CN113428382B - Laser aircraft launching system and method with relay satellite - Google Patents

Laser aircraft launching system and method with relay satellite Download PDF

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CN113428382B
CN113428382B CN202110709704.6A CN202110709704A CN113428382B CN 113428382 B CN113428382 B CN 113428382B CN 202110709704 A CN202110709704 A CN 202110709704A CN 113428382 B CN113428382 B CN 113428382B
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laser
aircraft
relay satellite
relay
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CN113428382A (en
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朱浩
王鹏程
李志�
汪小卫
张雪梅
蔡国飙
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Beihang University
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/002—Launch systems
    • B64G1/005—Air launch
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Optical Communication System (AREA)

Abstract

The invention provides a laser aircraft launching system with a relay satellite and a method thereof, wherein the laser aircraft launching system comprises a foundation laser station and a laser aircraft; further comprising: the relay satellite carries a relay mirror; the ground-based laser station is used for providing laser beams for the laser aircrafts; the ground-based laser station is also used for transmitting the laser beam to the relay satellite; and the relay satellite is used for transmitting the laser beam to the laser aircraft in the horizontal acceleration stage after shaping and repositioning the laser beam by using the relay lens. The invention solves the technical problem that the laser cannot be received due to overlarge laser incidence angle in the prior art.

Description

Laser aircraft launching system and method with relay satellite
Technical Field
The invention relates to the technical field of laser aircrafts, in particular to a laser aircraft launching system with a relay satellite and a laser aircraft launching method.
Background
Laser propulsion is a novel aircraft propulsion technology, and can utilize a laser beam emitted by a foundation laser station as a power source, so that the laser aircraft generates thrust to complete an on-track launching task. The laser aircraft launching scheme relates to the multidisciplinary design of structure, power, trajectory and the like.
The structure of the existing laser aircraft mostly adopts a Myrabo light boat structure; the power mainly uses an air suction working mode and a rocket working mode; the traditional laser aircraft has a straight line trajectory and a curved trajectory, and the trajectory is vertically launched to the height of the rail and then horizontally accelerated to the height of the rail, and the trajectory is gradually launched to turn vertically and horizontally accelerated to the height of the rail. The laser incident angle generated by the two ballistic launching schemes in the flying process is too large, namely the included angle between the laser beam and the axis of the laser aircraft is too large, so that the laser receiving device of the laser aircraft is required to have a rotating function, and the requirement on the aircraft structure is too high. In the traditional linear trajectory and curve trajectory launching scheme, only one foundation laser station provides a light source, and the problem of the laser incidence angle even causes the situation that the aircraft cannot receive laser due to an overlarge included angle, so that the launching task fails.
Disclosure of Invention
In view of the above, the present invention provides a laser aircraft launching system and method with a relay satellite, so as to alleviate the technical problem that the laser cannot be received due to an excessively large laser incidence angle in the prior art.
In a first aspect, an embodiment of the present invention provides a laser aircraft launching system with a relay satellite, including a ground-based laser station and a laser aircraft; further comprising: a relay satellite carrying relay lenses; the ground-based laser station is used for providing laser beams for the laser aircraft; the ground-based laser station is further used for transmitting the laser beam to the relay satellite; and the relay satellite is used for transmitting the laser beam to the laser aircraft in a horizontal acceleration stage after the laser beam is shaped and repositioned by using the relay mirror.
Further, the laser aircraft is in a Myrabo light boat configuration.
Further, the system further comprises: an emission point; the launching point is the starting point of the launching process of the laser aircraft.
Further, the orbital altitude of the relay satellite is consistent with the in-orbit altitude of the laser vehicle.
Further, before the laser aircraft is in a horizontal acceleration stage, an included angle between a connecting line of the relay satellite and the geocenter and a connecting line of the laser aircraft and the geocenter is set to be pi/50.
In a second aspect, the embodiment of the invention further provides a laser aircraft launching method with a relay satellite, which is applied to a laser aircraft launching system; the laser aircraft launching system comprises: a ground based laser station and a relay satellite; the relay satellite carries a relay lens; the method comprises the following steps: setting the working mode of the laser aircraft to be an air suction mode, and providing laser beams for the laser aircraft by the foundation laser station so that the laser aircraft flies to a first height from an emission point in an accelerating manner at a preset pitch angle; setting the working mode of the laser aircraft to be a rocket mode, and continuing to provide laser beams for the laser aircraft by the foundation laser station so as to enable the laser aircraft to continue to accelerate from the first height for a first preset time; suspending the laser beam provided by the foundation laser station so that the laser aircraft glides by inertia for a second preset time; transmitting the laser beam transmitted to the relay satellite by the ground-based laser station to the laser aircraft after being relocated by the relay mirror so as to enable the laser aircraft to accelerate and fly to a second height in the horizontal direction; the second height is the in-orbit height of the laser aircraft.
Further, the laser incidence angle of the laser beam to the laser aircraft is zero.
Further, the laser vehicle comprises a fairing; and in the acceleration process after the laser aircraft is switched to the rocket mode, the fairing is thrown away.
In a third aspect, an embodiment of the present invention further provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, where the processor implements the steps of the method according to the second aspect when executing the computer program.
In a fourth aspect, the present invention further provides a computer-readable medium having a non-volatile program code executable by a processor, where the program code causes the processor to execute the method of the second aspect.
The invention provides a laser aircraft launching system with a relay satellite and a method, wherein the laser aircraft launching system comprises a foundation laser station and a laser aircraft; further comprising: and the relay satellite carries a relay lens. According to the embodiment of the invention, the relay satellite is added in the transmitting process, so that the laser beam can be shaped and repositioned, the laser incidence angle is zero in the flying process, the laser aircraft receiving device is not required to have a rotating function, and the technical problem that the laser cannot be received due to the overlarge laser incidence angle in the prior art is solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic diagram of a laser aircraft launching system with a relay satellite according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a laser vehicle in the configuration of a Myrabo lightboat provided by an embodiment of the present invention;
fig. 3 is a flowchart of a laser aircraft launching method with a relay satellite according to an embodiment of the present invention;
FIG. 4 is a diagram illustrating a conventional straight ballistic launch scheme and a curved ballistic launch scheme in accordance with an embodiment of the present invention;
fig. 5 is a schematic diagram of another conventional straight ballistic launching scheme and a curved ballistic launching scheme according to an embodiment of the present invention.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. 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.
The first embodiment is as follows:
fig. 1 is a schematic diagram of a laser aircraft launching system with a relay satellite according to an embodiment of the invention. As shown in fig. 1, the launching system includes a laser vehicle 10, a ground-based laser station 20, and a relay satellite 30. Wherein the relay satellite 30 carries a relay mirror.
It should be noted that the launching system of fig. 1 further includes a laser beam 40 and a ballistic trajectory 50 of the laser vehicle 10.
Specifically, a ground based laser station 20 for providing a laser beam 40 to the laser vehicle 10.
And a ground based laser station 20 for transmitting a laser beam 40 to the relay satellite 30.
And a relay satellite 30 for transmitting the laser beam 40 to the laser vehicle 10 in the horizontal acceleration phase after shaping and repositioning the laser beam 40 using relay mirrors.
The invention provides a laser aircraft launching system with a relay satellite, which can reshape and relocate a laser beam by adding the relay satellite in the launching process, realizes that the laser incidence angle is zero in the flight process and a laser aircraft receiving device is not required to have a rotating function, and relieves the technical problem that the laser can not be received due to overlarge laser incidence angle in the prior art.
Preferably, the laser vehicle 10 in the present embodiment is of the Myrabo lightboat configuration. Fig. 2 is a schematic diagram of a laser aircraft in a Myrabo lightboat configuration provided by an embodiment of the invention. As shown in fig. 2, the external structure of the laser aircraft 10 includes: the thrust direction generated by the fairing 101, the annular sheath 102, the annular nozzle 103 and the parabolic reflector 104 is along the axis direction of the light boat.
As shown in fig. 2, the internal structure of the laser aircraft 10 provided by the embodiment of the present invention includes: a payload 105, a tank 106 containing rocket mode working fluid, a gas cylinder 107 containing pressurized helium gas, and electronics and attitude control devices. Where payload 105 is a microsatellite. Initial mass m of laser vehicle 10 0 Comprising a payload mass m pl Mass m of propellant p Structural mass m s And cowl mass m r 。
The laser aircraft is propelled by pulse laser, laser beams are provided by a foundation laser station, and the working modes include an air suction mode and a rocket mode. In the air suction working mode, detonation waves generated by laser breakdown gas are utilized to generate thrust; the working mode of the rocket utilizes the working medium carried by the laser ablation aircraft to generate thrust. The laser propulsion technology does not need to carry fuel under the air suction working mode, but obtains working media from the surrounding environment of the aircraft to generate thrust after the action of laser beams, thereby improving the propulsion efficiency and reducing the launching cost. In the embodiment of the invention, water is selected as an ablation working medium. Through simulation optimization design, the load ratio of the launching scheme of the laser aircraft with the relay mirror at the target orbit height of 200km reaches 0.0635, and is remarkably improved compared with the traditional chemical propulsion launching scheme.
Optionally, the system provided in the embodiment of the present invention further includes: an emission point; the launching point is the starting point of the launching process of the laser aircraft. Preferably, the emission point in an embodiment of the present invention is selected to have an altitude of 3.65km to minimize the effects of the atmosphere at ground altitude.
In the embodiment of the present invention, the relay satellite 30 with the relay mirror has a shaping and repositioning function for the laser beam 40 emitted from the ground-based laser station 20, and the orbital height of the relay satellite 30 is consistent with the in-orbit height of the laser vehicle 10. Before the laser aircraft 10 is in a horizontal acceleration stage, an included angle between a connecting line of the relay satellite 30 and the earth center and an included angle between a connecting line of the laser aircraft 10 and the earth center are set to be pi/50, so that interference between the laser aircraft 10 and a track of the relay satellite 30 in the flight process is prevented.
The embodiment of the invention provides a laser aircraft launching system with a relay satellite, which adopts a Myrabo light boat configuration, and provides power for a laser aircraft by adjusting a laser beam by using the relay satellite with the same orbit height and a relay mirror system based on two working modes of laser propulsion inspiration and rocket, so that the laser aircraft enters an orbit at a low orbit. The system effectively solves the problem of laser beam visibility caused by overlarge laser incidence angle and overlarge horizontal flying distance in the flying process; after simulation design, compared with the traditional launching scheme, the energy utilization rate is higher, and the carrying capacity is obviously improved.
The second embodiment:
FIG. 3 is a flowchart of a laser aircraft launching method with a relay satellite according to an embodiment of the invention, the method being applied to a laser aircraft launching system; wherein, laser aircraft transmitting system includes: a ground based laser station and a relay satellite; the relay satellite carries relay lenses. As shown in fig. 3, the method specifically includes the following steps:
and S302, setting the working mode of the laser aircraft to be an air suction mode, and providing laser beams for the laser aircraft by the foundation laser station so that the laser aircraft can accelerate from the emission point to a first height at a preset pitch angle. Wherein the laser incident angle of the laser beam to the laser aircraft is zero; the first height is the operating mode switch point height.
And S304, setting the working mode of the laser aircraft to be a rocket mode, and continuously providing laser beams for the laser aircraft by the foundation laser station so as to enable the laser aircraft to continuously accelerate from the first height for a first preset time.
In an embodiment of the invention, the laser vehicle comprises a fairing; the laser vehicle, during acceleration after switching to rocket mode, throws away the fairing.
And S306, suspending the laser beam provided by the foundation laser station so that the laser aircraft can coast for a second preset time.
Step S308, transmitting the laser beam transmitted to the relay satellite by the foundation laser station to the laser aircraft after being relocated by the relay lens so as to enable the laser aircraft to accelerate and fly to a second height in the horizontal direction; the second height is the staging height of the laser aircraft.
The invention provides a laser aircraft launching method with a relay satellite, which can reshape and relocate a laser beam by adding the relay satellite in the launching process, realizes that the laser incidence angle is zero in the flight process without a rotation function of a laser aircraft receiving device, and relieves the technical problem that the laser cannot be received due to overlarge laser incidence angle in the prior art. Meanwhile, a thrust-free sliding stage is added in the launching process, the speed of the laser aircraft in the vertical direction can be effectively reduced in the stage, conditions are provided for final rail entering, and the utilization rate of energy is improved.
In the embodiment of the invention, the launching process of the laser aircraft with the relay satellite can be divided into four stages, which are respectively as follows: an air-breathing mode accelerating section, a rocket mode accelerating section, a thrust-free gliding section and a horizontal accelerating section.
Specifically, the suction mode acceleration section: the emission point was chosen to be 3.65km in altitude to minimize the impact of the atmosphere at low altitude. Initial pitch angle at launch
Figure BDA0003133041190000071
And the laser frequency coefficient c is determined by an optimization result, the working mode of the laser aircraft at the stage is an air suction mode, and real-time thrust is calculated according to the flying height and the Mach number. The laser beam is directly provided by a foundation laser station, the pitch angle
Figure BDA0003133041190000072
Gradually reducing to ensure that the laser incident angle is zero until the flying height of the laser aircraft reaches the height H of the switching point of the working mode 1 This phase is over;
rocket mode acceleration segment: to a height H 1 And then, the working mode of the laser aircraft is switched to a rocket mode to continue acceleration, and the fairing is thrown away at a proper height. The laser beam is directly provided by a foundation laser station, the pitch angle
Figure BDA0003133041190000073
The gradual reduction ensures that the laser incidence angle is zero until the period of time T is set 2 Exhaustion, the phase ends;
a thrust-free gliding section: the foundation laser station does not provide laser beams any longer, and the laser aircraft does not slide under thrust until the non-thrust sliding time T G Exhaustion, this phase ends;
a horizontal acceleration section: the ground laser station emits laser beams to the relay satellite, the laser beams are shaped and repositioned by the relay lens system and then are emitted to the laser aircraft to provide power for the laser aircraft, the pitch angle changes ensure that the laser incidence angle is always zero, and the horizontal speed is increased until the target height H (namely the orbit-entering height) is reached for orbit entering.
In the laser aircraft transmitting method with the relay satellite, provided by the embodiment of the invention, the design parameter comprises the initial mass m 0 Initial pitch angle
Figure BDA0003133041190000081
Laser frequency coefficient c and working mode switching point height H 1 Rocket mode acceleration period time T 2 No thrust sliding section time T G And a staging height H. Wherein the initial mass m 0 Initial pitch angle
Figure BDA0003133041190000082
And the laser frequency coefficient c determines the initial state of the light ship when emitting and the thrust change in the first stage air suction working mode; height H of working mode switching point 1 Rocket mode acceleration period time T 2 No thrust sliding section time T G And the height H of the track entry determine the start and end conditions between the phases.
Fig. 4 is a schematic diagram of a conventional straight line ballistic launching scheme and a curved ballistic launching scheme according to an embodiment of the present invention, and fig. 5 is a schematic diagram of another conventional straight line ballistic launching scheme and a curved ballistic launching scheme according to an embodiment of the present invention.
Compared with the conventional straight line ballistic launching scheme and the conventional curved ballistic launching scheme shown in fig. 4 and 5, the laser aircraft launching method with the relay lens provided by the embodiment of the invention has the advantage that the flying process is mainly different in the added thrust-free taxiing section and the horizontal acceleration section formed after the relay satellite is added. The non-thrust gliding section enables the laser aircraft to effectively reduce the speed in the vertical direction, and provides conditions for final rail entry; in the horizontal acceleration section, because the limitation of the laser incidence angle is removed due to the existence of the relay satellite, the laser receiving device of the laser aircraft is not required to have a rotation function, the requirement of the structure of the laser aircraft is reduced, the thrust can be fully utilized to carry out horizontal acceleration to provide conditions for the orbit entering, and the utilization rate of energy is improved.
The method provided by the embodiment of the invention also solves the problems of laser beam visibility caused by the overlarge horizontal flight distance and the laser incident angle. Through simulation optimization design, the carrying capacity of the launching scheme is remarkably improved compared with that of the traditional linear and curve launching scheme, and the carrying capacity of 200km is improved by nearly 8 times; and the load ratio of the method provided by the embodiment of the invention at the target track height of 200km reaches 0.0635, which is obviously improved compared with the traditional chemical propulsion launching scheme.
Compared with the transmitting method in the prior art, the transmitting method of the laser aircraft with the relay satellite has the following technical effects:
(1) The embodiment of the invention adds the relay satellite, can reshape and relocate the laser, realizes that the laser incidence angle is zero in the flight process, does not need a laser receiving device of the laser aircraft to have a rotating function, and reduces the requirement on the structure of the laser aircraft;
(2) The laser beam is shaped and reoriented through the relay satellite, and can be provided for the laser aircraft at a higher height, so that the irradiation range of the laser beam is enlarged, and the visibility problem of the laser beam emitted by the foundation laser due to overlarge horizontal flight distance is avoided;
(3) Through simulation optimization design, compared with the traditional linear trajectory and curve trajectory launching scheme, the method provided by the embodiment of the invention has the advantages that the carrying capacity is obviously improved;
(4) The combination of the thrust-free gliding section and the horizontal acceleration section improves the utilization rate of energy;
(5) Compared with the traditional chemical propulsion, the method provided by the embodiment of the invention obviously improves the load ratio.
An embodiment of the present invention further provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, and when the processor executes the computer program, the steps of the method are implemented.
Embodiments of the present invention also provide a computer readable medium having non-volatile program code executable by a processor, where the program code causes the processor to execute the above method.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims (2)

1. A laser aircraft launching method with a relay satellite is characterized by being applied to a laser aircraft launching system; the laser aircraft launching system comprises: a ground based laser station and a relay satellite; the relay satellite carries relay lenses;
the ground-based laser station is used for providing laser beams for the laser aircraft; and further for transmitting the laser beam to the relay satellite;
the relay satellite is used for transmitting the laser beam to the laser aircraft in a horizontal acceleration stage after the laser beam is shaped and repositioned by using the relay lens; the orbital height of the relay satellite is consistent with the in-orbit height of the laser aircraft; the laser incident angle of the laser beam to the laser aircraft is zero;
the method comprises the following steps:
setting the working mode of the laser aircraft to be an air suction mode, and providing laser beams for the laser aircraft by the foundation laser station so that the laser aircraft flies to a first height from a launching point at a preset pitch angle in an accelerated manner; the altitude of the transmitting point is 3.65km;
setting the working mode of the laser aircraft to be a rocket mode, and continuously providing laser beams for the laser aircraft by the ground-based laser station so as to enable the laser aircraft to continuously accelerate from the first height for a first preset time;
suspending the laser beam provided by the foundation laser station so that the laser aircraft glides by inertia for a second preset time;
transmitting the laser beam transmitted to the relay satellite by the ground-based laser station to the laser aircraft after being relocated by the relay mirror so as to enable the laser aircraft to accelerate and fly to a second height in the horizontal direction; the second height is the height of the laser aircraft during the track entering; before the laser aircraft is in a horizontal acceleration stage, an included angle between a connecting line of the relay satellite and the geocenter and a connecting line of the laser aircraft and the geocenter is set to be pi/50.
2. The method of claim 1, the laser vehicle comprising a fairing; characterized in that the laser vehicle, during acceleration after switching to rocket mode, throws away the fairing.
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