JPH01263499A - Programmed guidance system - Google Patents

Abstract

PURPOSE:To enable a missile to be positively met with a target by a method wherein even if an orbit of the target or its position is varied after an emission of the missile, an orbit data is corrected. CONSTITUTION:A orbit or a position of a target 19 is calculated and if this orbit or position is different from a calculated orbit or position, a signal 4 having an orbit connecting command and a correction orbit data combined to each other is transmitted toward a missile 18. This signal 6 is received by a command receiving unit 7 of the missile, a switch 9 is changed over by the orbit correction command 8 to store the correction orbit data 26 in an orbit data memory device b11. After storing the correction orbit data 26, the command receiving unit 7 may output an orbit correction data transmission completing command 13, the switch 12 is changed over to the orbit data memory device b11 and then the correction orbit data 26 is outputted to the guiding signal calculator 16. At the guiding signal calculator 16, position, posture, speed and acceleration data 15 of the missile outputted from the inertia device 14 are compared with the correction orbit data 26; thereby, the guiding signal 17 is calculated and then the missile is guided to an expected meeting point.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a program guidance device for a flying object.

[Conventional technology]

A conventional program guiding device is shown in FIG. In the figure, αα is a trajectory data storage device in which programmed trajectory data is stored; 9. Q3 is orbit data that is output multiple times from the orbit data storage device α0.

Q4 is an inertial device, a9 is a device constituted by this inertial device, attitude, velocity, and acceleration data, α61u guidance signal calculator, and 0η are acceleration command data of the flying object.

All of the above devices were installed on the flying vehicle and guided the flying vehicle to the expected rendezvous point by comparing the output data from the inertial device with the trajectory data programmed before the launch of Shi-2.

[Problem to be solved by the invention]

If the trajectory position of the target changes after one firing in the conventional program guidance device, it will be impossible to guide it to the target because it has no correction means.

Figure 4 shows an example of a surface-to-air missile α-Cho, in which the initial and middle stages are programmed guidance and the final stage is brought to the target by homing guidance. In conventional program guidance, the target θ value deviates from the initial predicted trajectory due to maneuver (21), and the target 0I deviates from the lock-on possible angle Qω and lock-on possible range of the surface-to-air missile α ladder. There was a problem in that the surface-to-air missile (I) could not be programmed to be guided to a position where it could lock on to target 09, which is necessary for transitioning to homing guidance.

The present invention has been made to solve the above-mentioned problems, and an object of the present invention is to provide a program guidance device that can correct programmed trajectory data after launching a flying object.

[Means to solve the problem]

The program guidance device in this invention has two storage devices installed inside the flying body, the first storage device is used to store trajectory data before correction, and the second storage device is used to store trajectory data before correction. This storage device is used to store corrected trajectory data, and when the sending of corrected trajectory data sent from IP etc. is completed, switching from the first storage device to the second storage device allows the body to fly to the corrected trajectory. It is a guide.

[Effect]

The neuronoram reading device (according to this invention) adds 1j to the trajectory or position of the target, and if the trajectory or position of the target is deviated, calculates new trajectory data from the above measured trajectory or position. The flying object can be guided to the target by transmitting it to the flying object and correcting the programmed trajectory data before the target's trajectory or position deviates.

[Embodiments of the invention]

FIG. 1 shows an embodiment of the present invention. In the figure, a target measuring device (1) and a trajectory calculator (3).

The command transmitter (5) is installed at a location different from the flying object, for example, on the ground. Target measuring device (1)
tracks the target 01 and outputs data (2) such as the position and speed of the target 01 to the trajectory calculator (3). Orbit calculator (3
) is calculated based on the above data (2) and the trajectory or position of the target ([9 is different from the trajectory or position calculated by the trajectory calculator (3) p before this).

A signal (4) in which a trajectory correction command and Fz normal trajectory data are combined is transmitted from a command transmitter (5) as a high frequency signal (6) such as a microwave to the flying object. Receive this No. 46 (6) with the command receiver (7) on the side of the flying body, switch the switch (9) with the orbit correction command (8), and send the corrected orbit data (2) to the orbit data storage device b. (II). Before the corrected trajectory data (A) is stored, the trajectory data in the trajectory data storage device aQcl is output to the guidance signal calculator aO, but the corrected trajectory data (to) is stored in the trajectory data storage. After being stored in device 1) (11), the command receiver (l) outputs orbit correction data sending completion command 09, switches switch 2 to the orbit data storage device bO1l side, and guides the correction trajectory data (to). Signal calculation &A (output to IO.

In the guidance signal calculator a6), the above-mentioned normal orbit data (a)
By comparing the position, attitude, velocity, and acceleration data α9 of the flying object output from the inertial device α, a guidance signal OD is calculated, and the flying object is guided to the predicted meeting point.

As a result of the above, for example, as shown in Figure 2, the target (1!l is a large air maneuver 01lj, but the program guidance device changes the initial trajectory (21) of the surface-to-air missile OQ to the corrected trajectory (23), In order to bring the surface-to-air missile (01) to the target 01 at the rendezvous point, guide the surface-to-air missile 01 to a position where it can capture the target 01 within the lock-on angle and within the lock-on range. Corrected trajectory of surface-to-air missile 08 (24 is.

Trajectory data storage device a (L[l and trajectory data storage device b
It can be corrected multiple times by alternately switching συ.

Note that although the above embodiments have been described with reference to the case where the target is in the air, the present invention can be similarly applied regardless of whether the target is located anywhere, such as a ground target or a sea target.

〔Effect of the invention〕

As described above, according to the present invention, even if the trajectory or position of the target changes after the flying object is launched, the flying object can be reliably brought to the target by correcting the trajectory data. This has the advantage that it is possible to provide a program guiding device that can perform the following tasks.

[Brief explanation of the drawing]

Fig. 1 is a schematic diagram showing an embodiment of the program guidance device according to the present invention, Fig. 2 is an explanatory diagram showing the effect of the invention when the target makes a large maneuver in the air, and Fig. 3 is a conventional program guidance device. FIG. 4 is an explanatory diagram when the target makes a large maneuver in the air using the conventional program guidance method. +1+ is target measuring device, +3) i-j, trajectory calculator,
(5) is a command transmitter, (7) is a command receiver,
(91, (1'21 is a switch, (11 is a trajectory data storage device a, (lυ is a trajectory data storage device), (131 is a trajectory correction data sending completion command, 04I is an inertial device,
00 is a guidance signal calculator, α barrel is a surface-to-air missile, aIH
Target, ■ is the initial trajectory, Cυ is the maneuver, (2 is the corrected trajectory, +23 is the possible lock-on range, (2 is the predicted meeting point, I23 is the possible lock-on angle. (A) is the corrected trajectory data, C7) is the initial predicted trajectory. In Figure 1, the same or equivalent parts are given the same reference numerals.

Claims (1)

[Claims] A device that tracks a target and measures its position, speed, etc., and calculates a target trajectory or position from the measured values of this measurement device, and determines whether this target trajectory or position was the previous target trajectory or position before calculating this target trajectory or position. a trajectory calculator that calculates corrected trajectory data to the flying object if the position is different; a command transmitter that sends a trajectory correction command and the corrected trajectory data to the flying object; and a command that receives the command and the corrected trajectory data. a receiver, a first trajectory data storage device that stores trajectory data before the trajectory is corrected, and a second trajectory data storage device that stores the corrected trajectory data;
An inertial device that measures the position, attitude, velocity, and acceleration of the flying object, and a guidance signal is calculated by comparing the output of this inertial device with the trajectory data output from the first or second trajectory data storage device. A program guidance device characterized by comprising a guidance signal calculator.