CN114963867B - Vacuum high-speed emission system of combined power rocket and emission and recovery method thereof - Google Patents
Vacuum high-speed emission system of combined power rocket and emission and recovery method thereof Download PDFInfo
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- CN114963867B CN114963867B CN202210686241.0A CN202210686241A CN114963867B CN 114963867 B CN114963867 B CN 114963867B CN 202210686241 A CN202210686241 A CN 202210686241A CN 114963867 B CN114963867 B CN 114963867B
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- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000011084 recovery Methods 0.000 title abstract description 8
- 230000007246 mechanism Effects 0.000 claims abstract description 11
- 238000004064 recycling Methods 0.000 claims abstract description 9
- 230000008569 process Effects 0.000 claims description 14
- 230000008602 contraction Effects 0.000 claims description 6
- 239000000446 fuel Substances 0.000 abstract description 7
- 235000015842 Hesperis Nutrition 0.000 description 5
- 235000012633 Iberis amara Nutrition 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 2
- 239000002760 rocket fuel Substances 0.000 description 2
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/0406—Rail launchers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
Abstract
The invention discloses a vacuum high-speed launching system of a combined power rocket and a launching and recycling method thereof, wherein the launching system comprises a vacuum pipeline, a vacuum pump is arranged on the vacuum pipeline, and the vacuum pump is used for generating negative pressure for the vacuum pipeline; the vacuum pipeline is a hollow pipeline, and two ends of the vacuum pipeline are respectively provided with an openable valve; a track is laid at the bottom of the vacuum pipeline and is used for providing a path for the movement of the carrier rocket; the carrier rocket comprises a space carrier rocket, wherein the tail end of the space carrier rocket is connected with an accelerating rocket, a stamping boosting rocket is respectively arranged at the two sides of the space carrier rocket and near the tail end of the space carrier rocket, and an air rudder is respectively arranged at the two sides of the space carrier rocket and near the front end of the space carrier rocket; the air rudder is internally provided with a folding-state speed reducing wing which is connected with an unfolding and shrinking mechanism. The method solves the problems of small effective load, high cost and high fuel consumption of the rocket recovery method in the existing rocket launching method.
Description
Technical Field
The invention belongs to the technical field of rocket launching, and particularly relates to a vacuum high-speed launching system of a combined power rocket and a launching and recycling method thereof.
Background
In recent years, with the rapid development of small satellite technology and rocket technology, a small carrier rocket is pushed to a large stage of space launching. In the future, the small carrier rocket capable of realizing quick and effective space launching has great value and becomes a tomorrow star for human beings to carry out space activities. At present, a large number of small-sized carrier rockets are launched, mainly by accelerating the carrier rockets from the ground or the sea surface to the atmosphere through the power of the rockets, and then continuously flying the rockets into a target orbit by the rear-stage rockets. The launching method needs a very large first-stage rocket, the mass of the first-stage rocket is about half of the total mass, the effective load ratio of the rocket is small, and the cost is high.
In addition, the vertical recovery of space is successfully realized at present, and the first mode is that the rocket falls from a track to an original launching site by being driven by a rocket engine, and the mode needs to consume about 27% of taking-off carried fuel; the other mode is to directly fall to the sea surface from the track position, the returning mode only needs to consume less than 10% of fuel, but a movable offshore recovery platform needs to be additionally built, the cost is high, and meanwhile, the recovered rocket needs to be returned to a rocket launching site for a plurality of days, so that the recycling efficiency of the rocket is affected.
Disclosure of Invention
The invention aims to provide a vacuum high-speed launching system of a combined power rocket and a launching and recycling method thereof, which are used for solving the problems of smaller effective load and high cost of the rocket and high fuel consumption of the existing rocket recycling method in the existing rocket launching method.
The invention adopts the following technical scheme: the vacuum high-speed launching system of the combined power rocket comprises a vacuum pipeline, wherein a vacuum pump is arranged on the vacuum pipeline and used for generating negative pressure for the vacuum pipeline; the vacuum pipeline is a hollow pipeline, and two ends of the vacuum pipeline are respectively provided with an openable valve; a track is paved at the bottom of the vacuum pipeline and is used for providing a path for the movement of the carrier rocket;
the carrier rocket comprises a space carrier rocket, wherein the tail end of the space carrier rocket is connected with an accelerating rocket, a stamping boosting rocket is respectively arranged at the positions, close to the tail end, of the two sides of the space carrier rocket, and an air rudder is respectively arranged at the positions, close to the front end, of the space carrier rocket; a speed reducing wing in a folded state is arranged in the air rudder, and the speed reducing wing is connected with an unfolding and shrinking mechanism;
the accelerating rocket is used for accelerating the space carrier rocket positioned in the vacuum pipeline and separating the space carrier rocket when the space carrier rocket flies out of the vacuum pipeline; the stamping boosting rocket is used for starting working after the space carrier rocket flies out of the vacuum pipeline and pushing the space carrier rocket to fly out of the atmosphere; the air rudder is used for changing the flight direction of the space launch vehicle; the expansion and contraction mechanism is used for expanding the deceleration wing after the ram booster rocket is separated from the space carrier rocket.
Further, the expansion and contraction mechanism includes: track grooves are formed in two sides of the space launch vehicle, the track grooves are formed along the extending direction of the space launch vehicle, a lead screw is installed in each track groove, and one end of each lead screw is connected with a steering engine for driving the lead screw to rotate; the unfolding side of the deceleration wing is connected with a deceleration wing control rod, one end of the deceleration wing control rod is connected to the screw rod, and the deceleration wing control rod is used for reciprocating translation along the length direction of the screw rod so as to unfold or fold the deceleration wing.
Further, the cross section of the rail is I-shaped, a guide rail is arranged on the rail Fang Qiantao and used for moving reciprocally along the rail, the guide rail is connected with the space launch vehicle through an electromagnetic pin, and the electromagnetic pin is used for connecting or separating the space launch vehicle from the rail.
Further, the device also comprises a launching platform, wherein the launching platform is used as a ground landing place for returning the space carrier rocket.
The second technical scheme adopted by the invention is that the launching method of the combined power rocket vacuum high-speed launching system is based on the combined power rocket vacuum high-speed launching system, and comprises the following steps:
firstly, combining a space carrier rocket, a ram rocket, an accelerating rocket and an air rudder together to complete the assembly work of the carrier rocket, then installing the carrier rocket on a track in a vacuum pipeline, and then closing valves at two ends of the vacuum pipeline;
secondly, the master control system controls the vacuum pump to work so that the vacuum degree in the vacuum pipeline reaches a target value;
thirdly, the master control system controls the accelerating rocket to start ignition work, the space carrier rocket is accelerated to Mach 2-2.5, when the space carrier rocket reaches the tail end of a vacuum pipeline, a valve at the outlet of the vacuum pipeline is opened, and an electromagnetic pin is opened at the same time, so that the space carrier rocket is separated from the guide rail, and the space carrier rocket flies out of the vacuum pipeline;
fourthly, the accelerating rocket is separated from the space carrier rocket, the direction and the gesture of the space carrier rocket are adjusted through the air rudder, the ram rocket starts to work, and after the space carrier rocket is continuously pushed to fly to the outside of the atmosphere, the ram rocket is separated from the space carrier rocket;
and fifthly, continuously flying the space carrier rocket to a target position, and returning the space carrier rocket to a launching platform independently after completing the task.
The second technical scheme adopted by the invention is that the recovery method of the combined power rocket vacuum high-speed launching system is based on the combined power rocket vacuum high-speed launching system, and comprises the following steps:
step one, implementing a free falling process: the space carrier rocket freely falls into the atmosphere until the altitude is less than or equal to 30 km;
secondly, implementing a rocket braking process: starting rocket braking to enable the space carrier rocket to decelerate to be smaller than or equal to Mach 0.6-0.8, and opening the deceleration wing;
thirdly, implementing a flying process; under the control of the air rudder and the deceleration wings, the space carrier rocket continues to adjust the pose and decelerate, and guides the flying according to the signals received from the launching platform;
fourthly, implementing the gesture adjusting and speed reducing landing process: after the space carrier rocket flies to the set height above the launching platform, the engine of the space carrier rocket is started to decelerate again, and the engine, the deceleration wing and the air rudder are adjusted to be in a vertical landing posture together, and then gradually land to the launching platform.
The beneficial effects of the invention are as follows: the pipeline launching mode adopted by the invention can efficiently and quickly increase the space carrier rocket to the designed target speed in the vacuum pipeline, even if the space carrier rocket realizes high initial speed on the ground, the rocket fuel is greatly saved, and the effective load ratio of the rocket is improved; the weight of the first-stage rocket can be saved, the rocket launching efficiency is greatly improved, and the launching cost is reduced. The ram boosting rocket is adopted in the accelerating rocket power atmosphere environment, so that the space carrier rocket can be continuously pushed to continuously fly without the oxidant, and the passive mass of rocket launching is further reduced. Meanwhile, the space carrier rocket can change the flight direction by means of an air rudder, so that a vacuum pipeline can be built in more relief environments, and the launching geographic position is flexible; the air rudder can regulate and control the flight direction, the gesture and the like of the space carrier rocket, realizes the self-control capability of the space carrier rocket in the air, and is convenient for the space carrier rocket to fly in a safer airspace and a more accurate gesture. The invention adopts the emission mode of various power combinations, and can greatly expand the effective carrying capacity and application market of the emission mode by selecting or adjusting the performance design of related power. In addition, the rocket return mode adopted by the invention has the advantages that the fuel consumption is reduced to within 7 percent, and the recycling efficiency is higher.
Drawings
FIG. 1 is a schematic diagram of a system structure of a vacuum high-speed launching system of a combined power rocket and a launching and recycling method thereof;
FIG. 2 is a schematic diagram of a control flow of a return system of a vacuum high-speed launching system and a launching and recycling method of a combined power rocket according to the present invention;
FIG. 3 is a schematic diagram of a vacuum high-speed launching system of a hybrid rocket according to the present invention;
FIG. 4 is a schematic view of a rail assembly cross section of a modular power rocket vacuum high speed launch system of the present invention;
FIG. 5 is a schematic view of the structure of a launch vehicle of a combined power rocket vacuum high-speed launch system according to the present invention;
FIG. 6 is a schematic view of the space launch vehicle of the vacuum high-speed launch system of the combined power rocket of the present invention;
FIG. 7 is an enlarged schematic view of a orbital slot of a vacuum high-speed launch system of a hybrid rocket according to the present invention;
fig. 8 is a schematic diagram of a deceleration wingspan open state of a combined power rocket vacuum high-speed launch system according to the present invention.
Wherein, 1, a general control system, 2, a vacuum pipeline, 21, a front valve, 22, a rear valve, 3, a vacuum pump, 4, a carrier rocket, 41, an accelerating rocket, 42, a ram boosting rocket, 43, a space carrier rocket, 44, rudders, 441, track slots, 442, speed reducing wing control rods, 443, speed reducing wings, 444, steering engines, 445, lead screws, 5, launch platform, 6, tracks, 61, guide tracks, 62, electromagnetic pins, 7, brackets.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The invention provides a vacuum high-speed launching system of a combined power rocket, which is shown in fig. 3, and comprises a vacuum pipeline 2, wherein the vacuum pipeline 2 is built on a rocket launching site. The vacuum pipeline 2 is a hollow pipeline, an openable front valve 21 is arranged at the inlet end of the vacuum pipeline 2, an openable rear valve 22 is arranged at the outlet end of the vacuum pipeline 2, and a sealed space is formed in the vacuum pipeline 2 through the front valve 21 and the rear valve 22. When the carrier rocket 4 enters or leaves the vacuum tube 2, the valve at the corresponding end is opened or closed. The vacuum pipeline 2 is externally connected and provided with a vacuum pump 3, and the vacuum pump 3 is used for generating negative pressure for the vacuum pipeline 2.
As shown in fig. 4, a rail 6 is laid on the bottom side of the vacuum pipe 2 along the axial direction of the vacuum pipe 2, and the rail 6 is used for providing a path for the movement of the carrier rocket 4.
As shown in fig. 5, the carrier rocket 4 includes a space carrier rocket 43, an accelerating rocket 41 is connected to the tail end of the space carrier rocket 43, a ram booster rocket 42 is respectively disposed at the positions near the tail end of the space carrier rocket 43 on both sides of the space carrier rocket 43, and an air rudder 44 is respectively disposed at the positions near the front end of the space carrier rocket 43 on both sides of the space carrier rocket; a speed reducing wing 443 in a folded state is placed in the rudder 44, and the speed reducing wing 443 is connected with an unfolding and folding mechanism. The accelerating rocket 41 is operated in the vacuum tube 2 and is released from the space launch vehicle 43 after it exits the vacuum tube 2. The ram booster rocket 42 is in a working state in the atmosphere after the space carrier rocket 43 flies out of the vacuum pipeline 2.
The accelerating rocket 41 is used for accelerating the space carrier rocket 43 positioned in the vacuum pipeline 2 and separating the space carrier rocket 43 when the space carrier rocket 43 flies out of the vacuum pipeline 2; the ram booster rocket 42 is used for starting working after the space carrier rocket 43 flies out of the vacuum pipeline 2 and pushing the space carrier rocket 43 out of the atmosphere; the rudder 44 is used for changing the flight direction of the space launch vehicle 43, the rudder 44 is installed in front of the space launch vehicle 43, and the attitude of the rocket can be controlled by adjusting the angle. The expansion and contraction mechanism is used for expanding the deceleration wing 443 after the ram booster rocket 42 is disengaged. The space launch vehicle 43 may carry a payload, which is transported to a target location by its own control system and rocket power system, and the return of the launch vehicle 4 is also completed by the space launch vehicle 43.
In some embodiments, as shown in fig. 6 to 8, the deployment and retraction mechanism includes, on two sides of the space launch vehicle 43, a track groove 441 is provided, the track groove 441 is provided along the extending direction of the space launch vehicle 43, a screw rod 445 is installed in the track groove 441, and one end of the screw rod 445 is connected with a steering engine 444 for driving the screw rod to rotate; the unfolding side of the deceleration wing 443 is connected with a deceleration wing control rod 442, one end of the deceleration wing control rod 442 is connected to the screw 445, and the deceleration wing control rod 442 is used for reciprocally translating along the length direction of the screw 445 so as to unfold or fold the deceleration wing 443. The deceleration wing 443 is made of a soft foldable material, and in the initial state, the deceleration wing control lever 442 is folded in half, and after the deceleration wing 443 is folded to reduce the volume, the deceleration wing 443 is put into the air rudder 44 together.
The steering engine 444 and the screw 445 are both arranged in the track groove 441, the steering engine 444 drives the screw 445 to rotate, one end of the speed reducing wing control rod 442 is connected to the screw 445, and the speed reducing wing control rod 442 is perpendicular to the screw 445. Rotation of the lead screw 445 translates the deceleration wing control lever 442 along the orbital slot 441 from the rudder 44 toward the tail of the space launch vehicle 43, causing the deceleration wing 443 to deploy. In the initial state, the deceleration wings 443 and the deceleration wing control rods 442 are folded and then mounted in the air rudder 44, and after the space carrier rocket 43 returns to the atmosphere and decelerates, the main control system 1 controls the action of the expansion and contraction mechanism, so that the deceleration wing control rods 442 and the deceleration wings 443 are automatically opened, and the deceleration and posture adjustment of the space carrier rocket 43 can be realized.
In some embodiments, as shown in fig. 4, the cross section of the rail 6 is i-shaped, a guide rail 61 is nested above the rail 6, and the guide rail 61 is used for reciprocating along the rail 6. The guide rail 61 is connected with the space launch vehicle 43 through an electromagnetic pin 62, and the electromagnetic pin 62 is used for connecting and disconnecting the space launch vehicle 43 with the rail 6. The rail 6 is fixed in the vacuum pipeline 2, a guide rail 61 is arranged above the rail 6, and the guide rail 61 is used for moving along the constraint direction of the rail 6. While the carrier rocket 4 is mounted on the guide rail 61 by means of electromagnetic pins 62, the guide rail 61 carries the carrier rocket 4 along the rail 6 together in the vacuum tube 2.
In some embodiments, as shown in fig. 1, a combined power rocket vacuum high speed launch system further comprises a launch platform 5, said launch platform 5 being adapted to return to the ground landing site as said space launch vehicle 43, while the launch platform 5 may send a position signal to the returning space launch vehicle 43.
In some embodiments, the bottom of the vacuum pipe 2 is mounted on the ground by a bracket 7, the angle of the bracket 7 being adjustable.
The invention also provides a transmitting method of the combined power rocket vacuum high-speed transmitting system, which comprises the following steps: as shown in fig. 1, the master control system 1 is a control center of all launching systems, and the master control system 1 is in data connection with a vacuum pipeline 2, a vacuum pump 3, a carrier rocket 4 and a launching platform 5 and commands and controls all power work and work of other systems.
Firstly, combining a space carrier rocket 43, a ram rocket 42, an accelerating rocket 41 and an air rudder 44 together to complete the assembly work of the carrier rocket 4, then installing the carrier rocket 4 on a track 6 in a vacuum pipeline 2, and then closing valves at two ends of the vacuum pipeline 2.
And secondly, the master control system 1 controls the vacuum pump 3 to work so that the vacuum degree in the vacuum pipeline 2 reaches a target value.
Third, the master control system 1 controls the accelerating rocket 41 to start ignition, accelerates the space carrier rocket 43 to Mach 2-2.5, opens a valve at the outlet of the vacuum pipeline 2 when the space carrier rocket 43 reaches the tail end of the vacuum pipeline 2, and simultaneously opens the electromagnetic pin 62 to separate the space carrier rocket 43 from the guide rail 61, and the space carrier rocket 43 flies out of the vacuum pipeline 2.
Fourth, the accelerating rocket 41 is separated from the space carrier rocket 43, the direction and the gesture of the space carrier rocket 43 are adjusted by the air rudder 44, the ram rocket 42 starts to work, and after the space carrier rocket 43 is continuously pushed to fly outside the atmosphere, the ram rocket 42 is separated from the space carrier rocket 43.
And fifthly, the space carrier rocket 43 continuously flies to a target position, and returns to the launching platform 5 independently after the task is completed.
The invention also provides a recovery method of the combined power rocket vacuum high-speed launching system, which comprises the following steps: as shown in fig. 2, autonomous return of space launch vehicle 43 includes free-fall, rocket drag, flight, attitude-alignment, deceleration landing processes. Step one, implementing a free falling process: the space carrier rocket 43 freely falls into the atmosphere until the altitude is less than or equal to 30 km. Secondly, implementing a rocket braking process: and starting rocket braking to enable the space carrier rocket 43 to decelerate to be smaller than or equal to Mach 0.6-0.8, and opening the deceleration wing 443.
Thirdly, implementing a flying process; under the control of the rudder 44 and the deceleration wings 443, the space launch vehicle 43 continues to pitch and decelerate, and performs guided flight according to the signals received from the launch platform 5. Fourthly, implementing the gesture adjusting and speed reducing landing process: after the space carrier rocket 43 flies to the set height above the launching platform 5, the engine of the space carrier rocket 43 is started to decelerate again, and the space carrier rocket, the deceleration wing 443 and the air rudder 44 are adjusted to be in a vertical landing posture, and then gradually drops to the launching platform 5.
The pipeline launching mode adopted by the invention can efficiently and quickly increase the space carrier rocket to the designed target speed in the vacuum pipeline, even if the space carrier rocket realizes high initial speed on the ground, the rocket fuel is greatly saved, and the effective load ratio of the rocket is improved; the weight of the first-stage rocket can be saved, the rocket launching efficiency is greatly improved, and the launching cost is reduced. The ram boosting rocket is adopted in the accelerating rocket power atmosphere environment, so that the space carrier rocket can be continuously pushed to continuously fly without the oxidant, and the passive mass of rocket launching is further reduced. The space carrier rocket can change the flight direction by means of the air rudder, so that the vacuum pipeline can be constructed in more relief environments, and the launching geographic position is flexible; meanwhile, the flight direction, the gesture and the like of the space carrier rocket can be regulated and controlled, the automatic control capability of the space carrier rocket in the air is realized, and the space carrier rocket can conveniently fly in a safer airspace and a more accurate gesture. The invention adopts the emission mode of various power combinations, and can greatly expand the effective carrying capacity and application market of the emission mode by selecting or adjusting the performance design of related power.
When the space carrier rocket returns, the rocket engine is firstly adopted to ignite and reversely push and decelerate at the low-pressure high-altitude 30km, the low-pressure high-altitude rocket engine has higher efficiency and larger thrust, and more fuel is saved compared with the rocket engine which is restarted at the low-pressure high-altitude; in addition, the space carrier rocket can be controlled to fly to the upper part of the launching field through the air rudder and the speed reducing wings in the flying process in the atmosphere, and compared with the prior art that the space carrier rocket is pushed to fly to the position of the launching field through a rocket engine, fuel consumption is not needed. The space carrier rocket can directly return to the launching platform without additionally building a movable offshore launching platform and transporting the recovered ground for a long time, and has the characteristics of low recovery cost and high rocket reuse efficiency.
Claims (5)
1. The vacuum high-speed launching system of the combined power rocket is characterized by comprising a vacuum pipeline (2), wherein a vacuum pump (3) is arranged on the vacuum pipeline (2), and the vacuum pump (3) is used for generating negative pressure for the vacuum pipeline (2); the vacuum pipeline (2) is a hollow pipeline, and two ends of the vacuum pipeline (2) are respectively provided with an openable valve; a track (6) is paved at the bottom of the vacuum pipeline (2), and the track (6) is used for providing a path for the movement of the carrier rocket (4);
the carrier rocket (4) comprises a space carrier rocket (43), an accelerating rocket (41) is arranged at the tail end of the space carrier rocket (43), a stamping boosting rocket (42) is arranged at the positions, close to the tail end, of the two sides of the space carrier rocket (43), and an air rudder (44) is arranged at the positions, close to the front end, of the space carrier rocket (43); a speed reducing wing (443) in a folded state is arranged in the air rudder (44), and the speed reducing wing (443) is connected with an unfolding and shrinking mechanism;
the expansion and contraction mechanism includes: track grooves (441) are formed in two sides of the space carrier rocket (43), the track grooves (441) are formed along the extending direction of the space carrier rocket (43), a lead screw (445) is arranged in the track grooves (441), and one end of the lead screw (445) is connected with a steering engine (444) for driving the lead screw to rotate; the unfolding side of the deceleration wing (443) is connected with a deceleration wing control rod (442), one end of the deceleration wing control rod (442) is connected to the screw rod (445), and the deceleration wing control rod (442) is used for reciprocally translating along the length direction of the screw rod (445) so as to unfold or fold the deceleration wing (443);
the accelerating rocket (41) is used for accelerating the space carrier rocket (43) positioned in the vacuum pipeline (2) and separating from the space carrier rocket (43) when the space carrier rocket flies out of the vacuum pipeline (2); the stamping boosting rocket (42) is used for starting working after the space carrier rocket (43) flies out of the vacuum pipeline (2) and pushing the space carrier rocket (43) to fly out of the atmosphere; -said rudder (44) for changing the direction of flight of said space launch vehicle (43); the expansion and contraction mechanism is used for expanding the deceleration wing (443) after the ram booster rocket (42) is separated from the space carrier rocket (43).
2. A combined power rocket vacuum high-speed launching system according to claim 1, wherein the cross section of the rail (6) is i-shaped, a guiding rail (61) is mounted on the rail (6) Fang Qiantao, the guiding rail (61) is used for reciprocating along the rail (6), the guiding rail (61) is connected with the space launch vehicle (43) through an electromagnetic pin (62), and the electromagnetic pin (62) is used for connecting or separating the space launch vehicle (43) from the rail (6).
3. A combined power rocket vacuum high-speed launch system according to claim 2 and further comprising a launch platform (5), said launch platform (5) being adapted to return to ground landing as said space launch vehicle (43).
4. A method for launching a combined power rocket vacuum high-speed launching system, characterized in that the method is based on a combined power rocket vacuum high-speed launching system as claimed in claim 2, and comprises the following steps:
firstly, combining a space carrier rocket (43), a ram rocket (42), an accelerating rocket (41) and an air rudder (44) together to finish the assembly work of the carrier rocket (4), then installing the carrier rocket (4) on a track (6) in a vacuum pipeline (2), and then closing valves at two ends of the vacuum pipeline (2);
secondly, the master control system (1) controls the vacuum pump (3) to work so that the vacuum degree in the vacuum pipeline (2) reaches a target value;
thirdly, a master control system (1) controls the accelerating rocket (41) to start ignition work, accelerates the space carrier rocket (43) to Mach 2-2.5, opens a valve at the outlet of the vacuum pipeline (2) when the space carrier rocket (43) reaches the tail end of the vacuum pipeline (2), and simultaneously opens an electromagnetic pin (62) to separate the space carrier rocket (43) from the guide rail (61), and the space carrier rocket (43) flies out of the vacuum pipeline (2);
fourthly, the accelerating rocket (41) is separated from the space carrier rocket (43), the direction and the gesture of the space carrier rocket (43) are adjusted through the air rudder (44), the ram rocket (42) starts to work, and after the space carrier rocket (43) is continuously pushed to fly to the outside of the atmosphere, the ram rocket (42) is separated from the space carrier rocket (43);
and fifthly, continuously flying the space carrier rocket (43) to a target position, and returning the space carrier rocket to the launching platform (5) independently after completing the task.
5. A method for recycling a combined power rocket vacuum high-speed launching system, which is based on the combined power rocket vacuum high-speed launching system as claimed in claim 3, and comprises the following steps:
step one, implementing a free falling process: the space carrier rocket (43) freely falls into the atmosphere until the altitude is less than or equal to 30 km;
secondly, implementing a rocket braking process: starting rocket braking to enable the space carrier rocket (43) to decelerate to be smaller than or equal to Mach 0.6-0.8, and opening the deceleration wing (443);
thirdly, implementing a flying process; under the control of the air rudder (44) and the deceleration wings (443), the space carrier rocket (43) continues to adjust the pose and decelerate, and performs guided flight according to the signals received from the launching platform (5);
fourthly, implementing the gesture adjusting and speed reducing landing process: after the space carrier rocket (43) flies to the set height above the launching platform (5), the engine of the space carrier rocket (43) is started to decelerate again, and the space carrier rocket, the deceleration wing (443) and the air rudder (44) are adjusted to be in a vertical landing posture, and then gradually drops to the launching platform (5).
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| CN202210686241.0A CN114963867B (en) | 2022-06-16 | 2022-06-16 | Vacuum high-speed emission system of combined power rocket and emission and recovery method thereof |
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| CN202210686241.0A CN114963867B (en) | 2022-06-16 | 2022-06-16 | Vacuum high-speed emission system of combined power rocket and emission and recovery method thereof |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106500550A (en) * | 2016-12-15 | 2017-03-15 | 福州幻科机电科技有限公司 | Escape tower trouserss booster rocket with the remote control hang gliding tail vane wing |
| CN106871723A (en) * | 2017-02-07 | 2017-06-20 | 国网技术学院 | Rise pocket emission system and its launch assist method |
| CN110186326A (en) * | 2019-06-03 | 2019-08-30 | 深磁科技(深圳)有限公司 | A kind of recyclable emission system and method |
| CN111071492A (en) * | 2019-12-02 | 2020-04-28 | 燕山大学 | Rocket for recovering turbine brake by utilizing gas energy and recovery deceleration method thereof |
| US11041692B1 (en) * | 2020-05-12 | 2021-06-22 | Michael Chromych | System and method for launching and acceleration of objects |
| CN114001597A (en) * | 2021-11-05 | 2022-02-01 | 航天科工火箭技术有限公司 | Recyclable carrier rocket and working method |
-
2022
- 2022-06-16 CN CN202210686241.0A patent/CN114963867B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106500550A (en) * | 2016-12-15 | 2017-03-15 | 福州幻科机电科技有限公司 | Escape tower trouserss booster rocket with the remote control hang gliding tail vane wing |
| CN106871723A (en) * | 2017-02-07 | 2017-06-20 | 国网技术学院 | Rise pocket emission system and its launch assist method |
| CN110186326A (en) * | 2019-06-03 | 2019-08-30 | 深磁科技(深圳)有限公司 | A kind of recyclable emission system and method |
| CN111071492A (en) * | 2019-12-02 | 2020-04-28 | 燕山大学 | Rocket for recovering turbine brake by utilizing gas energy and recovery deceleration method thereof |
| US11041692B1 (en) * | 2020-05-12 | 2021-06-22 | Michael Chromych | System and method for launching and acceleration of objects |
| CN114001597A (en) * | 2021-11-05 | 2022-02-01 | 航天科工火箭技术有限公司 | Recyclable carrier rocket and working method |
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