CN114408217A - Cargo ship for space station cargo transportation and cargo transportation method - Google Patents
Cargo ship for space station cargo transportation and cargo transportation method Download PDFInfo
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- CN114408217A CN114408217A CN202210094341.4A CN202210094341A CN114408217A CN 114408217 A CN114408217 A CN 114408217A CN 202210094341 A CN202210094341 A CN 202210094341A CN 114408217 A CN114408217 A CN 114408217A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
Abstract
The invention provides a cargo ship for space station cargo transportation and a cargo transportation method. A cargo ship for space station cargo transport comprising: the cargo hold, the aircraft, the mechanical locking mechanism of flange butt joint, driving system, the docking mechanism of space station, pneumatic control flap and landing recovery mechanism, the mechanical locking mechanism of flange butt joint installs on the butt joint face of aircraft and cargo hold, the cargo hold passes through the mechanical locking mechanism detachably of flange butt joint and installs on the butt joint face of aircraft, driving system, the docking mechanism of space station, pneumatic control flap and landing recovery mechanism all install in the aircraft, driving system and landing recovery mechanism install on the lateral wall of aircraft, the docking mechanism of space station installs the afterbody at the aircraft, the corresponding head and the afterbody at the aircraft of installing of pneumatic control flap.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a freight airship and a freight method for space station cargo transportation.
Background
The space station is a deep space springboard stepped by human beings and has important significance on national security. The Chinese space station is comprehensively built before and after 2022 years, and then enters a normalized operation and application stage, so that the requirements of a flexible and efficient cargo transportation system with various forms and low cost are provided. At present, only a space station is used as a space ship for goods transportation and material supply in China, but the space station cannot be reused, the freight cost is high, and the requirement of low-cost goods transportation of the space station is difficult to meet.
Disclosure of Invention
The invention aims to solve the technical problem of the prior art and provides a cargo ship for space station cargo transportation and a cargo transportation method.
The technical scheme for solving the technical problems is as follows: a cargo vessel for space station cargo transport, comprising: a cargo hold, an aircraft, a flange butt mechanical locking mechanism for connecting the cargo hold and the aircraft, a power system, a space station butt mechanism for butt joint with a space station, a pneumatic control flap for adjusting the flight attitude in the reentry process and a landing recovery mechanism, the flange butt joint mechanical locking mechanism is arranged on the butt joint surface of the aircraft and the cargo hold, the cargo hold is detachably arranged on the butt joint surface of the aircraft through the flange butt joint mechanical locking mechanism, the power system, the space station docking mechanism, the pneumatically controlled flap, and the landing recovery mechanism are all mounted in the aircraft, the power system and the landing recovery mechanism are installed on the side wall of the aircraft, the docking mechanism of the space station is installed at the tail of the aircraft, and the pneumatic control flap is correspondingly installed at the head and the tail of the aircraft.
The invention has the beneficial effects that: the locking mechanism of the flange butt joint machine, the power system, the docking mechanism of the space station for docking with the space station, the pneumatic control flap for adjusting the flight attitude in the reentry process and the landing recovery mechanism are installed in the aircraft, the aircraft can return to the space station and can be repeatedly used, the cargo hold is disposable, the cost of the cargo hold is reduced, the freight cost of the space station is reduced, the cargo hold is disposable, the cargo hold has the functions of ascending cargos for the space station and carrying away from wastes, and is controlled to enter the atmosphere again for burning, space fragments are not generated, and the requirements of ascending transportation, descending return and carrying away from the wastes are met.
Further, the power system includes: the main engines, the attitude control engines and the intersection butt joint engines are respectively and correspondingly arranged on two sides of the aircraft.
The beneficial effect of adopting the further scheme is that: the arrangement of the main engines, the attitude and orbit control engines and the intersection butt joint engines enables a power system of the aircraft to have three-level thrust control capability, power descending and deceleration, track transfer maneuver, track and attitude correction control and tail-end butt joint and station-ship separation functions are correspondingly realized respectively, the installation and maintenance are convenient, the engine depth regulation requirement is reduced, the scheme is simple, and the cost is low.
Further, a butt joint protection hatch cover used for protecting the space station butt joint mechanism is installed on the outer side of the space station butt joint mechanism.
The beneficial effect of adopting the further scheme is that: the space station docking mechanism is a mechanical peripheral docking mechanism, is used for docking the freight ship and the space station, and supports the transport of astronauts and the transfer of goods. The mechanical peripheral docking mechanism is arranged on the inner side of the docking protection cabin cover, after the cargo ship approaches the space station, the docking protection cabin cover is opened, and the cargo ship is docked with the space station; and in the launching and returning processes of the cargo ship, the butt joint protection cabin cover is in a closed state, so that the mechanical peripheral butt joint mechanism can be effectively protected, and the repeated use is realized.
Further, the pneumatically controlled flap comprises: the pair of empennages are telescopically arranged at the tail part of the aircraft, and the pair of duck wings are telescopically arranged at two sides of the head part of the aircraft.
The beneficial effect of adopting the further scheme is that: the empennage and the canard are jointly used for adjusting the flight attitude in the reentry process, and simultaneously, the empennage and the canard play a role in pneumatic deceleration. The aircraft adopts the aerodynamic shape of a small flap lift body, a controllable tail wing and a canard wing mode to reduce the aerodynamic design difficulty, realizes the vertical recovery of the horizontal posture of the aircraft, and reduces the technical difficulty of safe soft landing through the vertical landing scheme of the horizontal posture. The pneumatic appearance of the small flap lift body slows down the maximum overload and heat flow, reduces the technical difficulty of the structure and the material and the manufacturing cost, and increases the controllability of the pneumatic control flap. The vertical landing mode supports accurate landing, reduces the ground searching cost, has no special requirement on a landing area, and can land on land and on the sea; the horizontal posture is not easy to overturn, and the landing stability can be improved; and the vertical landing mode of the horizontal attitude does not need to adjust the attitude greatly in the atmospheric reentry and descent landing section, thereby reducing the technical difficulty of attitude control.
Further, the landing retrieval mechanism includes: buffering energy-absorbing structural layer and a plurality of landing leg, buffering energy-absorbing structural layer is energy-absorbing lattice structure, buffering energy-absorbing structural layer cladding is in the bottom of aircraft, it is a plurality of landing leg is installed with extending the both sides of aircraft, the landing leg is for folding and extending the mechanism.
The beneficial effect of adopting the further scheme is that: and the buffering energy-absorbing structural layer is used for bearing most of pneumatic load in the reentry process and impact load at the landing moment. The landing legs are foldable mechanisms, are folded in the aircraft before the landing stage, are unfolded to bear part of impact load during landing, and play a role in adjusting and stabilizing the attitude of the aircraft.
Further, the flange butt mechanical locking mechanism comprises: the air pressure and information transmission system comprises a butt joint sealing cabin door, a butt joint interface of the air pressure and environment control system and a butt joint interface of the electric power and information transmission line, wherein the butt joint sealing cabin door, the butt joint interface of the air pressure and environment control system and the butt joint interface of the electric power and information transmission line are arranged on the butt joint surface of the aircraft and the cargo cabin in a delta shape.
The beneficial effect of adopting the further scheme is that: the arrangement of the butt joint sealing cabin door, the butt joint interface of the air pressure and environment control system and the butt joint interface of the electric power and information transmission line is convenient for the connection of the cargo hold and the aircraft and the information interaction, the control of the cargo hold by the aircraft is convenient, and the stability and the reliability of the cargo ship are improved.
Further, the mechanical locking mechanism for flange butt joint is a clamping jaw type locking mechanism, and the cargo hold is a sealed pressurization type cargo hold, a semi-open type cargo hold or an open type cargo hold.
The beneficial effect of adopting the further scheme is that: the flange butt joint mechanical locking mechanism is a clamping claw type locking mechanism, and can realize the locking and the separation which can be controlled independently between the cargo compartment and the aircraft. The cargo hold adopts the modularized design, supports transportation pressurization, non-pressurization goods and carries out nimble ratio, to different kinds of goods, removable different cargo hold modules adapt to diversified space station freight task, and the cargo hold of modularized design supports same batch processing simultaneously, reduces the production and processing cost.
In addition, the invention also provides a freight transportation method for goods transportation at the space station, based on any one of the freight airships for goods transportation at the space station, the freight transportation method comprises the following steps:
s1, the cargo ship enters the earth atmosphere at the reentry point;
s2, separating the cargo compartment from the aircraft and burning;
and S3, landing the aircraft, and recycling the aircraft.
Further, step S1 is preceded by:
the cargo ship is transferred from the track entering point to the space station crossing track;
the freight ship is butted with the space station;
the freight ship executes the tasks of cargo ascending, load descending and waste carrying-away of the space station;
the cargo ship is separated from the space station;
the cargo vessels move from the space station orbits to the earth re-entry point.
The invention has the beneficial effects that: the cargo compartment is disposable, has the functions of ascending cargos and carrying away waste for the space station, is controlled to enter the atmosphere for burning, does not generate space debris, and meets the requirements of ascending transportation, descending return and carrying away waste.
Further, the aircraft is landed to a landing field in a manner that the aircraft is safely and softly landed in a vertical landing mode with a horizontal posture.
The beneficial effect of adopting the further scheme is that: the aircraft adopts the aerodynamic shape of a small flap lift body, a controllable tail wing and a canard wing mode to reduce the aerodynamic design difficulty, and the technical difficulty of safe soft landing is reduced through a vertical landing scheme with a horizontal posture. The vertical landing mode supports accurate landing, reduces the ground searching cost, has no special requirement on a landing area, and can land on land and on the sea; the horizontal posture is not easy to overturn, and the landing stability can be improved; and the vertical landing mode of the horizontal attitude does not need to adjust the attitude greatly in the atmospheric reentry and descent landing section, thereby reducing the technical difficulty of attitude control.
Advantages of additional aspects of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
Fig. 1 is a schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 2 is a second schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 3 is a third schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 4 is a fourth schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 5 is a fifth schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 6 is a sixth schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 7 is a seventh schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 8 is an eighth schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 9 is a ninth schematic structural view of a cargo ship according to an embodiment of the present invention.
Figure 10 is a ten-fold schematic illustration of the structure of a cargo ship according to an embodiment of the present invention.
Fig. 11 is an eleventh schematic structural view of a cargo ship according to the embodiment of the present invention.
Fig. 12 is a twelve schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 13 is a thirteen schematic structural view of a cargo ship according to an embodiment of the present invention.
Figure 14 is a fourteen schematic structural view of a cargo vessel according to an embodiment of the present invention.
Fig. 15 is a fifteen-level schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 16 is a sixteenth schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 17 is a seventeenth schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 18 is an eighteen schematic structural view of a cargo ship according to an embodiment of the present invention.
Fig. 19 is a schematic flow chart diagram of a shipping method provided by an embodiment of the invention.
Fig. 20 is a schematic flow chart of a shipping method provided by an embodiment of the invention.
The reference numbers illustrate: 1. a cargo compartment; 2. an aircraft; 3. a flange butt mechanical locking mechanism; 4. a power system; 5. a space station docking mechanism; 6. a pneumatically controlled flap; 7. a landing recovery mechanism; 8. a main engine; 9. an attitude and orbit control engine; 10. rendezvous and butt joint the engine; 11. butting a protection cabin cover; 12. a tail wing; 13. duck wings; 14. a buffering energy-absorbing structural layer; 15. landing legs; 16. butting the sealed cabin doors; 17. a docking interface for air pressure and an environmental control system; 18. a docking interface for power and information transmission lines; 19. a butt joint surface; 20. sealing the pressurized cargo compartment; 21. a semi-open cargo tank; 22. an open cargo tank.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
As shown in fig. 1 to 18, an embodiment of the present invention provides a cargo ship for space station cargo transportation, including: the cargo hold 1, the aircraft 2, the flange docking mechanical locking mechanism 3 for connecting the cargo hold 1 and the aircraft 2, the power system 4, the space station docking mechanism 5 for docking with the space station, the pneumatic control flap 6 for adjusting the flight attitude in the reentry process and the landing recovery mechanism 7, the flange docking mechanical locking mechanism 3 is arranged on a docking surface 19 of the aircraft 2 and the cargo hold 1, the cargo hold 1 is detachably arranged on the docking surface 19 of the aircraft 2 through the flange docking mechanical locking mechanism 3, the power system 4, the space station docking mechanism 5, the pneumatic control flap 6 and the landing recovery mechanism 7 are all arranged in the aircraft 2, the power system 4 and the landing recovery mechanism 7 are arranged on the side wall of the aircraft 2, the space station docking mechanism 5 is arranged at the tail part of the aircraft 2, the pneumatic control flaps 6 are correspondingly mounted at the head and tail of the aircraft 2.
The invention has the beneficial effects that: the locking mechanism of the flange butt joint machine, the power system, the docking mechanism of the space station for docking with the space station, the pneumatic control flap for adjusting the flight attitude in the reentry process and the landing recovery mechanism are installed in the aircraft, the aircraft can return to the space station and can be repeatedly used, the cargo hold is disposable, the cost of the cargo hold is reduced, the freight cost of the space station is reduced, the cargo hold is disposable, the cargo hold has the functions of ascending cargos for the space station and carrying away from wastes, and is controlled to enter the atmosphere again for burning, space fragments are not generated, and the requirements of ascending transportation, descending return and carrying away from the wastes are met.
The head of the aircraft and the output end of the power system are made of ceramic heat insulation tile materials, the butt joint surface of the aircraft is made of phenolic aldehyde ablation-resistant composite materials, and the pneumatic control flap is made of carbon or silicon carbide composite materials. The cargo hold is a disposable cargo hold and the aircraft is a recyclable aircraft.
The structure of the flange butting mechanical locking mechanism 3 can be the prior art, for example: patent six: CN 202110357851.1-A mechanism for realizing locking and separation between combined aircrafts and its working method, published 20210907; the seventh patent: CN201811080928. X-A docking type multi-module cooperative flexible taper rod type docking mechanism and a working method thereof, entitled Notice date 20200424.
The structure of the space station docking mechanism 5 may be of the prior art, for example: and a fourth patent: CN 201811347636.8-a spacecraft low impact space butt joint sealing device, grant notice date 20201218; and a fifth patent: CN201811101932. X-a linkage type space butt-joint locking and separating device and method, Kokai 20190308.
The cargo hold and the aircraft are spliced to form a cone structure, the cargo hold and the aircraft are respectively of a semi-cone structure, the heads of the cargo hold and the aircraft are respectively of a semi-parabolic rotation body structure, the two sides of the head of the cargo hold close to the joint surface are respectively provided with a protrusion, the two sides of the head of the aircraft close to the joint surface are respectively provided with an inner groove, and the protrusions are installed in the inner grooves.
The aircraft can be recovered, the pneumatic appearance of the freight airship is improved, the pneumatic appearance of a small flap lifting body is adopted, and the movable canard and the tail wing are configured for pneumatic control; the power system configuration adopts a three-level power system; a landing recovery mechanism is added; a reentry thermal protection system is added.
A cargo ship comprises: the cargo hold adopts a modular design, supports the transportation of pressurized and non-pressurized cargos and carries out flexible proportioning; the aircraft adopts the aerodynamic shape of a small flap lift body and a controllable empennage/canard mode to reduce the aerodynamic design difficulty, and the technical difficulty of safe soft landing is reduced through a vertical landing scheme with a horizontal posture. The low-cost goods transportation in the space station is realized, and the requirements of uplink transportation, downlink return and waste removal are met. The most efficient is reusable, vertical recovery in horizontal attitude. The design of each component can adopt a mature scheme as much as possible, so that the cargo ship scheme has more engineering feasibility.
A cargo ship for space station cargo transport comprising: the cargo hold and the aircraft are tightly connected into a whole through a flange butt mechanical locking mechanism. The flange butt mechanical locking mechanism is butt-jointed with a sealed cabin door, a butt joint interface of an air pressure and environment control system and a butt joint interface of an electric power and information transmission line, the butt joint interfaces are distributed on the butt joint surfaces of the cargo compartment, the aircraft and the cargo compartment in a delta shape, and active control clamping claw type locking mechanisms are arranged at three positions, so that the locking and the separation of the independent control between the cargo compartment and the aircraft are realized. The cargo hold is disposable, only necessary shelf structures, power supply cables, thermal control pipelines and the like are deployed, and the manufacturing cost of the cargo hold is reduced as much as possible. The sealed pressurized support systems, energy sources, and thermal control support equipment required for the cargo compartment are all deployed on the aircraft. Aircraft are reusable, deploying expensive, reusable components, including power systems, space station docking mechanisms, and the like. The cargo ship reduces space station freight costs through a cost-maximizing reusable solution.
The cargo hold adopts a modular design and comprises: a sealed pressurized cargo tank, a semi-open cargo tank, an open cargo tank, wherein: the sealed pressurized cargo hold is used for transporting pressurized cargo; the semi-open cargo hold supports the transportation of pressurized cargo and non-pressurized cargo at the same time, and the proportion of the pressurized cargo and the non-pressurized cargo can be flexibly configured; open cargo holds are used to transport non-pressurized cargo. I.e. different cargo compartment modules may be exchanged for different kinds of cargo, the cargo compartment modules comprising a sealed pressurized cargo compartment, a semi-open cargo compartment and an open cargo compartment. For non-pressurized cargo, it may be disposed within an open portion of a semi-open cargo tank or within an open cargo tank. For pressurized cargo, it may be placed in a sealed pressurized section of a sealed pressurized cargo tank or a semi-open cargo tank. The open portion of the semi-open cargo hold and the bulkheads of the open cargo hold can be controllably opened to remove cargo from the hold using the space station robot and then deposit waste from the space station. The sealed pressurizing part of the sealed pressurizing cargo hold or the semi-open cargo hold is connected with the space station through the space station docking mechanism to support the astronauts to enter and carry the cargo.
The aircraft comprises: driving system, space station docking mechanism, pneumatic control flap, thermal protection system, landing recovery mechanism etc. wherein: the power system comprises: the main engine, the attitude and orbit control engine and the rendezvous and docking engine are three-stage propulsion engines; the main engine adopts a dinitrogen tetroxide/methylhydrazine two-component engine which is used for power descent deceleration and track transfer maneuver, and the storage tank is designed as a low-pressure storage tank and is pressurized by an electric pump. The attitude and orbit control engine adopts a dinitrogen tetroxide/methylhydrazine two-component engine for correcting and controlling the orbit and the attitude, the storage tank is designed as a high-pressure storage tank, and a cold air constant-pressure extrusion type pressurization scheme is adopted. The rendezvous and docking engine adopts a cold air propeller for docking at the tail section, separating from a standing ship and configuring a cold air bottle. The tank is used for storing fuel, and a pressurization system is arranged between the engine and the tank.
The aircraft is provided with a power system, a docking mechanism of a space station, a pneumatic control flap, a thermal protection system and a landing recovery mechanism. Specifically, the power system of the aircraft comprises a main engine, an attitude and orbit control engine and an intersection butt joint engine; the docking mechanism of the space station of the aircraft is a mechanical peripheral docking mechanism; the pneumatic control flap of the aircraft comprises a tail wing and a duck wing; the thermal protection system of the aircraft comprises a ceramic heat insulation tile, a phenolic aldehyde ablation-resistant composite material and a carbon/silicon carbide composite material; the landing recovery mechanism of the aircraft comprises a buffering energy-absorbing structural layer and landing legs.
Preferably, 14 main engines are arranged on the left side and the right side of the aircraft symmetrically, a dinitrogen tetroxide/methylhydrazine double-component engine is adopted for power descent deceleration and track transfer maneuvering, and the storage tank is designed as a low-pressure storage tank and is pressurized by an electric pump. The attitude and orbit control engine is provided with 12 sets, is symmetrically arranged on the left side and the right side of the aircraft, adopts a dinitrogen tetroxide/methylhydrazine double-component engine for correcting and controlling the orbit and the attitude, and adopts a cold air constant pressure extrusion type pressurization scheme, wherein the storage tank is designed as a high-pressure storage tank. The rendezvous and docking engine configuration table is symmetrically arranged on the left side and the right side of the aircraft, cold air propellers are adopted for end docking and station-ship separation, and cold air bottles are adopted for air supply.
The space station butt joint structure is a standard mechanical peripheral butt joint mechanism, is designed according to the standard interface specification of the Chinese space station, is used for butt joint of a cargo ship and the space station, and supports astronauts to carry and transfer goods. The mechanical peripheral docking mechanism is arranged on the inner side of the docking protection cabin cover, after the cargo ship approaches the space station, the docking protection cabin cover is opened, and the cargo ship is docked with the space station; and in the launching and returning processes of the cargo ship, the butt joint protection cabin cover is in a closed state, so that the mechanical peripheral butt joint mechanism can be effectively protected, and the repeated use is realized. The space station docking mechanism is designed according to the standard and is the prior art.
The pneumatically controlled flap comprises: empennages and duck wings; the duck wing is positioned at the head of the aircraft, and is changed from a contracted state to an extended state after the aircraft enters the atmosphere again; the empennage is located the afterbody of aircraft, and the empennage is used for adjusting the flight attitude of reentry process with duck wing jointly, also plays the effect of pneumatic speed reduction simultaneously.
Preferably, the empennage arrangement 2 is arranged at the tail of the aircraft, and can swing when the aircraft enters the atmosphere again and changes from a contraction state to an extension state. The canard wing is configured with 2, is located the head left and right sides of aircraft respectively, and when the aircraft reentry the atmosphere, the shrink state becomes the state of stretching out, is used for adjusting the flight gesture of reentry process with the fin jointly, also plays pneumatic deceleration's effect simultaneously. The two sets of movable flaps increase the pneumatic control capability, reduce the pneumatic appearance design difficulty of the aircraft, and simultaneously facilitate the improvement of accurate descent and landing.
The aircraft also comprises a thermal protection system, wherein the thermal protection system adopts a method of combining a ceramic heat insulation tile material and a phenolic aldehyde ablation-resistant composite material; adopting ceramic heat insulation tile materials at the front edge, windward side and engine nozzle of the aircraft, and bonding the ceramic heat insulation tile materials with the internal cold structure through room temperature vulcanized silicone rubber; the pneumatic control flap is made of carbon/silicon carbide composite material; the back of the aircraft is made of a phenolic aldehyde ablation-resistant composite material.
Preferably, ceramic heat insulation tile materials are adopted on the front edge, the windward side and the engine nozzle of the aircraft, and are bonded with the internal cold structure through room temperature vulcanized silicone rubber; the back of the aircraft is made of a phenolic aldehyde ablation-resistant composite material; the pneumatic control flap is made of carbon/silicon carbide composite material. The heat protection system is designed in a partition mode according to the use temperature requirement, and meanwhile, the design principle of low cost and repeated reusability is considered.
The landing recovery mechanism comprises: the energy absorption structure comprises a buffering energy absorption structure layer and landing legs; the buffering energy-absorbing structure layer is composed of an energy-absorbing lattice structure and is used for bearing most of pneumatic load and impact load at the landing moment in the reentry process; the landing legs are foldable mechanisms, are folded in the aircraft before the landing stage, are unfolded to bear part of impact load during landing, and play a role in adjusting and stabilizing the attitude of the aircraft.
As shown in fig. 1 to 18, further, the power system 4 includes: a plurality of main engines 8 for power descent deceleration and track transfer maneuver, a plurality of attitude and orbit control engines 9 for correction control of track and attitude, a plurality of rendezvous and docking engines 10 for end docking and station ship separation, the plurality of main engines 8, the plurality of attitude and orbit control engines 9 and the plurality of rendezvous and docking engines 10 are respectively and correspondingly installed on both sides of the aircraft 2.
The beneficial effect of adopting the further scheme is that: the arrangement of the main engines, the attitude and orbit control engines and the intersection butt joint engines enables a power system of the aircraft to have three-level thrust control capability, power descending and deceleration, track transfer maneuver, track and attitude correction control and tail-end butt joint and station-ship separation functions are correspondingly realized respectively, the installation and maintenance are convenient, the engine depth regulation requirement is reduced, the scheme is simple, and the cost is low.
The main engine 8 may be of the prior art construction, for example, patent ten: CN 201811528869.8-a power system for launch vehicle upper stage and orbit transfer vehicle, published 20190416.
The configuration of the attitude control motor 9 may be prior art, for example, patent eight: CN 201510046713.6-a rotation control solid attitude and orbit control motor, authorized bulletin date 20160302; the nine patents: CN 201610970965.2-attitude and orbit control coupling control system and method based on pre-swing of engine under large mass center transverse movement, grant notice date 20190809.
The structure of the engine 10 in rendezvous and docking may be of the prior art, for example, patent eleven: cn202110205749. x-an ascender that can carry and deliver samples of the moon, publication No. 20210713.
Wherein, the main engine and the attitude and orbit control engine are dinitrogen tetroxide/methyl hydrazine two-component engines, and the intersection butt joint engine is a cold air propeller.
As shown in fig. 1 to 18, further, a docking protection hatch 11 for protecting the space station docking mechanism 5 is installed outside the space station docking mechanism 5.
The beneficial effect of adopting the further scheme is that: the space station docking mechanism is a mechanical peripheral docking mechanism, is used for docking the freight ship and the space station, and supports the transport of astronauts and the transfer of goods. The mechanical peripheral docking mechanism is arranged on the inner side of the docking protection cabin cover, after the cargo ship approaches the space station, the docking protection cabin cover is opened, and the cargo ship is docked with the space station; and in the launching and returning processes of the cargo ship, the butt joint protection cabin cover is in a closed state, so that the mechanical peripheral butt joint mechanism can be effectively protected, and the repeated use is realized.
As shown in fig. 1 to 18, further, the aerodynamic control flap 6 comprises: a pair of tail wings 12 and a pair of duck wings 13, wherein the pair of tail wings 12 are telescopically installed at the tail part of the aircraft 2, and the pair of duck wings 13 are telescopically installed at both sides of the head part of the aircraft 2.
The beneficial effect of adopting the further scheme is that: the empennage and the canard are jointly used for adjusting the flight attitude in the reentry process, and simultaneously, the empennage and the canard play a role in pneumatic deceleration. The aircraft adopts the aerodynamic shape of a small flap lift body, a controllable tail wing and a canard wing mode to reduce the aerodynamic design difficulty, realizes the vertical recovery of the horizontal posture of the aircraft, and reduces the technical difficulty of safe soft landing through the vertical landing scheme of the horizontal posture. The pneumatic appearance of the small flap lift body slows down the maximum overload and heat flow, reduces the technical difficulty of the structure and the material and the manufacturing cost, and increases the controllability of the pneumatic control flap. The vertical landing mode supports accurate landing, reduces the ground searching cost, has no special requirement on a landing area, and can land on land and on the sea; the horizontal posture is not easy to overturn, and the landing stability can be improved; and the vertical landing mode of the horizontal attitude does not need to adjust the attitude greatly in the atmospheric reentry and descent landing section, thereby reducing the technical difficulty of attitude control.
The structure of the tail 12 can be, among others, the prior art, for example: patent II: CN 201810310026.4-a high-speed hybrid layout vertical take-off and landing aircraft, published japanese 20180810. The structure of the duck wing 13 can be the prior art, for example: and (3) patenting: CN 201810191684.6-a fly control method, a fly control system and an airplane based on canard wing, granting bulletin date 20200908.
As shown in fig. 1 to 18, further, the landing recovery mechanism 7 includes: buffering energy-absorbing structural layer 14 and a plurality of landing leg 15, buffering energy-absorbing structural layer 14 is energy-absorbing lattice structure, buffering energy-absorbing structural layer 14 cladding is in the bottom of aircraft 2, it is a plurality of landing leg 15 is installed extensibly the both sides of aircraft 2, landing leg 15 is for rolling over the extension mechanism.
The beneficial effect of adopting the further scheme is that: and the buffering energy-absorbing structural layer is used for bearing most of pneumatic load in the reentry process and impact load at the landing moment. The landing legs are foldable mechanisms, are folded in the aircraft before the landing stage, are unfolded to bear part of impact load during landing, and play a role in adjusting and stabilizing the attitude of the aircraft.
The landing leg 15 may be of the prior art, such as the following patent: CN 202110091987.2-a gradient energy-absorbing inner core planet detection buffer landing leg based on memory alloy, published 20210430;
as shown in fig. 1 to 18, further, the flange butting mechanical locking mechanism 3 includes: the docking system comprises a docking sealed cabin door 16, a docking interface 17 of an air pressure and environment control system and a docking interface 18 of an electric power and information transmission line, wherein the docking sealed cabin door 16, the docking interface 17 of the air pressure and environment control system and the docking interface 18 of the electric power and information transmission line are arranged on a docking surface 19 of the aircraft 2 and the cargo hold 1 in a delta shape.
The beneficial effect of adopting the further scheme is that: the arrangement of the butt joint sealing cabin door, the butt joint interface of the air pressure and environment control system and the butt joint interface of the electric power and information transmission line is convenient for the connection of the cargo hold and the aircraft and the information interaction, the control of the cargo hold by the aircraft is convenient, and the stability and the reliability of the cargo ship are improved.
The structure of the butt-sealed hatch 16 may be of the prior art, for example, as described in the twelve patents: cn201420815937. x-a sealed form, grant notice date 20150701.
The control method of the flange butt mechanical locking mechanism 3 can be the prior art, such as thirteen patents: CN 201811101446.8-a logistics aircraft and cargo hold, published 20190329.
As shown in fig. 1 to 18, further, the flange butting mechanical locking mechanism 3 is a claw type locking mechanism, and the cargo hold 1 is a sealed pressurized cargo hold 20, a semi-open cargo hold 21 or an open cargo hold 22.
The beneficial effect of adopting the further scheme is that: the flange butt joint mechanical locking mechanism is a clamping claw type locking mechanism, and can realize the locking and the separation which can be controlled independently between the cargo compartment and the aircraft. The cargo hold adopts the modularized design, supports transportation pressurization, non-pressurization goods and carries out nimble ratio, to different kinds of goods, removable different cargo hold modules adapt to diversified space station freight task, and the cargo hold of modularized design supports same batch processing simultaneously, reduces the production and processing cost.
The structure of the cargo hold can be the prior art, for example: patents fourteen: CN 201810246432.9-a multi-functional container system for manufacturing containers employable in the cargo holds of aircraft, publication No. 20181009; patent fifteen: CN 201821541733.6-a logistics transportation system, grant notice date 20190910.
The embodiment of the invention provides a cargo ship for space station cargo transportation, which effectively reduces the cargo transportation task cost through a maximum-benefit reusable technology.
A cargo vessel for space station cargo transport comprising: the cargo hold and the aircraft are tightly connected into a whole through a flange butt mechanical locking mechanism. The cargo hold is disposable, only necessary shelf structures, power supply cables, thermal control pipelines and the like are deployed, and the manufacturing cost of the cargo hold is reduced as much as possible. Aircraft are reusable, deploying expensive, reusable components, including power systems, space station docking mechanisms, and the like.
According to the freight ship, the high-value and reusable component assemblies are deployed on the aircraft and then enter the atmosphere to return to the earth, so that the maximum benefit can be reused, and the cargo transportation task cost of the space station is reduced; meanwhile, the disposable cargo hold can be used for loading space station wastes and is controlled to be burnt out by entering the atmosphere again, and space fragments are not generated.
Further, the cargo compartment is of modular design, including: a sealed pressurized cargo tank, a semi-open cargo tank, an open cargo tank, wherein: the sealed pressurized cargo hold is used for transporting pressurized cargo; the semi-open cargo hold supports the transportation of pressurized cargo and non-pressurized cargo at the same time, and the proportion of the pressurized cargo and the non-pressurized cargo can be flexibly configured; open cargo holds are used to transport non-pressurized cargo.
The beneficial effect of adopting the further scheme is that: the cargo ship can flexibly load pressurized and non-pressurized cargos and is suitable for various cargo transportation tasks of space stations; meanwhile, the cargo hold with the modular design supports the same batch processing, and the production and processing cost is reduced.
Furthermore, the power system of the aircraft comprises a main engine, an attitude and orbit control engine and an intersection butt joint engine which have three stages of propulsion engines; the main engine adopts a dinitrogen tetroxide/methylhydrazine two-component engine which is used for power descent deceleration and track transfer maneuver, and the storage tank is designed as a low-pressure storage tank and is pressurized by an electric pump. The attitude and orbit control engine adopts a dinitrogen tetroxide/methylhydrazine two-component engine for correcting and controlling the orbit and the attitude, the storage tank is designed as a high-pressure storage tank, and a cold air constant-pressure extrusion type pressurization scheme is adopted. The rendezvous and docking engine adopts a cold air propeller for docking at the tail section, separating from a standing ship and configuring a cold air bottle.
The beneficial effect of adopting the further scheme is that: the power system of the aircraft has three-stage thrust control capability, and the requirement on depth adjustment of the engine is reduced; dinitrogen tetroxide/methyl hydrazine is a normal-temperature propellant and is easy to store; the electric pump pressurization scheme is beneficial to adjusting the thrust, and has the advantages of simple scheme and low cost.
Furthermore, the aircraft is provided with a docking structure of the space station, and the mechanical peripheral docking mechanism is designed according to the standard interface specification of the Chinese space station.
The beneficial effect of adopting the further scheme is that: the freight ship can be butted with a space station to support the transport of astronauts and the transfer of goods
Furthermore, the aircraft adopts a small flap lift body aerodynamic profile and a pneumatic control flap of a controllable empennage/canard.
The beneficial effect of adopting the further scheme is that: the pneumatic appearance of the small flap lifting body slows down the maximum overload and heat flow, and reduces the technical difficulty of the structure and the material and the manufacturing cost; the controllability of the pneumatic control flap is improved, and the pneumatic design difficulty is reduced.
Further, the landing recovery mechanism of the air vehicle which reciprocates from the heaven to the earth comprises a buffering energy-absorbing structural layer and landing legs; the buffering energy-absorbing structure layer is composed of an energy-absorbing lattice structure; the landing legs are foldable mechanisms, are folded in the aircraft before the landing stage, and are unfolded during landing.
The beneficial effect of adopting the further scheme is that: the buffering energy-absorbing structural layer is used for bearing most of pneumatic load and impact load at the landing moment in the reentry process; the landing leg is used for bearing part of impact load during landing and plays a role in adjusting and stabilizing the attitude of the aircraft.
Further, the aircraft adopts a vertical landing mode with a horizontal attitude.
The beneficial effect of adopting the further scheme is that: the vertical landing mode supports accurate landing, reduces the ground searching cost, has no special requirement on a landing area, and can land on land and on the sea; the horizontal posture is not easy to overturn, and the landing stability can be improved; and the vertical landing mode of the horizontal attitude does not need to adjust the attitude greatly in the atmospheric reentry and descent landing section, thereby reducing the technical difficulty of attitude control.
As shown in fig. 19 to 20, the present invention further provides a freight transportation method for space station cargo transportation, based on any one of the above-mentioned cargo airships for space station cargo transportation, the freight transportation method including:
s1, the cargo ship enters the earth atmosphere at the reentry point;
s2, separating the cargo compartment from the aircraft and burning;
and S3, landing the aircraft, and recycling the aircraft.
Further, step S1 is preceded by:
the cargo ship is transferred from the track entering point to the space station crossing track;
the freight ship is butted with the space station;
the freight ship executes the tasks of cargo ascending, load descending and waste carrying-away of the space station;
the cargo ship is separated from the space station;
the cargo vessels move from the space station orbits to the earth re-entry point.
The invention has the beneficial effects that: the cargo compartment is disposable, has the functions of ascending cargos and carrying away waste for the space station, is controlled to enter the atmosphere for burning, does not generate space debris, and meets the requirements of ascending transportation, descending return and carrying away waste.
The freight transportation method may comprise the steps of:
s11, phase modulation rendezvous, wherein the cargo ship is transferred from the track entry point to the space station rendezvous track;
s21, docking the station ship, and completing docking of the cargo ship and the space station;
s31, cargo transfer, wherein the cargo ship completes the tasks of cargo ascending, load descending and waste removal at the space station;
s41, separating the station ship from the space station;
s51, returning to transfer, wherein the cargo ship is transferred from the space station orbit to the earth re-entry point;
s61, enabling atmosphere to enter again, enabling the cargo ship to enter the earth atmosphere again, selecting a machine to separate the cargo compartment, enabling the cargo compartment to enter the atmosphere again to be burnt, and enabling the aircraft to fly in a pneumatic deceleration mode;
and S71, descending and landing, wherein the aircraft is safely and softly landed to a landing field in a vertical landing mode with a horizontal posture.
The cargo hold of the cargo ship is disposable, has the functions of moving goods upwards and carrying away wastes for the space station, is controlled to enter the atmosphere again and is burnt out, and space fragments are not generated; the aircraft enters again and returns to support repeated use, has the functions of ascending cargos and descending loads for the space station, effectively reduces the cargo transportation cost of the space station through a repeated use technical approach, and is expected to promote the sustainable development of the space station.
Further, the aircraft is landed to a landing field in a manner that the aircraft is safely and softly landed in a vertical landing mode with a horizontal posture.
The beneficial effect of adopting the further scheme is that: the aircraft adopts the aerodynamic shape of a small flap lift body, a controllable tail wing and a canard wing mode to reduce the aerodynamic design difficulty, and the technical difficulty of safe soft landing is reduced through a vertical landing scheme with a horizontal posture. The vertical landing mode supports accurate landing, reduces the ground searching cost, has no special requirement on a landing area, and can land on land and on the sea; the horizontal posture is not easy to overturn, and the landing stability can be improved; and the vertical landing mode of the horizontal attitude does not need to adjust the attitude greatly in the atmospheric reentry and descent landing section, thereby reducing the technical difficulty of attitude control.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A cargo ship for space station cargo transport, comprising: cargo hold (1), aircraft (2), be used for connecting cargo hold (1) and aircraft (2) flange butt joint mechanical locking mechanism (3), driving system (4), be used for with space station docking mechanism (5) of space station butt joint, be used for adjusting reentry process's flight attitude's pneumatic control flap (6) and landing recovery mechanism (7), flange butt joint mechanical locking mechanism (3) are installed on aircraft (2) and cargo hold (1) butt joint face (19), cargo hold (1) passes through flange butt joint mechanical locking mechanism (3) detachably install on aircraft (2) butt joint face (19), driving system (4) space station docking mechanism (5), pneumatic control flap (6) and landing recovery mechanism (7) all install in aircraft (2), driving system (4) and landing recovery mechanism (7) install aircraft (2)'s butt joint face (19) are retrieved On the side wall, the docking mechanism (5) of the space station is installed at the tail part of the aircraft (2), and the pneumatic control flaps (6) are correspondingly installed at the head part and the tail part of the aircraft (2).
2. A cargo ship for space station cargo transportation according to claim 1, characterized in that the power system (4) comprises: the main engines (8) used for power descent deceleration and track transfer maneuvering, the attitude and orbit control engines (9) used for correcting and controlling the track and the attitude, the intersection butt joint engines (10) used for butt joint of the tail section and separation of the standing ship, and the main engines (8), the attitude and orbit control engines (9) and the intersection butt joint engines (10) are respectively and correspondingly installed on two sides of the aircraft (2).
3. A cargo ship for space station cargo transportation according to claim 1, characterized in that a docking protection hatch (11) for protecting the space station docking mechanism (5) is installed outside the space station docking mechanism (5).
4. A cargo ship for space station cargo transport according to claim 1, characterized in that the pneumatic control flap (6) comprises: a pair of fin (12) and a pair of duck wing (13), a pair of fin (12) telescopically install the afterbody of aircraft (2), a pair of duck wing (13) telescopically install the head both sides of aircraft (2).
5. A cargo ship for space station cargo transportation according to claim 1, characterized in that the landing recovery mechanism (7) comprises: buffering energy-absorbing structural layer (14) and a plurality of landing leg (15), buffering energy-absorbing structural layer (14) are energy-absorbing lattice structure, buffering energy-absorbing structural layer (14) cladding is in the bottom of aircraft (2), it is a plurality of landing leg (15) install with extending the both sides of aircraft (2), landing leg (15) are for folding and unfolding the mechanism.
6. A cargo ship for space station cargo transportation according to claim 1, characterized in that the flange docking mechanical locking mechanism (3) comprises: the air pressure and information transmission system comprises a butt joint sealing cabin door (16), a butt joint interface (17) of an air pressure and environment control system and a butt joint interface (18) of an electric power and information transmission line, wherein the butt joint sealing cabin door (16), the butt joint interface (17) of the air pressure and environment control system and the butt joint interface (18) of the electric power and information transmission line are installed on butt joint surfaces (19) of the aircraft (2) and the cargo hold (1) in a delta shape.
7. A cargo ship for space station cargo transport according to claim 1, characterized in that the flange joint mechanical locking means (3) is a claw locking means and the cargo hold (1) is a sealed pressurized cargo hold (20), a semi-open cargo hold (21) or an open cargo hold (22).
8. A freight ship for space station cargo transportation according to any one of claims 1 to 7, wherein the freight ship comprises:
s1, the cargo ship enters the earth atmosphere at the reentry point;
s2, separating the cargo compartment from the aircraft and burning;
and S3, landing the aircraft, and recycling the aircraft.
9. A method of transporting goods for space station freight according to claim 8, characterised in that step S1 is preceded by:
the cargo ship is transferred from the track entering point to the space station crossing track;
the freight ship is butted with the space station;
the freight ship executes the tasks of cargo ascending, load descending and waste carrying-away of the space station;
the cargo ship is separated from the space station;
the cargo vessels move from the space station orbits to the earth re-entry point.
10. A method of freight transportation for space station freight transportation in accordance with claim 8, characterised in that the aircraft landing is a safe soft landing of the aircraft to the landing site in a vertical landing mode with a horizontal attitude.
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| CN114408217B (en) | 2022-12-13 |
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