CN114701667A - Space transportation system based on manned Mars detection and detection method - Google Patents
Space transportation system based on manned Mars detection and detection method Download PDFInfo
- Publication number
- CN114701667A CN114701667A CN202210287007.0A CN202210287007A CN114701667A CN 114701667 A CN114701667 A CN 114701667A CN 202210287007 A CN202210287007 A CN 202210287007A CN 114701667 A CN114701667 A CN 114701667A
- Authority
- CN
- China
- Prior art keywords
- nuclear
- engine
- stage
- power
- track
- 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
- 238000001514 detection method Methods 0.000 title claims abstract description 50
- 238000012546 transfer Methods 0.000 claims abstract description 115
- 238000003860 storage Methods 0.000 claims abstract description 75
- 239000001257 hydrogen Substances 0.000 claims abstract description 40
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 40
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 39
- 239000003380 propellant Substances 0.000 claims abstract description 20
- 239000007788 liquid Substances 0.000 claims abstract description 18
- 238000013459 approach Methods 0.000 claims abstract description 17
- 230000001174 ascending effect Effects 0.000 claims abstract description 7
- 230000004308 accommodation Effects 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 42
- 230000008569 process Effects 0.000 claims description 25
- 239000000446 fuel Substances 0.000 claims description 16
- 238000005457 optimization Methods 0.000 claims description 16
- 238000001816 cooling Methods 0.000 claims description 15
- 239000000411 inducer Substances 0.000 claims description 9
- 230000001172 regenerating effect Effects 0.000 claims description 9
- 239000007921 spray Substances 0.000 claims description 7
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 6
- 239000007789 gas Substances 0.000 claims description 6
- 230000005855 radiation Effects 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 4
- 238000001228 spectrum Methods 0.000 claims description 4
- 206010048669 Terminal state Diseases 0.000 claims description 3
- 238000011065 in-situ storage Methods 0.000 claims description 3
- 230000001050 lubricating effect Effects 0.000 claims description 3
- 239000003758 nuclear fuel Substances 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims description 2
- 239000002360 explosive Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 description 6
- 210000001503 joint Anatomy 0.000 description 6
- 230000000630 rising effect Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 230000009977 dual effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000012937 correction Methods 0.000 description 2
- 238000005498 polishing Methods 0.000 description 2
- 230000001737 promoting effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 238000009440 infrastructure construction 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
- 238000005381 potential energy Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000004580 weight loss Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/12—Artificial satellites; Systems of such satellites; Interplanetary vehicles manned
-
- 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
-
- 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
-
- 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
- B64G1/408—Nuclear spacecraft propulsion
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- High Energy & Nuclear Physics (AREA)
- Monitoring And Testing Of Nuclear Reactors (AREA)
Abstract
The invention provides a manned Mars detection-based space transportation system and a detection method, wherein the space transportation system comprises a nuclear propulsion stage, a storage box stage and an effective load stage; the nuclear propulsion stage is positioned at the tail end of the transport system, comprises a main engine containing a nuclear reactor and a primary liquid hydrogen storage tank and is used for propelling the whole transport system to enter a fire ground transfer track, track control, fire approach and ground approach braking; the tank stage is positioned at the front end of the nuclear propulsion stage and comprises a plurality of secondary liquid hydrogen tanks for storing propellant, and the propellant is provided for a main engine of the nuclear propulsion stage when the transportation system enters the ground fire transfer track; the payload stage comprises a manned payload and a cargo payload, the manned payload comprises a manned detection aircraft and a transfer accommodation cabin, and the cargo payload comprises a Mars landing and ascending detector. The manned Mars detection-based space transportation system and the detection method provided by the invention provide great reference for manned Mars detection.
Description
Technical Field
The invention belongs to the technical field of space transportation and deep space exploration, and particularly relates to a space transportation system and a detection method based on manned Mars detection.
Background
Manned Mars detection has important significance in aspects of exploring extraterrestrial life, transferring people between stars, promoting scientific and technological development, improving national status, promoting human social progress and the like. At present, people only carry out dozens of times of unmanned Mars detection, and the Mars are investigated, so that manned Mars detection is not realized. The aerospace transportation system technology is a basic technology for implementing manned Mars detection tasks, and the technical level of the aerospace transportation system technology also has important influence on the aspects of the framework, the transportation capacity and the like of the manned Mars detection tasks. Therefore, there is a need to develop a space transportation system and a detection method based on manned mars detection.
Disclosure of Invention
In order to overcome the defects in the prior art, the inventor of the invention carries out intensive research and provides a space transportation system and a detection method based on manned Mars detection.
The technical scheme provided by the invention is as follows:
in a first aspect, a manned Mars-detection-based space transportation system comprises a nuclear propulsion stage, a storage tank stage and a payload stage; the nuclear propulsion stage is positioned at the tail end of the transport system, comprises a main engine containing a nuclear reactor and a primary liquid hydrogen storage tank and is used for propelling the whole transport system to enter a fire ground transfer track, track control, fire approach and ground approach braking; the tank stage comprises a plurality of secondary liquid hydrogen tanks for storing a propellant to be supplied to the main engine of the nuclear propulsion stage when the transport system enters the ground fire transfer track; the payload stage comprises a manned payload and a cargo payload, the manned payload comprises a manned detection aircraft and a transfer accommodation cabin, and the cargo payload comprises a Mars landing and ascending detector.
Furthermore, a nuclear heat single-main power form or a nuclear heat nuclear power double-main power form is selected as a main engine containing a nuclear reactor in the nuclear propulsion stage; the nuclear heat single main power mode adopts a nuclear heat engine as a main engine and is responsible for completing the tasks of entering an earth fire transfer track, a mars brake entering the track and entering the fire transfer track; the nuclear heat and nuclear power double-active power form adopts a nuclear heat engine and a nuclear power engine, the nuclear heat engine is used for entering the tasks of an earth fire transfer track, a Mars brake entering the track and an earth fire transfer track, and the nuclear power engine is used for accelerating and decelerating during the earth fire reciprocating period.
Furthermore, the nuclear heat engine in the form of the nuclear heat single main power adopts a double-turbine pump expansion circulation mode, and mainly comprises two sets of turbine pump systems, a reactor system, a thrust chamber system, a valve and a pipeline system; each turbine pump system mainly comprises a secondary centrifugal pump, an inducer, a secondary counter-force turbine and a lubricating system; the two-stage centrifugal pump, the inducer and the two-stage counter-force turbine are arranged on the same shaft, and the two-stage counter-force turbine drives the centrifugal pump and the inducer to rotate through the shaft; the reactor system mainly comprises a fuel unit, a supporting tube, a control rod and a reactor shielding layer, wherein the whole reactor system is hexagonal honeycomb, the fuel unit is in a small hexagonal hollow structure and is in a reactor hexagon which is formed by the supporting tube and the control rod outside the fuel unit side by side, and the shielding layer is positioned at the head part and the periphery of the reactor system and used for shielding radiation; the thrust chamber system mainly comprises a spray pipe and a reactor outlet small-section cylinder section, and the thrust chamber is cooled in a mode of combining regenerative cooling and radiation cooling; the valve and pipeline system mainly comprises a working medium conduit and various valves; when the nuclear heat engine is started, a main valve of the storage tank is opened, working media in the storage tank enter a secondary centrifugal pump under the action of the self-pressurization pressure of the storage tank to be pressurized to form high-pressure working media, the high-pressure working media are divided into two paths after passing through the secondary centrifugal pump, one path of the working media is firstly cooled by a regenerative cooling channel through a thrust chamber system, and then enters a control rod to cool the periphery of a reactor after the regenerative cooling of the thrust chamber is completed; the other path enters a supporting tube structure to be heated and plays a role in cooling the interior of the reactor; the two paths of working media are mixed in front of the turbine and enter the turbine to expand and do work to drive the turbine to rotate; the working medium gas after passing through the turbine enters the reactor fuel unit to be heated continuously, finally becomes a high-temperature and high-pressure working medium at the outlet of the reactor, expands through the spray pipe and is discharged at a high speed, and thus thrust is generated.
Furthermore, the transportation system comprises an auxiliary power system besides a main engine serving as a main power system, wherein the auxiliary power system is used for carrying out attitude control and orbit control and forms an integrated main and auxiliary power system based on a hydrogen working medium together with the main power system; the auxiliary power system adopts the technical scheme that vaporized hydrogen in a storage tank is heated by a nuclear reactor and then directly sprayed to form thrust, or the vaporized hydrogen and liquid oxygen in the storage tank are used as propellants of the auxiliary power system, the vaporized hydrogen and the liquid oxygen are sprayed to form the thrust after being combusted, and part of the hydrogen after exchanging heat with the nuclear reactor is used as pressurizing gas of the storage tank to implement stable and continuous pressurization.
In a second aspect, a space transportation method based on manned mars detection comprises the following steps:
s1, respectively sending the nuclear propulsion stage, the storage box stage and the payload stage to a near-earth orbit by a carrier rocket, and performing on-orbit assembly;
s2, starting the nuclear heat engine, entering the ground fire transfer track, discarding the used storage tank in the storage tank level, closing the nuclear heat engine, then transferring the nuclear heat single main power form by adopting the Hoeman transfer track, and starting the nuclear power engine in the nuclear heat nuclear power double main power form in the transfer process to optimize the track;
s3, when a Mars approaches, the nuclear heat engine is started again to perform fire approaching braking, stays on the fire surrounding track to wait for the Mars to execute a task, and is closed;
s4, after the manned Mars task is finished, the space transportation system restarts the nuclear heat engine, the nuclear heat engine is closed after entering a fire ground transfer track, and then the nuclear heat single main power mode adopts a Hoemann transfer track for transfer; the nuclear power engine is started in the transferring process in the nuclear heat and nuclear power double-active power mode, the orbit is optimized, and the earth is directly landed through the manned spacecraft when the orbit is close to the earth.
Further, in step S4, when entering the ground fire transfer orbit, a method for optimizing the ground fire transfer point based on the back effect thrust of the nuclear heat main power is used, and the terminal state of the transportation system can meet the condition of entering the ground fire transfer orbit by solving the starting time and the attitude direction of the main engine during starting; the method specifically comprises the following steps:
the method comprises the steps of determining the magnitude of the thrust amplitude and the acting time of a nuclear heat engine by aiming at the interpolation fitting of a thrust curve of the nuclear heat engine, representing and forming the aftereffect thrust of the engine, and using the aftereffect thrust as a constraint condition of track optimization;
selecting the maximum quality optimization target of a terminal of a transportation system entering a ground fire transfer track; selecting unit vector components of engine thrust in a three-dimensional space at the startup and shutdown time and in the startup process as optimization parameters;
adopting a differential form Gaussian pseudo-spectrum method, dispersing the state time history and the control time history of the transportation system on the track on a series of Gaussian points, then respectively constructing Lagrange interpolation polynomials by using the dispersed states and the control to approximate the real state and the control time history, and converting the dynamic differential equation constraint into a series of algebraic constraints; and solving and optimizing two processes of entering a transfer orbit and entering a target orbit according to the determined mass of the propellant discharged by the nuclear heat engine at each moment and the flight condition, so as to obtain an orbit with minimum fuel consumption in the flight process of entering the ground fire transfer orbit.
The method for detecting the manned mars on the flights based on the nuclear transportation system comprises the following steps:
s1, selecting a Lagrange point 2 as a space base, respectively sending the core propulsion stage, the storage box stage and the effective load stage to the space base by a carrier rocket, and performing on-orbit assembly;
s2, starting from the space base, starting a nuclear heat engine, entering an underground fire transfer track, without throwing away a storage tank in a used storage tank level, closing the nuclear heat engine, then transferring by adopting a Hueman transfer track in a nuclear heat single-main power mode, starting the nuclear power engine in a nuclear heat nuclear power double-main power mode in the transfer process, and optimizing the track;
s3, when a Mars approaches, the nuclear heat engine is started again to perform fire approaching braking, stays on the fire surrounding track to wait for the Mars to execute a task, and is closed;
s4, after the manned Mars task is finished, the Mars in-situ resource is used for filling fuel into the storage box on the rail, the nuclear heat engine is restarted by the space transportation system, the nuclear heat engine is closed after entering a fire ground transfer rail, and then the nuclear heat single main power form is transferred by adopting a Hoeman transfer rail; starting a nuclear power engine in a nuclear-thermal nuclear power double-active power mode in a transfer process, optimizing a track, and returning to a space base;
s5, after filling is carried out again at the space base, waiting is carried out;
s6, returning the personnel who finish the task to the earth surface, and simultaneously conveying the personnel to the space base from the earth surface;
s7, the person enters the space transportation system and runs on fire again
According to the manned Mars detection-based space transportation system and the detection method provided by the invention, the following beneficial effects are achieved:
the invention provides a space transportation system and a detection method based on manned Mars detection, which provide two space transportation systems by designing a carrier with single nuclear heat propulsion power and a carrier with a dual nuclear heat nuclear power mode, and adopt an optimized design scheme of an earth fire transfer orbit under the back effect thrust of the nuclear heat propulsion power based on an integrated main and auxiliary power system of a hydrogen working medium, so that the system efficiency is higher and the transfer time is shorter.
Drawings
FIG. 1 is a nuclear thermal propulsion based monomaster vehicle configuration of the present invention;
FIG. 2 is a nuclear thermoelectric power dual mode based vehicle configuration of the present invention;
FIG. 3 is a nuclear-thermal nuclear power dual-active ground fire transfer orbit of the present invention;
FIG. 4 is a schematic illustration of a dual turbo pump expansion cycle of the nuclear thermal main power engine of the present invention;
FIG. 5 is an integrated hydrogen working medium-based main and auxiliary power system of the present invention;
fig. 6 illustrates a control method of the present invention suitable for use in a nuclear space transportation system.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The invention discloses a manned Mars detection-based space transportation system which mainly comprises a nuclear propulsion stage, a storage box stage and an effective load. The nuclear propulsion stage is positioned at the tail end of the transport system, comprises a main engine containing a nuclear reactor and a primary liquid hydrogen storage tank and is used for propelling the whole transport system to enter a fire ground transfer track, track control, fire approach and ground approach braking; the tank stage is positioned at the front end of the nuclear propulsion stage and comprises a plurality of secondary liquid hydrogen tanks for storing propellant, and the propellant is provided to a main engine of the nuclear propulsion stage when the transportation system enters the ground fire transfer track; the payload stage comprises a manned payload and a cargo payload, the manned payload comprises a manned detection aircraft and a transfer accommodation cabin, and the cargo payload comprises a Mars landing and ascending detector.
The main engines of the nuclear propulsion stage including the nuclear reactor mainly comprise two types, wherein one type is a main engine based on a nuclear heat single main power form, and the other type is a main engine based on a nuclear heat nuclear power double main power form. The nuclear heat single-main power mode adopts a nuclear heat engine as a main propulsion system and is responsible for completing the tasks of entering an earth fire transfer track, a mars brake entering the track and entering the fire transfer track; the nuclear heat and nuclear power double-main-power mode adopts a nuclear heat engine and a nuclear power engine, the nuclear heat engine is used for tasks of entering an earth fire transfer track, a Mars brake entering the track and entering the fire transfer track, and the nuclear power engine is used for acceleration and deceleration during the earth fire reciprocating period so as to reduce the total time of the tasks. The adoption of the main engine based on the nuclear heat single main power form ensures that the space transportation system is simpler in design and longer in transfer time, and is a basic design system of the nuclear power transportation system; the main engine system based on the nuclear-thermal nuclear power double main power is slightly complex, has advantages in transfer time of a space transportation system, and can be used for short-time transfer tasks.
The manned Mars detection task based on the nuclear heat single main power form mainly comprises the following steps: (1) respectively sending the nuclear propulsion stage, the storage box stage and the cargo-carrying type payload to the near-earth orbit by a carrier rocket; the nuclear propulsion stage, the storage box stage and the cargo-carrying type payload are assembled on the rail to form a cargo-carrying transfer stage carrying the payload; (2) the nuclear heat engine is started at the cargo carrying transfer stage, the nuclear heat engine enters the ground fire transfer track, then the used storage box is thrown off, the nuclear heat engine slides on the track, and the nuclear heat engine transfers by adopting the Hoeman transfer track in a single-main power mode; (3) when approaching a spark, using near fire braking to carry out ring fire; (4) when all the material equipment which reaches the mars runs well and reaches a launching window, the carrier rocket respectively sends a nuclear propulsion stage, a storage tank stage, a manned payload and the like to the near-earth orbit; carrying out on-orbit assembly on a nuclear propulsion stage, a storage box stage and a manned payload to form a manned transfer stage carrying the payload; (5) the manned transfer level starts a nuclear heat engine, the nuclear heat engine enters an underground fire transfer track, then a used storage tank is thrown off, the nuclear heat engine slides on the track, and a nuclear heat single main power mode adopts an Hoeman transfer track to transfer; (6) when a Mars approaches, the manned transfer level starts the nuclear heat engine to perform fire approaching braking, enters a fire surrounding track to stay, and waits for a Mars detection task; (7) the manned spacecraft is separated from the nuclear power carrier and is in butt joint with a landing and rising detector which is arranged on the ring fire track, and an astronaut can detect the surface of a landing Mars through the Mars landing and rising detector, then enters the manned spacecraft which is in butt joint with the Mars landing and rising detector and returns to the ring fire track; (8) the manned spacecraft is in butt joint with the manned transfer stage waiting on the ring fire track again; the manned transfer stage starts the nuclear heat engine, enters a fire transfer track and directly lands the earth through the manned spacecraft when approaching the earth.
The nuclear heat engine in the form of nuclear heat single main power adopts a double-turbine pump expansion circulation mode, and mainly comprises two sets of turbine pump systems, a reactor system, a thrust chamber system, a valve and a pipeline system; each turbine pump system mainly comprises a secondary centrifugal pump, an inducer, a secondary counter-force turbine and a lubricating system; the two-stage centrifugal pump, the inducer and the two-stage counter-force turbine are arranged on the same shaft, and the two-stage counter-force turbine drives the centrifugal pump and the inducer to rotate through the shaft; the reactor system mainly comprises a fuel unit, a supporting tube, a control rod and a reactor shielding layer, wherein the whole reactor system is in a hexagonal honeycomb shape, the fuel unit is in a small hexagonal hollow structure and is in a reactor hexagon which is formed by the supporting tube and the control rod outside the fuel unit side by side, and the shielding layer is positioned at the head part and the periphery of the reactor system and used for shielding radiation; the thrust chamber system is a non-detachable welding structure and mainly comprises a spray pipe and a reactor outlet small-section cylinder section, and the thrust chamber is cooled by adopting a mode of combining regenerative cooling and radiation cooling; the valve and pipeline system is mainly composed of working medium conduit and various valves. When the nuclear heat engine is started, a main valve of the storage tank is opened, working media in the storage tank enter a secondary centrifugal pump to be pressurized under the action of the self-pressurization pressure of the storage tank to form high-pressure working media, the high-pressure working media are mainly divided into two paths after passing through the secondary centrifugal pump, one path of the working media is firstly cooled by a regenerative cooling channel to a thrust chamber system, and then enters a control rod to cool the periphery of a reactor after the regenerative cooling of the thrust chamber is completed; the other path enters a supporting tube structure to be heated and plays a role in cooling the interior of the reactor; the two paths of working media are mixed in front of the turbine and enter the turbine to expand and do work to drive the turbine to rotate; the working medium gas after passing through the turbine enters the reactor fuel unit to be heated continuously, finally becomes high-temperature and high-pressure working medium at the outlet of the reactor, expands through a spray pipe such as a Laval spray pipe and is discharged at a high speed, and thus thrust is generated. As shown in fig. 4. Compared with a single-turbine pump expansion circulation mode, a double-turbine pump air-pumping circulation mode and the like, the double-turbine pump expansion circulation mode has the advantages of high specific impulse and high reliability.
For example: the space transportation system in the form of nuclear heat single-main power is shown in fig. 1, has a diameter of 9m and a total length of about 90m, and mainly comprises a primary nuclear heat propulsion stage, two flushable hydrogen storage tanks and a payload. 3 100kN nuclear heat engines are adopted as main power; the nuclear heat propulsion grade weighs about 99 tons, 61 tons of liquid hydrogen are filled, and the nuclear heat propulsion grade is mainly used for starting operation at a near-fire braking section and a fire transfer section. The two disposable tanks were filled with 132 tons of liquid hydrogen and were thrown away to lose weight after entering the ground fire transfer section. The manned payload is 65 tons in total, mainly is manned airship and living cabin; the cargo-carrying type payload is 103 tons in total, is mainly a Mars landing and rising detector (used for Mars surface and infrastructure construction of a fire-surrounding, including a fire-surrounding space station, a filling station and the like), and can provide 7200m/s of speed increment for 65-ton payloads.
The nuclear heat engine in the nuclear heat nuclear power double-main power form and the main engine in the nuclear heat single-main power form are in the same operation mode, and the nuclear power engine in the nuclear heat nuclear power double-main power form utilizes electric energy formed by nuclear heat conversion to act on the liquid hydrogen working medium and jet out at a high speed to form thrust.
The manned Mars detection task based on the nuclear-thermal nuclear power double-main-power form is different from the manned Mars detection task based on the nuclear-thermal single-main-power form mainly in a manned transfer part, and the manned transfer part mainly comprises the following steps: (1) a carrier rocket is used for respectively conveying a nuclear heat propulsion core level, a nuclear power propulsion system, a liquid hydrogen storage tank, a manned spacecraft and the like to a near-earth orbit; (2) nuclear thermal propulsion core grade, nuclear power propulsion system, liquid hydrogen storage tank, manned spacecraft and the like are assembled on track to form a manned nuclear power carrier carrying effective load; (3) starting a nuclear heat engine, entering a ground fire transfer track, then discarding a used storage tank, and optimizing the track by adopting nuclear power in the transfer process; (4) when a Mars approaches, a nuclear heat engine is started to perform fire approaching braking, and then the nuclear heat engine stays on a fire surrounding track to wait for the Mars to execute a task; (5) the manned spacecraft is separated from the nuclear power carrier and is in butt joint with the Mars ascending and descending aircraft which is arranged on the ring fire track, and an astronaut lands the Mars surface through the Mars ascending and descending aircraft to detect, then enters the manned spacecraft which is in butt joint with the Mars ascending and descending aircraft and returns to the ring fire track; (6) the manned spacecraft is in butt joint with the nuclear power carrier waiting on the ring fire track again to form the nuclear power carrier with the manned spacecraft; (7) the nuclear power carrier starts a nuclear heat engine, enters a fire ground transfer orbit, adopts nuclear electric power to optimize the orbit in the transfer process, and directly lands the earth through a manned spacecraft when approaching the earth.
For example: the nuclear-thermal nuclear power double-main-power space transportation system is shown in figure 2. The nuclear power carrier is 9m in diameter and about 88m in total length and mainly comprises a primary nuclear heat propulsion stage, a primary post-polishing storage tank, two secondary post-polishing liquid hydrogen storage tanks and an effective load; 3 100kN nuclear heat engines are used as transfer main power, 10 4.5N hydrogen magnetic plasma electric thrusters are used as track optimization main power, and the transfer time and the total task time are shortened. The two front throwing storage tanks are filled with 165 tons of liquid hydrogen, and weight loss is thrown away after entering a ground fire transfer section; 59 tons of liquid hydrogen are filled into the rear hydrogen throwing storage tank, and the weight can be thrown off after the rear hydrogen throwing storage tank enters the circular fire track; the nuclear heat propulsion stage is filled with 69 tons of liquid hydrogen and is mainly used for a fire transfer section and a track optimization section.
In a preferred embodiment, the nuclear propulsion stage, the tank stage and the payload are connected by a truss. The tandem type storage tank and the semi-surrounding type truss structure in the storage tank stage are fixed at a plurality of connection points, the truss is of a semi-surrounding type truss structure, the tandem type storage tank and the semi-surrounding type truss structure in the storage tank stage are fixed at a plurality of circumferentially and uniformly distributed connection points through explosion bolts, the storage tank is thrown out after entering a ground fire transfer orbit and the propellant in the storage tank is used up in a one-time mars detection mode, and the storage tank is reserved for filling and reusing or integral replacing and using in a shift mars detection mode (a mode of repeated and repeated mars detection); the structural form is shown in figure 1.
When the propellant demand is too large, the attitude control cost is too large and the overall structure flexibility is too large due to the fact that the storage tank level adopts a serial structure, the storage tanks in the storage tank level adopt a parallel structure or a serial-parallel combination mode, and the truss is of a central shaft truss structure. The parallel storage tanks are symmetrically arranged around the central shaft truss and are axially fixed, and the throwing mode of the parallel storage tanks is consistent with that of the serial storage tanks. The structure form is shown in figure 2.
In a preferred embodiment, the space transportation system comprises an auxiliary power system besides a main engine serving as a main power system, so as to perform attitude control and orbit control, thereby forming an integrated main and auxiliary power system based on a hydrogen working medium, and the hydrogen working medium is used as a propellant for nuclear thermal propulsion of the main power to realize high-efficiency propulsion of the space transportation system. The auxiliary power system adopts the way that vaporized hydrogen in the storage tank is heated by a nuclear reactor and then directly sprayed out to form thrust, or the vaporized hydrogen and liquid oxygen in the storage tank are used as propellants of the auxiliary power system, and the vaporized hydrogen and the liquid oxygen are sprayed out after being combusted to form the thrust; meanwhile, partial hydrogen after heat exchange with the nuclear reactor can be used as pressurized gas of the storage tank to implement stable and continuous pressurization. As shown in fig. 5.
In a preferred embodiment, the nuclear heat engines in the nuclear heat single main power form or the nuclear heat nuclear power double main power form are all three main engines which are uniformly distributed in a delta shape. Each main engine is provided with two hydraulic swing servo actuators, one hydraulic swing servo actuator is used for pitching, the other hydraulic swing servo actuator is used for yawing, and the swing range of the engine is +/-4 degrees; simultaneously, 4 installation end faces are adopted, 4 auxiliary power engines (RCS) of 5 units are installed on each end face, and 5 auxiliary power engines of each unit are installed in a cross shape; (ii) a Meanwhile, as a preferred scheme, a single-frame control moment gyro is arranged outside a payload level to serve as a running fire and ring fire track attitude control execution structure. The nuclear power carrier is large in scale, the nuclear heat engine is long in after effect time, and the control difficulty is different in different flight states, so that three control executing mechanisms are selected to be used for controlling different flight states at the same time. In the starting stage of the nuclear heat engine, swinging the nuclear heat engine to track a guidance instruction; in the stage that the nuclear heat engine is closed but the aftereffect thrust exists, the attitude is stabilized by means of an auxiliary power engine; during the period of transferring the ground fire after the end of the aftereffect of the nuclear heat main engine, the attitude control of the carrier is carried out by using the control moment gyro, and meanwhile, the auxiliary power system participates in the angular momentum unloading of the control moment gyro and the backup control during the period. As shown in fig. 6.
The invention also provides a manned mars detection method based on the nuclear transportation system. The method comprises the following steps: s1, respectively sending the nuclear propulsion stage, the storage box stage and the payload stage to a near-earth orbit by a carrier rocket, and performing on-orbit assembly; s2, starting the nuclear heat main engine, entering the ground fire transfer track, discarding the used storage tank in the storage tank level, closing the nuclear heat engine, and then transferring the nuclear heat single main power form by adopting the Hoeman transfer track; the nuclear power engine is started in the nuclear thermal nuclear power double-active power mode in the transfer process, track optimization is carried out, and transfer time is shortened; s3, when a Mars approaches, the nuclear heat engine is started again to perform fire approaching braking, stays on the fire surrounding track to wait for the Mars to execute a task, and is closed; s4, after the manned Mars task is finished, the space transportation system restarts the nuclear heat engine, the nuclear heat engine is closed after entering a fire ground transfer track, and then the nuclear heat single main power mode adopts a Hoemann transfer track for transfer; the nuclear power engine is started in the nuclear heat nuclear power double-active power mode in the transfer process, the orbit is optimized, the transfer time is shortened, and the earth is directly landed through the manned spacecraft when the earth is close to the earth.
When the transportation system enters the ground fire transfer orbit, an optimization method of the ground fire transfer point based on the back effect thrust of the nuclear heat main power is adopted, and the terminal state of the transportation system can meet the condition of entering the ground fire transfer orbit by solving the starting time and the attitude direction of the engine during starting. The method specifically comprises the following steps:
and S1, interpolating and fitting a thrust curve of the nuclear heat engine, determining the magnitude of the thrust amplitude and the acting time of the nuclear heat engine, and representing the formed engine aftereffect thrust as a constraint condition of the orbit optimization.
The whole transportation system flies outside the atmosphere, no complex pneumatic constraint action exists, the existing constraint is mainly engine thrust amplitude constraint, and the amplitude constraint can be determined according to the form of thrust curve interpolation fitting because the influence of front effect and back effect needs to be considered in the working process of the nuclear thermal propulsion engine.
Component u of thrust vector in three directions during startup1、u2、u3And the sum of squares of the three satisfies the constraint:
meanwhile, in order to ensure that the terminal can reach the transfer track, the terminal constraint is required to meet the requirement of six tracks.
And S2, selecting the terminal quality of the transportation system entering the ground fire transfer track to be the maximum, namely the minimum propellant consumption as an optimization target. According to flight mission requirements and engine working conditions, the mass of the propellant discharged by the engine at each moment can be determined, meanwhile, the correction requirements of a guidance system are considered, more propellant is reserved, and therefore the performance index is selected as the terminal mass mfMaximum, i.e. minimum, propellant consumption.
max J＝mf
Selecting the starting time t of the engine0And shutdown the deviceTime tfAnd the unit vector component of the engine thrust in the three-dimensional space in the starting process is an optimization parameter, namely
u＝(u1(t),u2(t),u3(t),t0,tf)T
S3, adopting a differential form Gaussian pseudo-spectrum method, dispersing the state time course and the control time course of the transportation system on the track on a series of Gaussian points, then respectively constructing Lagrange interpolation polynomial by using the dispersed states and control to approximate the real state and the control time course, converting the kinetic differential equation constraint into a series of algebraic constraints, and finally converting the optimal control problem into a parameter optimization problem subjected to the series of algebraic constraints through the steps. And solving and optimizing two processes of entering a transfer orbit and entering a target orbit according to the determined mass of the propellant discharged by the engine at each moment and the flight condition. The original complex optimization problem is changed into a nonlinear programming problem which is easy to solve by using a Gaussian pseudo-spectrum method, and the orbit with the minimum fuel consumption in the process of braking by near fire can be obtained by solving the problem. The method considers the ultra-long aftereffect of the nuclear heat engine, and utilizes the nuclear heat engine in the track braking process, so that on the premise of ensuring the track precision, the fuel consumption is reduced, and the extra speed correction consumption caused by the traditional aftereffect is avoided.
A flight manned Mars detection method based on a nuclear transportation system comprises the following steps:
s1, selecting a Lagrangian point 2 from three high potential energy orbits of a Lagrangian point 2, a Lagrangian point 2 and a lunar high orbit as a space base; respectively sending the nuclear propulsion stage, the storage tank stage and the payload stage to a space base by a carrier rocket, and performing on-orbit assembly;
s2, starting from the space base, starting a nuclear heat engine, entering an underground fire transfer track, without discarding a storage tank in a used storage tank level, closing the nuclear heat engine, then transferring by adopting a Hueman transfer track in a nuclear heat single-main power mode, starting the nuclear power engine in a nuclear heat nuclear power double-main power mode in the transferring process, and optimizing the track;
s3, when a Mars approaches, the nuclear heat engine is started again to perform fire approaching braking, stays on the fire surrounding track to wait for the Mars to execute a task, and is closed;
s4, after the manned Mars task is finished, utilizing Mars in-situ resources to fill fuel for the storage box in the rail, restarting the nuclear heat engine by the space transportation system, closing the nuclear heat engine after entering a fire ground transfer rail, and then transferring the nuclear heat engine by adopting a Hoeman transfer rail in a nuclear heat single-master power mode; starting a nuclear power engine in a nuclear-thermal nuclear power double-active power mode in a transfer process, optimizing a track, and returning to a space base;
s5, filling at the space base, and waiting;
s6, returning the personnel who finish the task to the earth surface, and simultaneously conveying the personnel to the space base from the earth surface;
s7, the person enters the space transportation system and runs on fire again.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (12)
1. A space transportation system based on manned Mars detection is characterized by comprising a nuclear propulsion stage, a storage box stage and a payload stage; the nuclear propulsion stage is positioned at the tail end of the transport system, comprises a main engine containing a nuclear reactor and a primary liquid hydrogen storage tank and is used for propelling the whole transport system to enter a fire ground transfer track, track control, fire approach and ground approach braking; the tank stage comprises a plurality of secondary liquid hydrogen tanks for storing a propellant to be supplied to the main engine of the nuclear propulsion stage when the transport system enters the ground fire transfer track; the payload stage comprises a manned payload and a cargo payload, the manned payload comprises a manned detection aircraft and a transfer accommodation cabin, and the cargo payload comprises a Mars landing and ascending detector.
2. The manned Mars sounding-based space transportation system of claim 1, wherein the nuclear propulsion stage, the tank stage and the payload are connected by a truss, the truss is a semi-enclosed truss structure, the tandem tank and the semi-enclosed truss structure in the tank stage are fixed by explosive bolts at a plurality of circumferentially evenly distributed connection points, the tank is thrown after entering the ground fire transfer orbit in a one-time Mars sounding mode and after the propellant in the tank is used up, and is reserved for filling reuse or integral replacement use in a space Mars sounding mode.
3. The manned mars detection-based space transportation system of claim 2, wherein the nuclear propulsion stage, the tank stages, and the payload are connected by a truss, the truss is a central-axis truss structure, the tanks in the tank stages are in a parallel configuration or a series-parallel combination, the parallel tanks are symmetrically arranged around the central-axis truss and axially fixed, and their rejection patterns are identical to the series tanks.
4. The manned mars detection-based space transportation system of claim 1, wherein a primary engine in the nuclear propulsion stage, which contains a nuclear reactor, is selected from a nuclear-thermal single-primary-power form or a nuclear-thermal nuclear-power double-primary-power form; the nuclear heat single main power mode adopts a nuclear heat engine as a main engine and is responsible for completing the tasks of entering an earth fire transfer track, a mars brake entering the track and entering the fire transfer track; the nuclear heat and nuclear power double-active power form adopts a nuclear heat engine and a nuclear power engine, the nuclear heat engine is used for entering the tasks of an earth fire transfer track, a Mars brake entering the track and an earth fire transfer track, and the nuclear power engine is used for accelerating and decelerating during the earth fire reciprocating period.
5. The manned Mars sounding-based space transportation system of claim 4, wherein the nuclear heat engine in the form of nuclear heat single main power adopts a double-turbine pump expansion cycle mode, and mainly comprises two sets of turbine pump systems, a reactor system, a thrust chamber system, valves and a pipeline system;
each turbine pump system mainly comprises a secondary centrifugal pump, an inducer, a secondary counter-force turbine and a lubricating system; the two-stage centrifugal pump, the inducer and the two-stage counter-force turbine are arranged on the same shaft, and the two-stage counter-force turbine drives the centrifugal pump and the inducer to rotate through the shaft; the reactor system mainly comprises a fuel unit, a supporting tube, a control rod and a reactor shielding layer, wherein the whole reactor system is hexagonal honeycomb, the fuel unit is in a small hexagonal hollow structure and is in a reactor hexagon which is formed by the supporting tube and the control rod outside the fuel unit side by side, and the shielding layer is positioned on the periphery of the head part of the reactor system and used for shielding radiation; the thrust chamber system mainly comprises a spray pipe and a reactor outlet small-section cylinder section, and the thrust chamber is cooled in a mode of combining regenerative cooling and radiation cooling; the valve and pipeline system mainly comprises a working medium conduit and various valves;
when the nuclear heat engine is started, a main valve of the storage tank is opened, working media in the storage tank enter a secondary centrifugal pump under the action of the self-pressurization pressure of the storage tank to be pressurized to form high-pressure working media, the high-pressure working media are divided into two paths after passing through the secondary centrifugal pump, one path of the working media is firstly cooled by a regenerative cooling channel through a thrust chamber system, and then enters a control rod to cool the periphery of a reactor after the regenerative cooling of the thrust chamber is completed; the other path enters a supporting tube structure to be heated and plays a role in cooling the interior of the reactor; the two paths of working media are mixed in front of the turbine and enter the turbine to expand and do work to drive the turbine to rotate; the working medium gas after passing through the turbine enters the reactor fuel unit to be heated continuously, finally becomes a high-temperature and high-pressure working medium at the outlet of the reactor, expands through the spray pipe and is discharged at a high speed, and thus thrust is generated.
6. The manned Mars detection-based space transportation system of claim 5, wherein the nuclear heat engine in the nuclear heat nuclear power double-main-power form and the main engine in the nuclear heat single-main-power form operate in the same mode, and the nuclear power engine in the nuclear heat nuclear power double-main-power form utilizes electric energy formed by nuclear heat conversion to act on the liquid hydrogen working medium and jet out at a high speed to form thrust.
7. The manned mars detection-based space transportation system of claim 1, wherein the transportation system further comprises an auxiliary power system for attitude control and orbit control, in addition to the main engine serving as the main power system, and the auxiliary power system and the main power system together form an integrated main and auxiliary power system based on a hydrogen working medium; the auxiliary power system adopts the technical scheme that vaporized hydrogen in a storage tank is heated by a nuclear reactor and then directly sprayed to form thrust, or the vaporized hydrogen and liquid oxygen in the storage tank are used as propellants of the auxiliary power system, the vaporized hydrogen and the liquid oxygen are sprayed to form the thrust after being combusted, and part of the hydrogen after exchanging heat with the nuclear reactor is used as pressurizing gas of the storage tank to implement stable and continuous pressurization.
8. The manned mars detection-based space transportation system according to claim 1, wherein the nuclear heat engines in the nuclear heat single-master power form or the nuclear heat nuclear power double-master power form are all three main engines uniformly distributed in a delta shape, each main engine has two hydraulic swing servo actuators, one is used for pitching, the other is used for yawing, and the swing range of the engine is ± 4 degrees;
four groups of power auxiliary systems which are uniformly distributed are respectively configured on a plurality of axial end faces of the transportation system to carry out multi-degree-of-freedom combined control, 4 installation end faces are adopted, 4 auxiliary power engines of 5 units are installed on each end face, and 5 auxiliary power engines of each unit are installed in a cross shape;
and configuring a single-frame control moment gyroscope outside the payload level as a running and ring fire track attitude control execution structure.
9. A manned Mars detection method based on a nuclear transportation system is characterized by comprising the following steps:
s1, respectively sending the nuclear propulsion stage, the storage box stage and the payload stage to a near-earth orbit by a carrier rocket, and performing on-orbit assembly;
s2, starting the nuclear heat engine, entering the ground fire transfer track, discarding the used storage tank in the storage tank level, closing the nuclear heat engine, then transferring the nuclear heat single main power form by adopting the Hoeman transfer track, and starting the nuclear power engine in the nuclear heat nuclear power double main power form in the transfer process to optimize the track;
s3, when a Mars approaches, the nuclear heat engine is started again to perform fire approaching braking, stays on the fire surrounding track to wait for the Mars to execute a task, and is closed;
s4, after the manned Mars task is finished, the space transportation system restarts the nuclear heat engine, the nuclear heat engine is closed after entering a fire ground transfer track, and then the nuclear heat single main power mode adopts a Hoemann transfer track for transfer; the nuclear power engine is started in the nuclear heat nuclear power double-active power mode in the transfer process, the orbit is optimized, and the earth is directly landed through the manned spacecraft when the orbit approaches the earth.
10. The manned mars detection method based on the nuclear transportation system of claim 9, wherein in step S4, an optimization method of the ground fire transfer point based on the back-thrust of the nuclear heat main power is adopted when entering the ground fire transfer orbit, and the terminal state of the transportation system can meet the condition of entering the ground fire transfer orbit by solving the starting time of the main engine and the attitude direction when starting; the method specifically comprises the following steps:
the method comprises the steps of determining the magnitude of the thrust amplitude and the acting time of a nuclear heat engine by aiming at the interpolation fitting of a thrust curve of the nuclear heat engine, representing and forming the aftereffect thrust of the engine, and using the aftereffect thrust as a constraint condition of track optimization;
selecting the maximum quality optimization target of a terminal of a transportation system entering a ground fire transfer track; selecting unit vector components of engine thrust in a three-dimensional space at the startup and shutdown time and in the startup process as optimization parameters;
adopting a differential form Gaussian pseudo-spectrum method, dispersing the state time history and the control time history of the transportation system on the track on a series of Gaussian points, then respectively constructing Lagrange interpolation polynomials by using the dispersed states and the control to approximate the real state and the control time history, and converting the dynamic differential equation constraint into a series of algebraic constraints; and solving and optimizing two processes of entering a transfer orbit and entering a target orbit according to the determined mass of the propellant discharged by the nuclear heat engine at each moment and the flight condition, so as to obtain the orbit with the minimum fuel consumption in the flight process of entering the ground fire transfer orbit.
11. The manned mars detection method based on the nuclear transportation system, according to claim 9, wherein in the starting phase of the nuclear heat engine, the nuclear heat engine is swung to track the guidance instruction; in the stage that the nuclear heat engine is closed but the aftereffect thrust exists, the attitude is stabilized by means of an auxiliary power engine; during the period of transferring the ground fire after the end of the aftereffect of the nuclear heat engine, the attitude control of the carrier is carried out by using the control moment gyro, and meanwhile, the auxiliary power system participates in the angular momentum unloading of the control moment gyro and the backup control during the period.
12. A flight manned Mars detection method based on a nuclear transportation system is characterized by comprising the following steps:
s1, selecting a Lagrange point 2 as a space base, respectively sending the core propulsion stage, the storage box stage and the effective load stage to the space base by a carrier rocket, and performing on-orbit assembly;
s2, starting from the space base, starting a nuclear heat engine, entering an underground fire transfer track, without throwing away a storage tank in a used storage tank level, closing the nuclear heat engine, then transferring by adopting a Hueman transfer track in a nuclear heat single-main power mode, starting the nuclear power engine in a nuclear heat nuclear power double-main power mode in the transfer process, and optimizing the track;
s3, when a Mars approaches, the nuclear heat engine is started again to perform fire approaching braking, stays on the fire surrounding track to wait for the Mars to execute a task, and is closed;
s4, after the manned Mars task is finished, the Mars in-situ resource is used for filling fuel into the storage box on the rail, the nuclear heat engine is restarted by the space transportation system, the nuclear heat engine is closed after entering a fire ground transfer rail, and then the nuclear heat single main power form is transferred by adopting a Hoeman transfer rail; starting a nuclear power engine in a nuclear-thermal nuclear power double-active power mode in a transfer process, optimizing a track, and returning to a space base;
s5, after filling is carried out again at the space base, waiting is carried out;
s6, returning the personnel who finish the task to the earth surface, and simultaneously conveying the personnel to the space base from the earth surface;
s7, the person enters the space transportation system and runs the fire again.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210287007.0A CN114701667A (en) | 2022-03-22 | 2022-03-22 | Space transportation system based on manned Mars detection and detection method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210287007.0A CN114701667A (en) | 2022-03-22 | 2022-03-22 | Space transportation system based on manned Mars detection and detection method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114701667A true CN114701667A (en) | 2022-07-05 |
Family
ID=82168226
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210287007.0A Pending CN114701667A (en) | 2022-03-22 | 2022-03-22 | Space transportation system based on manned Mars detection and detection method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114701667A (en) |
-
2022
- 2022-03-22 CN CN202210287007.0A patent/CN114701667A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10246200B2 (en) | Centripetal aerodynamic platform spacecraft | |
| EP3423716B1 (en) | A system of using compressed air as a force source and method thereof; airplane | |
| CN109018444A (en) | Rocket-powered mars transporter power system | |
| Baiocco | Overview of reusable space systems with a look to technology aspects | |
| Komar | Hercules single-stage reusable vehicle supporting a safe, affordable, and sustainable human lunar & mars campaign | |
| Williams et al. | Realizing" 2001: A space odyssey": Piloted spherical torus nuclear fusion propulsion | |
| Sippel et al. | A viable and sustainable European path into space–for cargo and astronauts | |
| JP2023537855A (en) | Integrated ammonia-based moderator and propellant for nuclear thermal propulsion stage | |
| Beardsley | The way to go in space | |
| RU196251U1 (en) | Unmanned Helicopter "SHADOW" | |
| Oleson | A 1 MW Solar Electric and Chemical Propulsion Vehicle for Piloted Mars Opposition Class Missions | |
| Borowski et al. | Artificial gravity vehicle design option for NASA's human Mars mission using'bimodal'NTR propulsion | |
| CN114701667A (en) | Space transportation system based on manned Mars detection and detection method | |
| Borowski | Modular growth NTR space transportation system for future NASA human Lunar, NEA and Mars exploration missions | |
| Sumrall et al. | Update on the Ares V to support heavy lift for US space exploration policy | |
| RU111516U1 (en) | SYSTEM OF LIFTING INTO THE EARTH'S ORBIT AND DOWN | |
| Wang et al. | Review, Prospect and Technical Challenge of Launch Vehicle | |
| Benton | Spaceship Discovery-NTR Vehicle Architecture for Human Exploration of the Solar System | |
| Rauwolf et al. | Mission performance of emerging in-space propulsion concepts for one-year crewed Mars missions | |
| Yamanaka | Space plane research activities in Japan | |
| RU2621805C2 (en) | Vehicle for interplanetary communication (versions) | |
| Rubinraut | MARSZUG—A Space Train for Regular Delivery of Astronauts onto Mars | |
| Oeftering | The Impact on Flight Hardware Scavenging on Space Logistics | |
| Rubinraut | Expedition to Mars North Pole and Creation: There Is a Scientific Research Base | |
| ODell et al. | The Mars Base Camp Re-Usable Crewed Descent and Ascent Vehicle |
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 |