CN114963867A - Vacuum high-speed launching system of combined power rocket and launching and recovering method thereof - Google Patents
Vacuum high-speed launching system of combined power rocket and launching and recovering method thereof Download PDFInfo
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- 235000012633 Iberis amara Nutrition 0.000 claims abstract description 9
- 230000001133 acceleration Effects 0.000 claims description 16
- 239000000446 fuel Substances 0.000 abstract description 7
- 238000011084 recovery Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
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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
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Abstract
The invention discloses a combined power rocket vacuum high-speed launching system and a launching and recovering 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; the bottom of the vacuum pipeline is laid with a track which is used for providing a path for the motion of the carrier rocket; the space carrier rocket comprises a space carrier rocket, the tail end of the space carrier rocket is connected with an accelerating rocket, two stamping boosting rockets are 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 two sides of the space carrier rocket; the air rudder is internally provided with a reduction wing in a folded state, and the reduction wing is connected with an unfolding and contracting mechanism. The method solves the problems that in the existing rocket launching method, the effective load of the rocket is small, the cost is high, and the fuel consumption is high in the rocket recovery method.
Description
Technical Field
The invention belongs to the technical field of rocket launching, and particularly relates to a combined power rocket vacuum high-speed launching system and launching and recovering methods thereof.
Background
In recent years, with the rapid development of small satellite technology and rocket technology, small carrier rockets are pushed to large stages for space launching. In the future, a small carrier rocket capable of realizing rapid and effective space launching has great value and will become a sunday star for people to carry out space activities. At present, the launching methods of small-sized carrier rockets are more, the carrier rockets are accelerated from the ground or the sea surface from zero through the self power of the rockets, the carrier rockets fly out of the atmosphere in a path as short as possible, and then the rocket is continuously made to fly into a target orbit by a later stage rocket. The launching method needs the first stage rocket to be very large, the mass of the first stage rocket usually accounts for about half of the total mass, the effective load ratio of the rocket is small, and the cost is high.
In addition, the conventional rocket return recovery successfully realizes the spacex vertical recovery, and has two forms, wherein the first form is that the rocket is driven by a rocket engine from the track to return to land to the original launching site, and the mode consumes about 27% of the take-off carried fuel; the other mode is that the rocket directly falls to the sea surface from the orbit position, the return mode only consumes less than 10% of fuel, but a movable offshore recovery platform needs to be additionally built, the cost is high, and meanwhile, the time for returning the recovered rocket to the rocket launching site is several days, so that the recycling efficiency of the rocket is influenced.
Disclosure of Invention
The invention aims to provide a combined power rocket vacuum high-speed launching system and a launching and recovering method thereof, and aims to solve the problems that in the existing rocket launching method, the effective load of a rocket is small, the cost is high, and the fuel consumption is high in the existing rocket recovering method.
The invention adopts the following technical scheme: a vacuum high-speed launching system of a combined power rocket comprises a vacuum pipeline, wherein a vacuum pump is arranged on the vacuum pipeline and is used for generating negative pressure to 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 used for providing a path for the motion of the carrier rocket;
the space carrier rocket comprises a space carrier rocket, the tail end of the space carrier rocket is connected with an accelerating rocket, punching boosting rockets are respectively arranged at the positions, close to the tail end, of two sides of the space carrier rocket, and air rudders are respectively arranged at the positions, close to the front end, of two sides of the space carrier rocket; a folded speed reduction wing is arranged in the air rudder and is connected with an unfolding and folding mechanism;
the acceleration rocket is used for accelerating the space launch vehicle positioned in the vacuum pipeline and separating from the space launch vehicle when the space launch vehicle flies out of the vacuum pipeline; the stamping boosting rocket is used for starting to work after the space launch vehicle flies out of the vacuum pipeline and pushing the space launch vehicle to fly out of the atmosphere; the air rudder is used for changing the flight direction of the space launch vehicle; and the unfolding and folding mechanism is used for unfolding the decelerating wings after the stamping boosting rocket is separated from the space carrier rocket.
Further, the unfolding and folding mechanism comprises: track grooves are formed in two sides of the space launch vehicle, the track grooves are formed in 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 used for driving the lead screw to rotate; the unfolding side of the decelerating wing is connected with a decelerating wing control rod, one end of the decelerating wing control rod is connected to the screw rod, and the decelerating wing control rod is used for performing reciprocating translation along the length direction of the screw rod so as to unfold or fold the decelerating wing.
Furthermore, the cross section of the track is I-shaped, a guide track is nested above the track and used for moving back and forth along the track, the guide track 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 and the track.
Furthermore, the space launch vehicle also comprises a launching platform which is used as a site for returning the space launch vehicle to the landing ground.
The invention adopts a second technical scheme that a launching method of a combined power rocket vacuum high-speed launching system is based on the combined power rocket vacuum high-speed launching system and comprises the following contents:
firstly, combining a space launch vehicle, a ram rocket, an acceleration rocket and an air rudder together to finish the assembly work of the launch vehicle, then installing the launch vehicle on a track in the 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 general control system controls the acceleration rocket to start ignition work, accelerates the space carrier rocket to Mach 2-2.5, opens a valve at an outlet of a vacuum pipeline when the space carrier rocket reaches the tail end of the vacuum pipeline, and opens an electromagnetic pin at the same time so as to separate the space carrier rocket from the guide track, and the space carrier rocket flies out of the vacuum pipeline;
fourthly, the acceleration rocket is separated from the space carrier rocket, the direction and the posture of the space carrier rocket are adjusted through the air rudder, the ram rocket starts to work, and the ram rocket is separated from the space carrier rocket after the space carrier rocket is continuously pushed to fly to be close to the atmosphere;
and fifthly, the space launch vehicle continuously flies to a target position, and automatically returns to the launching platform after the mission is finished.
The second technical scheme adopted by the invention is that a recovery method of a combined power rocket vacuum high-speed launching system is based on the combined power rocket vacuum high-speed launching system and comprises the following contents:
the first step, the free fall process is implemented: the space launch vehicle freely falls into the atmosphere until the altitude is less than or equal to 30 km;
step two, implementing a rocket braking process: starting rocket braking to enable the space carrier rocket to be decelerated to Mach 0.6-0.8 or less, and then opening the decelerating wings;
thirdly, implementing a flight process; under the control of the air rudder and the decelerating wings, the space launch vehicle continues to adjust the attitude and decelerate and carries out guided flight according to the signals received from the launching platform;
fourthly, implementing a posture-adjusting, speed-reducing and landing process: after the space launch vehicle flies to a set height above the launching platform, the engine of the space launch vehicle starts to decelerate again, adjusts the posture of the engine together with the decelerating wings and the air rudder into a vertical landing posture, and then gradually lands on the launching platform.
The invention has the beneficial effects that: the space launch vehicle can be efficiently increased to the designed target speed in a short time in the vacuum pipeline by adopting a pipeline launching mode, so that the space launch vehicle can realize high initial speed on the ground, rocket fuel is greatly saved, and the effective load ratio of the rocket is increased; the weight of a first-stage rocket can be saved, the rocket launching efficiency is greatly improved, and the launching cost is reduced. The stamping boosting rocket is adopted in the accelerating rocket power atmospheric environment, so that the space carrier rocket can be continuously pushed to continuously fly without an oxidant, and the negative mass of rocket launching is further reduced. Meanwhile, the flight direction of the space launch vehicle can be changed by means of the air rudder, so that the vacuum pipeline can be built in more terrain environments, and the launching geographic position is flexible; the air rudder can regulate and control the flight direction, the attitude 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 ignite and fly in a safer airspace and a more accurate attitude. The invention adopts a launching mode of combining various powers, and can greatly expand the effective carrying capacity and application market of the launching mode by selecting or adjusting the performance design of the related power. In addition, the rocket return mode adopted by the invention reduces the fuel consumption to be within 7 percent, and the recycling and reusing efficiency is higher.
Drawings
FIG. 1 is a schematic diagram of a vacuum high-speed launching system of a combined power rocket and launching and recovering methods thereof;
FIG. 2 is a schematic view of a control flow of a return system of a combined power rocket vacuum high-speed launching system and launching and recovering methods thereof according to the present invention;
FIG. 3 is a schematic structural diagram of a vacuum high-speed launching system of a combined power rocket according to the present invention;
FIG. 4 is a schematic cross-sectional view of a track assembly of a combined power rocket vacuum high-speed launching system according to the present invention;
FIG. 5 is a schematic view of a launch vehicle incorporating a power rocket vacuum high-speed launching system according to the present invention;
FIG. 6 is a schematic view of a space launch vehicle of a combined power rocket vacuum high-speed launching system according to the present invention;
FIG. 7 is an enlarged schematic view of the orbital slot of a vacuum high-speed launching system of a combined power rocket according to the present invention;
FIG. 8 is a schematic diagram of the deceleration span opening state of the vacuum high-speed launching system of a combined power rocket.
The system comprises a general control system 1, a vacuum pipeline 2, a front valve 21, a rear valve 22, a vacuum pump 3, a launch vehicle 4, an acceleration vehicle 41, a ram boosting vehicle 42, a space launch vehicle 43, an air vane 44, an orbit groove 441, a deceleration wing control rod 442, a deceleration wing 443, a steering engine 444, a lead screw 445, a launching platform 5, an orbit 6, a guide orbit 61, an electromagnetic pin 62 and a support 7.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention provides a vacuum high-speed launching system of a combined power rocket, which comprises a vacuum pipeline 2 as shown in figure 3, wherein the vacuum pipeline 2 is built at 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 pipe 2, the valve at the corresponding end is opened or closed. The vacuum pipeline 2 is externally connected 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 track 6 is laid on the inner bottom side of the vacuum pipe 2 along the axial direction of the vacuum pipe 2, and the track 6 is used for providing a path for the movement of the carrier rocket 4.
As shown in fig. 5, the space rocket 4 includes a space rocket 43, the tail end of the space rocket 43 is connected with an acceleration rocket 41, two stamping booster rockets 42 are respectively arranged at two sides of the space rocket 43 near the tail end, and two air rudders 44 are respectively arranged at two sides of the space rocket 43 near the front end; a decelerating wing 443 in a folded state is placed in the air rudder 44, and the decelerating wing 443 is connected with an unfolding and folding mechanism. The acceleration rocket 41 is operated in the vacuum tube 2 and is detached from the space launch vehicle 43 after it has flown out of the vacuum tube 2. The ram-boosted rocket 42 is in working state in the atmosphere after the space carrier rocket 43 flies out of the vacuum pipeline 2.
The acceleration rocket 41 is used for accelerating the space launch vehicle 43 positioned in the vacuum pipe 2 and separating from the space launch vehicle 43 when the space launch vehicle 43 flies out of the vacuum pipe 2; the stamping booster rocket 42 is used for starting to work after the space launch vehicle 43 flies out of the vacuum pipeline 2 and pushing the space launch vehicle 43 out of the atmosphere; the air rudder 44 is used for changing the flight direction of the space launch vehicle 43, and the air rudder 44 is installed in front of the space launch vehicle 43 and can control the rocket attitude by adjusting the angle. The deployment and retraction mechanism is used to deploy the deceleration wings 443 after the ram-assisted rocket 42 is disengaged. The space launch vehicle 43 carries the payload to the target location via its own control system and rocket power system, and the return of the launch vehicle 4 is accomplished by this space launch vehicle 43.
In some embodiments, as shown in fig. 6 to 8, the unfolding and folding mechanism includes track grooves 441 disposed on two sides of the space launch vehicle 43, the track grooves 441 are disposed along the extending direction of the space launch vehicle 43, a lead screw 445 is installed 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 445 to rotate; a decelerating wing control rod 442 is connected to the deploying side of the decelerating wing 443, one end of the decelerating wing control rod 442 is connected to the lead screw 445, and the decelerating wing control rod 442 is used for reciprocating translation along the length direction of the lead screw 445 to deploy or retract the decelerating wing 443. The decelerating wing 443 is made of a soft foldable material, and in an initial state, the decelerating wing control rod 442 is folded in half, and after the decelerating wing 443 is folded to reduce its volume, the decelerating wing 443 is placed in the air vane 44.
The steering gear 444 and the lead screw 445 are installed in the track groove 441, the steering gear 444 drives the lead screw 445 to rotate, one end of the speed reduction wing control rod 442 is connected to the lead screw 445, and the speed reduction wing control rod 442 is perpendicular to the lead screw 445. Rotation of the lead screw 445 translates the deceleration wing control rod 442 along the track slot 441 from the air rudder 44 towards the tail of the space launch vehicle 43, causing the deceleration wing 443 to deploy. In the initial state, the decelerating wings 443 and the decelerating wing control rods 442 are folded and installed inside the air rudder 44, and after the space launch vehicle 43 returns to the atmosphere and decelerates, the main control system 1 controls the unfolding and folding mechanisms to act, so that the decelerating wing control rods 442 and the decelerating wings 443 are automatically opened, and the deceleration and posture adjustment of the space launch vehicle 43 can be realized.
In some embodiments, as shown in fig. 4, the rail 6 has an i-shaped cross section, and a guide rail 61 is nested above the rail 6, and the guide rail 61 is configured to reciprocate along the rail 6. The guide rail 61 is connected to the space launch vehicle 43 by an electromagnetic pin 62, and the electromagnetic pin 62 is used for connecting and disconnecting the space launch vehicle 43 to and from the rail 6. The rail 6 is fixed in the vacuum pipeline 2, and 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. And the carrier rocket 4 is mounted on the guide rail 61 by the electromagnetic pin 62, the guide rail 61 carries the carrier rocket 4 in the vacuum tube 2 to be movable together along the rail 6.
In some embodiments, as shown in FIG. 1, a combined power rocket vacuum high-speed launching system further comprises a launch platform 5, wherein the launch platform 5 is used as a site for returning the space launch vehicle 43 to the landing ground, and the launch platform 5 can 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, and the angle of the bracket 7 is adjustable.
The invention also provides a launching method of the combined power rocket vacuum high-speed launching 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 launch vehicle 4 and a launching platform 5, and commands and controls all power operations and operations of other systems.
Firstly, combining a space launch vehicle 43, a ram rocket 42, an acceleration rocket 41 and an air rudder 44 together to finish the assembly work of the launch vehicle 4, then installing the launch vehicle 4 on a track 6 in the vacuum pipeline 2, and 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.
Thirdly, the general control system 1 controls the acceleration 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 the electromagnetic pin 62 to separate the space carrier rocket 43 from the guide track 61, so that the space carrier rocket 43 flies out of the vacuum pipeline 2.
Fourthly, the acceleration rocket 41 is separated from the space carrier rocket 43, the direction and the posture 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, the space launch vehicle 43 continuously flies to the target position, and automatically returns to the launching platform 5 after the mission is finished.
The invention also provides a recovery method of the vacuum high-speed launching system of the combined power rocket, which comprises the following steps: as shown in FIG. 2, the autonomous return of the space launch vehicle 43 includes free-fall, rocket braking, flight, attitude-adjusting, deceleration, and landing processes. The first step, the free fall process is implemented: the space launch vehicle 43 freely falls into the atmosphere until the altitude is less than or equal to 30 km. Step two, implementing a rocket braking process: starting rocket braking to decelerate the space carrier rocket 43 to be less than or equal to Mach 0.6-0.8, and then opening the decelerating wings 443.
Thirdly, implementing a flight process; under the control of the air rudder 44 and the deceleration wings 443, the space launch vehicle 43 continues to adjust attitude and decelerate and to direct flight in accordance with the signals received from the launch platform 5. Fourthly, implementing a posture-adjusting, speed-reducing and landing process: after the space launch vehicle 43 flies to a set height above the launching platform 5, the engine of the space launch vehicle 43 is started again to decelerate, and the attitude of the engine, the deceleration wings 443 and the air rudder 44 are adjusted to be a vertical landing attitude, and then the engine gradually lands on the launching platform 5.
The space launch vehicle can be efficiently increased to the designed target speed in a short time in the vacuum pipeline by adopting a pipeline launching mode, so that the space launch vehicle can realize high initial speed on the ground, rocket fuel is greatly saved, and the effective load ratio of the rocket is increased; the weight of a first-stage rocket can be saved, the rocket launching efficiency is greatly improved, and the launching cost is reduced. The stamping boosting rocket is adopted in the accelerating rocket power atmospheric environment, so that the space carrier rocket can be continuously pushed to continuously fly without an oxidant, and the negative mass of rocket launching is further reduced. The flight direction of the space launch vehicle can be changed by means of the air rudder, so that the vacuum pipeline can be built in more terrain environments, and the launching geographic position is flexible; meanwhile, the flight direction, the attitude and the like of the space carrier rocket can be regulated and controlled, the self-control capability of the space carrier rocket in the air is realized, and the space carrier rocket can conveniently ignite and fly in a safer airspace and a more accurate attitude. The invention adopts a launching mode of combining various powers, and can greatly expand the effective carrying capacity and application market of the launching mode by selecting or adjusting the performance design of the related power.
When the space carrier rocket returns, the rocket engine is adopted to ignite and reversely push to decelerate at the low-pressure high altitude of 30km, the low-pressure high altitude rocket engine has higher efficiency and larger thrust, and more fuel is saved compared with the low-pressure high-pressure deceleration; in addition, the space launch vehicle can be controlled to fly to the sky above a launching site through the air rudder and the decelerating wings in the process of flying in the atmosphere, and compared with the prior art that the space launch vehicle is propelled to fly to the position of the launching site through a rocket engine, fuel does not need to be consumed. The space launch vehicle can directly return to the launching platform without additionally building a movable marine 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 (6)
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 laid 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 space launch vehicle (4) comprises a space launch vehicle (43), the tail end of the space launch vehicle (43) is connected with an acceleration rocket (41), two stamping boosting rockets (42) are respectively arranged at the positions, close to the tail end, of the two sides of the space launch vehicle (43), and air rudders (44) are respectively arranged at the positions, close to the front end, of the two sides of the space launch vehicle (43); a folded decelerating wing (443) is arranged in the air rudder (44), and the decelerating wing (443) is connected with an unfolding and folding mechanism;
-said acceleration rocket (41) for accelerating said space launch vehicle (43) located inside said vacuum tube (2) and disengaging said space launch vehicle (43) when it flies out of said vacuum tube (2); the stamping booster rocket (42) is used for starting to work after the space launch vehicle (43) flies out of the vacuum pipeline (2) and pushing the space launch vehicle (43) to fly out of the atmosphere; -said air rudder (44) for changing the flight direction of said space launch vehicle (43); the unfolding and folding mechanism is used for unfolding the decelerating wing (443) after the ram-propelled rocket (42) is separated from the space launch vehicle (43).
2. A combination power rocket vacuum high speed launching system according to claim 1, wherein said deployment and retraction mechanism comprises: track grooves (441) are formed in two sides of the space launch vehicle (43), the track grooves (441) are arranged along the extending direction of the space launch vehicle (43), a lead screw (445) is installed 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; a decelerating wing control rod (442) is connected to the unfolding side of the decelerating wing (443), one end of the decelerating wing control rod (442) is connected to the lead screw (445), and the decelerating wing control rod (442) is used for reciprocating and translating along the length direction of the lead screw (445) so as to unfold or fold the decelerating wing (443).
3. A combined power rocket vacuum high-speed launching system as described in claim 1 or 2, characterized in that the cross section of said orbit (6) is i-shaped, a guiding orbit (61) is nested above said orbit (6), said guiding orbit (61) is used for reciprocating along said orbit (6), said guiding orbit (61) is connected with said space launch vehicle (43) through an electromagnetic pin (62), said electromagnetic pin (62) is used for connecting or separating said space launch vehicle (43) with the orbit (6).
4. A combination power rocket vacuum high-speed launching system according to claim 3, further comprising a launching platform (5), said launching platform (5) being adapted to return to the landing site as said space launch vehicle (43).
5. A launching method of 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 any one of claims 1-4, and comprises the following contents:
firstly, combining a space launch vehicle (43), a ram rocket (42), an acceleration rocket (41) and an air rudder (44) together to finish the assembly work of the launch vehicle (4), then installing the launch vehicle (4) on a track (6) in the 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, the general control system (1) controls the acceleration rocket (41) to start ignition work, accelerates the space launch vehicle (43) to Mach 2-2.5, when the space launch vehicle (43) reaches the end of the vacuum pipeline (2), opens a valve at the outlet of the vacuum pipeline (2) and opens an electromagnetic pin (62) at the same time, so that the space launch vehicle (43) is separated from the guide track (61), and the space launch vehicle (43) flies out of the vacuum pipeline (2);
fourthly, the acceleration rocket (41) is separated from the space launch vehicle (43), the direction and the posture of the space launch vehicle (43) are adjusted through the air rudder (44), the ram rocket (42) starts to work, and after the space launch vehicle (43) is continuously pushed to fly to be close to the atmosphere, the ram rocket (42) is separated from the space launch vehicle (43);
and fifthly, the space launch vehicle (43) continuously flies to the target position, and automatically returns to the launching platform (5) after the mission is finished.
6. A method for recovering a vacuum high-speed launching system of a combined power rocket, which is based on the vacuum high-speed launching system of the combined power rocket as claimed in any one of claims 1 to 4, and comprises the following steps:
the first step, implementing a free fall process: the space launch vehicle (43) freely falls into the atmosphere until the altitude is less than or equal to 30 km;
step two, implementing a rocket braking process: starting rocket braking to enable the space launch vehicle (43) to decelerate to be less than or equal to Mach 0.6-0.8, and then opening the decelerating wings (443);
thirdly, implementing a flight process; under the control of the air rudder (44) and the decelerating wings (443), the space launch vehicle (43) continues to adjust the attitude and decelerate and to make a guided flight according to the signals received from the launching platform (5);
fourthly, implementing a posture-adjusting, speed-reducing and landing process: after the space launch vehicle (43) flies to the set height above the launching platform (5), the engine of the space launch vehicle (43) is started again to decelerate, and the attitude of the engine, the decelerating wings (443) and the air rudder (44) are adjusted to be a vertical landing attitude, and then the engine gradually lands on the launching platform (5).
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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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| CN114963867B (en) | 2023-12-29 |
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