CN113879547A - Rotary support of micro turbojet engine - Google Patents
Rotary support of micro turbojet engine Download PDFInfo
- Publication number
- CN113879547A CN113879547A CN202111354720.4A CN202111354720A CN113879547A CN 113879547 A CN113879547 A CN 113879547A CN 202111354720 A CN202111354720 A CN 202111354720A CN 113879547 A CN113879547 A CN 113879547A
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- China
- Prior art keywords
- turbojet engine
- micro turbojet
- engine
- rotating
- side plates
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- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 230000017525 heat dissipation Effects 0.000 claims 3
- 238000005507 spraying Methods 0.000 abstract description 4
- 230000005855 radiation Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/16—Aircraft characterised by the type or position of power plant of jet type
- B64D27/20—Aircraft characterised by the type or position of power plant of jet type within or attached to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
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- B64D27/40—
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- B64D27/404—
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pest Control & Pesticides (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a rotary bracket of a micro turbojet engine, which comprises a pair of supporting side plates for supporting the micro turbojet engine, wherein the micro turbojet engine is rotatably arranged between the pair of supporting side plates through an engine clamping and rotating device; a connecting cover plate for connecting bearing equipment is arranged on the pair of supporting side plates above the micro turbojet engine; the device comprises a rotary driving device and a wireless controller used for controlling the rotary driving device, wherein the wireless controller is in wireless connection with the rotary driving device, accurately controls the deflection angle of the micro turbojet engine, and changes the spraying direction of a tail spraying nozzle of the micro turbojet engine. The invention realizes the horizontal starting and the vertical operation of the micro turbojet engine, and is suitable for fixing the micro turbojet engine below an unmanned aerial vehicle to extinguish fire, fight fire and the like when the micro turbojet engine is used as a core power device.
Description
Technical Field
The invention relates to a matching device of a micro turbojet engine, in particular to a rotary support of the micro turbojet engine.
Background
The micro-accident spraying engine has the advantages of small volume, light weight, high power and the like, and is widely applied to high-speed unmanned aerial vehicles, flying patrol bombs, decoy bombs, target drone and the like; in addition, the micro-turbojet engine can be used as a core power device to be applied to civil fields such as turbojet snow removal/deicing, turbojet fire extinguishing, turbojet fog dissipation and the like.
When the micro turbojet engine is used as a core power device and applied to the fields of snow removal, fire extinguishment and the like in the air, the micro turbojet engine is fixed and hung below the unmanned aerial vehicle when needed, the common method is to directly fix the micro turbojet engine and the unmanned aerial vehicle, when the micro turbojet engine and the unmanned aerial vehicle are horizontally fixed, the engine is started in a horizontal rotating state, and a bent pipe and the like are installed to change the direction of airflow during operation; when perpendicular fixed, generally the spout is down, and this just has on the initial stage, and unmanned aerial vehicle is on ground, and engine during operation high temperature gas can upwards flow back, makes unmanned aerial vehicle, engine annex etc. burnt out by high temperature gas, and take off unmanned aerial vehicle earlier, when flying to in the air, the engine of vertical start again, and the thrust oil that the engine produced can influence the stability that unmanned aerial vehicle flies, has the potential safety hazard.
Disclosure of Invention
The invention aims to avoid the defects of the prior art and provides a rotary bracket of a micro turbojet engine, which can be used for mounting the micro turbojet engine, realizing horizontal starting and vertical operation of the micro turbojet engine, and enabling the engine to deflect from 0 degree to 90 degrees in the operation process so as to meet different use requirements.
In order to achieve the purpose, the invention adopts the technical scheme that: a micro turbojet engine rotary support comprises a pair of supporting side plates for supporting a micro turbojet engine, wherein the micro turbojet engine is rotatably arranged between the pair of supporting side plates through an engine clamping and rotating device; a connecting cover plate for connecting bearing equipment is arranged on the pair of supporting side plates above the micro turbojet engine;
the wireless controller controls the rotation driving device to drive the engine to clamp the rotating device so as to rotate the micro turbojet engine, thereby accurately controlling the deflection angle of the micro turbojet engine and changing the spraying direction of a tail nozzle of the micro turbojet engine; the rotary driving device is also arranged on the supporting side plate.
Furthermore, the rotary driving device comprises a servo steering engine, and the rotating end of a tiller of the servo steering engine is connected with the rotating end of the upper rocker arm; the rotating connecting end of the engine clamping rotating device is connected with the rotating end of the lower rocker arm; the other ends of the rotating ends of the upper rocker arm and the lower rocker arm are swinging ends, and the swinging ends of the upper rocker arm and the lower rocker arm are connected through a pull rod; the servo steering engine is used for driving the swing end of the upper rocker arm to swing, the swing end of the lower rocker arm is driven to swing through the pull rod, and the rotating end of the lower rocker arm drives the engine clamping rotating device to drive the micro turbojet engine to rotate.
Furthermore, a servo steering engine of the rotary driving device is arranged in a steering engine mounting hole formed in the supporting side plate, and the rotating end of the lower rocker arm is connected with the rotary connecting end of the engine clamping and rotating device.
Further, engine chucking rotary device including fixed chucking the clamp on the miniature turbojet engine circumference casing be equipped with a pair of engaging lug on the clamp, the one end and the clamp of engaging lug link firmly, the rotatable connection of the other end of engaging lug is in a pair of support curb plate on.
Furthermore, the connecting end of the connecting lug and the supporting side plate is fixedly provided with a connecting clamping sleeve, the connecting clamping sleeve is provided with a rotating shaft, the rotating shaft is rotatably arranged in the connecting holes in the pair of supporting side plates in a penetrating way, and the connecting end part of the rotating shaft is connected with the rotary driving device.
Furthermore, the connecting end part of the rotating shaft is nested and fixedly connected with the rotating end of the lower rocker arm of the rotary driving device.
Furthermore, the connecting cover plate is fixed on the pair of supporting side plates through the matching of bolts and connecting holes, and the connecting holes are formed in the end faces of the connecting ends of the supporting side plates and the connecting cover plate.
Furthermore, the jet angle of the tail jet nozzle of the micro turbojet engine is 0-90 degrees, when the jet angle is 0 degree, the connecting cover plate of the rotating support is positioned at the cold air inlet end of the micro turbojet engine, and the pair of supporting side plates are parallel to the arrangement direction of the micro turbojet engine; when the injection angle is 90 degrees, a pair of supporting side plates of the rotating support and the arrangement direction of the micro turbojet engine are perpendicular to each other, and the connecting cover plate and the micro turbojet engine are horizontally arranged.
Furthermore, the distance between the lower surface of the connecting cover plate and the cold air inlet end of the micro turbojet engine is larger than 30 mm.
Furthermore, the connecting cover plate and the pair of supporting side plates are respectively provided with a heat radiation hole for heat radiation of the micro turbojet engine, and the hole area of the heat radiation hole accounts for more than 50% of the plate surface area of the connecting cover plate and the supporting side plates respectively.
The invention has the beneficial effects that: the miniature turbojet engine is started in a horizontal state and operated in a vertical direction, the engine can be deflected by 0-90 degrees in the operation process to change the exhaust direction, and the miniature turbojet engine is suitable for being fixed below an unmanned aerial vehicle to extinguish fire, fight fire and the like in the air when being used as a core power device.
The invention realizes the integral deflection of the micro turbojet engine, can ensure the horizontal starting of the micro turbojet engine, and can deflect at any angle within the range of 0-90 degrees so as to change the jet air flow direction of the engine, and has simple and reasonable integral structure and high safety and reliability.
In recent years, with the rapid development of the aviation industry in China, the design and manufacture of a micro turbojet engine gradually become mature, and the manufacturing cost is low. The working performance of the miniature spray engine is stable, the power of the miniature spray engine is 2-2.5 times that of a small gasoline engine, and the mass of the miniature spray engine is only about 1/3 that of the small gasoline engine. Therefore, the micro turbojet engine is adopted as a core power device and is combined with the unmanned aerial vehicle, and the micro turbojet engine is modified and applied to civil fields such as aerial fire extinguishment, fire fighting and the like, and has wide market prospect.
Drawings
FIG. 1 is a schematic view of a rotary support of the micro turbojet engine of the present invention;
FIG. 2 is a schematic view of a rotary support of the micro turbojet engine of the present invention.
Numbering in the figures: 1. connecting the cover plate; 2. an engine support side panel; 3. an engine clamping and rotating device; 31. clamping a hoop; 32. connecting lugs; 33. connecting the clamping sleeve; 34. a rotating shaft; 4. a micro turbojet engine; 5. a rotation driving device; 51. a servo steering engine; 52. an upper rocker arm; 54. a lower rocker arm; 53 a pull rod; 9. connecting holes; 12. steering wheel mounting hole.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Because the technique of miniature turbojet engine is mature gradually to its range of application also crescent, when being used for fields such as snow removing in the air, putting out a fire, when using, need fix miniature turbojet engine and hang in the unmanned aerial vehicle below, so, the thrust oil that the engine produced can influence the stability of unmanned aerial vehicle flight, has the potential safety hazard. Therefore, the invention provides a rotary bracket for a micro turbojet engine installed on an unmanned aerial vehicle, which enlarges the application scenes of the micro turbojet engine, reduces the potential safety hazard with low cost, and adopts the following specific embodiments:
example 1: as shown in fig. 1 and 2, a micro turbojet engine rotary support comprises a pair of engine supporting side plates 2, and a micro turbojet engine 4 is rotatably mounted between the pair of supporting side plates 2 through an engine clamping and rotating device 3; the connecting cover plate 1 is used for connecting bearing equipment and is arranged on a pair of supporting side plates 2 above the micro turbojet engine 4, so that the integral structural strength is ensured; the bearing equipment mainly refers to an unmanned aerial vehicle and an unmanned aerial vehicle.
The miniature turbojet engine 4 is driven to rotate by the rotation driving device 5 through the engine clamping and rotating device 3, so that the injection angle of a tail nozzle of the miniature turbojet engine 4 is changed, the rotation driving device 5 is controlled by a wireless controller, the rotation driving device 5 sends a servo coding signal to the wireless controller, the deflection direction of the miniature turbojet engine 4 is accurately set, namely the injection angle position of a specific tail nozzle is positioned, and the angle deflection of the miniature turbojet engine 4 is realized; the jet angle of a tail jet nozzle of the micro turbojet engine 4 is 0-90 degrees, when the jet angle is 0 degrees, the connecting cover plate 1 of the rotating bracket is positioned at the cold air inlet end of the micro turbojet engine 4, and the pair of supporting side plates 2 are parallel to the arrangement direction of the micro turbojet engine 4; when the injection angle is 90 degrees, the pair of supporting side plates 2 of the rotating bracket is vertically arranged with the arrangement direction of the micro turbojet engine 4, and the connecting cover plate 1 is horizontally arranged with the micro turbojet engine 4. The distance between the lower surface of the connecting cover plate 1 and the cold air inlet end of the micro turbojet engine 4 is more than 30 mm.
The rotary driving device 5 is also arranged on the supporting side plate 2, the rotary driving device 5 comprises a servo steering engine 51, the servo steering engine 51 is arranged in a steering engine mounting hole 12 formed in the supporting side plate 2, the rotating end of a tiller of the servo steering engine 51 is connected with the rotating end of the upper rocker arm 52 through a bolt, and the upper rocker arm 52 is used for transmitting the torque transmitted by the servo steering engine 51; the other ends of the rotating ends of the upper rocker arm 52 and the lower rocker arm 54 are swing ends, the swing ends of the two rocker arms are connected through a pull rod 53, the pull rod 53 is used for transmitting torque, the integral deflection of the two rocker arms is realized, meanwhile, the telescopic length of the pull rod 53 can be adjusted by threads, and the length of the pull rod 53 is ensured to meet the deflection requirement; the servo steering engine 51 is used for driving the swinging end of the upper rocker arm 52 to swing, so that the swinging end of the lower rocker arm 54 is driven to swing through the pull rod 53, and the rotating end of the lower rocker arm 54 drives the micro turbojet engine 4 to rotate through the engine clamping and rotating device 3.
The engine clamping and rotating device 3 comprises a clamp 31 fixedly clamped on the circumferential shell of the micro turbojet engine 4, a pair of connecting lugs 32 is arranged on the clamp 31, one end of each connecting lug 32 is fixedly connected with the clamp 31, and the other end of each connecting lug 32 is rotatably connected to a pair of supporting side plates 2. A connecting clamping sleeve 33 is fixedly arranged at one end of the connecting lug 32 connected with the supporting side plates 2, a rotating shaft 34 is arranged on the connecting clamping sleeve 33, the rotating shaft 34 is rotatably arranged in a connecting hole 35 on the pair of supporting side plates 2 in a penetrating way, and the connecting end part of the rotating shaft 34 is nested and fixedly connected with the rotating end of the lower rocker arm 54 of the rotary driving device 5.
The connecting cover plate 1 is fixed on the pair of supporting side plates 2 through the matching of bolts and connecting holes 9, and the connecting holes 9 are arranged on the end faces of the connecting ends of the supporting side plates 2 and the connecting cover plate 1. The connecting cover plate 1 and the pair of supporting side plates 2 are respectively provided with a heat radiation hole 7 for heat radiation of the micro turbojet engine 4, and the hole areas of the heat radiation holes 7 respectively account for more than 50% of the plate surface areas of the connecting cover plate 1 and the supporting side plates 2. The plate surfaces of the connecting cover plate 1 and the supporting side plate 2 are designed in a hollow mode, so that the weight is reduced, and the air flow required by the vertical operation of the micro turbojet engine is guaranteed.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. The rotating support of the micro turbojet engine is characterized by comprising a pair of supporting side plates (2) for supporting the micro turbojet engine, wherein the micro turbojet engine (4) is rotatably arranged between the pair of supporting side plates (2) through an engine clamping and rotating device (3); a connecting cover plate (1) for connecting bearing equipment is arranged on the pair of supporting side plates (2) above the micro turbojet engine (4);
the device is characterized by also comprising a rotation driving device (5) and a wireless controller for controlling the rotation driving device (5), wherein the wireless controller is wirelessly connected with the rotation driving device (5), and controls the rotation driving device (5) to drive the engine to clamp the rotation device (3) so as to rotate the micro turbojet engine (4), thereby accurately controlling the deflection angle of the micro turbojet engine (4) and changing the injection direction of a tail nozzle of the micro turbojet engine (4); the rotary driving device (5) is also arranged on the supporting side plate (2).
2. The rotary bracket of the micro turbojet engine according to claim 1, wherein the rotary drive device (5) comprises a servo steering engine (51), and the rotating end of a tiller of the servo steering engine (51) is connected with the rotating end of the upper rocker arm (52); the rotating connecting end of the engine clamping rotating device (3) is connected with the rotating end of the lower rocker arm (54); the other ends of the rotating ends of the upper rocker arm (52) and the lower rocker arm (54) are swinging ends, and the swinging ends of the upper rocker arm (52) and the lower rocker arm (54) are connected through a pull rod (53); the servo steering engine (51) is used for driving the swinging end of the upper rocker arm (52) to swing, so that the swinging end of the lower rocker arm (54) is driven to swing through the pull rod (53), and the rotating end of the lower rocker arm (54) drives the engine clamping and rotating device (3), so that the micro turbojet engine (4) is driven to rotate.
3. The rotary bracket of the micro turbojet engine according to claim 2, wherein the servo steering engine (51) of the rotary driving device (5) is mounted in a steering engine mounting hole (12) formed in the supporting side plate (2), and the rotating end of the lower rocker arm (54) is connected with the rotary connecting end of the engine clamping and rotating device (3).
4. The rotary bracket of a micro turbojet engine according to claim 2, wherein the engine clamping and rotating device (3) comprises a clamp (31) fixedly clamped on the circumferential casing of the micro turbojet engine (4), a pair of engaging lugs (32) are arranged on the clamp (31), one end of each engaging lug (32) is fixedly connected with the clamp (31), and the other end of each engaging lug (32) is rotatably connected to the pair of support side plates (2).
5. The rotary bracket of a micro turbojet engine according to claim 4, wherein a connecting sleeve (33) is fixedly arranged at one end of the connecting lug (32) connected with the support side plates (2), a rotating shaft (34) is arranged on the connecting sleeve (33), the rotating shaft (34) is rotatably inserted into the connecting holes (35) in the pair of support side plates (2), and the connecting end of the rotating shaft (34) is connected with the rotation driving device (5).
6. The rotary bracket of a micro turbojet engine according to claim 5, wherein the connection end of the rotary shaft (34) is nested and attached to the rotating end of the lower rocker arm (54) of the rotary drive device (5).
7. The rotary bracket of a micro turbojet engine according to claim 1, wherein the connecting cover plate (1) is fixed to the pair of support side plates (2) by bolts in cooperation with the connecting holes (9), and the connecting holes (9) are formed in the end faces of the support side plates (2) at the end connected with the connecting cover plate (1).
8. The rotary bracket of a micro turbojet engine according to any one of claims 1 to 7, wherein the jet angle of the tail jet nozzle of the micro turbojet engine (4) is 0 to 90 °, and when the jet angle is 0 °, the connecting cover plate (1) of the rotary bracket is positioned at the cold air inlet end of the micro turbojet engine (4), and the pair of support side plates (2) are parallel to the arrangement direction of the micro turbojet engine (4); when the injection angle is 90 degrees, the arrangement directions of a pair of supporting side plates (2) of the rotating support and the micro turbojet engine (4) are perpendicular to each other, and the connecting cover plate (1) and the micro turbojet engine (4) are horizontally arranged.
9. The rotary bracket of a micro turbojet engine according to claim 8, wherein the distance between the lower surface of the connecting cover plate (1) and the cold air inlet end of the micro turbojet engine (4) is greater than 30 mm.
10. The rotating bracket of a micro turbojet engine according to any one of claims 1 to 7, wherein the connecting cover plate (1) and the pair of support side plates (2) are provided with heat dissipation holes (7) for heat dissipation of the micro turbojet engine (4), and the hole areas of the heat dissipation holes (7) respectively account for more than 50% of the plate surface areas of the connecting cover plate (1) and the support side plates (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111354720.4A CN113879547A (en) | 2021-11-16 | 2021-11-16 | Rotary support of micro turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111354720.4A CN113879547A (en) | 2021-11-16 | 2021-11-16 | Rotary support of micro turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113879547A true CN113879547A (en) | 2022-01-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111354720.4A Pending CN113879547A (en) | 2021-11-16 | 2021-11-16 | Rotary support of micro turbojet engine |
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| Country | Link |
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| CN (1) | CN113879547A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN110194268A (en) * | 2019-06-13 | 2019-09-03 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of unmanned plane miniature gas turbine hybrid power apparatus of oil and electricity |
| CN111450445A (en) * | 2020-04-12 | 2020-07-28 | 赣州江钨汽车改装有限公司 | Dedicated unmanned aerial vehicle of fire control |
| CN216233006U (en) * | 2021-11-16 | 2022-04-08 | 西安觉天动力科技有限责任公司 | Rotary support of micro turbojet engine |
-
2021
- 2021-11-16 CN CN202111354720.4A patent/CN113879547A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN110194268A (en) * | 2019-06-13 | 2019-09-03 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of unmanned plane miniature gas turbine hybrid power apparatus of oil and electricity |
| CN111450445A (en) * | 2020-04-12 | 2020-07-28 | 赣州江钨汽车改装有限公司 | Dedicated unmanned aerial vehicle of fire control |
| CN216233006U (en) * | 2021-11-16 | 2022-04-08 | 西安觉天动力科技有限责任公司 | Rotary support of micro turbojet engine |
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