CN114278461B - Disconnect-type T type pulse thruster group suitable for vertical launch aircraft - Google Patents
Disconnect-type T type pulse thruster group suitable for vertical launch aircraft Download PDFInfo
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- CN114278461B CN114278461B CN202111346280.8A CN202111346280A CN114278461B CN 114278461 B CN114278461 B CN 114278461B CN 202111346280 A CN202111346280 A CN 202111346280A CN 114278461 B CN114278461 B CN 114278461B
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- 239000007921 spray Substances 0.000 claims abstract description 25
- 238000009434 installation Methods 0.000 claims abstract description 14
- 230000000149 penetrating effect Effects 0.000 claims abstract description 3
- 238000002485 combustion reaction Methods 0.000 claims description 44
- 238000005192 partition Methods 0.000 claims description 11
- 230000000903 blocking effect Effects 0.000 claims description 3
- 230000005570 vertical transmission Effects 0.000 claims 2
- 239000002737 fuel gas Substances 0.000 abstract description 8
- 239000002360 explosive Substances 0.000 description 12
- 238000007789 sealing Methods 0.000 description 8
- 238000005507 spraying Methods 0.000 description 6
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000011888 foil Substances 0.000 description 2
- 230000002441 reversible effect Effects 0.000 description 2
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 150000003863 ammonium salts Chemical class 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- 238000006467 substitution reaction Methods 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Abstract
The invention discloses a separated T-shaped pulse thruster group suitable for a vertical launching aircraft, which comprises a connector axially connected to the aircraft and a thruster arranged in the connector, wherein a plurality of thruster mounting through holes are axially formed in the connector, spray holes are radially formed in the side wall of the connector in a penetrating manner, and the middle section of the thruster mounting through holes is intersected with the inner side of the spray holes to form a T-shaped channel; the thruster comprises two thruster sub-pieces which are separated from each other, and the two thruster sub-pieces are respectively and detachably arranged at two ends of the thruster mounting through hole. When the aircraft flies vertically to a preset height, two sections of charges in the thruster are ignited by two ignition devices at the same time, generated fuel gas is sprayed out from the spray holes to the outside after passing through the installation through holes of the thruster, so that thrust vertical to the axis of the connector is generated.
Description
Technical Field
The invention relates to the technical field of aircraft power, in particular to a separated T-shaped pulse thruster group suitable for a vertical-launching aircraft.
Background
After the vertical launching aircraft drives away from the launching box, a pulse thruster set is often adopted to complete turning action of the vertical launching aircraft, when the aircraft drives away from the launching box by a certain height, the engine is ignited to push the aircraft to continue flying, and turning of the aircraft from a vertical launching state to a preset flying direction is realized through the pulse thruster set, and the pulse thruster set can provide enough thrust vertical to the axis of the aircraft.
The pulse thruster sub-piece commonly used at present is a large-caliber integral L-shaped pulse thruster group, the spout axis of the thruster sub-piece group is vertical to the axis of the aircraft, an inner hole machined in the aircraft shell is used as a combustion chamber of the L-shaped pulse thruster sub-piece, a radial spout is radially machined in the aircraft shell, and the combustion chamber and the spout of the thruster sub-piece are of an integral structure.
Scientific researchers find that the combustion of the charging of the single L-shaped pulse thruster sub-part is incomplete in the ground static test of the single L-shaped pulse thruster sub-part, and the main reason is that the ignition time of the charging surface is delayed due to the longer charging length of the thruster sub-part; in addition, as the flying overload of the aircraft increases, the longer charging length of the thruster sub-part (namely, the larger length-diameter ratio of the explosive column) can also cause the problems of the explosive column fracture and the like which affect the structural integrity of the charging structure; in addition, as the outer diameter of the aircraft increases, the weight of the shell of the integral L-shaped pulse thruster group also increases, and a large load is brought to the flight of the aircraft.
Disclosure of Invention
The invention aims to solve the problems that the existing integral L-shaped pulse thruster set has incomplete charge combustion caused by longer explosive column, the explosive column is easy to break, and the pulse thruster set shell is too heavy to increase the flying load caused by the increase of the outer diameter of an aircraft, and provides a separated T-shaped pulse thruster set suitable for a vertical launching aircraft, which optimizes the combustion efficiency of the charge and the assembly performance through the sectional charge mode.
The technical effects to be achieved by the invention are realized by the following technical scheme:
the utility model provides a disconnect-type T type pulse thruster group suitable for vertical launch aircraft, is in including the connector of axial coupling on the aircraft and setting the internal thruster of connector, the inside of connector is provided with a plurality of thruster installation through-hole along the axial, the lateral wall of connector is along radially running through and being equipped with the orifice, its characterized in that, the middle section of thruster installation through-hole with the inboard of orifice takes place to meet, the thruster installation through-hole with form T shape passageway from this between the orifice, the thruster includes two thruster sub-pieces that separate from each other, two thruster sub-pieces detachably installs respectively the both ends of thruster installation through-hole.
When the aircraft flies vertically to a preset height, the thruster sub-parts on two sides of the thruster mounting through hole are ignited synchronously, and fuel gas generated by the loading of the thruster sub-parts is sprayed outwards from the spray hole after passing through the thruster mounting through hole, and the reverse impact force generated by spraying can form radial thrust to the side wall of the connector, so that the turning action of the aircraft is assisted. The invention provides a thruster mounting through hole, namely, thruster sub-parts are respectively arranged at two sides of an axial spraying channel, and aims to divide the original length of a grain into two parts so as to shorten the length of a single-section grain, thereby overcoming the problems of incomplete charge combustion, easy grain breakage and other grain structural integrity caused by overlong grain. In addition, the number of the thruster sub-parts can be flexibly increased or decreased by adopting a detachable mounting mode, and the weight of the pulse thruster group can be greatly reduced by detaching the redundant thruster sub-parts under the condition that the turning power requirement of the aircraft is not high, so that the load environment of the aircraft is optimized.
Preferably, the two thruster sub-pieces connected with the same thruster mounting through hole are symmetrically arranged relative to the spray hole and synchronously ignite, and the axis of the thruster mounting through hole and the axis of the thruster sub-piece are positioned on the same straight line.
Preferably, the thrust forces of the two thruster sub-members connected to the same thruster mounting through hole are identical.
Preferably, each of said thruster subassemblies comprises a combustion chamber, a charge and an ignition device, the dimensions of the two sets of symmetrically arranged combustion chambers, charges and ignition devices being in accordance with each other.
Preferably, the two ends of the thruster mounting through hole are provided with internal threads, the end part of the thruster sub-piece is provided with external threads, and the thruster mounting through hole is connected with the thruster sub-piece through threads.
Preferably, each of said thruster sub-assemblies comprises said combustion chamber, a charge, an ignition means for igniting said charge; the combustion chamber is characterized in that an external thread is arranged at one end of the combustion chamber and is in threaded screwing connection with the thruster mounting through hole, the end is open, after screwing connection, the combustion chamber is communicated with the thruster mounting through hole, and a blocking cover is arranged at the other end of the combustion chamber. After the fuel gas generated by the explosive charge in the thruster sub-piece after ignition passes through the thruster mounting through hole, the fuel gas can be sprayed out from the spray hole to the outside, so that the thrust vertical to the axis of the connector is generated.
Preferably, the combustion chamber adopts a cylindrical structure, the charges are uniformly arranged around the axis of the combustion chamber and extend along the axis direction, the charges are loaded with grains, and the ends of the charges are fixed on the inner side wall of the blanking cover.
Preferably, the thruster mounting through holes are distributed from inside to outside around the axis of the connector, the number of turns is more than two, each turn is provided with more than four thruster mounting through holes, and only one thruster mounting through hole and one spray hole are arranged on the same radius line of the connector.
Preferably, the connecting body adopts a cylindrical structure close to the outer diameter of the aircraft, a partition plate is arranged in the connecting body along the radial direction, the thruster mounting through holes are formed in the partition plate in a penetrating mode, and each thruster mounting through hole is correspondingly connected with one thruster.
Preferably, the number of the thruster mounting through holes is equal to the number of the spray holes, the positions of the thruster mounting through holes and the spray holes are in one-to-one correspondence, the corresponding thruster mounting through holes and the spray holes are positioned on the same radial line of the connecting body, and each spray hole extends towards the inside of the partition plate along the radial line of the connecting body until the corresponding thruster mounting through holes are intersected.
Compared with the prior art, the invention has the beneficial effects that:
the separated T-shaped pulse thruster set provided by the invention maintains or even increases the transverse thrust of the thruster sub-part by providing two sections of combustion chambers capable of igniting synchronously on the basis that the axial direction of the thruster is perpendicular to the axial direction of the spray hole, and the two sections of combustion chambers divide the original long explosive into two sections of half-long explosive, so that the length of a single section of explosive is obviously shortened, and the technical defects of explosive breakage and easy cutting caused by long explosive length (large length-diameter ratio of the explosive) are overcome; in addition, the number of the thrusters is multiple, the thrusters are uniformly distributed around the axis of the connecting body, detachable installation is adopted between the thrusters and the connecting body, and according to the installation characteristics, a user can appropriately increase or decrease the number of the thrusters according to actual flight turning power requirements, so that the loading load of the aircraft can be reasonably configured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present invention, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic side view of the present embodiment;
FIG. 2 is a cross-sectional view taken along A-A of FIG. 1;
FIG. 3 is a schematic cross-sectional view of a combustion chamber;
in the figure, 1-linker; 2-thrusters; 2 a-thruster subassembly; 3-ignition means; 4-plugging a cover; 5-a sealing ring I; 6-an adhesive; 7-a sealing ring II; 8-charging; 9-a combustion chamber; 10-a sealing ring III; 11-aluminum foil; 12-a separator; 13-a thruster mounting through hole; 14-spraying holes; 15-axial through holes.
Detailed Description
The following describes the embodiments of the present invention further with reference to the drawings. The description of these embodiments is provided to assist understanding of the present invention, but is not intended to limit the present invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
Referring to fig. 1 and 2, the present embodiment provides a separated T-shaped pulse thruster assembly suitable for a vertical launch aircraft, which includes a connector 1 axially connected at a non-center of mass position of the aircraft, and a thruster 2 disposed in the connector 1, wherein a partition 12 is radially disposed in the connector, the partition 12 is axially disposed through a plurality of thruster mounting holes 13, a nozzle 14 is disposed through a sidewall of the connector, and the nozzle 14 extends toward the inside of the partition 12 along a radial line of the connector 1 until intersecting with the corresponding thruster mounting hole 13.
The thruster mounting through hole 13 is connected with the thruster 2, the thruster 2 comprises two thruster sub-pieces 2a separated from each other, the two thruster sub-pieces 2a are detachably mounted at two ends of the thruster mounting through hole 13 respectively, and the spraying directions of the thruster sub-pieces 2a are aligned with the intersection. When the aircraft flies vertically to a preset height, the thruster sub-parts 2a at the two sides of the thruster mounting through hole 13 are synchronously ignited, the fuel gas generated by the charge 8 of the thruster sub-parts is sprayed outwards from the spray hole 14 after passing through the thruster mounting through hole 13, and the reverse impact force generated by spraying can form radial thrust to the side wall of the connector 1, so as to assist in the preset turning of the vertical-launching aircraft.
With continued reference to fig. 2, it should be noted that in this embodiment, the two thruster sub-members 2 are symmetrically disposed with respect to one thruster mounting through hole 13, so as to divide the original length of the grain into two parts, thereby shortening the length of a single-section grain, and overcoming the structural problems of incomplete combustion of the charge and easy breakage of the grain caused by overlong grain, etc., in order to ensure that the ignition is sufficient and the gas can be quickly ejected, the center line of the thruster 2 and the axis of the corresponding thruster mounting through hole 13 should be collinear, and when the charge 8 is ignited and combusted, the gas in the thruster sub-members will impact the opposite thruster sub-members and the thruster mounting through hole 13 at a sufficiently fast impact speed, so that even if the required turning power is small, the two opposite thruster sub-members 2a should be synchronously ignited, so as to jointly eject the charge together, so as to avoid phagocytizing the combustion value of the charge inside the connecting body 1, and thus weakening the ejection strength to the outside.
Further, the thrust forces of the two thruster sub-members 2a connected with the same thruster mounting through hole 13 should be consistent, specifically, each thruster sub-member 2a comprises a combustion chamber 9, a charge 8 and an ignition device 3, and the dimensions of the two groups of symmetrically arranged combustion chambers 9, charges 8 and ignition devices 3 are consistent with each other; by the arrangement, the two thruster sub-parts 2a can emit the same impact strength after being synchronously ignited, and the two thruster sub-parts together finish the injection action outwards, so that the balance degree of the aircraft is not influenced by internal mixed flow.
In this embodiment, the connector 1 adopts a cylindrical structure close to the outer diameter of the aircraft, the number of the thruster mounting holes 13 is more than four, and the holes are uniformly distributed around the axis of the connector 1, and correspondingly, the spray holes 14 should also be uniformly distributed around the axis of the connector 1, so as to ensure that the present embodiment can provide turning thrust in at least four directions relative to the connector 1.
In practical application, the turning requirement of the aircraft is more various, and multiple times, multiple levels of intensity and even multiple angles of turning operation are often needed, so that in some embodiments, the thruster mounting through holes 13 are distributed around the axis of the connector 1 in two circles, each circle is provided with seven thruster mounting through holes 13, the thruster sub-assembly mounting holes 13 of adjacent circles are staggered with each other, and multiple application of turning overload to the aircraft can be realized by increasing the number of thrusters of the aircraft in the same cross section.
In the case of two-turn and multi-turn distribution, each of the thruster-mounting holes 13 can communicate with only one of the injection holes 14 radially outward, that is, only one of the thruster-mounting holes 13 and the injection holes 14 can be provided on the same radial line of the connecting member 1. The number of the thruster mounting through holes 13 is equal to that of the spray holes 14, the positions of the thruster mounting through holes and the spray holes are in one-to-one correspondence, and each spray hole 14 is not intersected, so that when the explosive charge 8 is ignited, the spray holes 14 in opposite directions are conducted, high-speed fuel gas is sprayed at the same time, and the turning effect is destroyed.
Similarly, in order to prevent the gas from being strung between the different thruster mounting holes 13 to cause a risk of explosion when the charges 8 are ignited, only one thruster mounting through hole 13 should be provided on the same radial line of the connection body 1.
In other embodiments, especially for the case of larger diameter of the aircraft, smaller charge diameter, or more complex turning angle, three or more circles of mutually staggered thruster mounting through holes 13 may be provided, and the ignition devices of the thrusters 2 at the designated positions may be sequentially started according to the preset settings, so that more multi-level turning actions may be realized.
In this embodiment, each thruster subassembly 2a is detachably mounted in the thruster mounting hole 13, for example, by a snap fit or a screw fit. In order to lighten the processing intensity, facilitate the operation of personnel and ensure the installation stability, the thruster sub-piece 2a is in threaded connection with the thruster installation through hole 13, the two ends of the thruster installation through hole 13 are provided with internal threads, the end part of the thruster sub-piece 2a is provided with external threads, and the thruster sub-piece 2a can be quickly installed by hole site alignment and tightening. In this embodiment, the thruster 2 and the connecting piece 1 are arranged in a split type and are detachably mounted, so that the number of the thrusters 2 is flexibly increased or decreased, and under the condition that the turning power requirement of the aircraft is not high, an operator can greatly reduce the weight of the pulse thruster group 2 by disassembling the redundant thruster sub-parts, optimize the load environment of the aircraft, and overcome the technical defect that the pulse thruster group shell is overweight due to the increase of the outer diameter of the aircraft.
Specifically, each thruster 2 includes a combustion chamber 9, a charge 8 installed in the combustion chamber 9, an ignition device 3 for igniting the charge 8, an outer end lead wire of the ignition device 3 is connected with a front end controller (not shown in the figure) of the aircraft, an end of the combustion chamber 9 is provided with an external thread for screwing connection with a thruster mounting through hole 13, the end is open, after screwing connection, the combustion chamber 9 is communicated with the thruster mounting through hole 13, and the other end of the combustion chamber 9 is provided with a blocking cover 4.
When the aircraft flies vertically to a preset height, the front-end controller controls the ignition device 3 in the combustion chamber 9 to ignite, the charge 8 is ignited, and fuel gas generated by the charge 8 is sprayed outwards from the spray hole 14 after passing through the thruster mounting through hole 13 to provide turning adjustment power for the aircraft; the front-end controller sequentially ignites one or more thrusters 2 to realize multiple turns of the aircraft, and finally realizes turning gesture adjustment of the aircraft.
It should be added that, since the two thruster sub-members 2a corresponding to the same thruster mounting hole 13 are symmetrically distributed, the spraying directions of the two thruster sub-members 2a are aligned with the thruster mounting hole 13, so that the respective ignition devices 3 thereof are arranged in opposite directions, and there must be an outgoing wire of one ignition device 3 away from the front end controller, and for this purpose, an axial through hole 15 is provided at the center of the partition 12, wherein the outgoing wire of one ignition device 3 is directly connected to the front end controller, and the outgoing wire of the other ignition device 3 is connected to the front end controller through the axial through hole 15 in the middle of the partition 12.
Referring to fig. 3, in this embodiment, the combustion chamber 9 adopts a cylindrical structure, the charges 8 are uniformly arranged around the axis of the combustion chamber 9 and extend along the axis direction, the charges 8 adopt tubular grains processed by modified double-base propellant of modified ammonium copper-3, the grains are fixedly bonded to the inner wall of the plug cover 4 in a circumferential uniformly distributed manner through the adhesive 6, one end of the charges 8 is fixedly bonded to the inner wall of the plug cover 4 through the adhesive 6, and the diameter of the plug cover 4 is matched with the diameter of the combustion chamber 9. The ignition device 3 is fixed at the center of the blanking cover 4 in a threaded connection mode.
Further, in order to strengthen the stability of sealing connection, a sealing ring I5 is arranged at the joint of the ignition device 3 and the blanking cover 4, a sealing ring II 7 is arranged at the joint of the blanking cover 4 and the combustion chamber 9, and a sealing ring III 10 is arranged at the joint of the thruster mounting through hole 13 and the combustion chamber 9.
In addition, the combustion chamber 9 is provided with an aluminum foil sheet 11 for sealing at a position near the port of the nozzle hole 14.
The working procedure of this embodiment is briefly described below:
when the aircraft flies vertically to a preset height, the front-end controller controls two opposite ignition devices 3 in the T-shaped pulse thruster sub-parts to ignite simultaneously, the ignition devices 3 ignite two opposite charges 8, and fuel gas generated by each grain is sprayed outwards from the radial spray holes 14 after passing through the axial thruster mounting through holes 13 to provide power for turning of the aircraft, so that turning of the aircraft is finally realized.
The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, and still fall within the scope of the invention.
Claims (7)
1. The utility model provides a disconnect-type T type pulse thruster group suitable for vertical launch aircraft, includes the connector of axial connection on the aircraft and sets up the internal thruster of connector, the inside of connector is provided with a plurality of thruster installation through-hole along the axial, the lateral wall of connector is along radially running through and being equipped with the orifice, its characterized in that, the middle section of thruster installation through-hole and the inboard of orifice take place to meet, form T shape passageway from this between thruster installation through-hole and the orifice, the thruster includes two thruster sub-pieces that separate each other, two thruster sub-pieces detachably install respectively the both ends of thruster installation through-hole; the two thruster sub-pieces connected with the same thruster mounting through hole are symmetrically arranged relative to the spray hole and synchronously ignite, and the axis of the thruster mounting through hole and the axis of the thruster sub-piece are positioned on the same straight line; the thrust forces of the two thruster sub-parts connected with the same thruster mounting through hole are consistent; each thruster subassembly comprises a combustion chamber, a charge and an ignition device, and the two groups of symmetrically arranged combustion chambers, charges and ignition devices are consistent with each other in size.
2. The split T-pulse thruster unit suitable for use in a vertical launch vehicle according to claim 1, wherein the thruster mounting through hole is provided with internal threads at both ends, the end of the thruster subassembly is provided with external threads, and the thruster mounting through hole is screwed with the thruster subassembly.
3. A split T-pulse thruster group suitable for use in a vertical-launch aircraft according to claim 2, wherein each of said thruster sub-units comprises said combustion chamber, a charge, ignition means for igniting said charge; the combustion chamber is characterized in that an external thread is arranged at one end of the combustion chamber and is in threaded screwing connection with the thruster mounting through hole, the end is open, after screwing connection, the combustion chamber is communicated with the thruster mounting through hole, and a blocking cover is arranged at the other end of the combustion chamber.
4. A split type T-pulse thruster group suitable for use in a vertical launch vehicle as defined in claim 3,
the combustion chamber adopts a cylindrical structure, the charges are uniformly distributed around the axis of the combustion chamber and extend along the axis direction, the charges are loaded with grains, and the end parts of the charges are fixed on the inner side walls of the blanking covers.
5. The separated T-shaped pulse thruster assembly for a vertical transmission aircraft according to claim 1, wherein the thruster mounting holes are distributed from inside to outside around the axis of the connection body in a number of turns, the number of turns is more than two, each turn is provided with more than four thruster mounting holes, and only one thruster mounting hole and jet hole are arranged on the same radius line of the connection body.
6. The separated T-type pulse thruster assembly for vertical transmission aircraft according to claim 5, wherein the connector adopts a cylindrical structure close to the outer diameter of the aircraft, a partition plate is radially arranged inside the connector, and the thruster mounting through holes are formed in the partition plate in a penetrating manner, and each thruster mounting through hole is correspondingly connected with one thruster.
7. The split-type T-pulse thruster group for a vertical-launch vehicle of claim 6, wherein,
the number of the thruster mounting through holes is equal to that of the spray holes, the thruster mounting through holes and the spray holes are in one-to-one correspondence, the corresponding thruster mounting through holes and the spray holes are positioned on the same radial line of the connecting body, and each spray hole extends towards the inside of the partition plate along the radial line of the connecting body until the corresponding thruster mounting through holes are intersected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111346280.8A CN114278461B (en) | 2021-11-15 | 2021-11-15 | Disconnect-type T type pulse thruster group suitable for vertical launch aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111346280.8A CN114278461B (en) | 2021-11-15 | 2021-11-15 | Disconnect-type T type pulse thruster group suitable for vertical launch aircraft |
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| CN114278461B true CN114278461B (en) | 2024-04-12 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201925048U (en) * | 2010-10-09 | 2011-08-10 | 南京理工大学 | Multi-powder-chamber variable thruster |
| CN107620652A (en) * | 2016-10-28 | 2018-01-23 | 湖北航天化学技术研究所 | A kind of multiple-pulse adjustable thrust Solid propeller |
| CN110425058A (en) * | 2019-08-18 | 2019-11-08 | 南京理工大学 | The soft interlayer ablation test device of Double pulse solid rocket motor |
| CN111350615A (en) * | 2020-03-27 | 2020-06-30 | 惠州学院 | Integral turning device suitable for vertical launching aircraft |
| CN113404618A (en) * | 2021-06-24 | 2021-09-17 | 北京机械设备研究所 | Solid pulse power device |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8051640B2 (en) * | 2008-05-09 | 2011-11-08 | Robert L Geisler | Propulsion system, opposing grains rocket engine, and method for controlling the burn rate of solid propellant grains |
| US8242422B2 (en) * | 2009-02-23 | 2012-08-14 | Raytheon Company | Modular divert and attitude control system |
| US8667776B2 (en) * | 2009-02-23 | 2014-03-11 | Raytheon Company | Pellet-loaded multiple impulse rocket motor |
-
2021
- 2021-11-15 CN CN202111346280.8A patent/CN114278461B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201925048U (en) * | 2010-10-09 | 2011-08-10 | 南京理工大学 | Multi-powder-chamber variable thruster |
| CN107620652A (en) * | 2016-10-28 | 2018-01-23 | 湖北航天化学技术研究所 | A kind of multiple-pulse adjustable thrust Solid propeller |
| CN110425058A (en) * | 2019-08-18 | 2019-11-08 | 南京理工大学 | The soft interlayer ablation test device of Double pulse solid rocket motor |
| CN111350615A (en) * | 2020-03-27 | 2020-06-30 | 惠州学院 | Integral turning device suitable for vertical launching aircraft |
| CN113404618A (en) * | 2021-06-24 | 2021-09-17 | 北京机械设备研究所 | Solid pulse power device |
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| CN114278461A (en) | 2022-04-05 |
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