CN108839807A - A kind of novel mars device compound propulsion system - Google Patents

Abstract

The invention relates to a novel combined propulsion system of a Mars spacecraft, and relates to the technical fields of Mars exploration and Mars spacecraft power. In order to solve the problem that the existing propulsion system needs to carry a large amount of fuel from the earth and cannot meet the full-stage mission of the Mars spacecraft. The output ends of the oxidant storage tank and the fuel storage tank are connected to the input ends of the oxidant pump and the fuel pump respectively; Both are equipped with flow regulating valves; the fuel in the oxidant storage tank and the fuel storage tank is delivered to the combustion chamber through the oxidant pump and the fuel pump respectively for combustion, and the end of the combustion chamber is connected with the head end of the tail nozzle. The present invention can utilize the available resources of Mars to directly prepare the propellant required by the aircraft.

Description

A New Combined Propulsion System for Mars Vehicle

technical field

The invention relates to a novel combined propulsion system of a Mars vehicle, and relates to the technical fields of Mars exploration and Mars vehicle power.

Background technique

With the improvement of human ability to enter space and the development of aerospace technology, deep space has become one of the important fields of human exploration. Mars exploration has become a hotspot in human deep space exploration in recent years. The continuous development of propulsion technology has provided the possibility for difficult space missions such as manned Mars exploration and return Mars exploration. With the continuous success of manned spaceflight and moon landing programs, the space competition goal of various countries has gradually turned to Mars. China's Mars exploration program was officially established in January 2016. Under the general goal of "serving the sustainable development of human society", the program will explore the origin and evolution of Mars, topography, natural environment, and information on life activities. A series of scientific questions, and finally make an assessment of the long-term transformation of Mars and the possibility of a large number of immigrants in the future to establish a second human habitat. As the background technology of the present invention, the Mars spacecraft will play an important role in transporting materials and transferring personnel.

The operation of the Mars spacecraft is inseparable from the advanced propulsion system. The propulsion system will provide thrust for the Mars spacecraft in various stages such as take-off, climb, and cruise. According to different methods of obtaining oxidants, the existing aerospace propulsion systems can be divided into two categories: air-breathing engines and rocket engines. The oxidants required by the former are obtained from the earth's atmosphere, while the oxidants required by the latter are carried by themselves. No matter which of the two, if it is used directly on the Mars spacecraft, it will face two problems: 1. The main component of the Martian atmosphere is carbon dioxide, and the existing air-breathing engines will not be used; 2. Rocket engines The service life of the rocket is limited by the amount of fuel used. If the existing rocket engine is used on Mars, it is bound to carry a large amount of energy from the earth, which will greatly increase the cost of the mission.

The aircraft flies in the atmosphere, relying on the lift generated by the relative motion of the wings and the air, and the thrust provided by the propulsion system. The particularity of the Mars spacecraft is that there are huge differences in engine thrust requirements for different stages of missions. On the one hand, due to the low density of the Martian atmosphere, the lift provided by the wings is very limited, so the propulsion system needs to provide a large thrust during the take-off phase to accelerate the aircraft to take off from the ground; on the other hand, the aircraft in the cruise phase Compared with the take-off stage, the thrust demand is much smaller, and it has higher requirements on the economy of the propulsion system.

Therefore, it is difficult to complete the full-stage flight mission only by one engine. It is necessary to develop a new type of combined propulsion system for Mars spacecraft, which can not only solve the energy demand of the propulsion system, but also can work normally in the Martian environment without transporting it from the earth. A large amount of fuel can meet the thrust and efficiency requirements of the aircraft at different stages.

Contents of the invention

In order to solve the problem that the existing propulsion system needs to carry a large amount of fuel from the earth and cannot meet the full-stage mission of the Mars spacecraft, the present invention provides a new type of combined propulsion system for the Mars spacecraft. The technical solution adopted is:

A new type of combined propulsion system for a Mars vehicle, including propellers and rocket motors, the propellers and rocket motors are installed on the wings of the vehicle, and the rocket motors include oxidant storage tanks, fuel storage tanks, oxidant pumps, fuel pumps, combustion Chamber, tailpipe and flow regulating valve;

The output ends of the oxidant storage tank and the fuel storage tank are connected to the input ends of the oxidant pump and the fuel pump respectively; Both are equipped with flow regulating valves; the fuel in the oxidant storage tank and the fuel storage tank is delivered to the combustion chamber through the oxidant pump and the fuel pump respectively for combustion, and the end of the combustion chamber is connected with the head end of the tail nozzle.

Further defined, the propulsion system also includes a battery power system, and the battery power system includes a battery, a power converter, and an electric motor; the driving ends of the oxidant pump, fuel pump, and propeller are respectively provided with electric motors, and the oxidant pump, fuel pump, and Fuel pump and propeller drive; the DC signal output of the battery is connected to the DC signal input of the power converter, and the AC signal output of the power converter is respectively connected to the AC signal input of the three motors.

Beneficial effects of the present invention: a novel combined propulsion system for a Mars spacecraft according to the present invention, the rocket motor in the propulsion system works during the take-off and climbing phases of the aircraft, and with the help of the relatively large thrust provided by the rocket motor, the aircraft can fly in a short distance The propeller engine works in the climbing, cruising, descending and landing stages of the aircraft to provide thrust to balance the resistance during flight; the propeller in the landing stage adopts a counter-rotating working method to provide braking for the aircraft required reverse thrust. The entire combined propulsion system can provide the thrust necessary for the normal work of the Mars spacecraft at all stages of the mission;

The propellant of the rocket engine in the present invention is directly prepared from the available resources of Mars, and the electric energy stored in the storage battery can be obtained through photovoltaic power generation or nuclear power generation. The cost of the task.

Description of drawings

Fig. 1 is a kind of novel Mars spacecraft combined propulsion system structural representation of the present invention;

Fig. 2 is a schematic diagram of an embodiment of the rocket engine of the present invention;

Fig. 3 is a schematic diagram of an embodiment of the battery power system of the present invention.

Detailed ways

The present invention will be further described below in conjunction with specific examples, but the present invention is not limited by the examples.

Specific embodiments: this embodiment will be described in conjunction with Fig. 1 to Fig. 3: a kind of new-type Mars aircraft combined propulsion system mentioned in this embodiment includes propeller 1 and rocket engine 2, and described propeller 1 and rocket engine 2 are installed On the wing of the aircraft 3, the rocket engine 2 includes an oxidizer tank 4, a fuel tank 5, an oxidizer pump 6, a fuel pump 7, a combustion chamber 8, a tail nozzle 9 and a flow regulating valve 11; The output ends of the tank 4 and the fuel storage tank 5 are connected to the input ends of the oxidizer pump 6 and the fuel pump 7 respectively; Flow regulating valves 11 are provided on the connected pipelines; the fuel in the oxidant storage tank 4 and the fuel storage tank 5 is delivered to the combustion chamber 8 by the oxidant pump 6 and the fuel pump 7 for combustion respectively, and the end of the combustion chamber 8 is connected to the The head end of tail nozzle 9 is connected. The propulsion system also includes a battery power system, and the battery power system includes a battery 12, a power converter 13, and an electric motor 10; the driving ends of the oxidant pump 6, the fuel pump 7, and the propeller 1 are respectively provided with an electric motor 10, through which the electric motor 10 realizes the drive of the oxidant pump 6, the fuel pump 7 and the propeller 1; the DC signal output terminal of the storage battery 12 is connected with the DC signal input terminal of the power converter 13, and the AC signal output terminal of the power converter power 13 is respectively connected with three electric motors The AC signal input terminals of 10 are correspondingly connected.

Referring to Fig. 1, after the Mars vehicle completes the pre-take-off preparations, start the rocket engine 2, and rely on the thrust provided by the rocket engine 2, the vehicle 3 accelerates to the speed required for take-off; when the vehicle 3 leaves the ground and enters the climbing phase, Start the propeller engine, and turn off the rocket engine 2 after the propeller engine reaches the design speed, and the thrust required by the aircraft 3 in the climbing, cruising and descending phases is provided by the propeller engine; Part of the reverse thrust required for aircraft 3 braking.

Referring to Fig. 2, the oxidant and fuel required by the rocket engine are stored in the oxidant storage tank 4 and the fuel storage tank 5 respectively, and are delivered to the combustion chamber 8 by the oxidant pump 6 and the fuel pump 7 to participate in combustion; 9 internal expansion works to generate thrust; oxidant pump 6 and fuel pump 7 are both driven by motor 10; the flow of fuel and oxidant entering combustion chamber 8 is controlled by flow regulating valve 11.

Referring to Fig. 3, the power converter 13 is used to convert the direct current provided by the battery 12 into an alternating current of a specific frequency to control the rotation speed of the motor 10; the battery 12, the power converter 13 and the motor 10 are directly installed on other components in the battery power system, Used to keep the temperature of each component constant; propeller 1 , oxidant pump 6 and fuel pump 7 are all driven by electric motor 10 .

The novel combined propulsion system of the Mars spacecraft described in the present invention is not limited to the specific structure described in the above-mentioned various embodiments, but can also be a reasonable combination of the features described in the above-mentioned various embodiments.

Claims (2)

1. a novel Mars vehicle combination propulsion system, comprises propeller (1) and rocket motor (2), and described propeller (1) and rocket motor (2) are installed on the wing of aircraft (3), it is characterized in that , the rocket engine (2) comprises an oxidant tank (4), a fuel tank (5), an oxidant pump (6), a fuel pump (7), a combustion chamber (8), a tail nozzle (9) and a flow regulator valve (11); The output ends of the oxidant storage tank (4) and the fuel storage tank (5) are connected to the input ends of the oxidant pump (6) and the fuel pump (7) respectively; 6) A flow regulating valve (11) is provided on the connected pipeline and the pipeline connected between the fuel storage tank (5) and the fuel pump (7); The fuel in the oxidant storage tank (4) and the fuel storage tank (5) is delivered to the combustion chamber (8) for combustion by the oxidant pump (6) and the fuel pump (7) respectively, and the end of the combustion chamber (8) is connected to The head end of tail nozzle (9) links to each other. 2. a kind of novel Mars aircraft combined propulsion system according to claim 1, is characterized in that, described propulsion system also comprises accumulator power system, and accumulator power system comprises accumulator (12), power converter (13) and electric motor (10); the drive ends of the oxidant pump (6), fuel pump (7) and propeller (1) are respectively provided with motors (10), and the oxidant pump (6), fuel pump ( 7) and the drive of propeller (1); The DC signal output terminal of the storage battery (12) is connected to the DC signal input terminal of the power converter (13), and the AC signal output terminals of the power converter power (13) correspond to the AC signal input terminals of the three motors (10) respectively connected.