CN112325709A - Portable target space motion characteristic simulation platform for missile seeker - Google Patents
Portable target space motion characteristic simulation platform for missile seeker Download PDFInfo
- Publication number
- CN112325709A CN112325709A CN202011209988.4A CN202011209988A CN112325709A CN 112325709 A CN112325709 A CN 112325709A CN 202011209988 A CN202011209988 A CN 202011209988A CN 112325709 A CN112325709 A CN 112325709A
- Authority
- CN
- China
- Prior art keywords
- plate
- swing
- seeker
- turnover
- missile
- 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
Images
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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention provides a portable target space motion characteristic simulation platform for a missile seeker, which is matched with a corresponding simulation target (visible light, infrared light and laser light) and applied to daily performance detection of the seeker, seeker tracking performance during missile joint test and basic characteristic verification of servo and operation control in a missile loop; the invention is that; one set of mechanism can realize the rotation motion of the two-dimensional far end around the axis; the structure is simple, the carrying is convenient, and the use is convenient; the adaptability is strong, and no fixed requirements are made on the installation mode and the environment of the missile and the seeker; simple and clear operation, good safety and low cost.
Description
Technical Field
The invention belongs to the technical field of guidance heads, and particularly relates to a portable target space motion characteristic simulation platform for a missile guidance head.
Background
The seeker is a core component of the guided missile, and an optical system of the seeker receives information of a distant target, converges the information and converts the information into an electric signal to control an optical axis to follow and track the target. When the optical system main shaft rotates around the center of the universal bracket in follow-up. The infinite target characteristic is generated by a simulation target during indoor test, the simulation target is generally realized by a micro collimator, different light-emitting sources are placed on the focal plane of the collimator, parallel rays are formed after the light-emitting sources emit the light-emitting sources to obtain the infinite simulation target characteristic in different modes, and therefore indoor simulation targets such as laser, television, infrared and the like can be formed. During testing, the optical axis of the simulated target is aligned with the rotation center of the seeker to swing, the relative position and movement of the target and the missile are obtained, and target information is positioned in the visual field of the seeker and received by the detection unit, as shown in fig. 1.
The arrangement is shown in figure 2 when the seeker is tested indoors using a single axis turret. The rotation center of the seeker receiving unit is overlapped with the rotating shaft of the rotating table, the simulation target is located on the axis extension line of the seeker and can rotate around the rotating shaft within a certain angle range according to the required angle, angular speed and motion rule, response output information of the seeker is obtained by taking the simulation target as an input basis, and accordingly performance parameters of the seeker are obtained through processing. Because the signal response of the seeker is generally a yaw channel and a pitch channel, a target also needs to move in two directions during testing, and in the process of developing the seeker, the seeker is usually subjected to performance testing in the other direction after being circumferentially rotated by 90 degrees after testing in one direction is completed.
After the guided missile is assembled, the seeker is positioned at the top end of the missile body, the guided missile is arranged on the hanging rack or the support, the front part of the seeker is in a suspended state, the performance detection of the seeker and the ground performance detection of the guided missile can be generally carried out on a simple site, the requirements of a special detection rotary table of a general seeker on the use environment and the installation mode of a detected piece are relatively complex, and the test requirements under the state cannot be met.
Disclosure of Invention
In view of the above, the present invention provides a portable target space motion characteristic simulation platform for a missile seeker, which can provide two-channel simulated target motion using a seeker rotation center as a rotation axis.
A portable target space motion characteristic simulation platform for a missile seeker comprises a tripod (1), a main angle plate (2), a turnover plate (4), a turnover motor (3), a swing plate (6), a swing motor (5) and a simulation target (7);
the main angle plate (2) is of an L-shaped plate structure, the bottom plate is in butt joint with the tripod (1), and the tripod (1) supports the bottom plate; a turnover motor (3) is arranged on the outer side of the side plate of the main angle plate (2); the turnover plate (4) is also of an L-shaped plate structure, and the side plate is fixedly connected with an output shaft of the turnover motor (3) and can be driven to turn over; the swing plate (6) is placed on the upper surface of the bottom plate of the turnover plate (4), a swing shaft is fixedly connected to the outer side of the swing plate, and the lower end of the swing shaft is connected with a swing motor (5); the inner side of the swing plate (6) is supported on the bottom plate of the turnover plate (4) through a bearing; the simulation target (7) and the output shaft of the turnover motor (3) are coaxially fixed on the upper surface of the swing plate (6).
Furthermore, the device also comprises a balancing weight (8) which is fixed at the upper end of the side plate of the turnover plate (4).
Preferably, the lower end of the swing shaft penetrates through the bottom plate of the turnover plate (4) to be connected with a swing motor (5).
Preferably, the swing shaft is connected with a swing motor (5) through a gear set.
Preferably, the simulated target (7) has a size not greater than 85mmx160mm, a weight not greater than 3Kg, a swing range + -25 DEG, and a maximum swing angular velocity of 15 DEG/s.
The invention has the following beneficial effects:
the invention provides a portable target space motion characteristic simulation platform for a missile seeker, which is matched with a corresponding simulation target (visible light, infrared light and laser light) and applied to daily performance detection of the seeker, seeker tracking performance during missile joint test and basic characteristic verification of servo and operation control in a missile loop; the invention is that; one set of mechanism can realize the rotation motion of the two-dimensional far end around the axis; the structure is simple, the carrying is convenient, and the use is convenient; the adaptability is strong, and no fixed requirements are made on the installation mode and the environment of the missile and the seeker; simple and clear operation, good safety and low cost.
Drawings
FIG. 1 is a diagram of a prior art arrangement of a seeker relative to a simulation target;
FIG. 2 is a layout of a prior art indoor testing of a seeker with a single axis turntable;
FIG. 3 is a simplified structural diagram of a simulation platform according to the present invention;
FIG. 4 is a state diagram of a test of the yaw channel of the present invention;
FIG. 5 is a state diagram of a test of the pitch channel of the present invention;
the device comprises a tripod 1, a main angle plate 2, a turnover motor 3, a turnover plate 4, a swing motor 5, a swing plate 6, a simulation target 7, a balancing weight 8, a guide head 9, a support plate 10 and a test board 11.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention relates to a portable target space motion characteristic simulation platform for a missile seeker, which is used for testing the basic function of the seeker when a missile is suspended, realizing the test of the basic function of the seeker when a missile body is not dislocated and parts are not decomposed, and simultaneously simulating the target motion characteristic when the missile is electrified and tested.
According to the application characteristics and the test requirements, the invention provides a portable target space motion characteristic simulation platform for a missile seeker, which is used for installing a special simulation target and generating the motion characteristic of a simple target so as to achieve the basic performance detection of the missile seeker by combining with the real environment parameters in the actual engineering.
The purpose of the invention is realized as follows:
the platform comprises a tripod 1, a main angle plate 2, a turnover plate 4, a turnover motor 3, a swing plate 6, a swing motor 5, a simulation target 7, a balancing weight 8, a gear set, a bearing set and the like. And the external control box sends an instruction to realize the swinging motion and the channel turnover of the simulation target.
The invention is further described below with reference to the accompanying drawings.
The tripod 1 is an outsourcing three-degree-of-freedom bracket and is used for supporting the platform main body and realizing yaw, pitching and height adjustment; the main angle plate 2 is the main body of the whole platform and is of an L-shaped plate structure, and the bottom plate is in butt joint with the tripod 1 and is supported by the tripod 1. And the outer side of the side plate of the main angle plate 2 is provided with a turnover motor 3. The bottom panel of the main corner panel 2 also serves to support the roll-over panel 4 and the components thereon. The turnover plate 4 is also of an L-shaped plate structure, and a side plate is fixedly connected with an output shaft of the turnover electrode 3 and can be turned over under the driving of the turnover plate; the swing plate 6 is placed on the upper surface of the bottom plate of the turnover plate 4, the outer side of the swing plate is connected with a swing shaft, and the lower end of the swing shaft penetrates through the bottom plate of the turnover plate 4 and is driven by a swing motor 5; the inner side of the wobble plate 5 is supported on the bottom plate of the roll-over plate 4 by means of bearings. The simulation target 7 and the output shaft of the turnover motor 3 are coaxially fixed on the upper surface of the swing plate 6.
The balancing weight 8 is fixed at the upper end of the side plate of the turnover plate 4 and is mainly used for balancing the dynamic moment of the turnover plate 4 so as to reduce the turnover head-up error; the main effect of the bearing is to overcome the strength deformation of the cantilever structure and reduce the friction of each rotating link so as to improve the rotating efficiency.
The channel overturning motor 3 provides a rotating moment for the overturning plate 4, the switching of a yaw channel and a pitching channel is carried out through the instruction of the control box, the overturning plate 4 achieves the position reaching of the yaw channel and the pitching channel under the action of the overturning motor 3, the swinging motor 5 provides power for the swinging plate 6 through a gear set, the simulation target 7 arranged on the swinging plate 6 swings around a rotation center under the instruction of the control box;
fig. 4 shows a test state view of the yaw channel, and fig. 5 shows a test state view of the pitch channel.
The platform can provide performance test for a seeker (missile) 9 with the diameter less than phi 150mm, the size of the simulation light source 7 is not more than phi 85mmx160mm, the weight is not more than 3Kg, the swinging range is +/-25 degrees, and the maximum swinging angular speed is 15 degrees/s.
The invention has the following advantages:
1) and one set of mechanism realizes the rotation motion of the two-dimensional far end around the axis. The test channel conversion is usually completed by circumferentially rotating the seeker, and the invention achieves the relative conversion of the seeker test channel by rotating a platform rotating shaft;
2) simple structure, portability and convenient use. The two-dimensional turntable can also realize two-channel testing, but the structure is relatively large and complex, the carrying and the installation are complicated, and the requirements on the field and the use conditions are higher, so that the two-dimensional turntable can achieve the effect of a two-dimensional channel through one-dimensional channel conversion, the structure is simplified, and the use conditions are reduced;
3) the adaptability is strong, and the installation mode and the environment of the missile and the seeker are not fixedly required. The platform can basically support the test of basic performance no matter the seeker is arranged in the same body with the missile or independently, and no matter the seeker is arranged on the hanger or supported by a ground bracket;
4) the operation is simple and clear, and the safety is good. When the device works, a technician inputs an instruction at the control box end, no manual link is provided, all parts have mechanical hard limit in the motion process, and the motor torque is limited due to small load, so that the device cannot cause any damage to a measured object and an operator even if the device is out of control or the operation is wrong;
5) the cost is low. The simple scheme achieves the realization of multiple functions, and the manufacturing cost and the use cost are both low.
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 portable target space motion characteristic simulation platform for a missile seeker is characterized by comprising a tripod (1), a main angle plate (2), a turnover plate (4), a turnover motor (3), a swing plate (6), a swing motor (5) and a simulation target (7);
the main angle plate (2) is of an L-shaped plate structure, the bottom plate is in butt joint with the tripod (1), and the tripod (1) supports the bottom plate; a turnover motor (3) is arranged on the outer side of the side plate of the main angle plate (2); the turnover plate (4) is also of an L-shaped plate structure, and the side plate is fixedly connected with an output shaft of the turnover motor (3) and can be driven to turn over; the swing plate (6) is placed on the upper surface of the bottom plate of the turnover plate (4), a swing shaft is fixedly connected to the outer side of the swing plate, and the lower end of the swing shaft is connected with a swing motor (5); the inner side of the swing plate (6) is supported on the bottom plate of the turnover plate (4) through a bearing; the simulation target (7) and the output shaft of the turnover motor (3) are coaxially fixed on the upper surface of the swing plate (6).
2. The missile seeker portable target space motion characteristic simulation platform as in claim 1, further comprising a counterweight (8) fixed to the upper end of the side plate of the turnover plate (4).
3. The missile seeker portable target space motion characteristic simulation platform as in claim 1, wherein the lower end of the swing shaft penetrates through the bottom plate of the turnover plate (4) and is connected with the swing motor (5).
4. The missile seeker portable target space motion characteristic simulation platform as in claim 1, wherein the swing shaft is connected with the swing motor (5) through a gear set.
5. The missile seeker portable target space motion characteristic simulation platform as in claim 1, wherein the simulated target (7) has a size not greater than phi 85mmx160mm, a weight not greater than 3Kg, a swinging range +/-25 degrees and a maximum swinging angular speed of 15 degrees/s.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202011209988.4A CN112325709A (en) | 2020-11-03 | 2020-11-03 | Portable target space motion characteristic simulation platform for missile seeker |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202011209988.4A CN112325709A (en) | 2020-11-03 | 2020-11-03 | Portable target space motion characteristic simulation platform for missile seeker |
Publications (1)
Publication Number | Publication Date |
---|---|
CN112325709A true CN112325709A (en) | 2021-02-05 |
Family
ID=74323509
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN202011209988.4A Pending CN112325709A (en) | 2020-11-03 | 2020-11-03 | Portable target space motion characteristic simulation platform for missile seeker |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN112325709A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102023000398A1 (en) | 2023-02-09 | 2024-08-14 | Diehl Defence Gmbh & Co. Kg | Method for operating a guided missile on a launch platform |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4446363A (en) * | 1982-03-01 | 1984-05-01 | The United States Of America As Represented By The Secretary Of The Navy | Target for optically activated seekers and trackers |
EP1608931A1 (en) * | 2003-03-29 | 2005-12-28 | Diehl BGT Defence GmbH & Co.KG | Seeker head comprising a pitching/yawing internal cardanic system |
US7408653B1 (en) * | 2006-01-27 | 2008-08-05 | The United States Of America As Represented By The Secretary Of The Army | Shim dialer platform and process to compensate for optical variations in components used in the assembly of seeker heads with folded optics for semi-active laser guided cannon launched projectiles |
CN201993123U (en) * | 2010-12-31 | 2011-09-28 | 西安航天精密机电研究所 | Multi-degree-of-freedom infrared target simulation test mechanism |
CN202452892U (en) * | 2011-12-30 | 2012-09-26 | 洛阳理工学院 | Motion analogue simulation system for infrared target |
CN204301963U (en) * | 2014-11-13 | 2015-04-29 | 北京航天计量测试技术研究所 | A kind of novel infinity moving-target simulator |
CN105404173A (en) * | 2015-10-30 | 2016-03-16 | 北京控制工程研究所 | Dynamic solar simulator and dynamic simulation method thereof |
CN105953656A (en) * | 2016-05-04 | 2016-09-21 | 北京航天易联科技发展有限公司 | Method for testing performance of seeker |
-
2020
- 2020-11-03 CN CN202011209988.4A patent/CN112325709A/en active Pending
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4446363A (en) * | 1982-03-01 | 1984-05-01 | The United States Of America As Represented By The Secretary Of The Navy | Target for optically activated seekers and trackers |
EP1608931A1 (en) * | 2003-03-29 | 2005-12-28 | Diehl BGT Defence GmbH & Co.KG | Seeker head comprising a pitching/yawing internal cardanic system |
US7408653B1 (en) * | 2006-01-27 | 2008-08-05 | The United States Of America As Represented By The Secretary Of The Army | Shim dialer platform and process to compensate for optical variations in components used in the assembly of seeker heads with folded optics for semi-active laser guided cannon launched projectiles |
CN201993123U (en) * | 2010-12-31 | 2011-09-28 | 西安航天精密机电研究所 | Multi-degree-of-freedom infrared target simulation test mechanism |
CN202452892U (en) * | 2011-12-30 | 2012-09-26 | 洛阳理工学院 | Motion analogue simulation system for infrared target |
CN204301963U (en) * | 2014-11-13 | 2015-04-29 | 北京航天计量测试技术研究所 | A kind of novel infinity moving-target simulator |
CN105404173A (en) * | 2015-10-30 | 2016-03-16 | 北京控制工程研究所 | Dynamic solar simulator and dynamic simulation method thereof |
CN105953656A (en) * | 2016-05-04 | 2016-09-21 | 北京航天易联科技发展有限公司 | Method for testing performance of seeker |
Non-Patent Citations (1)
Title |
---|
纪小辉: "导引头性能检测装置设计", 《中国测试》 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102023000398A1 (en) | 2023-02-09 | 2024-08-14 | Diehl Defence Gmbh & Co. Kg | Method for operating a guided missile on a launch platform |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN204649386U (en) | A kind of high precision multiband dynamic goal simulator device | |
CN105923168B (en) | Gyroplane flight simulation platform for airborne tripod head test | |
CN109093379A (en) | Low-pressure turbo unit body Intelligent assembly platform | |
CN106569205A (en) | Co-aperture infrared/radar composite seeker | |
CN108825941A (en) | A kind of Airborne Camera ground motion test device of multiaxis cooperative motion | |
CN111089608B (en) | Seeker performance test system | |
CN207516543U (en) | A kind of optics dynamic target system | |
CN105242570A (en) | Aircraft-to-sun relationship ground simulation device | |
CN212556849U (en) | High-precision double-shaft simulation turntable with no shielding of clearance of pitching shaft | |
CN101251440A (en) | Dynamic goal simulator | |
CN112325709A (en) | Portable target space motion characteristic simulation platform for missile seeker | |
CN201173855Y (en) | Dynamic target generator | |
CN105509577A (en) | Target motion stimulating device based on mechanical arms | |
CN110487509B (en) | Three-channel pupil coupling laser semi-active target simulator | |
CN211234453U (en) | Seeker performance testing device | |
CN109917343A (en) | A kind of target simulation system | |
CN111059962A (en) | Spherical surface movement mechanism | |
CN103744438B (en) | A kind of ball-type powdered soil | |
CN109027772A (en) | It is a kind of to cardioid dynamic solar simulator | |
CN107887700A (en) | A kind of target seeker servo-drive system transmission mechanism | |
CN106227241A (en) | A kind of motion platform double-view field double loop scan tracing system and method | |
CN101832911B (en) | Photomechanical equipment of vehicular infrared detection system | |
CN208204386U (en) | A kind of Airborne Camera ground motion test device of multiaxis cooperative motion | |
CN205675261U (en) | Gyroplane flight simulation platform for airborne tripod head test | |
CN108414198A (en) | A kind of pilot system and method focused for simulated solar irradiation |
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 | ||
WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20210205 |
|
WD01 | Invention patent application deemed withdrawn after publication |