CN111948611A - Fixing mechanism of aviation radar - Google Patents
Fixing mechanism of aviation radar Download PDFInfo
- Publication number
- CN111948611A CN111948611A CN202010814329.7A CN202010814329A CN111948611A CN 111948611 A CN111948611 A CN 111948611A CN 202010814329 A CN202010814329 A CN 202010814329A CN 111948611 A CN111948611 A CN 111948611A
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- CN
- China
- Prior art keywords
- radar
- radar body
- clamping jaw
- positioning block
- fixing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/93—Radar or analogous systems specially adapted for specific applications for anti-collision purposes
- G01S13/933—Radar or analogous systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electromagnetism (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention relates to a fixing mechanism of an aviation radar, belonging to the technical field of aviation radars; comprises a fixing device and a mounting frame; the fixing device is used for fixing the radar body and is arranged above the installation frame; the fixing device comprises a connecting frame, a vertical plate, a clamping jaw, a rotating wheel, a transmission rod, a positioning block and a torsion spring; placing a base of the radar body on the inner bottom surface of the connecting frame; the clamping jaw is movably connected with the two vertical plates through a pin shaft; one end of the transmission rod penetrates through the clamping jaw, a positioning block is fixed at the end head, and the positioning block is in contact with the radar body base; the other end of the transmission rod is coaxially provided with a rotating wheel, the transmission rod is driven by the rotating wheel to move in the hole of the clamping jaw and move to one side of the radar body, the positioning block is further pressed against the radar body, and the clamping jaw is pushed to rotate anticlockwise through reaction force; when the transmission rod moves to the maximum stroke and the bottom of one support arm of the clamping jaw is tightly pressed with the surface of the radar body, the two-way extrusion and fixation of the radar body are completed.
Description
Technical Field
The invention belongs to the technical field of aviation radars, and particularly relates to a fixing mechanism of an aviation radar.
Background
The aviation radar is a general name of various radars installed on an aviation aircraft, is mainly used for controlling and guiding weapons, implementing air warning and reconnaissance, and guaranteeing accurate navigation and flight safety, has the same basic principle and composition as other military radars, and is characterized in that: generally, an antenna platform stabilizing system or a data stabilizing device is provided, and a wave band below 3 cm is adopted, so that the antenna platform stabilizing system is small in size and light in weight.
The clearance needs regularly to be dismantled to the air radar in the use, but the inside at the aircraft is mostly passed through the bolt fastening to the air radar that has now, and the connected mode is comparatively loaded down with trivial details, connects the face comparatively single moreover, can't satisfy the user demand of maintaining the back and installing fast.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the fixing mechanism of the aerial radar has the advantage of convenience in installation and fixation, and solves the problems that the existing aerial radar is mostly fixed inside an aerial plane through bolts, the connection mode is complicated, the connection surface is single, and the use requirement of quick installation after maintenance cannot be met.
The technical scheme of the invention is as follows: the utility model provides an aviation radar's fixed establishment which characterized in that: comprises a fixing device and a mounting frame; the fixing device is used for fixing the radar body and is arranged above the installation frame;
the fixing device comprises a connecting frame, a vertical plate, a clamping jaw, a rotating wheel, a transmission rod, a positioning block and a torsion spring; the connecting frame is of a box body structure with openings at the upper end and one side wall, and the base of the radar body is placed on the inner bottom surface of the connecting frame; the two vertical plates are opposite and vertically fixed at the opening of the side wall of the connecting frame, and the clamping jaw is arranged at the upper part between the two vertical plates through a pin shaft and can rotate relative to the opposite plates; one support arm of the clamping jaw is in contact with the base of the radar body, and the other support arm is positioned between the two vertical plates; one end of the transmission rod penetrates through the through hole in the other support arm of the clamping jaw, a positioning block is fixed at the end head, and the positioning block is in contact with the base of the radar body; the other end of the transmission rod is coaxially provided with a rotating wheel, the transmission rod is driven by the rotating wheel to move in the hole of the clamping jaw and move to one side of the radar body, the positioning block is further pressed against the radar body, and the clamping jaw is pushed to rotate anticlockwise through reaction force; when the transmission rod moves to the maximum stroke and the bottom of one support arm of the clamping jaw is tightly pressed with the surface of the radar body, the two-way extrusion and fixation of the radar body are completed.
The further technical scheme of the invention is as follows: and the pin shafts on the two sides of the clamping jaw are sleeved with torsional springs respectively for limiting the axial displacement of the clamping jaw.
The further technical scheme of the invention is as follows: the interior top surface edge and the interior bottom surface of connecting frame are fixed with the shock pad through the hot melt, the shock pad contacts with the base surface of radar body, the material of shock pad is damping material.
The further technical scheme of the invention is as follows: a pressurizing pad is fixed at one end of the positioning block, which faces the radar body, and is positioned between the positioning block and the radar body and used for increasing the friction force between the positioning block and the radar body; the surface of the pressurizing pad is provided with anti-skid lines made of silica gel.
The further technical scheme of the invention is as follows: the two-way screw is vertically arranged in the mounting frame, and two ends of the two-way screw are respectively and rotatably connected with the bottom surface of the mounting frame and the bottom surface of the connecting frame through bearings; the lifting plate is of a flat plate structure with a threaded through hole in the center and is coaxially matched and arranged at the upper part of the bidirectional screw through threads; the four fixing rods are vertically arranged at four top corners of the lifting plate, one end of each fixing rod is fixed with the lifting plate, and the other end of each fixing rod penetrates through the bottom surface of the connecting frame and extends to the bottom of the radar body base; the lifting plate is driven to move upwards by rotating the bidirectional screw rod, and therefore the radar body can be longitudinally compressed and limited.
The further technical scheme of the invention is as follows: the bidirectional screw is provided with a ratchet mechanism, and the ratchet mechanism comprises a ratchet wheel and a shifting rod; the ratchet wheel is coaxially arranged at the lower part of the bidirectional screw rod through threads; one end of the shifting rod is rotatably connected with the bidirectional screw through a bearing and is positioned below the ratchet wheel, and the other end of the shifting rod extends to the outer side of the mounting frame; and a pawl is arranged at the position, close to the bidirectional screw rod, of the shifting lever and is meshed with the ratchet wheel.
Advantageous effects
The invention has the beneficial effects that:
1. according to the invention, the transmission rod is driven by the rotating wheel to move in the claw and move to the left, the transmission rod drives the positioning block to contact with the right side of the radar body and pushes the claw to rotate anticlockwise through reaction force, when the transmission rod moves to the maximum stroke and the bottom of the claw contacts with the surface of the radar body, the bidirectional extrusion and fixation of the radar body are completed, and the problems that the existing aviation radar is mostly fixed in an aviation aircraft through bolts, the connection mode is complicated, the connection surface is single, and the use requirement of quick installation after maintenance cannot be met are solved.
2. According to the invention, the torsion spring is arranged, so that the jaw can be supported, the stability of the jaw in the moving process can be improved, and the operation steps of rotating the jaw by a user are saved.
3. According to the invention, the shock pad is arranged, so that the radar body can be protected, and the influence of external vibration on the radar body is reduced.
4. According to the invention, the pressure pad is arranged, so that the friction force between the positioning block and the radar body can be improved, and the abrasion generated when the positioning block is in extrusion contact with the radar body is reduced.
5. According to the invention, the bidirectional screw rod, the lifting plate and the fixing rod are arranged, so that the radar body can be longitudinally limited, and the radar body is prevented from sliding in the connecting frame.
6. The invention is specially provided with the ratchet wheel and the deflector rod, so that a user can conveniently rotate the bidirectional screw rod, and the phenomenon of rotation of the bidirectional screw rod can be avoided.
Drawings
FIG. 1 is a schematic view of the inventive structure;
FIG. 2 is a schematic sectional front view of a partial structure according to the present invention;
fig. 3 is an enlarged schematic view of a portion a in fig. 2 according to the present invention.
Description of reference numerals: 1. a connecting frame; 2. a radar body; 3. a sidewall opening; 4. a vertical plate; 5. a claw; 6. a rotating wheel; 7. a transmission rod; 8. positioning blocks; 9. a mounting frame; 10. a torsion spring; 11. a shock pad; 12. a pressure pad; 13. a bidirectional screw; 14. a lifting plate; 15. fixing the rod; 16. a ratchet wheel; 17. a deflector rod.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
As shown in fig. 1 to 3, the fixing mechanism for an airborne radar provided by the patent of the present invention includes a connecting frame 1 and a mounting frame 9, wherein the connecting frame 1 is used for fixing a radar body 2 and is mounted above the mounting frame 9;
inside sliding connection of linking frame 1 has radar body 2, opening 3 has been seted up on the right side of linking frame 1, the front side at 1 top of linking frame is located the riser 4 of opening 3 both sides with the equal fixedly connected with in rear side, there is jack catch 5 inboard through round pin axle swing joint of riser 4, jack catch 5 keep away from one side of riser 4 extend to radar body 2 the top and with radar body 2's surface contact, the right side of linking frame 1 is provided with runner 6, the left side fixedly connected with transfer line 7 of runner 6, jack catch 5 is run through and extend to jack catch 5's left side to the left end of transfer line 7, the left end fixedly connected with locating piece 8 of transfer line 7, locating piece 8 keeps away from one side of transfer line 7 and radar body 2's surface contact, the bottom fixedly connected with installation frame 9 of.
Referring to fig. 3, the front surface and the back surface of the jaw 5 are both provided with a torsion spring 10 sleeved on the surface of the pin shaft, and one end of the torsion spring 10, which is far away from the jaw 5, extends to the left side of the vertical plate 4 and contacts with the surface of the vertical plate 4.
As a technical optimization scheme of the invention, the torsion spring 10 is arranged, so that the claw 5 can be supported, the stability of the claw 5 in the moving process can be improved, and the operation steps of rotating the claw 5 by a user are saved.
Referring to fig. 1, the top of the connection frame 1 is connected with a shock pad 11 through hot melting, the outer surface of the shock pad 11 contacts with the surface of the radar body 2, and the shock pad 11 is made of damping material.
As a technical optimization scheme of the invention, the shock pad 11 is arranged, so that the radar body 2 can be protected, and the influence of external vibration on the radar body 2 is reduced.
Referring to fig. 3, a pressure pad 12 is fixedly connected to one side of the positioning block 8 away from the transmission rod 7, one side of the pressure pad 12 away from the positioning block 8 contacts with the surface of the radar body 2, anti-slip lines are formed on the surface of the pressure pad 12, and the pressure pad 12 is made of silica gel.
As a technical optimization scheme of the present invention, by providing the pressure pad 12, the friction between the positioning block 8 and the radar body 2 can be increased, and the abrasion of the positioning block 8 and the radar body 2 generated during the pressing contact can be reduced.
Referring to fig. 2, there is a bidirectional screw 13 at the bottom of the inner wall of the mounting frame 9 through a bearing swing joint, there is a bearing swing joint at the top of the bidirectional screw 13 and the bottom of the connecting frame 1, there is a lifting plate 14 on the surface of the bidirectional screw 13, there is a fixing rod 15 fixedly connected to four corners of the top of the lifting plate 14, and one end of the fixing rod 15 far away from the lifting plate 14 runs through the connecting frame 1 and extends to the bottom of the radar body 2.
As a technical optimization scheme of the invention, the bidirectional screw 13, the lifting plate 14 and the fixing rod 15 are arranged, so that the radar body 2 can be longitudinally limited, and the radar body 2 is prevented from sliding in the connecting frame 1.
Referring to fig. 2, a ratchet wheel 16 is fixedly connected to the surface of the bidirectional screw 13, a shift lever 17 located at the bottom of the ratchet wheel 16 is movably connected to the surface of the bidirectional screw 13 through a bearing, one end of the shift lever 17 away from the bidirectional screw 13 extends to the right side of the mounting frame 9, and the shift lever 17 is engaged with the ratchet wheel 16.
As a technical optimization scheme of the invention, the ratchet wheel 16 and the deflector rod 17 are arranged, so that a user can conveniently rotate the bidirectional screw 13, and the phenomenon that the bidirectional screw 13 rotates can be avoided.
The working principle and the using process of the invention are as follows: during the use, the user places radar body 2 in the inside of splice frame 1 through the opening 3 department of splice frame 1 both sides, then it is rotatory with ratchet 16 promotion two-way screw rod 13 through driving lever 17, two-way screw rod 13 drives lifter plate 14 upward movement and makes dead lever 15 run through splice frame 1, accomplish the vertical spacing to radar body 2 when dead lever 15 extends to the outside of radar body 2, then the rotatory runner 6 of user, runner 6 drives transfer line 7 and moves and move in the inside of jack catch 5 and the left side, transfer line 7 drives the right side contact of locating piece 8 and radar body 2 and promotes jack catch 5 anticlockwise rotation through reaction force, when transfer line 7 moves to the surface contact of maximum stroke and jack catch 5's bottom and radar body 2, accomplish the two-way extrusion of radar body 2 and fix.
In summary, the following steps: this fixing mechanism of aviation radar, it removes and moves to the left side at the inside of jack catch 5 to drive transfer line 7 through runner 6, transfer line 7 drives the right side contact of locating piece 8 and radar body 2 and promotes jack catch 5 anticlockwise rotation through reaction force, when transfer line 7 removes to the bottom of maximum stroke and jack catch 5 and radar body 2's surface contact, the completion is fixed to radar body 2's both-way extrusion, it is many through the inside of bolt fastening at aviation aircraft to have solved current aviation radar, connected mode is comparatively loaded down with trivial details, and it is comparatively single to connect the face, can't satisfy the problem of the user demand of the quick installation after maintaining.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (6)
1. The utility model provides an aviation radar's fixed establishment which characterized in that: comprises a fixing device and a mounting frame; the fixing device is used for fixing the radar body and is arranged above the installation frame;
the fixing device comprises a connecting frame, a vertical plate, a clamping jaw, a rotating wheel, a transmission rod, a positioning block and a torsion spring; the connecting frame is of a box body structure with openings at the upper end and one side wall, and the base of the radar body is placed on the inner bottom surface of the connecting frame; the two vertical plates are opposite and vertically fixed at the opening of the side wall of the connecting frame, and the clamping jaw is arranged at the upper part between the two vertical plates through a pin shaft and can rotate relative to the opposite plates; one support arm of the clamping jaw is in contact with the base of the radar body, and the other support arm is positioned between the two vertical plates; one end of the transmission rod penetrates through the through hole in the other support arm of the clamping jaw, a positioning block is fixed at the end head, and the positioning block is in contact with the base of the radar body; the other end of the transmission rod is coaxially provided with a rotating wheel, the transmission rod is driven by the rotating wheel to move in the hole of the clamping jaw and move to one side of the radar body, the positioning block is further pressed against the radar body, and the clamping jaw is pushed to rotate anticlockwise through reaction force; when the transmission rod moves to the maximum stroke and the bottom of one support arm of the clamping jaw is tightly pressed with the surface of the radar body, the two-way extrusion and fixation of the radar body are completed.
2. The airborne radar fixing mechanism according to claim 1, wherein: and the pin shafts on the two sides of the clamping jaw are sleeved with torsional springs respectively for limiting the axial displacement of the clamping jaw.
3. The airborne radar fixing mechanism according to claim 1, wherein: the interior top surface edge and the interior bottom surface of connecting frame are fixed with the shock pad through the hot melt, the shock pad contacts with the base surface of radar body, the material of shock pad is damping material.
4. The airborne radar fixing mechanism according to claim 1, wherein: a pressurizing pad is fixed at one end of the positioning block, which faces the radar body, and is positioned between the positioning block and the radar body and used for increasing the friction force between the positioning block and the radar body; the surface of the pressurizing pad is provided with anti-skid lines made of silica gel.
5. The airborne radar fixing mechanism according to claim 1, wherein: the two-way screw is vertically arranged in the mounting frame, and two ends of the two-way screw are respectively and rotatably connected with the bottom surface of the mounting frame and the bottom surface of the connecting frame through bearings; the lifting plate is of a flat plate structure with a threaded through hole in the center and is coaxially matched and arranged at the upper part of the bidirectional screw through threads; the four fixing rods are vertically arranged at four top corners of the lifting plate, one end of each fixing rod is fixed with the lifting plate, and the other end of each fixing rod penetrates through the bottom surface of the connecting frame and extends to the bottom of the radar body base; the lifting plate is driven to move upwards by rotating the bidirectional screw rod, and therefore the radar body can be longitudinally compressed and limited.
6. The airborne radar fixing mechanism according to claim 5, wherein: the bidirectional screw is provided with a ratchet mechanism, and the ratchet mechanism comprises a ratchet wheel and a shifting rod; the ratchet wheel is coaxially arranged at the lower part of the bidirectional screw rod through threads; one end of the shifting rod is rotatably connected with the bidirectional screw through a bearing and is positioned below the ratchet wheel, and the other end of the shifting rod extends to the outer side of the mounting frame; and a pawl is arranged at the position, close to the bidirectional screw rod, of the shifting lever and is meshed with the ratchet wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010814329.7A CN111948611A (en) | 2020-08-13 | 2020-08-13 | Fixing mechanism of aviation radar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010814329.7A CN111948611A (en) | 2020-08-13 | 2020-08-13 | Fixing mechanism of aviation radar |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111948611A true CN111948611A (en) | 2020-11-17 |
Family
ID=73343307
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010814329.7A Pending CN111948611A (en) | 2020-08-13 | 2020-08-13 | Fixing mechanism of aviation radar |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111948611A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113567988A (en) * | 2021-07-23 | 2021-10-29 | 深圳市国天电子股份有限公司 | Positioning mechanism for assembling radar shell |
-
2020
- 2020-08-13 CN CN202010814329.7A patent/CN111948611A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113567988A (en) * | 2021-07-23 | 2021-10-29 | 深圳市国天电子股份有限公司 | Positioning mechanism for assembling radar shell |
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