CN108839807A - A kind of novel mars device compound propulsion system - Google Patents
A kind of novel mars device compound propulsion system Download PDFInfo
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- CN108839807A CN108839807A CN201810455436.8A CN201810455436A CN108839807A CN 108839807 A CN108839807 A CN 108839807A CN 201810455436 A CN201810455436 A CN 201810455436A CN 108839807 A CN108839807 A CN 108839807A
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- oxidant
- petrolift
- tank
- mars
- fuel
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/023—Aircraft characterised by the type or position of power plant of rocket type, e.g. for assisting taking-off or braking
Abstract
The present invention relates to a kind of novel mars device compound propulsion systems, are related to mars exploration and mars device power technology field.In order to solve the problem of that existing propulsion system needs carry a large amount of fuel from the earth and are unable to satisfy the full stage aerial mission of mars device.The output end of the oxidant tank and fuel tank is corresponding with the input terminal of oxidant pump and petrolift respectively to be connected；Flow control valve is equipped on the pipeline that the oxidant tank is connected with oxidant pump and on pipeline that fuel tank is connected with petrolift；Fuel in oxidant tank and fuel tank passes through oxidant pump respectively and petrolift is delivered in combustion chamber and burns, and the end of the combustion chamber is connected with the head end of jet pipe.Propellant needed for the available resources that the present invention can use Mars directly prepare aircraft.
Description
Technical field
The present invention relates to a kind of novel mars device compound propulsion system, it is related to mars exploration and mars device is dynamic
Power technical field.
Background technique
Enter the promotion of spacial ability and the development of space technology with the mankind, deep space has become the important exploration neck of the mankind
One of domain.Mars exploration becomes a hot spot of mankind's deep space exploration in recent years.It is manned Mars that Push Technology, which continues to develop,
Detection and the highly difficult space tasks such as recoverable mars exploration provide possibility, with manned space flight, Lunar Probe Project it is continuous
Success, the angle space of every country slowly turn to Mars by target.The mars exploration plan of China is in January, 2016
Formal project verification, the plan will under the general objective of " for the sustainable development service of human society ", the origin of Mars Exploration and evolution,
A series of problem in science such as topography and geomorphology, natural environment and vital movement information, finally to the long-term transformation of Mars and from now on
A possibility that a large amount of immigrants establish second habitat of the mankind makes assessment.As background technique of the invention, mars device
It will play a significant role in terms of transporting goods and materials, transfer.
The operation of mars device be unable to do without advanced propulsion system.Propulsion system will take off, climb, cruise etc. it is each
A stage provides thrust for mars device.It, can be by existing spacecraft propulsion system according to different oxidant acquisition modes
System is divided into airbreathing motor and rocket engine two major classes, and the oxidant needed for the former is obtained from earth atmosphere, and the latter
Required oxidant is by its own carrying.The two is either any, if be used directly on mars device, can face
Two problems：1. the main component of martian atmosphere is carbon dioxide, existing airbreathing motor will be unable to using；2. rocket is sent out
The service life of motivation is limited by institute's quantity of fuel, certainly will will be from the earth if using existing rocket engine on Mars
Mass energy is carried, this will be so that task cost greatly increases.
Aircraft flies in an atmosphere, and the lift for being wing and air relative motion generation and propulsion system leaned on mentions
The thrust of confession.The particularity of mars device is that there are huge for requirement of the aerial mission of different phase to motor power
Difference.On the one hand, it is restricted by martian atmosphere low-density, the lift that wing can be provided is extremely limited, so propulsion system needs
It to provide in takeoff phase compared with high thrust, aircraft could be accelerated to liftoff take off；On the other hand, aircraft is in cruising phase
Thrust requirements it is much smaller compared to takeoff phase, and have higher requirement to the economy of propulsion system.
Therefore, it relies solely on a kind of engine to be difficult to complete the aerial mission in full stage, it is necessary to develop a kind of novel
Mars device compound propulsion system, both can solve the energy demand of propulsion system, can be worked normally under Mars environment and
Without conveying a large amount of fuel from the earth, and it is able to satisfy the thrust, efficiency requirements of the aircraft under different phase.
Summary of the invention
The present invention carries a large amount of fuel to solve existing propulsion system needs from the earth, and is unable to satisfy mars
The problem of device full stage aerial mission, provides a kind of novel mars device compound propulsion system, the technical solution of use
It is：
A kind of novel mars device compound propulsion system, including propeller and rocket engine, the propeller and
Rocket engine is mounted on the wing of aircraft, and the rocket engine includes oxidant tank, fuel tank, oxidant
Pump, petrolift, combustion chamber, jet pipe and flow control valve；
The output end of the oxidant tank and fuel tank phase corresponding with the input terminal of oxidant pump and petrolift respectively
Even；On the pipeline that the oxidant tank is connected with oxidant pump and on pipeline that fuel tank is connected with petrolift
Equipped with flow control valve；Fuel in oxidant tank and fuel tank passes through oxidant pump respectively and petrolift is delivered to burning
Interior is burnt, and the end of the combustion chamber is connected with the head end of jet pipe.
It further limiting, the propulsion system further includes battery dynamical system, and battery dynamical system includes battery,
Power converter and motor；The driving end of the oxidant pump, petrolift and propeller is respectively equipped with motor, by described
The driving of motor realization oxidant pump, petrolift and propeller；The DC signal output end and power inverter of battery
Direct current signal input terminal be connected, the ac signal output end of power inverter power exchanges letter with three motor respectively
Number input terminal is corresponding to be connected.
Beneficial effects of the present invention：The novel mars device compound propulsion system of one kind of the present invention, the propulsion
Rocket engine in system works in aircraft takeoff, ramp-up period, by the relatively high thrust that rocket engine provides, flight
Device can accelerate to the required flying speed that takes off in short distance；Airscrew engine aircraft climb, cruise, decline and
Land stage work provides thrust to balance the resistance in flight course；Landing period propeller is using the work side reversely rotated
Formula, propulsive thrust needed for aircraft brakes are provided.Entire compound propulsion system can fly in each stage of aerial mission for Mars
Row device, which provides, works normally necessary thrust；
The propellant of rocket engine is directly prepared using the available resources of Mars in the present invention, the electricity stored by battery
It can be obtained by way of photovoltaic power generation or nuclear energy power generation, there is no need to carry extra propellant from the earth, be facilitated
Reduce the cost of entire mars exploration task.
Detailed description of the invention
Fig. 1 is the novel mars device compound propulsion system structural schematic diagram of one kind of the present invention；
Fig. 2 is the embodiment schematic diagram of rocket engine of the present invention；
Fig. 3 is the embodiment schematic diagram of battery dynamical system of the present invention.
Specific embodiment
The present invention will be further described combined with specific embodiments below, but the present invention should not be limited by the examples.
Specific embodiment：Illustrate present embodiment in conjunction with Fig. 1 to Fig. 3：It is novel that present embodiment proposes described one kind
Mars device compound propulsion system, including propeller 1 and rocket engine 2, the propeller 1 and rocket engine 2 are pacified
On the wing of aircraft 3, the rocket engine 2 includes oxidant tank 4, fuel tank 5, oxidant pump 6, petrolift
7, combustion chamber 8, jet pipe 9 and flow control valve 11；The output end of the oxidant tank 4 and fuel tank 5 respectively with oxidation
Agent pump 6 is connected with the input terminal of petrolift 7 correspondence；On the pipeline that the oxidant tank 4 is connected with oxidant pump 6, and
Flow control valve 11 is equipped on the pipeline that fuel tank 5 is connected with petrolift 7；Combustion in oxidant tank 4 and fuel tank 5
Material is delivered in combustion chamber 8 and is burnt by oxidant pump 6 and petrolift 7 respectively, the end of the combustion chamber 8 and jet pipe
9 head end is connected.The propulsion system further includes battery dynamical system, and battery dynamical system includes battery 12, power
Converter 13 and motor 10；The driving end of the oxidant pump 6, petrolift 7 and propeller 1 is respectively equipped with motor 10, leads to
Cross the driving that the motor 10 realizes oxidant pump 6, petrolift 7 and propeller 1；The DC signal output end of battery 12
It is connected with the direct current signal input terminal of power inverter 13, the ac signal output end of power inverter power 13 is respectively with three
The AC signal input terminal of a motor 10 is corresponding to be connected.
Start rocket engine 2, by rocket engine 2 after preparing before the completion of mars device is taken off referring to Fig. 1
Provided thrust, aircraft 3 accelerate to liftoff required speed of taking off；After aircraft 3 is liftoff and enters ramp-up period,
Start airscrew engine, and after airscrew engine reaches design speed close rocket engine 2, aircraft 3 climb,
Thrust needed for cruise and decline stage is provided by airscrew engine；After aircraft 3 lands, airscrew engine is using reversion
Working method, aircraft 3 is provided and brakes required part propulsive thrust.
Referring to fig. 2, oxidant and fuel needed for rocket engine are stored in respectively in oxidant tank 4 and fuel tank 5,
And it is delivered in combustion chamber 8 by oxidant pump 6 and petrolift 7 participates in burning respectively；Combustion product expands work in jet pipe 9
Function generates thrust；Oxidant pump 6 and petrolift 7 are driven by motor 10；Fuel and oxidizer flow rate into combustion chamber 8 is logical
Overcurrent adjustable valve 11 is controlled.
Referring to Fig. 3, power converter 13 is used for the direct current for providing battery 12, is converted into the alternating current of specific frequency
To control 10 revolving speed of motor；Battery 12, power converter 13 and motor 10 are directly installed in battery dynamical system
On other component, for maintaining the temperature of each component constant；Propeller 1, oxidant pump 6 and petrolift 7 are driven by motor 10
It is dynamic.
The novel mars device compound propulsion system of one kind of the present invention is not limited to and above-mentioned each embodiment
Described specific structure can also be the reasonable combination of feature described in above-mentioned each embodiment.
Claims (2)
1. a kind of novel mars device compound propulsion system, including propeller (1) and rocket engine (2), the spiral
Paddle (1) and rocket engine (2) are mounted on the wing of aircraft (3), which is characterized in that the rocket engine (2) includes
Oxidant tank (4), fuel tank (5), oxidant pump (6), petrolift (7), combustion chamber (8), jet pipe (9) and flow are adjusted
Valve (11)；
The input with oxidant pump (6) and petrolift (7) respectively of the output end of the oxidant tank (4) and fuel tank (5)
End is corresponding to be connected；On the pipeline that the oxidant tank (4) is connected with oxidant pump (6) and fuel tank (5) and fuel
Flow control valve (11) are equipped on the connected pipeline of pump (7)；
Fuel in oxidant tank (4) and fuel tank (5) passes through oxidant pump (6) respectively and petrolift (7) is delivered to combustion
It burns in room (8) and burns, the end of the combustion chamber (8) is connected with the head end of jet pipe (9).
2. the novel mars device compound propulsion system of one kind according to claim 1, which is characterized in that the propulsion
System further includes battery dynamical system, and battery dynamical system includes battery (12), power converter (13) and motor
(10)；The driving end of the oxidant pump (6), petrolift (7) and propeller (1) is respectively equipped with motor (10), by described
The driving of motor (10) realization oxidant pump (6), petrolift (7) and propeller (1)；
The DC signal output end of battery (12) is connected with the direct current signal input terminal of power inverter (13), power conversion
The ac signal output end of device power (13) is corresponding with the AC signal input terminal of three motor (10) respectively to be connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810455436.8A CN108839807B (en) | 2018-05-14 | 2018-05-14 | Novel mars aircraft combination propulsion system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810455436.8A CN108839807B (en) | 2018-05-14 | 2018-05-14 | Novel mars aircraft combination propulsion system |
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| CN108839807A true CN108839807A (en) | 2018-11-20 |
| CN108839807B CN108839807B (en) | 2020-12-11 |
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| CN201810455436.8A Active CN108839807B (en) | 2018-05-14 | 2018-05-14 | Novel mars aircraft combination propulsion system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110594040A (en) * | 2019-10-23 | 2019-12-20 | 哈尔滨工业大学 | Fuel cell supply system for rocket engine |
| WO2020155459A1 (en) * | 2019-02-02 | 2020-08-06 | 中国科学院宁波材料技术与工程研究所 | Method for flying on mars and mars flight apparatus |
| WO2020155458A1 (en) * | 2019-02-02 | 2020-08-06 | 中国科学院宁波材料技术与工程研究所 | Flying method and flying device |
| CN111516910A (en) * | 2019-02-02 | 2020-08-11 | 中国科学院宁波材料技术与工程研究所 | Flight method on moon and moon flight device |
| CN111776249A (en) * | 2020-07-06 | 2020-10-16 | 马世航 | Lunar surface low-altitude aircraft taking lunar surface soil as projection working medium |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111516906A (en) * | 2019-02-02 | 2020-08-11 | 中国科学院宁波材料技术与工程研究所 | Flight method and flight device |
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| CN111776249A (en) * | 2020-07-06 | 2020-10-16 | 马世航 | Lunar surface low-altitude aircraft taking lunar surface soil as projection working medium |
| CN111776249B (en) * | 2020-07-06 | 2023-10-24 | 马世航 | Lunar surface low-altitude aircraft taking lunar surface soil as casting working medium |
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| Publication number | Publication date |
|---|---|
| CN108839807B (en) | 2020-12-11 |
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