CN112284194B - Missile attitude adjusting device based on high-speed airflow blowing - Google Patents
Missile attitude adjusting device based on high-speed airflow blowing Download PDFInfo
- Publication number
- CN112284194B CN112284194B CN201910663972.1A CN201910663972A CN112284194B CN 112284194 B CN112284194 B CN 112284194B CN 201910663972 A CN201910663972 A CN 201910663972A CN 112284194 B CN112284194 B CN 112284194B
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- Prior art keywords
- angle
- sideslip
- attack angle
- adjusting
- test piece
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- 238000007664 blowing Methods 0.000 title claims abstract description 18
- 238000009434 installation Methods 0.000 claims description 7
- 230000036544 posture Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a missile attitude adjusting device based on high-speed airflow blowing, wherein a test piece mounting platform is used for mounting a test piece and is fixedly connected with an attack angle adjusting mechanism, the attack angle adjusting mechanism is fixed on a sideslip angle adjusting mechanism, and a rear height adjusting device enables the rear side of the test piece mounting platform to be lifted along a rear support guide groove through stepless telescopic length adjustment of a sliding bolt, so that the attack angle of the test piece mounting platform is adjusted, the upper side of the sideslip angle adjusting mechanism is connected with the attack angle adjusting mechanism, the lower side of the test piece mounting platform is connected with test piece bottom plate equipment, one end of the sideslip angle adjusting mechanism is fixed through the bolt, and the other end of the sideslip angle adjusting mechanism moves in the bottom plate equipment guide groove, and the lateral sliding of the test piece is realized. The invention not only can realize the adjustment of the attack angle of the test piece mounting platform, but also can realize the adjustment of the sideslip angle of the test piece mounting platform, has simple structure and convenient operation, and can meet the requirement of quickly adjusting the posture of the missile under the blowing of high-speed airflow.
Description
Technical Field
The invention particularly relates to a missile attitude adjusting device based on high-speed airflow blowing.
Background
When the missile performs high-speed air flow blowing tests, the high-speed air flow blowing tests are required to be performed on the missile under different postures, so that the regulation and fixation of different postures of the missile are required to be rapidly realized by using a posture regulating device with good strength and rigidity. At present, the existing high-speed air flow blowing test platform is a single fixing frame, the missile attitude is converted and the position is adjusted, and the change of the attitude of the missile relative to the air flow direction is adjusted by reloading and even different tools. For products with multi-gesture adjustment requirements, test pieces need to be assembled and disassembled for many times, and the connecting tool is complex and heavy, so that the problems of convenience in use, efficiency reduction and the like can be brought.
Disclosure of Invention
Technical problems: the invention mainly solves the technical problem of providing the missile attitude adjusting device based on high-speed airflow blowing, which not only can realize the rapid adjustment of the attack angle of the missile in a high-speed airflow blowing test, but also can test the rapid adjustment of the sideslip angle of the missile.
The technical scheme is as follows: missile attitude adjusting device based on high-speed air current blows down, its characterized in that: the adjusting device comprises a test piece mounting platform, an attack angle adjusting mechanism, a sideslip angle adjusting mechanism and bottom plate equipment, wherein the attack angle adjusting mechanism comprises a front attack angle bracket, a rear attack angle guiding device, a height adjusting device, an attack angle rotating shaft and an attack angle locking shaft. One end of the front attack angle bracket 2 and one end of the rear attack angle guiding device are fixed at the lower end of the test piece mounting platform, the other end of the front attack angle bracket is movably connected with the front sideslip bracket through an attack angle rotating shaft, the test piece mounting platform can rotate around the attack angle rotating shaft, and the other end of the rear attack angle guiding device is connected with the rear sideslip guiding bracket through an attack angle locking shaft; the height adjusting device consists of a sliding screw, one end of the height adjusting device is connected with the test piece mounting platform, the other end of the height adjusting device is connected with the sideslip angle adjusting bottom plate, the height adjusting device can rotate forward and backward, and the elongation of the sliding rod is changed through stepless adjustment, so that the rear attack angle guiding device moves on the rear sideslip guiding support, and after the rear attack angle guiding device is adjusted to a proper attack angle, the rear attack angle guiding device is locked by an attack angle locking shaft, so that the adjustment of the attack angle of the test piece mounting platform is realized;
The side slip angle adjusting mechanism comprises a front side slip support, a rear side slip guide support, a side slip angle adjusting bottom plate, a side slip locking shaft and a side slip rotating shaft, wherein the front side slip support and the rear side slip guide support are fixed on the side slip angle adjusting bottom plate, one end of the side slip angle adjusting bottom plate is fixed through the side slip rotating shaft, the other end of the side slip angle adjusting bottom plate is provided with a guide groove and can rotate around the side slip rotating shaft, and the side slip angle adjusting mechanism is fixed on a side slip angle locking hole of bottom plate equipment through the side slip locking shaft after being adjusted to a proper position, so that the side slip angle of a test piece installation platform is integrally adjusted.
In the scheme, the whole set of gesture adjusting device can be fixed on other mounting equipment through different interfaces by the base plate equipment and is used for mounting test pieces.
In the above scheme, the rear attack angle guide device is provided with a first distance-adjusting long hole along the height direction.
In the above scheme, the rear sideslip guide bracket is provided with a second distance-adjusting long hole along the height direction.
In the scheme, the first distance-adjusting long hole and the second distance-adjusting long hole are coaxial.
In the scheme, the lengths of the first distance-adjusting long hole and the second distance-adjusting long hole are matched with the maximum height of the height adjusting device.
In the scheme, the front attack angle bracket is provided with the first mounting hole, the front sideslip bracket is provided with the second mounting hole, and the first mounting hole and the second mounting hole are coaxial when overlapped.
In the scheme, the guide groove on the sideslip angle adjusting bottom plate is coaxial with the sideslip angle rotating shaft hole.
In the above scheme, the distance of the guide groove is determined according to the sideslip angle adjustment requirement degree required by the test.
In the scheme, the sideslip angle locking hole on the bottom plate device moves along the guide groove.
The invention has the following beneficial effects: the invention adopts a step-by-step adjustment method to realize the adjustment of the attack angle and sideslip angle posture of the test piece. Firstly, a test piece is mounted on a test piece mounting platform, and the attack angle adjusting mechanism utilizes the lifting adjustment of a height adjusting device to enable a rear attack angle guiding device to be subjected to height adjustment in a certain range, so that the test piece mounting platform rotates around an attack angle rotating shaft to realize the attack angle adjustment of the test piece mounting platform; the utility model provides an angle adjustment mechanism that sideslips, sideslips rotation axis is fixed through sideslip rotation axis one end, and the other end is opened there is the guide way to can rotate around the rotation axis that sideslips, be fixed in on the bottom plate equipment through sideslip locking axle after adjusting suitable position, wholly realize the adjustment of test piece mounting platform sideslip angle, its simple structure, convenient operation can satisfy the demand of test piece to the adjustment of attack angle and sideslip angle.
Drawings
The invention will be further described with reference to the accompanying drawings and examples, in which:
FIG. 1 is a schematic diagram of the structural assembly of an embodiment of the present invention;
FIG. 2 is a schematic exploded view of the structure of an embodiment of the present invention;
FIG. 3 is a schematic view of the angle of attack adjustment mechanism of the present invention;
FIG. 4 is a schematic diagram of the structure of the slip angle adjusting mechanism of the present invention;
Fig. 5 is a schematic view of the structure of the base plate apparatus of the present invention.
Wherein: the device comprises a 1-test piece mounting platform, a 2-front attack angle bracket, a 3-rear attack angle guiding device, a 4-height adjusting device, a 5-attack angle rotating shaft, a 6-front sideslip bracket, a 7-attack angle locking shaft, an 8-rear sideslip guiding bracket, a 9-sideslip angle adjusting bottom plate, a 10-sideslip locking shaft, an 11-sideslip rotating shaft, a 12-bottom plate device, a 13-guiding groove, a 14-first distance adjusting long hole, a 15-second distance adjusting long hole, a 16-mounting hole I, a 17-mounting hole II, a 18-sideslip angle locking hole, a 19-sideslip angle rotating shaft hole and a 20-bottom plate locking hole.
Detailed Description
The present invention will be described in further detail with reference to the drawings and the embodiments, in order to make the objects, technical solutions and advantages of the present invention more apparent.
Referring to fig. 1 to 5, the missile attitude adjusting device based on high-speed airflow blowing comprises a test piece mounting platform 1, an attack angle adjusting mechanism, a sideslip angle adjusting mechanism and a base plate device 12.
In this embodiment, the test piece mounting platform 1 is used for mounting a test piece, and the lower surface of the test piece mounting platform is connected with the front attack angle bracket 2 and the rear attack angle guiding device 3.
The attack angle adjusting mechanism comprises a front attack angle bracket 2, a rear attack angle guiding device 3, a height adjusting device 4, an attack angle rotating shaft 5 and an attack angle locking shaft 7. One end of the front attack angle bracket 2 and one end of the rear attack angle guiding device 3 are fixed at the lower end of the test piece mounting platform 1, the other end of the front attack angle bracket 2 is movably connected with the front sideslip bracket 6 through a first mounting hole 16 and a second mounting hole 17 by an attack angle rotating shaft 5, and the test piece mounting platform 1 can rotate around the attack angle rotating shaft 5; the other end of the rear attack angle guide device 3 moves along the first distance-adjusting long hole 14 through the attack angle locking shaft 7, is connected with the rear sideslip guide bracket 8, and can move in the second distance-adjusting long hole 15; the height adjusting device 4 consists of a sliding screw, one end of the height adjusting device is connected with the test piece mounting platform 1, the other end of the height adjusting device is connected with the sideslip angle adjusting bottom plate 9, the height adjusting device 4 can rotate forward and backward, the elongation of the sliding rod is changed through stepless adjustment, the rear attack angle guiding device 3 moves on the rear sideslip guiding support 8, and after the rear attack angle is adjusted to a proper attack angle, the rear attack angle guiding device is locked by the attack angle locking shaft 7, so that the attack angle of the test piece mounting platform is adjusted.
The sideslip angle adjusting mechanism comprises a front sideslip support 6, a rear sideslip guide support 8, a sideslip angle adjusting bottom plate 9, a sideslip locking shaft 10 and a sideslip rotating shaft 11. The front side sliding support 6 and the rear side sliding guide support 8 are fixed on the side sliding angle adjusting bottom plate 9, one end of the side sliding angle adjusting bottom plate 9 is fixed through the side sliding rotary shaft 11, the other end of the side sliding angle adjusting bottom plate 9 is provided with the guide groove 13 and can rotate around the side sliding angle rotary shaft hole 19, and when the side sliding angle adjusting bottom plate is adjusted to a proper position, the side sliding angle adjusting bottom plate is fixed on the side sliding angle locking hole 18 of the bottom plate device 12 through the side sliding locking shaft 10, and the adjustment of the side sliding angle of the test piece installation platform is integrally realized.
The invention adopts a step-by-step adjustment method, firstly, a test piece is arranged on a test piece mounting platform, the attack angle adjusting mechanism utilizes the lifting adjustment of a height adjusting device to enable a rear attack angle guiding device to carry out height adjustment within a certain range, so that the test piece mounting platform rotates around an attack angle rotating shaft, and when the attack angle is adjusted to a required attack angle position, the height adjusting device and the attack angle guiding device are locked at the same time, thereby realizing the attack angle adjustment of the test piece mounting platform; the utility model provides an angle adjustment mechanism that sideslips, sideslips rotation axis is fixed through sideslip rotation axis one end, and the other end is opened there is the guide way to can rotate around the rotation axis that sideslips, be fixed in on the bottom plate equipment through sideslip locking axle after adjusting suitable position, wholly realize the adjustment of test piece mounting platform sideslip angle, its simple structure, convenient operation can satisfy the demand of test piece to the adjustment of attack angle and sideslip angle. Therefore, the missile attitude adjusting device based on high-speed airflow blowing can conveniently and rapidly adjust the attack angle and sideslip angle of the test piece within a certain range.
The embodiments of the present invention have been described above with reference to the accompanying drawings, but the present invention is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those having ordinary skill in the art without departing from the spirit of the present invention and the scope of the claims, which are to be protected by the present invention.
Claims (8)
1. Missile attitude adjusting device based on high-speed air current blows down, its characterized in that: the adjusting device comprises a test piece mounting platform (1), an attack angle adjusting mechanism, a sideslip angle adjusting mechanism and a bottom plate device (12),
The attack angle adjusting mechanism comprises a front attack angle bracket (2), a rear attack angle guiding device (3), a height adjusting device (4), an attack angle rotating shaft (5) and an attack angle locking shaft (7), wherein one ends of the front attack angle bracket (2) and the rear attack angle guiding device (3) are fixed at the lower end of a test piece mounting platform (1), the other ends of the front attack angle bracket (2) are movably connected with a front sideslip bracket (6) through the attack angle rotating shaft (5), the test piece mounting platform (1) can rotate around the attack angle rotating shaft (5), and the other ends of the rear attack angle guiding device (3) are connected with a rear sideslip guiding bracket (8) through the attack angle locking shaft (7); the height adjusting device (4) consists of a sliding screw, one end of the height adjusting device is connected with the test piece mounting platform (1), the other end of the height adjusting device is connected with the sideslip angle adjusting bottom plate (9), the height adjusting device (4) can rotate forward and backward, the elongation of the sliding rod is changed through stepless adjustment, the rear attack angle guiding device (3) moves on the rear sideslip guiding support (8), and after the rear attack angle is adjusted to a proper attack angle, the rear attack angle guiding device is locked by the attack angle locking shaft (7), so that the adjustment of the attack angle of the test piece mounting platform is realized;
the sideslip angle adjusting mechanism comprises a front sideslip support (6), a rear sideslip guide support (8), a sideslip angle adjusting bottom plate (9), a sideslip locking shaft (10) and a sideslip rotating shaft (11), wherein a first installation hole (16) is formed in the front attack angle support (2), a second installation hole (17) is formed in the front sideslip support (6), and the first installation hole (16) and the second installation hole (17) are coaxial when overlapped; the guide groove (13) on the sideslip angle adjusting bottom plate (9) is coaxial with the sideslip angle rotating shaft hole (19); the front side sliding support (6) and the rear side sliding guide support (8) are fixed on the side sliding angle adjusting bottom plate (9), one end of the side sliding angle adjusting bottom plate (9) is fixed through the side sliding rotary shaft (11), the other end of the side sliding angle adjusting bottom plate is provided with the guide groove (13) and can rotate around the side sliding rotary shaft (11), and after the side sliding angle adjusting bottom plate is adjusted to a proper position, the side sliding angle adjusting bottom plate is fixed on the side sliding angle locking hole (18) of the bottom plate equipment (12) through the side sliding locking shaft (10), so that the adjustment of the side sliding angle of the test piece installation platform is integrally realized.
2. The missile attitude adjusting device based on high-speed airflow blowing according to claim 1, wherein: the bottom plate equipment (12) can fix the whole set of posture adjusting device on equipment to be installed through different interfaces for installing test pieces.
3. The missile attitude adjusting device based on high-speed airflow blowing according to claim 1, wherein: the rear attack angle guide device (3) is provided with a first distance-adjusting long hole (14) along the height direction.
4. A missile attitude adjustment device based on high velocity airflow attack as claimed in claim 3, wherein: the rear sideslip guide bracket (8) is provided with a second distance-adjusting long hole (15) along the height direction.
5. The missile attitude adjusting device based on high-speed airflow blowing according to claim 4, wherein: the first distance-adjusting long hole (14) and the second distance-adjusting long hole (15) are coaxial.
6. The missile attitude adjusting device based on high-speed airflow blowing according to claim 5, wherein: the lengths of the first distance-adjusting long hole (14) and the second distance-adjusting long hole (15) are matched with the maximum height of the height adjusting device (4).
7. The missile attitude adjusting device based on high-speed airflow blowing according to claim 1, wherein: the distance of the guide groove (13) is determined according to the sideslip angle adjustment requirement degree required by the test.
8. The missile attitude adjusting device based on high-speed airflow blowing according to claim 1, wherein: the side slip angle locking hole (18) on the base plate device (12) moves along the guide groove (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910663972.1A CN112284194B (en) | 2019-07-22 | 2019-07-22 | Missile attitude adjusting device based on high-speed airflow blowing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910663972.1A CN112284194B (en) | 2019-07-22 | 2019-07-22 | Missile attitude adjusting device based on high-speed airflow blowing |
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| Publication Number | Publication Date |
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| CN112284194A CN112284194A (en) | 2021-01-29 |
| CN112284194B true CN112284194B (en) | 2024-05-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910663972.1A Active CN112284194B (en) | 2019-07-22 | 2019-07-22 | Missile attitude adjusting device based on high-speed airflow blowing |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11108592A (en) * | 1997-10-02 | 1999-04-23 | Mitsubishi Electric Corp | Missile guide device |
| CN103076152A (en) * | 2012-12-31 | 2013-05-01 | 中国人民解放军国防科学技术大学 | Gesture adjusting device for model with four degrees of freedom for hypersonic speed pulse wind tunnel |
| JP2014126355A (en) * | 2012-12-27 | 2014-07-07 | Mitsubishi Heavy Ind Ltd | Missile guide system and missile guide method |
| CN106871748A (en) * | 2017-01-11 | 2017-06-20 | 北京理工大学 | For testing the turntable that missile wing launches under body multi-angle high rotational speeds |
| CN210892882U (en) * | 2019-07-22 | 2020-06-30 | 航宇救生装备有限公司 | Missile attitude adjusting device based on high-speed airflow blowing |
-
2019
- 2019-07-22 CN CN201910663972.1A patent/CN112284194B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11108592A (en) * | 1997-10-02 | 1999-04-23 | Mitsubishi Electric Corp | Missile guide device |
| JP2014126355A (en) * | 2012-12-27 | 2014-07-07 | Mitsubishi Heavy Ind Ltd | Missile guide system and missile guide method |
| CN103076152A (en) * | 2012-12-31 | 2013-05-01 | 中国人民解放军国防科学技术大学 | Gesture adjusting device for model with four degrees of freedom for hypersonic speed pulse wind tunnel |
| CN106871748A (en) * | 2017-01-11 | 2017-06-20 | 北京理工大学 | For testing the turntable that missile wing launches under body multi-angle high rotational speeds |
| CN210892882U (en) * | 2019-07-22 | 2020-06-30 | 航宇救生装备有限公司 | Missile attitude adjusting device based on high-speed airflow blowing |
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|---|---|
| CN112284194A (en) | 2021-01-29 |
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