CN109018439A - Rocket-powered mars transporter - Google Patents
Rocket-powered mars transporter Download PDFInfo
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- CN109018439A CN109018439A CN201810871801.3A CN201810871801A CN109018439A CN 109018439 A CN109018439 A CN 109018439A CN 201810871801 A CN201810871801 A CN 201810871801A CN 109018439 A CN109018439 A CN 109018439A
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- 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
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- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
-
- 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
Abstract
The invention provides a rocket-powered mars transporter, which comprises a bearing system, and a buffer landing system, a power system, an energy system and a navigation guidance and control system which are arranged on the bearing system, wherein the bearing system comprises a truss, and the power system comprises a main engine arranged at the bottom of a frame; the energy system comprises a plurality of high-pressure gas cylinders and a plurality of storage tanks, wherein the high-pressure gas cylinders are arranged in the middle of the truss, the storage tanks are annularly arranged on the side part of the truss at intervals, the high-pressure gas cylinders are communicated with the storage tanks through pipelines, and each storage tank is connected with the main engine through a pipeline. The modular design is adopted, the landing buffer device, the power system, the bearing system, the energy system and the navigation guidance and control system are more reasonably arranged on the truss, the loads are more dispersed on the premise of ensuring the structure of the mars conveyor to be more compact, and the gravity center of the mars conveyor is reduced, so that the mars conveyor has higher bearing capacity. The invention is applied to the field of celestial surface flight.
Description
Technical field
The present invention relates to martian surface aircraft more particularly to a kind of rocket-powered formula Mars transporters.
Background technique
With the development of mars exploration technology, people gradually deepen the understanding of Mars.In order to further explore and develop
Mars realizes the manned next target stepped on fire and have become various countries' Mars Mission.It is mars exploration and exploitation that the mankind, which step on fire,
A crucial step, stepping on after fire still has multiple problems to need to solve.Include how how carrying out zone of ignorance, carry out goods and materials fortune if efficiently detecting
Send it is mobile with personnel, how support personnel's safety etc..The above problem is related with transport, therefore reliable means of transport is to solve
The key of the above problem.
Currently, the Marsokhod to have come into operation is mainly used for detecting there is no the means of transport of profession on Mars, transport
Ability is weak, speed is slow, obstacle climbing ability is limited, by taking " curiosity " number Marsokhod as an example, payload 75Kg, and level land maximum speed
4cm/s (Hou Jianwen, sunlight etc., deep space exploration: mars exploration [M], National Defense Industry Press, 2016)；NASA latter design
For " Mars scout " aircraft scheme of Mars exploration, lift is generated using rotor, it is close since martian surface atmosphere is thin
Degree is only the 1% of the earth, and the aerodynamics environment in martian surface flight is equivalent in the earth 30,000m high idle loop
Border need to realize mars by improving rotor revolving speed and reducing quality, and fuselage gross mass only 1.8kg is not suitable for transporting
(Xing Qiang Mars scout: the Mars helicopter project .2018 of NASA's madness).
Current research the result shows that, reusable carrier rocket has similar function, and technology maturation.Article
" Cui Naigang, Wu Rong, Wei Changzhu, Xu great Fu, bright VTOL Control System for Reusable Launch Vehicle current situation and key technology point
Analyse [J] aerospace general technical, 2018, (02): 27-42. " points out, New Shepard VTOL rocket can fly to
100km height, and realize vertical soft landing recycling, the Falcon9 rocket of Space-X company also achieves returning for LEO
It receives.But such rocket task object is different with Mars short distance transportation, and its structure is slender bodies, realizes traversing and decline all
Posture is needed substantially to adjust, furthermore its structure is complicated, volume is big, cost is high, launch preparation time is long.
In the research of other vertically taking off and landing flyer, the testing machine for planetary landing is more.Including tatou space flight development
Testing machine Pixel, Mod；The a series of experiments machine that Masten space system (MSS) company develops, representative are vertical rise
Fall fire arrow Xodiac and model machine XL-1T for moon landing；With invent herein it is the most similar be U.S. NASA develop dream
Refreshing number (Morpheus).Article " Tianlin County, the development of the U.S. An Jinkundeng morpheus planetary landing device prototype system and enlightenment [J]
Spacecraft engineering, 2015, (05): 105-112. " and article " P.McManamen John, A.Hurlbert Eric, Kroeger
Dennis.Development and Flight Operation of a 5lbf to 20lbf O2/CH4Roll Control
Engine for Project Morpheus[M].50th AIAA/ASME/SAE/ASEE Joint Propulsion
Conference；American Institute of Aeronautics and Astronautics.2014. " points out morpheus
Number platform mass is about 900kg, can at most carry 2900kg propellant and 180kg payload.Main structure using cross every
Plate form.Guidance, navigation and control subsystem and other electronic equipments are arranged on the siding above main structure, lower section installation 1
Platform sustainer and 4 propellant tanks.4 landing leg ends buffer overload equipped with honeycomb.Morpheus number uses and falls pressure
Formula supply system, and all engines share a set of supply system, alleviate quality.
Above-mentioned morpheus result of study shows that morpheus number uses cellular cushion structure, needs replacing after every subtask, inconvenient
In reuse；Its thrust chamber chamber pressure is low, and propellant specific impulse is small, and engine efficiency is not high, and morpheus number applies to ground experiment
Verifying；In addition, morpheus payload is small.
Summary of the invention
The object of the present invention is to provide a kind of rocket-powered formula Mars transporters, for overcoming Mars transport in the prior art
The defects such as machine bearing capacity is low, improve the bearing capacity of transporter, can efficiently complete martian surface transport task.
The technical solution adopted by the present invention is that:
A kind of rocket-powered formula Mars transporter, comprising:
Bearing system, the truss including the main support frame as Mars pallet；
Landing system is buffered, is located on truss for playing load-bearing, buffering work when Mars transporter takes off, lands
With；
Dynamical system, the sustainer including being located at truss bottom, for providing vertical direction and level side to transporter
To mobile thrust；
Energy resource system is located at purlin including high pressure gas cylinder and multiple tanks that can store propellant, the high pressure gas cylinder
The middle part of frame, the tank are spaced the side for being located at truss in a ring, and the high pressure gas cylinder and each tank pass through pipeline connection
With for being pressurized to tank, each tank is connected with sustainer by pipeline；
Navigational guidance and control system, are located on truss, for realizing the positioning of Mars transporter, constant speed and navigation.
As a further improvement of the above technical scheme, the bearing system further include:
Top load storehouse is arranged in truss top, for carrying Marsokhod and infrastructure goods and materials；
Base load storehouse, quantity be it is multiple, structure is suspended on truss bottom in a ring, for load detecting devices and basis
Construction machines.
As a further improvement of the above technical scheme, the buffering landing system includes that several intervals are located at truss side
Hydraulic leg, be equipped with buffer spring in the hydraulic cavities of the hydraulic leg, the top of the hydraulic leg and truss are hinged, institute
The bottom end for stating hydraulic leg is hinged with foot pad.
As a further improvement of the above technical scheme, the dynamical system further includes attitude control subsystem, the attitude control point
System includes several attitude control engines for being spaced and being located at the outside of each tank, and each attitude control engine composition ring structure is to be used for
Pose adjustment is carried out to Mars transporter, the high pressure gas cylinder is connected to be used to send out for attitude control by pipeline with each attitude control engine
Motivation provides working medium.
As a further improvement of the above technical scheme, the dynamical system further includes pressurization subsystem, the pressurization system
System is the electric-motor pump being located between tank and sustainer on pipeline.
As a further improvement of the above technical scheme, the dynamical system further includes change propulsive subsystem, and the change pushes away
Power subsystem is the adjustable Venturi tube that is located between tank and sustainer on pipeline for adjusting the propellant stream in pipeline
Amount.
As a further improvement of the above technical scheme, the sustainer is bifid pipe change propulsive sustainer.
Advantageous effects of the invention:
The present invention uses modularized design, by landing buffer system, dynamical system, bearing system, energy resource system and navigation
Guidance and control system is mounted on truss with more reasonable distribution mode, is guaranteeing that Mars conveyor designs are overall compact
Under the premise of load more disperse, reduce the center of gravity of Mars transporter so that Mars transporter have higher carrying energy
Power can efficiently complete martian surface transport task.
Detailed description of the invention
Fig. 1 is the present embodiment overall structure diagram
Fig. 2 is dynamical system and energy resource system structural schematic diagram；
Fig. 3 is bifid pipe ejector filler structural schematic diagram；
Fig. 4 is the present embodiment moderate heat star transporter flight course schematic diagram；
Fig. 5 is dynamical system thrust variation figure.
Specific embodiment
For the ease of implementation of the invention, it is further described below with reference to specific example.
A kind of rocket-powered formula Mars transporter as shown in Figs. 1-2, including buffering landing system, dynamical system, carrying
System, navigational guidance and control system and energy resource system.
Bearing system includes:
Truss 1, the main support frame as Mars transporter are laid out in " cross "；
Top load storehouse, be arranged in 1 top of truss and and it is not shown, for carrying Marsokhod and infrastructure goods and materials；
Base load storehouse 21 has multiple, is suspended on 1 bottom of truss in a ring, sets for loading detecting devices with infrastructure
It is standby.
By so that Mars conveyor designs are more compact, and dropping Mars transporter center of gravity for load dispersed placement
It is low, be conducive to the stabilization of Mars transporter.
Buffering landing system includes being located on truss 1 for playing load-bearing, buffering when Mars transporter takes off, lands
Effect.Buffering landing system includes several hydraulic legs 31 for being spaced and being located at 1 side of truss, is set in the hydraulic cavities of hydraulic leg 31
There is buffer spring, the top of hydraulic leg 31 and truss 1 are hinged, and the bottom end of hydraulic leg 31 is hinged with foot pad 32.
Specifically, each hydraulic leg 31 includes hydraulic stem 311 and telescopic rod 312, it is equipped in hydraulic stem 311 axial
Hydraulic cavities, be filled with hydraulic oil in hydraulic cavities, the top of hydraulic stem 311 is equipped with and the damping hole of hydraulic chamber into communication and and truss
1 is hinged, and the top of telescopic rod 312 is slidably connected in hydraulic cavities, and buffer spring is located in hydraulic cavities and the axis with hydraulic stem 311
To parallel.When Mars transporter takes off or lands, hydraulic oil and buffer spring collective effect, with more stable carrying with
Pooling feature.Meanwhile also hingedly there are two first hydraulic cylinder 33, one end of two first hydraulic cylinders 33 for the bottom end of hydraulic stem 311
The other end bifurcated of the same point being hinged on hydraulic stem 311, two first hydraulic cylinders 33 is hinged on the bottom end and part of truss 1
Truss 1 forms triangular structure, further improves the carrying and buffer capacity of hydraulic leg 31.Foot pad 32 is recessed cambered surface
Structure, effectively increase with the contact area on ground, enable transporter grease it in.
Navigational guidance includes: with control system
Subsystem is guided, is smoothly moved to target position from current location for realizing Mars transporter；
Navigation subsystem, by strap-down inertial, relative measurement navigation and terrain match guiding combination, for realizing fire
The accurate positioning of star transporter, constant speed；
Subsystem is controlled, for realizing the orbits controlling and gesture stability of Mars transporter；
The present embodiment midcourse guidance subsystem, navigation subsystem, control subsystem are diagram.
Navigational guidance and control system particularly further include for detect the small-scale obstacle and slope Flash laser radar with
And some other indispensable GNC equipment, camera is additionally provided on truss 1, for the shooting of aerial photograph and simple aerial
Detection.
Energy resource system includes high pressure gas cylinder 421 and the tank 422 that can store propellant, the quantity of high pressure gas cylinder 421
To be multiple, the quantity of tank 422 is multiple and interval is located at the side of truss 1 in a ring, and a part of tank is promoted for storing
Fuel in agent, another part tank are used to store the oxidant in propellant, and high pressure gas cylinder 421 passes through with each tank 422
Pipeline connection is with for being pressurized tank 422, and each tank 422 and dynamical system are by pipeline connection, in the present embodiment
The quantity of high pressure gas cylinder 421 is four middle parts that truss 1 is located in cross structure, and high pressure gas is helium, and tank 422 is spherical shape
Tank, tank 422 are arranged with thermal insulation layer for keeping the temperature to tank 422 outside.Propellant in the present embodiment is in view of fire
Manufacture in situ on star, therefore propellant uses liquid oxygen/liquid methane, the quantity of tank 422 is four and is in Roundabout structure
It is located at the side of truss 1, two of them are for storing liquid oxygen, such as two tanks on right side in Fig. 2；Other two is for storing liquid
Methane, such as two tanks 422 in left side in Fig. 2, the quantity and distributed architecture of high pressure gas cylinder 421 and tank 422 make Mars
The structure of transporter is more compact, while load is more dispersed.The wall of thrust chamber 412 is sandwich, in power system operational
When, by pipeline directly through entering dynamical system, liquid methane first passes through re-generatively cooled after pipeline, subsequently enters power liquid oxygen
System, to effectively promote the enthalpy of liquid methane.
Dynamical system includes sustainer, attitude control subsystem, pressurization subsystem and change propulsive subsystem；
Sustainer includes ejector filler 411, igniter and the thrust chamber 412 for being located at 1 bottom of truss, thrust chamber 412
One end is connected to ejector filler 411, and towards the bottom of Mars transporter, igniter is located in thrust chamber 412 and does not scheme the other end
Show.Thrust chamber 412 includes the combustion chamber 4121 being fixedly linked and jet pipe 4122, and ejector filler 411 is connected to combustion chamber 4121, is fired
The bottom of 4121 hinged truss 1 of room is burnt, combustion chamber 4121 is equipped with and second hydraulic cylinder (not shown) is for jet pipe
4122 spray angle is adjusted, and combustion chamber 4121 is cylindrical structure, and the quantity of second hydraulic cylinder is two and interval is set
On the outer wall of combustion chamber 4121, the angle of line is 90 ° between 4121 axis of two second hydraulic cylinders and combustion chamber, the second liquid
The fixing end of cylinder pressure and the bottom of truss 1 are hinged, and the telescopic end of second hydraulic cylinder and the outer wall of combustion chamber 4121 are hinged, the second liquid
Cylinder pressure is connected with control subsystem control.
Jet pipe 4122 is campanula halleri Halleri, available higher ejection efficiency and the length for shortening jet pipe 4122.Tail
4122 converging portion of jet pipe uses two arc transitions, and expansion segment adds parabolic segment using arc section.
Attitude control subsystem includes several attitude control engines 431, and 431 quantity of attitude control engine in the present embodiment is 12,
Corresponding control valve 432 is designed on each attitude control engine 431, with the starting or closing for controlling attitude control engine 431.
Multiple attitude control engines are arranged in the outside spacers of tank 422, and each attitude control engine 431 forms ring structure for transporting to Mars
Defeated machine carries out pose adjustment, and high pressure gas cylinder 421 is connected with each attitude control engine 431 by pipeline to be used for as attitude control engine
431 provide working medium.
Pressurization subsystem be located on the pipeline between tank 422 and ejector filler 411 with for the propellant in pipeline into
Row pressurization.Being pressurized subsystem is integrated electric-motor pump, and integrated electric motor pump includes being driven be connected direct current generator 441 and centrifugal pump
442, direct current generator 441 is electrical connected by inverter 443 with power supply 444, and inverter 443 is used to direct current being converted to exchange
Electricity, centrifugal pump 442 are located on the pipeline between tank 422 and ejector filler 411 with for being pressurized to the propellant in pipeline,
Direct current generator 441 is connected with control subsystem control.In the present embodiment, two tanks for storing liquid oxygen share a pair of of centrifugal pump
With direct current generator, two tanks for storing liquid methane share another pair centrifugal pump and direct current generator, and two direct current generators share one
A power supply and inverter.
Change propulsive subsystem is located on the pipeline between tank 422 and ejector filler 411 for the propellant in pipeline
Flow is controlled, and in the present embodiment, two tanks 422 for storing liquid oxygen share a set of change propulsive subsystem, stores liquid methane
Two tanks 422 share another set of change propulsive subsystem.
Change propulsive system is adjustable Venturi tube, specifically includes Venturi tube 451, plug cone and stepper motor, Venturi tube 451 and is located at
On pipeline between tank 422 and ejector filler 411, plug cone is located in Venturi tube 451, and stepper motor is located at outside Venturi tube 451 simultaneously
Be connected by drive rod with plug cone transmission with for controlling the propellant flow rate in Venturi tube 451, drive rod one end and
The output end of stepper motor is connected, and the other end is connected after the wall of Venturi tube 451 with plug cone, stepper motor and control subsystem
Control is connected.
With reference to Fig. 3, ejector filler 411 is bifid pipe ejector filler, and bifid pipe ejector filler includes spray general pipeline 4111, the first spray
Pipe 4112 and the second injection into orbit pipe 4113, the head end and tank 422 of spray general pipeline 4111 pass through pipeline connection, the first injection into orbit pipe 4112
Head end, the second injection into orbit pipe 4113 head end be connected to respectively with the tail end of spray general pipeline 4111, the tail end of the first injection into orbit pipe 4112,
The tail end of second injection into orbit pipe 4113 is communicated with thrust chamber 412 respectively, and the first injection into orbit pipe 4112 is equipped with the first solenoid valve 4114, the
One solenoid valve 4114 is connected with control subsystem control.Propellant flow rate it can be become smaller in pipeline using bifid pipe ejector filler
In the case of, it keeps injection pressure drop constant, keeps good atomization, so that sustainer is that bifid pipe change propulsive master starts
Machine.
It is additionally provided on pipeline between tank 422 and ejector filler 411:
First plus valve 461 is let out, for filling to the propellant in tank 422；
Second solenoid valve 462, for controlling releasing for propellant in tank 422；
Filter 463, for preventing dirt, particulate matter or fragment from entering thrust chamber 412；
Turbine flowmeter 464, for monitoring volume flow in pipeline, and can indirect monitoring mixing ratio situation of change；
Compensator 465, for compensation conduit radially, axially with angular displacement deviation；
Solenoid valve 466 is released in pre-cooling, for pipeline to be pre-chilled；
First plus let out valve 461, second solenoid valve 462, pre-cooling release solenoid valve 466 respectively with control subsystem control phase
Even.
With reference to Fig. 3, in the present embodiment, each tank is correspondingly provided with a set of first plus lets out valve, second solenoid valve, filtering
Device, two tanks for storing liquid oxygen share a set of turbine flowmeter, solenoid valve is released in compensator, pre-cooling, store the two of liquid methane
A tank shares another set of turbine flowmeter, solenoid valve is released in compensator, pre-cooling.
On pipeline between high pressure gas cylinder 421 and tank 422 and between high pressure gas cylinder 421 and attitude control engine 431
It is equipped on pipeline:
Second plus valve 471 is let out, for filling to the high pressure gas in high pressure gas cylinder 421；
Third solenoid valve 472, for controlling releasing for 421 mesohigh gas of high pressure gas cylinder；
Pressure reducer 473, for reducing the high-pressure gas pressure in pipeline；
Second plus let out valve 471, third solenoid valve 472 respectively with control subsystem control be connected.
With reference to Fig. 3, in the present embodiment, four high pressure gas cylinders share one second plus let out valve, third solenoid valve, high pressure gas
There is a pressure reducing valve on pipeline between bottle 421 and attitude control engine 431, on the pipeline between high pressure gas cylinder 421 and tank 422
There are two pressure reducing valves.
The course of work of dynamical system are as follows:
After dynamical system starting, propellant is discharged from tank 422, arrives later by second solenoid valve 462, filter 463
Before centrifugal pump 442, direct current generator 441 drives centrifugal pump 442 to be pressurized respectively to liquid oxygen and methane, and pressurized propellant flows through whirlpool
Valve before flowmeters 464, Venturi tube 451, compensator 465 and spray, liquid oxygen spray into combustion chamber 4121 by bifid pipe ejector filler,
Liquid methane is used for re-generatively cooled, therefore the interlayer that be introduced into push-in room is cooling, then enters thrust chamber by bifid pipe ejector filler
412, after igniter fire success, dynamical system is started to work.
When continuous thrust, 442 revolving speed of centrifugal pump is constant, and guidance subsystem is transferred to navigation after making change signal
Subsystem, navigation subsystem give control one digital signal being continuously reduced of subsystem, and control subsystem will be continuously reduced number
Signal is converted into the electric signal of stepper motor, and stepper motor drives the continuous movement of plug cone, subtracts flow in Venturi tube 451 linearly
Small, so that thrust be made linearly to reduce, when flow reduces half, control subsystem control bifid pipe ejector filler closes the first injection into orbit pipe
The first solenoid valve 4114 on 4112, propellant carries out spray from the second injection into orbit pipe 4113 at this time, it is ensured that injection pressure drop is constant, protects
Hold good atomization.
When changing thrust direction, guidance subsystem is transferred to navigation subsystem, navigation subsystem after making change signal
Control subsystem is sent by 4122 swinging signal of jet pipe, control subsystem is believed to the second hydraulic cylinder on combustion chamber 4121
Number, second hydraulic cylinder is flexible to make jet pipe 4122 swing to corresponding position, to keep 4122 thrust direction change of jet pipe specified
Angle.
In Mars transporter flight course, the sensor on navigation subsystem detects that Mars transporter state of flight has
Deviation is instructed according to navigation subsystem, and the control valve 432 of control subsystem control attitude control engine 431 opens rapidly a timing
Between then shut rapidly, the high-pressure helium in high pressure gas cylinder 421 is depressurized by pressure reducing valve, by the preceding valve of spray, is started into attitude control
Machine 431 generates impulse force, by Mars transporter state revision.
It is described below using crossing mountain range as transporter function of the flight task to the present embodiment:
Transporter takes off gross mass 3t, carries 1450kg propellant, specific flight course is as shown in figure 4, in flight course
Thrust variation is as shown in Figure 5.Igniter fire when taking off, dynamical system provide the thrust of maximum 22.8kN.Ascent stage, transporter
Accelerated in 5s to 46m, adjusted by propellant flow rate, thrust step changes to 15.1kN, after vary continuously to 9.46kN,
Transporter rises to 1096m, keeps thrust, and transporter deceleration rises to 1961m hovering, which consumes propellant in total
350.2kg.Traversing section, the second hydraulic cylinder on combustion chamber 4121 acts on thrust chamber 412, so that jet pipe 4122 is deflected 5 °, pushes away
Power is constant, and transporter accelerates traversing 1005m, and latter 5 ° of 4122 reverse deflection of jet pipe, the at the uniform velocity traversing 36m of the process transporter, after
Transporter deceleration is traversing to 1996m, and horizontal direction speed is reduced to 0, at this point, jet pipe 4122 restores vertically, the process is in total
Consume propellant 440.5kg.Landing section, after transporter declines 114m, foot pad 32 and ground face contact, hydraulic leg 31 play work
With buffering overload, the process consumes propellant 112.3kg.
If flight course meets disturbance, so that transporter tilts, attitude control engine 431 works, with transporter in axis and certain
For one attitude control engine, 431 plane is tilted, the downward jet of side attitude control engine 431, symmetrical attitude control is sprayed upwards therewith
Gas after a period of time, is regurgitated simultaneously, and transporter is made to restore normal.
In entire flight course, tank 422 persistently provides propellant, consumes propellant about 900kg, residual propellant in total
550kg meets return demand.
Above-mentioned flight course design payload is 900kg.
To sum up, which can carry 900kg payload, and vertical ascent 2000m is completed in 300s, traversing
2000m, and the traversing change decline in side, the flight course of final grease it in.
Contain the explanation of the preferred embodiment of the present invention above, this be for the technical characteristic that the present invention will be described in detail, and
Be not intended to for summary of the invention being limited in concrete form described in embodiment, according to the present invention content purport carry out other
Modifications and variations are also protected by this patent.The purport of the content of present invention is to be defined by the claims, rather than by embodiment
Specific descriptions are defined.
Claims (7)
1. a kind of rocket-powered formula Mars transporter characterized by comprising
Bearing system, the truss including the main support frame as Mars pallet；
Landing system is buffered, is located on truss for playing load-bearing, buffer function when Mars transporter takes off, lands；
Dynamical system, the sustainer including being located at truss bottom, for both vertically and horizontally being moved to transporter offer
Dynamic thrust；
Energy resource system is located at truss including high pressure gas cylinder and multiple tanks that can store propellant, the high pressure gas cylinder
Middle part, the tank are spaced the side for being located at truss in a ring, the high pressure gas cylinder and each tank by pipeline connection with
It is pressurized in tank, each tank is connected with sustainer by pipeline；
Navigational guidance and control system, are located on truss, for realizing the positioning of Mars transporter, constant speed and navigation.
2. rocket-powered formula Mars transporter according to claim 1, which is characterized in that the bearing system further include:
Top load storehouse is arranged in truss top, for carrying Marsokhod and infrastructure goods and materials；
Base load storehouse, quantity be it is multiple, structure is suspended on truss bottom in a ring, for loading detecting devices and infrastructure
Equipment.
3. rocket-powered formula Mars transporter according to claim 1, which is characterized in that if the buffering landing system includes
It is dry to be spaced the hydraulic leg for being located at truss side, buffer spring, the hydraulic leg are equipped in the hydraulic cavities of the hydraulic leg
Top and truss it is hinged, the bottom end of the hydraulic leg is hinged with foot pad.
4. any one of -3 rocket-powered formula Mars transporter according to claim 1, which is characterized in that the dynamical system is also
Including attitude control subsystem, the attitude control subsystem includes several attitude control engines for being spaced and being located at the outside of each tank, each appearance
Control cluster engine circularizes structure for carrying out pose adjustment, the high pressure gas cylinder and each attitude control engine to Mars transporter
It is connected by pipeline to be used to provide working medium for attitude control engine.
5. any one of -3 rocket-powered formula Mars transporter according to claim 1, which is characterized in that the dynamical system is also
Including being pressurized subsystem, the pressure charging system is the electric-motor pump being located between tank and sustainer on pipeline.
6. any one of -3 rocket-powered formula Mars transporter according to claim 1, which is characterized in that the dynamical system is also
Including change propulsive subsystem, the change propulsive subsystem be the adjustable Venturi tube that is located between tank and sustainer on pipeline with
For adjusting the propellant flow rate in pipeline.
7. rocket-powered formula Mars transporter according to claim 6, which is characterized in that the sustainer is the change of bifid pipe
Thrust sustainer.
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| CN110262528A (en) * | 2019-05-30 | 2019-09-20 | 北京空间飞行器总体设计部 | Take off-landing-of a kind of month surface detector moves implementation method |
| CN110979746A (en) * | 2019-12-18 | 2020-04-10 | 北京航空航天大学 | Rocket three-stage solid-liquid main power and attitude control integrated system and method thereof |
| CN112963269A (en) * | 2021-01-19 | 2021-06-15 | 中国人民解放军63921部队 | Carrier rocket base-level vertical recovery method using traveling engine |
| CN113212808A (en) * | 2021-05-08 | 2021-08-06 | 北京格锐德科技有限公司 | Carrier rocket based on extrusion engine |
| CN114019824A (en) * | 2021-09-27 | 2022-02-08 | 北京控制工程研究所 | Modelica-based star vehicle moving process simulation system and construction method |
| CN114353604A (en) * | 2021-12-15 | 2022-04-15 | 北京航空航天大学 | Experimental platform for simulating vector thrust redundancy configuration of recoverable rocket |
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| CN110262528B (en) * | 2019-05-30 | 2022-07-29 | 北京空间飞行器总体设计部 | Takeoff-landing-movement implementation method of lunar surface detector |
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| CN110979746B (en) * | 2019-12-18 | 2021-05-28 | 北京航空航天大学 | Rocket three-stage solid-liquid main power and attitude control integrated system and method thereof |
| CN112963269A (en) * | 2021-01-19 | 2021-06-15 | 中国人民解放军63921部队 | Carrier rocket base-level vertical recovery method using traveling engine |
| CN112963269B (en) * | 2021-01-19 | 2022-04-15 | 中国人民解放军63921部队 | Carrier rocket base-level vertical recovery method using traveling engine |
| CN113212808A (en) * | 2021-05-08 | 2021-08-06 | 北京格锐德科技有限公司 | Carrier rocket based on extrusion engine |
| CN114019824A (en) * | 2021-09-27 | 2022-02-08 | 北京控制工程研究所 | Modelica-based star vehicle moving process simulation system and construction method |
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| CN114353604A (en) * | 2021-12-15 | 2022-04-15 | 北京航空航天大学 | Experimental platform for simulating vector thrust redundancy configuration of recoverable rocket |
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