Motor-driven pulse thrust attitude control device
A motor-driven, pulsed technology, applied in the direction of projectiles, offensive equipment, weapon types, etc., can solve the problems of limiting the application range of pulse thrust controllers, and achieve the effects of simplified structure installation, efficient attitude control, and expanded use range
Pending Publication Date: 2021-11-16
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology
[0003] However, under the condition that it is necessary to ensure the stability of the roll angle of the aircraft (such as using an image seeker or a platform seeker on an arrow aircraft), in order to ensure the reliable operation of the seeker, the rotational speed of the missile body cannot exceed 1 revolution / second ), the projectile cannot spin around its own axis, and the traditional pulse thrust attitude control device cannot produce the desired control force
This greatly limits the application range of the pulse thrust controller. Therefore, it is necessary to develop a pulse thrust attitude control device to ensure that the pulse thrust attitude control device can be used effectively on missile aircraft using image seekers or platform seekers. Work
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[0040] The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0041] This embodiment provides a motor-driven pulse thrust attitude control device, which is used for the attitude control of missile aircraft. The pulse thrust attitude control device is driven to rotate around its own axis through the rotation of the motor, and the angle sensor is used to measure the relative position of the pulse thrust attitude control device to the aircraft. The rotation angle of the aircraft determines the number and position of the pulse motors working in each control cycle, and realizes the attitude and trajectory control of the aircraft.
[0042] Such as figure 1 As shown, the pulse thrust attitude control device 0 is coaxially installed with the external aircraft, and the pulse thrust attitude control device 0 is close to the aircraft head position (between the head and the fuselage);
[0043] Such as figure 2 and image 3 A...
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The invention discloses a motor-driven pulse thrust attitude control device, and relates to the technical field of missile and rocket manufacturing. The motor-driven pulse thrust attitude control device comprises a support structure, a motor stator, a motor rotor, a pulse engine assembly and an ignition control circuit board, wherein the two ends of the support structure are of disc structures and are coaxially mounted between the head and the fuselage of an external aircraft; the motor stator, the motor rotor, the pulse engine assembly and the ignition control circuit board are sequentially supported between the discs at the two ends of the support structure; an angle sensor is arranged on the ignition control circuit board; and an ignition control circuit is arranged on the ignition control circuit board and used for driving the pulse engine assembly to ignite.
Description
technical field [0001] The invention relates to the technical field of guided missiles, in particular to a motor-driven pulse thrust attitude control device. Background technique [0002] Missile aircraft are widely used in the military field, and the pulse thrust attitude control device is a control actuator widely used in rotary guided missiles. The current pulse thrust attitude control device generally arranges several pulse engines on its surface, and its working principle is: according to the control command and the roll angle of the aircraft, generate a pulse engine ignition command, control the ignition of the pulse engine at the corresponding position, rely on the sub-engine to generate The thrust changes the attitude and flight path of the aircraft. Since the pulse engine is disposable, it is necessary to rotate the pulse thrust attitude control device around its own axis in order to generate multiple control forces in a certain direction. The traditional pulse-th...
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IPC IPC(8): F42B10/66
CPCF42B10/661
Inventor 于剑桥李世鹏胡俊吴小胜
Owner BEIJING INSTITUTE OF TECHNOLOGYGY