CN113353295A - Solid fuel space capsule - Google Patents
Solid fuel space capsule Download PDFInfo
- Publication number
- CN113353295A CN113353295A CN202110727989.6A CN202110727989A CN113353295A CN 113353295 A CN113353295 A CN 113353295A CN 202110727989 A CN202110727989 A CN 202110727989A CN 113353295 A CN113353295 A CN 113353295A
- Authority
- CN
- China
- Prior art keywords
- capsule
- solid fuel
- space capsule
- threaded rod
- auger
- 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
- 239000002775 capsule Substances 0.000 title claims abstract description 60
- 239000004449 solid propellant Substances 0.000 title claims abstract description 42
- 238000007599 discharging Methods 0.000 claims abstract description 9
- 239000000463 material Substances 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 2
- 239000000446 fuel Substances 0.000 description 18
- 238000012856 packing Methods 0.000 description 5
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 4
- 239000002760 rocket fuel Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G4/00—Tools specially adapted for use in space
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Abstract
The invention relates to the field of spaceflight, and discloses a solid fuel space capsule which is characterized by comprising a capsule body, a movable top cover, a threaded rod, a feeding auger, a discharging auger and a space capsule guaranteeing system, wherein the capsule body is internally provided with the threaded rod, the movable top cover is provided with a threaded hole matched with the threaded rod in a rotating mode, the movable top cover moves up and down along with the forward rotation and the reverse rotation of the threaded rod, the capsule body is provided with the feeding auger and the discharging auger, and the top of the capsule body is connected with the space capsule guaranteeing system. The invention has the advantages of reducing the difficulty of launching the spacecraft and reducing the launching cost.
Description
Technical Field
The invention relates to the field of spaceflight, in particular to a solid fuel space capsule.
Background
The existing spacecraft equipment for lunar landing and other interstellar navigation is large, the requirement for propelling rocket fuel is large, the rocket launched from the ground once is thousands of tons less and ten thousand tons more, and the development of the large rocket needs a large amount of manpower, material resources, financial resources and technical breakthroughs, so that the further development of human aerospace industry is restricted, and a new spacecraft launching mode and a propulsion technology for spacecraft in space operation are developed.
Disclosure of Invention
Aiming at the defects of the existing large spacecraft launching technology, the invention provides the solid fuel space capsule, and the solid fuel space capsule is used for filling fuel for the thrust rocket of the large spacecraft, so that the difficulty of launching the spacecraft is reduced, and the launching cost is reduced.
In order to solve the technical problems, the invention adopts the following technical scheme.
The utility model provides a solid fuel space capsule, a serial communication port, including the cabin body, remove the top cap, the threaded rod, the feeding auger, ejection of compact auger, space capsule guarantee system, the internal portion of cabin is equipped with the threaded rod, remove and set up on the top cap and suit rotation fit's screw hole with the threaded rod, remove the top cap and realize reciprocating along with the forward rotation and the reverse rotation of threaded rod, be provided with feeding auger on the cabin body, ejection of compact auger, space capsule guarantee system is connected at the top of the cabin body.
Preferably, the feeding auger and the discharging auger are made of light materials.
The invention has the advantages that: the solid fuel space capsule is established on the near-ground track, so that fuel can be conveniently filled into the thrust rocket of the large-scale spacecraft, the difficulty of launching the spacecraft is reduced, and the launching cost is reduced.
Drawings
FIG. 1 is a schematic view of the outline structure of a solid fuel space capsule, a freight rocket and a power rocket of a spacecraft of the invention.
Wherein, each reference number in the figure is: 1. a solid fuel space capsule; 1.1, moving a top cover; 1.2, bottom; 1.3, top; 1.4, a threaded rod; 1.5, a discharging auger; 1.6, a feeding auger; 1.7, a cabin body; 1.8, a space capsule guarantee system; 2. a freight rocket; 2.1, a feeding freight warehouse; 3. a powered rocket; 3.1, a power rocket fuel bin; 4. the spacecraft is loaded.
Detailed Description
In order to make the technical solutions of the present invention better understood and make the aforementioned objects, features and advantages of the present invention comprehensible, the present invention is further described in detail with reference to the following embodiments and accompanying drawings.
As shown in fig. 1, the solid fuel space capsule comprises a capsule body 1.7, a movable top cover 1.1, a threaded rod 1.4, a feeding auger 1.6, a discharging auger 1.5 and a space capsule guaranteeing system 1.8, wherein the threaded rod 1.4 is arranged in the capsule body, a threaded hole matched with the threaded rod 1.4 in a rotating mode is formed in the movable top cover 1.1, the movable top cover 1.1 can move up and down along with the forward rotation and the reverse rotation of the threaded rod 1.4, the feeding auger 1.6 and the discharging auger 1.5 are arranged on the capsule body 1.7, and the space capsule guaranteeing system 1.8 is connected to the top of the capsule body 1.7.
The feeding auger 1.6 and the discharging auger 1.5 are made of light materials.
The capsule body of the solid fuel capsule of the invention is loaded with solid fuel, the interior of the capsule does not bear high temperature and high pressure, and only the capsule body needs to resist the space environment, so the capsule can be made thinner.
The movable top cover of the solid fuel space capsule can move up and down and is a special part related to fuel sinking.
The invention relates to a threaded rod of a solid fuel space capsule, which is a component for pushing a movable top cover to move up and down.
The packing auger of the solid fuel space capsule is a component for inputting and outputting fuel.
Because of space weightlessness, the solid fuel can not be completely gathered at the discharge port in the cabin body, and the fuel is pushed to the bottom discharge port by the movable top cover, so that the fuel sinks.
Because of space weightlessness and small friction between fuel in the packing auger and the wall of the packing auger, the packing auger can be made of light materials.
Because the fuel in the solid fuel space capsule is input in batches, the space capsule can be made to be very large, and can continuously fill fuel for a plurality of batches of large-scale spacecrafts for a long time.
The working mode is that the solid fuel space capsule 1 without or carrying a little solid fuel is launched to a near-ground track, a movable top cover 11 is pushed to the top 1.3 through the rotation of a threaded rod 1.4, a freight rocket 2 is launched to the near-ground track to be synchronously butted with the solid fuel space capsule 1, the movable top cover of a feeding freight cabin 2.1 is moved towards the bottom to enable the fuel to sink, the fuel at the butted port is sent into the solid fuel space capsule 1 through a feeding packing auger 1.6, the operations are carried out for a plurality of times, and the solid fuel space capsule 1 is filled. The power rocket 3 in the empty bin is launched to the near-earth orbit to be butted with the solid fuel space capsule 1, the movable top cover of the power rocket fuel bin 3.1 pushes the top, the movable top cover 1.1 of the solid fuel space capsule 1 moves to the bottom, fuel is input into the power rocket fuel bin 3.1 through the discharging auger 1.5, and the butt joint port is separated after the fuel is filled.
And butting the power rocket 3 with the spacecraft load 4, igniting and starting, and driving the spacecraft to move by the power rocket 3.
Firstly, a solid fuel space capsule is built on a near-earth orbit, the solid fuel space capsule (capsule is empty capsule) is launched to the near-earth orbit by using the existing rocket in the first step, a freight capsule loaded with solid fuel is launched to the near-earth orbit in the second step, the freight capsule is butted with the solid fuel space capsule, the solid fuel in the freight capsule is filled into the solid fuel space capsule, and the steps are carried out for several times until the solid fuel space capsule is filled with the fuel. Secondly, a thin-shell solid fuel rocket with application number 2019211975465 is used as a thrust rocket for the large spacecraft to run in space, fuel required by the thin-shell solid fuel rocket is injected from a solid fuel space capsule, the solid fuel rocket without fuel is firstly launched to a near-earth orbit to be butted with the solid fuel space capsule, the fuel is input into a fuel bin of the solid fuel rocket from the space capsule, then the spacecraft is launched to the near-earth orbit to be butted with the solid fuel rocket, the rocket is started, and a spacecraft flight task is started. By utilizing the technology, the difficulty of launching the spacecraft is reduced, the existing rocket can complete the task of launching the large spacecraft, and meanwhile, the resident orbit of the solid fuel space capsule can be recycled, so that the launching cost is reduced.
Claims (2)
1. The utility model provides a solid fuel space capsule, a serial communication port, including the cabin body, remove the top cap, the threaded rod, the feeding auger, ejection of compact auger, space capsule guarantee system, the internal portion of cabin is equipped with the threaded rod, remove and set up on the top cap and suit rotation fit's screw hole with the threaded rod, remove the top cap and realize reciprocating along with the forward rotation and the reverse rotation of threaded rod, be provided with feeding auger on the cabin body, ejection of compact auger, space capsule guarantee system is connected at the top of the cabin body.
2. The solid fuel space capsule of claim 1, wherein the feeding auger and the discharging auger are made of light materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110727989.6A CN113353295A (en) | 2021-06-29 | 2021-06-29 | Solid fuel space capsule |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110727989.6A CN113353295A (en) | 2021-06-29 | 2021-06-29 | Solid fuel space capsule |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113353295A true CN113353295A (en) | 2021-09-07 |
Family
ID=77537095
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110727989.6A Pending CN113353295A (en) | 2021-06-29 | 2021-06-29 | Solid fuel space capsule |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113353295A (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2511970A1 (en) * | 1981-09-02 | 1983-03-04 | Europ Agence Spatiale | Satellite for refuelling geostationary satellites - transfers fuel from supplementary tanks on docking to increase operating time |
| US7559508B1 (en) * | 2006-12-07 | 2009-07-14 | Taylor Thomas C | Propellant depot in space |
| US20110042521A1 (en) * | 2008-11-18 | 2011-02-24 | Sample Daniel S | Spacecraft Launch and Exploration System |
| CN103950554A (en) * | 2014-04-10 | 2014-07-30 | 中国运载火箭技术研究院 | Spacecraft propellant in-orbit filling system and spacecraft propellant in-orbit filling method |
| CN104691781A (en) * | 2015-01-13 | 2015-06-10 | 中国空间技术研究院 | Space-based platform based on open structure |
| US20160207641A1 (en) * | 2015-01-21 | 2016-07-21 | Gateway Galactic, Inc. | Fuel depot in space |
| CN106379561A (en) * | 2016-12-07 | 2017-02-08 | 上海宇航***工程研究所 | In-orbit extensible spacecraft for space fuel storage |
| CN107856885A (en) * | 2017-10-25 | 2018-03-30 | 北京空间技术研制试验中心 | Spacecraft is in-orbit to add the autonomous interaction of propellant data and disposal system and method |
| CN109455313A (en) * | 2018-11-15 | 2019-03-12 | 河北工业大学 | For space propultion from pressurized fuel case |
| CN110539899A (en) * | 2019-08-26 | 2019-12-06 | 北京空间技术研制试验中心 | System and method for blowing off residual propellant in on-orbit replenishing pipeline of spacecraft |
| CN110589029A (en) * | 2019-10-18 | 2019-12-20 | 深圳市魔方卫星科技有限公司 | Solid fuel micro propeller |
| CN111406022A (en) * | 2017-07-21 | 2020-07-10 | 诺思路·格鲁曼创新***公司 | Spacecraft service device and related components, systems and methods |
| CN111452999A (en) * | 2020-04-24 | 2020-07-28 | 北京卫星环境工程研究所 | Device and method suitable for cyclic supply of gas resources of space station |
| CN211116306U (en) * | 2019-07-29 | 2020-07-28 | 杨德安 | Thin-shell solid fuel rocket |
-
2021
- 2021-06-29 CN CN202110727989.6A patent/CN113353295A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2511970A1 (en) * | 1981-09-02 | 1983-03-04 | Europ Agence Spatiale | Satellite for refuelling geostationary satellites - transfers fuel from supplementary tanks on docking to increase operating time |
| US7559508B1 (en) * | 2006-12-07 | 2009-07-14 | Taylor Thomas C | Propellant depot in space |
| US20110042521A1 (en) * | 2008-11-18 | 2011-02-24 | Sample Daniel S | Spacecraft Launch and Exploration System |
| CN103950554A (en) * | 2014-04-10 | 2014-07-30 | 中国运载火箭技术研究院 | Spacecraft propellant in-orbit filling system and spacecraft propellant in-orbit filling method |
| CN104691781A (en) * | 2015-01-13 | 2015-06-10 | 中国空间技术研究院 | Space-based platform based on open structure |
| US20160207641A1 (en) * | 2015-01-21 | 2016-07-21 | Gateway Galactic, Inc. | Fuel depot in space |
| CN106379561A (en) * | 2016-12-07 | 2017-02-08 | 上海宇航***工程研究所 | In-orbit extensible spacecraft for space fuel storage |
| CN111406022A (en) * | 2017-07-21 | 2020-07-10 | 诺思路·格鲁曼创新***公司 | Spacecraft service device and related components, systems and methods |
| CN107856885A (en) * | 2017-10-25 | 2018-03-30 | 北京空间技术研制试验中心 | Spacecraft is in-orbit to add the autonomous interaction of propellant data and disposal system and method |
| CN109455313A (en) * | 2018-11-15 | 2019-03-12 | 河北工业大学 | For space propultion from pressurized fuel case |
| CN211116306U (en) * | 2019-07-29 | 2020-07-28 | 杨德安 | Thin-shell solid fuel rocket |
| CN110539899A (en) * | 2019-08-26 | 2019-12-06 | 北京空间技术研制试验中心 | System and method for blowing off residual propellant in on-orbit replenishing pipeline of spacecraft |
| CN110589029A (en) * | 2019-10-18 | 2019-12-20 | 深圳市魔方卫星科技有限公司 | Solid fuel micro propeller |
| CN111452999A (en) * | 2020-04-24 | 2020-07-28 | 北京卫星环境工程研究所 | Device and method suitable for cyclic supply of gas resources of space station |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9676499B2 (en) | Fuel depot in space | |
| EP1163152B1 (en) | Payload carry and launch system | |
| Marciniak et al. | Development of the ILR-33 “Amber” sounding rocket for microgravity experimentation | |
| Tadini et al. | Active debris multi-removal mission concept based on hybrid propulsion | |
| Sippel et al. | A viable and sustainable European path into space–for cargo and astronauts | |
| CN113353295A (en) | Solid fuel space capsule | |
| CN110525695A (en) | A kind of spacecraft propulsion developing agent storage and manage split type system | |
| Mercer et al. | Solar electric propulsion concepts for human space exploration | |
| Salotti | Launcher size optimization for a crewed Mars mission | |
| Kutter | Distributed launch-enabling beyond LEO missions | |
| Deneu et al. | Promising solutions for fully reusable two-stage-to-orbit configurations | |
| Benton | Crew and Cargo Landers for Human Exploration of Mars-Vehicle System Design | |
| Whitehead | Single stage to orbit mass budgets derived from propellant density and specific impulse | |
| Bradford et al. | Concept assessment of a hydrocarbon fueled RBCC-powered military spaceplane | |
| Anselmo et al. | Active debris removal space mission concepts based on hybrid propulsion | |
| Tadini et al. | Active debris removal space mission concepts based on hybrid propulsion | |
| Stough | NASA’S SPACE LAUNCH SYSTEM OPENS NEW FRONTIERS FOR HIGH C3 SCIENCE MISSIONS TO DEEP SPACE | |
| Hempsell et al. | The requirement generation process for the SKYLON launch system | |
| Smith | Interstellar Probe on Space Launch System (SLS) | |
| Dumont et al. | Suitability of reusability and in-situ propellant production for a Lunar transportation system | |
| Haws et al. | SLS Capability: Sometimes You Need a Big Truck | |
| Torgerson et al. | Methodologies for Construction of the First Lunar Spaceport | |
| Ito et al. | Repetitive-Use Rocket-Crane/Rover System (R3S) for Planetary Surface Missions | |
| Konyukhov et al. | Ukrainian space engineering for international lunar programs | |
| Jackman et al. | NASA's Space Launch System: Progress Toward the Proving Ground |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210907 |
|
| RJ01 | Rejection of invention patent application after publication |