Rocket boosting launching device and launching method thereof

Abstract

The invention relates to a rocket boosting launching device and a launching method thereof, and belongs to the technical field of rocket boosting launching, the rocket boosting launching device comprises a boosting platform, a plurality of racks and a plurality of mechanical clamping arms, the bottom end of the boosting platform is fixedly provided with a plurality of liquid boosting engines A distributed in an array mode at intervals, and a rocket is supported on the table top of the boosting platform; the multiple racks are distributed on the peripheral side of the boosting platform at intervals in the circumferential direction, and the side faces, corresponding to the boosting platform, of the racks are provided with sliding grooves formed in the motion direction of the rocket. And the multiple mechanical clamping arms are oppositely clamped outside the rocket and slide in the multiple sliding grooves correspondingly, and liquid boosting engines B are fixed to the bottom ends of the multiple mechanical clamping arms correspondingly. According to the technical scheme of rocket power vertical boosting launching, the existing rocket vertical take-off launching efficiency can be effectively improved, the propellant mass of a rocket engine is reduced, the effective load of the rocket is effectively improved, meanwhile, the recoverability is improved, and the rocket launching cost is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rocket boost launch, in particular to a rocket boost launch device and a launch method thereof. BACKGROUND

[0002] With the rapid development of space industry, the frequency of space launch tasks has increased significantly in recent years. To further improve the economy of rocket launch, low-cost and reusable launch systems have become the core demand of space engineering. Traditional rocket launch adopts vertical launch technology, which relies on lower stage engines during ground take-off and initial acceleration. This process consumes a large amount of propellant, greatly increasing the rocket load mass.

[0003] In addition, under the demand of reusability, the rocket must carry redundant fuel to ensure the recycling of lower stage engines, which seriously restricts the rocket payload. In view of the above problems, various rocket ground boost launch technologies have been developed in recent years, including electromagnetic catapult, solid rocket boost and air launch methods. However, these methods generally have the problems of insufficient thrust, non-reusability, and non-adjustable thrust, which are difficult to apply to heavy rocket reusable launch.

[0004] Therefore, the present application provides a rocket boost launch device and a launch method thereof. The method uses controllable rocket liquid engines as ground boost acceleration devices, which not only provides considerable initial speed for heavy rocket launch, significantly reduces the overall take-off mass of the rocket, but also quickly resets the ground boost engine through the ground track recovery module, has high reusability, and has the advantages of "high thrust, low cost, and high reusability". It has a very wide application prospect in the future reusable and high-density launch task scenarios. SUMMARY

[0005] The present application provides a rocket boost launch device and a launch method thereof, which aims to provide initial vertical speed for the launch vehicle, reduce the amount of propellant carried, effectively improve the rocket payload, and improve the reliability of reusable rockets.

[0006] The technical solution of the present application to solve the above technical problems is as follows: a rocket boost launch device, comprising: a boost platform, a plurality of racks and a plurality of mechanical clamping arms,

[0007] The bottom end of the boost platform is fixed with a plurality of arrayed liquid boost engines A, and the platform top supports a rocket, so as to boost the rocket vertically upward before the rocket is ignited, and to obtain an initial speed of the rocket before ignition; a plurality of the racks are circumferentially spaced on the outer periphery of the boost platform, and the corresponding sides of the boost platform are each provided with a chute arranged along the movement direction of the rocket; a plurality of the mechanical clamping arms are oppositely clamped outside the rocket and respectively slide in the plurality of chutes, and the bottom end of each of the plurality of mechanical clamping arms is fixed with a liquid boost engine B to boost the rocket in the movement direction.

[0008] The beneficial effects of the present application are:

[0009] 1. The rocket power vertical boost launch technical scheme can provide a high initial speed for the rocket in the launch phase, realize partial replacement of the lower stage engine of the rocket, on the one hand, reduce the propellant carrying capacity of the rocket engine, and improve the effective payload of the rocket; on the other hand, the push platform, the plurality of constraint rods, the plurality of liquid boost engines A and the plurality of liquid boost engines B are convenient to recycle, greatly improve the equipment reusability, reduce the rocket launch cost, compared with the complex electromagnetic boost and pneumatic boost system, have the advantages of large thrust, simple structure, strong reusability, suitable for high frequency launch, etc., greatly improve the rocket launch efficiency and economy;

[0010] 2. The present application uses a plurality of liquid boost engines A and a plurality of liquid boost engines B as the power source of the ground boost system, which can generate a thrust of more than 100 tons, used to replace the traditional rocket lower stage to accelerate the rocket, reduce the overall mass of the rocket, improve the problem of low effective payload of the rocket from the source, and improve the rocket launch economy;

[0011] 3. The present application uses different thrust grade rocket liquid engines as the power source of the ground boost system, which can flexibly configure the number of engines according to the take-off mass of the rocket, the task type and the launch condition, meet the power demand of light, medium and even heavy rocket launch tasks, and improve the engineering adaptability of the boost system.

[0012] On the basis of the above technical scheme, the present application can also be improved as follows.

[0013] Further, a plurality of liquid fuel storage pipes are arranged along the height direction of the rack and are respectively fixed in the plurality of racks, the bottom end of each of the plurality of liquid fuel storage pipes is a closed end, and a liquid fuel filling hose is fixedly connected to the side pipe wall and communicates with the plurality of liquid boost engines A and the plurality of liquid boost engines B.

[0014] The further beneficial effect is that the multiple liquid fuel filling hoses are respectively connected with the multiple liquid fuel storage pipes and the liquid boost engine A and the liquid boost engine B, so that the liquid boost engine A and the liquid boost engine B can be continuously supplied with combustion fuel.

[0015] Further, the multiple electromagnetic drive pistons are respectively sealed and slid in the multiple liquid fuel storage pipes to push the liquid fuel in the liquid fuel storage pipes (7) to the liquid boost engine A or the liquid boost engine B at high pressure.

[0016] Further, the multiple pressure sensors are respectively fixed on the multiple electromagnetic drive pistons, the multiple electromagnetic pressure controllers and the multiple storage batteries are respectively fixed on the multiple racks, and the multiple electromagnetic pressure controllers are respectively electrically connected with the corresponding pressure sensors and the storage batteries.

[0017] Further, the multiple dampers are respectively fixed on the multiple racks and can be respectively contacted with the multiple mechanical clamping arms to stop the corresponding constraint rods.

[0018] The further beneficial effect is that after the ground boost system completes the boost, the system is automatically reset by the dampers, and after the propellant in the liquid fuel storage pipe is filled, the launch task can be quickly carried out. Compared with the existing rocket lower stage recovery scheme, the propulsion platform, the multiple constraint rods, the multiple liquid boost engines A and the multiple liquid boost engines B can be quickly recovered without consuming additional propellant for recovery, and have the functions of launch efficiency and launch multiplicity, which greatly improves the launch frequency and launch economy.

[0019] In addition, a rocket boost launch method is provided, which comprises the rocket boost launch device, and the specific steps are as follows.

[0020] S1, the rocket is placed on the boost platform;

[0021] S2, the multiple mechanical clamping arms are first clamped on the outer periphery of the rocket, and then the multiple mechanical clamping arms are respectively slid in the multiple sliding grooves;

[0022] S3, liquid fuel is injected into the multiple liquid fuel storage pipes, the pressure in the multiple liquid fuel storage pipes is increased to a set value, and the temperature in the multiple liquid fuel storage pipes is controlled to be below the liquid fuel liquefaction temperature;

[0023] S4, the liquid pressure in the multiple liquid fuel storage pipes is respectively pushed into the multiple liquid boost engines A and the multiple liquid boost engines B;

[0024] S5, ignite multiple liquid boost engines A and multiple liquid boost engines B, the high-temperature and high-pressure gas generated by combustion of the multiple liquid boost engines A and the multiple liquid boost engines B is rapidly ejected to push the boost platform and the rocket to move vertically upward;

[0025] S6, the multiple mechanical clamping arms constrain the movement direction of the rocket to improve the attitude stability;

[0026] S7, before the boost stage is completed, the self engine of the rocket is started, at this time, the multiple mechanical clamping arms release the rocket, the rocket is separated from the multiple mechanical clamping arms, and enters the autonomous flight stage;

[0027] S8, after the boost stage is completed, the boost platform and the multiple mechanical clamping arms return to the initial position.

[0028] Further, the liquid fuel of the multiple liquid boost engines A and the multiple liquid boost engines B is liquid methane and liquid oxygen, and the release duration is controlled to be 2-5s.

[0029] Further, the rocket in S4 starts 0.3-0.5s before the boost stage is completed. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 it is a perspective structural schematic view of a rocket boost launching device of the present application;

[0031] Figure 2 it is a perspective structural schematic view of a boost platform, multiple mechanical clamping arms and a rocket in a rocket boost launching device of the present application;

[0032] Figure 3 it is a perspective structural schematic view of a stand in a rocket boost launching device of the present application;

[0033] Figure 4 it is a perspective structural schematic view of a liquid fuel storage tube, an electromagnetic driving piston, a pressure sensor, an electromagnetic pressure controller and a storage battery in a rocket boost launching device of the present application.

[0034] In the drawings, the component list represented by each reference numeral is as follows:

[0035] 1, boost platform, 2, stand, 21, sliding chute, 3, mechanical clamping arm, 4, liquid boost engine A, 5, rocket, 6, liquid boost engine B, 7, liquid fuel storage tube, 8, electromagnetic driving piston, 9, pressure sensor, 10, electromagnetic pressure controller, 11, storage battery. DETAILED DESCRIPTION

[0036] The principles and characteristics of the present application are described below in combination with the drawings, and the examples are only used to explain the present application, and are not used to limit the scope of the present application.

[0037] like Figure 1 As shown, a rocket booster launch device includes: a booster platform 1, multiple launch stands 2, and multiple mechanical grippers 3.

[0038] Multiple arrayed liquid booster engines A4 are fixed at the bottom of the booster platform 1, and a rocket 5 is supported on its platform. This helps the rocket 5 move vertically upward before ignition, so that the rocket 5 can gain initial velocity before ignition. Multiple platforms 2 are distributed circumferentially on the outer periphery of the booster platform 1, and each platform 2 has a groove 21 arranged along the direction of rocket 5 movement on its corresponding side. Multiple mechanical clamping arms 3 are clamped relative to each other on the outside of the rocket 5 and slide in the multiple grooves 21. Liquid booster engines B6 are fixed at the bottom of the multiple mechanical clamping arms 3 to boost and guide the rocket 5 in the direction of movement.

[0039] like Figure 1 and Figure 4 As shown, in some specific embodiments, it may also include multiple liquid fuel storage pipes 7, which are arranged along the height direction of the test stand 2 and fixed in multiple test stands 2 respectively. The bottom ends of the multiple liquid fuel storage pipes 7 are all closed ends and liquid fuel filling hoses are fixedly connected to their side walls. The multiple liquid fuel filling hoses are respectively connected to multiple liquid booster engines A4 and multiple liquid booster engines B6.

[0040] like Figure 1 and Figure 4 As shown, in some specific embodiments, it may also include multiple electromagnetically driven pistons 8, which are respectively sealed and slid within multiple liquid fuel storage pipes 7, and push the liquid fuel in the liquid fuel storage pipes 7 to the liquid booster engine A4 or the liquid booster engine B6 under high pressure.

[0041] like Figure 1 and Figure 4 As shown, in some specific embodiments, it may also include multiple pressure sensors 9, multiple electromagnetic pressure controllers 10 and multiple batteries 11. The multiple pressure sensors 9 are respectively fixed on multiple electromagnetic drive pistons 8; the multiple electromagnetic pressure controllers 10 and multiple batteries 11 are respectively fixed on multiple stands 2 and the multiple electromagnetic pressure controllers 10 are respectively electrically connected to the corresponding pressure sensors 9 and batteries 11.

[0042] In some specific embodiments, multiple dampers are also included. The multiple dampers are fixed on multiple platforms 2 and can contact multiple mechanical clamping arms 3 respectively to stop the corresponding mechanical clamping arms 3.

[0043] In addition, a rocket booster launch method is provided, including the aforementioned rocket booster launch device, the specific steps of which are as follows;

[0044] In addition, a rocket booster launch method is provided, including the rocket 5 booster launch device, and the specific steps are as follows;

[0045] S1. Place rocket 5 on booster platform 1;

[0046] S2. First, use multiple mechanical clamping arms 3 to clamp the rocket 5 around its outer periphery, and then slide the multiple mechanical clamping arms 3 into the multiple sliding grooves 21 respectively.

[0047] S3. Inject liquid fuel into multiple liquid fuel storage pipes 7, increase the pressure in multiple liquid fuel storage pipes 7 to a set threshold, and control the temperature in multiple liquid fuel storage pipes 7 to be below the liquid fuel liquefaction temperature.

[0048] S4. The liquid pressure in the multiple liquid fuel storage pipes 7 is pushed into the multiple liquid booster engines A4 and multiple liquid booster engines B6 respectively.

[0049] S5. Ignite multiple liquid booster engines A4 and B6. The high-temperature and high-pressure gas generated by the combustion of multiple liquid booster engines A4 and B6 is rapidly ejected, propelling booster platform 1 and rocket 5 vertically upward.

[0050] S6. Multiple mechanical clamping arms 3 constrain the movement direction of rocket 5, improving attitude stability;

[0051] Just before the boost phase is about to be completed, S7 and Rocket 5 start their own engines. At this time, multiple mechanical clamping arms 3 release Rocket 5, and Rocket 5 separates from multiple mechanical clamping arms 3 and enters the autonomous flight phase.

[0052] S8. After the boost phase is completed, the booster platform 1 and multiple mechanical grippers 3 return to their initial positions.

[0053] In some specific embodiments, the liquid fuels of the multiple liquid booster engines A4 and B6 are liquid methane and liquid oxygen, and the release duration is controlled within 2 to 5 seconds.

[0054] In some specific embodiments, S4 begins 0.3 to 0.5 seconds before the boost phase is completed.

[0055] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A rocket booster launch device, characterized in that, include: The booster platform (1) has multiple array-distributed liquid booster engines A (4) fixed at the bottom end of the booster platform (1) and a rocket (5) supported on its platform. Before the rocket (5) is ignited, the booster platform (1) will help the rocket (5) move vertically upward so that the rocket (5) can obtain an initial velocity before ignition. Multiple test stands (2) are distributed circumferentially on the outer periphery of the booster platform (1), and each of the test stands (2) is provided with a groove (21) arranged along the direction of movement of the rocket (5) on the side of the booster platform (1). Multiple mechanical clamping arms (3) are clamped relative to each other outside the rocket (5) and slide in multiple sliding grooves (21). The bottom ends of the multiple mechanical clamping arms (3) are fixed with liquid booster engines B (6) to boost and guide the movement direction of the rocket (5).

2. The rocket booster launch device according to claim 1, characterized in that, It also includes multiple liquid fuel storage pipes (7), which are arranged along the height direction of the platform (2) and fixed in multiple platforms (2). The bottom ends of the multiple liquid fuel storage pipes (7) are all closed ends and liquid fuel filling hoses are fixedly connected to their side walls. The multiple liquid fuel filling hoses are respectively connected to multiple liquid booster engines A (4) and multiple liquid booster engines B (6).

3. The rocket booster launch device according to claim 2, characterized in that, It also includes multiple electromagnetically driven pistons (8), which are respectively sealed and slid within multiple liquid fuel storage pipes (7) to push the liquid fuel in the liquid fuel storage pipes (7) into the liquid booster engine A (4) or the liquid booster engine B (6) under high pressure.

4. A rocket booster launch device according to claim 3, characterized in that, It also includes multiple pressure sensors (9), multiple electromagnetic pressure controllers (10) and multiple batteries (11), with the multiple pressure sensors (9) respectively fixed on multiple electromagnetic drive pistons (8); the multiple electromagnetic pressure controllers (10) and the multiple batteries (11) are respectively fixed on multiple stands (2) and the multiple electromagnetic pressure controllers (10) are respectively electrically connected to the corresponding pressure sensors (9) and batteries (11).

5. A rocket booster launch device according to claim 1, characterized in that, It also includes multiple dampers, which are respectively fixed on multiple stands (2) and can respectively contact multiple mechanical clamps (3) to stop the corresponding mechanical clamps (3).

6. A rocket booster launch method, characterized in that, Including the rocket booster launch device according to any one of claims 1-5, the specific steps are as follows; S1. Place the rocket (5) on the booster platform (1); S2. First, use multiple mechanical clamping arms (3) to clamp the rocket (5) on the outer periphery, and then slide the multiple mechanical clamping arms (3) into multiple sliding grooves (21); S3. Ignite multiple liquid booster engines A (4) and multiple liquid booster engines B (6). The high-temperature and high-pressure gas generated by the combustion of multiple liquid booster engines A (4) and multiple liquid booster engines B (6) is rapidly ejected, propelling the booster platform (1) and rocket (5) to move vertically upward. S4. Multiple mechanical clamping arms (3) constrain the direction of rocket (5) movement, improving attitude stability; S5. Before the boost phase is about to be completed, the rocket (5) starts its own engine. At this time, multiple mechanical clamps (3) release the rocket (5), and the rocket (5) separates from the multiple mechanical clamps (3) and enters the autonomous flight phase. S6. After the boost phase is completed, the boost platform (1) and multiple mechanical grippers (3) return to their initial positions.

7. A rocket-assisted launch method according to claim 6, characterized in that, The liquid fuels of multiple liquid booster engines A (4) and multiple liquid booster engines B (6) are liquid methane and liquid oxygen, and the release duration is controlled between 2 and 5 seconds.

8. A rocket-assisted launch method according to claim 6, characterized in that, The rocket (5) described in S4 begins 0.3 to 0.5 seconds before the completion of the boost phase.

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