CN215119218U - Double-antenna integrated device for remote measurement and guidance of rotary target projectile - Google Patents
Double-antenna integrated device for remote measurement and guidance of rotary target projectile Download PDFInfo
- Publication number
- CN215119218U CN215119218U CN202120404342.5U CN202120404342U CN215119218U CN 215119218 U CN215119218 U CN 215119218U CN 202120404342 U CN202120404342 U CN 202120404342U CN 215119218 U CN215119218 U CN 215119218U
- Authority
- CN
- China
- Prior art keywords
- antenna
- target
- shell
- telemetering
- antennas
- 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.)
- Active
Links
- 238000005259 measurement Methods 0.000 title claims abstract description 15
- 230000009977 dual effect Effects 0.000 claims description 8
- 230000000694 effects Effects 0.000 claims description 7
- 230000007123 defense Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 238000012549 training Methods 0.000 description 3
- 230000006872 improvement Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
Abstract
The utility model discloses a rotatory target bomb telemetering measurement defends leads double antenna integrated device relates to target bomb technical field and includes: the target bomb cabin section comprises a shell, a remote measuring antenna and a satellite antenna; the outer circumferential surface of the shell of the target bomb cabin section is provided with two telemetering antennas and two guarding antennas, and the central connecting line of the two telemetering antennas and the central connecting line of the two guarding antennas are vertical in space and do not intersect; the telemetering antennas and the guard guide antennas are symmetrically and crossly arranged on the same cabin section of the rotary target missile, so that the relative gain areas of the antennas are consistent, and the two antennas are uniformly covered by 360 degrees along the circumferential direction.
Description
Technical Field
The utility model relates to a target bullet technical field, concretely relates to rotatory target bullet telemetering measurement defends leads double antenna integrated device.
Background
With the development of military technical level of each country, the improvement of military force and the aggravation of military tension in hot spots, the supersonic cruise missile is gradually paid more attention by more countries and regions due to the characteristics of high flying speed, strong penetration resistance and the like. China and surrounding countries and regions are also equipped or planned with supersonic cruise missiles, and in order to deal with the threat of supersonic cruise missile weapons, supersonic cruise target missiles simulate the flight characteristics and observation characteristics of supersonic cruise missiles in scientific research tests and training exercises and are used for inspecting and training air defense systems.
In inspection and training, it is a necessary process to transmit satellite navigation data to a ground station system in real time by telemetry. However, the projectile body structure of the target projectile is mostly a missile which is changed or retired by a rocket projectile, the structural layout is solidified, the available projectile body space is small, the independent telemetering device and the independent guarding device occupy a large projectile body space, the telemetering device and the guarding device of different cabin sections need to consider the whole electrical layout and electromagnetic compatibility of the target projectile, and how to realize the dual functions of telemetering data transmission and guarding data reception in the limited projectile body space is a problem which needs to be solved urgently. Therefore, the rotary target projectile telemetering guard antenna needs to be designed integrally.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides a rotatory target bomb telemetering measurement defends leads two antenna integrated devices, symmetrical cross arrangement telemetering measurement antenna and defend lead antenna (satellite navigation antenna) on the same cabin section of rotatory target bomb, make every kind of antenna relative gain area unanimous, and two kinds of antennas are along 360 even covers of circumference.
The technical scheme of the utility model is that: a rotary target projectile telemetering and guarding double-antenna integrated device comprises: the target bomb cabin section comprises a shell, a remote measuring antenna and a satellite antenna; two telemetering antennas and two guarding antennas are arranged on the outer circumferential surface of the shell of the target bomb cabin section, and the central connecting line of the two telemetering antennas and the central connecting line of the two guarding antennas are perpendicular to each other and do not intersect with each other in space.
Preferably, the distance between the central line of each telemetry antenna along the circumference of the shell of the target bomb cabin section and the central line of each satellite antenna along the circumference of the shell of the target bomb cabin section is a set value.
Preferably, the set value is greater than 50 mm.
Preferably, the two defense antennas are positioned on the outer circumferential surface of the upper end of the shell of the target bomb cabin section, the two telemetering antennas are positioned on the outer circumferential surface of the lower end of the shell of the target bomb cabin section, the lower edge of the defense antenna is not lower than the central line of the telemetering antenna along the circumferential direction of the shell of the target bomb cabin section, and the upper edge of the telemetering antenna is not higher than the central line of the defense antenna along the circumferential direction of the shell of the target bomb cabin section; wherein, the end that the target bomb cabin section casing links to each other with the control cabin section is the upper end, and the end that links to each other with the engine is the lower extreme.
Preferably, the central angle of the telemetry antenna relative to the central axis of the target projectile chamber section shell is between 55 and 60 degrees.
Preferably, the central angle of the satellite antenna relative to the central axis of the shell of the target bomb compartment is between 30 and 35 degrees.
Preferably, when the target bomb cabin shell rotates along with the target bomb, the projection areas on the XZ plane are always equal, and the positive direction of the satellite antenna to the Y axis is constantly guaranteed to be equivalent to a receiving antenna, and the negative direction of the remote sensing antenna to the Y axis is constantly guaranteed to be equivalent to a sending antenna; the receiving effect of the defense antenna is uniformly covered along the circumferential direction of the shell of the target bomb cabin section, and the sending effect of the remote measuring antenna is uniformly covered along the circumferential direction of the shell of the target bomb cabin section; the X-axis positive direction is upward along the axial direction of the target bomb cabin shell, and the Y-axis negative direction is the ground direction of the target bomb cabin shell.
Preferably, the areas of the telemetry antenna and the satellite antenna on the target bomb section shell are determined according to antenna gain.
Preferably, the area of the guard antenna is no more than two thirds of the area of the telemetry antenna.
Preferably, the sum of the areas of the satellite antenna and the telemetry antenna is no more than one-half of the surface area of the entire target capsule section housing.
Has the advantages that:
1. the utility model discloses a double antenna integrated device, symmetrical cross arrangement telemetering measurement antenna and defend lead the antenna on the same cabin section of rotatory target bomb, make every kind of antenna relative gain area unanimous, and two kinds of antennas along 360 even covers of circumference, guarantee under structural strength's the condition, two kinds of antenna cross layout, satisfy that same cabin section has two kinds of antenna functions.
2. The utility model discloses the position relation of the central line of the structure size of two kinds of antennas of well definite, circumference and edge line overlaps the overall arrangement, guarantees that two kinds of communications do not have mutual interference, has reduced the length of target bomb cabin section.
3. The utility model discloses well telemetry antenna and defend lead the electromagnetic compatibility design of antenna in same target bomb cabin section and more defend lead antenna, the independent target bomb cabin section design of telemetry antenna simple.
Drawings
Fig. 1 is the utility model provides a rotatory target bomb telemetering measurement defends leads double antenna integrated device's schematic structure diagram.
Fig. 2 is a front view (looking down the guard antenna) of fig. 1.
Fig. 3 is a top view (looking down on the telemetry antenna) of fig. 1.
The target bomb cabin comprises a target bomb cabin section shell, a 2-telemetering antenna, a 3-guide antenna and a 4-connecting screw.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings by way of examples.
The embodiment provides a rotatory target projectile telemetering guarding leads two antenna integrated device, and symmetrical cross arrangement telemetering measurement antenna and guarding lead antenna make the relative gain area of every kind of antenna unanimous on the same cabin section of rotatory target projectile, and 360 evenly covers along circumference for two kinds of antennas.
As shown in fig. 1, the dual antenna integrated device includes: the target bomb cabin section comprises a shell 1, a remote measuring antenna 2 and a satellite antenna 3; the two telemetering antennas 2 are uniformly arranged along the circumferential direction of the target bomb cabin section shell 1, the two guarding and guiding antennas 3 are uniformly arranged along the circumferential direction of the target bomb cabin section shell 1, and the two telemetering antennas 2 and the two guarding and guiding antennas 3 are perpendicularly crossed along the circumferential direction (namely the central connecting line of the two telemetering antennas 2 is perpendicular to the central connecting line of the two guarding and guiding antennas 3) and are arranged along the axial direction in a staggered mode (namely a set distance is reserved between the central line of each telemetering antenna 2 along the circumferential direction of the target bomb cabin section shell 1 and the central line of each guarding and guiding antenna 3 along the circumferential direction of the target bomb cabin section shell 1);
as shown in fig. 2, each satellite antenna 3 is fixed on the target projectile cabin section shell 1 between two telemetering antennas 2 through eight hexagon socket countersunk head connecting screws 4; as shown in fig. 3, each telemetry antenna 2 is fixed to the target projectile bay section housing 1 between two satellite antennas 3 by eight hexagonal countersunk head connection screws 4.
The utility model discloses in, every telemetering measurement antenna 2 is followed the central line of 1 circumference of target bomb cabin section casing and is defended with every and lead antenna 3 and be greater than 50mm along the interval between the central line of 1 circumference of target bomb cabin section casing (can design the value that corresponds according to the different bores of target bomb).
In the utility model, two guarding and guiding antennas 3 are positioned on the outer circumferential surface of the upper end of a target bomb cabin section shell 1, two telemetering antennas 2 are positioned on the outer circumferential surface of the lower end of the target bomb cabin section shell 1, the lower edge of the guarding and guiding antenna 3 does not cross the central line of the telemetering antenna 2 along the circumferential direction of the target bomb cabin section shell 1, and the upper edge of the telemetering antenna 2 does not cross the central line of the guarding and guiding antenna 3 along the circumferential direction of the target bomb cabin section shell 1; wherein, the end of the shell 1 of the target bomb cabin section connected with the control cabin section is the upper end, and the end connected with the power device (or engine) is the lower end.
In the utility model, the central angle of the telemetering antenna 2 relative to the central axis of the target projectile cabin shell 1 is between 55 degrees and 60 degrees.
In the utility model, the central angle of the antenna 3 relative to the central axis of the target bomb compartment shell 1 is between 30 degrees and 35 degrees.
The utility model discloses in, the area of telemetering measurement antenna 2 and defend leading antenna 3 on target bomb cabin section casing 1 is confirmed according to antenna gain.
In the utility model, when the shell 1 of the target bomb cabin rotates along with the target bomb, the projection area on the XZ plane is always equal, the positive direction of the Y axis of the satellite antenna 3 is equivalent to a receiving antenna, and the negative direction of the Y axis of the remote measuring antenna 2 is equivalent to a sending antenna; the receiving effect of the guard guide antenna 3 can be uniformly covered along the circumferential direction of the shell 1 of the target bomb cabin section, and the sending effect of the remote measuring antenna 2 can be uniformly covered along the circumferential direction of the shell 1 of the target bomb cabin section; the X-axis positive direction is upward along the axial direction of the target bomb compartment shell 1, the Y-axis negative direction is the ground direction of the target bomb compartment shell 1, and the Z-axis can be uniquely determined under the condition that the X-axis and the Y-axis are known.
The utility model discloses in, for avoiding that projectile cabin section casing 1 is overweight to the quality, the barycenter of projectile body to produce the influence, guarantee projectile cabin section casing 1's intensity simultaneously and defend the effect of leading 3 received data of antenna and the sending data of telemetering measurement antenna 2, the area of defending leading 3 antenna is not more than the two-thirds of telemetering measurement antenna 2, the area sum of defending leading 3 antenna and telemetering measurement antenna 2 is not more than the half of whole projectile cabin section casing 1's surface area.
In summary, the above 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 (10)
1. The utility model provides a rotatory target missile telemetering measurement defends leads two antenna integrated device which characterized in that includes: the target bomb cabin section comprises a target bomb cabin section shell (1), a remote measuring antenna (2) and a satellite antenna (3); two telemetering antennas (2) and two guarding antennas (3) are arranged on the outer circumferential surface of the target bomb cabin section shell (1), and the central connecting line of the two telemetering antennas (2) and the central connecting line of the two guarding antennas (3) are perpendicular and do not intersect.
2. The rotary target projectile telemetry missile and dual-antenna integrated device as claimed in claim 1, wherein the distance between the center line of each telemetry antenna (2) along the circumferential direction of the target projectile cabin section shell (1) and the center line of each missile antenna (3) along the circumferential direction of the target projectile cabin section shell (1) is a set value.
3. The rotary target projectile telemetry and guard dual antenna integrated device as claimed in claim 2, wherein the set value is greater than 50 mm.
4. The rotary target projectile telemetering missile and double-antenna integrated device according to claim 1, wherein two missile antennas (3) are positioned on the outer circumferential surface of the upper end of the missile bay section shell (1), two telemetering antennas (2) are positioned on the outer circumferential surface of the lower end of the missile bay section shell (1), the lower edge of each missile antenna (3) is not lower than the central line of each telemetering antenna (2) along the circumferential direction of the missile bay section shell (1), and the upper edge of each telemetering antenna (2) is not higher than the central line of each missile antenna (3) along the circumferential direction of the missile bay section shell (1); wherein, the end of the target bomb cabin shell (1) connected with the control cabin is the upper end, and the end connected with the engine is the lower end.
5. A rotary target projectile telemetry guard dual antenna integrated device as claimed in claim 1 wherein the central angle of the telemetry antenna (2) relative to the central axis of the target projectile chamber section housing (1) is between 55 ° and 60 °.
6. A rotary target projectile telemetry guard dual antenna integrated device as claimed in claim 1 wherein the central angle of the guard antenna (3) relative to the central axis of the target projectile chamber section housing (1) is between 30 ° and 35 °.
7. The rotary target projectile telemetering missile and double-antenna integrated device as claimed in claim 1, wherein when the target projectile cabin shell (1) rotates along with the target projectile, the projection areas on an XZ plane are always equal, so that the positive direction of the missile antenna (3) to the Y axis is equivalent to a receiving antenna at any moment, and the negative direction of the telemetering antenna (2) to the Y axis is equivalent to a transmitting antenna; the receiving effect of the guard antenna (3) is uniformly covered along the circumferential direction of the shell (1) of the target bomb cabin section, and the sending effect of the remote measuring antenna (2) is uniformly covered along the circumferential direction of the shell (1) of the target bomb cabin section; the X-axis positive direction is upward along the axial direction of the target bomb cabin shell (1), and the Y-axis negative direction is the ground direction of the target bomb cabin shell (1).
8. A rotary target projectile telemetry and guard dual antenna integrated device as claimed in claim 1 wherein the area of the telemetry antenna (2) and guard antenna (3) on the target projectile cabin section casing (1) is determined by antenna gain.
9. A rotary target projectile telemetry and guard dual antenna integrated device as claimed in claim 1 or 8 wherein the area of the guard antenna (3) is no more than two thirds of the area of the telemetry antenna (2).
10. A rotary target projectile telemetry missile and dual antenna integrated device as claimed in claim 1 or 8, characterized in that the sum of the areas of the missile antenna (3) and the telemetry antenna (2) is not more than half of the surface area of the whole projectile cabin shell (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120404342.5U CN215119218U (en) | 2021-02-24 | 2021-02-24 | Double-antenna integrated device for remote measurement and guidance of rotary target projectile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120404342.5U CN215119218U (en) | 2021-02-24 | 2021-02-24 | Double-antenna integrated device for remote measurement and guidance of rotary target projectile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215119218U true CN215119218U (en) | 2021-12-10 |
Family
ID=79335980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120404342.5U Active CN215119218U (en) | 2021-02-24 | 2021-02-24 | Double-antenna integrated device for remote measurement and guidance of rotary target projectile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215119218U (en) |
-
2021
- 2021-02-24 CN CN202120404342.5U patent/CN215119218U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2551821C1 (en) | Fighting short- and medium-range drones with help of electromagnetic radiation of microwaves band | |
| KR101411699B1 (en) | Systems and methods for disambiguating shooter locations with shockwave-only location | |
| US7600421B1 (en) | Instrumented ballistic test projectile | |
| US8648285B2 (en) | Remotely guided gun-fired and mortar rounds | |
| CA2343350A1 (en) | Autonomous off-board defensive aids system | |
| CN102087083A (en) | Rope course type short-range missile intercepting device | |
| US11371812B2 (en) | Anti-drone weapon | |
| CN114432625B (en) | Remote accurate guidance fire extinguishing bomb | |
| CN215119218U (en) | Double-antenna integrated device for remote measurement and guidance of rotary target projectile | |
| EP2268996B1 (en) | Methods and apparatus for guidance of ordnance delivery device | |
| CN108128456A (en) | Unmanned helicopter-mounted fire-fighting fire extinguishing gondola | |
| CN207860455U (en) | Unmanned helicopter-mounted fire-fighting fire extinguishing gondola | |
| CN107152895B (en) | A kind of conformal radar survey height/global location set composite | |
| CN206003956U (en) | A kind of telemetering antenna piece assembly apparatus for rocket projectile | |
| RU2733600C1 (en) | Thermobaric method of swarm control of small-size unmanned aerial vehicles | |
| US4178596A (en) | Radar augmentation system for airborne target | |
| US4137819A (en) | Launch tube antenna | |
| CN108072871A (en) | A kind of ballistic missile early warning information processing system | |
| RU2534157C1 (en) | Practice guided missile | |
| RU2184343C1 (en) | Radio-controlled anti-aircraft missile | |
| RU2808733C1 (en) | Unmanned aerial combat vehicle system | |
| KR102608406B1 (en) | Drone comprising charging module and charging apparatus combined with charging assembly docking the charging module | |
| RU2769455C1 (en) | Aerial target simulator | |
| CN115973469A (en) | Hand-throwing unmanned aerial vehicle and application thereof | |
| CN212253846U (en) | Low-altitude low-speed small target low-cost interception system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240104 Address after: Room 316, 3rd Floor, No. 8 Tianrong Street, Beizangcun Town, Daxing District, Beijing 102600 Patentee after: China Shipbuilding (Beijing) Intelligent Equipment Technology Co.,Ltd. Address before: Room 306, floor 3, building 6, courtyard 10, KEGU 1st Street, Beijing Economic Development Zone, Daxing District, Beijing 100176 Patentee before: CSIC sea air intelligent equipment Co.,Ltd. |
|
| TR01 | Transfer of patent right |