CN111290436A - Aircraft wireless instruction correction method and system - Google Patents
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Abstract
The invention provides an aircraft wireless instruction correction method and system, which comprise a flight mission range determining module, a flight trajectory model determining module, an instruction correction capability parameter table forming module, new target point acquiring equipment, an aircraft flight distance determining module, an instruction correction distance determining module, a target correction distance module, a maximum target correction distance module and a correction judging module. The invention reduces the flight position estimation error and improves the accuracy of the instruction correction capability of the estimated aircraft under the condition of a simplex instruction correction system; the invention adopts the aerial flight position of the aircraft under the multi-constraint condition to obtain the instruction correction capability of the aircraft, and can ensure effective execution of wireless instruction correction.
Description
Technical Field
The invention relates to an aircraft wireless instruction correction method and system, and belongs to the technical field of guidance control.
Background
When an aircraft adopting a simplex instruction correction mode strikes a time-sensitive target, the enemy time of the aircraft is required to be shortened as much as possible, and the weapon combat efficiency is improved. And the target detection capability and the capture accuracy are deteriorated due to the influence of factors such as target concealment and the like. Therefore, the target detection accuracy and the combat aging are in conflict. The ground command system can launch the aircraft only by mastering the initial position of the target and a possibly scattered area by using the aircraft of the wireless instruction correction system, further determines the maneuvering elements of the target in the flight process, and sends the maneuvering elements to the aircraft through the correction system, so that the target hit probability is improved. And the aircraft adopts a simplex instruction correction mode, so that the ground command system cannot acquire the current accurate position of the aircraft, and the instruction correction capability of the aircraft cannot be accurately estimated.
Under different launching environmental conditions, the position of the aircraft is very widely dispersed, and if a conservative estimation mode is adopted, the estimation of the instruction correction capability of the aircraft has a very large error, so that the combat efficiency of the aircraft cannot be fully exerted. In the prior art, a preset flight trajectory is generally obtained by taking a target initial position, a launching speed, a launching sector and the like as input constraint conditions, and the preset flight trajectory has a certain difference from a flight trajectory in a real flight process, so that a position information error obtained by estimation according to the preset flight trajectory is large. Therefore, a method for reducing flight position estimation errors, accurately estimating the instruction correction capability of the aircraft and providing a decision of the ground command system on whether to execute the instruction correction under various constraint conditions such as emission conditions, the self dynamic characteristics of the aircraft, the control capability, the maneuvering capability and the like is needed to be designed.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides an aircraft wireless instruction correction method and system for reducing flight position estimation errors and accurately estimating the instruction correction capability of an aircraft.
The technical solution of the invention is as follows: an aircraft wireless instruction correction method is realized by the following steps:
firstly, determining flight mission range R of aircraftmt；
Secondly, determining a flight path model under multiple constraint conditions,
a2.1, selecting a key state point on a preset flight track;
a2.2, determining a speed calculation model of the key state point selected in the step A2.1;
a2.3, fitting to obtain an aircraft flight speed calculation model according to the speed calculation model of each key state point obtained in the step A2.2;
a2.4, obtaining a flight track model under multiple constraint conditions according to the aircraft flight speed calculation model obtained in the step A2.3;
thirdly, forming a command correction capability parameter table;
fourthly, acquiring the position information of the new target point, wherein the acquisition time is the current time;
fifthly, determining the flying distance S of the aircraft at the current moment according to the flying track model determined in the second stepfx；
Sixthly, obtaining the command correction distance R of the current moment according to the flight mission range determined in the first step and the flight distance of the aircraft at the current moment determined in the fifth stepxz；
Seventhly, determining a target correction distance L according to the initial target point and the position information of the new target point acquired in the fourth stepxz；
Eighth step, correcting the distance R according to the instruction obtained in the sixth stepxzDetermining the maximum target correction distance L allowed at the current time by using the instruction correction capability parameter table formed in the third stepxz max；
Ninth, the target correction distance L obtained in the seventh step is usedxzThe maximum target correction distance L allowed by the current time obtained in the eighth stepxz maxJudging whether L is satisfiedxz≤Lxz maxIf the instruction correction is not satisfied, the instruction correction capability of the aircraft is exceeded, and the instruction correction is not executed.
A wireless instruction correction system of an aircraft comprises a flight mission range determining module, a flight path model determining module, an instruction correction capability parameter table forming module, new target point acquiring equipment, an aircraft flight distance determining module, an instruction correction distance determining module, a target correction distance module, a maximum target correction distance module and a correction judging module;
the flight mission range determining module determines a flight mission range according to the initial launching point and the initial target point information;
the flight path model determining module obtains flight path models under multiple constraint conditions;
the instruction correction capability parameter table forming module forms an instruction correction capability parameter table;
the new target point acquisition equipment acquires the position information of the new target point;
the aircraft flight distance determining module obtains the flight distance of the aircraft at the current moment according to the flight track model under the multi-constraint condition determined by the flight track model determining module;
the instruction correction distance determining module obtains an instruction correction distance at the current moment according to the flight mission range obtained by the flight mission range determining module and the flight distance of the aircraft at the current moment obtained by the aircraft flight distance determining module;
the target correction distance module obtains a target correction distance at the current moment according to the initial target point and the new target point position information obtained by the new target point obtaining equipment;
the maximum target correction distance module obtains the maximum target correction distance allowed at the current moment through interpolation according to the instruction correction capability parameter table formed by the instruction correction capability parameter table forming module and the instruction correction distance obtained by the instruction correction distance determining module;
the correction judging module compares the maximum target correction distance allowed at the current moment obtained by the maximum target correction distance module with the target correction distance allowed at the current moment obtained by the target correction distance module, if the target correction distance at the current moment is less than or equal to the maximum target correction distance allowed at the current moment, a correction instruction is sent to the aircraft, and if the target correction distance at the current moment is greater than the maximum target correction distance allowed at the current moment, the correction instruction is not sent to the aircraft.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention reduces the flight position estimation error and improves the accuracy of the instruction correction capability of the estimated aircraft under the condition of a simplex instruction correction system;
(2) the invention adopts the aerial flight position of the aircraft under the multi-constraint condition to obtain the instruction correction capability of the aircraft, thereby ensuring effective execution of wireless instruction correction;
(3) the invention adopts the instruction correction capability parameter table, obtains accurate judgment basis through interpolation, and further improves the effective execution of wireless instruction correction;
(4) the invention solves the contradiction between the target detection precision and the combat timeliness, improves the combat efficiency, and achieves the expected effect through the verification of simulation and multiple flight tests.
Drawings
FIG. 1 is a flow chart of the present invention;
FIG. 2 is a block diagram of the present invention.
Detailed Description
The present invention will be described in detail with reference to the following examples and accompanying drawings.
The invention provides an aircraft wireless instruction correction method as shown in fig. 1, which is realized by the following steps:
firstly, determining flight mission range R of aircraftmt；
The step can obtain the distance between the initial launching point and the initial target point, namely the flight mission range R of the aircraft according to the information of the initial launching point and the initial target point in the combat mission parameters of the aircraftmt。
The combat mission parameters of the aircraft mainly comprise an initial launching point, initial target point information, a launching sector, an initial attitude and the like, and are preset values.
Secondly, determining a flight path model under multiple constraint conditions,
a2.1, selecting a key state point on a preset flight track;
the key state point selection is generally an aerodynamic profile change point and a power transition point, and can be selected by a person skilled in the art according to the condition of the aircraft.
A2.2, determining a speed calculation model of the key state point selected in the step A2.1;
according to the method, a speed calculation model of each selected key state point is obtained by adopting a ballistic simulation method according to a launching sector in combat mission parameters and taking environmental conditions (wind speed, temperature and the like), aircraft dynamic characteristics and attitude control capability as input conditions;
a2.3, fitting to obtain an aircraft flight speed calculation model according to the speed calculation model of each key state point obtained in the step A2.2;
the fitting method in this step is well known in the art, and those skilled in the art can select an appropriate fitting method according to the form of the velocity calculation model.
A2.4, obtaining a flight track model under the multi-constraint condition of the formula (1) according to the aircraft flight speed calculation model obtained in the step A2.3;
wherein SfxIs the flight distance of the aircraft, VnxFor the model of the aircraft flight velocity calculation, t is time.
Thirdly, forming a command correction capability parameter table;
calculating the corresponding relation between the missile-target distance (instruction correction distance) and the maximum target correction distance according to the maneuvering overload capacity of the aircraft and the aircraft flight speed calculation model determined in the second step to form an instruction correction capacity parameter table;
this step calculation is well known in the art.
Fourthly, acquiring the position information of the new target point, wherein the acquisition time is the current time;
the ground command system in this step can be obtained by various detection means such as radar, satellite and the like, and the new target point can be the new position of the initial target or the new target after adjustment.
Fifthly, determining the flying of the aircraft at the current moment according to the flying track model determined in the second stepLine distance Sfx；
Sixthly, obtaining the command correction distance R of the current moment according to the flight mission range determined in the first step and the flight distance of the aircraft at the current moment determined in the fifth stepxz；
Obtaining an instruction correction distance R by adopting a formula (2)xz，
Rxz＝Rmt-Sfx(2)。
Seventhly, determining a target correction distance L according to the initial target point and the position information of the new target point acquired in the fourth stepxz；
The target correction distance in this step is the distance from the point to be corrected (initial target point) to the corrected target point (new target point at the current moment), and the information of the geodetic distance between the two points is obtained by resolving according to the longitude and latitude information of the two points, namely the target correction distance Lxz。
Eighth step, correcting the distance R according to the instruction obtained in the sixth stepxzDetermining the maximum target correction distance L allowed at the current time by using the instruction correction capability parameter table formed in the third stepxz max；
In this step, the capability parameter table is corrected according to the formed instruction and the instruction correction distance R obtained in the sixth stepxzAnd obtaining the maximum target correction distance L allowed at the current moment by interpolationxz maxInterpolation calculations are well known in the art.
Ninth, the target correction distance L obtained in the seventh step is usedxzThe maximum target correction distance L allowed by the current time obtained in the eighth stepxz maxJudging whether L is satisfiedxz≤Lxz maxIf the instruction correction is not satisfied, the instruction correction capability of the aircraft is exceeded, and the instruction correction is not executed.
In this step, if L is satisfiedxz≤Lxz maxIf the L does not meet the requirement, the ground command system sends a correction instruction to the aircraft, the aircraft executes the correction instruction after receiving the correction instruction, and if the L does not meet the requirement, the ground command system sends a correction instruction to the aircraftxz≤Lxz maxIf the command is beyond the command correction capability of the aircraft, the ground command system does not execute command correction, and does not execute command correctionAnd sending a correction instruction to the aircraft. And the information included in the correction instruction is the position information of the new target point.
Further, as shown in fig. 2, the present invention further provides an aircraft wireless instruction correction system, which includes a flight mission range determining module, a flight trajectory model determining module, an instruction correction capability parameter table forming module, a new target point obtaining device, an aircraft flight distance determining module, an instruction correction distance determining module, a target correction distance module, a maximum target correction distance module, and a correction judging module.
And the flight mission range determining module determines the flight mission range according to the initial launching point and the initial target point information.
The flight path model determining module selects key state points on a preset flight path, fits the speed calculation model of the selected key state points to obtain an aircraft flight speed calculation model, and then obtains a flight path model under a multi-constraint condition according to the aircraft flight speed calculation model.
And the instruction correction capability parameter table forming module determines an aircraft flight speed calculation model fitted by the module according to the aircraft maneuvering overload capability and the flight path model, calculates to obtain the corresponding relation between the missile target distance and the maximum target correction distance, and forms an instruction correction capability parameter table.
The new target point acquisition device acquires position information of the new target point.
The aircraft flying distance determining module obtains the flying distance of the aircraft at the current moment according to the flying track model determined by the flying track model determining module under the multi-constraint condition.
And the instruction correction distance determining module obtains the instruction correction distance at the current moment according to the flight mission range obtained by the flight mission range determining module and the flight distance of the aircraft at the current moment obtained by the aircraft flight distance determining module.
And the target correction distance module obtains the target correction distance at the current moment according to the initial target point and the new target point position information obtained by the new target point obtaining equipment.
The maximum target correction distance module obtains the maximum target correction distance allowed at the current time through interpolation according to the instruction correction capability parameter table formed by the instruction correction capability parameter table forming module and the current time instruction correction distance obtained by the instruction correction distance determining module.
And the correction judging module compares the maximum target correction distance allowed at the current moment and obtained by the maximum target correction distance module with the target correction distance allowed at the current moment, sends a correction instruction to the aircraft if the target correction distance at the current moment is less than or equal to the maximum target correction distance allowed at the current moment, and does not send the correction instruction to the aircraft if the target correction distance at the current moment is greater than the maximum target correction distance allowed at the current moment.
Example 1
A simplex instruction correction system is adopted for a certain type of aircraft, and the combat mission parameters are as follows: initial emission point (121.0E, 40.0N), initial target point information (121.0E, 40.9N)
The correction steps are as follows:
1. calculating the flight mission range R according to the information of the initial launching point and the initial target point in the combat mission parametersmt＝100km。
2. And determining a flight track model under multiple constraint conditions.
Determines T from the preset flight path1、T2、T3As a key state point, the battle mission emits a sector psi0Taking environmental conditions (wind speed, temperature and the like), aircraft dynamic characteristics and attitude control capability as input conditions, and obtaining a corresponding typical speed V by adopting a ballistic simulation methodnx1,Vnx2,Vnx3。
Fitting to obtain a flight speed calculation model of the aircraft,
wherein k is1Is the velocity slope, t is time.
The flight path model is
3. The command modification capability parameter table is formed as follows according to the maneuvering overload capability of the aircraft.
| Command correction distance (km) | 60 | 50 | 40 |
| Maximum target correction Range (km) | 38 | 30 | 22 |
4. The ground command system acquires new target information (21.09494E, 40.9N) through radar, and t is 200.0s after the current time point is the flight zero point.
5. Calculating to obtain the flight distance S of the current momentfx＝46km。
6. Calculating an instruction correction distance R according to the flight mission range and the current flight distance of the aircraftxz＝Rmt-Sfx＝100-46＝54km。
7. Calculating the target correction distance L according to the information of the initial target point and the new target pointxz＝8km。
8. According to the target correction distance and the instruction correction distance at the current moment, the maximum target correction distance L allowed at the current moment is obtained by interpolation by using an instruction correction capability parameter tablexz max＝33.2km。
9. Judgment of Lxz≤Lxz maxIf yes, the ground command system allows to execute command correction and flyThe device sends a correction instruction.
Example 2
The flight vehicle adopts a simplex command correction system, and a ground command system is provided with a flight vehicle wireless command correction system which comprises a flight mission range determining module, a flight path model determining module, a command correction capability parameter table forming module, new target point acquiring equipment, a flight distance determining module of the flight vehicle, a command correction distance determining module, a target correction distance module, a maximum target correction distance module and a correction judging module.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (10)
1. An aircraft wireless instruction correction method is characterized by comprising the following steps:
firstly, determining flight mission range R of aircraftmt；
Secondly, determining a flight path model under multiple constraint conditions,
a2.1, selecting a key state point on a preset flight track;
a2.2, determining a speed calculation model of the key state point selected in the step A2.1;
a2.3, fitting to obtain an aircraft flight speed calculation model according to the speed calculation model of each key state point obtained in the step A2.2;
a2.4, obtaining a flight track model under multiple constraint conditions according to the aircraft flight speed calculation model obtained in the step A2.3;
thirdly, forming a command correction capability parameter table;
fourthly, acquiring the position information of the new target point, wherein the acquisition time is the current time;
fifthly, determining the flying distance S of the aircraft at the current moment according to the flying track model determined in the second stepfx；
Sixthly, obtaining the command correction distance R of the current moment according to the flight mission range determined in the first step and the flight distance of the aircraft at the current moment determined in the fifth stepxz；
Seventhly, determining a target correction distance L according to the initial target point and the position information of the new target point acquired in the fourth stepxz；
Eighth step, correcting the distance R according to the instruction obtained in the sixth stepxzDetermining the maximum target correction distance L allowed at the current time by using the instruction correction capability parameter table formed in the third stepxzmax；
Ninth, the target correction distance L obtained in the seventh step is usedxzThe maximum target correction distance L allowed by the current time obtained in the eighth stepxzmaxJudging whether L is satisfiedxz≤LxzmaxIf the instruction correction is not satisfied, the instruction correction capability of the aircraft is exceeded, and the instruction correction is not executed.
2. The aircraft wireless command correction method of claim 1, characterized in that: and in the step A2.2, a speed calculation model of each selected key state point is obtained by adopting a ballistic simulation method according to the launching sector in the combat mission parameter and taking the environmental condition, the dynamic characteristic of the aircraft and the attitude control capability as input conditions.
3. The aircraft wireless command correction method of claim 1, characterized in that: and B, selecting key state points in the step A2.1 as a pneumatic appearance change point and a power gear shifting point.
4. The aircraft wireless command correction method of claim 1, characterized in that: the flight path model under the multi-constraint condition in the step A2.4 is a formula (1),
wherein SfxIs the flight distance of the aircraft, VnxFor the model of the aircraft flight velocity calculation, t is time.
5. The aircraft wireless command correction method of claim 1, characterized in that: and in the third step, calculating the corresponding relation between the missile-target distance and the maximum target correction distance according to the maneuvering overload capacity of the aircraft and the aircraft flight speed calculation model determined in the second step to form an instruction correction capacity parameter table.
6. The aircraft wireless command correction method of claim 1, characterized in that: in the sixth step, the instruction correction distance R is obtained by adopting a formula (2)xz，
Rxz＝Rmt-Sfx(2)。
7. The aircraft wireless command correction method of claim 1, characterized in that: in the first step, the distance between the initial launching point and the initial target point, namely the flight mission range R of the aircraft, can be obtained according to the information of the initial launching point and the initial target point in the combat mission parameters of the aircraftmt。
8. An aircraft wireless command correction system, characterized by: the system comprises a flight mission range determining module, a flight trajectory model determining module, a command correction capability parameter table forming module, new target point acquiring equipment, an aircraft flight distance determining module, a command correction distance determining module, a target correction distance module, a maximum target correction distance module and a correction judging module;
the flight mission range determining module determines a flight mission range according to the initial launching point and the initial target point information;
the flight path model determining module obtains flight path models under multiple constraint conditions;
the instruction correction capability parameter table forming module forms an instruction correction capability parameter table;
the new target point acquisition equipment acquires the position information of the new target point;
the aircraft flight distance determining module obtains the flight distance of the aircraft at the current moment according to the flight track model under the multi-constraint condition determined by the flight track model determining module;
the instruction correction distance determining module obtains an instruction correction distance at the current moment according to the flight mission range obtained by the flight mission range determining module and the flight distance of the aircraft at the current moment obtained by the aircraft flight distance determining module;
the target correction distance module obtains a target correction distance at the current moment according to the initial target point and the new target point position information obtained by the new target point obtaining equipment;
the maximum target correction distance module obtains the maximum target correction distance allowed at the current moment through interpolation according to the instruction correction capability parameter table formed by the instruction correction capability parameter table forming module and the instruction correction distance obtained by the instruction correction distance determining module;
the correction judging module compares the maximum target correction distance allowed at the current moment obtained by the maximum target correction distance module with the target correction distance allowed at the current moment obtained by the target correction distance module, if the target correction distance at the current moment is less than or equal to the maximum target correction distance allowed at the current moment, a correction instruction is sent to the aircraft, and if the target correction distance at the current moment is greater than the maximum target correction distance allowed at the current moment, the correction instruction is not sent to the aircraft.
9. The aircraft wireless command correction system of claim 8, wherein: the flight path model determining module selects key state points on a preset flight path, fits the speed calculation model of the selected key state points to obtain an aircraft flight speed calculation model, and obtains a flight path model under a multi-constraint condition according to the aircraft flight speed calculation model;
10. the aircraft wireless command correction system of claim 8, wherein: the instruction correction capability parameter table forming module determines an aircraft flight speed calculation model fitted by the module according to the aircraft maneuvering overload capability and the flight path model, calculates to obtain the corresponding relation between the missile target distance and the maximum target correction distance, and forms an instruction correction capability parameter table.
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