CN111547266A - Multi-channel foldable box-type low-altitude sounding rocket launching device - Google Patents
Multi-channel foldable box-type low-altitude sounding rocket launching device Download PDFInfo
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- CN111547266A CN111547266A CN202010400650.0A CN202010400650A CN111547266A CN 111547266 A CN111547266 A CN 111547266A CN 202010400650 A CN202010400650 A CN 202010400650A CN 111547266 A CN111547266 A CN 111547266A
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- 238000003466 welding Methods 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 230000001681 protective effect Effects 0.000 description 4
- 238000001514 detection method Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
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Abstract
The invention provides a multi-channel foldable box-type low-altitude sounding rocket launching device, which comprises a box body, a director assembly, a supporting rod and supporting legs, wherein the box body is provided with a box body; the orientator assembly is connected with the box body through a support trunnion; one end of the supporting rod is connected with the supporting lug at the bottom of the box body, the other end of the supporting rod is connected with the supporting lug on the directing device assembly, the length of the supporting rod is adjustable, and the adjustment of the emitting angle of the directing device assembly is realized by adjusting the length of the supporting rod; four landing legs pass through the landing leg hub connection to the box on, the landing leg can be around the landing leg axle gyration, adjusts the support area that 4 landing legs formed through changing the gyration angle to improve launch stability.
Description
Technical Field
The invention belongs to the technical field of meteorological detection operation, and particularly relates to a multi-channel foldable box-type low-altitude sounding rocket launching device.
Background
The low-altitude sounding rocket mainly probes PTU (pressure, temperature and humidity) parameters in the height range of 0-1km, and the meteorological parameters can provide basis for low-altitude atmospheric detection. At present, low-altitude detection is the national requirement, and low-altitude sounding rocket launching device is mostly the single tube and weight is heavier, and the operation is inconvenient, should not carry, therefore designs a simple convenient low-altitude sounding rocket launching device and has important meaning.
Disclosure of Invention
In view of the above, the invention aims to provide a multi-channel foldable box-type low-altitude sounding rocket launching device,
the technical scheme for realizing the invention is as follows:
a multi-channel foldable box type low-altitude sounding rocket launching device comprises a box body, a direction finder assembly, supporting rods and supporting legs;
the orientator assembly is connected with the box body through a support trunnion; one end of the supporting rod is connected with the supporting lug at the bottom of the box body, the other end of the supporting rod is connected with the supporting lug on the directing device assembly, the length of the supporting rod is adjustable, and the adjustment of the emitting angle of the directing device assembly is realized by adjusting the length of the supporting rod; four landing legs pass through the landing leg hub connection to the box on, the landing leg can be around the landing leg axle gyration, adjusts the support area that 4 landing legs formed through changing the gyration angle to improve launch stability.
Furthermore, universal wheels are mounted at the bottom of the box body.
Furthermore, the director component mainly comprises two brackets, a director frame, a guide rail, a support lug, a trunnion support and an ignition device. The bracket is formed by welding hollow square steel pipes, mounting holes are formed in the bracket and are fixed on two sides of the directional frame through bolts, the trunnion support is welded on the bracket on one side and is used for being connected with a support lug shaft mounted on the box body, and the support lug is welded on the bracket on the other side and is used for being connected with a support rod; the orientator frame is a square hollow frame, and the guide rail is fixed in the orientator frame; the ignition device is arranged on two sides of the guide rail.
Furthermore, the invention forms 4 rocket launching cavities according to the fact that the direction finder frame is shaped like a Chinese character 'tian', and guide rails are respectively installed in each launching cavity.
Furthermore, the inner hole of the limiting sleeve on the ignition device is a square hole and is matched with a square structure below the contact.
Furthermore, the supporting rod is of a telescopic cylindrical structure, is used for adjusting the rocket launching angle and fixing the direction finder component during rocket launching, and is used for supporting and fixing the direction finder component during transportation; mainly constitute by connector, sleeve pipe, adapter and handle, wherein the handle both ends are respectively through a connector and sleeve pipe one end threaded connection, the sheathed tube other end links to each other with the connector.
Has the advantages that:
firstly, the direction finder component is connected with the box body through the support lug, and the direction finder component and the box body are connected by adopting the length-adjustable support rod, so that the length of the support rod can be quickly adjusted during launching, and the launching angle can be quickly adjusted; can be with the length of shortening the bracing piece during the transportation, make director subassembly level, realize emitter's folding small volume when satisfying the transportation, easy operation, convenience.
Secondly, the supporting legs are connected with the box body through the supporting leg shafts, the rotatable supporting legs are adopted, and the supporting area formed by 4 supporting legs can be increased by adjusting the rotation angle, so that the launching stability is improved.
Thirdly, the anti-rotation integrated ignition device is adopted, a square hole is formed in the limiting sleeve and is matched with a square structure below the contact, the wire can be prevented from being twisted and broken in the rotation process of the contact, and the reliability of the contact is improved.
Fourthly, the box type closed structure is adopted, the appearance is neat, no redundancy exists, the protection of the direction finder can be realized, and in addition, the universal wheels are installed on the box body, so that the movement is convenient.
Drawings
FIG. 1 is a front view of the general structure of a low altitude sounding rocket launching device of the present invention;
FIG. 2 is a top view of the overall structure of the low altitude sounding rocket launching device of the present invention;
FIG. 3 is a schematic structural view of the case of the present invention;
FIG. 4 is a side view of the construction of the orienter assembly of the present invention;
FIG. 5 is a schematic view of the construction of the director assembly of the present invention;
FIG. 6 is a schematic view of the structure of the orienting frame of the present invention;
FIG. 7 is a schematic structural view of a support rod according to the present invention;
FIG. 8 is a schematic view of the ignition device of the present invention;
FIG. 9 is a schematic structural view of a leg of the present invention;
the device comprises a box body 1, a direction finder component 2, a support rod 3, a support leg 4, a cross beam 5, a support lug 6, a longitudinal beam 7, a suspension lug 8, a trunnion support 9, an upper bracket 10, a support lug 11, a direction finder frame 12, an ignition device 13, a guide rail 14, a lower bracket 15, a connector 16, a sleeve 17, an adapter 18, a handle 19, a protective cap 20, a contact 21, a connecting sleeve 22, a spring 23, an inner core 24, a protective cover 25, a limiting sleeve 26, a support foot 27, a fixing sleeve 28, a branch pipe I29 and a branch pipe II 30.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention.
As shown in figures 1-2, the invention relates to a low-altitude sounding rocket launching device, which comprises a box body 1, a direction finder component 2, a supporting rod 3 and a supporting leg 4. The box body 1 is a cuboid, a door is arranged on one side of the box body 1 in the width direction, and a lock is arranged on the door, so that the whole box body can be opened and closed; the direction finder component 2 is connected with the box body 1 through a branch trunnion; one end of the support rod 3 is connected with a support lug at the bottom of the box body 1, and the other end is connected with a support lug of a lower bracket of the orientator assembly 2, so that the emission angle is adjusted; four landing legs 4 are connected to box 1 through the landing leg axle on, and landing leg 4 can be around the landing leg axle gyration, through changing gyration angle adjustment area of contact, improves launch stability.
Referring to fig. 2, the box body 1 mainly comprises a box body frame and a skin, wherein the box body frame is formed by welding a cross beam 5, a support lug 6, a longitudinal beam 7, a hanging lug 8 and the skin. The cross beam 5 is of an angle steel structure, the longitudinal beam 7 is of a square steel tube structure, the support lug 6 is welded on the longitudinal beam 7 and is used for being connected with the support rod 3 through a pin shaft, and the hanging lug 8 is welded on the longitudinal beam 7 and is used for being connected with the support leg 4 through a pin shaft; the covering is installed on the box body frame through the screw, and the door is installed at the top of the box body, so that the door can be opened during launching, and the door is closed when the box body is not used, so that the box body is sealed.
Referring to fig. 4-6, the orienter assembly 2 is generally comprised of a trunnion mount 9, an upper bracket 10, a support ear 11, an orienter frame 12, an ignition device 13, a guide rail 14, and a lower bracket 15. The trunnion support 9 is welded on both sides of the upper bracket 10, the upper surface of the orientator frame 12 is connected to the upper bracket 10 through bolts, the lower surface of the orientator frame 12 is connected to the lower bracket 15 through bolts, the guide rail 14 is connected to the orientator frame 12 through bolts, and the ignition device 13 is of a telescopic contact structure and is connected to both sides of the guide rail, so that rocket ignition is realized.
Referring to fig. 7, the support rod 3 is mainly composed of two connectors 16, two sleeves 17, two adapters 18 and a handle 19. The sleeve 17 is a hollow cylinder, one end of the sleeve is connected with the connector 16 through welding, and the other end of the sleeve is connected with the adapter 18 through welding; the adapter 18 is a hollow cylinder, and a threaded hole is formed in the inner cavity of the adapter; the handle 19 is a solid cylindrical rod, external threads are arranged at two ends of the solid cylindrical rod and connected with an internal thread hole of the adapter 18, and the length of the supporting rod can be adjusted by rotating the handle.
Referring to fig. 8, the ignition device is a telescopic anti-rotation structure, is installed on two sides of the guide rail, and is in contact with the rocket ignition contact piece to realize rocket ignition. The ignition device 5 mainly comprises a protective cap 20, a contact 21, a connecting sleeve 22, a spring 23, an inner core 24, a protective cover 25 and a limiting sleeve 26, wherein a square hole is formed in the limiting sleeve 26 and is matched with a square structure below the contact 22, so that the contact cannot rotate, and a lead above the contact is prevented from being twisted and broken.
Referring to fig. 9, the supporting leg 4 mainly comprises a supporting leg 27, a fixing sleeve 28, a branch pipe i 29 and a branch pipe ii 30; the branch pipe I29 and the branch pipe II 30 are rectangular hollow square pipes which are connected through welding, a round hole is formed below the branch pipe II 30, and the fixing sleeve 28 is welded to the branch pipe II 30 through the round hole; the fixing sleeve 28 is a hollow cylinder with internal screw threads and is connected with the supporting legs 27, and the height of the launching device can be adjusted by adjusting the supporting legs 27.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A multi-channel foldable box-type low-altitude sounding rocket launching device is characterized by comprising a box body (1), a direction finder component (2), a supporting rod (3) and supporting legs (4);
the direction finder component (1) is connected with the box body (1) through a support trunnion; one end of the supporting rod (3) is connected with a supporting lug at the bottom of the box body (1), the other end of the supporting rod is connected with a supporting lug on the direction finder component (2), and the length of the supporting rod (3) is adjustable; the four supporting legs (4) are connected to the box body (1) through supporting leg shafts, and the supporting legs (4) can rotate around the supporting leg shafts;
the direction finder component (2) mainly comprises two brackets (10,15), a direction finder frame (12), a guide rail (14), a trunnion support (9), a support lug (11) and an ignition device (13); the brackets (10,15) are formed by welding hollow square steel pipes, mounting holes are formed in the brackets and are fixed to two sides of the orientation frame (12) through bolts, the trunnion support (9) is welded on the bracket (10) on one side and is used for being connected with a trunnion shaft mounted on the box body (1), and the support lug (11) is welded on the bracket (15) on the other side and is used for being connected with the support rod (3); the guide rail (14) is fixed in the orientation frame (12), and the ignition device (13) is arranged on two sides of the guide rail (14).
2. The multi-channel foldable box-type low-altitude sounding rocket launcher according to claim 1, characterized in that 4 rocket launching cavities are formed according to the shape of the director frame (12), and each rocket launching cavity is internally provided with a guide rail.
3. The multi-channel foldable box-type low-altitude sounding rocket launcher according to claim 1 is characterized in that universal wheels are installed at the bottom of the box body (1).
4. A multi-channel collapsible box-type low altitude sounding rocket launcher according to claim 1 characterized in that the limiting sleeve (26) on said ignition device (13) has a square hole inside it, cooperating with a square structure under the contact (21).
5. The multi-channel foldable box-type low-altitude sounding rocket launcher according to claim 1 is characterized by comprising a connector (16), a sleeve (17), a connector (18) and a handle (19), wherein two ends of the handle (19) are respectively in threaded connection with one end of the sleeve (17) through the connector (16), and the other end of the sleeve (17) is connected with the connector (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010400650.0A CN111547266A (en) | 2020-05-13 | 2020-05-13 | Multi-channel foldable box-type low-altitude sounding rocket launching device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010400650.0A CN111547266A (en) | 2020-05-13 | 2020-05-13 | Multi-channel foldable box-type low-altitude sounding rocket launching device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111547266A true CN111547266A (en) | 2020-08-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010400650.0A Pending CN111547266A (en) | 2020-05-13 | 2020-05-13 | Multi-channel foldable box-type low-altitude sounding rocket launching device |
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| CN (1) | CN111547266A (en) |
Citations (14)
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|---|---|---|---|---|
| US3710677A (en) * | 1968-12-19 | 1973-01-16 | Oerlikon Buehrle Ag | Rocket projector magazines |
| CN2316624Y (en) * | 1998-03-11 | 1999-04-28 | 中国航天工业总公司第四研究院第四十一研究所 | Rocket launching apparatus for increasing rain and preventing hailstone |
| CN201016649Y (en) * | 2006-10-23 | 2008-02-06 | 新疆维吾尔自治区人工影响天气办公室 | Multifunctional artificial hail-proof rain-increasing rocket pod and emission controller thereof |
| CN101240992A (en) * | 2008-02-15 | 2008-08-13 | 陈延文 | Fixed range pressure-dividing controllable fireworks burning device and its method |
| DE102008019666A1 (en) * | 2008-04-18 | 2009-10-22 | Alexander Rubinraut | Spaceship for flight to mars, has analog engines and rocket launch complex system for launching of rocket from earth and running into orbit and for flight from earth orbit to mars orbit |
| CN101983306A (en) * | 2008-02-04 | 2011-03-02 | Bsh博施及西门子家用器具有限公司 | Gas hob and gas burner for a gas hob of this type |
| CN204854478U (en) * | 2015-05-13 | 2015-12-09 | 郑德杨 | Rocket projectile emitter based on campus space flight science popularization experiment |
| CN205854533U (en) * | 2016-08-10 | 2017-01-04 | 尹鸿俊 | A kind of unmanned aerial vehicle ejecting supports case |
| CN206112994U (en) * | 2016-10-09 | 2017-04-19 | 刘舜楠 | Piezo electric ignition ware |
| CN207611690U (en) * | 2017-10-30 | 2018-07-13 | 辽沈工业集团有限公司 | A kind of switching device in the case of high overload |
| CN207816096U (en) * | 2017-12-06 | 2018-09-04 | 新疆维吾尔自治区人工影响天气办公室 | Integrated form hail-proof rain-increasing rocket launching igniting contact assembly |
| CN110030875A (en) * | 2019-04-18 | 2019-07-19 | 永卓防务科技有限公司 | A kind of launcher |
| CN209263792U (en) * | 2018-09-07 | 2019-08-16 | 陕西中天火箭技术股份有限公司 | A kind of rocket scattering finder |
| CN111055984A (en) * | 2020-01-09 | 2020-04-24 | 新余国科特种装备有限公司 | Rocket launcher for ships |
-
2020
- 2020-05-13 CN CN202010400650.0A patent/CN111547266A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3710677A (en) * | 1968-12-19 | 1973-01-16 | Oerlikon Buehrle Ag | Rocket projector magazines |
| CN2316624Y (en) * | 1998-03-11 | 1999-04-28 | 中国航天工业总公司第四研究院第四十一研究所 | Rocket launching apparatus for increasing rain and preventing hailstone |
| CN201016649Y (en) * | 2006-10-23 | 2008-02-06 | 新疆维吾尔自治区人工影响天气办公室 | Multifunctional artificial hail-proof rain-increasing rocket pod and emission controller thereof |
| CN101983306A (en) * | 2008-02-04 | 2011-03-02 | Bsh博施及西门子家用器具有限公司 | Gas hob and gas burner for a gas hob of this type |
| CN101240992A (en) * | 2008-02-15 | 2008-08-13 | 陈延文 | Fixed range pressure-dividing controllable fireworks burning device and its method |
| DE102008019666A1 (en) * | 2008-04-18 | 2009-10-22 | Alexander Rubinraut | Spaceship for flight to mars, has analog engines and rocket launch complex system for launching of rocket from earth and running into orbit and for flight from earth orbit to mars orbit |
| CN204854478U (en) * | 2015-05-13 | 2015-12-09 | 郑德杨 | Rocket projectile emitter based on campus space flight science popularization experiment |
| CN205854533U (en) * | 2016-08-10 | 2017-01-04 | 尹鸿俊 | A kind of unmanned aerial vehicle ejecting supports case |
| CN206112994U (en) * | 2016-10-09 | 2017-04-19 | 刘舜楠 | Piezo electric ignition ware |
| CN207611690U (en) * | 2017-10-30 | 2018-07-13 | 辽沈工业集团有限公司 | A kind of switching device in the case of high overload |
| CN207816096U (en) * | 2017-12-06 | 2018-09-04 | 新疆维吾尔自治区人工影响天气办公室 | Integrated form hail-proof rain-increasing rocket launching igniting contact assembly |
| CN209263792U (en) * | 2018-09-07 | 2019-08-16 | 陕西中天火箭技术股份有限公司 | A kind of rocket scattering finder |
| CN110030875A (en) * | 2019-04-18 | 2019-07-19 | 永卓防务科技有限公司 | A kind of launcher |
| CN111055984A (en) * | 2020-01-09 | 2020-04-24 | 新余国科特种装备有限公司 | Rocket launcher for ships |
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Application publication date: 20200818 |