CN111038736A

CN111038736A - Spacecraft slow-speed high-throwing type launching method and launching platform

Info

Publication number: CN111038736A
Application number: CN201811232822.7A
Authority: CN
Inventors: 姚宏威
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-10-11
Filing date: 2018-10-11
Publication date: 2020-04-21

Abstract

The invention discloses a launching method of a spacecraft and a launching platform formed based on the basic principle of the method, and the launching method of the spacecraft is technically characterized in that: the launching speed is low, the slow flying height is high, and the launching method is called as a slow high-throw launching method for short. The slow-speed high-throw launching platform developed based on the invention mainly comprises a platform body, a power system, an attitude adjusting system, an instrument measurement and control system, auxiliary system equipment such as a buffering column base and materials, and the flight mode of the slow-speed high-throw launching platform has the technical characteristics of slow-speed high-throw.

Description

Spacecraft slow-speed high-throwing type launching method and launching platform

Technical Field

The invention relates to an aerospace launching technology, in particular to an aerospace launching device and method, and accordingly an aerospace launching device is developed.

Background

The development of human aerospace technology has been in history for nearly a century, and as scientists, engineers, astronauts and all the related personnel make efforts, research and development and active practice, the aerospace technology is rapidly advanced, and aerospace products such as satellites, spacecrafts, space shuttles and space stations are colorful. The dependence on aerospace technology is established to different degrees whether in military or civil use.

The results of aerospace industry are tired, but aerospace technology is still developing, and there are many places to continue exploring. In the launching practice of the spacecraft, some phenomena are observed and found, for example, rockets are all in a long rod shape, the head is provided with a fairing, the whole rocket is made into a streamline shape, and the shape and the volume of the spacecraft are limited; meanwhile, the fairing is an indispensable device with a protection function from the safety perspective, and from the energy perspective, the fairing is not a power part, is not a target device, and is a load discarded midway; for another example, a booster, a fairing, a rocket body and the like are thrown off shortly after the rocket is lifted off, the initial throws are often close to a launching site (about 1000 km), which interferes with the life of people to some extent, and is avoided or reduced as much as possible?

The invention relates to a spacecraft slow-speed high-throw launching method and a launching platform, which aim to solve a series of problems including the problems and carry out analysis and research, and provides a technical solution which can effectively realize launching of a spacecraft with a large cross section, reduce the rejection of substances in the launching process of the spacecraft as much as possible, and try to expand the new functions and performances of a spacecraft launching system, thereby providing a new technical basis for the subsequent development of the aerospace technology.

Disclosure of Invention

For brevity and clarity of description, specific, unified descriptions of concepts in related patent documents are provided. Features or objects which come within the scope of the claims, or new concepts which are to be defined temporarily, or which are mentioned at different points of view according to the requirements of the expert, are equally disclosed, possibly using common technical concepts:

1. speed, acceleration: for simplicity and intuition, the speed concept does not distinguish precise technical concepts such as instantaneous speed, average speed and the like in the implementation process of technical design, but generally refers to nominal speeds in different flight program segments and different technical grade ranges; acceleration also refers to the nominal acceleration under this principle;

2. normal direction and tangential direction: the direction along the radius of the earth is called normal, and the direction perpendicular to the radius of the earth is called tangential, such as normal velocity and tangential velocity. The normal direction and the tangential direction are mainly used in principle description or comprehensive description, and generally do not contain engineering errors;

3. vertical direction, horizontal direction: the direction perpendicular to the ground is called a vertical direction, and the direction parallel to the ground is called a horizontal direction, such as vertical lift-off, horizontal flight and the like. The vertical flying speed and the horizontal flying speed respectively correspond to the normal speed and the tangential speed; the vertical direction and the horizontal direction generally include engineering errors such as system errors and manually set inclination angles.

4. Rocket: according to the needs of the expert, the general principle description and rocket concepts in the prior art refer to the traditional rocket which starts to take off from the ground, and the stages of the rocket are respectively called a first-stage rocket, a second-stage rocket, a third-stage rocket and the like;

5. platform rocket: refers to a vehicle launched from the ground and mainly assuming slow flight mission. The platform rocket is a concept based on function definition, is equivalent to the first stage of the traditional rocket or partial functions of the first stage rocket in the classification property, and has a flight mode comprising a function of slowly penetrating through dense atmosphere and a function of continuously flying as a main rocket after the rocket penetrates through the dense atmosphere, wherein manual control and recovery are generally pursued but not strictly required;

6. a launching platform: the launching platform is a special technical concept of the patent, and is launched from the ground, only slowly ascends and flies vertically, after slowly flying to a set height, the launching platform flies in an accelerated manner or not according to specific task requirements, releases a main rocket system, and then starts to control a returning carrier. The launching platform is a specially developed platform rocket with an independent technical structure, only undertakes the tasks of slow speed and high throwing, does not participate in subsequent flight, and requires controlled landing and recovery;

6. a main rocket: the rocket which is ignited from the launching platform and is launched at high speed is respectively called as a primary rocket, a secondary rocket, a final rocket and the like in the stage;

7. installation: the assembly refers to the assembly in the launching process, namely, the secondary object is installed on the primary object in the launching process, such as the installation of a main rocket on a launching platform, the installation of a spacecraft on a rocket, and the like, which are also called loading;

8. assembling: the method is a process of taking a spacecraft, a rocket, a launching platform, a main rocket and the like as independent machine equipment, assembling and combining parts, subsystems and the like in required design into a whole, and debugging all the parts to achieve design performance and functions;

9. butt joint: refers to the assembly process of the cabin body with independent functions of the spacecraft and external parts. Installation, assembly and butt joint are sometimes not distinguished obviously, and are generally called as assembly;

10. a spacecraft: this patent document refers generally to individual docking units, such as individual functional compartments, solar sailboards, independently operating satellites, and the like. If the space docking body such as an international space station is referred to as a whole due to the requirement of the literary works, the following words are limited.

11. Size and dimension: dimension refers to a geometric figure of a single element, such as diameter, length, etc.; the dimension is a short term for a plurality of dimensions with the same property without specific distinction, for example, the length and the width of a planar body are called planar dimensions for short, and the length, the width and the height of a spatial body are called object dimensions for short.

(this patent document mainly describes an embodiment of launching platform + vertically mounted main rocket, and other embodiments can be analogized)

As is known, the launching process of a spacecraft is a process of providing a desired orbital flight speed for a target device which finally enters an orbit by using a rocket to jet a large amount of substances according to a momentum conservation law. In the launching of the spacecraft, most rockets are vertically installed, after the rocket is ignited, the rocket flies vertically upwards firstly, then turns a corner through a program, the rocket starts to incline, a horizontal velocity component is provided to a required direction, the vertical velocity component is gradually reduced, the horizontal velocity component is increased, and finally the spacecraft enters an orbit at a set height to stably run.

Thus, we analyze the relevant emission elements of the spacecraft: spacecraft orbit altitude, tangential flight velocity, and normal flight velocity. Under the condition that the earth is an ideal sphere without atmosphere, theoretically, the spacecraft can fly along the surface of the earth, the practical spacecraft needs to be hundreds of kilometers above the ground, mainly for avoiding the resistance of low-altitude atmosphere, and therefore the flying height of the spacecraft is necessary; based on the law of circular motion, it is obvious that the required tangential flight speed is also not freely changeable for different orbits of different spacecrafts; however, we can find that the normal velocity during launch is only a process element during launch, and is not a necessary parameter for the final orbit of the spacecraft, and the magnitude of the normal velocity can be changed according to the launch requirement.

The invention relates to a spacecraft slow-speed high-throw launching method and a spacecraft launching platform, which are based on the principle, the launching process of a rocket is adjusted necessarily, and the normal speed of the rocket is controlled mainly in the initial stage of launching, or the normal speed and the tangential speed of the rocket are separated for a long time and are controlled respectively and independently. Compared with the existing launching mode, the rocket is firstly slowly lifted off at a very low speed until the rocket flies out of a dense atmosphere, and then is accelerated to finish the work in a high-throwing stage; then, normal flight is changed to the second, the task is mainly to control the tangential speed of the rocket in a turning way, and under the condition that almost no air resistance exists, the engine does work under full load, so that the tangential speed of the rocket is rapidly increased. For launching in a mode of 'launching platform + main rocket', after the launching platform slowly rises to a set height, the main rocket starts to ignite, the processes of ignition, program turning, acceleration and the like are started according to a set program, the launching program is sequentially expanded, the tangential speed of the main rocket starts to generate and rapidly increases, and finally the spacecraft enters a set orbit. In practice, in order to furthest strip off the task of normal flight of the main rocket, as an optimal scheme, after the launching platform slowly ascends to a set height, the normal acceleration is directly started, and the main rocket does not start to be ignited to launch and fly according to a program until the normal speed reaches a set value or reaches the set height according to the speed. Meanwhile, the launching platform starts a shutdown falling program and enters a returning process.

The spacecraft slow-speed high-throw launching method is developed and actually has the revolutionary property of launching technology in a certain sense. The technical essence is that two major hindering factors which need to be overcome in the rocket launching process are respectively overcome in stages. In the first stage, the slow ascending stage has the core task of overcoming air resistance and gravity; in the second stage, the second stage is the orbit flight stage, and the core task is to overcome the gravitational attraction and the air resistance. This results in three technical effects: firstly, the design of the rocket and the spacecraft does not give importance to the streamline shape flying in dense atmosphere, a fairing is not required to be arranged, and the cross section of the rocket can be designed to be very large; secondly, in the initial stage of practical development and implementation of the technology, under the same fuel energy condition, the mass carrying capacity of the launching system is reduced along with the increase of the projectile height within a certain range; thirdly, under the condition of the same target spacecraft quality, for the main rocket, because the air resistance and the vertical lift-off energy consumption are reduced to be extremely low, the fuel required to be carried can be effectively reduced; or the length-diameter ratio of the main rocket and the whole load thereof can be effectively reduced due to the widening of the cross section dimension, the fuel carrying capacity of the main rocket can be effectively increased under the condition that the fixed mass of the main rocket is not increased or slightly increased while the system stability is increased, and the mass of the finally-targeted spacecraft can be increased according to the ziolkowski formula.

The invention relates to a launching platform derived from a spacecraft slow-speed high-throw launching method, which mainly comprises a launching platform body, namely a bearing system (31), a main engine system (32), an attitude adjusting system (33), a return system (34), corresponding internal equipment, instruments and meter systems and the like.

The invention relates to a spacecraft slow-speed high-throw launching method and a launching platform, which can bring about a dramatic application effect by application:

1) according to the launching method, the sections of the rocket and the spacecraft can be made to be very large along with the weakening of air resistance, so that the spacecraft with a large volume or special-shaped form can be launched within a certain limit;

2) according to the launching method, in part of launching tasks, because the energy consumption of lifting off is transferred to the launching platform and the energy consumption of air resistance is weakened in a large proportion, under the same target track and launching load conditions, the energy carried by the main rocket is relatively low; or under the same fixed mass condition as the traditional rocket, the main rocket can carry more fuel, and the mass carrying capacity can be improved to some extent;

3) according to the launching method, the special slow-speed high-throw launching platform provides multiple installation basic conditions for the main rocket, and according to launching practices, the main rocket can be vertically installed (vertically installed), obliquely installed upwards (obliquely installed) or even horizontally installed (horizontally installed).

4) According to the launching method, the launching platform only flies in the vertical direction in the launching process, so that the control difficulty of the launching platform in the launching and flying process is reduced, and the launching platform can become an independent first-level of an aerospace launching system and can be controlled independently; meanwhile, compared with the traditional cylindrical form, the large cross section form reduces the technical difficulty of return control of the launching platform in practice, so that the technical difficulty of launching platform recovery is greatly reduced;

5) according to the launching method, the realization possibility is provided for subsequent applications such as aviation fuel engines or nuclear energy engines, the aerospace field and other subsequent technical developments, and at least a technical support basis is provided;

6) the spacecraft slow-speed high-throw launching platform also has other microscopic performance optimization and improvement effects, for example, simple ineffective energy waste caused by air resistance can be effectively reduced; as another example, according to the preferable scheme of the invention, the launching platform can be recycled, the launching of the spacecraft can effectively reduce the abandonment of low-altitude substances in a certain sense, the fairing is not necessary to be a necessary component, and the original first-stage rocket and the booster are converted into the recyclable launching platform, so that the waste of substances is reduced, and the threat and the interference of the abandoned substances to the living beings and the environment on the earth surface are reduced.

However, it should be clearly noted that, although the spacecraft slow-speed high-throw launching mode and launching platform of the present invention effectively overcome the simple ineffective energy waste caused by air resistance, it still may but does not necessarily have an energy saving effect, and theoretically, the overall energy consumption may be even higher than that of the traditional launching mode, and of course, the energy saving effect is set according to the parameters of a specific launching task.

Drawings

FIG. 1 is a schematic diagram of the principle of a spacecraft slow-speed high-throw launching method and launching platform of the present invention:

in the figure: 1-target spacecraft, 2-main rocket (shaded), 3-launch platform; 31-a launching platform carrying system, 32-a launching platform main engine system, 33-a launching platform attitude adjusting system and 34-a launching platform returning system.

Detailed Description

The technical solution implementation principle in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without any creative work belong to the protection scope of the present invention.

The invention relates to a slow-speed high-throw launching method of a spacecraft, which is technically characterized in that two tasks of overcoming air resistance and gravity in the launching process are properly separated and respectively overcome by stages as key points. The external physical technical characteristics are that the launching system penetrates through dense atmospheric layer at a slow speed and then carries out tangential acceleration, thus realizing the stable operation of the spacecraft in space.

Air resistance, according to its general principle formula f ═ C ρ Sv²)/2. In current aerospace technology, the magnitude of drag is not very large relative to gravity and rocket thrust under the precise calculation and scientific settings of aerospace technologists. Because the air density ρ decreases as the rocket increases in velocity v as it flies, there will always be an optimum relationship curve for both. However, the maximum value can reach dozens of tons or hundreds of tons, the existence of low-altitude dense air not only needs a fairing, but also needs to increase the structural strength of a rocket system, and the uneven airflow causes troubles to the control precision of the flight trajectory for the rocket flying at high speed.

In particular, as can be seen from the above formula, the air resistance is proportional to the cross-sectional area S of the rocket, i.e., proportional to the square of the cross-sectional dimension (or radial dimension) of the rocket. According to the traditional launching mode, the increase of the cross section size of the spacecraft not only causes the sharp increase of ineffective energy consumption, but also causes the air resistance to become the bottleneck whether the launching of the spacecraft can be successful in a certain even very small time period; at the same time, the increased size of the spacecraft requires larger fairings. This greatly limits the desire of space scientists to launch large volume spacecraft.

The invention relates to a slow-speed high-throw type launching method of a spacecraft, which can improve the influence of air resistance by selecting a smaller lifting speed at the initial stage of rocket launching. According to the assumption that the air resistance is kept unchanged, the reduction of the speed can provide conditions for increasing the cross section of the rocket and the aerospace, and meanwhile, the reduction of the speed and the increase of the cross section can fully compress the length-diameter ratio of a rocket system, so that the controllability of the variation range of the gravity center of the rocket and the stability of the rocket are improved. And so on. These variations have real advantages for launching large cross-section spacecraft.

The invention relates to a slow-speed high-throw launching method of a spacecraft, which can be directly applied by changing a launching flight program from a first-stage rocket of a traditional rocket from the principle perspective. Namely: after the rocket is ignited and accelerated to obtain an initial speed which accords with the set value, the acceleration is adjusted to be zero or an extremely small value, the rocket is kept flying in the atmosphere at a slow speed until the launching system flies out of a dense atmosphere, and then accelerated flying is started, so that slow-speed high-throwing is realized.

In order to ensure the successful implementation of a project, the invention provides a spacecraft slow-speed high-throw launching method, which is characterized in that the value of an initial technical parameter is set, the slow-speed flying speed is less than or equal to 100.0m/s, and the slow-speed flying height is greater than or equal to 12.0Km, and the parameter is the parameter limit of the patent claims. In fact, to fully exploit the slow high throw launch effect, those two values should be far from that limit value. Preferably, the slow flying speed is generally not higher than the level of 20.0m/s, the lower limit value is not limited, the slow flying height is not lower than 40.0Km, and the upper limit value is not limited. Of course, the parameters selected for the actual launching task need to be considered for balancing energy consumption with the quality of the target task, and the influence of atmospheric events (such as wind and thunder) on the launching system.

Meanwhile, in order to fully shorten the travel of the launching system in dense air, avoid the influence of atmospheric events on the launching system and simplify the control on the rocket system, preferentially, the vertical direction is selected as the flight direction in the slow-speed flight stage of the launching system. And therefore, under the condition of considering the recoverability beneficial to the traditional first-stage rocket, a slow-speed high-throw launching platform of the spacecraft is developed.

The invention relates to a slow-speed high-throw launching platform of a spacecraft, which mainly comprises a launching platform body, namely a bearing system (31), a main engine system (32), an attitude adjusting system (33), a return system (34), corresponding auxiliary equipment, instrument and meter systems (the equipment pipelines and the like belong to auxiliary measurement and control connection supporting components of the front main function systems, the configuration, the sharing and the specificity of each launching task are different, and serial numbers are not marked in the attached drawings) and the like.

1. The invention relates to a system composition of a spacecraft slow-speed high-throw launching platform

Fig. 1 is a schematic diagram of the principle, which shows the system principle and the launching platform structure principle of the spacecraft slow-speed high-throw launching method of the present invention, wherein 1 is a target spacecraft, 2 is a main rocket (with a shadow part), and 3 is a launching platform.

In the illustrated embodiment, the target spacecraft (1) is a medium-sized spacecraft with a spherical main body. The main rocket (2) is divided into a primary rocket stage and a final rocket stage, the primary rocket stage is arranged on the table top of the launching platform (3) in a jacking mode, the table top is provided with a positioning device, and the final rocket stage is sleeved in the spacecraft (1), so that the installation mode is favorable for the ignition takeoff of the main rocket (2) and the ignition separation of the spacecraft (3). In practical design, attention should be paid to setting safety settings with various possible accidents, such as a platform surface guiding device, and the safety settings have a controllable fastening function, so that fastening in an abnormal state is facilitated, and active loosening and auxiliary releasing after ignition of a main rocket are facilitated.

In the schematic representation of the structural principle of the launching platform (3), in order to make the drawing clear, the serial numbers of the subsystems of the platform rocket are marked on the characteristic executing parts, the equipment installed in the launching platform body is not explicitly shown, but the fuel bin, the auxiliary agent bin, the accessory equipment instrument bin, the attitude adjustment special power cabin and the like are respectively and schematically represented by adopting dotted line boxes.

The embodiment illustrated in the figure also shows the technical feature that the cross section of the spacecraft can be made very large, and the cross section of the rocket system can be made very large, due to the slow flight in dense atmosphere. In the figure, the diameter of the final stage of the main rocket (2) is similar to that of the traditional rocket, the cross sections of the primary stage of the main rocket (2) and the platform rocket are very large, so that the installation height of a launching system is not increased but can be reduced actually when a spacecraft with larger size is launched; meanwhile, each power cabin is not limited to the traditional vertical assembly, and can also be transversely arranged (the arrangement interval form of the fuel cabin auxiliary agent cabin and the like is indicated by dotted lines in the figure), and generally, the capacity of the large-cross-section container is larger than that of the vertical arrangement. The medium pipelines and the equipment and elements thereof are schematically represented by reserving a bin section in a centralized way, and can be distributed in practice and connected with corresponding actuators through middle reserved channels or outer reserved channels.

Bearing system (31), its main part is the launching platform body, and the launching platform body is a support body class structure of high strength, and its intensity and rigidity require can guarantee that platform self stable in structure, can bear main rocket system equipment to can stand the impact force of returning the in-process, require to adopt the light material of high temperature resistance as far as possible on this basis. The outline of the main plane of the launching platform is circular or N-edge polygon (N is more than or equal to 3), and the surface of the launching platform is provided with holes or is not provided with holes according to a specific launching task. The launch platform surface is provided with positioning, guiding and fixing accessories, has the functions of installing, positioning and launching a spacecraft rocket, and is generally called as an installation frame.

The main engine system (32) comprises a fuel bin, an auxiliary agent bin, corresponding accessory equipment and pipelines which are arranged in the launching platform body, and also comprises engines arranged at the lower part of the launching platform, wherein the number of the engines can be 1, or M engines (M is more than or equal to 3); the main engine system is similar to the first engine system of a traditional rocket, and necessary heat preservation and protection facilities are all in the right condition according to the nature of fuel.

An attitude control system (33) comprising a plurality of instrument communication valve control systems and a main engine system

And other spouts and the like. It is known that the ideal normal launch trajectory in theoretical design is difficult to guarantee in practice because the launch platform deviates from the design value after being lifted off due to the influence of the uniformity of the engine power, the influence of atmospheric events (such as air flow) in the large-stroke slow-speed lifting process and even the earth system. The launch platform is equipped with positioning, orientation and leveling instrumentation. And the control center controls according to the instrument feedback data, so that the levelness of the bearing surface of the launching platform, the position and the direction of the launching platform after being lifted off and the like are kept within a set tolerance range.

And the return system (34) comprises an attitude adjusting system, a deceleration resistance device, a recoil device, a buffer device and the like. After the main rocket is discharged, the launching platform begins the return stroke. When the launching platform is at a set height close to the ground, an engine (a special posture adjusting engine or a main engine) arranged at the bottom of the launching platform works again in high power to provide a reverse thrust power, and the launching tower is ensured to land stably.

The return system may be provided with mechanical resistance means, but is generally not provided with uncontrollable resistance means such as a drogue. The bottom of the launching platform is provided with a buffer column base to protect equipment such as an engine and the like from being impacted. The buffering column base preferably adopts a hydraulic spring, a hinge type elastic device and the like, so that the phenomenon of indefinite bounce can be avoided after the launching platform falls to the ground.

The hydraulic spring is a hydraulic device which is mainly composed of a piston type oil cylinder and a type throttle valve, elements such as a check valve, a liquid supplementing valve or an air release valve can be added according to different purposes to form complete matching of various systems, but the core components are the piston type oil cylinder and the throttle valve, and the throttle valve is preferably an adjustable throttle valve. The working principle is that when the piston rod is pushed or pulled, liquid flows into the oil cylinder on the top surface or the bottom surface of the piston through the throttle valve, resistance which hinders the reciprocating motion of the piston rod is formed under the action of the throttle valve, the motion of the piston rod is damped, the effect similar to spring damping is achieved, and the damping rigidity of the hydraulic spring is achieved by adjusting the flow of the throttle valve. Hydraulic springs are effective springs for pushing or pulling in a single pass, requiring additional recovery after use. If the device is used for the alternate working condition of pushing and pulling, or is provided with a return device of the return pump in the ground application state, the device can continuously work. In application, attention is paid to that hydraulic workers and hydraulic pipelines are required to be made into structural parts for high-strength stress levels.

2. The invention relates to a spacecraft slow-speed high-throw type launching platform which is matched with other related systems of a spacecraft launching system

The invention relates to a slow-speed high-throw type launching platform of a spacecraft, which is used as a subsystem of a space launching system, and the technical performance of the launching platform is matched with the requirement of the space launching system. The launch platform is functionally equivalent to the first stage rocket of a conventional rocket, but it is not intended that a conventional rocket simply starts from the second stage and becomes the main rocket as defined herein. The primary rocket of the main rocket has larger fuel capacity requirement than the secondary rocket of the traditional rocket, and particularly, the power of the engine is required to be greatly improved than the power of the secondary engine of the original rocket, so that enough large thrust can be provided, and the tangential speed of the main rocket can be rapidly increased.

The installation mode of the main rocket on the launching platform comprises a plurality of modes such as vertical installation, inclined installation, horizontal installation and the like, and the vertical installation mode is suggested to be adopted for the installation of the main rocket on the launching platform in the initial implementation stage. The main rocket is initially designed to take off from a take-off mode on a launching platform by taking vertical installation as an example, the main rocket is ignited and takes off actively, the mounting frame mainly carries out strong restraint on five of six degrees of freedom of the main rocket, and the vertical axial movement of the main rocket is not limited by strong force generally so as to be beneficial to the automatic launching and releasing of the main rocket. And so on.

3. The invention relates to launching of a spacecraft slow-speed high-throw launching platform

In the embodiment, the spacecraft slow-speed high-throw launching platform only flies in a vertical ascending mode, and theoretically, the launching field and the recovery field are coincident. From the engineering practice method, the embodiment can actually intentionally relax the flight error of the launching platform in one direction, so that the return of the launching platform has a fixed landing range. A slight inclination angle relative to the vertical direction can be generally arranged in the flight direction of the main rocket, so that the launching field and the recovery field are separated at intervals, the interval is generally not more than 10.0Km, and the launching field can even be arranged beside the edge of the recovery field under the condition that the practical control capability is fully ensured. Therefore, the safety of the facility of the launching site is facilitated, the difficulty of transportation from the launching platform to the launching site can be reduced, and the reuse of the launching platform is facilitated.

The launching site is a site for high-strength curing of concrete, the recovery site can cover the concrete but not strictly requires, but needs manual finishing, leveling and curing, so that the ground surface of the recovery site can be subjected to wind and rain to keep necessary levelness and hardness, the set bearing capacity is realized, and the impact when the launching platform returns can be borne and the running of heavy equipment can be guaranteed. The surface of the recycling site can be planted with flowers and grass to form a lawn, and the beautification is not listed in the claims of the invention.

And an on-site factory is arranged at a safe position relative to the launching site and the recovery site, and is used for carrying out inspection maintenance and other production assembly tasks on the recovered launching platform. The distance from the factory to the field of emission should also not be greater than 10.0Km in general.

It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the principles or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

In addition, the technical scheme has the step-type technical platform property, and various embodiments can be derived. It should be understood that although the present description has been described in terms of the embodiments, not every embodiment includes only a single embodiment, and such description is for clarity purposes only, and those skilled in the art will recognize that the embodiments described herein may be combined as suitable to form other embodiments, as will be appreciated by those skilled in the art.

Claims

1. A launching method of a spacecraft is technically characterized by comprising the following steps: in the initial launching stage of the spacecraft, the launching speed is low, the low-speed flight normal displacement is large, namely the vertical lift-off height is high, and the launching method is called as a slow-speed high-throw launching method for short.

2. The technical method according to claim 1, characterized in that: in the initial stage of spacecraft launching, the rocket slowly penetrates through a dense atmospheric layer (generally an atmospheric troposphere and a stratosphere) at a set speed range, and after reaching a set slow-speed levitation height, the rocket starts to accelerate to fly according to a set program, so that the spacecraft can stably run in the space.

3. A platform rocket of a spacecraft is technically characterized in that: the rocket is functionally equivalent to the first stage of a traditional rocket, the initial flight technical characteristics of the rocket accord with the technical characteristics of claim 1, and the rocket continuously participates in the main rocket flight task according to the flight program of the traditional rocket after the slow-speed high-throw task is completed.

4. A launching platform of a spacecraft is technically characterized in that: the independent structure with the structural boundary with the main rocket has the technical characteristics of flight according to the technical characteristics of claim 1 and has specific and novel flight characteristics: the launching platform only carries out vertical ascending flight, after the launching platform slowly flies to a set height, the main rocket is ignited from the launching platform to take off according to a set program, and after the main rocket system is released, the launching platform starts to be controlled to return.

5. The launch platform of claim 4, characterized by: the system mainly comprises a launching platform body, namely a bearing system, a main engine system, an attitude adjusting system, a return system, a corresponding internal equipment instrument system and the like.

6. The launch platform of claim 4, characterized by: the outline of the main plane of the launching platform body is circular or polygonal with N sides (N is more than or equal to 3), and the surface of the launching platform is provided with holes or is not provided with holes according to a specific launching task; the launching platform surface is provided with positioning and fixing accessories and has the functions of installing and positioning and assisting the launching spacecraft to launch the main rocket according to task requirements.