CN115336431B - Method for determining pointing angle of phased-array antenna beam of rocket missile-borne relay measurement and control system - Google Patents
Method for determining pointing angle of phased-array antenna beam of rocket missile-borne relay measurement and control system Download PDFInfo
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Abstract
The invention relates to a method for calculating the pointing angle of a phased array antenna beam of a rocket missile-borne relay measurement and control system, which comprises the following steps: (1) To relay the defenderThe coordinates (H, lambda, B) of the star in the geodetic coordinate system are converted into coordinates (X) in the geocentric rectangular coordinate system R ，Y R ，Z R ) (ii) a (2) Coordinates (X) of relay satellite in a geocentric rectangular coordinate system R ，Y R ，Z R ) Conversion to coordinates (X) in the Earth's center rectangular inertial frame I ，Y I ，Z I ) (ii) a (3) Relaying the coordinates (X) of the satellite in the Earth's center rectangular inertial frame I ，Y I ，Z I ) Conversion to coordinates (x) in the transmit inertial frame R ，y R ，z R ) (ii) a (4) Calculating a transmit inertial coordinate system O F x R y R z R The arrowed missile points to the vector of the relay satellite(ii) a (5) Calculating rocket projectile coordinate system O o x 1 y 1 z 1 The arrowed missile points to the vector of the relay satellite
(ii) a (6) Calculating the vector of the arrow bullet pointing to the relay satellite in the antenna body coordinate system OxyzFurther obtaining pointing angles alpha and beta; the method solves the problem of calculating the beam pointing angle of the phased array antenna pointing to the relay satellite of the arrowed missile-borne relay measurement and control system in the process of establishing a link between the rocket missile and the relay satellite, and realizes the calculation of the beam pointing angle of the phased array antenna.
Description
Technical Field
The invention relates to a method for determining a phased array antenna beam pointing angle of a rocket projectile carrier relay measurement and control system, and belongs to the technical field of rocket projectile carrier space-based measurement and control.
Background
Space-based measurement and control is a technology for measurement and control and data transmission by using a relay satellite. The design idea of space-based network fundamentally solves the problem of high coverage rate of measurement and control and communication, and the construction of the space-based network can greatly reduce the number of land-based and sea-based measurement and control stations.
In foreign countries, the space-based measurement and control technology of aircraft supported by a relay satellite system has been applied for a long time. In the early 90 s, the ESA (European Space Agency) signed a contract, and the research on the transmission of high-speed telemetry data of heavy-duty launch vehicles to ground-based rocket-based systems via data relay satellites was carried out by Astrium SAS Company with the support of EADS (European Aeronoutic Defence and Space Company) and was already in use. In the united states, the relay satellite system successfully provides data transmission support for dozens of tasks of multiple launch vehicles, and gradually becomes an important means for solving marine launch measurement and control. By 2001, essentially all launch vehicles have been supported by relay satellite S-band uni-site return traffic.
In China, the frequency of space launching tasks is continuously increased during the 'twelve five' period, the requirements for measuring arc sections are continuously improved, and in order to complete the measurement and control tasks of the active sections and the characteristic points of the aircrafts, a plurality of measurement relay ships are required to be arranged in relevant sea areas to provide measurement and control support. The existing aircraft measurement and control in China mainly depend on the established land/sea-based measurement and control network, the existing remote measurement means for the spacecraft in China only has a land/sea-based measurement mode of a fixed or mobile ground station and a measurement ship, the measurement coverage rate is very limited, the data transmission rate is low, the defects of poor coverage, poor timeliness, poor emergency capability, high cost-efficiency ratio and the like exist due to the limitation of geographical positions and coverage characteristics, and the realization of the requirement of the space measurement and control task is greatly restricted. Therefore, the space-based measurement and control means represented by the application of the relay satellite system becomes an important component of the aerospace measurement and control system in China.
In 7 months 2012, the first flight of the carrier rocket for implementing space-based measurement and control by using a relay satellite system in China is fully successful. The rocket-borne relay measurement and control system developed by the inventor is excellent in flight test, solves the problem that measurement and control of a gliding section of a carrier rocket cannot be fully covered, eliminates a rocket measurement and control blind area, and successfully fills the gap in the relay measurement and control field of the carrier rocket in China.
The rocket projectile-borne relay measurement and control system serves as a space-based measurement and control system and is wireless transmission equipment which is arranged on a rocket projectile platform and completes forward return remote measurement and remote control tasks by establishing a link with a ground measurement and control network through a relay satellite system.
In the process of establishing the arrow projectile and relay satellite return link, the arrow projectile-loaded relay measurement and control system needs to clarify the vector relationship between the arrow projectiles and the relay satellite according to the position information and the attitude information of the arrow projectile body and utilize a series of operations such as coordinate conversion and the like to calculate the pointing angle in real time so as to control the arrow projectile-loaded phased array antenna (contained in the arrow-loaded relay user terminal) to point to the relay satellite. Because the pointing angle changes with the change of the rocket projectile position and posture, a method for calculating the pointing angle of the phased array antenna beam of the rocket projectile-borne relay measurement and control system is needed.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, provides a method for determining the pointing angle of the phased array antenna beam of the rocket missile-borne relay measurement and control system, and solves the problem of calculating the pointing angle of the phased array antenna beam when the rocket-borne relay measurement and control system establishes link communication with a relay satellite.
The above purpose of the invention is mainly realized by the following technical scheme:
the method for determining the pointing angle of the phased array antenna beam of the rocket missile-borne relay measurement and control system comprises the following steps:
(1) Converting coordinates (H, lambda, B) of the relay satellite in the geodetic coordinate system to coordinates (X) in the geocentric rectangular coordinate system R ，Y R ，Z R )：
Wherein: n is the radius of the prime circle of the earth,
a is the equator radius of the earth, and e is the first eccentricity of the earth; h is the vertical distance from the spatial point to the earth's reference ellipsoid, called geodetic height; the angle lambda is in the equatorial plane of the reference ellipsoid and is the angle of the projection from the initial meridian plane eastward to the sagittal diameter of the space point in the equatorial plane, which is called the geodetic longitude; the angle B is an included angle between the equatorial plane and the normal line of the reference ellipsoid passing through the space point, is called the geodetic latitude, and is positive when facing north;
(2) The relay satellite is arranged in a rectangular coordinate system of the earth's centerCoordinate (X) of R， Y R ，Z R ) Conversion to coordinates (X) in the Earth's center rectangular inertial frame I ，Y I ，Z I )：
Wherein: r is Z Is a rotation matrix, omega is the rotation angular velocity of the earth, and t is the flight time of the rocket projectile;
earth, heart rectangular coordinate system OX R Y R Z R Is defined as: origin O of coordinate system at geocentric, OX R Pointing to meridian where Greenwich astronomical table is located in equatorial plane, OZ axis pointing to north pole perpendicular to equatorial plane, OX R Y R Z R Forming a right-hand rectangular coordinate system;
earth's center rectangular inertial coordinate system OX I Y I Z I At the moment of takeoff of rocket projectile, OX is orthogonal coordinate system with the center of the earth R Y R Z R Coincident and centroidal rectangular inertial frame OX I Y I Z I The inertia space is kept still;
(3) Relaying coordinates (X) of the satellite in the Earth's center rectangular inertial frame I ，Y I ，Z I ) Conversion to coordinates (x) in the transmit inertial frame R ，y R ，z R )
Wherein: (X) OF ，Y OF ，Z OF ) Is the coordinate of the emitting point in the centroid rectangular inertial coordinate system, alpha OF 、
And λ OF Respectively the geodetic azimuth, the geodetic longitude and the geodetic latitude of the transmitting point; r x ，R y ，R z Is a rotation matrix;
emission inertial frame O F x R y R z R At the moment of emission, the origin of coordinates is the emission point O F ，O F x R The axis is in the horizontal plane of the emission point and points to the emission aiming direction, O F y R The axis pointing upwards perpendicular to the horizontal plane of the emission point, O F z R Axis and x R O F y R The surfaces are vertical to each other and form a right-hand coordinate system, and the emission inertia coordinate system keeps still in an inertia space;
(4) Calculating a transmit inertial coordinate system O F x R y R z R The arrowed missile points to the vector of the relay satellite
Wherein: (x) m ，y m ，z m ) The coordinates of the rocket projectile in a launching inertial coordinate system are shown;
(5) Calculating rocket projectile coordinate system O o x 1 y 1 z 1 The arrowed missile points to the vector of the relay satellite
Wherein: (x) o ，y o ，z o ) The coordinates of the arrow missile pointing to the relay satellite in the arrow missile coordinate system;
corner
For rocket projectile coordinate system O o x 1 Axial in-transmit inertial frame x R O F y R Projection on plane and O F x R The included angle of the axes;
angle theta is rocket projectileThe yaw angle in the track is the rocket projectile coordinate system O o x 1 Axis and launch inertial frame x R O F y R The included angle of the plane;
the angle gamma is the rolling angle in the projectile trajectory and is a rocket projectile body coordinate system O o x 1 The angle of rotation of the shaft;
wherein: rocket projectile coordinate system O o x 1 y 1 z 1 Origin of coordinates O o Is the center of mass of the rocket projectile, O o x 1 Is the axis of the rocket projectile and points to the head of the rocket projectile; o is o y 1 In the longitudinal symmetry plane of the projectile, perpendicular to O o x 1 ；O o z 1 Perpendicular to the longitudinal plane of symmetry of the projectile, viewed in the direction of launch, z 1 The axis points to the right;
(6) Calculate the antenna body coordinate system Ox a y a z a The arrowed missile points to the vector of the relay satellite
Further obtaining the pointing angles alpha and beta of the phased array antenna;
wherein: alpha (alpha) ("alpha") a The mounting angle of the antenna in the direction of the rocket projectile is shown; beta is a beta a The mounting angle of the antenna on the rocket bomb in pitching is set;
wherein: antenna body coordinate system Ox a y a z a The origin of coordinates O is on the arrow shaft, and Oz is determined when the mounting angle of the antenna on the rocket is 0 degree a Ox of axis and rocket projectile coordinate system 1 Coincident axes of Ox a Oy of axis and arrow coordinate system 1 Axis coincidence, oy a Oz of axis and arrow coordinate system 1 The axes coincide.
In the method for determining the pointing angle of the phased array antenna beam of the rocket-borne relay measurement and control system, in the step (III), the rotation matrix R x ，R y ，R z The expression is as follows:
compared with the prior art, the invention has the following advantages:
(1) The method is suitable for calculating the beam pointing angle of the phased array antenna of the rocket projectile-borne relay measurement and control system, the rocket projectile-satellite space geometric model is established, the coordinates of the rocket projectile body and the coordinates of the relay satellite are converted into the same coordinate system through corresponding coordinate transformation, the concept of a geocentric rectangular inertial coordinate system is innovatively provided in the coordinate transformation process, the operation amount is effectively reduced, the vector of the rocket projectile body pointing to the relay satellite is obtained, the pointing angle of the phased array antenna of the rocket projectile-borne relay measurement and control system pointing to the relay satellite is further deduced, and the problem of calculating the beam pointing angle of the phased array antenna when the rocket projectile-borne relay measurement and control system and the relay satellite establish link communication is effectively solved;
(2) The phased array antenna beam pointing calculation method is simple and easy to implement and strong in operability, an effective and reliable way is provided for calculating the pointing angle of the rocket projectile-borne space-based measurement and control system, a foundation is laid for data transmission of a subsequent space-based measurement and control system, and the development of rocket projectile-borne space-based measurement and control technology in China is promoted to a certain extent;
(3) The rocket projectile-borne relay measurement and control system is used as a new technology and new equipment, and in the rocket projectile flying process, a rocket projectile needs to calculate a pointing angle in real time through the rocket projectile-borne relay measurement and control system phased-array antenna wave beams to point to a relay satellite, so that the relay satellite is tracked; the method for calculating the wave beam pointing of the phased array antenna of the rocket projectile carrier relay measurement and control system can realize that the wave beam of the phased array antenna of the rocket projectile carrier relay measurement and control system points to a relay satellite, has important guiding significance for the development of the rocket projectile carrier relay measurement and control system, and promotes the development of the rocket projectile carrier space-based measurement and control technology.
Drawings
Fig. 1 is a flowchart of a method for calculating a beam pointing angle of a phased array antenna according to the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
Firstly, the coordinates of the relay satellite in the geodetic coordinate system are converted into a geocentric rectangular coordinate system, then are converted into a geocentric rectangular inertial coordinate system, then are converted into a transmitting inertial coordinate system, and are combined with the coordinates in the rocket-borne transmitting inertial coordinate system, so that the vector of the rocket-borne relay measurement and control system phased array antenna pointing to the relay satellite in the transmitting inertial coordinate system is derived
Then will be
Vector converted into rocket projectile coordinate system and pointing to relay satellite by arrow missile-borne relay measurement and control system phased array antenna
Finally, according to the installation angle of the phased array antenna on the rocket projectile
Converted into vector pointing to relay satellite by arrow missile-borne relay measurement and control system phased array antenna in antenna body coordinate system
By
And pointing angles alpha and beta of the rocket missile-borne relay measurement and control system phased array antenna pointing to the relay satellite can be obtained.
Fig. 1 is a flow chart of a method for calculating a beam pointing angle of a phased array antenna according to the present invention, which specifically includes:
the method comprises the following steps of (1) defining the relation between space information of rocket projectiles and relay satellites and the pointing angle of a rocket projectile-borne relay measurement and control system phased-array antenna beam;
the projectile flies with a predetermined trajectory, in space, a target moving relative to the earth, and the relay satellite operates in geostationary orbit, in space, a target stationary relative to the earth. By processing and calculating the projectile trajectory and the relay satellite orbit information, a vector of the projectile body pointing to the relay satellite can be obtained;
the phased array antenna of the rocket missile-borne relay measurement and control system realizes the pointing of the beam fixed point to the relay satellite by controlling the azimuth angle alpha and the pitch angle beta. The azimuth angle alpha represents the direction of the projection of the vector of the rocket projectile pointing to the relay satellite in the cross section of the rocket projectile, and the pitch angle beta represents the included angle between the vector of the rocket projectile pointing to the relay satellite and the axial direction of the rocket projectile.
Determining a coordinate conversion process of phased array antenna beam pointing calculation, and determining each coordinate system involved in the coordinate conversion process;
the trajectory of the rocket projectile comprises attitude information and position information, and the attitude information and the position information are provided by an inertial combination platform of the rocket projectile and are information in an inertial coordinate system; the relay satellite orbit information comprises longitude, latitude and elevation, and is information under a geodetic coordinate system; in order to obtain the vector of the rocket projectile pointing to the relay satellite, the rocket projectile and the relay satellite need to be converted into the same coordinate system, which is as follows:
the geodetic coordinate system (H, λ, B) is defined as: h is the vertical distance of the spatial point to the earth's reference ellipsoid, called the geodetic height. The angle lambda is in the equatorial plane of the reference ellipsoid, is the angle of the projection from the initial meridian plane to the east to the sagittal diameter of the space point in the equatorial plane and is called the geodetic longitude, the angle B is the included angle between the equatorial plane and the normal line of the reference ellipsoid passing through the space point and is called the geodetic latitude, and the north direction is positive.
Earth center rectangular coordinate system OX R Y R Z R Is defined as: the origin O of the coordinate system is at the geocentric. OX R In the equatorial plane, points to the meridian on which the Greenwich astronomical instrument is located, OZ R The axis is directed perpendicular to the equatorial plane towards the north pole. OX R Y R Z R And forming a right-hand rectangular coordinate system. Due to the coordinates OX R And the pointed meridian rotates with the earth, so that the coordinate system is a dynamic reference system.
Earth's center rectangular inertial coordinate system OX I Y I Z I At the moment of rocket projectile take-off, the earth's center rectangular inertial coordinate system OX I Y I Z I Orthogonal coordinate system OX with earth center R Y R Z R And (4) overlapping. Earth center rectangular inertial coordinate system OX I Y I Z I Remain stationary in inertial space;
emission inertial frame O F x R y R z R At the moment of emission, the origin of coordinates is the emission point O F ，O F x R The axis being in the horizontal plane of the launch point and pointing in the launch aiming direction, O F y R The axis pointing upwards perpendicular to the horizontal plane of the emission point, O F z R Axis and x R O F y R The planes are vertical to form a right-hand coordinate system, and the transmitting inertial coordinate system is kept still in an inertial space;
rocket projectile coordinate system O o x 1 y 1 z 1 Origin of coordinates O o Is the center of mass of the projectile. O is o x 1 Is the axis of the rocket projectile and points to the head part of the rocket projectile; o is o y 1 In the longitudinal symmetry plane of the projectile, perpendicular to O o x 1 ；O o z 1 Perpendicular to the longitudinal plane of symmetry of the projectile, viewed in the direction of launch, z 1 The axis is directed to the right. O is o x 1 y 1 z 1 Is a right-hand rectangular coordinate system. The coordinate system reflects the posture of the projectile in the air at the position of the space;
antenna body coordinate system Ox a y a z a The origin of coordinates O is on the arrow shaft, and Oz is when the mounting angle of the antenna on the rocket projectile is 0 degree a Axis and rocket projectile coordinate system Ox 1 The axes coincide with each other, ox a Oy of axis and arrow coordinate system 1 Axis coincidence, oy a Oz of axis and arrow coordinate system 1 The axes coincide. When the mounting angle of the antenna on the rocket projectile is not 0 degree, the coordinates of the antenna body coordinate system are obtained by performing corresponding coordinate transformation on the coordinates of the rocket projectile body coordinate system according to the mounting angle.
Step three, finishing calculation of the pointing angle of the wave beam of the phased array antenna of the rocket missile-borne relay measurement and control system according to the determined coordinate conversion relation;
(1) Converting coordinates (H, lambda, B) of the relay satellite in the geodetic coordinate system to coordinates (X) in the geocentric rectangular coordinate system R ，Y R ，Z R )：
Wherein N is the radius of the unitary-mortise circle of the earth,
a is the equator radius of the earth, and e is the first eccentricity of the earth;
(2) Coordinates (X) of relay satellite in a geocentric rectangular coordinate system R ，Y R ，Z R ) Conversion to coordinates (X) in the Earth's center rectangular inertial frame I ，Y I ，Z I )：
Wherein R is Z Is a rotation matrix, omega is the rotational angular velocity of the earth, and t is the flight time of the projectile.
(3) Relaying coordinates (X) of the satellite in the Earth's center rectangular inertial frame I ，Y I ，Z I ) Conversion to coordinates (x) in the transmit inertial frame R ，y R ，z R )：
In the formula (X) OF ，Y OF ，Z OF ) Is the coordinate of the emitting point in the earth's center rectangular inertial coordinate system, alpha OF 、
And λ OF Respectively, the geodetic azimuth, the geodetic longitude and the geodetic latitude of the transmitting point. R is x ，R y ，R z For the rotation matrix:
the rotation matrix expression is:
(4) Calculating a transmit inertial coordinate system O F Vector of xyz arrowhead pointing to relay satellite
In the formula (x) m ，y m ，z m ) As coordinates of rocket projectile in inertial coordinate system of launching。
(5) Calculating rocket projectile coordinate system O o x 1 y 1 z 1 The arrowed missile points to the vector of the relay satellite
In the formula (x) o ，y o ，z o ) Coordinates of the rocket projectile pointing to the relay satellite in a coordinate system of the rocket projectile body.
Corner
For rocket projectile coordinate system O o x 1 Axial in-transmit inertial frame x R O F y R Projection amount on plane and O F x R Angle of axis projected on O F x R A positive angle is arranged above the shaft;
the angle theta is called the yaw angle in the projectile trajectory and is the projectile body coordinate system O o x 1 Axis and launch inertial frame x R O F y R Angle of plane, O o x 1 Axis in x R O F y R To the left of the plane, the plane is,
taking the angle as a positive value;
the angle gamma is called the rolling angle in the rocket projectile trajectory and is a coordinate system O of the rocket projectile around the rocket projectile body o x 1 Angle of rotation of the shaft, when angular velocity vector of rotation is equal to O o x 1 If the axes are aligned, the angle γ takes a positive value.
(6) Calculate the antenna body coordinate system Ox a y a z a The arrowed missile points to the vector of the relay satellite
Further solving the pointing angles alpha and beta of the phased array antenna:
the above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (2)
1. The method for determining the pointing angle of the phased array antenna beam of the rocket missile-borne relay measurement and control system is characterized by comprising the following steps of:
(1) Converting coordinates (H, lambda, B) of the relay satellite in the geodetic coordinate system to coordinates (X) in the geocentric rectangular coordinate system R ，Y R ，Z R )：
Wherein: n is the radius of the prime circle of the earth,
a is the equator radius of the earth, and e is the first eccentricity of the earth; h is the vertical distance from the space point to the earth reference ellipsoid, called the geodetic height; the angle λ is in the equatorial plane of the reference ellipsoid and is from the start meridian plane east to the sagittal axis of the space point at the equatorThe angle of the projection in the plane, called the geodetic longitude; the angle B is the included angle between the equatorial plane and the normal line of the reference ellipsoid passing through the space point, is called the geodetic latitude, and is positive in the north direction;
(2) Coordinates (X) of relay satellite in geocentric rectangular coordinate system R ，Y R ，Z R ) Conversion to coordinates (X) in the Earth's center rectangular inertial frame I ，Y I ，Z I )：
Wherein: r Z Is a rotation matrix, omega is the rotation angular velocity of the earth, and t is the flight time of the rocket projectile;
earth center rectangular coordinate system OX R Y R Z R Is defined as follows: origin O of coordinate system at geocentric, OX R Pointing to meridian where Green-forming Zengzhu celestial platform is located in equatorial plane, OZ axis perpendicular to equatorial plane pointing to north pole, OX R Y R Z R Forming a right-hand rectangular coordinate system;
earth's center rectangular inertial coordinate system OX I Y I Z I At the moment of takeoff of rocket projectile, OX is orthogonal coordinate system with the earth center R Y R Z R Coincident and centroidal rectangular inertial frame OX I Y I Z I The inertia space is kept still;
(3) Relaying coordinates (X) of the satellite in the Earth's center rectangular inertial frame I ，Y I ，Z I ) Conversion to coordinates (x) in the transmit inertial frame R ，y R ，z R )
Wherein: (X) OF ，Y OF ，Z OF ) Is the coordinate of the emitting point in the centroid rectangular inertial coordinate system, alpha OF 、
And λ OF The geodetic azimuth, the geodetic longitude and the geodetic latitude of the transmitting point are respectively; r is x ，R y ，R z Is a rotation matrix;
emission inertial frame O F x R y R z R At the moment of emission, the origin of coordinates is the emission point O F ，O F x R The axis is in the horizontal plane of the emission point and points to the emission aiming direction, O F y R The axis pointing upwards perpendicular to the horizontal plane of the emission point, O F z R Axis and x R O F y R The surfaces are vertical to each other and form a right-hand coordinate system, and the emission inertia coordinate system keeps still in an inertia space;
(4) Calculating a transmit inertial coordinate system O F x R y R z R The arrowed missile points to the vector of the relay satellite
Wherein: (x) m ，y m ，z m ) The coordinates of the rocket projectile under the launching inertial coordinate system are obtained;
(5) Calculating rocket projectile coordinate system O o x 1 y 1 z 1 The arrowed missile points to the vector of the relay satellite
Wherein: (x) o ，y o ，z o ) The coordinates of the arrow missile pointing to the relay satellite in the arrow missile coordinate system;
corner
As rocket projectile coordinate system O o x 1 Axial in-transmit inertial frame x R O F y R Projection on plane and O F x R The included angle of the axes;
the angle theta is the yaw angle in the rocket projectile trajectory and is the rocket projectile coordinate system O o x 1 Axis and launch inertial frame x R O F y R The included angle of the plane;
the angle gamma is the rolling angle in the projectile trajectory and is a rocket projectile body coordinate system O o x 1 The angle of rotation of the shaft;
wherein: rocket projectile coordinate system O o x 1 y 1 z 1 Origin of coordinates O o Is the center of mass of the rocket projectile, O o x 1 Is the axis of the rocket projectile and points to the head of the rocket projectile; o is o y 1 In the longitudinal symmetry plane of the projectile, perpendicular to O o x 1 ；O o z 1 Perpendicular to the longitudinal plane of symmetry of the projectile, viewed in the direction of launch, z 1 The axis points to the right;
(6) Calculate the antenna body coordinate system Ox a y a z a The arrowed missile points to the vector of the relay satellite
Further obtaining the pointing angles alpha and beta of the phased array antenna;
wherein: alpha is alpha a The mounting angle of the antenna in the direction of the rocket projectile is set; beta is a a The mounting angle of the antenna on the rocket projectile in pitching is shown;
wherein: antenna body coordinate system Ox a y a z a The origin of coordinates O is on the arrow shaft, and Oz is when the mounting angle of the antenna on the rocket projectile is 0 degree a Axis and rocket projectile coordinate system Ox 1 The axes coincide with each other, ox a Oy of axis and rocket body coordinate system 1 Coincident axes, oy a Oz of axis and rocket body coordinate system 1 The axes coincide.
2. The method for determining the pointing angle of the phased-array antenna beam of the rocket-borne relay measurement and control system according to claim 1, characterized in that: the rotation matrix R x ，R y ，R z The expression is as follows:
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107831502A (en) * | 2017-10-17 | 2018-03-23 | 中国科学院电子学研究所 | Satellite points to the computational methods of angle approximation |
| CN114036780A (en) * | 2021-12-06 | 2022-02-11 | 航天科工火箭技术有限公司 | Rocket attitude angle design method constrained by space-based measurement and control |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107831502A (en) * | 2017-10-17 | 2018-03-23 | 中国科学院电子学研究所 | Satellite points to the computational methods of angle approximation |
| CN107831502B (en) * | 2017-10-17 | 2023-05-09 | 中国科学院电子学研究所 | Method for calculating satellite pointing included angle approximation |
| CN114036780A (en) * | 2021-12-06 | 2022-02-11 | 航天科工火箭技术有限公司 | Rocket attitude angle design method constrained by space-based measurement and control |
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