WO2020155459A1 - 一种在火星上的飞行方法以及火星飞行装置 - Google Patents

一种在火星上的飞行方法以及火星飞行装置 Download PDF

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WO2020155459A1
WO2020155459A1 PCT/CN2019/085933 CN2019085933W WO2020155459A1 WO 2020155459 A1 WO2020155459 A1 WO 2020155459A1 CN 2019085933 W CN2019085933 W CN 2019085933W WO 2020155459 A1 WO2020155459 A1 WO 2020155459A1
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medium
mars
unit
flying
flying device
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PCT/CN2019/085933
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English (en)
French (fr)
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张文武
王玉峰
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中国科学院宁波材料技术与工程研究所
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    • 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
    • B64G1/105—Space science
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • 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
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • 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
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for

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  • the invention belongs to the field of flying technology, and in particular relates to a flying method on Mars and a Mars flying device.
  • the landing and returning of Mars mainly rely on the rocket principle, that is, the reaction material is carried by the aircraft, and the medium impulse is generated through chemical reaction to overcome the gravitational constraint.
  • the reaction material is carried by the aircraft, and the medium impulse is generated through chemical reaction to overcome the gravitational constraint.
  • rocket fuel due to limited rocket fuel, it is difficult to use rocket fuel in the Martian environment for a long time.
  • Other propulsion methods such as electric propulsion, plasma propulsion, etc., still require a large amount of auxiliary energy, structure, and medium consumption, so flying on Mars is very difficult.
  • the detection of Mars after landing is realized by the electric drive wheel drive device, that is, the wheel is driven by on-board electric power to realize the movement on Mars.
  • the present invention provides a flight method on Mars, which can be used to achieve flight on Mars, thereby breaking through the obstacles of the Martian surface morphology to scientific investigation, and expanding human's ability to detect and develop Mars.
  • the technical solution provided by the present invention is: a method of flying on Mars, using the medium on Mars and the medium acceleration unit; under the action of electric power, the medium acceleration unit works, transports the medium to the medium acceleration unit, and the medium is After acceleration, it leaves the medium acceleration unit. Due to the momentum conservation effect, a reaction force is generated. The reaction force overcomes the gravity of Mars and drives the load to take off.
  • the medium includes solid medium, such as sufficient resources on the planet such as soil, gravel, rock, and fluid medium, such as water resources on Mars.
  • the method of obtaining the medium is not limited, including one or a combination of a medium obtaining unit, such as a mechanical gripper, a belt retractor, and a suction pipe.
  • a medium obtaining unit such as a mechanical gripper, a belt retractor, and a suction pipe.
  • the medium acceleration unit is not limited, and may be a device that converts electrical energy into mechanical motion.
  • a drive unit such as a motor and a motor is composed of a rotating unit such as a blade and an impeller. Under the action of electric power, the drive unit works to drive the rotating unit to rotate and transport When the medium reaches the rotating unit, the medium is accelerated by the rotating unit and then thrown out; it can also be an electromagnetic device, for example, the medium is polarized and then input into the electromagnetic device, and the medium is accelerated by the electromagnetic field and then leaves the electromagnetic device.
  • the power supply mode is not limited, and one or more of generators, storage batteries, remote energy transmission power supplies, and airborne nuclear power supplies can be used.
  • the generators include, but are not limited to, fuel-based generators. On the earth, it can be a fuel-burning internal combustion engine with oxygen taken from the atmosphere; on Mars, it can be a configuration similar to a rocket engine, using fuel and oxidizer, such as kerosene and oxygen.
  • the advantage of the generator is that the power can be expanded as needed to achieve heavy load flight.
  • Solar energy is an available resource on Mars, so in the present invention, the generator can use solar energy to convert into electrical energy as a power supply unit.
  • a solar panel is provided on the flying device, and the solar panel can receive solar energy and convert it into electrical energy.
  • the battery can be charged through a power station, for example, through a Mars solar power station or other types of power stations.
  • the storage battery can be charged through a power station, which includes a solar power station or other types of power stations, and can also be charged by solar energy through a solar sail board installed on the flying device.
  • Remote energy transmission power supplies transmit energy remotely, such as electromagnetic waves to transmit energy over long distances, including microwaves, light energy, etc., and then convert them into electrical energy.
  • the onboard nuclear power supply can provide electricity for a long time.
  • the medium is continuously consumed.
  • land before the medium is exhausted and take off after loading the medium.
  • the method for conveying the medium to the medium acceleration unit is not limited, and it can be through free fall, transmission through transmission, such as conveyor belt transmission, or transmission through vibration.
  • the media acceleration unit includes a driving unit and a rotating unit
  • the rotating unit preferably uses lightweight materials.
  • a wear-resistant coating such as a diamond coating, is provided on the surface of the rotating unit.
  • the stress experienced by the rotating unit during high-speed rotation is lower than its ultimate yield stress.
  • the size of the reaction force determines the size of the load mass that can take off.
  • the magnitude of the reaction force is related to the diameter (m) of the rotating unit, the speed (rpm), and the mass flow rate (Kg/s) of the medium being thrown out. That is, other conditions are certain, and the reaction force can be controlled by controlling the diameter (m), rotation speed (rpm) of the rotating unit and the mass flow rate (Kg/s) of the medium being thrown out, thereby controlling the mass of the load that can take off.
  • the reaction force is proportional to the diameter (m) and rotation speed (rpm) of the rotating unit.
  • the following table shows the reaction force achieved by using high-speed motors to drive blades and the ultimate mass for takeoff on Mars.
  • the invention also provides a Mars flying device, including a power supply, a medium acceleration unit and a medium storage unit;
  • the power supply supplies power to the medium acceleration unit, and the medium acceleration unit works.
  • the medium is transported from the medium storage unit to the medium acceleration unit. After the medium acceleration unit is accelerated, it leaves the medium acceleration unit.
  • the reaction force generated overcomes the gravity of Mars and drives the flying device take off.
  • the Mars flying device further includes an ejection unit, and the medium leaves the medium acceleration unit after passing through the ejection unit.
  • the ejection unit includes a first ejection unit and a second ejection unit. After the medium is accelerated, the medium is separated from the medium acceleration unit through the first ejection unit, and the reaction force generated is used to overcome the gravitational force of Mars and pass the second ejection unit. After the ejection unit is separated from the medium acceleration unit, the reaction force generated is used to control the flight direction.
  • the first spray unit is arranged on the bottom of the flying device, and the second spray unit is arranged on the side of the flying device.
  • the power source can be a generator or a battery.
  • the generator includes, but is not limited to, a rocket engine using fuel and oxidizer.
  • the advantage of the generator is that the power can be expanded as needed to achieve heavy load flight.
  • Solar energy is an available resource on Mars, so in the present invention, the generator can use solar energy to convert into electrical energy as a power supply unit.
  • a solar panel is provided on the flying device, and the solar panel can receive solar energy and convert it into electrical energy.
  • the battery can be charged by solar energy, for example, it can be charged by solar energy through the Mars solar power station, or it can be charged by solar energy through a solar sail board installed on the flying device.
  • the flying device further includes a detector for detection, investigation, research and other purposes.
  • the flying device further includes a communicator for communication.
  • the flying device further includes a central controller for coordinated control of the entire flying device.
  • the present invention provides a new method of flying on Mars. Because there is no atmosphere on Mars, it is impossible to fly with atmospheric buoyancy.
  • the present invention uses the medium existing on Mars. The medium is accelerated by a medium acceleration unit and then separated from the medium acceleration unit. Returning to Mars, through the momentum conservation effect to produce a reaction force to overcome the gravity of Mars to cleverly achieve the purpose of flying, breaking through the obstacles of the Martian ground morphology to scientific investigation, and expanding the human ability to detect, investigate, and exploit Mars.
  • Fig. 1 is a schematic diagram of the structure of the Mars flying device in embodiment 1 of the present invention.
  • Figure 2 is a schematic diagram of the structure of the Mars flying device in Embodiment 2 of the present invention.
  • Fig. 3 is a schematic structural diagram of a Mars flying device in embodiment 3 of the present invention.
  • Fig. 4 is a schematic structural diagram of a Mars flying device in embodiment 4 of the present invention.
  • Fig. 5 is a schematic structural diagram of a Mars flying device in embodiment 5 of the present invention.
  • Fig. 6 is a schematic structural diagram of a Mars flying device in embodiment 6 of the present invention.
  • FIG. 1-6 The reference signs in Figures 1-6 are: 1. Aircraft body; 2. Solar sail; 3. Probe A; 4. Probe B; 5. Communicator; 6. Nozzle; 7. First nozzle; 8. , Soil; 9. solar power station; 10, soil grab and filter device; 11, power supply; 12, high-speed motor; 13, impeller; 14, soil storage container; 15, central processing unit; 16, power generation device; 17, section Two nozzles; 19. Support wheel.
  • a Mars flying device as shown in FIG. 1, includes a flying body 1, which includes a power supply 16, a high-speed motor 12, an impeller 13 and a soil storage container 14.
  • the power supply 16 supplies power to the high-speed motor 12, and the high-speed motor 12 works to drive the impeller 13 to rotate at a high speed.
  • the soil 8 falls from the soil storage container 14 to the impeller 13, and is accelerated by the high-speed rotating impeller 13, and is thrown out through the nozzle 6.
  • the reaction force overcomes the gravity of Mars and drives the flying device to take off on Mars.
  • the flying device also includes a probe A3 and a probe B4 for detection research.
  • the flying device also includes a communicator 5 for communication.
  • the flying device also includes a central controller 15 for coordinated control of the entire flying device.
  • the soil 8 is grabbed into the soil storage container 14 from the outside of the flying device by the soil grabbing and filtering device 10.
  • the soil in the soil storage container 14 is 30Kg, and the mass flow rate at which the soil 8 is thrown out is 0.1Kg/s, which can achieve a 300-second flight. Such a flight time can meet certain scientific detection and engineering requirements.
  • the flying device achieves a soft landing, and the soil grabbing and filtering device 10 is used to load the soil 8 before taking off.
  • a Mars flying device as shown in FIG. 2, includes a flying body 1 which includes a power supply 11, a high-speed motor 12, an impeller 13 and a soil storage container 14.
  • the power supply 11 supplies power to the high-speed motor, and the high-speed motor 12 works to drive the impeller 13 to rotate at a high speed.
  • the soil 8 falls from the soil storage container 14 to the impeller 13, and is accelerated by the high-speed rotating impeller 13 and thrown out through the nozzle 6.
  • the reaction force overcomes the gravity of Mars and drives the flying device to take off on Mars.
  • the power source 11 is a battery, and the onboard battery can be quickly charged by the Mars solar power station 9 when necessary.
  • the soil 8 is grabbed into the soil storage container 14 by the soil grabbing and filtering device 10 from outside the flying device. Before the soil 8 is exhausted, the flying device achieves a soft landing, and the soil grabbing and filtering device 10 is used to load the soil 8 before taking off.
  • the flying device also includes a probe A3 and a probe B4 for detection research.
  • the flying device also includes a communicator 5 for communication.
  • the flying device also includes a central controller 15 for coordinated control of the entire flying device.
  • the structure of the Mars flying device is basically the same as that of the second embodiment.
  • the difference is that the solar power station 9 is replaced by a solar panel 2 which is installed on the flying device. Therefore, when the power is insufficient, the flying device The battery 11 is charged by the solar panel 2.
  • the flying method of the flying device is the same as in the first embodiment.
  • a Mars flying device as shown in FIG. 4, includes a flying body 1, which includes a high-speed motor, an impeller, and a soil storage container.
  • Two solar windsurfing boards 2 are arranged on the side of the flying main body 1. Taking advantage of the fact that there is no atmospheric resistance on Mars, the solar windsurfing boards can be installed on the upper part of the aircraft to provide electricity for high-speed motors.
  • the solar panel 2 provides electrical energy for the high-speed motor.
  • the high-speed motor works to drive the impeller to rotate at high speed.
  • the soil 8 falls from the soil storage container to the impeller, and is accelerated by the high-speed rotating impeller, passing through the first nozzle 6 and the second nozzle 7.
  • the first nozzle 6 is set on the side of the flying body 1, the reaction force after the soil is thrown out is used to control the flight direction, and the second nozzle 7 is set on the bottom surface of the flying body 1, and the reaction force after the soil is thrown out is used To overcome the gravity of Mars.
  • the flying device further includes a supporting wheel 9 arranged on the side of the flying main body 1 to maintain the attitude of the flying device and realize the cushioning of take-off and landing.
  • the flying device before the soil 8 is exhausted, the flying device achieves a soft landing, and takes off after the soil 8 is loaded.
  • the flying device also includes a probe A3 and a probe B4 for detection research.
  • the flying device also includes a communicator 5 for communication.
  • the flying device also includes a central controller 15 for coordinated control of a series of actions of the flying device, including take-off, detection, and timely landing replenishment.
  • the structure of the Mars flying device is basically the same as that of the fourth embodiment. The difference is that there is no atmospheric resistance on Mars.
  • the solar panel 2 is installed on the top of the flying body and placed vertically. .
  • the flying method of the flying device is the same as in the fourth embodiment.
  • the structure of the Mars flying device is basically the same as that of the fourth embodiment.
  • the difference is that the solar panel 2 is replaced by a power generating device 16 arranged inside the flying main body 1.
  • the power generating device 16 may be Generators, batteries, remote energy transmission power sources or on-board nuclear power sources provide electrical energy to high-speed motors.

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Abstract

一种在火星上的飞行方法，采用火星表面的介质与介质加速单元，在电力作用下，介质加速单元工作，输送介质到介质加速单元，介质在介质加速单元被加速后脱离介质加速单元，由于动量守恒产生反作用力，该反作用力克服火星引力，带动负载起飞。还包括一种火星飞行装置，包括电源、介质加速单元与介质储存单元，介质加速单元工作，输送介质到介质加速单元，介质在介质加速单元被加速后脱离介质加速单元，产生反作用力克服火星引力，带动负载起飞。该方法及装置适用于由于无大气而无法借助大气浮力进行飞行的火星环境，可拓展人类对火星的探测、考察、开拓能力。

Description

一种在火星上的飞行方法以及火星飞行装置 技术领域
本发明属于飞行技术领域，尤其涉及一种在火星上的飞行方法以及火星飞行装置。
背景技术
与存在致密大气层的地球不同，火星表面大气层很稀薄，无法很好地借助大气浮力在火星进行飞行运动。
目前，火星的着陆、返回主要依靠火箭原理，即，由飞行器自带反应物质，通过化学反应产生介质冲量，克服引力约束。但由于火箭燃料有限，很难在火星环境长时间使用火箭燃料。其它的推进手段，如电推进、等离子体推进等，尚需要较大的辅助能源、结构和介质消耗，因此在火星上的飞行存在很大困难。
为此，可以考虑的着陆后的火星探测是通过电驱轮动装置实现的，即，通过车载电力驱动车轮转动，实现在火星上的运动。
但是，由于火星上许多区域的土壤松软，在火星上运动需要克服较大的阻力，尤其是当遇到复杂地貌时，电驱轮动装置容易出现意外。此外，对于陡峭或高处地貌，电驱轮动装置无法就近观察、取样。因此，对火星的探测、考察等面临很大困境。
发明内容
针对上述技术现状，本发明提供一种在火星上的飞行方法，利用该方法可实现在火星上的飞行，从而突破火星表面形貌对科学考察的障碍，拓展人类对火星的探测、开拓能力。
本发明提供的技术方案为：一种在火星上的飞行方法，采用火星上的介质与介质加速单元；在电力作用下，介质加速单元工作，输送介质到介质加速单元，介质在介质加速单元被加速后脱离介质加速单元，由于动量守恒效应产生反作用力，该反作用力克服火星引力，带动负载起飞。
所述介质包括固体介质，例如土壤、沙砾、岩石等星球上的充足资源，也包括流体介质，例如火星上的水资源等。
获取介质的方式不限，包括通过介质获取单元，例如机械抓手、带式卷入器、吸入式管道等中的一种或者几种的组合。
所述介质加速单元不限，可以是将电能转换为机械运动的装置，例如电机、马达等驱动单元与叶片、叶轮等旋转单元组成，在电力作用下，驱动单元工作，带动旋转单元旋转，输送介质到旋转单元上，介质经旋转单元加速后被甩出；也可以是电磁装置，例如，将介质进行极化处理后输入电磁装置内，在电磁场作用 下介质被加速后离开电磁装置。
所述的介质加速单元工作时，供电方式不限，可以采用发电机、蓄电池、远程能量输送电源、机载核能电源等中的一种或者几种。
所述发电机包括但不限于燃料类发电机，在地球上可以是燃油内燃机，氧气取自大气；在火星上可以是类似火箭发动机的配置，使用燃料与氧化剂，如煤油与氧气混合等。发电机的优点是功率可以根据需要扩展，实现重载飞行。太阳能是火星上的可用资源，因此本发明中，发电机可利用太阳能转换为电能，作为电力供给单元。作为一种实现方式，在飞行装置上设置太阳帆板，所述太阳帆板可以接收太阳能并将其转换为电能。
所述蓄电池可以通过电站进行充电，例如，可以通过火星太阳能电站或者其它类型的电站进行充电。
所述蓄电池可以通过电站充电，电站包括太阳能电站或者其它类型的电站，也可以通过设置在飞行装置上的太阳帆板进行太阳能充电。
远程能量输送电源通过远程传输能量，例如电磁波远距离传能，包括微波、光能等，然后转换为电能。
机载核能电源可以长时间提供电力。
在飞行过程中，介质不断消耗，作为一种实现方式，在介质耗尽前着陆，装载介质后再起飞。
介质被输送至介质加速单元的方法不限，可以通过自由落体，通过传动传输、例如传送带传输，或者通过振动传输等。
当所述介质加速单元包括驱动单元与旋转单元时，为了减少冲击磨损，旋转单元优选使用轻质材料。作为进一步优选，旋转单元表面设置耐磨涂层，例如金刚石涂层等。另外，旋转单元高速旋转时承受的应力低于其极限屈服应力。
所述的反作用力的大小决定了能够起飞的负载质量大小。反作用力的大小与旋转单元的直径(m)、转速(rpm)以及介质被甩出的质量流速(Kg/s)等参量有关。即，其它条件一定，通过控制旋转单元的直径(m)、转速(rpm)以及介质被甩出的质量流速(Kg/s)可以控制反作用力大小，从而控制能够起飞的负载质量。当介质被甩出的质量流速一定，以及其它条件一定的情况下，反作用力与旋转单元的直径(m)、转速(rpm)成正比关系。
例如，下表是采用高速电机驱动叶片实现的反作用力以及在火星起飞的极限质量。
Figure PCTCN2019085933-appb-000001
Figure PCTCN2019085933-appb-000002
从上表中可以看出，当设定土壤甩出的质量流为0.1Kg/s，使用直径为100毫米的叶轮，在75000rpm转速下，土壤甩出的速度为392.7m/s，可以实现约39N的反作用力。火星引力常数约为地球的38％，因此，该反作用力可以带动起飞的负载质量约为10.54Kg。在同等条件下，使用直径为200毫米叶轮，可以实现21Kg级的负载起飞；使用直径为400毫米的叶轮，可以实现42Kg级的负载起飞。高速电机可以驱动叶片实现10000-600000rpm的转速，因此可以带动起飞的负载质量很大。
本发明还提供一种火星飞行装置，包括电源、介质加速单元与介质储存单元；
工作状态时，电源为介质加速单元供电，介质加速单元工作，介质自介质储存单元输送至介质加速单元，在介质加速单元被加速后脱离介质加速单元，产生的反作用力克服火星引力，带动飞行装置起飞。
作为优选，所述火星飞行装置还包括喷出单元，介质经喷出单元后脱离介质加速单元。作为进一步优选，所述喷出单元包括第一喷出单元与第二喷出单元，介质被加速后通过第一喷出单元脱离介质加速单元，产生的反作用力用于克服火星引力，通过第二喷出单元后脱离介质加速单元，产生的反作用力用于控制飞行方向。作为进一步优选，所述第一喷出单元设置在飞行装置底部，第二喷出单元设置在飞行装置侧面。
所述电源可以是发电机，也可以是蓄电池。
所述发电机包括但不限于使用燃料与氧化剂的火箭发动机。发电机的优点是功率可以根据需要扩展，实现重载飞行。太阳能是火星上的可用资源，因此本发明中，发电机可利用太阳能转换为电能，作为电力供给单元。作为一种实现方式，在飞行装置上设置太阳帆板，所述太阳帆板可以接收太阳能并将其转换为电能。
所述蓄电池可以通过太阳能进行充电，例如，可以通过火星太阳能电站进行太阳能充电，也可以通过设置在飞行装置上的太阳帆板进行太阳能充电。
作为优选，所述飞行装置还包括探测器，用于进行探测、考察、研究等目的。
作为优选，所述飞行装置还包括通讯器，用于进行通讯联系。
作为优选，所述飞行装置还包括中央控制器，用于协调控制整个飞行装置。
本发明提供了一种在火星上的飞行新方法，火星上由于无大气而无法借助大气浮力进行飞行，本发明利用火星上存在的介质，该介质通过介质加速单元加速后脱离介质加速单元而重新回归火星，通过动量守恒效应产生反作用力克服火星 引力而巧妙地实现飞行目的，突破了火星的地面形貌对科学考察的障碍，可拓展人类对火星的探测、考察、开拓能力。
附图说明
图1是本发明实施例1中火星飞行装置的结构示意图。
图2是本发明实施例2中火星飞行装置的结构示意图。
图3是本发明实施例3中火星飞行装置的结构示意图。
图4是本发明实施例4中火星飞行装置的结构示意图。
图5是本发明实施例5中火星飞行装置的结构示意图。
图6是本发明实施例6中火星飞行装置的结构示意图。
具体实施方式
下面结合实施例对本发明作进一步详细描述，需要指出的是，以下所述实施例旨在便于对本发明的理解，而对其不起任何限定作用。
图1-6中的附图标记为：1、飞行器主体；2、太阳帆板；3、探测器A；4、探测器B；5、通讯器；6、喷嘴；7、第一喷嘴；8、土壤；9、太阳能电站；10、土壤抓取及过滤装置；11、电源；12、高速电机；13、叶轮；14、土壤储存容器；15、中央处理器；16、发电装置；17、第二喷嘴；19、支撑轮。
实施例1：
一种火星飞行装置，如图1所示，包括飞行主体1，飞行主体1包括电源16、高速电机12、叶轮13以及土壤储存容器14。
工作状态时，电源16为高速电机12供电，高速电机12工作，驱动叶轮13高速旋转，土壤8自土壤储存容器14落下至叶轮13，被高速旋转的叶轮13加速，通过喷嘴6甩出，产生的反作用力克服了火星引力，带动飞行装置在火星起飞。
该飞行装置还包括探测器A3和探测器B4，用于进行探测研究。
该飞行装置还包括通讯器5，用于进行通讯联系。
该飞行装置还包括中央控制器15，用于协调控制整个飞行装置。
本实施例中，土壤8由土壤抓取与过滤装置10从飞行装置外部抓入土壤储存容器14中。土壤储存容器14中的土壤为30Kg，土壤8被甩出的质量流速为0.1Kg/s，可以实现300秒飞行，这样的飞行时间能够满足一定的科学探测和工程要求。土壤8耗尽前，该飞行装置实现软着陆，利用土壤抓取与过滤装置10装载土壤8，再继续起飞。
实施例2：
一种火星飞行装置，如图2所示，包括飞行主体1，飞行主体1包括电源11、高速电机12、叶轮13以及土壤储存容器14。
工作状态时，电源11为高速电机供电，高速电机12工作，驱动叶轮13高 速旋转，土壤8自土壤储存容器14落下至叶轮13，被高速旋转的叶轮13加速，通过喷嘴6甩出，产生的反作用力克服了火星引力，带动飞行装置在火星起飞。
本实施例中，电源11为蓄电池，必要时该机载蓄电池可以通过火星太阳能电站9进行快速充电。
另外，本实施例中，土壤8由土壤抓取与过滤装置10从飞行装置外部抓入土壤储存容器14中。土壤8耗尽前，该飞行装置实现软着陆，利用土壤抓取与过滤装置10装载土壤8，再继续起飞。
该飞行装置还包括探测器A3和探测器B4，用于进行探测研究。
该飞行装置还包括通讯器5，用于进行通讯联系。
该飞行装置还包括中央控制器15，用于协调控制整个飞行装置。
实施例3：
本实施例中，火星飞行装置的结构与实施例2基本相同，所不同的是太阳能电站9由太阳帆板2代替，太阳帆板2设置在飞行装置上，因此在电力不足时，该飞行装置通过太阳帆板2为蓄电池11进行充电。
本实施例中，飞行装置的飞行方法与实施例1相同。
实施例4：
本实施例中，一种火星飞行装置，如图4所示，包括飞行主体1，飞行主体1包括高速马达、叶轮以及土壤储存容器。
飞行主体1的侧面设置两个太阳帆板2，利用火星上没有大气阻力的便利，可以将太阳帆板安装在飞行器上部，为高速马达提供电能。
工作状态时，太阳帆板2为高速马达提供电能，高速马达工作，驱动叶轮高速旋转，土壤8自土壤储存容器落下至叶轮，被高速旋转的叶轮加速，通过第一喷嘴6与第二喷嘴7甩出，第一喷嘴6设置在飞行主体1的侧面，土壤被甩出后的反作用力用于控制飞行方向，第二喷嘴7设置在飞行主体1的底面，土壤被甩出后的反作用力用于克服火星引力。
本实施例中，飞行装置还包括支撑轮9，设置在飞行主体1侧面，用于保持飞行装置的姿态，并实现起飞和降落的缓冲。
另外，本实施例中，土壤8耗尽前，该飞行装置实现软着陆，装载土壤8后再起飞。
该飞行装置还包括探测器A3和探测器B4，用于进行探测研究。
该飞行装置还包括通讯器5，用于进行通讯联系。
该飞行装置还包括中央控制器15，用于协调控制飞行装置的一系列动作，包括起飞、探测、及时着陆补给等。
实施例5：
本实施例中，火星飞行装置的结构与实施例4基本相同，所不同的是利用火星上没有大气阻力的便利，如图5所示，将太阳帆板2安装在飞行主体的顶部， 垂直放置。
本实施例中，飞行装置的飞行方法与实施例4相同。
实施例6：
本实施例中，火星飞行装置的结构与实施例4基本相同，所不同的是太阳帆板2由设置在飞行主体1内部的发电装置16取代，如图6所示，该发电装置16可以是发电机、蓄电池、远程能量输送电源或者机载核能电源，给高速马达提供电能。
以上所述的实施例对本发明的技术方案进行了详细说明，应理解的是以上所述仅为本发明的具体实施例，并不用于限制本发明，凡在本发明的原则范围内所做的任何修改、补充或类似方式替代等，均应包含在本发明的保护范围之内。

Claims (25)

  1. 一种在火星上的飞行方法，其特征是：采用火星上的介质与介质加速单元；
    在电力作用下，介质加速单元工作，输送介质到介质加速单元，介质在介质加速单元被加速后脱离介质加速单元，由于动量守恒效应产生反作用力，该反作用力克服火星引力，带动负载起飞。
  2. 如权利要求1所述的在火星上的飞行方法，其特征是：所述介质是固体介质或者流体介质。
  3. 如权利要求1所述的在火星上的飞行方法，其特征是：所述固体介质是土壤、沙砾、岩石中的一种或者几种。
  4. 如权利要求1所述的在火星上的飞行方法，其特征是：所述流体介质是水。
  5. 如权利要求1所述的在火星上的飞行方法，其特征是：所述介质加速单元包括驱动单元与旋转单元，在电力作用下，驱动单元工作，带动旋转单元旋转，输送介质到旋转单元上，介质经旋转单元加速后被甩出。
  6. 如权利要求5所述的在火星上的飞行方法，其特征是：所述驱动单元是电动马达或者电机。
  7. 如权利要求5所述的在火星上的飞行方法，其特征是：所述旋转单元是叶片或者叶轮。
  8. 如权利要求1所述的在火星上的飞行方法，其特征是：所述介质加速单元是电磁装置，将介质进行极化处理后输入电磁装置内，在电磁场作用下介质被加速后离开电磁装置。
  9. 如权利要求1所述的在火星上的飞行方法，其特征是：采用发电机、蓄电池、远程能量输送电源、机载核能电源中的一种或者几种为介质加速单元供电。
  10. 如权利要求1所述的在火星上的飞行方法，其特征是：利用火星上的太阳能站，将太阳能转换为电能，为驱动单元供电。
  11. 如权利要求1所述的在火星上的飞行方法，其特征是：介质通过传动传输、振动传输或者自由落体输送至介质加速单元。
  12. 如权利要求1所述的在火星上的飞行方法，其特征是：在介质耗尽前着陆，装载介质后再起飞。
  13. 如权利要求1至12中任一权利要求所述的在火星上的飞行方法，其特征是：所述介质加速单元由驱动单元与旋转单元组成，通过控制旋转单元的直径、转速以及介质被甩出的质量流速控制起飞的负载质量。
  14. 一种火星飞行装置，其特征是：包括电源、介质加速单元与介质储存单元；
    工作状态时，电源为介质加速单元供电，介质加速单元工作，介质自介质储 存单元输送至介质加速单元，在介质加速单元被加速后脱离介质加速单元，产生的反作用力克服火星引力，带动飞行装置起飞。
  15. 如权利要求14所述的火星飞行装置，其特征是：还包括喷出单元，介质经喷出单元后脱离介质加速单元。
  16. 如权利要求14所述的火星飞行装置，其特征是：所述喷出单元包括第一喷出单元与第二喷出单元，介质被加速后通过第一喷出单元脱离介质加速单元，产生的反作用力用于克服火星引力，通过第二喷出单元后脱离介质加速单元，产生的反作用力用于控制飞行方向。
  17. 如权利要求14所述的火星飞行装置，其特征是：所述第一喷出单元设置在飞行装置底部，第二喷出单元设置在飞行装置侧面。
  18. 如权利要求14所述的火星飞行装置，其特征是：所述电源是发电机或者蓄电池。
  19. 如权利要求18所述的火星飞行装置，其特征是：所述发电机将太阳能转换为电能。
  20. 如权利要求18所述的火星飞行装置，其特征是：在飞行装置上设置太阳帆板，所述太阳帆板接收太阳能并将其转换为电能。
  21. 如权利要求18所述的火星飞行装置，其特征是：所述蓄电池通过太阳能进行充电。
  22. 如权利要求21所述的火星飞行装置，其特征是：通过火星太阳能电站进行太阳能充电，或者通过设置在飞行装置上的太阳帆板进行太阳能充电。
  23. 如权利要求14所述的火星飞行装置，其特征是：所述飞行装置还包括探测器。
  24. 如权利要求14所述的火星飞行装置，其特征是：所述飞行装置还包括通讯器。
  25. 如权利要求14所述的火星飞行装置，其特征是：所述飞行装置还包括中央控制器。
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