CN116537975B - Recoverable aircraft jet control device - Google Patents
Recoverable aircraft jet control device Download PDFInfo
- Publication number
- CN116537975B CN116537975B CN202310819325.1A CN202310819325A CN116537975B CN 116537975 B CN116537975 B CN 116537975B CN 202310819325 A CN202310819325 A CN 202310819325A CN 116537975 B CN116537975 B CN 116537975B
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- engine
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- 230000007246 mechanism Effects 0.000 claims abstract description 41
- 239000002737 fuel gas Substances 0.000 claims abstract description 10
- 230000005540 biological transmission Effects 0.000 claims description 16
- 230000001681 protective effect Effects 0.000 claims description 16
- 238000002347 injection Methods 0.000 claims description 12
- 239000007924 injection Substances 0.000 claims description 12
- 239000007789 gas Substances 0.000 abstract description 24
- 239000007787 solid Substances 0.000 abstract description 6
- 238000005507 spraying Methods 0.000 abstract description 5
- 235000015842 Hesperis Nutrition 0.000 abstract description 3
- 235000012633 Iberis amara Nutrition 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 20
- 238000000034 method Methods 0.000 description 13
- 239000000956 alloy Substances 0.000 description 7
- 238000011084 recovery Methods 0.000 description 6
- 238000001514 detection method Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 230000003014 reinforcing effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/90—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using deflectors
Abstract
The invention provides a recoverable aircraft jet control device, which is applied to a jet port of a rocket engine, and relates to the technical field of solid rockets, and comprises the following components: a fixed disk provided with a first through hole, and the jet orifice penetrates through the first through hole and is fixedly connected with the fixed disk; the fixed disk is provided with a turbulent flow mechanism at one side close to the jet orifice, the turbulent flow mechanism comprises at least two turbulent flow pieces, the two turbulent flow pieces are positioned at the periphery of the jet orifice and are arranged around the axial direction of the engine, and a first flow passage is formed in the two turbulent flow pieces; the other ends of the two turbulence pieces are connected with a driving mechanism for driving the turbulence pieces to rotate around a first axis, and the first axis is perpendicular to the axis of the engine; the fuel gas flow sprayed from the engine passes through the first flow channel and impacts the turbulence piece so as to control the spraying speed and the spraying direction of the fuel gas flow; according to the invention, the turbulence piece is arranged at the jet orifice, so that the size and the direction of the gas flow can be controlled, and the flying speed and the flying direction of the aircraft can be indirectly controlled.
Description
Technical Field
The invention relates to the technical field of solid rockets, in particular to a recoverable aircraft jet control device.
Background
Along with the development of science and technology, the recovery technology is largely applied to the rocket field, in order to reduce the launching cost, recoverable solid rockets are gradually developed in the solid rocket field, and in the process of recovering each solid rocket, the direction and the size of jet flow need to be controlled so as to ensure that an rocket body can be safely recovered; in the prior art, when a solid rocket is recovered, a parachute is generally used, for example, a parachute system and a parachute recovery method for aircraft recovery are disclosed in patent document with publication number CN110589032B, and the rocket is recovered by using a parachute, but the rocket body is recovered in such a way that the weight born by the parachute is limited due to the large mass of the rocket body, and the rocket body may be separated from the parachute, so that the rocket body is damaged or disintegrated, and cannot be recovered normally.
Disclosure of Invention
The object of the present invention is to solve the above problems, and to provide a recoverable aircraft jet control device applied to the jet of a rocket engine, said control device comprising:
the fixed disc is provided with a first through hole, and the jet orifice penetrates through the first through hole and is fixedly connected with the fixed disc;
the turbulence mechanism is arranged on one side of the fixed disc, which is close to the jet orifice, and comprises at least two turbulence pieces, wherein the two turbulence pieces are positioned at the periphery of the jet orifice and are arranged around the axis direction of the engine, and a first flow passage is formed in the two turbulence pieces;
the driving mechanism is respectively connected with the two turbulence pieces and used for driving the turbulence pieces to rotate around a first axis, and the first axis is perpendicular to the axis of the engine;
the fuel gas flow sprayed from the engine passes through the first runner and impacts the turbulence piece so as to control the spraying speed and the spraying direction of the fuel gas flow.
According to the technical scheme provided by the invention, the turbulence mechanism further comprises a fixed seat arranged on the fixed disc, a connecting rod assembly is arranged between the fixed seat and the turbulence piece, the connecting rod assembly comprises a first connecting rod hinged with the turbulence piece and a first connecting piece hinged with the first connecting rod, and one end, relatively far away from the first connecting rod, of the first connecting piece is hinged with the fixed seat.
According to the technical scheme provided by the invention, the driving mechanism comprises a first mounting seat, the first mounting seat is arranged on one surface of the fixed disc, which is relatively far away from the fixed seat, the driving mechanism further comprises a linear driving piece arranged in the first mounting seat, a second through hole is formed in the fixed disc, and the output end of the linear driving piece penetrates through the second through hole and is hinged with the first connecting piece.
According to the technical scheme provided by the invention, a transmission shaft is arranged between the output end and the first connecting piece, one end of the transmission shaft is hinged with the first connecting piece, and the other end of the transmission shaft is fixedly connected with the output end.
According to the technical scheme provided by the invention, a switching assembly is further arranged between the transmission shaft and the first connecting piece, the switching assembly comprises a first switching piece hinged with the first connecting piece, and a second switching piece is hinged with the other end of the first switching piece.
According to the technical scheme provided by the invention, the second through hole is internally provided with the second mounting seat, the second mounting seat is provided with the sliding rail extending along the first direction, the second adapter is provided with the sliding groove extending along the first direction, and the sliding groove is in sliding connection with the sliding rail.
According to the technical scheme provided by the invention, the fixed disc is further provided with the protective cover with the first opening, the protective cover is provided with the accommodating space, the jet opening and the spoiler are both positioned in the accommodating space, and the spoiler is rotationally connected with the inner wall of the protective cover.
According to the technical scheme provided by the invention, the number of the turbulence pieces is two.
Compared with the prior art, the invention has the beneficial effects that: the jet orifice of the engine is provided with a turbulent flow mechanism, the turbulent flow mechanism at least comprises two turbulent flow pieces, the two turbulent flow pieces are arranged around the axis direction of the engine, the two turbulent flow pieces are positioned at the periphery of the jet orifice, a first runner is formed in the two turbulent flow pieces, the jet orifice of the engine is provided with a fixed disk, a first through hole is formed in the fixed disk, the jet orifice of the engine penetrates through the first through hole and is fixedly connected with the fixed disk, and the turbulent flow mechanism is arranged on one surface of the fixed disk relatively close to the jet orifice; in the use, the gas flow is spouted from the jet orifice of the engine, and enters the first flow channel, when the gas flow enters the first flow channel, the gas flow can collide with two spoilers, after the gas flow collides with two spoilers, the speed and the direction of the gas flow jet can be changed due to the blocking of the two spoilers on the gas flow, the size and the direction of the gas flow can be controlled by arranging the spoilers at the jet orifice of the engine, the impact force of part of the gas flow is dispersed, and the falling speed of the rocket body can be reduced because the impact force is reduced, so that the rocket body can not be damaged or disintegrated in the falling process, the stable falling and recovery of the rocket body can be realized, and the development cost and the emission cost of the rocket are reduced to a great extent.
Drawings
FIG. 1 is a front view of a recoverable aircraft jet control device provided by the present invention;
FIG. 2 is a schematic view of the overall structure of the recoverable aircraft jet control device provided by the present invention;
FIG. 3 is a schematic structural view of a fixing plate according to the present invention;
FIG. 4 is a schematic view of a single spoiler according to the present invention;
FIG. 5 is a schematic view of two turbulence members and jet ports according to the present invention;
FIG. 6 is a schematic structural view of a protective cover according to the present invention;
fig. 7 is a schematic structural diagram of a fixing seat provided by the present invention;
FIG. 8 is a schematic structural view of a first connector according to the present invention;
FIG. 9 is a schematic view of a connecting rod assembly according to the present invention;
fig. 10 is a schematic structural diagram of a first mounting seat provided by the present invention;
FIG. 11 is an exploded view of the connecting rod assembly provided by the present invention;
fig. 12 is a schematic structural diagram of a second mounting seat provided by the present invention.
The text labels in the figures are expressed as: 1. an engine; 2. a fixed plate; 3. a first through hole; 4. a spoiler; 401. a rotating shaft; 402. a first hinge part; 5. a protective cover; 501. a first connection portion; 502. a first mounting portion; 503. a second connecting portion; 504. a second mounting portion; 505. a first mounting hole; 506. a second mounting hole; 507. a second opening; 6. a fixing seat; 601. a first fixing plate; 602. a first connection plate; 603. a second connecting plate; 604. a first hinge hole; 7. a first connecting rod; 701. a first link; 702. a second link; 703. a third link; 7001. a second hinge hole; 7002. a third hinge hole; 7003. a fourth hinge hole; 8. a first mount; 801. a first fixing portion; 802. a second fixing portion; 803. a third fixing portion; 804. a support plate; 805. a splice plate; 8051. a first edge; 8052. a second side; 8053. a third side; 8054. fourth side; 9. a linear driving member; 10. a second through hole; 11. a transmission shaft; 12. a first adapter; 13. a second adapter; 14. a second mounting base; 141. a second mounting plate; 142. a third mounting plate; 143. reinforcing ribs; 15. a slide rail; 16. a chute; 17. a second connector; 18. and a heat insulating member.
Detailed Description
In order that those skilled in the art may better understand the technical solutions of the present invention, the following detailed description of the present invention with reference to the accompanying drawings is provided for exemplary and explanatory purposes only and should not be construed as limiting the scope of the present invention.
A recoverable aircraft jet control device for use at the jet of a rocket engine 1, comprising:
the fixed disc 2 is provided with a first through hole 3, and the jet orifice penetrates through the first through hole 3 and is fixedly connected with the fixed disc 2;
the turbulence mechanism is arranged on one side of the fixed disc 2, which is close to the jet orifice, and comprises at least two turbulence pieces 4, wherein the two turbulence pieces 4 are positioned at the periphery of the jet orifice and are arranged around the axis direction of the engine 1, and a first flow channel is formed in the two turbulence pieces 4;
the driving mechanisms are respectively connected with the two turbulence pieces 4 and are used for driving the turbulence pieces 4 to rotate around a first axis, and the first axis is perpendicular to the axis of the engine 1.
The fuel gas flow injected from the engine 1 passes through the first flow passage and hits the spoiler 4 to control the injection speed and injection direction of the fuel gas flow.
Specifically, in this embodiment, referring to fig. 1 and fig. 2, the engine 1 is in a cylindrical shape, the injection port of the engine 1 is shown in fig. 5, and the engine further includes a fixing disc 2, the engine 1 is fixedly connected with the fixing disc 2, the diameter of the fixing disc 2 is larger than the diameter of the engine 1, as shown in fig. 1 or fig. 3, the fixing disc 2 is in a disc shape, a first through hole 3 is formed in the center of the fixing disc 2, the first through hole 3 is a circular hole, the diameter of the first through hole 3 is smaller than the diameter of the fixing disc 2, the injection port passes through the first through hole 3 and is fixedly connected with the fixing disc 2, a plurality of first bolt holes are formed in the fixing disc 2 around the axial direction of the injection port, a plurality of second bolt holes corresponding to the first bolt holes are formed in the engine 1, and the first bolt holes and the second bolt holes are fixed together by using bolts, that is, namely, the fixing disc 2 and the engine 1 are fixed together by using bolts; a spoiler mechanism is further arranged on one side of the fixed disk 2 relatively close to the injection port, the spoiler mechanism is connected with the fixed disk 2, further, a protective cover 5 is fixed on the fixed disk 2, please refer to fig. 6, the specific structure of the protective cover 5 will be disclosed in a preferred embodiment, a first mounting hole 505 and a second mounting hole 506 are formed on the protective cover 5, bearings are respectively arranged in the first mounting hole 505 and the second mounting hole 506, the number of the first mounting hole 505 and the second mounting hole 506 is two, the two first mounting holes 505 are arranged along the direction e in fig. 6, the two second mounting holes 506 are also arranged along the direction e in fig. 6, the spoiler mechanism comprises at least two spoiler pieces 4, the two spoiler pieces 4 encircle the periphery of the injection port around the axis direction of the injection port, the shape of each spoiler piece 4 is as shown in fig. 4 and fig. 5, the two spoiler pieces 4 take on the shape, the opening of each spoiler piece 4 is provided with a common flow channel along the axis direction of each spoiler piece 4; as shown in fig. 4, two rotating shafts 401 are disposed on the outer wall of the spoiler 4, the two rotating shafts 401 are respectively disposed at the positions where the spoiler 4 is relatively close to the outer edge, the two rotating shafts 401 are relatively far away from the first mounting hole 505 and one surface of the second mounting hole 506 with the bearing, a driving mechanism is further disposed on the fixed disc 2, the driving mechanism is respectively hinged with the two spoiler 4, the driving mechanism is used for driving the two spoiler 4 to rotate around a first axis, the first axis is perpendicular to the axis of the engine 1, that is, the two spoiler 4 respectively rotates around the axes of the two rotating shafts 401, so that the two spoiler 4 moves in a direction where the two spoiler 4 is relatively close to or far away from each other, the spoiler 4 is composed of a metal supporting material and a heat insulating member 18, the heat insulating member 18 is in direct contact with a fuel gas flow, the heat insulating material is a high-resistant material, the high-resistant material is adopted as the heat insulating material, the high-resistant material has a high-resistant property, and the high-resistant alloy material is used as the high-temperature alloy material, and the high-resistant alloy material is used for welding the high-resistant alloy material, and has good heat-resistant strength, and high-resistant alloy material is used for welding, and the high-resistant alloy material is used for the high-resistant alloy is blown-resistant material; the rocket is also provided with a controller, the controller is in signal connection with the driving mechanism, the rocket is also provided with a detection piece, the detection piece is in signal connection with the controller, the detection piece can observe the gesture of the aircraft and detect the speed of the aircraft in the falling process, so that whether the gesture and the speed of the aircraft meet the requirements in the falling process can be judged, if the aircraft only needs to fall along the vertical direction in the falling process of the aircraft, the detection piece can continuously observe the gesture of the aircraft, when the aircraft is observed to be far left or far right, the detection piece can send the information to the controller, the gesture of the aircraft is required to be adjusted back to the normal gesture, the controller can process the signal after receiving the signal to obtain a first processing signal, the first processing signal comprises the force provided by the driving mechanism, namely, when the driving mechanism provides the force of x Newton, one of the spoiler 4 or two spoiler 4 can move towards the same direction or the two spoiler 4 along the driving axis, and the two spoiler 4 can move towards each other in the same direction or the same direction, and the two spoiler 4 can be adjusted to move along the same direction; when the detecting piece detects that the speed of the aircraft is too high or too low, a signal is sent to the controller, the controller processes the received signal to obtain a second processed signal, the second processed signal comprises the force provided by the driving mechanism, the second processed signal is sent to the driving mechanism, after the driving mechanism receives the second processed signal, Y Newton force is provided for the two spoilers 4, one or the two spoilers 4 are driven by the driving mechanism, the two spoilers 4 are controlled to be relatively close to each other or far away from each other by the signal, or the two spoilers 4 are simultaneously moved to the same side, so that the speed of the jet of the gas flow can be controlled, and the speed of the aircraft descent can be controlled; the specific operating systems such as the controller and the detecting member described above are disclosed in the patent with publication number CN207440620U, which belongs to the prior art.
In the use, the gas flow is sprayed to the inside of first runner from the jet orifice of engine 1, when the gas flow gets into first runner, partial gas flow can directly strike on the vortex piece 4 of vortex mechanism, two the vortex piece 4 can block the gas flow to can be through reducing the impact force of gas flow and then indirect control gas flow's size and direction, because the gas flow impact force has reduced, so the decline speed of arrow body also can reduce thereupon, can guarantee that the arrow body can not take place to damage or the disintegration at the in-process that falls, can realize the steady landing and the recovery of arrow body, greatly reduced the development cost and the transmission cost of rocket.
Further, the spoiler mechanism further comprises a fixing seat 6 arranged on the fixing plate 2, a connecting rod assembly is arranged between the fixing seat 6 and the spoiler 4, the connecting rod assembly comprises a first connecting rod 7 hinged to the spoiler 4 and a first connecting piece hinged to the first connecting rod 7, and one end, far away from the first connecting rod 7, of the first connecting piece is hinged to the fixing seat 6.
Specifically, in this embodiment, the spoiler mechanism further includes a fixing seat 6 disposed on the fixed disk 2, as shown in fig. 7, the fixing seat 6 includes a first fixing plate 601, the first fixing plate 601 is rectangular, a plurality of third bolt holes are disposed on two opposite sides of the first fixing plate 601, the fixing seat 6 may be fixed on the fixed disk 2 through the third bolt holes, a first connecting plate 602 and a second connecting plate 603 are further disposed on a surface of the first fixing plate 601 opposite to the fixed disk 2, the first connecting plate 602 and the second connecting plate 603 are parallel to each other, an extending direction of the first connecting plate 602 and the second connecting plate 603 is consistent with an extending direction of an axis of the fixed disk 2, one end of the first connecting plate 602 and one end of the second connecting plate 603 opposite to the first fixing plate 601 are arc-shaped, the opening of the arc shape faces the first fixing plate 601, a first hinge hole 604 is further formed at the arc ends of the first connecting plate 602 and the second connecting plate 603, the two first hinge holes 604 are parallel to each other, the axes of the two first hinge holes 604 are mutually overlapped, a first rotating space is formed between the first connecting plate 602 and the second connecting plate 603, a connecting rod assembly is rotationally connected in the first rotating space, the connecting rod assembly comprises a first connecting rod 7 and a first connecting piece which are rotationally connected with each other, the shape of the first connecting piece is as shown in fig. 8, the first connecting piece is sequentially connected with a first connecting rod 701, a second connecting rod 702 and a third connecting rod 703 around the axial direction of the first connecting piece, a second hinge hole 7001 is arranged at the joint of the first connecting rod 701 and the second connecting rod 702, a third hinge hole 7002 is formed at the connection position between the second connecting rod 702 and the third connecting rod 703, a fourth hinge hole 7003 is formed at the connection position between the third connecting rod 703 and the first connecting rod 701, the first hinge hole 604 and the fourth hinge hole 7003 on the fixing base 6 are connected together by using a hinge shaft, one end of the first connecting rod 7 is connected with the third hinge hole 7002 by using a hinge shaft, one end of the first connecting rod 7, which is relatively far from the third hinge hole 7002, is rotatably connected with the spoiler 4, as shown in fig. 4, a first hinge part 402 is formed on one surface, which is relatively far from each other, of each spoiler 4, and the first hinge part 402 is rotatably connected with the first connecting rod 7 by using a hinge shaft.
Further, the driving mechanism comprises a first mounting seat 8, the first mounting seat 8 is arranged on one surface of the fixed disc 2, which is relatively far away from the fixed seat 6, the driving mechanism further comprises a linear driving piece 9 arranged in the first mounting seat 8, a second through hole 10 is formed in the fixed disc 2, and the output end of the linear driving piece 9 penetrates through the second through hole 10 and is hinged with the first connecting piece.
Specifically, in this embodiment, as shown in fig. 3, a first mounting seat 8 is disposed on a surface of the fixing plate 2 opposite to the fixing seat 6, as shown in fig. 10, the first mounting seat 8 includes a first mounting plate, the first mounting plate includes a first fixing portion 801, a second fixing portion 802, and a third fixing portion 803 that are sequentially connected, the first fixing portion 801 and the third fixing portion 803 are each rectangular, the first fixing portion 801 and the third fixing portion 803 extend along a direction shown in fig. 10, the second fixing portion 802 connects the first fixing portion 801 and the third fixing portion 803 together, an extending direction of the second fixing portion 802 extends along a direction b shown in fig. 10, and extending directions of the first fixing portion 801, the third fixing portion 803, and the second fixing portion 802 are mutually perpendicular, the first fixing portion 801 and the third fixing portion 803 are respectively provided with two support plates 804, the two support plates 804 are respectively triangle-shaped, the two support plates 804 are parallel to each other, the extending direction of the two support plates 804 is consistent with the extending direction of the axis of the fixed disk 2, a connecting plate 805 is further connected between the two support plates 804, the connecting plate 805 is rectangular, the connecting plate 805 comprises a first side 8051, a second side 8052, a third side 8053 and a fourth side 8054 which are sequentially connected, the first side 8051 and the third side 8053 are respectively connected with one side of the two support plates 804 close to each other and are respectively perpendicular to one side of the two support plates 804 close to each other, the fourth side 8054 is connected with the first fixing portion 801 and the third fixing portion 803, and the engagement plate 805 is perpendicular to the first fixing portion 801 and the third fixing portion 803, two support plates 804, the engagement plate 805, the first fixing portion 801, the third fixing portion 803 and the second fixing portion 802 together form an installation space, the linear driving member 9 is disposed in the installation space, the linear driving member 9 is a linear servo motor, a second through hole 10 is formed in the fixing plate 2, the second through hole 10 is rectangular, a notch of the first mounting plate is consistent with the second through hole 10, the linear driving member 9 has a linear driving end, and the linear driving end is rotationally connected with the second hinge hole 7001 of the first connecting member by using a pin shaft.
During the use, the gas flow sprayed from the injection port of the engine 1 enters the first flow channel and impinges on the two turbulence pieces 4, after colliding with the two turbulence plates, the speed and the direction of the gas flow spraying can be changed due to the blocking of the two turbulence plates on the gas flow, when the detecting piece detects that the falling speed of the air vehicle is too fast or too slow or the gesture of the air vehicle is separated from the fixed preset gesture, the detecting piece can send a signal to the controller, the controller can process the signal after receiving the signal sent by the detecting piece, and obtain the second processed signal, the second processed signal is sent to the driving mechanism in a signal mode, after receiving the second processed signal, a certain driving force is transmitted to the first connecting piece 7 according to the second processed signal, and then is transmitted to the turbulence pieces 4 through the first connecting piece 7, and the two turbulence pieces 4 are driven to move towards or away from each other relative to the opposite directions of the air vehicle, so that the two turbulence pieces can move towards or away from each other relative to the opposite directions of the air vehicle, and the opposite directions of the two turbulence pieces can be controlled to move towards or away from each other, and the opposite directions of the air vehicle can be controlled, and the opposite directions of the jet directions of the air flow can be moved towards each other.
Further, a transmission shaft 11 is disposed between the output end and the first connecting piece, one end of the transmission shaft 11 is hinged to the first connecting piece, and the other end of the transmission shaft is fixedly connected with the output end.
Specifically, in this embodiment, referring to fig. 9 and 11, a driving shaft 11 is further fixedly connected to the linear driving end of the linear driving member 9, and the other end of the driving shaft 11 is rotatably connected to the second hinge hole 7001 of the first connecting member.
Further, a switching assembly is further arranged between the transmission shaft 11 and the first connecting piece, the switching assembly comprises a first switching piece 12 hinged with the first connecting piece, and a second switching piece 13 is hinged to the other end of the first switching piece 12.
Specifically, in this embodiment, referring to fig. 11, an adaptor assembly is further provided between the transmission shaft 11 and the first connector, the adaptor assembly includes a first adaptor 12, the first adaptor 12 is shaped as shown in fig. 11, one end of the first adaptor 12 is hinged to the first connector, one end of the first adaptor 12, which is relatively far away from the first connector, is hinged to a second adaptor 13, one end of the second adaptor 13, which is relatively far away from the first adaptor 12, is hinged to the transmission shaft 11, and since the gas flow sprayed from the engine 1 is very strong, when the rotation angle of the spoiler 4 is adjusted by the driving mechanism, the driving mechanism receives the impact force from the gas flow, the impact force of the gas flow is gradually transferred to the linear driving member 9, and damage is caused to the linear driving member 9.
Further, a second mounting seat 14 is disposed in the second through hole 10, a sliding rail 15 extending along a first direction is disposed on the second mounting seat 14, a sliding groove 16 extending along the first direction is disposed on the second adaptor 13, and the sliding groove 16 is slidably connected with the sliding rail 15.
Specifically, in this embodiment, referring to fig. 2, 9 and 12, a second mounting seat 14 is further disposed in the second through hole 10, the second mounting seat 14 includes a second mounting plate 141, the second mounting plate 141 is rectangular, the second mounting plate 141 extends in the vertical direction in fig. 11, extends in the c direction in fig. 12, a third mounting plate 142 is disposed on one surface of the second mounting plate 141, the third mounting plate 142 is disposed in the middle of the second mounting plate 141 and perpendicular to the second mounting plate 141, the second mounting plate 141 and the third mounting plate 142 together form a T-shaped structure, a reinforcing rib 143 is further disposed between the second mounting plate 141 and the third mounting plate 142, the reinforcing rib 143 is in a right triangle shape, two right-angle sides of the reinforcing rib 143 are respectively fixedly connected with the second mounting plate 141 and the third mounting plate 142, for example, the third mounting plate 142 is provided with a plurality of bolt holes, the third mounting plate 142 is fixed on the fixed plate 2 by using bolts, the second mounting plate 141 is arranged in the second through hole 10, a rectangular accommodating hole is formed at one end of the connecting plate 805 relatively close to the first mounting seat 8, one end of the second mounting plate 141 extends into the accommodating hole, a sliding rail 15 is arranged on the second mounting plate 141, the sliding rail 15 extends along the first direction, a sliding groove 16 is arranged on the second adapting piece 13, the sliding groove 16 also extends along the first direction, the sliding groove 16 is in sliding connection with the sliding rail 15, a second connecting piece 17 is further arranged between the sliding rail 15 and the second adapting piece 13, the second connecting piece 17 is in a T shape, the second connecting piece 17 is divided into a third connecting portion and a fourth connecting portion which are connected vertically, the third connecting portion extends along a second direction, the second direction is perpendicular to the first direction, the second direction is a horizontal direction shown in fig. 11, the fourth connecting portion extends along the first direction, the first direction is a vertical direction in fig. 11, the third connecting portion is located at the left side of the fourth connecting portion, a T-shaped structure is formed together, if the sliding rail 15 is directly mounted on the second adapting piece 13, the sliding rail 15 may fall off on the second adapting piece 13, so the second adapting piece 13 is provided with the second connecting piece 17, the second adapting piece 13 is fixedly connected with the second connecting piece 17, and the sliding rail 15 is fixedly connected with the second connecting piece 17.
In the use, when the flight speed and the flight direction of the aircraft need to be adjusted, the gas flow can act on the spoiler 4, can produce very strong effort, can cause the damage to the linear driving piece 9, because the impact force that the linear driving piece 9 can bear is limited, be equipped with on the fixed disk 2 the second mount pad 14 be provided with on the second mount pad 15 the spout is provided with on the second adaptor 13, when effort is passed on to the spout with on the spout 15, the spout 15 can move in the spout, makes the effect of a part of impact force that produces on the spout 15, thereby reduces to the impact of linear driving piece 9.
Furthermore, a protective cover 5 with a first opening is further arranged on the fixed disc 2, the protective cover 5 is provided with an accommodating space, the jet opening and the spoiler 4 are both positioned in the accommodating space, and the spoiler 4 is rotatably connected with the inner wall of the protective cover 5.
Specifically, in this embodiment, a protection cover 5 is further disposed on the fixed disk 2, as shown in fig. 2, the installation positions of the protection cover 5 and the fixed disk 2 are as shown in fig. 6, the protection cover 5 includes a first portion and a second portion that are connected to each other, the first portion is in a hollow cylindrical shape, the diameter of the first portion in fig. 6 increases gradually along the d direction, the second portion includes a first connection portion 501, a first installation portion 502, a second connection portion 503, and a second installation portion 504 that are sequentially arranged around the first portion axis direction, the first connection portion 501 and the second connection portion 503 are all in a circular arc shape, the openings of the circular arcs face the axis direction of the first portion, the first installation portion 502 and the second installation portion 504 are all in a flat plate shape, a first installation hole 505 and a second installation hole 506 are respectively disposed on the first installation portion and the second installation portion 504, a first installation hole 505 is respectively disposed in the first installation hole 505 and the second installation hole 506, a second installation hole 505 is respectively disposed in the second installation hole 506 and is respectively in the second installation hole 401 and the second installation hole 4, and the two installation holes are respectively arranged in the two opposite directions of the first surface and the second surface are respectively, the first surface and the second surface is respectively opposite to the first surface and the second surface is respectively provided with a bearing hole 401 and the second surface is respectively disposed in the two opposite directions of the first surface and the second surface is respectively, the first surface and the second surface is opposite to the first surface and the second surface, and the second surface is the first surface, and the second surface is the installation hole is provided; the inside of the protective cover 5 is provided with an accommodating space, the jet opening and the spoiler 4 are both positioned in the accommodating space, the protective cover 5 can protect the jet opening, the spoiler 4 and other parts, and the spoiler 4 can be prevented from being damaged by external atmospheric air flow in the working process; two second openings 507 are arranged on the first subsection, the two second openings 507 are symmetrically arranged relative to the extending direction of the axis of the first subsection, and one end of the turbulence mechanism extends into the accommodating space through the two second openings 507 and is rotationally connected with the turbulence piece 4.
Further, the number of the turbulence pieces 4 is two.
Specifically, in this embodiment, the number of the turbulence pieces 4 is two altogether, the two turbulence pieces 4 are arranged around the periphery of the injection port in the axial direction of the engine 1, and form the first flow channel, and the two turbulence pieces 4 rotate around the first axis under the driving of the linear driving piece 9, so that the two turbulence pieces 4 are relatively close to each other or relatively far away from each other, or the two turbulence pieces 4 move towards the same side at the same time, so that the size and direction of the fuel gas flow can be controlled, and further, the falling speed and the falling direction in the falling process of the aircraft can be controlled, so that the aircraft can not be disassembled or damaged in the recovery process.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the method of the present invention and its core ideas. The foregoing is merely illustrative of the preferred embodiments of this invention, and it is noted that there is objectively no limit to the specific structure disclosed herein, since numerous modifications, adaptations and variations can be made by those skilled in the art without departing from the principles of the invention, and the above-described features can be combined in any suitable manner; such modifications, variations and combinations, or the direct application of the inventive concepts and aspects to other applications without modification, are contemplated as falling within the scope of the present invention.
Claims (3)
1. A recoverable aircraft jet control device for use at the jet of a rocket engine (1), comprising:
the fixed disc (2), the fixed disc (2) is provided with a first through hole (3), and the jet orifice penetrates through the first through hole (3) and is fixedly connected with the fixed disc (2);
the turbulence mechanism is arranged on one side of the fixed disc (2) close to the jet orifice, the turbulence mechanism comprises at least two turbulence pieces (4), the at least two turbulence pieces (4) are arranged on the periphery of the jet orifice and are arranged around the axis direction of the engine (1), and a first flow passage is formed in the at least two turbulence pieces (4);
the driving mechanism is respectively connected with at least two turbulence pieces (4) and is used for driving the turbulence pieces (4) to rotate around a first axis, and the first axis is perpendicular to the axis of the engine (1);
-a flow of fuel gas injected from the engine (1), via the first flow channel and impinging on the spoiler (4), to control the injection speed and injection direction of the flow of fuel gas;
the turbulence mechanism further comprises a fixed seat (6) arranged on the fixed disc (2), a connecting rod assembly is arranged between the fixed seat (6) and the turbulence piece (4), the connecting rod assembly comprises a first connecting rod (7) hinged with the turbulence piece (4) and a first connecting piece hinged with the first connecting rod (7), and one end, far away from the first connecting rod (7), of the first connecting piece is hinged with the fixed seat (6);
the driving mechanism comprises a first mounting seat (8), the first mounting seat (8) is arranged on one surface of the fixed disc (2) relatively far away from the fixed seat (6), the driving mechanism further comprises a linear driving piece (9) arranged in the first mounting seat (8), a second through hole (10) is formed in the fixed disc (2), and the output end of the linear driving piece (9) penetrates through the second through hole (10) and is hinged with the first connecting piece;
a transmission shaft (11) is arranged between the output end and the first connecting piece, one end of the transmission shaft (11) is hinged with the first connecting piece, and the other end of the transmission shaft is fixedly connected with the output end;
a switching assembly is further arranged between the transmission shaft (11) and the first connecting piece, the switching assembly comprises a first switching piece (12) hinged with the first connecting piece, and a second switching piece (13) is hinged with the other end of the first switching piece (12);
a second mounting seat (14) is arranged in the second through hole (10), a sliding rail (15) extending along the first direction is arranged on the second mounting seat (14), a sliding groove (16) extending along the first direction is arranged on the second adapter (13), and the sliding groove (16) is in sliding connection with the sliding rail (15).
2. The recoverable aircraft jet control device according to claim 1, wherein a protective cover (5) with a first opening is further provided on the fixed disk (2), the protective cover (5) has a receiving space, the jet and the spoiler (4) are both located in the receiving space, and the spoiler (4) is rotatably connected with the inner wall of the protective cover (5).
3. Recoverable aircraft jet control device according to claim 1, characterised in that the number of spoilers (4) is two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310819325.1A CN116537975B (en) | 2023-07-06 | 2023-07-06 | Recoverable aircraft jet control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310819325.1A CN116537975B (en) | 2023-07-06 | 2023-07-06 | Recoverable aircraft jet control device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116537975A CN116537975A (en) | 2023-08-04 |
| CN116537975B true CN116537975B (en) | 2023-10-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310819325.1A Active CN116537975B (en) | 2023-07-06 | 2023-07-06 | Recoverable aircraft jet control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116537975B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1308913A (en) * | 1969-08-12 | 1973-03-07 | Imp Metal Ind Kynoch Ltd | Control systems for rocket motors |
| US4432512A (en) * | 1978-08-31 | 1984-02-21 | British Aerospace Public Limited Company | Jet propulsion efflux outlets |
| CN1283253A (en) * | 1997-08-12 | 2001-02-07 | 太空通道有限公司 | Ejector ramjet engine |
| EP1959124A2 (en) * | 2007-02-15 | 2008-08-20 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Device for controlling the nozzle thrust direction of a rocket engine |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6154537B2 (en) * | 2014-02-19 | 2017-06-28 | 三菱重工業株式会社 | Thrust deflector |
| EP3634857B1 (en) * | 2017-06-08 | 2021-03-10 | AVIO S.p.A. | Attitude control and thrust boosting system and method for space launchers |
| US11352978B2 (en) * | 2020-06-24 | 2022-06-07 | Raytheon Company | Deflectable distributed aerospike rocket nozzle |
-
2023
- 2023-07-06 CN CN202310819325.1A patent/CN116537975B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1308913A (en) * | 1969-08-12 | 1973-03-07 | Imp Metal Ind Kynoch Ltd | Control systems for rocket motors |
| US4432512A (en) * | 1978-08-31 | 1984-02-21 | British Aerospace Public Limited Company | Jet propulsion efflux outlets |
| CN1283253A (en) * | 1997-08-12 | 2001-02-07 | 太空通道有限公司 | Ejector ramjet engine |
| EP1959124A2 (en) * | 2007-02-15 | 2008-08-20 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Device for controlling the nozzle thrust direction of a rocket engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116537975A (en) | 2023-08-04 |
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