CN109018444A - Rocket-powered mars transporter power system - Google Patents
Rocket-powered mars transporter power system Download PDFInfo
- Publication number
- CN109018444A CN109018444A CN201810872988.9A CN201810872988A CN109018444A CN 109018444 A CN109018444 A CN 109018444A CN 201810872988 A CN201810872988 A CN 201810872988A CN 109018444 A CN109018444 A CN 109018444A
- Authority
- CN
- China
- Prior art keywords
- subsystem
- pipeline
- mars
- tank
- transporter
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000945 filler Substances 0.000 claims description 41
- 239000003380 propellant Substances 0.000 claims description 32
- 238000002485 combustion reaction Methods 0.000 claims description 24
- 238000005183 dynamical system Methods 0.000 claims description 24
- 238000002347 injection Methods 0.000 claims description 23
- 239000007924 injection Substances 0.000 claims description 23
- 230000008859 change Effects 0.000 claims description 22
- 239000007921 spray Substances 0.000 claims description 19
- 230000001141 propulsive effect Effects 0.000 claims description 18
- 238000001816 cooling Methods 0.000 claims description 9
- 230000032258 transport Effects 0.000 claims description 8
- 238000011049 filling Methods 0.000 claims description 6
- 238000012544 monitoring process Methods 0.000 claims description 6
- 238000006073 displacement reaction Methods 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 3
- 239000003638 chemical reducing agent Substances 0.000 claims description 3
- 239000012634 fragment Substances 0.000 claims description 3
- 238000002156 mixing Methods 0.000 claims description 3
- 239000013618 particulate matter Substances 0.000 claims description 3
- 241000123667 Campanula Species 0.000 claims description 2
- 238000009413 insulation Methods 0.000 claims description 2
- 238000010276 construction Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 description 26
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 22
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 12
- 239000007788 liquid Substances 0.000 description 12
- 230000006872 improvement Effects 0.000 description 9
- 238000011161 development Methods 0.000 description 6
- 230000018109 developmental process Effects 0.000 description 6
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 241000254032 Acrididae Species 0.000 description 3
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 3
- 238000005119 centrifugation Methods 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000001307 helium Substances 0.000 description 2
- 229910052734 helium Inorganic materials 0.000 description 2
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000004064 recycling Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 101000603420 Homo sapiens Nuclear pore complex-interacting protein family member A1 Proteins 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 102100038845 Nuclear pore complex-interacting protein family member A1 Human genes 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 210000003746 feather Anatomy 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- KFZMGEQAYNKOFK-UHFFFAOYSA-N isopropyl alcohol Natural products CC(C)O KFZMGEQAYNKOFK-UHFFFAOYSA-N 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000010200 validation analysis Methods 0.000 description 1
Classifications
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides a rocket-powered Mars transporter power system, which comprises a main engine, an energy subsystem, an attitude control subsystem, a pressurization subsystem and a variable thrust subsystem, wherein the main engine is connected with the energy subsystem; the power subsystem comprises an injector, an igniter and a thrust chamber; the energy subsystem comprises a battery, a high-pressure gas cylinder and a storage box, wherein the high-pressure gas cylinder is communicated with the storage box through a pipeline, and the storage box is communicated with the injector through a pipeline; the attitude control subsystem comprises a plurality of attitude control engines, wherein the attitude control engines are annularly arranged at the side part of the Mars conveyor at intervals, and the high-pressure gas cylinder is connected with the attitude control engines through pipelines. The attitude control engine and the storage box share one set of high-pressure gas cylinder, the structure of the power system is simplified, the pressure of the storage box is reduced through the pressurization of the pressurization subsystem, the quality of the storage box is reduced, the pressure of a thrust chamber is improved, the power system has an attitude adjustment function through the attitude control subsystem, and the power system has a variable thrust function through the variable thrust subsystem. The invention is applied to the field of celestial surface flight.
Description
Technical field
The present invention relates to celestial body surface flight domain more particularly to a kind of rocket-powered formula Mars transporter dynamical systems.
Background technique
Detection result for many years shows there are water-ice, carbon dioxide, a small amount of oxygen on Mars, may be the mankind in fire
Star long term survival provides support.Each spacefaring nation of our times is all actively developing mars exploration plan, and China also announces
The task of the year two thousand twenty development mars exploration.It is matter of time that the mankind, which step on fire, and will face many new challenges after stepping on fire.It is unknown
The transport of goods and materials between the efficient detection in region, base, the mobile etc. of personnel must all solve.The key solved these problems exists
In possessing reliable delivery vehicle, it is seen then that developing Mars transporter has great meaning for the Mars development strategy of human future
Justice.
Currently, not having professional traffic machine on Mars, Marsokhod is mainly used for detecting, and transport capacity is weak, speed is slow, obstacle detouring
Ability is limited, is not able to satisfy the mission requirements of efficient transportation, it would be desirable to one kind can fast reserve, and larger quality can be loaded
Tool, aircraft is obviously more suitable for.Martian surface atmosphere is thin, and aerodynamic force formula aircraft will realize above-mentioned big load transport
Task difficulty is very big, and therefore, rocket-powered formula aircraft becomes primary selection.In conclusion Mars transporter must have with
Lower feature: VTOL and crossrange maneuvering under the support of change propulsive vector rocket engine；Load is larger；It is reusable；Easily
In maintenance and maintenance；Structure is simple；Cost is relatively low；Short-distance flight etc. can be achieved.
Scheme similar in technology is broadly divided into two major classes at present.
The first kind is reusable rocket.1) the fast sail of the Delta of McDonnell-Douglas Corporation is that a kind of provided by rocket engine is moved
The Single Stage To Orbit of power, VTOL, the vehicle reused completely.4.1 meters of diameter, height 12 meters, nearly 19 tons of quality of taking off,
Although the project is finally halted by U.S. army, the development that its key technology remains as subsequent recovery rocket provides reference.2)
Blue origin company is based on BE rocket series engine, successively has developed the Charon VTOL using hydrogen peroxide as propellant
The Goddard model of model machine and hydrogen peroxide kerosene bipropellant, both models all rest on the ground validation stage, most
Big only hundred meters or so of flying height.It is subsequent to have carried out the various types of developments of NewShepard, it is pushed away using liquid oxygen liquid hydrogen double elements
Into agent, can 20~100% a wide range of depth flow adjust, thrust has reached 490kN, has realized the more of hundred kilometers of grade height
Secondary use, so that the model becomes the first vertically taking off and landing flyer into space.3) SpaceX is so far at this
The farthest private company technically walked." heavy falcon " carrier rocket completes the complete recycling mark of two pieces and booster rocket
Will rocket recovery technology be mature on the whole, for the dynamic VTOL feasibility of the verifying anti-pushing of engine, SpaceX is in falcon -9
On the basis of the sub- level-one of rocket, " grasshopper " (Grasshopper), F9R Dev experimental prototype, Grasshopper are successively developed
8 flight tests are completed, returning exactly under low clearance and low-speed conditions and throwing power are demonstrated.4) Japanese space agency
(JAXA) Control System for Reusable Launch Vehicle (RVT) project has been carried out.During project, 4 kinds of vehicles: RVT#1, RVT# are had developed altogether
2, RVT#3, RVT#4, it is therefore intended that solve the technological challenge that the following reusable carrier rocket is faced.Known total progress
14 tests, to engine performance, turbine pump igniting etc. is probed into and has been studied, and has laid base for its future development
Plinth.5) first domestic private space flight company tail feather visitor space flight had developed RLV-T series reusable rocket, current energy from 2014
Enough realize vertical ascent, hovering is traversing, declines basic function, but apart from real launch recycling is realized, there are also very long roads
It walks.From the point of view of current research, the dynamical system thrust of reusable rocket is larger, can be realized transportation function, but fly
Structure is complicated for device itself, volume is big, cost is high, launch preparation time is long, is generally not used for short distance transportation, on the other hand, because
It is slender bodies for rocket body structure, realizes that traversing and decline requires posture and substantially adjusts.
Second class is VTOL lander.1) the Pixel series of tatou space flight development uses a Variable Thrust Engine,
Using liquid-oxygen-alcohol as propellant, take-off weight 667.5kg, motor power 13.35kN (4:1 is adjustable), load 24.5kg.It should
The lander of series adjusts to realize aerial fixed point and lateral displacement by vector controlled and flow.2)Masten space
The newest VTOL model machine Xodiac of system (MSS) is using liquid oxygen isopropanol as propellant, thrust 5.34kN, verifying height
496m, verifying side are adjusted by vector controlled and flow away from 301m to realize aerial fixed point and lateral displacement.3) morpheus of NASA
Number planetary landing device falls pressure type variable thrust rocket engine using liquid oxygen/liquid methane, and tank pressure is high, and quality is big, burning
Chamber pressure is low, specific impulse is low.Thrust no-load voltage ratio 4:1,400 meters of maximum transversal moving distance, can at most be carried by 400 meters of ceiling altitude
180kg payload.Main purpose is to verify liquid oxygen liquid methane change propulsive technology and independent landing and risk averse skill
Art declines engine for star landing and provides technical support.4) NASA and other mechanisms have also carried out Lunar Robot landing, fortune
The project of delivery object.XL-1 is small-sized, special purpose a shipping Lunar satellite orbit, by 100kg load transportation to the moon
Surface, active force are 4 MXP-351 engines.Xeus is a moon landing verification machine, by MSS and ULA cooperation research and development.It can
In moon landing, at most to carry 10t load, load is reduced to 5t when reuse.Find out from these researchs, VTOL is landed
Device dynamical system thrust is smaller, but aircraft load is small, flying distance is short, and mainly verification machine, it is therefore an objective to verify related skill
Art.
Summary of the invention
The object of the present invention is to provide a kind of rocket-powered formula Mars transporter dynamical systems, for overcoming in the prior art
The defects of dynamical system thrust is smaller, so that Mars transporter has higher bearing capacity while keeping maneuverability,
Martian surface transport task can efficiently be completed.
The technical solution adopted by the present invention is that:
A kind of rocket-powered formula Mars transporter dynamical system, including sustainer, energy subsystem, attitude control subsystem,
It is pressurized subsystem, change propulsive subsystem and control subsystem；
The sustainer includes ejector filler, igniter and the thrust chamber for being located at Mars transport motor spindle, the thrust
One end of room is connected to ejector filler, and the other end is located in thrust chamber towards the bottom of Mars transporter, the igniter；
The energy subsystem includes battery, high pressure gas cylinder and the tank that can store propellant, the high pressure gas cylinder
With tank by pipeline connection to be used to be pressurized tank, the tank and ejector filler pass through pipeline connection；
The attitude control subsystem includes several attitude control engines, and each attitude control engine is spaced is located at Mars transporter in a ring
Side with for carrying out pose adjustment to Mars transporter, the high pressure gas cylinder and each attitude control engine by pipeline be connected with
For providing working medium for attitude control engine；
The pressurization subsystem is located on the pipeline between tank and ejector filler for carrying out to the propellant in pipeline
Pressurization；
The change propulsive subsystem is located on the pipeline between tank and ejector filler for the propellant stream in pipeline
Amount is controlled；
The pressurization subsystem, change propulsive subsystem are electrical connected with battery respectively；
The control subsystem respectively with sustainer, energy subsystem, attitude control subsystem, pressurization subsystem, change propulsive
Subsystem control is connected.
As a further improvement of the above technical scheme, the change propulsive system includes Venturi tube, plug is bored and stepper motor,
The Venturi tube is located on the pipeline between tank and ejector filler, and the plug cone is located in Venturi tube, and the stepper motor is located at
Venturi tube is outer and bores by drive rod with plug to be driven and is connected with for controlling the propellant flow rate in Venturi tube, the step
It is connected into motor with control subsystem control, the stepper motor is electrical connected with battery.
As a further improvement of the above technical scheme, the ejector filler is bifid pipe ejector filler, the bifid pipe spray
Device includes spray general pipeline, the first injection into orbit pipe and the second injection into orbit pipe, and the head end and tank of the spray general pipeline passes through pipeline connection, institute
The head end of the head end, the second injection into orbit pipe of stating the first injection into orbit pipe is connected to the tail end of spray general pipeline respectively, first injection into orbit pipe
Tail end, the second injection into orbit pipe tail end communicated respectively with thrust chamber, first injection into orbit pipe be equipped with the first solenoid valve, described first
Solenoid valve is connected with control subsystem control.
As a further improvement of the above technical scheme, the pressurization subsystem is integrated electric-motor pump, the integration
Electric-motor pump includes brshless DC motor and centrifugal pump, and the brshless DC motor is connected with centrifugation pump drive, and the centrifugal pump is set
With for being pressurized to the propellant in pipeline on pipeline between tank and ejector filler, the brshless DC motor and control
Subsystem control processed is connected, and the brshless DC motor is electrical connected with battery.
As a further improvement of the above technical scheme, it is additionally provided on the pipeline between the tank and ejector filler:
First plus valve is let out, for filling to the propellant in tank；
Second solenoid valve, for controlling releasing for propellant in tank；
Filter, for preventing dirt, particulate matter or fragment from entering thrust chamber；
Turbine flowmeter, for monitoring volume flow in pipeline, and can indirect monitoring mixing ratio situation of change；
Compensator, for compensation conduit radially, axially with angular displacement deviation；
Solenoid valve is released in pre-cooling, for pipeline to be pre-chilled；
Described first plus let out valve, second solenoid valve, pre-cooling release solenoid valve and are connected respectively with control subsystem control.
As a further improvement of the above technical scheme, on the pipeline between the high pressure gas cylinder and tank and high pressure gas
It is equipped on pipeline between bottle and attitude control engine:
Second plus valve is let out, for filling to the high pressure gas in high pressure gas cylinder；
Third solenoid valve, for controlling releasing for high pressure gas cylinder mesohigh gas；
Pressure reducer, for reducing the high-pressure gas pressure in pipeline；
Described second plus let out valve, third solenoid valve respectively with control subsystem control be connected.
As a further improvement of the above technical scheme, the tank is spherical tank, is arranged with outside the tank heat-insulated
Layer.
As a further improvement of the above technical scheme, the thrust chamber includes the combustion chamber being fixedly linked and jet pipe,
The ejector filler and combustion chamber, the bottom of the hinged Mars transporter in combustion chamber, the combustion chamber are equipped with electronic liquid
Compression bar for the spray angle to jet pipe to be adjusted, the fixing end of the electric hydaulic bar and the bottom of Mars transporter
Hingedly, the telescopic end of the electric hydaulic bar and the outer wall of combustion chamber are hinged, and the control subsystem and electric hydaulic bar control
It is connected with flexible for controlling electric hydaulic bar.
As a further improvement of the above technical scheme, the combustion chamber is cylindrical structure, and the jet pipe is bell
Structure.
As a further improvement of the above technical scheme, the quantity of the electric hydaulic bar is two and interval is located at burning
On the outer wall of room.
Advantageous effects of the invention:
The present invention is in dynamical system collectivity Scheme Design, by making attitude control engine and tank share a set of high pressure gas
Bottle, to simplify the structure of dynamical system, while the pressurization by being pressurized subsystem reduces tank pressure, alleviates tank
Quality improves thrust chamber pressure, makes dynamical system have the function of pose adjustment by attitude control subsystem, and push away by becoming
Power subsystem makes dynamical system have the function of efficient, reliable change propulsive, so that Mars transporter is keeping maneuverability
It is provided simultaneously with higher bearing capacity, can efficiently complete martian surface transport task.
Detailed description of the invention
Fig. 1 is the present embodiment overall structure diagram；
Fig. 2 is bifid pipe ejector filler structural schematic diagram.
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 dynamical system as shown in Figs. 1-2, including sustainer, the energy point is
System, attitude control subsystem are pressurized subsystem, change propulsive subsystem and control subsystem, and the control subsystem in the present embodiment is several
Word controller and and it is not shown, be electrical connected with the master control of Mars transporter.
Sustainer include ejector filler 11, igniter and be located at Mars transport motor spindle thrust chamber, the one of thrust chamber
End is connected to ejector filler 11, and towards the bottom of Mars transporter, igniter is located in thrust chamber and and not shown the other end.Thrust
Room includes the combustion chamber 121 being fixedly linked and jet pipe 122, and ejector filler 11 is connected to combustion chamber 121, the hinged fire in combustion chamber 121
The bottom of star transporter, combustion chamber 121 is equipped with and electric hydaulic bar (not shown) is for the spray angle to jet pipe 122
It is adjusted, combustion chamber 121 is cylindrical structure, and the quantity of electric hydaulic bar is two and interval is located at the outer of combustion chamber 121
On wall, the angle of line is 90 ° between 121 axis of two electric hydaulic bars and combustion chamber, the fixing end and fire of electric hydaulic bar
The bottom of star transporter is hinged, and the telescopic end of electric hydaulic bar and the outer wall of combustion chamber 121 are hinged, electric hydaulic bar and control point
System control is connected.
Jet pipe 122 is campanula halleri Halleri, available higher ejection efficiency and the length for shortening jet pipe 122.Tail spray
122 converging portion of pipe uses two arc transitions, and expansion segment adds parabolic segment using arc section.
Energy subsystem includes high pressure gas cylinder 21 and the tank 22 that can store propellant, high pressure gas cylinder 21 and tank 22
By pipeline connection to be used to be pressurized tank 22, tank 22 and ejector filler 11 pass through pipeline connection, height in the present embodiment
The quantity of air bottle 21 is four, and high pressure gas is helium.Tank 22 is spherical tank, is arranged with thermal insulation layer 221 outside tank 22
With for being kept the temperature to tank 22, the quantity of tank 22 be it is multiple, a part of tank is used to store the fuel in propellant, separately
A part of tank is used to store the oxidant in propellant.Propellant in the present embodiment considers the manufacture in situ on Mars,
Therefore propellant uses liquid oxygen/liquid methane, and the quantity of tank 22 is four, and two of them are used to store liquid oxygen, as shown in figure 1 right side
Two tanks；Other two is used to store liquid methane, as shown in figure 1 two tanks in left side.The wall of thrust chamber is sandwich,
In power system operational, liquid oxygen is directly over ejector filler 11 by pipeline and enters combustion chamber 121, and liquid methane is first after pipeline
Re-generatively cooled is carried out by the interlayer of the wall of thrust chamber, ejector filler 11 is then passed through and enters combustion chamber 121, to effectively be promoted
The enthalpy of liquid methane.
Attitude control subsystem includes several attitude control engines 31, and 31 quantity of attitude control engine in the present embodiment is 12, often
Corresponding control valve 32 is designed on a attitude control engine 31, with the starting or closing for controlling attitude control engine 31.Each appearance
Control engine 31 is spaced in a ring is located at the side of Mars transporter for carrying out pose adjustment, high pressure gas to Mars transporter
Bottle 21 is connected to be used to provide working medium for attitude control engine 31 by pipeline with each attitude control engine 31.
Pressurization subsystem is located on the pipeline between tank 22 and ejector filler 11 for carrying out to the propellant in pipeline
Pressurization.Being pressurized subsystem is integrated electric-motor pump, and integrated electric motor pump includes being driven be connected brshless DC motor 41 and centrifugal pump
42, brshless DC motor 41 is electrical connected by inverter 43 with battery 44, and inverter 43 is used to direct current being converted to exchange
Electricity, centrifugal pump 42 are located on the pipeline between tank 22 and ejector filler 11 with for being pressurized to the propellant in pipeline, nothing
Brushless motor 41 is connected with control subsystem control.In the present embodiment, two tanks for storing liquid oxygen share a pair of of centrifugation
Pump and brshless DC motor, two tanks for storing liquid methane share another pair centrifugal pump and brshless DC motor, and two brushless
Direct current generator shares a battery and inverter.
Change propulsive subsystem is located on the pipeline between tank 22 and ejector filler 11 for the propellant stream in pipeline
Amount is controlled, and in the present embodiment, two tanks for storing liquid oxygen share a set of change propulsive subsystem, two for storing liquid methane
Tank shares another set of change propulsive subsystem.Change propulsive system includes Venturi tube 51, plug cone and stepper motor, stepper motor and electricity
Pond is electrical connected, and Venturi tube 51 is located on the pipeline between tank 22 and ejector filler 11, and plug cone is located in Venturi tube 51, stepping electricity
Machine is located at outside Venturi tube 51 and is connected with plug cone transmission for the propellant flow rate progress in Venturi tube 51 by drive rod
Control, drive rod one end are connected with the output end of stepper motor, and the other end is connected after the wall of Venturi tube 51 with plug cone, stepping
Motor is connected with control subsystem control.
With reference to Fig. 2, ejector filler 11 is bifid pipe ejector filler, and bifid pipe ejector filler includes spray general pipeline 111, the first injection into orbit pipe
The head end and tank 22 of 112 and second injection into orbit pipe 113, spray general pipeline 111 by pipeline connection, the head end of the first injection into orbit pipe 112,
The head end of second injection into orbit pipe 113 is connected to the tail end of spray general pipeline 111 respectively, tail end, the second injection into orbit pipe of the first injection into orbit pipe 112
113 tail end is communicated with thrust chamber respectively, and the first injection into orbit pipe 112 is equipped with the first solenoid valve 114, the first solenoid valve 114 and control
Subsystem control processed is connected.Using bifid pipe ejector filler can propellant flow rate becomes smaller in pipeline in the case where, keep spray
Pressure drop is constant, keeps good atomization.
It is additionally provided on pipeline between tank 22 and ejector filler 11:
First plus valve 61 is let out, for filling to the propellant in tank 22；
Second solenoid valve 62, for controlling releasing for propellant in tank 22；
Filter 63, for preventing dirt, particulate matter or fragment from entering thrust chamber；
Turbine flowmeter 64, for monitoring volume flow in pipeline, and can indirect monitoring mixing ratio situation of change；
Compensator 65, for compensation conduit radially, axially with angular displacement deviation；
Solenoid valve 66 is released in pre-cooling, for pipeline to be pre-chilled；
First plus let out valve 61, second solenoid valve 62, pre-cooling release solenoid valve 66 respectively with control subsystem control be connected.
With reference to Fig. 1, 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.
Pipeline on pipeline between high pressure gas cylinder 21 and tank 22 and between high pressure gas cylinder 21 and attitude control engine 31
On be equipped with:
Second plus valve 71 is let out, for filling to the high pressure gas in high pressure gas cylinder 21；
Third solenoid valve 72, for controlling releasing for 21 mesohigh gas of high pressure gas cylinder；
Pressure reducer 73, for reducing the high-pressure gas pressure in pipeline；
Second plus let out valve 71, third solenoid valve 72 respectively with control subsystem control be connected.
With reference to Fig. 1, in the present embodiment, four high pressure gas cylinders 21 share one second plus let out valve, third solenoid valve, high pressure
There is a pressure reducing valve on pipeline between gas cylinder 21 and attitude control engine 31, has on the pipeline between high pressure gas cylinder 21 and tank 22
Two pressure reducing valves.
The working process of this embodiment is as follows:
After dynamical system starting, propellant is discharged from tank 22, by second solenoid valve 62, filter 63 later to centrifugation
Before pump 42, brshless DC motor 41 drives centrifugal pump 42 to be pressurized respectively to liquid oxygen and methane, and pressurized propellant flows through turbine
Valve before flowmeter 64, Venturi tube 51, compensator 65 and spray, liquid oxygen spray into combustion chamber 121, liquid methane by bifid pipe ejector filler
For re-generatively cooled, therefore the interlayer that be introduced into push-in room is cooling, then enters thrust chamber, igniter by bifid pipe ejector filler
After lighting a fire successfully, dynamical system is started to work.
When continuous thrust, 42 revolving speed of centrifugal pump is constant, and the master control of Mars transporter is continuous to control subsystem one
Reduced digital signal, the electric signal that control subsystem will be continuously reduced digital signal and be converted into stepper motor, stepper motor band
The dynamic continuous movement of plug cone, reduces flow in Venturi tube 51 linearly, thus reduce thrust linearly, when flow reduces half, control
Subsystem control bifid pipe ejector filler processed closes the first solenoid valve 114 on the first injection into orbit pipe 112, and propellant is sprayed from second at this time
It infuses pipe 113 and carries out spray, it is ensured that injection pressure drop is constant, keeps good atomization.
When changing thrust direction, 122 swinging signal of jet pipe is sent control subsystem by the master control of Mars transporter, control
Subsystem processed issues signal to the motor of electric hydaulic bar, and motor drives electric hydaulic bar is flexible jet pipe 122 is made to swing to phase
Position is answered, to make 122 thrust direction change specified angle of jet pipe.
In Mars transporter flight course, sensor detects that Mars transporter state of flight has deviation, according to Mars
The master control of transporter instructs, and the control valve 32 of attitude control engine 31 is opened rapidly certain time and then shut rapidly, high pressure gas cylinder
High-pressure helium in 21 is depressurized by pressure reducing valve, impulse force is generated, by Mars into attitude control engine 31 by valve before spraying
Transporter state revision.
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 (10)
1. a kind of rocket-powered formula Mars transporter dynamical system, which is characterized in that including sustainer, energy subsystem, appearance
Control subsystem, pressurization subsystem, change propulsive subsystem and control subsystem；
The sustainer includes ejector filler, igniter and is located at the thrust chamber that Mars transports motor spindle, the thrust chamber
One end is connected to ejector filler, and the other end is located in thrust chamber towards the bottom of Mars transporter, the igniter；
The energy subsystem includes battery, high pressure gas cylinder and the tank that can store propellant, the high pressure gas cylinder and storage
For case by pipeline connection to be used to be pressurized tank, the tank and ejector filler pass through pipeline connection；
The attitude control subsystem includes several attitude control engines, and each attitude control engine is spaced the side for being located at Mars transporter in a ring
Portion is with for carrying out pose adjustment to Mars transporter, the high pressure gas cylinder is connected with each attitude control engine by pipeline to be used for
Working medium is provided for attitude control engine；
The pressurization subsystem is located on the pipeline between tank and ejector filler for being pressurized to the propellant in pipeline；
The change propulsive subsystem be located on the pipeline between tank and ejector filler with for the propellant flow rate in pipeline into
Row control；
The pressurization subsystem, change propulsive subsystem are electrical connected with battery respectively；
The control subsystem is divided with sustainer, energy subsystem, attitude control subsystem, pressurization subsystem, change propulsive respectively
System control is connected.
2. rocket-powered formula Mars transporter dynamical system according to claim 1, which is characterized in that the change propulsive system
It is located on the pipeline between tank and ejector filler including Venturi tube, plug cone and stepper motor, the Venturi tube, the plug cone is located at
In Venturi tube, the stepper motor is located at outside Venturi tube and is connected with plug cone transmission for in Venturi tube by drive rod
Propellant flow rate is controlled, and the stepper motor is connected with control subsystem control, the stepper motor and battery electrical property phase
Even.
3. rocket-powered formula Mars transporter dynamical system according to claim 1, which is characterized in that the ejector filler is double
Manifold ejector filler, the bifid pipe ejector filler include spray general pipeline, the first injection into orbit pipe and the second injection into orbit pipe, the spray general pipeline's
Head end and tank by pipeline connection, the head end of first injection into orbit pipe, the second injection into orbit pipe head end respectively with spray general pipeline's
Tail end connection, the tail end of first injection into orbit pipe, the tail end of the second injection into orbit pipe are communicated with thrust chamber respectively, first injection into orbit pipe
It is equipped with the first solenoid valve, first solenoid valve is connected with control subsystem control.
4. rocket-powered formula Mars transporter dynamical system according to claim 1, which is characterized in that the pressurization subsystem
For integrated electric-motor pump, the integrated electric motor pump includes brshless DC motor and centrifugal pump, the brshless DC motor with from
Heart pump transmission is connected, and the centrifugal pump is located on the pipeline between tank and ejector filler for carrying out to the propellant in pipeline
Pressurization, the brshless DC motor are connected with control subsystem control, and the brshless DC motor is electrical connected with battery.
5. rocket-powered formula Mars transporter dynamical system according to claim 1, which is characterized in that the tank and spray
It is additionally provided on pipeline between device:
First plus valve is let out, for filling to the propellant in tank；
Second solenoid valve, for controlling releasing for propellant in tank；
Filter, for preventing dirt, particulate matter or fragment from entering thrust chamber；
Turbine flowmeter, for monitoring volume flow in pipeline, and can indirect monitoring mixing ratio situation of change；
Compensator, for compensation conduit radially, axially with angular displacement deviation；
Solenoid valve is released in pre-cooling, for pipeline to be pre-chilled；
Described first plus let out valve, second solenoid valve, pre-cooling release solenoid valve and are connected respectively with control subsystem control.
6. rocket-powered formula Mars transporter dynamical system according to claim 1, which is characterized in that the high pressure gas cylinder with
It is equipped on pipeline on pipeline between tank and between high pressure gas cylinder and attitude control engine:
Second plus valve is let out, for filling to the high pressure gas in high pressure gas cylinder；
Third solenoid valve, for controlling releasing for high pressure gas cylinder mesohigh gas；
Pressure reducer, for reducing the high-pressure gas pressure in pipeline；
Described second plus let out valve, third solenoid valve respectively with control subsystem control be connected.
7. according to claim 1 to any one of 6 rocket-powered formula Mars transporter dynamical systems, which is characterized in that described
Tank is spherical tank, is arranged with thermal insulation layer outside the tank.
8. according to claim 1 to any one of 6 rocket-powered formula Mars transporter dynamical systems, which is characterized in that described
Thrust chamber includes the combustion chamber being fixedly linked and jet pipe, the ejector filler and combustion chamber, the hinged Mars in combustion chamber
The bottom of transporter, the combustion chamber be equipped with electric hydaulic bar to be adjusted for the spray angle to jet pipe, it is described
The fixing end of electric hydaulic bar and the bottom of Mars transporter are hinged, the telescopic end of the electric hydaulic bar and the outer wall of combustion chamber
Hingedly, the control subsystem is connected with flexible for controlling electric hydaulic bar with the control of electric hydaulic bar.
9. rocket-powered formula Mars transporter dynamical system according to claim 8, which is characterized in that the combustion chamber is circle
Column construction, the jet pipe are campanula halleri Halleri.
10. rocket-powered formula Mars transporter dynamical system according to claim 9, which is characterized in that the electric hydaulic
The quantity of bar is two and interval is located on the outer wall of combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810872988.9A CN109018444A (en) | 2018-08-02 | 2018-08-02 | Rocket-powered mars transporter power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810872988.9A CN109018444A (en) | 2018-08-02 | 2018-08-02 | Rocket-powered mars transporter power system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109018444A true CN109018444A (en) | 2018-12-18 |
Family
ID=64647890
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810872988.9A Pending CN109018444A (en) | 2018-08-02 | 2018-08-02 | Rocket-powered mars transporter power system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109018444A (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109695515A (en) * | 2019-02-01 | 2019-04-30 | 北京星际荣耀空间科技有限公司 | Total assembling structure, rocket engine, liquid rocket |
| CN109774975A (en) * | 2019-02-01 | 2019-05-21 | 北京蓝箭空间科技有限公司 | Rocket body recycles attitude control dynamical system and carrier rocket |
| CN109826725A (en) * | 2019-02-19 | 2019-05-31 | 北京星际荣耀空间科技有限公司 | Power mechanism, propulsion system and the liquid rocket system of propulsion system |
| CN109883721A (en) * | 2019-01-14 | 2019-06-14 | 北京星际荣耀空间科技有限公司 | A kind of variable working condition gas generator low-temperature test system and test method |
| CN110332060A (en) * | 2019-03-22 | 2019-10-15 | 北京蓝箭空间科技有限公司 | Liquid oxygen methane rocket and liquid oxygen methane Rocket tank fall pressure type pressurized design method |
| CN110406699A (en) * | 2019-06-19 | 2019-11-05 | 上海空间推进研究所 | Propulsion and generating integration device and its operating method for space power system |
| CN110510128A (en) * | 2019-08-02 | 2019-11-29 | 宁波天擎航天科技有限公司 | A kind of propulsion system |
| CN113107711A (en) * | 2021-04-20 | 2021-07-13 | 北京控制工程研究所 | Initial parameter design method of two-component centrifugal engine |
| CN113431706A (en) * | 2021-06-30 | 2021-09-24 | 湖北航天技术研究院总体设计所 | Venturi tube combination device and system for liquid engine and operation method of venturi tube combination device |
| CN114162361A (en) * | 2022-02-14 | 2022-03-11 | 中国人民解放军战略支援部队航天工程大学 | Aerodynamic vector propulsion system of satellite ground simulation device |
| CN114275194A (en) * | 2021-12-14 | 2022-04-05 | 中国运载火箭技术研究院 | Autogenous pressurization system suitable for pressurization of multi-working-condition storage tank of nuclear carrier |
| CN114439651A (en) * | 2022-02-08 | 2022-05-06 | 北京航空航天大学 | Adjustable injector intelligent self-adaptive calibration system and calibration method |
| CN114719688A (en) * | 2022-05-20 | 2022-07-08 | 精易兴航(北京)科技创新有限公司 | Pneumatic separation recoverable carrier rocket for launching suborbital load |
| CN114275194B (en) * | 2021-12-14 | 2024-05-31 | 中国运载火箭技术研究院 | Self-generating pressurization system suitable for multi-station storage tank pressurization of nuclear carrier |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907040A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Nitrogen cold gas micro propulsion device adopting ring storage tank |
| CN102926889A (en) * | 2012-10-31 | 2013-02-13 | 北京控制工程研究所 | Method for using bipropellants efficiently |
| US20150000755A1 (en) * | 2011-12-14 | 2015-01-01 | Snecma | Pressurizing device and method |
-
2018
- 2018-08-02 CN CN201810872988.9A patent/CN109018444A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907040A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Nitrogen cold gas micro propulsion device adopting ring storage tank |
| US20150000755A1 (en) * | 2011-12-14 | 2015-01-01 | Snecma | Pressurizing device and method |
| CN102926889A (en) * | 2012-10-31 | 2013-02-13 | 北京控制工程研究所 | Method for using bipropellants efficiently |
Non-Patent Citations (5)
| Title |
|---|
| 叶伟: "双燃烧室冲压发动机冲压空气涡轮泵供应系统方案研究", 《中国优秀硕士学位论文全文数据库工程科技II辑》 * |
| 崔朋等: "变推力液体火箭发动机系统方案研究进展", 《中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议论文集》 * |
| 田林等: "美国梦神号行星着陆器原型系统发展及启示", 《航天器工程》 * |
| 金煊等: "低压比煤油涡轮数值计算与优化设计", 《推进技术》 * |
| 金煊等: "超然冲压发动机再生冷却技术研究进展", 《火箭推进》 * |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109883721A (en) * | 2019-01-14 | 2019-06-14 | 北京星际荣耀空间科技有限公司 | A kind of variable working condition gas generator low-temperature test system and test method |
| CN109774975A (en) * | 2019-02-01 | 2019-05-21 | 北京蓝箭空间科技有限公司 | Rocket body recycles attitude control dynamical system and carrier rocket |
| CN109695515A (en) * | 2019-02-01 | 2019-04-30 | 北京星际荣耀空间科技有限公司 | Total assembling structure, rocket engine, liquid rocket |
| CN109826725A (en) * | 2019-02-19 | 2019-05-31 | 北京星际荣耀空间科技有限公司 | Power mechanism, propulsion system and the liquid rocket system of propulsion system |
| CN110332060B (en) * | 2019-03-22 | 2020-10-16 | 蓝箭航天空间科技股份有限公司 | Liquid oxymethane rocket and liquid oxymethane rocket storage tank pressure-drop type pressurization design method |
| CN110332060A (en) * | 2019-03-22 | 2019-10-15 | 北京蓝箭空间科技有限公司 | Liquid oxygen methane rocket and liquid oxygen methane Rocket tank fall pressure type pressurized design method |
| CN110406699A (en) * | 2019-06-19 | 2019-11-05 | 上海空间推进研究所 | Propulsion and generating integration device and its operating method for space power system |
| CN110510128B (en) * | 2019-08-02 | 2021-04-20 | 宁波天擎航天科技有限公司 | Propulsion system |
| CN110510128A (en) * | 2019-08-02 | 2019-11-29 | 宁波天擎航天科技有限公司 | A kind of propulsion system |
| CN113107711A (en) * | 2021-04-20 | 2021-07-13 | 北京控制工程研究所 | Initial parameter design method of two-component centrifugal engine |
| CN113107711B (en) * | 2021-04-20 | 2022-03-04 | 北京控制工程研究所 | Initial parameter design method of two-component centrifugal engine |
| CN113431706A (en) * | 2021-06-30 | 2021-09-24 | 湖北航天技术研究院总体设计所 | Venturi tube combination device and system for liquid engine and operation method of venturi tube combination device |
| CN114275194A (en) * | 2021-12-14 | 2022-04-05 | 中国运载火箭技术研究院 | Autogenous pressurization system suitable for pressurization of multi-working-condition storage tank of nuclear carrier |
| CN114275194B (en) * | 2021-12-14 | 2024-05-31 | 中国运载火箭技术研究院 | Self-generating pressurization system suitable for multi-station storage tank pressurization of nuclear carrier |
| CN114439651A (en) * | 2022-02-08 | 2022-05-06 | 北京航空航天大学 | Adjustable injector intelligent self-adaptive calibration system and calibration method |
| CN114439651B (en) * | 2022-02-08 | 2023-04-28 | 北京航空航天大学 | Intelligent self-adaptive calibration system and calibration method for adjustable injector |
| CN114162361A (en) * | 2022-02-14 | 2022-03-11 | 中国人民解放军战略支援部队航天工程大学 | Aerodynamic vector propulsion system of satellite ground simulation device |
| CN114162361B (en) * | 2022-02-14 | 2022-05-06 | 中国人民解放军战略支援部队航天工程大学 | Aerodynamic vector propulsion system of satellite ground simulation device |
| CN114719688A (en) * | 2022-05-20 | 2022-07-08 | 精易兴航(北京)科技创新有限公司 | Pneumatic separation recoverable carrier rocket for launching suborbital load |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109018444A (en) | Rocket-powered mars transporter power system | |
| US10246200B2 (en) | Centripetal aerodynamic platform spacecraft | |
| EP3423716B1 (en) | A system of using compressed air as a force source and method thereof; airplane | |
| US10815935B2 (en) | Throttleable propulsion launch escape systems and devices | |
| EP1163152B1 (en) | Payload carry and launch system | |
| US20060208136A1 (en) | Centripetal reflex method of space launch | |
| CN107063006A (en) | A kind of reusable carrying space system and round method | |
| CN105649775A (en) | System taking compressed air as force applying source, operation method for system and airplane | |
| US6119983A (en) | Airship/spacecraft | |
| JPH01501133A (en) | Method and apparatus for launching a spacecraft using a recoverable rocket upper stage | |
| US11643994B2 (en) | Rocket propulsion systems and associated methods | |
| CN109018439A (en) | Rocket-powered mars transporter | |
| CN114476141A (en) | Moon landing aircraft propulsion method and system | |
| RU2609539C1 (en) | Rocket vehicle, return stage of rocket vehicle and method of its launch upon return and system of helicopter pick-up of return stage | |
| GB2359876A (en) | Method and apparatus for placing satellites in low-earth orbitt | |
| RU196251U1 (en) | Unmanned Helicopter "SHADOW" | |
| JPH02108838A (en) | Structure of turbo ram rocket coupling propulsion engine | |
| CN116929159B (en) | Carrier rocket with solid-liquid hybrid power and launching method thereof | |
| RU2775088C1 (en) | Launch facility for prelaunch preparation and launch of a launch rocket with a space warning part | |
| US10907580B2 (en) | Method and apparatus for providing external fuel to a rocket | |
| Burry et al. | Liquid propellant rocket engines-Their status and future. | |
| CN114701667A (en) | Space transportation system based on manned Mars detection and detection method | |
| RU2621805C2 (en) | Vehicle for interplanetary communication (versions) | |
| LEWIS et al. | Design of a university launch vehicle system | |
| CN117589008A (en) | Carrier rocket with solid-liquid hybrid power and launching method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181218 |
|
| RJ01 | Rejection of invention patent application after publication |