CN108128483B - Space station material descending aircraft - Google Patents
Space station material descending aircraft Download PDFInfo
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- CN108128483B CN108128483B CN201711284906.0A CN201711284906A CN108128483B CN 108128483 B CN108128483 B CN 108128483B CN 201711284906 A CN201711284906 A CN 201711284906A CN 108128483 B CN108128483 B CN 108128483B
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- 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
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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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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Abstract
The invention relates to a space station material downlink aircraft, which comprises: a load compartment for carrying a load; a heat shield surrounding the load compartment for cushioning and insulating heat; a support bar between the load compartment and the heat shield for connecting the load compartment and the heat shield; an antenna disposed on the load compartment; and a hollow layer is arranged between the load cabin and the heat-proof shell. The space station material descending aircraft has the advantages of low cost, large load capacity, reasonable and reliable structure.
Description
Technical Field
The invention relates to the field of space station material descending, in particular to a space station material descending aircraft.
Background
The international space station mainly depends on the space shuttle to realize load descending, and after the space shuttle is retired, the alliance manned spacecraft and the dragon spacecraft are adopted to descend. At present, only the manned spacecraft of the Shenzhou is a spacecraft which can realize the load downlink transportation of a space station in China. According to the scale of the uplink load of the space station in China and the proportion of the downlink load and the uplink load of the international space station, the weight of the downlink load is estimated to be at least 6 tons in the operation stage of the space station in China. The descending capacity of the manned spacecraft of the Shenzhou is only 50kg at present, the total descending capacity of the space station in the operation stage does not exceed 1 ton, and the requirement of the future space station operation on load descending can not be met.
The space station in China is about to be put into formal operation before and after 2022 years, and the development of a new generation airship or a novel returning aircraft is difficult to meet the time schedule requirement, and the development cost is very high. If the space station in China starts to operate, no available large-batch load downloading technology exists, a large number of experimental products are overstocked, and the benefit of the space station in China is seriously reduced.
Therefore, at present, a low-cost and engineering-implementable space station material descending device is urgently needed, engineering development is completed in a short time, and the device enters a practical stage so as to meet the urgent need of space stations in China.
Disclosure of Invention
The invention aims to provide a space station material descending aircraft with low cost and engineering implementation and large load capacity.
In order to achieve the above object, the present invention provides a space station material descending aircraft, including:
a load compartment for carrying a load;
a heat shield surrounding the load compartment for cushioning and insulating heat;
a support bar between the load compartment and the heat shield for connecting the load compartment and the heat shield;
an antenna disposed on the load compartment;
and a hollow layer is arranged between the load cabin and the heat-proof shell.
According to one aspect of the invention, the diameter of the load compartment is 740 mm.
According to one aspect of the present invention, the diameter of the heat shield shell is 1440 mm.
According to one aspect of the invention, the total thickness of the heat-proof shell and the hollow layer is 350 mm.
According to one aspect of the invention, there are at least 6 support bars.
In order to achieve the above object, the present invention provides a method for descending the freight load of an aircraft by using materials of a space station, which comprises the following steps:
a. the heat-proof shell and the load cabin are respectively arranged in a cargo bag of the cargo ship and move upwards along with the cargo ship;
b. during parking of the space station, the downward load is loaded into the load cabin, and then the heat-proof shell is installed on the load cabin;
c. fixing the descending aircraft carrying the descending load in the freight transport ship;
d. the space station material descending aircraft is separated from the space station along with the freight airship;
e. the space station material descending aircraft descends along with the freight airship to finish return voyage.
According to one aspect of the invention, in the step c, the space station material descending aircraft is connected with the goods shelves of the goods cabin in the freight transport aircraft through brackets and is fixed in the middle of the passage of the goods cabin.
According to one aspect of the invention, in the step d, after the freight ship performs the last off-track pulse, the freight ship flies at a fixed angle required for the material downlink aircraft to return to the land, the rolling direction rotates at a certain angular speed, and the material downlink aircraft rotates together with the ship body.
According to one aspect of the invention, in the step e, the cargo ship carries the material descending aircraft into the atmosphere, the cargo ship ablates and disintegrates, and the material descending aircraft navigates back through the atmosphere according to the predicted track by autogyration.
According to the space station material descending aircraft, devices such as floating, vibration damping buffering, ejection and spin-off do not need to be additionally arranged, so that the cost of the space station material descending aircraft is lower, and meanwhile, due to the connection relation and the arrangement of the structure size of the load cabin, the heat-proof shell, the hollow layer and other structures in the space station material descending aircraft, the structure of the space station material descending aircraft is reasonable and reliable, a large number of loads can be loaded, the safety of the aircraft can be guaranteed, and the overall damage caused by impact or impact can be avoided. In addition, the battery endurance time of the aircraft can reach more than 30 days, sufficient time can be reserved for sea surface searching work, and the searching cost is saved.
Drawings
FIG. 1 schematically illustrates a structural layout of a space station material descending aircraft according to one embodiment of the present invention;
fig. 2 schematically shows a block diagram of a space station material descending aircraft according to the present invention loaded in a cargo freighter.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Fig. 1 schematically shows a structural layout of a space station material descending aircraft according to an embodiment of the present invention. As shown in fig. 1, the space station material descending aircraft according to the present invention includes a load compartment 1, a heat-proof shell 2, a support pole 3, and an antenna 4. The space station material descending aircraft according to the invention has a hollow layer 5 between the load cabin 1 and the heat protection shell 2. In the present embodiment, the load compartment is located at the center of the descending aircraft of the present invention, and the heat shield shell 2 surrounds the load compartment 1 from the outside in a ring-shaped configuration. In the present embodiment, the support rods 3 fixedly connect the outer surface of the load compartment 1 and the inner surface of the heat shield 2 to each other. At least six support rods 3 are arranged in the space station material descending aircraft according to the invention. In the present embodiment, as shown in fig. 1, the space station material descending aircraft is provided with six support rods 3, and the six support rods 3 are arranged in order, that is, the angle between every two support rods 3 is 90 °. In the present invention, the antenna 4 is provided on the load compartment 1. As shown in fig. 1, in the present embodiment, the space station material descending aircraft is provided with two pairs of antennas, and the two pairs of antennas are oppositely arranged and correspondingly arranged beside two opposite support rods 3. As shown in fig. 1, specifically, one of the pair of antennas 4 is located on one side of the support rod 3, and the other is located on the other side of the support rod 3.
The diameter of the load compartment 1 of the space station material descending aircraft according to the invention is 740 mm. The diameter of the heat-proof shell 2 is 1440mm, and the total thickness of the heat-proof shell 2 and the hollow layer 5 is 350 mm.
According to the space station material descending aircraft disclosed by the invention, in order to fully improve the effective space of a descending load, the diameter of the load cabin 1 is set to be 740mm under the condition that the constraint of an accessible docking port is met, so that the effective loading space of the descending load can be ensured to be not less than 50mm x 50 mm. The heat-proof shell 2 is installed on the orbit by astronauts, and can fully utilize the cargo cabin passage space of the cargo ship, so that the overall diameter of the space station material descending aircraft can reach 1440 mm. A hollow layer 5 is arranged between the heat-proof shell 2 and the load cabin 1, and the heat-proof shell 2 is connected with the load cabin 1 through a supporting rod 3. In the present invention, the hollow layer 5 has two functions: firstly, space is provided for the antenna 4 extending out of the surface of the cabin body, and an antenna extending mechanism required for extending the antenna 4 out of the heat-proof shell 2 is avoided; and secondly, the density of the material descending aircraft is reduced as much as possible, so that the aircraft can automatically float after splashing off the sea when returning, and an airbag lamp floating device is avoided being additionally arranged. Therefore, the space station material descending aircraft is reasonable and reliable in overall structure, and does not need to be additionally provided with other auxiliary devices, so that the cost of the space station material descending aircraft is lower, and the load capacity is larger.
Meanwhile, in order to make the structure of the space station material descending aircraft of the invention further simple and reliable, the cabin body is required to have strong shock resistance without adopting landing buffer devices such as parachutes and reverse thrust engines, and therefore, the support rod 3 arranged between the load cabin 1 and the heat-proof shell 2 has the functions of vibration reduction and buffering. Meanwhile, in the present invention, the heat-proof shell 2 has a multi-layer structure, or adopts an inflatable heat-insulating structure, so that it has a shock-absorbing and buffering function.
Fig. 2 schematically shows a block diagram of a space material descending aircraft according to the present invention loaded in a cargo freighting ship. As shown in fig. 2, the space station material descending aircraft according to the present invention is powered up and down by a cargo ship 6. As shown in fig. 2, the cargo ship 6 includes a docking port 601 into which the aircraft of the present invention can be loaded, a shelf 602 that supports the aircraft of the present invention, and a cargo compartment passage 603 that houses the aircraft of the present invention. In this embodiment, the terminal material descending aircraft is supported on the racks by two supports 604.
According to the arrangement of the space station material descending aircraft and the freight ship for carrying the space station material descending aircraft to ascend or descend, the invention also provides a method for utilizing the space station material descending aircraft freight load, which comprises the following steps:
a. the heat-proof shell and the load cabin are respectively arranged in a cargo bag of the cargo ship and move upwards along with the cargo ship;
b. during parking of the space station, the downward load is loaded into the load cabin, and then the heat-proof shell is installed on the load cabin;
c. fixing the descending aircraft carrying the descending load in the freight transport ship;
d. the space station material descending aircraft is separated from the space station along with the freight airship;
e. the space station material descending aircraft descends along with the freight airship to finish return voyage.
In step a, first, the ground assembly stage is passed, and the heat-proof shell is in a prefabricated split or non-unfolded state, so as to pass through the docking port 601 of the cargo ship.
In the above steps b and c, during the docking of the space station, the astronaut loads the load compartment 1 with the downward load, then fixes the heat-proof shell 2 on the load compartment 1, and then connects the assembled material downward aircraft with the goods compartment shelf 602 through the bracket 604, thereby fixing the aircraft in the middle of the goods compartment passage 603.
In the step d, after the freight ship executes the last off-track pulse, the freight ship flies at a fixed angle required by the material descending aircraft returning to the land, the rolling direction rotates at a certain angular speed, and the material descending aircraft rotates together with the ship body.
In the step e, the cargo ship carries the material descending aircraft to enter the atmosphere, the cargo ship ablates and disintegrates, and all parts of the ship body are thrown away from the track direction under the action of the rotating centrifugal force. The material descending aircraft passes through the atmosphere and splashes down to the sea surface by self-rotation according to an expected track.
And then, the material descending aircraft floats on the sea surface, the AIS system is arranged on the material descending aircraft, and the AIS system sends out signals to the rescue ship to search and salvage.
According to the arrangement and the method, the space of the sealed cabin of the freight airship is fully utilized, and a spacecraft assembles a material descending aircraft in orbit, so that the load loading space is maximized, and meanwhile, enough space is provided for realizing high-strength fragment impact resistance and water impact resistance and automatic floating on the sea with low overall density through structural design, thereby avoiding the addition of landing systems such as parachutes, air bags and the like; the separation, the rail falling, the spin starting and the reentry of the freight airship from the space station are fully utilized, and the reentry returns to and splashes down the sea by an uncontrolled trajectory, so that the ejection and spin starting devices are avoided, and the restriction of the ejection on the installation of the interface of the freight airship is eliminated; by utilizing the AIS (automatic identification system of the ship) widely applied to the ship, nearby ships are attracted to search and salvage in a bonus manner, and the goods are delivered to the appointed port, so that low-cost downlink recovery of the goods at the space station is realized.
In order to realize low-cost descending of materials of the space station, the load cabin 1 of the aircraft for descending the materials of the space station adopts a reuse technology. The load cabin 1 equipment mainly comprises a vibration damping buffer device, a battery, a landing search beacon machine, a beacon antenna, an AIS system and a load environment maintaining device. The reuse of the load compartment is achieved from two aspects:
firstly, mounting platform equipment at the irregular position of the edge of the cabin body as much as possible, and placing a load in the central space of the cabin; the reasonable design load loading space satisfies most of down load of space station and lays the demand, possesses the ability that satisfies special load demand through the repacking, improves 1 space utilization efficiency in load cabin as far as possible.
The vibration reduction and buffering design of the whole cabin ensures that the cabin structure and equipment of the load cabin 1 are not damaged by landing impact; by the sealing design of the cabin body, the load cabin is prevented from being eroded by seawater and salt mist during the floating period of the sea surface.
The low-cost, low-density, anti-impact, vibration-absorbing and heat-proof structure is a key technology of a material downlink aircraft of a space station. The heat-proof shell 2 is disposable, and the cost is low; the density of the heat-proof shell 2 is low, so that the overall density of the material descending aircraft can be effectively reduced; in order to prevent the freight ship from fully colliding with the aircraft descending due to the incomplete ablation of goods and materials in the reentry process and to ensure the failure of the heat-proof shell, the heat-proof shell needs strong impact resistance; in order to reduce the impact on the load compartment when exposed to water, the heat protection shell 2 needs to have a certain shock absorption capacity. Because the heat-proof shell 2 has abundant space, low-cost ablation materials with enough thickness can be used to form a multilayer structure with nonmetal structural materials, even if the surface heat-proof material layer is impacted or worn out, the inner heat-proof material layer can still play the role of ablation heat-proof due to the protection of the structural material layer, and the multilayer structure is reasonably designed to absorb certain vibration.
AIS is widely applied to ships and becomes an important means for governments of various countries to manage the ships. Each legal vessel is equipped with AIS and can be positioned relative to each other. The re-entry capsule is provided with AIS, and other ships nearby can search and salvage through AIS positioning technology, and attract the ships to the appointed port for returning to the party in a bonus mode. Meanwhile, the international universality of AIS can be utilized to ensure that the returning capsule can not be stolen by other ships.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A method of loading a space station material descending aircraft with freight, the space station material descending aircraft comprising:
a load compartment (1) for carrying a load;
a heat shield (2) surrounding the load compartment for cushioning and insulating heat;
the method comprises the following steps:
a. the heat-proof shell (2) and the load cabin (1) are respectively arranged in a cargo bag of the cargo ship and move upwards along with the cargo ship;
b. during the parking space station, loading the downward load into the load cabin (1), and then installing the heat-proof shell (2) on the load cabin (1);
c. fixing the descending aircraft carrying the descending load in the freight transport ship;
d. the space station material descending aircraft is separated from the space station along with the freight airship;
e. the space station material descending aircraft descends along with the cargo ship, the cargo ship ablates and disintegrates, and the space station material descending aircraft finishes return flight.
2. The method for freight loading of a space station material descending aircraft according to claim 1, wherein in the step c, the space station material descending aircraft is connected with the goods shelf of the freight cabin in the freight aircraft through a bracket and is fixed in the middle of the passage of the freight cabin.
3. The method for freight loading of a spacecraft for space station logistics in accordance with claim 1, wherein in said step d, after the spacecraft for freight transportation has performed the last off-track pulse, the spacecraft for freight transportation is flown at a fixed angle required for the spacecraft for logistics to return to the land, the spacecraft for logistics being rotated at an angular speed in a rolling direction, and the spacecraft for logistics being rotated together with the vessel body.
4. The method according to claim 1, wherein in said step e, the cargo spacecraft carries the cargo spacecraft into the atmosphere, the cargo spacecraft ablates and disintegrates, and the cargo spacecraft navigates back through the atmosphere by autorotation in a projected trajectory.
5. The method for freight loading of a spacecraft equipped for downward flight of space station materials according to claim 1, wherein the spacecraft equipped for downward flight of space station materials further comprises: a support rod (3) located between the load compartment (1) and the heat shield (2) for connecting the load compartment (1) and the heat shield (2);
an antenna (4) arranged on the load compartment (1);
a hollow layer (5) is arranged between the load compartment (1) and the heat-proof shell (2);
the antenna (4) is provided with two pairs, the two pairs of antennas (4) are oppositely arranged, one pair of antennas (4) is respectively arranged on two sides of one supporting rod (3), and the other pair of antennas (4) is respectively arranged on two sides of the other supporting rod (3).
6. A method for space station material descending aircraft freight load according to claim 1, characterised in that the diameter of the load compartment (1) is 740 mm.
7. A method for space station material descending aircraft freight load according to claim 1, characterised in that the diameter of the heat protection shell (2) is 1440 mm.
8. The method for the space station material descending aircraft freight load according to claim 5, characterized in that the total thickness of the heat protection shell (2) and the hollow layer (5) is 350 mm.
9. A method for space station material descending aircraft freight load according to claim 5, characterised in that the support bars (3) are provided with at least 6.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711284906.0A CN108128483B (en) | 2017-12-07 | 2017-12-07 | Space station material descending aircraft |
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| CN201711284906.0A CN108128483B (en) | 2017-12-07 | 2017-12-07 | Space station material descending aircraft |
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| CN108128483B true CN108128483B (en) | 2021-05-18 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112660424A (en) * | 2021-01-05 | 2021-04-16 | 北京空间飞行器总体设计部 | Method for expanding space station energy by utilizing freight ship |
| CN112963501B (en) * | 2021-02-08 | 2022-03-25 | 浙江大学 | Return capsule buffering shell filled with phase-change material |
| CN114408217B (en) * | 2022-01-26 | 2022-12-13 | 中国科学院空间应用工程与技术中心 | Cargo ship for space station cargo transportation and cargo transportation method |
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| US6945498B2 (en) * | 2002-10-15 | 2005-09-20 | Kistler Aerospace Corporation | Commercial experiment system in orbit |
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Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10081446B2 (en) * | 2015-03-11 | 2018-09-25 | William C. Stone | System for emergency crew return and down-mass from orbit |
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|---|---|---|---|---|
| US4896847A (en) * | 1988-11-02 | 1990-01-30 | General Dynamics Corporation, Convair Division | Aerodynamic braking system for recovering a space vehicle |
| US6945498B2 (en) * | 2002-10-15 | 2005-09-20 | Kistler Aerospace Corporation | Commercial experiment system in orbit |
| CN102730203A (en) * | 2012-07-10 | 2012-10-17 | 西北工业大学 | Reentry inflation cover with controllable direction |
| CN106428634A (en) * | 2016-09-22 | 2017-02-22 | 北京空间飞行器总体设计部 | Main load-bearing structure suitable for ballistic reentry recovery capsule |
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