust adjustment of a plurality of individual engines can be realized by using one pumping device, and compared with the prior art, the number of turbopumps can be greatly reduced, thereby improving the thrust-weight ratio of the rocket.

The system set itself is described below:

firstly, the liquid rocket thrust control system in the embodiment pumps fuel or oxidant to the plurality of adjusting branches 3 through the single pumping device 1 respectively, and the plurality of adjusting branches 3 can act on the power device 4 respectively, such as a combustion chamber of an engine, so that the problem that each engine needs to be provided with a turbopump can be avoided, the number of turbopumps on the rocket is reduced, and the thrust-weight ratio of the rocket is improved;

furthermore, in this embodiment, each adjusting branch 3 is further provided with a metering valve 31 and a constant pressure difference throttle valve 32, and the constant pressure difference throttle valve 32 is used for maintaining the stability of the front and rear pressure differences of the metering valve 31, so as to ensure the accuracy of flow statistics of the metering valve 31 in unit time, realize the accurate control of the flow of the oxidant or the fuel provided by the power device 4, and the accuracy of the flow control of the oxidant or the fuel.

In order to change the flow rate of the adjusting branch, in this embodiment, an adjusting and executing structure 34 is provided on the metering valve 31, the adjusting and executing structure 34 is used for controlling the opening degree of the metering valve 31, and the opening degree of the metering valve 31 is adjusted by adjusting the executing structure 34, so that the flow rate of the adjusting branch 3 can be changed by changing the opening degree of the metering valve 31 on the premise of pressure stabilization. The adjusting structure in this embodiment is an electric adjusting structure.

The embodiment further comprises the following steps: the pressure increasing valves 5 are connected in parallel at two ends of the pumping device 1 and are communicated with the adjusting branch 3; and the pressure comparison device 6 is connected in parallel between the regulating branches 3 to detect the maximum pressure between the regulating branches 3 and feed back to the pressure increasing valve 5. Firstly, the booster valve can improve the pumping pressure of the pumping device to meet the pumping pressure requirement of each adjusting branch, secondly, the reaction pressure of the oxidant and the fuel is preset, so that the pressure of each adjusting branch introduced into the power device finally needs to reach the preset value, the pressure comparison device 6 can detect the pressure condition of the fluid on each adjusting branch, when the adjustment is carried out, the required pressure possibly changes, the pressure condition on each adjusting branch needs to be monitored, when the compared highest pressure is greater than the preset pressure value, the highest pressure is fed back to the booster valve to reduce the pressure behind the pump, and meanwhile, the redundant fluid can be returned to the front of the pump again, so that the reasonable utilization of the fuel or the oxidant is realized. The pressure comparison device in this embodiment is mainly a combination of a check valve and a throttle valve, and when the highest pressure in each adjusting branch exceeds a preset pressure value of the check valve, the check valve is opened and a highest pressure signal is fed back to the pressure increasing valve 5.

As shown in the figure, the open-close valve 33 is arranged behind the constant pressure difference throttle valve 32 in the fluid flow direction, and the open-close valve 33 is arranged on each adjusting branch, so that the design can ensure that the adjusting branches can be directly closed through the open-close valve when needing to be closed in some cases, and the adjustment is simple and convenient.

Of course, in some other embodiments, the position of the open/close valve 33 can be set directly after the pump as the total control valve for each regulating branch.

Further, a pressure comparison device 6 is connected downstream of the constant pressure difference throttle 32, defined in the fluid flow direction. Because the pressure needed by the reaction of the power device 4 preset by the pressure comparison device 6 is arranged behind the constant differential pressure throttle valve 32, the measured pressure condition is closest to the reaction pressure of the power device 4, the influence of the metering valve 31 and the pipeline wall resistance on the pressure measurement result is avoided, and the accuracy of the pressure comparison result is ensured.

Example 2

The present embodiment provides a liquid rocket including the liquid rocket thrust control system, and has all the technical advantages thereof, which are not described herein in detail.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.