CN116793157A - Reusable rocket - Google Patents

Abstract

The application relates to the technical field of rocket, in particular to a reusable rocket, which comprises the following components: the landing leg recovery device comprises a first sub-stage, a second sub-stage, a booster, a plurality of recovery landing legs and a plurality of grid rudder devices; the first sub-stage comprises a first-stage tail section, a first-stage rear transition section, a first-stage fuel tank section, a first-stage tank interval section, a first-stage oxygen tank section and a second-stage section from bottom to top in sequence; the booster is arranged at the outer side of one sub-level; the secondary sub-stage comprises a secondary fuel tank section, a secondary tank interval section, a secondary oxygen tank section, a switching frame and a fairing from bottom to top in sequence; one end of the plurality of recovery landing legs is uniformly hinged to a circumference of the outer surface of a sub-stage; the plurality of rudder units are uniformly hinged to a circumference of an outer surface of a sub-stage. The application can realize the repeated use of the rocket and reduce the track-in cost of the rocket.

Description

Reusable rocket

Technical Field

The application relates to the technical field of rockets, in particular to a reusable rocket.

Background

With the development of aerospace technology, each country and each large technology body are actively laying out the space field, preempting space satellite orbit frequency resources, and currently, the number of communication satellite constellation plans distributed worldwide exceeds 25, and the number of planned launching satellites exceeds 4 ten thousand. The prior carrier rocket is designed and developed aiming at a certain engineering task, but for commercial satellites with the market ratio of more than 70% in the future, no particularly suitable rocket exists, so that a new generation of medium carrier rocket with more 'Qinpeople' needs to be developed, the gap of the launching capability of the solar synchronous orbit satellite is filled, various launching requirements in the future are met, a large number of satellite launching requirements overflow, and the development of reusable rockets is urgently needed, and the market requirements are met.

Market demand and technical innovation jointly drive the development of reusable carrier rockets, and quick response, wide adaptability and economy are main targets pursued by aerospace transportation systems. The carrier rocket technology is gradually mature and tends to be industrialized after decades of development, breaks through a plurality of fields such as aerospace power, electronic components, new materials, advanced manufacturing processes and the like, and technical innovation enables the carrier rocket to return to space like an airplane returns to a launch field (a port of space), and to launch again after filling fuel and simple maintenance. In addition, to build and maintain a systematic steady operation of the aerospace system, there is a need to reduce the cost of entering space, promoting an exponential increase in emission demand in the form of an "orbital revolution". Such a carrier that greatly reduces the in-orbit price is not possible with disposable rockets, and a reusable rocket technology must be employed.

Therefore, how to make the rocket reusable so as to reduce the cost of rocket in orbit is a technical problem which needs to be solved by those skilled in the art at present.

Disclosure of Invention

The application provides a reusable rocket, which is used for realizing the reuse of the rocket and reducing the track-entering cost of the rocket.

In order to solve the technical problems, the application provides the following technical scheme:

a reusable rocket, comprising: the landing leg recovery device comprises a first sub-stage, a second sub-stage, a booster, a plurality of recovery landing legs and a plurality of grid rudder devices; wherein, the first sub-stage comprises a first-stage tail section, a first-stage rear transition section, a first-stage fuel tank section, a first-stage tank interval section, a first-stage oxygen tank section and a second-stage section from bottom to top in sequence; the primary engine is positioned in the primary tail section, the primary fuel tank is positioned in the primary fuel tank section, the primary oxygen tank is positioned in the primary oxygen tank section, and the primary oxygen tank and the primary fuel tank are communicated with the primary engine so as to provide fuel and oxygen for the primary engine; the booster is arranged at the outer side of one sub-stage to provide boosting power for the sub-stage; the secondary sub-stage comprises a secondary fuel tank section, a secondary tank interval section, a secondary oxygen tank section, a switching frame and a fairing from bottom to top in sequence; the secondary engine is positioned in a secondary stage, the upper end of the secondary stage is a secondary separating surface when the primary stage and the secondary stage are separated, the secondary fuel tank is positioned in the secondary fuel tank stage, the secondary oxygen tank is positioned in the secondary oxygen tank stage, and the secondary oxygen tank and the secondary fuel tank are communicated with the secondary engine so as to provide fuel and oxygen for the secondary engine; the lower end of the switching frame is fixedly connected with the upper end of the secondary oxygen box section, and the upper end of the switching frame is used for fixedly mounting a load bracket of the carrying equipment; the switching frame is enveloped in the fairing; one end of the plurality of recovery landing legs is uniformly hinged to a circumference of the outer surface of a sub-stage; the plurality of recovery landing legs can rotate from top to bottom by a preset obtuse angle around the hinge point, so that the recovery landing legs rotate from being flush with the outer surface of one sub-level to extending obliquely downwards, and the plurality of recovery landing legs are opened; the plurality of grid rudder devices are uniformly hinged to a circumference of the outer surface of a sub-stage and are rotatable about the hinge point from flush with the outer surface of a sub-stage to perpendicular to the outer surface of a sub-stage to control the attitude of a sub-stage during a sub-stage recovery vertical descent phase.

The reusable rocket as described above, wherein preferably 3 primary engines are arranged in a line in a primary tail section and 2 secondary engines are arranged in a line in a secondary section.

A reusable rocket as described above, wherein the booster is preferably statically indeterminate in a sub-stage.

The reusable rocket as described above, wherein preferably four recovery landing legs are hinged on the same circumference of the outer surface of a sub-stage and four rudder units are hinged on the same circumference of the outer surface of a sub-stage.

A reusable rocket as described above, wherein preferably recovering landing legs comprises: the main support leg, the auxiliary support leg and the buffer support leg; the main support leg is telescopic, one end of the main support leg is hinged to the first circumference of the outer surface of the primary fuel tank section, and the other end of the main support leg is hinged to one end of the auxiliary support leg; the other end of the auxiliary supporting leg is hinged to the first circumference of the outer surface of the first-stage rear transition section; one end of the buffer supporting leg is hinged to the second circumference of the outer surface of the primary fuel tank section, the other end of the buffer supporting leg is hinged to the hinged position of the main supporting leg and the auxiliary supporting leg, the buffer supporting leg is bent, and one side of the bent protruding portion faces the auxiliary supporting leg.

A reusable rocket as described above, wherein preferably the recovery landing leg further comprises: a foot pad; the foot pad is fixed to the lower surface of the end of the auxiliary leg hinged to the main leg to play a role of buffering at the moment of recovering the landing leg to be contacted with the ground.

A reusable rocket as described above, wherein preferably the lattice rudder means comprises: the device comprises a grid rudder, a grid rudder shaft, a transmission mechanism, a driving system and an unfolding locking mechanism; the grid rudder is hinged with a grid rudder shaft, the grid rudder shaft penetrates through the side wall of a sub-stage and stretches into the sub-stage, the transmission mechanism is positioned in the sub-stage and connected with the grid rudder shaft, and the driving system is also positioned in the sub-stage and connected with the transmission mechanism; the grid rudder is provided with a locking hole, the unfolding locking mechanism is fixed on the inner surface of one sub-stage, the locking end of the unfolding locking mechanism penetrates through the side wall of one sub-stage, and when the grid rudder is flush with the outer surface of one sub-stage before the grid rudder does not rotate around a hinge point hinged with the grid rudder shaft, the locking end of the unfolding locking mechanism penetrating through the side wall of one sub-stage stretches into the locking hole on the grid rudder.

A reusable rocket as described above, wherein preferably the grid rudder comprises: the honeycomb grid rudder comprises a frame and a plurality of grid walls, wherein the plurality of grid walls are embedded in the frame in a crossing mode to form the honeycomb grid rudder.

The reusable rocket as described above, wherein preferably the primary oxygen tank, primary fuel tank, secondary oxygen tank and secondary fuel tank all employ a self-generated booster system.

A reusable rocket as described above, wherein preferably the autogenous pressurizing system comprises: a heating line, a boost line, and an engine propellant vapor line; one end of the heating pipeline is connected to a transmission pipeline which is communicated with the primary fuel tank and the primary engine, a transmission pipeline which is communicated with the primary oxygen tank and the primary engine, a transmission pipeline which is communicated with the secondary fuel tank and the secondary engine, and a transmission pipeline which is communicated with the secondary oxygen tank and the secondary engine, and the other end of the heating pipeline is connected to an engine heating part so as to heat the vaporized part of oxygen/fuel to be introduced into the heating part; one end of an engine propellant steam pipeline is connected to the engine heating part, the other end of the engine propellant steam pipeline is connected to one end of a pressurizing pipeline, and the other end of the pressurizing pipeline is connected to the upper end of the primary oxygen tank/primary fuel tank/secondary oxygen tank/secondary fuel tank so as to send heated and vaporized oxygen/fuel vapor into the primary oxygen tank/primary fuel tank/secondary oxygen tank/secondary fuel tank to realize self-generated pressurizing.

Compared with the background technology, the reusable rocket provided by the application has the advantages that after the first sub-stage and the second sub-stage are separated, the first sub-stage vertically returns, the second sub-stage sends a payload into a preset track, the first sub-stage provides pneumatic resistance through the reverse thrust of the ignition of the first-stage engine and the deployment of the grid rudder, the deceleration of the first sub-stage is realized, the first sub-stage is supported by the recovery landing supporting leg arranged at the lower part of the first sub-stage during vertical landing, and the launching task can be re-executed after the recovery of the second sub-stage is repaired, assembled and fuel is supplemented.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings may be obtained according to these drawings for a person having ordinary skill in the art.

FIG. 1 is a schematic view of a reusable rocket of the present application;

FIG. 2 is a front view of a sub-stage of the reusable rocket of the present application;

FIG. 3 is a perspective view of the recovered landing leg of the reusable rocket of the present application;

FIG. 4 is a front view of the recovered landing leg of the reusable rocket of the present application;

FIG. 5 is a bottom view of the recovered landing leg of the reusable rocket of the present application;

FIG. 6 is a top view of the grid rudder device of the reusable rocket of the present application;

FIG. 7 is a perspective view of a lattice rudder arrangement of a reusable rocket of the present application;

FIG. 8 is a schematic diagram of the self-pressurizing system of the reusable rocket of the present application;

FIG. 9 is a schematic view of the avionics system of the reusable rocket of the present application;

FIG. 10 is a schematic view of the recovery of a sub-stage of the reusable rocket of the present application.

Detailed Description

Embodiments of the present application are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. In addition, spatial relationship terms such as "upper", "lower", "left", "right", "front", "rear", and the like are used for convenience of description to explain a positional relationship between two components. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the application.

As shown in fig. 1 and 2, the present application provides a reusable rocket, comprising: a first sub-stage 110, a second sub-stage 120, a booster 130, a plurality of recovery landing legs 140, and a plurality of grid rudder devices 150.

Wherein, the first sub-stage 110 is sequentially provided with a first-stage tail section 111, a first-stage rear transition section 112, a first-stage fuel tank section 113, a first-stage tank interval section 114, a first-stage oxygen tank section 115 and a second-stage section 116 from bottom to top; a primary engine is located in the primary tail section 111, a primary fuel tank is located in the primary fuel tank section 113, a primary oxygen tank is located in the primary oxygen tank section 115, and the primary oxygen tank and the primary fuel tank are in communication with the primary engine to provide fuel and oxygen to the primary engine. As an example, a sub-stage 110 has a diameter of 3.35m; the 3 liquid oxygen fuel liquid engines with 85 tons are arranged in the first-stage tail section 111 in a straight line, the ground specific impulse 291.3s and the engine mixing ratio are ensured to be 2.8, the control moment is provided by the swinging of the 3 liquid oxygen fuel liquid engines with 85 tons, the engine has the capability of starting the single task for more than three times, the thrust adjustment can reach 40% -100%, the starting acceleration is less than 2 seconds, the swinging angle of the engine is +/-8 degrees, and the thrust mass ratio is more than 90.

The booster 130 is disposed outside of a sub-stage 110 to provide boosting power for the sub-stage 110. As an example, the booster 130 and the sub-stage 110 adopt a hyperstatic binding mode, a rear main force transmission structure mode is adopted, a main binding point is arranged at the first-stage rear transition section 112, three-degree-of-freedom rear main force transmission binding is formed through a ball head seat and a ball head mode, a binding link mechanism is arranged at the front short shell of the first-stage oxygen tank in the first-stage tank interval 114 and the first-stage oxygen tank interval 115, each booster 130 and the sub-stage 110 adopt three binding links at each shell section (the first-stage tail section 111, the first-stage rear transition section 112, the first-stage fuel tank section 113, the first-stage tank interval 114, the first-stage oxygen tank interval 115 and the second-stage interval 116), the sub-stage 110 and the booster 130 are bound to form positioning constraint, and integral modal response is promoted. Optionally, two boosters 130 are provided outside of a sub-stage 110.

The secondary sub-stage 120 comprises a secondary fuel tank section 121, a secondary tank interval section 122, a secondary oxygen tank section 123, a switching frame 124 and a fairing 125 from bottom to top in sequence; the secondary engine is positioned in the secondary stage section 116, the upper end of the secondary stage section 116 is a secondary separating surface when the primary stage 110 and the secondary stage 120 are separated, the secondary fuel tank is positioned in the secondary fuel tank section 121, the secondary oxygen tank is positioned in the secondary oxygen tank section 123, and the secondary oxygen tank and the secondary fuel tank are communicated with the secondary engine so as to provide fuel and oxygen for the secondary engine; the lower end of the transfer frame 124 is fixedly connected with the upper end of the secondary oxygen box segment 123, and the upper end of the transfer frame 124 is used for fixing a load bracket so as to install carrying equipment (such as a satellite) through the load bracket; the transfer frame 124 is enveloped into the fairing 125, the load bracket mounted on the upper end of the transfer frame 124 and the carrying device fixed on the load bracket are enveloped into the fairing 125, and the separation of the fairing 125 is realized by rotating the transfer frame 124. As an example, the second sub-stage 121 is also 3.35m in diameter; the 2 vacuum plate 10 ton liquid oxygen fuel liquid engines are arranged in a two-stage section 116 in a straight line, the vacuum specific impulse 355s and the engine mixing ratio are ensured to be 3.0, the control moment is provided by the swing of the 2 vacuum plate 10 ton liquid oxygen fuel liquid engines, the engine stage has the capability of starting the single task for more than three times, the thrust adjustment can reach 40% -100%, the starting acceleration is less than 2 seconds, the swing angle of the engine is +/-8 degrees, and the thrust mass ratio is more than 40.

As shown in fig. 2, one end of the plurality of recovery landing legs 140 is uniformly hinged to a circumference of the outer surface of a sub-stage 110; and the plurality of recovery landing legs 140 may be rotated about the hinge point from the upper side to the lower side by a predetermined obtuse angle so as to be rotated from being flush with the outer surface of one sub-stage 110 to extending obliquely downward, thereby opening the plurality of recovery landing legs 140; the plurality of recovery landing legs 140 may be rotated about the hinge point from bottom to top at a predetermined obtuse angle such that it extends obliquely downward to be flush with the outer surface of a sub-stage 110, thereby closing the plurality of recovery landing legs 140. Optionally, four recovery landing legs 140 are hinged on the same circumference of the outer surface of a sub-stage 110.

In particular, as shown in fig. 3-5, the retrieve landing leg 140 includes: a main leg 141, a sub leg 142, and a buffer leg 143; the main leg 141 is telescopic, and one end of the main leg 141 is hinged to a first circumference of the outer surface of the primary fuel tank section 113, and the other end of the main leg 141 is hinged to one end of the sub leg 142; the other end of the secondary leg 142 is hinged to a first circumference of the outer surface of the primary aft transition section 112; one end of the buffer leg 143 is hinged to a second circumference of the outer surface of the primary fuel tank segment 113, the other end of the buffer leg 143 is hinged to the hinge of the primary leg 141 and the secondary leg 142, and the buffer leg 143 is bent, and one side of the bent protrusion faces the secondary leg 142. In addition, the retrieve landing leg 140 further includes: a foot pad 144; the foot pad 144 is fixed to the lower surface of the end of the sub leg 142 hinged to the main leg 141 to play a cushioning role at the moment the recovery landing leg 140 contacts the ground.

The recovery landing leg 140 can be folded and closed in the lift-off stage of the rocket, the main leg 141 is elongated before soft landing in the recovery vertical landing stage of the sub-stage 110, and the auxiliary leg 142 and the buffer leg 143 are opened along with the main leg 141, so that the recovery vertical landing sub-stage 110 is supported on the ground; in addition, the bent buffer leg 143 is far away from the section of the sub-stage 110 and is contacted with the auxiliary leg 142, so that the impact force at the moment of landing is buffered at the moment of recovering the contact of the landing leg 140 with the ground, the gesture of the sub-stage 110 can be adjusted and adapted during collision, rollover is prevented, and the weight of the sub-stage 110 is born after landing is completed.

As shown in fig. 6, the plurality of rudder units 150 are uniformly hinged to a circumference of the outer surface of one sub-stage 110, and the plurality of rudder units 150 can be rotated about the hinge point from being flush with the outer surface of one sub-stage 110 to being perpendicular to the outer surface of one sub-stage 110, thereby controlling the flying attitude of one sub-stage 110 in the one sub-stage 110 recovery vertical descent stage. Optionally, four grid rudder devices 150 are hinged on the same circumference of the outer surface of one sub-stage 110. Still alternatively, a plurality of rudder units 150 are hinged to a circumference of the outer surface of the two-stage section 116. Alternatively, four grid rudder devices 150 are hinged on a circumference of the outer surface of the two-stage section 116, and the four grid rudder devices 150 are located at an angle of 45 ° from the positive quadrant of the outer surface of the two-stage section 116.

As shown in fig. 7, the grid rudder device 150 includes: grid rudder 151, grid rudder shaft 152, transmission 153, drive system 154, and deployment locking mechanism 155; the grid rudder 151 is hinged with the grid rudder shaft 152, the grid rudder shaft 152 penetrates through the side wall of the sub-stage 110 and stretches into the sub-stage 110, the transmission mechanism 153 is positioned in the sub-stage 110 and connected with the grid rudder shaft 152, and the driving system 154 is also positioned in the sub-stage 110 and connected with the transmission mechanism 153; the grid rudder 151 has a locking hole therein, the deployment locking mechanism 155 is fixed to the inner surface of the one sub-stage 110, and the locking end of the deployment locking mechanism 155 penetrates through the side wall of the one sub-stage 110, and the locking end of the deployment locking mechanism 155 penetrating through the side wall of the one sub-stage 110 protrudes into the locking hole in the grid rudder 151 when the grid rudder 151 is flush with the outer surface of the one sub-stage 110 before the grid rudder 151 is not rotated about the hinge point hinged with the grid rudder shaft 152.

During the recovery of a sub-stage 110, the grid rudder 151 needs to perform two actions, deployment and rotation; and when the grid rudder 151 is unfolded, the locking end of the unfolding locking mechanism 155 is separated from the locking hole of the grid rudder 151, so that the grid rudder 151 rotates around the hinge point where the grid rudder shaft 152 is hinged, and is unfolded from being flush with the outer surface of one sub-stage 110 to being perpendicular to the outer surface of one sub-stage 110; after the grid rudder 151 is unfolded, the driving mechanism 153 is driven by the driving system 154 to drive the grid rudder shaft 152 to rotate, so that the rotation of the grid rudder 151 is realized, that is, the adjustment of the inclination angle of the grid rudder 151 is realized, and the direction is controlled in the recovery process of the sub-stage 110.

In addition, the grid rudder 151 includes: the honeycomb grid rudder comprises a frame and a plurality of grid walls, wherein the plurality of grid walls are embedded in the frame in a crossing mode, so that the honeycomb grid rudder is formed. Because the grid rudder 151 has the characteristics of thin wall, complex appearance, bearing high temperature flow flushing and the like, high temperature resistant materials are preferably adopted, and therefore, the grid wall and the frame which are preferably selected in the application can be made of titanium alloy materials. Additionally, optionally, the drive system 154 is a hydraulic servo system.

In the reusable rocket ascending section, the grid rudders 151 are folded and clung to the outer surface of the first sub-stage 110 to reduce additional resistance, in the recovery section of the first sub-stage 110, the grid rudders 151 are unfolded and controlled to rotate pneumatically through the driving system 154, so that the stability of the first sub-stage 110 is improved, the effective control of the track and the gesture of the first sub-stage 110 is realized, and a certain deceleration effect is achieved.

On the basis, the primary oxygen tank section 115 is arranged above, and a self-generating pressurizing system can be adopted for the primary oxygen tank; the primary fuel tank section 113 is arranged below, and the primary fuel tank can adopt a normal-temperature helium pressurization system or a self-generated pressurization system; the first-stage fuel tank is communicated to the first-stage engine through a transmission pipeline; the primary fuel tank is provided with a tunnel pipe which penetrates up and down, the primary oxygen tank is communicated to the primary engine through a transmission pipeline, and the transmission pipeline penetrates through the tunnel pipe. The secondary oxygen tank section 123 is arranged on the upper part, and a self-generating pressurizing system can be adopted for the secondary oxygen tank; the secondary fuel tank section 121 is arranged below, the secondary fuel tank can adopt a normal-temperature helium pressurizing system, and the secondary fuel can also adopt a self-generating pressurizing system; the secondary fuel tank is communicated to the secondary engine through a transmission pipeline; the secondary fuel tank is provided with a tunnel pipe which penetrates up and down, the secondary oxygen tank is communicated to the secondary engine through a transmission pipeline, and the transmission pipeline penetrates through the tunnel pipe.

As shown in fig. 8, the autogenous supercharging system includes: a heating line, a boost line 161 and an engine propellant vapor line 162; one end of the heating pipeline is connected to a transmission pipeline which is communicated with the primary fuel tank and the primary engine, a transmission pipeline which is communicated with the primary oxygen tank and the primary engine, a transmission pipeline which is communicated with the secondary fuel tank and the secondary engine, and a transmission pipeline which is communicated with the secondary oxygen tank and the secondary engine, and the other end of the heating pipeline is connected to an engine heating component (evaporator), so that part of oxygen/fuel is introduced into the heating component (evaporator) to heat and vaporize the part of oxygen/fuel, and the temperature is heated to a required value; one end of the engine propellant vapor pipeline 162 is connected to an engine heating component (evaporator), the other end of the engine propellant vapor pipeline 162 is connected to one end of the pressurizing pipeline 161, the other end of the pressurizing pipeline 161 is connected to the upper end of the primary oxygen tank/primary fuel tank/secondary oxygen tank/secondary fuel tank, so that heated and vaporized oxygen/fuel vapor is sent into the primary oxygen tank/primary fuel tank/secondary oxygen tank/secondary fuel tank to realize self-generated pressurizing, the requirements of propellant inlet working pressure and propellant storage tank thin-wall structure bearing internal pressure required in the starting and flying processes of the primary engine and the secondary engine are met, the storage tank structure is ensured to have enough strength and rigidity, the self-generated pressurizing system is simple and reliable in structure, the self-generated pressurizing flow and temperature are determined through multiple iterations of experiments, and the pressurizing requirement in the whole flying stage can be met.

In addition, one end of the pressurizing line 161 is also connected to a ground pressurizing line 163, so that pressurizing of the primary oxygen tank/primary fuel tank/secondary oxygen tank/secondary fuel tank is achieved through the ground pressurizing line 163 before the reusable rocket is not launched.

On the basis of the above, as shown in fig. 9, the first sub-stage 110 has a first sub-stage avionics system 170, and the second sub-stage 110 has a second sub-stage avionics system 180; both the primary and secondary avionics systems 170 and 180 employ POWERLINK (industrial real-time Ethernet protocol) based Ethernet over which control and measurement communicate.

A sub-level avionics system 170 comprising: the system comprises a first-stage HUB (HUB), a first-stage measurement and control combination, a rate gyro, a first-stage servo system, a first-stage initiating explosive device battery system, a first-stage instrument battery system and two evaporators (an air-conditioning evaporator and a condenser); the first-stage measurement and control combination, the rate gyro, the first-stage servo system and the first-stage HUB are all connected through Ethernet communication; the primary initiating explosive device battery system, the primary instrument battery system, the two devices and the primary measurement and control combination are all connected through Ethernet communication.

The secondary avionics system 180 includes: the system comprises a secondary HUB (HUB), a flight control combination, a secondary servo system, a safety control combination, a laser inertial measurement unit, an intelligent control combination, a safety control antenna, a safety control battery system, a pulse coherent transponder, a secondary initiating explosive device battery system, a secondary instrument battery system, two devices (an air conditioning evaporator and a condenser), a camera, a transmitter, a telemetry antenna and a GNSS antenna; the flight control combination, the secondary servo system, the security control combination, the laser inertial measurement unit, the intelligent control combination and the secondary HUB are all connected through Ethernet communication; the safety control antenna, the safety control battery system and the safety control combination are all connected through Ethernet communication; the pulse coherent transponder, the secondary fire work battery system, the secondary instrument battery system and the flight control combination are all connected through Ethernet communication; the two devices, the camera, the transmitter, the GNSS antenna and the intelligent control combination are all connected through Ethernet communication; the telemetry antenna is communicatively coupled to the transmitter via an ethernet network.

The primary HUB is connected to the secondary HUB by ethernet communication and the communication between the primary HUB and the secondary HUB is disconnected after the primary and secondary sub-stages are separated.

As shown in FIG. 10, after the reusable rocket of the application is launched, the first sub-level and the second sub-level are separated, the fairing is separated and the rocket is separated in sequence, the three separations are all cold separation, can be unlocked through initiating explosive device connection, and are used as separation energy forms through springs or pneumatic thrust.

The explosion bolt point type connection of the bearing 28t of the 12-M24 can be used, the separated energy source selects the cold air thrust device with ZK1A being subjected to flight verification through ignition of the nonelectric explosion detonating cord, the interaction force during separation of the first sub-level and the second sub-level is provided, the condition that the second sub-level is knocked down due to the effect of thrust after the first sub-level is avoided, and the thrust action point is selected at 3-4 positions. 1 to 1.5 seconds before the explosion bolt is ignited, the cold air pushing device starts to charge air to provide separation force. A set of cold air RCS attitude controllers are arranged in a secondary stage and a secondary stage to control the returning attitude of the secondary stage, 2 forward-pushing rockets are arranged on one half cover of the fairing, and 2 forward-pushing rockets are arranged on the other half cover of the fairing so as to realize the sinking of the propellant before the secondary stage ignition after separation.

The fairing is separated by adopting a hinge rotation separation mode under small overload, 2 parallel hinges with a distance of about 700mm are arranged on a half cover of the fairing, 3 separation springs are respectively arranged on the outer sides of the half cover close to the separation surface, the half covers are transversely connected by adopting 12-M20 explosion bolt point type, and the longitudinal directions of the fairings are connected by adopting 10-M20+4-M24 explosion bolt point type, so that an external bolt box is formed; the fairing longitudinal separation device adopts the structural form of explosion bolts and linear connection, 4-M24 explosion bolts are arranged on the front cone section of the column section-fairing of the fairing and the back cone section of the column section-fairing of the fairing, so that the connection reliability in flight is ensured. In addition, the explosion bolt is ignited by using a non-electric explosion detonating cord, and the linear connection structure is unlocked by using a limiting explosion detonating cord. During unlocking, transverse unlocking is firstly performed (the linear structure is advanced by 1s, 4 explosion bolts are used for unlocking), longitudinal unlocking is performed after 0.1s, and the half cover is rotated and separated around the hinge under the action of the separating spring.

The satellite and rocket separation can select strap+explosion bolt connection unlocking, point type explosion bolt unlocking or memory alloy integrated separation unlocking according to task requirements, and the separation energy source selects more mature metal springs which are distributed on a payload support or in a separation structure of a satellite self strap.

It will be evident to those skilled in the art that the application is not limited to the details of the foregoing illustrative embodiments, and that the present application may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the application 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.

Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.

Claims (10)

1. A reusable rocket, comprising: the landing leg recovery device comprises a first sub-stage, a second sub-stage, a booster, a plurality of recovery landing legs and a plurality of grid rudder devices;

wherein, the first sub-stage comprises a first-stage tail section, a first-stage rear transition section, a first-stage fuel tank section, a first-stage tank interval section, a first-stage oxygen tank section and a second-stage section from bottom to top in sequence; the primary engine is positioned in the primary tail section, the primary fuel tank is positioned in the primary fuel tank section, the primary oxygen tank is positioned in the primary oxygen tank section, and the primary oxygen tank and the primary fuel tank are communicated with the primary engine so as to provide fuel and oxygen for the primary engine;

the booster is arranged at the outer side of one sub-stage to provide boosting power for the sub-stage;

the secondary sub-stage comprises a secondary fuel tank section, a secondary tank interval section, a secondary oxygen tank section, a switching frame and a fairing from bottom to top in sequence; the secondary engine is positioned in a secondary stage, the upper end of the secondary stage is a secondary separating surface when the primary stage and the secondary stage are separated, the secondary fuel tank is positioned in the secondary fuel tank stage, the secondary oxygen tank is positioned in the secondary oxygen tank stage, and the secondary oxygen tank and the secondary fuel tank are communicated with the secondary engine so as to provide fuel and oxygen for the secondary engine; the lower end of the switching frame is fixedly connected with the upper end of the secondary oxygen box section, and the upper end of the switching frame is used for fixedly mounting a load bracket of the carrying equipment; the switching frame is enveloped in the fairing;

one end of the plurality of recovery landing legs is uniformly hinged to a circumference of the outer surface of a sub-stage; the plurality of recovery landing legs can rotate from top to bottom by a preset obtuse angle around the hinge point, so that the recovery landing legs rotate from being flush with the outer surface of one sub-level to extending obliquely downwards, and the plurality of recovery landing legs are opened;

the plurality of grid rudder devices are uniformly hinged to a circumference of the outer surface of a sub-stage and are rotatable about the hinge point from flush with the outer surface of a sub-stage to perpendicular to the outer surface of a sub-stage to control the attitude of a sub-stage during a sub-stage recovery vertical descent phase.

2. A reusable rocket according to claim 1, wherein 3 primary engines are arranged in a first-stage tail section and 2 secondary engines are arranged in a second-stage section.

3. A reusable rocket according to claim 1 or claim 2, wherein the booster is statically indeterminate bundled with a sub-stage.

4. A reusable rocket according to claim 1 or claim 2 wherein four recovery landing legs are hinged to the same circumference of the outer surface of a sub-stage and four rudder units are hinged to the same circumference of the outer surface of a sub-stage.

5. A reusable rocket according to claim 1 or 2, wherein recovering the landing leg comprises: the main support leg, the auxiliary support leg and the buffer support leg;

the main support leg is telescopic, one end of the main support leg is hinged to the first circumference of the outer surface of the primary fuel tank section, and the other end of the main support leg is hinged to one end of the auxiliary support leg;

the other end of the auxiliary supporting leg is hinged to the first circumference of the outer surface of the first-stage rear transition section;

one end of the buffer supporting leg is hinged to the second circumference of the outer surface of the primary fuel tank section, the other end of the buffer supporting leg is hinged to the hinged position of the main supporting leg and the auxiliary supporting leg, the buffer supporting leg is bent, and one side of the bent protruding portion faces the auxiliary supporting leg.

6. A reusable rocket according to claim 5, wherein recovering the landing leg further comprises: a foot pad; the foot pad is fixed to the lower surface of the end of the auxiliary leg hinged to the main leg to play a role of buffering at the moment of recovering the landing leg to be contacted with the ground.

7. A reusable rocket according to claim 1 or claim 2, wherein the grid rudder means comprises: the device comprises a grid rudder, a grid rudder shaft, a transmission mechanism, a driving system and an unfolding locking mechanism;

the grid rudder is hinged with a grid rudder shaft, the grid rudder shaft penetrates through the side wall of a sub-stage and stretches into the sub-stage, the transmission mechanism is positioned in the sub-stage and connected with the grid rudder shaft, and the driving system is also positioned in the sub-stage and connected with the transmission mechanism;

the grid rudder is provided with a locking hole, the unfolding locking mechanism is fixed on the inner surface of one sub-stage, the locking end of the unfolding locking mechanism penetrates through the side wall of one sub-stage, and when the grid rudder is flush with the outer surface of one sub-stage before the grid rudder does not rotate around a hinge point hinged with the grid rudder shaft, the locking end of the unfolding locking mechanism penetrating through the side wall of one sub-stage stretches into the locking hole on the grid rudder.

8. A reusable rocket according to claim 7, wherein the grid rudder comprises: the honeycomb grid rudder comprises a frame and a plurality of grid walls, wherein the plurality of grid walls are embedded in the frame in a crossing mode to form the honeycomb grid rudder.

9. A reusable rocket according to claim 1 or claim 2, wherein the primary oxygen tank, primary fuel tank, secondary oxygen tank and secondary fuel tank all employ a self-generated booster system.

10. A reusable rocket according to claim 9, wherein the autogenous pressurization system comprises: a heating line, a boost line, and an engine propellant vapor line;

one end of the heating pipeline is connected to a transmission pipeline which is communicated with the primary fuel tank and the primary engine, a transmission pipeline which is communicated with the primary oxygen tank and the primary engine, a transmission pipeline which is communicated with the secondary fuel tank and the secondary engine, and a transmission pipeline which is communicated with the secondary oxygen tank and the secondary engine, and the other end of the heating pipeline is connected to an engine heating part so as to heat the vaporized part of oxygen/fuel to be introduced into the heating part;

one end of an engine propellant steam pipeline is connected to the engine heating part, the other end of the engine propellant steam pipeline is connected to one end of a pressurizing pipeline, and the other end of the pressurizing pipeline is connected to the upper end of the primary oxygen tank/primary fuel tank/secondary oxygen tank/secondary fuel tank so as to send heated and vaporized oxygen/fuel vapor into the primary oxygen tank/primary fuel tank/secondary oxygen tank/secondary fuel tank to realize self-generated pressurizing.