CN109595986A - A kind of missile launch test device - Google Patents
A kind of missile launch test device Download PDFInfo
- Publication number
- CN109595986A CN109595986A CN201811525057.8A CN201811525057A CN109595986A CN 109595986 A CN109595986 A CN 109595986A CN 201811525057 A CN201811525057 A CN 201811525057A CN 109595986 A CN109595986 A CN 109595986A
- Authority
- CN
- China
- Prior art keywords
- column
- regulating device
- missile launch
- test device
- launch test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G5/00—Elevating or traversing control systems for guns
- F41G5/26—Apparatus for testing or checking
Abstract
The invention discloses a kind of missile launch test devices; including pedestal (1) and column (3); column (3) is mounted on pedestal (1); side mounting base chair (4) in the middle part of column (3); column (3) is structure as a whole with position regulating device (5); top connects pitching regulating device (6); pitching regulating device (6) installed in front protects baffle (7), top mounting cylinder bullet mounting rack (8).Present invention emitter folding storage in no flight test mission is unfolded to use on test site when having test mission, adapts to high and low temperature environment and wind sand environment in packing case.
Description
Technical field
The invention belongs to tactical missile testing fields, especially suitable for transmitting examination of the portable missile under complex environment
It tests.
Background technique
Tactics type of missile weapon can carry out routine flying target during development and production has a try and tests, to verify guided missile force
The killing ability of device.Emitter is the ancillary equipment of MISSILE LAUNCHING, and specific effect is to support and fix single-shot guided missile, operation
Guided missile is adjusted to required angle and positive lock by the hand according to target angle of site of direction of motion traverser and azimuth,
Guarantee that guided missile can smoothly emit according to the predetermined angle of departure.
Summary of the invention
It can the technical problem to be solved by the present invention is providing a kind of height orientation angles that can be used for Missile Experiment
The emitter of tune is had a try with to meet missile flight target and tests demand.
The technical scheme is that
A kind of missile launch test device, including pedestal and column, column are mounted on the base, side peace in the middle part of column
Seat is filled, column is internally integrated position regulating device, and top connects pitching regulating device, the protection of pitching regulating device installed in front
Baffle, top mounting cylinder bullet mounting rack.
Pedestal includes three supporting legs and cover board, and three supporting leg hinges are mounted in column lower end, and cover board is mounted on three by bolt
The upper surface of supporting leg.
Leg ends are equipped with spiral regulating device.
Position regulating device includes roller bearing, inside and outside sleeve, clamping screw, and inside and outside sleeve, which is integrated in column, passes through axis
It forwards dynamic；Clamping screw is to tense two closing pieces by threaded rod, holds inner sleeve tightly and realizes position locking.
Pitching regulating device includes roller bearing, inside and outside sleeve, clamping screw, and inside and outside sleeve is rotated by bearing；Locking
Bolt is to tense two closing pieces by threaded rod, holds inner sleeve tightly and realizes position locking, the inside and outside sleeve of pitching regulating device is logical
Connection structure is crossed to be horizontally arranged above column.
Seat is made of stool, housing tube stent and clip, and seat bottom is screwed by adjusting bolt with housing tube stent
Fixed, height of seat adjusts bolt by rotation and is adjusted, and housing tube stent is by locked clip device on column.
Cylinder bullet mounting rack is buckled by two cylinder latches and mounting seat forms, and cylinder latch, which is buckled, is fixed to mounting seat by screw
On, mounting seat is connected with pitching regulating device.
Cylinder latch button designs for multi-link structure, has self-locking function, moves handle upwards, hook is disengaged, two side pressures
Plate is automatically separated, and can remove cylinder bullet.
Protection baffle is made of transparent organic glass and steel pipe skeleton.
Beneficial effects of the present invention: in no flight test mission, emitter folding storage is in packing case.There is examination
It is unfolded to use on test site when testing task, adapts to high and low temperature environment and wind sand environment.Manipulator sits to be passed through on the seat
Rotation of the handle to direction adjusting apparatus and dipping control realizes the adjustment being directed toward to guided missile, to reach requirement.
Detailed description of the invention:
Fig. 1 is emitter schematic diagram；
Fig. 2 is base schematic diagram；
Fig. 3 is supporting leg schematic diagram；
Fig. 4 is inner sleeve schematic diagram；
Fig. 5 is outer sleeve schematic diagram；
Fig. 6 is position regulating device schematic diagram；
Fig. 7 is outer sleeve support schematic diagram；
Fig. 8 is seat schematic diagram；
Fig. 9 is cylinder bullet mounting rack schematic diagram；
Figure 10 is that cylinder latch buckles schematic diagram；
Figure 11 is protection baffle schematic diagram.
Specific embodiment
Embodiment 1:
Emitter as shown in Figure 1 is by pedestal 1, column 3 (containing position regulating device 5), detachable seat 4, pitch regulation
The compositions such as device 6, cylinder bullet mounting rack 8, launcher protection baffle 7.Manipulator sits on the seat to adjust direction by handle and fill
The rotation with dipping control is set, the adjustment being directed toward to guided missile is realized, to reach requirement.
Pedestal 1 is made of three supporting legs (Fig. 3) and circular cover (Fig. 2), has spiral regulating device 2 on three supporting legs,
By the level for adjusting the adjustable emitter of height of three supporting leg supporting points.Remove the time receiving, remove cover board and supporting leg with
Supporting leg can be folded up after 2 mounting screws between column.
It is as shown in Figure 4 and Figure 5 inner sleeve and outer sleeve, the two general assembly is at column 3.Column 3 is the rotating shaft of seat 4,
The upper end of column 3 is equipped with miniature level meter, can be observed to the levelness of device, and the bottom of column 3 connects pedestal, middle part
Equipped with seat 4, top connects pitching regulating device 6.
Position regulating device 5 as shown in Figure 6 is mainly by dial (1), fastening ring (2), nut ring (3), roller bearing (4)
Deng composition, inside and outside sleeve is rotated by roller bearing, and top is equipped with dial, realizes that angle-data is read, position regulating device 5
Adjusting range be 0 °~360 ° and can be in any angle manual locking.
Pitching regulating device 6, principle is consistent with position regulating device but it is to be horizontally mounted.It is adjusted in pitch angle
Extreme position is provided with limited block, meets -5 °~+60 ° ranges of elevation coverage.
It is illustrated in figure 7 the housing tube stent of seat 4, top is the screw shell (1) installed with stool；
It is illustrated in figure 8 the stool of seat 4, stool surface panel beating forms, and backrest is welded using steel pipe bending, lower section
Equipped with height adjustment screw thread.For seat 4 entirely through locked clip device on column 3, the fixed position of clip avoids spending leg folding position
It sets, removes the time receiving and back out stool.
It is cylinder bullet mounting rack 8 as shown in Figure 9, buckles (Figure 10) by two cylinder latches and mounting seat (1) forms, mounting seat
It is the installation support of a latch button (Figure 10), there is 7 ° of correction angle due to the force of gravity by cylinder bullet requirement design.Cylinder latch button (Figure 10) passes through spiral shell
Nail is fixed on mounting seat (1).
It is that a latch button designs for multi-link structure as shown in Figure 10, there is self-locking function, move handle upwards, will link up with
It disengages, two side plates are automatically separated, can remove cylinder bullet.
It is protection baffle 7 as shown in figure 11, it is fixed using high-strength transparence organic glass (2), steel pipe skeleton (1), with cylinder
Playing the direction of the launch is in 90 ° of angles, plays protective action.Manipulator can observe run-home by protection baffle, and pass through handle
Adjust orientation, pitch angle.
Claims (8)
1. a kind of missile launch test device, including pedestal (1) and column (3), it is characterised in that: column (3) is mounted on bottom
On seat (1), side mounting base chair (4), column (3) are internally integrated position regulating device (5) in the middle part of column (3), and top connection is bowed
It faces upward regulating device (6), pitching regulating device (6) installed in front protects baffle (7), top mounting cylinder bullet mounting rack (8).
2. missile launch test device according to claim 1, it is characterised in that: pedestal (1) includes supporting leg and cover board,
Pedestal (1) hinge is mounted in column (3) lower end, and cover board is mounted on the upper surface of supporting leg by bolt.
3. missile launch test device according to claim 2, it is characterised in that: pedestal (1) end is equipped with spiral
Regulating device (2).
4. missile launch test device according to claim 1, it is characterised in that: column (3) and position regulating device
(5) it is an integral structure, position regulating device (5) includes roller bearing, inside and outside sleeve, clamping screw, and inside and outside sleeve is mounted to
Column (3) is rotated by bearing；Clamping screw is to tense two closing pieces by threaded rod, holds inner sleeve tightly and realizes position locking.
5. missile launch test device according to claim 1, it is characterised in that: pitching regulating device (6) includes rolling
Sub- bearing, inside and outside sleeve, clamping screw, inside and outside sleeve are rotated by bearing；Clamping screw is that two locks are tensed by threaded rod
Block holds inner sleeve tightly and realizes position locking, and the inside and outside sleeve of pitching regulating device (6) is horizontally arranged at column by connection structure
(3) top.
6. missile launch test device according to claim 1, it is characterised in that: seat (4) is by stool, outer sleeve branch
Frame and clip composition, stool bottom are tightened by bolt and outer sleeve, and height of seat is adjusted by height adjustment screw thread
Whole, outer sleeve is by locked clip device on column (3).
7. missile launch test device according to claim 1, it is characterised in that: cylinder bullet mounting rack (8) is by two cylinders
Latch button and mounting seat composition, cylinder latch is buckled to be fixed in mounting seat by screw, mounting seat and pitching regulating device
(6) it connects.
8. missile launch test device according to claim 1, it is characterised in that: protection baffle (7) is by transparent organic
Glass and steel pipe skeleton composition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811525057.8A CN109595986A (en) | 2018-12-13 | 2018-12-13 | A kind of missile launch test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811525057.8A CN109595986A (en) | 2018-12-13 | 2018-12-13 | A kind of missile launch test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109595986A true CN109595986A (en) | 2019-04-09 |
Family
ID=65961849
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811525057.8A Pending CN109595986A (en) | 2018-12-13 | 2018-12-13 | A kind of missile launch test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109595986A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2437381Y (en) * | 2000-08-22 | 2001-07-04 | 徐作吉 | Amusement air gun |
| CN102338594A (en) * | 2011-09-28 | 2012-02-01 | 北京机械设备研究所 | Portable two-degree-of-freedom balanced casting device |
| CN203550783U (en) * | 2013-11-01 | 2014-04-16 | 西安天伟电子系统工程有限公司 | Portable dual-mounted missile launcher |
| CN204388707U (en) * | 2014-12-23 | 2015-06-10 | 西安电子工程研究所 | A kind of for ramp-launched MISSILE LAUNCHING shelf structure |
| CN206479091U (en) * | 2017-01-20 | 2017-09-08 | 中国航天科工集团上海浦东开发中心 | A kind of portable a variety of MISSILE LAUNCHING hunting gears |
-
2018
- 2018-12-13 CN CN201811525057.8A patent/CN109595986A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2437381Y (en) * | 2000-08-22 | 2001-07-04 | 徐作吉 | Amusement air gun |
| CN102338594A (en) * | 2011-09-28 | 2012-02-01 | 北京机械设备研究所 | Portable two-degree-of-freedom balanced casting device |
| CN203550783U (en) * | 2013-11-01 | 2014-04-16 | 西安天伟电子系统工程有限公司 | Portable dual-mounted missile launcher |
| CN204388707U (en) * | 2014-12-23 | 2015-06-10 | 西安电子工程研究所 | A kind of for ramp-launched MISSILE LAUNCHING shelf structure |
| CN206479091U (en) * | 2017-01-20 | 2017-09-08 | 中国航天科工集团上海浦东开发中心 | A kind of portable a variety of MISSILE LAUNCHING hunting gears |
Non-Patent Citations (1)
| Title |
|---|
| 王大欢: ""便携式导弹发控测试设备的研制"", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190409 |
|
| RJ01 | Rejection of invention patent application after publication |