CN114750977A

CN114750977A - Pneumatic separation pull type recovery second-stage small carrier rocket with big-end melon petal sleeve cover

Info

Publication number: CN114750977A
Application number: CN202210654785.9A
Authority: CN
Inventors: 隋国发
Original assignee: Jingyi Xinghang Beijing Technology Innovation Co ltd
Current assignee: Jingyi Xinghang Beijing Technology Innovation Co ltd
Priority date: 2022-06-10
Filing date: 2022-06-10
Publication date: 2022-07-15
Anticipated expiration: 2042-06-10
Also published as: CN114750977B

Abstract

The invention discloses a large-head melon flap sleeve cover pneumatic separation pull type recovery second-stage small carrier rocket, which belongs to the technical field of space rockets and comprises a first-stage arrow body, wherein the upper end of the first-stage arrow body is provided with an openable large-head melon flap sleeve cover and a recovery power device, a pneumatic separation attitude control device is further arranged in the large-head melon flap sleeve cover and comprises a gas cylinder, the gas cylinder is connected with gas transmission pipelines, the tail end of each gas transmission pipeline is provided with four branch pipes and valves for controlling the branch pipes to be opened and closed, and the four branch pipes are respectively a first flat exhaust pipe, a second flat exhaust pipe, a lower exhaust pipe and an upper exhaust pipe. The pneumatic separation attitude control device provided with the first flat exhaust pipe, the second flat exhaust pipe, the lower exhaust pipe and the upper exhaust pipe is adopted, interstage separation is realized in a pneumatic mode, and the pneumatic separation attitude control device has the functions of attitude adjustment, auxiliary landing, fuel bottom sinking guarantee of the rocket body, reverse thrust providing and the like, is simpler and more compact in structure and is beneficial to reducing the cost.

Description

Pneumatic separation pull type recovery second-stage small carrier rocket for large-head melon petal sleeve cover

Technical Field

The invention belongs to the technical field of space rockets, and particularly relates to a two-stage small carrier rocket with a large-head melon petal sleeve cover pneumatically separated and pulled for recovery.

Background

The interstage separation refers to the separation between two adjacent stages of the multi-stage rocket, the separation is generally realized by a traditional carrier rocket in a 'priming work' mode, namely, the separation force is provided by gunpowder, the 'priming work' device has extremely high requirements on safety in the aspects of storage, installation and the like, and the heat generated by the 'priming work' device can damage a stage of rocket body and influence the recycling of the stage of rocket body. In addition, the existing separation mode does not have the function of adjusting the posture of the rocket, so the structure and the control are relatively complex, and the cost is difficult to reduce.

Disclosure of Invention

Based on the technical problems in the prior art, the invention provides a large-head small carrier rocket with a melon flap sleeve cover for pneumatic separation and pull recovery, which adopts a pneumatic separation attitude control device, realizes the functions of interstage separation, attitude control, auxiliary landing and the like in a non-explosive mode at lower cost, has stable working effect, and avoids generating high heat to influence the flight and recovery reuse of rocket bodies.

According to the technical scheme, the invention provides a large-head melon petal sleeve cover pneumatic separation pull type recovery second-stage small carrier rocket which comprises a first-stage rocket body, wherein the upper end of the first-stage rocket body is provided with a large-head melon petal sleeve cover capable of being opened and closed and a recovery power device, and the lower end of the first-stage rocket body is provided with a first-stage power engine; a second-stage rocket is accommodated in the big-head melon petal sleeve cover, and the upper end of the second-stage rocket is loaded with a launching load; the big-end melon petal cover is also provided with a pneumatic separation attitude control device, the pneumatic separation attitude control device comprises a gas cylinder, the gas cylinder is connected with gas transmission pipelines, the gas transmission pipelines are at least two symmetrically arranged, the tail end of each gas transmission pipeline is provided with four branch pipes and valves for controlling the on-off of the branch pipes, and the four branch pipes are respectively a first flat exhaust pipe, a second flat exhaust pipe, a lower exhaust pipe and an upper exhaust pipe; the first flat exhaust pipe and the second flat exhaust pipe are both positioned in a horizontal plane, are perpendicular to each other and are radially symmetrical relative to the first-stage arrow body; the lower exhaust pipe inclines downwards towards the outside of the first-stage arrow body; the tail ends of the first flat exhaust pipe, the second flat exhaust pipe and the lower exhaust pipe are all arranged on the outer side surface of the big-head melon petal cover and are communicated with the outside; the upper exhaust pipe is upward.

Further, the gas cylinder is connected with a cylinder for jacking the secondary rocket upwards.

Preferably, the total four gas transmission pipelines are uniformly arranged along the circumferential direction of the big-head melon petal cover.

Further, the big-end melon petal cover sequentially comprises a melon petal cover, a sliding rail cylinder cover and a support from top to bottom; the melon petal cover sequentially comprises a melon petal part and a shell section from top to bottom; the device comprises a shell, two or more than two melon sections, a plurality of movable actuating mechanisms and a plurality of movable actuating mechanisms, wherein the shell sections are cylindrical; the sliding rail cylinder cover comprises a sleeve and an inverted cone cabin; the upper part of the sleeve is connected with the lower part of the shell section through an inverted cone cabin, and the lower part of the sleeve is connected with the support.

Preferably, the inner side surface of the sleeve is provided with a slide rail along the axial direction of the sleeve, and at least one part of the secondary rocket is in sliding connection with the slide rail in a matching way; and the support is provided with an electric control locking device for locking and releasing the secondary rocket.

Preferably, the power recovery devices are at least two and symmetrically arranged at two sides or the periphery of the inverted cone cabin.

Further, the power recovery device comprises a power recovery engine, the power recovery engine is provided with a spray pipe, and a power recovery cover is arranged outside the power recovery engine.

Preferably, the recovery power engine is movably connected with the inverted cone cabin and is connected with a power swing mechanism for controlling the rotation of the inverted cone cabin.

According to some embodiments, one primary power engine is arranged at the central position of the bottom of the primary arrow body, or two, three or more primary power engines are uniformly distributed.

Preferably, the resultant thrust force of the recovered power engine is adjustable between 80% and 200% of the dry weight of the recovered rocket, i.e. the resultant thrust force of the recovered power engine is equal to any force between 80% and 200% of the dry weight of the recovered rocket.

Compared with the prior art, the large-head melon petal sleeve cover pneumatic separation pull type recovery second-stage small carrier rocket has the following beneficial technical effects:

1. the big-end melon petal sleeve cover pneumatic separation pull type recovery second-stage small carrier rocket adopts the pneumatic separation attitude control device with the first flat exhaust pipe, the second flat exhaust pipe, the lower exhaust pipe and the upper exhaust pipe, realizes interstage separation in a pneumatic mode, has the functions of attitude adjustment, auxiliary landing, fuel bottom sinking guarantee of rocket bodies, reverse thrust and the like, is simpler and more compact in structure, and contributes to reducing cost.

2. The posture control of the second-stage small carrier rocket for pneumatic separation pull type recovery of the large-head melon petal sleeve cover can be finished by combining a pneumatic separation posture control device and a recovery power system, and can also be finished independently by the pneumatic separation posture control device or the recovery power system, so that the large-head melon petal sleeve cover can be selected, redundant and more reliable.

3. The pneumatic separation attitude control device of the second-stage small carrier rocket is mounted on the upper portion of the rocket, the mounting position is farther from the mass center of the rocket, the force arm is increased, and the control efficiency can be improved.

4. The big-end melon petal cover hood of the pneumatic separation pull type recovery second-stage small carrier rocket does not throw the hood and is integrally recovered with the first-stage rocket body, so that the large manpower and material resource consumption caused by tracking, monitoring and recovery of a recovery ship for fairing split offshore recovery or parachute recovery is avoided.

Drawings

Fig. 1A is a schematic view of an appearance structure of a rocket according to an embodiment of the present invention.

FIG. 1B is a schematic cross-sectional view of the rocket shown in FIG. 1A.

FIG. 1C is a schematic diagram of the rocket stage shown in FIG. 1A after separation.

FIG. 1D is a schematic view of the rocket in FIG. 1A in a recovery landing state.

Fig. 2 is a schematic top view of the rocket shown in fig. 1A.

Fig. 3 is a partially enlarged view of a portion a in fig. 1B.

FIG. 4 is a schematic top view of a portion of the gas pipeline of FIG. 1C.

Fig. 5 is a partially enlarged view of a portion B in fig. 4.

Fig. 6 is a schematic view of the structure shown in fig. 5, as viewed from the direction C.

Fig. 7A-7D are schematic bottom views of a layout of a primary power engine according to some embodiments of the invention.

Detailed Description

The technical solution 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. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention. Additionally, the scope of the present invention should not be limited to the particular structures or components or the particular parameters described below.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or component being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.

Referring to fig. 1A to fig. 1C, the two-stage small carrier rocket with the cucurbita maxima petal jacket pneumatically separated and drawn for recovery mainly comprises a first-stage rocket body 1, a second-stage rocket 2, a cucurbita maxima jacket 6 and systems necessary for carrier rockets such as the whole body, power, conveying, pressurization, structure and electric control; the second-stage small carrier rocket with the large-head melon petal cover and the pneumatic separation and pull recovery function has the main function of conveying a launching load 5 (such as a satellite) to a space preset orbit.

The first-stage arrow body 1 mainly comprises a first-stage oxygen box 12, a first-stage fuel box 13 and a first-stage power engine 11 positioned at the bottom of the first-stage arrow body 1, the upper end of the first-stage arrow body 1 is provided with a large-head melon petal cover 6 and a power recovery device 66 which can be opened and closed, the large-head melon petal cover is a fairing cover, the shape of the large-head melon petal cover is similar to that of a large-head melon petal, and the fairing cover is called as a large-head melon petal cover; the second-stage rocket 2 is accommodated in the big-head melon-petal cover 6, and the upper end of the second-stage rocket 2 is loaded with a launching load 5. A pneumatic separation posture control device 65 is also arranged at the position of the big-head melon flap cover 6. Landing legs may be added to assist in landing the rocket, if the rocket is generally needed. The invention has the innovative key points of the overall structure of the rocket, the overall layout of the primary power engine 11 and the power recovery device 66, the form and function design of the big-head melon-petal cover 6, the separation and attitude control function design of the pneumatic separation attitude control device 65 and the combined attitude control function design of the attitude control and power recovery device 66 of the pneumatic separation attitude control device 65.

The big-head melon flap cover 6 is particularly suitable for the condition that the outer envelope diameter of the launching load 5 (such as a satellite) is larger. The big-end melon petal cover 6 sequentially comprises a melon petal cover 61, a sliding rail cylinder cover 62 and a support 63 from top to bottom. The melon flap cover 61 comprises a melon flap part 611 and a shell section 612 from top to bottom in sequence. Two or more than two of the petal sections 611 are provided, for example, as shown in fig. 2, when the diameter of the launch load 5 exceeds the outer diameter of the secondary rocket 2, it is preferable to divide the launch load into four petal sections 611, and other forms may be adopted as the case may be. The shell section 612 is cylindrical, the upper part of the shell section 612 is movably connected with each melon-petal part 611, the melon-petal parts 611 are connected with actuating mechanisms for controlling the melon-petal parts to be opened and closed, the melon-petal parts are actuated to be opened or closed through electric, pneumatic and hydraulic actuating mechanisms or steering engines, and the opening degree is gradually adjusted according to the required opening degree, so that the cover opening and closing are realized. The butt joint surfaces between the melon-petal parts 611 are provided with high-temperature-resistant sealing structures (such as high-temperature-resistant rubber sealing structures), when the melon-petal parts 611 are closed, the sealing structures are matched and are in sealed contact with each other, and sealing between the melon-petal parts 611 is ensured.

The sliding rail cylinder cover 62 is arranged under the big-head melon petal cover 6. The slide rail cartridge cover 62 includes a sleeve 621 and an inverted cone chamber 623. The upper portion of sleeve 621 is connected to the lower portion of shell section 612 by an inverted conical chamber 623. As shown in fig. 1C, the side of the inverted cone 623 is an inverted cone table, and the diameters of the upper and lower ends are respectively matched with the shell section 612 and the sleeve 621, so as to form a continuous transition connection. The lower portion of the sleeve 621 is connected to the support 63. In one embodiment, the lower portion of the sleeve 621 is connected to the upper end of the first-stage arrow body 1, and the support 63 is located inside the sleeve 621; in another embodiment, a support 63 is attached to the lower end of sleeve 621, and support 63 is attached to the upper end of one-stage arrow body 1. The big-end melon petal cover 6 is always integrated with the first-level arrow body 1 into a whole and is not separated, so that the big-end melon petal cover and the first-level arrow body 1 are integrally recycled, and the recycling efficiency is higher.

The slide rail barrel cover 62 and the melon-petal cover 61 have pneumatic protection effect on the secondary rocket 2 and the launching load 5, the working condition environment of the protected product is improved, the design requirement is lowered, and the cost of related products is reduced. The sleeve 621 in the slide rail cylinder cover 62 can adopt an aluminum alloy section, a ring frame and a skin structure, or adopt a glass fiber and carbon fiber composite structure to further reduce weight. The length of the sleeve 621 is designed to be about 3m in general in consideration of the convenience of the process and the overall cost. If the sleeve 621 is long in size, it can be designed and produced in stages.

According to the requirement, a slide rail 622 can be arranged on the inner side surface of the sleeve 621 along the axial direction of the sleeve, and at least one part of the second-stage rocket 2 is in matched sliding connection with the slide rail 622, so that the mounting, restraining and separating limiting effects are achieved. In one embodiment, two or more sliding rails 622 are uniformly arranged along the circumferential direction, and the length direction of the sliding rails 622 is consistent with the length direction of the sleeve 621 (i.e. the length direction of the rocket); two or more sliding blocks are correspondingly arranged on the outer side surface of the second-stage rocket 2, and the sliding rail 622 is in sliding connection with the sliding blocks in a matching mode. It is understood that the slide rail 622 and the slide block form a set of slide connecting components, the positions of the slide connecting components can be reversed, and the specific structure capable of realizing the sliding can be adopted, so that the present disclosure is not limited in detail. The sliding rail 622 is preferably of an aluminum-based ceramic material structure with good strength and rigidity, and a solid lubricating coating is formed on the surface of the sliding rail 622, so that the sliding rail is more favorable for separation and protects the secondary rocket 2, the launching load 5 and the like from being damaged by external force.

An electric control locking device is arranged on the support 63, and the second-stage rocket 2 is installed on the support 63 which is matched with the support and is locked, fixed or unlocked, opened and released through the electric control locking device. The support 63 is designed in a serialized modularization mode according to the load types of the secondary rocket 2 and the like, and is used for quick matching of various loads, so that the cost is reduced, and the development period is shortened.

The pneumatic separation attitude control device 65 is used for pneumatic separation and attitude control, and may be a rocket deceleration device that rapidly falls, or the like. The pneumatic separation attitude control device 65 comprises a gas cylinder 651, and the gas cylinder 651 is connected with a gas transmission pipeline 653. The gas cylinder 651 preferably adopts a 23MPa or 35MPa composite material high-pressure gas cylinder, wherein the gas is high-pressure nitrogen or other mixed gas with larger specific gravity; for example, as shown in fig. 1B, the gas cylinder 651 is preferably installed in the space inside or around the first-stage rocket body 1 and the second-stage rocket 2 engine nozzle in the big-end melon petal shroud 6, but may be installed in other positions.

Referring to fig. 1C and fig. 4 to 6, the air transmission pipeline 653 is at least two symmetrically arranged pipelines (preferably, four pipelines are arranged uniformly along the circumferential direction of the big-end melon flap cover 6, that is, uniformly distributed along four quadrant lines), the end of each air transmission pipeline is provided with four branch pipes and valves 654 (for example, four-way valves or one solenoid valve is used for controlling the on-off of the branch pipes), and the four branch pipes are respectively a first flat exhaust pipe 655A, a second flat exhaust pipe 655B, a lower exhaust pipe 656 and an upper exhaust pipe 657; the first and second flat exhaust ducts 655A and 655B are each in one horizontal plane, and the first and second flat exhaust ducts 655A and 655B are perpendicular to each other, and the first and second flat exhaust ducts 655A and 655B are radially symmetrical with respect to the one-stage arrow body 1; the lower exhaust pipe 656 is inclined downward toward the outside of the first-stage rocket body 1 (preferably, an included angle of 30 degrees is formed with the central line of the rocket, or the outlet position can be adjusted up, down, left and right). The ends of the first flat exhaust pipe 655A, the second flat exhaust pipe 655B and the lower exhaust pipe 656 are all disposed on the outer side surface of the big-head melon petal shroud 6 (for example, on the shell section 612 and the inverted cone cabin 623) and are communicated with the outside (for example, through holes are disposed at corresponding positions on the shell section 612 and the inverted cone cabin 623, and the exhaust pipes penetrate through the corresponding through holes). The upper exhaust pipe 657 is directed upward; in one embodiment, the end of upper exhaust duct 657 is located within large-headed melon flap shroud 6 and extends upwardly along the inside surface of shell section 612.

The gas cylinder 651 is also connected to a gas cylinder 652 for lifting up the secondary rocket 2. Specifically, for example, the cylinder 652 has a cylinder and a piston, the cylinder is fixedly connected with the first-stage rocket body 1 or the big-end melon petal shroud 6, and the piston contacts the bottom of the second-stage rocket 2. The gas cylinder 651 is provided with a gas cylinder valve for controlling the gas release of the gas cylinder 651, high-pressure gas in the gas cylinder 651 is controlled to enter the cylinder 652 through the gas cylinder valve, and the cylinder 652 forms upward acting force and downward reacting force along the central line of the rocket body under the action of gas pressure to push the second-stage rocket 2 and the first-stage rocket body 1 to separate. The cylinder 652 has a piston actuation distance of, for example, 0.3m, so that the two-stage rocket 2 and the one-stage rocket are subjected to forceThe arrow body 1 generates a certain relative separation speed to ensure smooth separation. For the pneumatic separation force, for example, 8 sets of cylinders 652 are selected and simultaneously used for supplying and exhausting gas, the diameter of the cylinder 652 is designed to be about 100mm, the gas pressure in the cylinder is 3MPa, and the generated separation force is: f =8 × 3.14 × 5²X 3 × 10=18.84 t. The pneumatic separation force of 18.8t is enough to separate the second-stage rocket 2 from the first-stage rocket body 1 smoothly.

In the process of separating the first-stage rocket body from the second-stage rocket, after the melon-petal cover 61 is opened, on one hand, the melon-petal cover is pushed by the air cylinder 652, on the other hand, the melon-petal cover is exhausted by the upper exhaust pipe 657, so that the separation of the first-stage rocket body and the second-stage rocket body is assisted, and the speed of the rocket is reduced.

In terms of attitude control, please refer to fig. 4 and 5, the first and second exhaust pipes in the same direction and the same side can exhaust (the exhaust direction is the same) to control pitching or yawing, and the first and second exhaust pipes in different directions can exhaust (the exhaust direction is opposite and located at two sides of the rocket) to control rolling. The four or two opposite lower exhaust pipes 656 exhaust the gas obliquely downwards together, and the generated reaction force gives a positive thrust and a positive acceleration to the rocket, so that the fuel of the storage tank (the primary oxygen tank 12 and the primary fuel tank 13) of the primary rocket body 1 is ensured to sink, and the phenomenon that the fuel cannot normally enter the engine in a weightless state to influence the operation of the engine is avoided. In addition, when the rocket is landed and recovered, the forward thrust can also reduce the speed of the first-stage rocket body 1, so that the rocket is favorably recovered.

Four sets of exhaust lines can also be simplified into two sets, and symmetrically installed on both sides of the shell section 612. When four sets of exhaust pipelines are designed, the symmetrical exhaust pipelines can be adopted to mainly consider attitude control and attitude adjustment; another group of symmetrically designed exhaust pipelines mainly considers a positive thrust for the rocket and a positive acceleration for the rocket to ensure that the fuel in the storage tank sinks; i.e. redundancy is taken into account, efficiency is also improved. The ends of the first planar exhaust duct 655A, the second planar exhaust duct 655B and the lower exhaust duct 656 are mounted as close as possible to the upper edge of the housing section 612; the farther the position is upward, the farther the distance from the center of mass of the rocket is, and the higher the attitude control efficiency is.

The recovery power devices 66 are preferably two and symmetrically arranged at two sides of the inverted cone 623, and preferably, a plurality of recovery power devices 66 uniformly distributed in the circumferential direction can be arranged according to requirements. As shown in fig. 3, the power recovery device 66 mainly includes a power recovery engine 661, the power recovery engine 661 includes a nozzle 662, and a power recovery cover 665 is provided outside the power recovery engine 661. In an embodiment, the recycling power cover 665 is fixedly connected with the outer side surface of the inverted cone 623 in a matching manner, and a through hole is formed at a corresponding position at the tail end of the spray pipe 662 so as to allow the flame sprayed by the spray pipe 662 to pass through. The power recovery engine 661 is movably connected with the inverted cone 623 and is connected with a power swing mechanism 663 for controlling the rotation of the power recovery engine. The power swing mechanism 663 includes, for example, a universal hinge mechanism and an actuator, the power recovery engine 661 is rotatably connected to the power recovery engine 661 through the hinge mechanism, and the direction of the nozzle 662 is controlled by controlling the rotation of the power recovery engine 661 through the actuator and the control system. Two specific embodiments of the power recovery device 66 and its operating mechanism are given below.

The first embodiment is as follows: the two-way swinging of the recovered power.

Two power recovery engines 661 are installed on the rocket, which can swing in both directions (both along the circumferential direction of the rocket and along the radial direction of the rocket). In the launching and taking-off section of the rocket, two power recovery engines 661 and the primary power engine 11 are started together to boost the rocket to ascend in an accelerated manner. After the rocket has risen to a certain height, the regenerative power engine 661 may be shut down at a proper time in order to reduce the rising acceleration of the rocket. The two power recovery engines 661 deflect in the same direction to control pitch and yaw attitude, and deflect in different directions to control roll attitude. The rocket is recovered to a certain height (about 10km away from the ground) before landing, a power recovery engine 661 is started to form upward thrust to the rocket, and the rocket is decelerated; before landing, the thrust of the recovery power engine 661 is adjusted to balance the gravity and speed of the rocket, and the attitude of the rocket is adjusted by the deflection of the recovery power engine 661 and the jet pipe 662 thereof, so that the rocket recovery process is stably controlled and accurate landing is achieved.

Example two: two circumferential unidirectional swing pipes for recovering power.

Two power recovery engines 661 are installed on the rocket, which can swing in one direction in the circumferential direction (only can rotate in the circumferential direction of the rocket, but cannot rotate in the radial direction of the rocket). In the launching and taking-off section of the rocket, two circumferential swinging recovery power engines 661 and the primary power engine 11 are started together to boost the rocket to ascend in an accelerated manner. After the rocket is raised to a certain height, the power recovery engine 661 may be shut down at a proper time in order to reduce the rising acceleration of the rocket. The pitching attitude of the rocket is controlled by circumferential homodromous deflection of the two recovery power engines 661, and the rolling attitude is controlled by heterodromous deflection; the yaw attitude of the rocket is controlled by adjusting the thrust of the two recovered power engines 661. The rocket is recovered to a certain height (about 10km away from the ground) before landing, a power recovery engine 661 is started to form upward thrust to the rocket, and the rocket is decelerated; before landing, the thrust of the recovery power engine 661 is adjusted to balance the gravity and speed of the rocket and adjust the attitude, and the attitude of the rocket is adjusted through the deflection recovery power engine 661 and the jet pipe 662 thereof, so that the rocket recovery process is stably controlled and accurate landing is realized.

Since the recovery power device 66 for rocket recovery is arranged on the side surface of the inverted cone 623, the aerodynamic influence of rocket flight is reduced. In addition, the thrust vector of the recovery power engine 661 is always above the gravity center of the rocket, forming a pulling force to the rocket, and being easier to control stably; instead of the prior rocket such as falcon, the power recovery device is arranged below the rocket body to form upward thrust to the rocket, and the rocket is in an inverted pendulum in the recovery process and is difficult to control.

The scheme of the invention adopts a working mechanism combining recovery power and pneumatic attitude control. For small carrier rockets, the attitude of the rocket can be controlled by a pneumatic separation attitude control device in the launching and taking-off section and the flying and recovering processes of the rocket (the pitching attitude of the rocket can also be controlled by radial deflection or thrust adjustment of two recovery power engines); before landing, the thrust of the recovery power engine is adjusted to balance the gravity and the speed of the rocket, so that the rocket recovery process is stably controlled and accurately landed.

Referring to fig. 7A to 7D, the arrangement and layout of the primary power engine 11 according to some embodiments of the present invention is shown. The primary power engine 11 is arranged at the bottom of the primary arrow body 1, and can be arranged at a central position, or two, three or four primary main engines are uniformly distributed, or a plurality of main engines such as five, six, seven, eight and the like can be arranged according to requirements. If the space of the outer diameter of the first-stage arrow body 1 is insufficient, the first-stage power engine 11 may protrude out of the outer shell of the first-stage arrow body 1, and a fairing or a wing cover may be added to the protruding portion.

In a preferred embodiment, the total thrust force of the recovery power engine is set at 8% to 12%, preferably around 10%, of the total thrust force of the primary power engine. For example, if the resultant force of the primary power engine and the recovered power engine is 165t, the resultant force of the thrust forces of the recovered power engine is set to about 15 t. The specific parameters need to be optimized and determined according to the dry weight of the recovered rocket, the recovered fuel, the allowance and other parameters. The thrust of the power recovery engine can be adjusted within 50% of the rated thrust. The total weight of the rocket during recovery and landing is set to be about 60% of the thrust of the recovery power engine, and 10% of margin is reserved. Preferably, the resultant thrust force of the recovered power engine is adjustable between 80% and 200% of the dry weight of the recovered rocket. The dry weight of the recovered rocket refers to the total weight of the rocket (excluding fuel) during recovery, namely the total weight of the first-stage rocket body, the big-end melon valve cover and the recovered power device, and related components therein.

The secondary power of the secondary rocket 2 can adopt a 15t bidirectional swinging engine, and the pitching and yawing postures are controlled through the swinging of the engine. The second-stage rocket 2 can also adopt a similar pneumatic attitude control system to control the rolling attitude, and the system is simple and has low cost.

Because the second-stage rocket is not recycled, the invention adopts a scheme of large first-stage and small second-stage, namely the resultant force of the engine thrust of the first-stage rocket body is far greater than that of the engine of the second-stage rocket, thereby improving the recycling and reusing efficiency of the rocket as much as possible. In the typical case of the present embodiment, the takeoff thrust and the secondary thrust are set to 165t and 15t, respectively.

The rocket flying procedure and state of a preferred embodiment of the present invention are as follows, please refer to fig. 1A to 1D.

(1) During ground launching of a carrier rocket and ascending flight of the first-stage rocket body 1, the first-stage power engine 11 is started to work, the melon petal cover 61 is in a cover closing state, the recovery power engine 661 is started to work, and the thrust generated by the first-stage power engine 11 and the carrier rocket are used for jointly pushing the rocket to ascend.

(2) And the primary power engine 11 and the power recovery engine 661 are turned off before the rocket passes through the atmosphere to reach the designated separation altitude and the primary rocket body and the secondary rocket are separated. The melon petal cover 61 is opened, the pneumatic separation attitude control device 65 is started, and the second-stage rocket 2 and the first-stage rocket body 1 are pushed to be separated; an upper exhaust pipe 657 of the pneumatic separation attitude control device 65 exhausts air, which not only assists the separation of the first-stage rocket body and the second-stage rocket, but also reduces the speed of the rocket.

(3) After the first-stage rocket body and the second-stage rocket are separated, the second-stage rocket 2 continues flying, and the launching load 5 (such as a satellite) is pushed to enter a preset orbit.

(4) After the first-stage rocket body and the second-stage rocket are separated, the melon petal cover covers, and the first-stage sub-orbital rocket comprising the first-stage rocket body 1 and the big-end melon petal cover 6 returns to the ground and falls back to the ground under the action of the gravity of the earth. In the process, the primary power engine and the power recovery engine are flamed out and do not work; the pneumatic separation attitude control device converts the attitude control function and plays a role in adjusting the attitude.

(5) The first-stage sub-orbital rocket returns to the atmosphere and continuously falls to fly to the ground. The rocket is preset at a preset height before falling to the ground, the recovery power engine 661 is restarted, the rocket is continuously adjusted according to the magnitude and direction of the thrust, the postures of pitching, yawing, rolling and the like of the rocket are controlled by combining the posture adjusting function of the pneumatic separation posture control device 65, the rocket slowly and stably descends, and finally the rocket lands on the recovery device 8 at a specified recovery position.

The general technical scheme and indexes of the rocket of the embodiment of the invention are as follows:

SSO load mass: low track load 1 t;

rocket length: 33 m;

the diameter of the segment of the melon petal housing is 3 m;

rocket power: liquid oxygen, kerosene systems;

primary power: two 75t engines (or three 50t engines);

secondary power: one 10t or two 5t bidirectional swinging engines;

recovering power: two 5t bidirectional swinging engines with 50% thrust adjustment;

takeoff thrust: 155 t;

and (3) recovery and reuse: and 20 times.

The technical scheme of the invention can be used for various small and medium carrier rockets with the diameter of 4.5m, and the high orbit load range can cover 100kg to 5 t.

In conclusion, the recovery power device for rocket recovery is arranged on the side surface of the large-head melon petal sheathing inverted cone cabin at the upper part of the rocket, so that the aerodynamic influence of the rocket in flight is reduced. Meanwhile, the thrust vector of the rocket recovery power engine is always above the gravity center of the rocket, so that tension is formed on the rocket, namely 'pull recovery', and the rocket recovery power engine is easier to stably control compared with the existing scheme that the recovery power is positioned at the bottom of the rocket.

The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the present invention may occur to those skilled in the art without departing from the principle of the present invention, and such modifications and embellishments should also be considered as within the scope of the present invention.

Claims

1. A big-end melon petal sleeve cover pneumatic separation pull type recovery second-stage small carrier rocket is characterized by comprising a first-stage rocket body, wherein the upper end of the first-stage rocket body is provided with a big-end melon petal sleeve cover and a recovery power device which can be opened and closed, and the lower end of the first-stage rocket body is provided with a first-stage power engine; a second-stage rocket is accommodated in the big-end melon petal sleeve cover, and the upper end of the second-stage rocket is loaded with a launching load;

the big-end melon petal cover is also internally provided with a pneumatic separation attitude control device, the pneumatic separation attitude control device comprises a gas cylinder, the gas cylinder is connected with gas transmission pipelines, the gas transmission pipelines are at least two symmetrically arranged, the tail end of each gas transmission pipeline is provided with four branch pipes and valves for controlling the branch pipes to be switched on and off, and the four branch pipes are respectively a first flat exhaust pipe, a second flat exhaust pipe, a lower exhaust pipe and an upper exhaust pipe; the first flat exhaust pipe and the second flat exhaust pipe are both positioned in a horizontal plane, are perpendicular to each other and are radially symmetrical relative to the first-stage arrow body; the lower exhaust pipe inclines downwards towards the outside of the first-stage arrow body; the tail ends of the first flat exhaust pipe, the second flat exhaust pipe and the lower exhaust pipe are all arranged on the outer side surface of the big-head melon petal cover and are communicated with the outside; the upper exhaust pipe is upward.

2. The big-head melon petal sleeve cover pneumatic separating and pulling type recovery second-stage small carrier rocket as claimed in claim 1, wherein the gas cylinder is further connected with a gas cylinder for jacking the second-stage rocket upwards.

3. The big-end melon flap sleeve cover pneumatic separation pull type recovery second-stage small carrier rocket as claimed in claim 1, wherein the number of the gas transmission pipelines is four and the gas transmission pipelines are uniformly arranged along the circumference of the big-end melon flap sleeve cover.

4. The big-end melon flap sleeve cover pneumatic separation pull type recovery two-stage small carrier rocket of claim 1, wherein the big-end melon flap sleeve cover comprises a melon flap cover, a sliding rail cylinder cover and a support from top to bottom in sequence; the melon petal cover sequentially comprises a melon petal part and a shell section from top to bottom; the device comprises a shell, two or more than two melon sections, a plurality of movable actuating mechanisms and a plurality of movable actuating mechanisms, wherein the shell sections are cylindrical; the sliding rail cylinder cover comprises a sleeve and an inverted cone cabin; the upper part of the sleeve is connected with the lower part of the shell section through the inverted cone cabin, and the lower part of the sleeve is connected with the support.

5. The big-end melon petal cover pneumatic separating and pulling type recovery second-stage small carrier rocket as claimed in claim 4, wherein the inner side surface of the sleeve is provided with a slide rail along the axial direction, and at least one part of the second-stage rocket is in sliding connection with the slide rail in a matching way; and the support is provided with an electric control locking device for locking and releasing the secondary rocket.

6. The big-end melon flap sleeve cover pneumatic separation pull type recovery second-stage small carrier rocket according to claim 4, characterized in that the recovery power device has at least two and is symmetrically arranged at two sides or periphery of the inverted cone cabin.

7. The large-head melon petal sleeve cover pneumatic separation and pull type recovery second-stage small carrier rocket as claimed in claim 6, wherein the power recovery device comprises a power recovery engine, the power recovery engine is provided with a spray pipe, and a power recovery cover is arranged outside the power recovery engine.

8. The large-head melon petal cover pneumatic separation and pull type recovery second-stage small carrier rocket as claimed in claim 7, wherein the recovery power engine is movably connected with the inverted cone cabin and is connected with a power swing mechanism for controlling the rotation of the inverted cone cabin.

9. The large-head melon petal cover pneumatic separating and pulling type recovery second-stage small carrier rocket as claimed in any one of claims 1-8, wherein one first-stage power engine is arranged at the central position of the bottom of the first-stage rocket body, or two or more first-stage power engines are uniformly distributed.

10. The cyrtomium fortunei petal shroud pneumatic separation pull type recovery second-stage small launch vehicle of any one of claims 1-8, characterized in that the thrust resultant force of the recovery power engine is equal to any one force between 80% -200% of the dry weight of the recovery rocket.