阅读说明：本技术 一种运载火箭液氧煤油末级钝化方法 (Final-stage passivation method for liquid oxygen kerosene of carrier rocket ) 是由 宁国富 杨赧 朱亮聪 杨帆 冯继航 洪刚 张亮 辛高波 李红兵 常东方 于 2021-06-11 设计创作，主要内容包括：本发明涉及一种运载火箭液氧煤油末级钝化方法,在主发动机控制气瓶上安装主发动机钝化电磁阀；首先运载火箭末级与卫星分离后进行箭体调姿；箭体调姿结束后,进行机动离轨；机动离轨结束后,利用主发动机的阀门进行液氧贮箱和煤油贮箱内的推进剂排放；然后贮箱增压气瓶排气降压；主发动机吹除气瓶排气降压；主发动机控制气瓶排气降压,辅助动力系统持续工作,对末级进行姿态控制,消耗辅助动力系统剩余姿控推进剂。最后箭上电池持续工作,对末级电气设备进行供电,消耗剩余电池电量。本发明可以实现采用液氧煤油推进剂的末级火箭钝化处理,确保末级火箭在轨不解体,并与卫星运行轨道有足够的安全距离,箭上不需新增阀门和管路。(The invention relates to a final-stage passivation method for carrier rocket liquid oxygen kerosene, wherein a main engine passivation electromagnetic valve is arranged on a main engine control gas cylinder; firstly, separating the last stage of the carrier rocket from the satellite and then adjusting the posture of the rocket body; after the arrow body posture adjustment is finished, maneuvering derailing is carried out; after the motor off-track operation is finished, propellant in the liquid oxygen storage tank and the kerosene storage tank is discharged by utilizing a valve of the main engine; then the storage tank pressurization gas cylinder exhausts and reduces the pressure; the main engine blows the gas cylinder to exhaust and reduce the pressure; the main engine controls the gas cylinder to exhaust and reduce the pressure, the auxiliary power system continuously works to control the attitude of the final stage, and the residual attitude control propellant of the auxiliary power system is consumed. And finally, the battery on the arrow continuously works to supply power to the final-stage electrical equipment, so that the residual battery power is consumed. The invention can realize the passivation treatment of the final rocket by adopting the liquid oxygen kerosene propellant, ensure that the final rocket is not disintegrated in orbit, have enough safety distance with the satellite orbit, and do not need to add valves and pipelines on the rocket.)

1. A final-stage passivation method for carrier rocket liquid oxygen kerosene is characterized by comprising the following steps:

step 1, installing a main engine passivation electromagnetic valve on a main engine control gas cylinder;

step 2, separating the carrier rocket final stage from the satellite, and then carrying out rocket body posture adjustment to enable the thrust of the main engine to be opposite to the flight speed;

step 3, after the arrow body posture adjustment is finished, utilizing a posture control forward pushing engine arranged at the last stage of the carrier rocket to perform maneuvering derailment;

step 4, after the motor off-track operation is finished, propellant in the liquid oxygen storage tank and the propellant in the kerosene storage tank are discharged by utilizing a valve of the main engine, and the propellant in the liquid oxygen storage tank and the propellant in the kerosene storage tank are simultaneously discharged;

step 5, opening the pressurizing electromagnetic valves of the liquid oxygen storage tank and the kerosene storage tank, and discharging gas in the pressurizing gas cylinder into the liquid oxygen storage tank and the kerosene storage tank through a valve of the main engine;

step 6, opening a main engine blowing electromagnetic valve, enabling gas in a main engine blowing gas cylinder to enter the main engine, and reducing the pressure of the main engine blowing gas cylinder;

step 7, discharging the propellant in the liquid oxygen storage tank for a period of time, opening a main engine passivation electromagnetic valve, and controlling the gas cylinder to exhaust and reduce the pressure by the main engine;

step 8, the auxiliary power system continuously works to perform attitude control on the last stage of the carrier rocket, and consumes an attitude control propellant;

and 9, continuously supplying power to the last-stage electrical equipment of the carrier rocket by using the battery on the rocket, and consuming the residual battery power.

2. The final stage passivation method for carrier rocket liquid oxygen kerosene as recited in claim 1, characterized in that in said step 3, the attitude control forward propulsion engine adopts a combination mode of working for a period of time and sliding for a period of time, so as to save the usage of forward propulsion propellant.

3. A final passivation method for carrier rocket liquid oxygen kerosene as described in claim 1, characterized in that in said step 4, the sign of the end of motor off-orbit is that the distance between the satellite and the rocket is not less than 1km, ensuring that the propellant discharge has no pollution and safety problem to the satellite.

4. The final stage passivation method for liquid oxygen kerosene of carrier rocket as recited in claim 1, wherein in step 4, the valve of main engine is used to discharge propellant in liquid oxygen storage tank and kerosene storage tank, the specific implementation method is: liquid oxygen in the liquid oxygen storage tank is discharged by a main engine precooling return valve, and kerosene in the kerosene storage tank is discharged by a main engine fuel discharge valve.

5. The final stage passivation method for carrier rocket liquid oxygen kerosene as recited in claim 4, characterized in that the main engine precooling reflux valve, the main engine fuel discharge valve, the pressurization solenoid valve, the main engine blow-off solenoid valve and the main engine passivation solenoid valve are not closed after being opened.

6. A final stage passivation method for a launch vehicle liquid oxygen kerosene as recited in claim 1, wherein in step 6, the duration of the main engine blow-off cylinder exhaust is determined based on the main engine ground test conditions.

Technical Field

The invention belongs to the field of carrier rocket design, and relates to a carrier rocket liquid oxygen kerosene final-stage passivation method.

Background

With the increase of human space activities, the number of near-earth orbit fragments is increased day by day, and if the number of the near-earth orbit fragments reaches a saturation state, the probability of collision between the fragments and a satellite is increased to an unacceptable range, even collision chain reaction can be generated, the safety of an in-orbit operation spacecraft is seriously threatened, and the passivation of the last stage of a carrier rocket is an important measure for reducing the generation of space fragments.

The final-stage passivation of the carrier rocket mainly reduces the possibility of on-orbit disintegration to the greatest extent by means of exhausting residual propellant and high-pressure gas source, exhausting battery energy and the like, and the specific implementation method is higher in association with a final-stage engine system, a pressurization conveying system, an electrical system and the like. At present, most researches on passivation schemes of a conventional propellant final stage and a liquid hydrogen liquid oxygen final stage are carried out in China, and flight tests prove that few researches on the passivation schemes of the final stage adopting a liquid oxygen kerosene propellant are carried out.

Disclosure of Invention

The technical problem solved by the invention is as follows: overcomes the defects of the prior art and provides a final-stage passivation method of carrier rocket liquid oxygen kerosene.

The technical scheme of the invention is as follows:

a final stage passivation method for carrier rocket liquid oxygen kerosene comprises the following steps:

step 1, installing a main engine passivation electromagnetic valve on a main engine control gas cylinder;

step 2, separating the carrier rocket final stage from the satellite, and then carrying out rocket body posture adjustment to enable the thrust of the main engine to be opposite to the flight speed;

step 3, after the arrow body posture adjustment is finished, utilizing a posture control forward pushing engine arranged at the last stage of the carrier rocket to perform maneuvering derailment;

step 4, after the motor off-track operation is finished, propellant in the liquid oxygen storage tank and the propellant in the kerosene storage tank are discharged by utilizing a valve of the main engine, and the propellant in the liquid oxygen storage tank and the propellant in the kerosene storage tank are simultaneously discharged;

step 5, opening the pressurizing electromagnetic valves of the liquid oxygen storage tank and the kerosene storage tank, and discharging gas in the pressurizing gas cylinder into the liquid oxygen storage tank and the kerosene storage tank through a valve of the main engine;

step 6, opening a main engine blowing electromagnetic valve, enabling gas in a main engine blowing gas cylinder to enter the main engine, and reducing the pressure of the main engine blowing gas cylinder;

step 7, discharging the propellant in the liquid oxygen storage tank for a period of time, opening a main engine passivation electromagnetic valve, and controlling the gas cylinder to exhaust and reduce the pressure by the main engine;

step 8, the auxiliary power system continuously works to perform attitude control on the last stage of the carrier rocket, and consumes an attitude control propellant;

and 9, continuously supplying power to the last-stage electrical equipment of the carrier rocket by using the battery on the rocket, and consuming the residual battery power.

In the step 3, the attitude control forward-push engine adopts a combined mode of working for a period of time and sliding for a period of time so as to save the usage amount of forward-push propellant.

In the step 4, the sign of the motor off-orbit end is that the distance between the satellite and the arrow is not less than 1km, so that the propellant discharge is ensured to have no pollution and safety problems to the satellite.

In step 4, the propellant in the liquid oxygen storage tank and the kerosene storage tank is discharged by utilizing a valve of the main engine, and the specific implementation method comprises the following steps: liquid oxygen in the liquid oxygen storage tank is discharged by a main engine precooling return valve, and kerosene in the kerosene storage tank is discharged by a main engine fuel discharge valve.

The main engine precooling reflux valve, the main engine fuel discharge valve, the supercharging electromagnetic valve, the main engine blow-off electromagnetic valve and the main engine passivation electromagnetic valve are not closed after being opened.

And 6, determining the exhaust duration of the blowing gas cylinder of the main engine according to the ground test condition of the main engine.

Compared with the prior art, the invention has the beneficial effects that:

the invention can realize the passivation treatment of the last-stage rocket adopting the liquid oxygen kerosene propellant, ensure that the last-stage rocket is not disintegrated in orbit, has enough safety distance with the satellite orbit, does not need to additionally arrange valves and pipelines on the rocket, and has the beneficial effects of simplifying the design on the rocket, improving the economy and the reliability and the like.

Drawings

FIG. 1 is a final stage attitude adjustment schematic of the present invention;

FIG. 2 is a schematic diagram of the arrangement of passivated objects on the last arrow of the present invention;

in the figure: 1. the system comprises a carrier rocket final stage, 2. a satellite, 3. a main engine, 4. a posture control forward engine, 5. a liquid oxygen storage tank, 6. a main engine precooling reflux valve, 7. a kerosene storage tank, 8. a main engine fuel discharge valve, 9. a battery, 10. a main engine control gas cylinder, 11. a storage tank pressurization gas cylinder, 12. a pressurization electromagnetic valve, 13. a main engine blow-off gas cylinder, 14. a main engine blow-off electromagnetic valve, 15. a main engine passivation electromagnetic valve and 16. an auxiliary power system hydrazine cylinder.

Detailed Description

The invention is further elucidated with reference to the drawing.

FIG. 1 is a final-stage attitude adjustment schematic diagram of the invention, and the carrier rocket 1 and the satellite 2 are separated and then subjected to rocket body attitude adjustment, so that the thrust of a main engine 3 is basically along the reverse direction of the flight speed.

Fig. 2 is a layout diagram of passivation objects on a last arrow of the invention, and the objects to be passivated include liquid oxygen in a liquid oxygen storage tank 5, kerosene in a kerosene storage tank 7, a storage tank pressurized gas cylinder 11, a main engine blow-off gas cylinder 13, a main engine control gas cylinder 10, an auxiliary power system 16 and a battery 9, wherein the liquid oxygen in the liquid oxygen storage tank 5, the kerosene in the kerosene storage tank 7 and gas in the storage tank pressurized gas cylinder 11 are discharged through related valves of the main engine 3, the gas in the main engine blow-off gas cylinder 13 and the main engine control gas cylinder 10 is discharged through related valves of the main engine 3, and the residual attitude control propellant of the auxiliary power system 16 and the residual electric quantity of the battery 9 are consumed through continuous operation.

According to the invention, the final stage passivation method of the carrier rocket liquid oxygen kerosene comprises the following steps:

step 1, installing a main engine passivation electromagnetic valve on a main engine control gas cylinder.

Step 2, arrow body posture adjustment: as shown in fig. 1, the rocket body posture adjustment is carried out after the carrier rocket final stage 1 is separated from the satellite 2, so that the thrust of the main engine 3 basically follows the reverse direction of the flight speed, and preparation is made for implementing the step 2.

Step 3, maneuvering derailing: after the attitude adjustment is finished, the attitude control forward-push engine 4 installed at the final stage 1 is used for maneuvering out-of-orbit, the height of the orbit of the final stage 1 is reduced, the safe distance between the attitude control forward-push engine 4 and the satellite 2 is ensured, the attitude control forward-push engine 4 adopts a combined mode of working for a period of time and sliding for a period of time, and the amount of forward-push propellant is saved.

The attitude control forward-thrust engine adopts a combined mode of working for a period of time and sliding for a period of time, and aims to save the amount of forward-thrust propellant. Such as a combination of work 40s and coast 175 s.

And 4, discharging a propellant in the tank: and (5) after the off-track operation is finished, the propellant in the storage tank is discharged by utilizing a valve of the main engine 3. Liquid oxygen in the liquid oxygen storage tank 5 is discharged by the aid of the main engine precooling return valve 6, kerosene in the kerosene storage tank 7 is discharged by the aid of the main engine fuel discharge valve 8, and the liquid oxygen and the kerosene are discharged simultaneously, so that discharge time is saved. After opening, the two valves are not closed until the battery 9 is exhausted or the pressure of the main engine control gas cylinder 10 is reduced to be incapable of maintaining the opening state.

The sign of the end of the off-orbit is that the distance between the satellite and the arrow is not less than 1km, and the discharged propellant has no pollution and safety problems to the satellite. The valve of the main engine is used for discharging the propellant in the storage tank, so that the valve and the pipeline on the rocket are not increased, and the economy and the reliability are improved.

And step 5, exhausting and reducing pressure of the storage tank pressurization gas cylinder 11: and opening the pressurizing electromagnetic valves 12 of the liquid oxygen storage tank 5 and the kerosene storage tank 7, allowing the gas in the pressurizing gas cylinder 11 to enter the liquid oxygen storage tank 5 and the kerosene storage tank 7 and to be discharged through the main engine precooling return valve 6 and the main engine fuel discharge valve 8, reducing the pressure of the tank pressurizing gas cylinder 11, and stopping the pressurizing electromagnetic valves 12.

Step 6, the main engine blows the gas cylinder 13 to exhaust and reduce pressure: and opening the main engine blow-off electromagnetic valve 14, enabling the gas in the main engine blow-off gas cylinder 13 to enter the main engine 3, reducing the pressure of the main engine blow-off gas cylinder 13, and enabling the main engine blow-off electromagnetic valve 14 to be not closed.

The exhaust duration of the blowing gas cylinder of the main engine is determined according to the ground test condition of the main engine. One embodiment is that the time is not less than 270 s.

Step 7, the main engine controls the gas cylinder 10 to exhaust and reduce pressure: and (3) discharging the propellant in the storage tank for a period of time, opening the main engine passivation electromagnetic valve 15, controlling the gas in the gas cylinder 10 to be discharged, reducing the pressure of the main engine control gas cylinder 10, and enabling the passivation electromagnetic valve 15 not to be closed any more.

The propellant discharge time is determined by calculation according to the discharge flow and the mass of the propellant remained in the storage tank, and the propellant discharge time in the liquid oxygen storage tank

And 8, continuously operating the auxiliary power system, performing attitude control on the carrier rocket final stage 1, and consuming the residual attitude control propellant of the hydrazine bottle 16 of the auxiliary power system.

And 9, continuously operating the battery 9 on the arrow to supply power to the electric equipment of the last stage 1, and consuming the residual battery power.

Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention. It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.