CN103754388B - Energy-saving type space booster - Google Patents
Energy-saving type space booster Download PDFInfo
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- CN103754388B CN103754388B CN201310458280.6A CN201310458280A CN103754388B CN 103754388 B CN103754388 B CN 103754388B CN 201310458280 A CN201310458280 A CN 201310458280A CN 103754388 B CN103754388 B CN 103754388B
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Abstract
Energy-saving type space booster, comprise a total air channel and the secondary air channel in the inner ring center main air channel that is connected with lower end, total air channel and centre circle center and crosswind road, outer ring, the hypomere in crosswind road, outer ring is provided with three little side propelling units; It is characterized in that: the position that total lower end, air channel connects with inner ring center main air channel is provided with the air door that can be closed the secondary air channel in inner ring center main air channel and centre circle center; Flying speed is brought up to about 30% ~ 50% of final required speed by design aircraft in atmospheric envelope, close air door when aircraft flies out atmospheric envelope, and the engine air flow of aircraft is reduced to optimum gas flow and the optimum gas Flow Velocity of applicable three little side propelling units; Less engine air flow amount so just can be utilized to produce enough reaction thrust, in the extraatmospheric flight period without atmospherical drag, the flying speed of aircraft is brought up to final required design speed to meet aircraft.
Description
Technical field
The present invention relates to energy-saving type space booster, be applicable to the energy-conservation of all space jet-propulsion plants, belong to aerospace driving engine sciemtifec and technical sphere.
Background technology
The research and development of modern aerospace driving engine are advanced by leaps and bounds, but all these driving engines are all the flying speed of aerospace flight vehicle brought up in an atmosphere to reach or close final required design speed, this is because these driving engines are at the obtainable reaction thrust of exoatmosphere institute, an obtainable reaction thrust is much smaller relatively in an atmosphere, the speed in fact improved in an atmosphere is more, and the resistance suffered by aircraft is larger, and its fuel consumed is also more, the present invention is the patent " methods of 201210457013.2 raising aero-engine air injection reverse thrust efficiency " utilizing uncle minister in ancient times Wei, near air nozzle, the method that one " air cushion " improves jet reaction thrust efficiency is formed in " 201210566883.3 directional expansion superchargings improve the method for aero-engine reaction thrust efficiency " and " 201310448764. 2 volute air cushion reinforcement propelling unit ", aerospacecraft is made in endoatmosphere, flying speed to be brought up to about 30% ~ 50% of the final required speed of aerospacecraft, then after aerospacecraft flies out atmospheric envelope, without under atmospherical drag condition, the flying speed of aerospacecraft is made to bring up to final required design speed, so just can reduce the fuel that aerospacecraft uses significantly.
Summary of the invention
The object of this invention is to provide and a kind ofly can obtain fair speed in exoatmosphere and can control in exoatmosphere and regulate the energy-saving type space booster of heading.
Energy-saving type space booster, the secondary air channel in the inner ring center main air channel comprising a total air channel and be connected with lower end, total air channel and centre circle center and crosswind road, outer ring, the secondary air channel in inner ring center main air channel and centre circle center and crosswind road, outer ring and total air channel are same central axis, be provided with the circular air channel of three duplicate symmetries in the hypomere in crosswind road, outer ring, the hypomere of three circular air channels forms three little side propelling units by the inner ring side air trunk of circular air channel and Ce Fu air channel, outer ring; It is characterized in that:
1, the position that lower end, total air channel connects with the secondary air channel in inner ring center main air channel and centre circle center and crosswind road, outer ring is provided with an air door, air door is made up of two semicircles, two semicircles share an air door rotating shaft, the central axis upright in air door rotating shaft and center main air channel also crosses central axis, two air doors to stand on when merging above air door rotating shaft and with the centerline axis parallel in center main air channel, now air door is in opening, two air doors open and central axis perpendicular to center main air channel time, two air doors form a disk and just cover the secondary air channel in center main air channel and center completely, now air door is in closed condition, air door rotating shaft two ends are connected with air door adjust bar, air door adjust bar stretches out the outside in total air channel and crosswind road, and be connected with control mechanism, adjusting control mechanism controls the opening and closing of air door.
2, air trunk spout centered by lower end, center main air channel, the spout in center main air channel down, the central axis of center main air channel spout is overlapping with center main air channel central axis, secondary air channel, the center spout of lower end, secondary air channel centered by around the spout of center main air channel, there is secondary air channel, the center spout arc baffle liner of an arc shape outer ring of secondary air channel, center spout, secondary air channel, Shi Cong center the spout high velocity air sprayed and the high velocity air Q at an angle sprayed from center air trunk spout,-45 °≤Q≤45 °, thus the high velocity air that secondary air channel, Shi Cong center spout sprays can inject directly on from the high velocity air of center air trunk spout injection, formed " air cushion " of a higher density, the high velocity air that Bing Shicong center air trunk spout sprays is in the moment leaving center main air channel spout, inject directly on " air cushion " of higher density, thus the reaction thrust substantially increased from center air trunk spout jet-stream wind.
3, flying speed is brought up to about 30% ~ 50% of final required speed by design aircraft in atmospheric envelope, when aircraft flies out atmospheric envelope, air door is closed by the control mechanism of air door adjust bar, now the secondary air channel in center main air channel and center is all in closed condition, and namely the secondary air channel in center main air channel and center no longer includes high velocity air and enters; While closedown air door, also the engine air flow of aircraft is reduced to the optimum gas flow and optimum gas Flow Velocity that are suitable for three little side propelling units; Less engine air flow amount so just can be utilized to produce enough reaction thrust, in the extraatmospheric flight period without atmospherical drag, the flying speed of aircraft is brought up to final required design speed to meet aircraft, thus reduce aircraft widely and flying speed is brought up to the fuel quantity that final required design speed consumes, and then the total weight of aircraft can be alleviated significantly or improve the capacity weight of aircraft significantly.
4, three little side propelling units are by the inner ring side air trunk of little side propelling unit and Ce Fu air channel, outer ring composition, air trunk lower end, side is side air trunk spout, the spout of side air trunk down, the central axis of side air trunk spout is overlapping with side air trunk central axis, it is secondary air channel, the side spout of secondary lower end, air channel, side around the air trunk spout of side, there is secondary air channel, the side spout arc baffle liner of an arc shape outer ring of secondary air channel, side spout, make the high velocity air that secondary air channel spout sprays from side and the high velocity air Q at an angle sprayed from side air trunk spout,-45 °≤Q≤45 °, thus make the high velocity air sprayed from secondary air channel, side spout can inject directly on from the high velocity air of side air trunk spout injection, formed " air cushion " of a higher density, and make the high velocity air sprayed from side air trunk spout in the moment leaving side air trunk spout, inject directly on " air cushion " of higher density, thus the reaction thrust substantially increased from side air trunk spout jet-stream wind.
5, crosswind road hypomere is retracted to only surplus three little side propelling units gradually, make high velocity airs all in crosswind road all can successfully, kinetic energy rejection minimally enters into three little side propelling units, and spray from side air trunk spout and the side secondary air channel spout of three little side propelling units, promote aircraft acceleration flight to produce maximum reaction thrust.
6, the circular air channel epimere forming three little side propelling units is respectively provided with a circular air channel control cock, regulate three circular air channel control cocks, just can regulate the spray air flow of three little side propelling units, the reaction thrust that three little side propelling units are produced is in different size, thus make the thrust acting on aircraft afterbody unbalanced, these unbalanced reaction thrust can the heading of change of flight device, so just can regulate the heading of aircraft on request in exoatmosphere.
The present invention compared with prior art has the following advantages:
1, the similar patent documentation report that aerospacecraft can be made to form " air cushion " is not found that there is.
2, the present invention can improve aerospacecraft widely in atmospheric envelope and extraatmospheric reaction thrust efficiency, thus can increase flight time and the flying distance of aircraft widely, and then can improve efficiency and the effect of aircraft significantly.
3, design aerospacecraft accelerates to about 30% ~ 50% of final required speed in endoatmosphere, then in exoatmosphere again by the flying speed of aircraft without under the condition of atmospherical drag, the speed of aerospacecraft is accelerated to final required speed, so just can reduce aircraft widely and flying speed be brought up to the fuel quantity that final required design speed consumes, and then the total weight of aircraft can be alleviated significantly or improve the capacity weight of aircraft significantly.
Accompanying drawing explanation
Fig. 1 is the generalized section of the embodiment of the present invention;
Fig. 2 is middle A-A generalized section embodiment illustrated in fig. 1;
Fig. 3 is middle B-B generalized section embodiment illustrated in fig. 1;
Fig. 4 is middle C-C generalized section embodiment illustrated in fig. 1;
Fig. 5 is middle P enlarged diagram embodiment illustrated in fig. 1.
In Fig. 1-5: 1, total air channel 2, shrinking zone, crosswind road 3, secondary air channel 4, center, secondary air channel, center spout 5, center main air channel high velocity air 6, center main air channel spout 7, side air trunk spout 8, side air trunk high velocity air 9, secondary air channel, side spout 10, side air trunk 11, secondary air channel 12, side, secondary air channel, center high velocity air 13, center main air channel 14, circular air channel control cock 15, crosswind road 16, crosswind road high velocity air 17, air door rotating shaft 18, air door adjust bar 19, air door 20, total air channel high velocity air 21, closed condition air door 22, opening air door 23, secondary air channel, center spout arc baffle liner 24, secondary air channel, side spout arc baffle liner.
detailed description of the invention
In the embodiment one shown in Fig. 1-5: energy-saving type space booster, the secondary air channel 3 in the inner ring center main air channel 13 comprising a total air channel 1 and be connected with lower end, total air channel 1 and centre circle center and crosswind road, outer ring 15, the secondary air channel 3 in inner ring center main air channel 13 and centre circle center and crosswind road, outer ring 15 are same central axis with total air channel 1, be provided with the circular air channel of three duplicate symmetries in the hypomere in crosswind road, outer ring 15, the hypomere of three circular air channels forms three little side propelling units by the inner ring side air trunk 10 of circular air channel and Ce Fu air channel, outer ring 11, it is characterized in that: the position that total lower end, air channel 1 connects with the secondary air channel 3 in inner ring center main air channel 13 and centre circle center and crosswind road, outer ring 15 is provided with an air door 19, air door 19 is made up of two semicircles, two semicircles share an air door rotating shaft 17, the central axis upright in air door rotating shaft 17 and center main air channel 13 also passes through central axis, two air doors 19 to stand on when merging above air door rotating shaft 17 and with the centerline axis parallel in center main air channel 13, now air door 19 is in opening, two air doors 19 open and central axis perpendicular to center main air channel 13 time, two air doors 19 form a disk and just cover the secondary air channel 3 in center main air channel 13 and center completely, now air door 19 is in closed condition, air door rotating shaft 17 two ends are connected with air door adjust bar 18, air door adjust bar 18 stretches out the outside in total air channel 1 and crosswind road 15, and be connected with control mechanism, adjusting control mechanism controls the opening and closing of air door 19.
Air trunk spout 6 centered by lower end, center main air channel 13, the spout in center main air channel 13 down, the central axis of center main air channel spout 6 is overlapping with center main air channel 13 central axis, secondary air channel, the center spout 4 of lower end, secondary air channel 3 centered by around center main air channel spout 6, there is secondary air channel, the center spout arc baffle liner 23 of an arc shape outer ring of secondary air channel, center spout 4, secondary air channel, Shi Cong center spout 4 high velocity air sprayed and the high velocity air Q at an angle sprayed from center air trunk spout 6,-45 °≤Q≤45 °, thus the high velocity air that secondary air channel, Shi Cong center spout 4 sprays can inject directly on from the high velocity air of center air trunk spout 6 injection, formed " air cushion " of a higher density, the high velocity air that Bing Shicong center air trunk spout 6 sprays is in the moment leaving center main air channel spout 6, inject directly on " air cushion " of higher density, thus the reaction thrust substantially increased from center air trunk spout 6 jet-stream wind.
Flying speed is brought up to about 30% ~ 50% of final required speed by design aircraft in atmospheric envelope, when aircraft flies out atmospheric envelope, air door 19 is closed by the control mechanism of air door adjust bar 18, now the secondary air channel 3 in center main air channel 13 and center is all in closed condition, and namely the secondary air channel 3 in center main air channel 13 and center no longer includes high velocity air and enters; While closedown air door 19, also the engine air flow of aircraft is reduced to the optimum gas flow and optimum gas Flow Velocity that are suitable for three little side propelling units; Less engine air flow amount so just can be utilized to produce enough reaction thrust, in the extraatmospheric flight period without atmospherical drag, the flying speed of aircraft is brought up to final required design speed to meet aircraft, thus reduce aircraft widely and flying speed is brought up to the fuel quantity that final required design speed consumes, and then the total weight of aircraft can be alleviated significantly or improve the capacity weight of aircraft significantly.
Three little side propelling units form by the inner ring side air trunk 10 of little side propelling unit and Ce Fu air channel, outer ring 11, side air trunk 10 lower end is side air trunk spout 7, the spout of side air trunk 10 down, the central axis of side air trunk spout 7 is overlapping with side air trunk 10 central axis, it is secondary air channel, the side spout 9 of secondary lower end, air channel 11, side around side air trunk spout 7, there is secondary air channel, the side spout arc baffle liner 24 of an arc shape outer ring of secondary air channel, side spout 9, make the high velocity air that secondary air channel spout 9 sprays from side and the high velocity air Q at an angle sprayed from side air trunk spout 7,-45 °≤Q≤45 °, thus make the high velocity air sprayed from secondary air channel, side spout 9 can inject directly on from the high velocity air of side air trunk spout 7 injection, formed " air cushion " of a higher density, and make the high velocity air sprayed from side air trunk spout 7 in the moment leaving side air trunk spout 7, inject directly on " air cushion " of higher density, thus the reaction thrust substantially increased from side air trunk spout 7 jet-stream wind.
Crosswind road 15 hypomere is retracted to only surplus three little side propelling units gradually, make high velocity airs all in crosswind road 15 all can successfully, kinetic energy rejection minimally enters into three little side propelling units, and spray from side air trunk spout 7 and the side secondary air channel spout 9 of three little side propelling units, promote aircraft acceleration flight to produce maximum reaction thrust.
The circular air channel epimere forming three little side propelling units is respectively provided with a circular air channel control cock 14, regulate three circular air channel control cocks 14, just can regulate the spray air flow of three little side propelling units, the reaction thrust that three little side propelling units are produced is in different size, thus make the thrust acting on aircraft afterbody unbalanced, these unbalanced reaction thrust can the heading of change of flight device, so just can regulate the heading of aircraft on request in exoatmosphere.
Claims (2)
1. energy-saving type space booster, the secondary air channel (3) in the inner ring center main air channel (13) comprising a total air channel (1) and be connected with total air channel (1) lower end and centre circle center and crosswind road, outer ring (15), the secondary air channel (3) in inner ring center main air channel (13) and centre circle center and crosswind road, outer ring (15) are same central axis with total air channel (1), the circular air channel of three duplicate symmetries is installed in the hypomere in crosswind road, outer ring (15), the hypomere of three circular air channels is by inner ring side air trunk (10) of circular air channel and Ce Fu air channel, outer ring (11) composition three little side propelling units, it is characterized in that: the position that total air channel (1) lower end connects with the secondary air channel (3) in inner ring center main air channel (13) and centre circle center and crosswind road, outer ring (15) is provided with an air door (19), air door (19) is made up of two semicircles, two semicircles share an air door rotating shaft (17), the central axis upright in air door rotating shaft (17) and center main air channel (13) also passes through central axis, stand on air door rotating shaft (17) top when two air doors (19) merge and with the centerline axis parallel of center main air channel (13), now air door (19) is in opening, two air doors (19) open and central axis perpendicular to center main air channel (13) time, two air door (19) composition disks also just cover the secondary air channel (3) in center main air channel (13) and center completely, now air door (19) is in closed condition, air door rotating shaft (17) two ends are connected with air door adjust bar (18), air door adjust bar (18) stretches out the outside of total air channel (1) and crosswind road (15), and be connected with control mechanism, adjusting control mechanism controls the opening and closing of air door (19), flying speed is brought up to 30% ~ 50% of final required speed by design aircraft in atmospheric envelope, when aircraft flies out atmospheric envelope, air door (19) is closed by the control mechanism of air door adjust bar (18), now the secondary air channel (3) in center main air channel (13) and center is all in closed condition, and namely center main air channel (13) and center pair air channel (3) no longer include high velocity air and enter, while closedown air door (19), also the engine air flow of aircraft is reduced to the optimum gas flow and optimum gas Flow Velocity that are suitable for three little side propelling units, less engine air flow amount so just can be utilized to produce enough reaction thrust, in the extraatmospheric flight period without atmospherical drag, the flying speed of aircraft is brought up to final required design speed to meet aircraft, thus reduce aircraft widely and flying speed is brought up to the fuel quantity that final required design speed consumes, and then the total weight of aircraft can be alleviated significantly or improve the capacity weight of aircraft significantly, the circular air channel epimere forming three little side propelling units is respectively provided with a circular air channel control cock (14), regulate three circular air channel control cocks (14), just can regulate the spray air flow of three little side propelling units, the reaction thrust that three little side propelling units are produced is in different size, thus make the thrust acting on aircraft afterbody unbalanced, the heading of these unbalanced reaction thrust change of flight devices, so just can regulate the heading of aircraft on request in exoatmosphere, three little side propelling units are by inner ring side air trunk (10) of little side propelling unit and Ce Fu air channel, outer ring (11) composition, side air trunk (10) lower end is side air trunk spout (7), the spout of side air trunk (10) down, the central axis of side air trunk spout (7) is overlapping with side air trunk (10) central axis, side air trunk spout (7) is around secondary air channel spout (9) in side of secondary air channel (11) lower end, side, there is secondary air channel spout arc baffle liner (24) in the side of an arc shape outer ring of secondary air channel spout (9) in side, make the high velocity air that secondary air channel spout (9) is sprayed from side and the high velocity air Q at an angle sprayed from side air trunk spout (7),-45 °≤Q≤45 °, thus the high velocity air high velocity air sprayed from secondary air channel spout (9) in side being injected directly on spray from side air trunk spout (7), formed " air cushion " of a higher density, and make the high velocity air sprayed from side air trunk spout (7) in the moment leaving side air trunk spout (7), inject directly on " air cushion " of higher density, thus the reaction thrust substantially increased from side air trunk spout (7) jet-stream wind, air trunk spout (6) centered by center main air channel (13) lower end, the spout in center main air channel (13) down, the central axis in center main air channel spout (6) is overlapping with center main air channel (13) central axis, secondary air channel spout (4) in the center of secondary air channel (3) lower end centered by around center main air channel spout (6), there is secondary air channel spout arc baffle liner (23) in the center of an arc shape outer ring of secondary air channel spout (4) in center, Shi Cong center secondary air channel spout (4) high velocity air sprayed and the high velocity air Q at an angle sprayed from center air trunk spout (6),-45 °≤Q≤45 °, thus the high velocity air that secondary air channel spout (4) in Shi Cong center is sprayed can inject directly on the high velocity air that sprays from center air trunk spout (6), formed " air cushion " of a higher density, the high velocity air that Bing Shicong center air trunk spout (6) is sprayed is in the moment leaving center main air channel spout (6), inject directly on " air cushion " of higher density, thus the reaction thrust substantially increased from center air trunk spout (6) jet-stream wind.
2. energy-saving type space booster as claimed in claim 1, it is characterized in that: crosswind road (15) hypomere is retracted to only surplus three little side propelling units gradually, make high velocity airs all in crosswind road (15) all can successfully, kinetic energy rejection minimally enters into three little side propelling units, and spray from secondary air channel spout (9) in side air trunk spout (7) and side of three little side propelling units, promote aircraft acceleration flight to produce maximum reaction thrust.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310458280.6A CN103754388B (en) | 2013-10-01 | 2013-10-01 | Energy-saving type space booster |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310458280.6A CN103754388B (en) | 2013-10-01 | 2013-10-01 | Energy-saving type space booster |
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| CN103754388A CN103754388A (en) | 2014-04-30 |
| CN103754388B true CN103754388B (en) | 2015-09-23 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4936869A (en) * | 1984-04-24 | 1990-06-26 | Minderman Peter A | Liquid hydrogen polygeneration system and process |
| RU2000258C1 (en) * | 1992-01-28 | 1993-09-07 | Научно-производственное и коммерческое акционерное общество "Восток" | Air-space aircraft |
| CN1077252A (en) * | 1992-02-29 | 1993-10-13 | 王建军 | End-vane guided propeller and application thereof |
| CN1190938A (en) * | 1995-06-07 | 1998-08-19 | 威廉·W·杰斯瓦恩 | Fluid propulsion system for accelerating and directionally controlling a fluid |
| RU2008142757A (en) * | 2008-10-29 | 2010-05-10 | Вячеслав Иванович Беляев (RU) | AEROSPACE PLANE (OPTIONS) |
-
2013
- 2013-10-01 CN CN201310458280.6A patent/CN103754388B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4936869A (en) * | 1984-04-24 | 1990-06-26 | Minderman Peter A | Liquid hydrogen polygeneration system and process |
| RU2000258C1 (en) * | 1992-01-28 | 1993-09-07 | Научно-производственное и коммерческое акционерное общество "Восток" | Air-space aircraft |
| CN1077252A (en) * | 1992-02-29 | 1993-10-13 | 王建军 | End-vane guided propeller and application thereof |
| CN1190938A (en) * | 1995-06-07 | 1998-08-19 | 威廉·W·杰斯瓦恩 | Fluid propulsion system for accelerating and directionally controlling a fluid |
| RU2008142757A (en) * | 2008-10-29 | 2010-05-10 | Вячеслав Иванович Беляев (RU) | AEROSPACE PLANE (OPTIONS) |
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Effective date of registration: 20180713 Address after: 226371 North four groups of Tu Shan village, Xingdong Town, Tongzhou District, Nantong, Jiangsu Patentee after: NANTONG HUAXIA AIRPLANE ENGINEERING TECHNOLOGY CO., LTD. Address before: 314408 304, room 2, 30 shallow water bay, Kashi street, Haining, Jiaxing, Zhejiang. Patentee before: Wei Boqing |