A Design Method for Information Synchronization of Main and Sub Navigation Devices
A navigation device and information synchronization technology, applied in directions such as navigation calculation tools, can solve the problem of no hardware synchronization signal between the main navigation and the sub-computer, and achieve the effect of ensuring effectiveness
Active Publication Date: 2020-09-18
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST +1
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Problems solved by technology
[0004] However, in the traditional aircraft maneuvering platform design, there is no hardware synchronization signal between the main navigation and the sub-computer
Method used
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[0036] Functionally, the present invention can be divided into two parts: hardware and software, and the two parts cooperate to realize the information synchronization of the main and sub-navigation devices. The specific implementation method is as follows:
[0037] 1. Hardware implementation
[0038] (1) second pulse signal
[0039] The second pulse signal is generated by the main navigation device and sent to the sub-navigation device, so it is necessary to add a hardware interface capable of sending the second pulse to the interface between the aircraft and the suspension.
[0040] hardware interface such as figure 2 As shown, AM26LS31M is used as the sending and receiving chip of 422 signals. The second pulse signal passes through the optocoupler, the driver chip (driving the 422 sending chip), and the 422 sending chip to generate a 422 differential signal, which is sent to the 422 receiving chip of the sub-navigation device, and is reshaped by the driving chip (for ex...
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The invention relates to a synchronous design method for information of primary and secondary navigation devices. The method comprises the following steps: generating a second pulse signal by the primary navigation device of an aircraft, and transmitting the signal to a secondary computer; updating UTC (Coordinated Universal Time) of a rising edge moment of the second pulse signal by the primary navigation device of the aircraft into a current frame of navigation information of the primary navigation device; acquiring primary navigation information of the primary navigation device per period by a primary computer of the aircraft and transmitting the information to the secondary computer; immediately generating interrupt after the secondary computer receives the second pulse signal transmitted by the primary navigation device, and recording the time as t0; receiving the primary navigation information transmitted by the primary computer; setting time of the received primary navigation information of the first frame as t1; calculating time delay to be t1-t0 if synchronization succeeds; eliminating the influence of the time delay during use of the primary and secondary navigation information by the secondary computer; and continuously synchronizing next second if synchronization fails. According to the synchronous design method for information of primary and secondary navigation devices disclosed by the invention, the time delay of primary navigation data reaching the secondary computer can be accurately acquired, and basis is provided for eliminating the influence of the timedelay for the secondary computer.
Description
technical field [0001] The invention relates to a method for designing information synchronization of a main navigation device and a sub navigation device, and belongs to the technical field of information synchronization. Background technique [0002] The main and sub-navigation devices are widely used in the fields of aviation and aerospace at present. The navigation information of the main navigation device is often used by the sub-navigation devices due to its multiple information sources and high navigation measurement accuracy. For example, the main navigation device uses high-precision inertial measurement devices, satellite navigation systems, and starlight measurement devices. Therefore, its measurement accuracy in navigation information such as speed, position, and attitude is relatively high. Relatively speaking, due to limitations in conditions, cost, volume, and weight, sub-navigation devices often only use inertial measurement devices with low precision, instea...
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IPC IPC(8): G01C21/20
CPCG01C21/20
Inventor 司文杰陈昌张建宏王瑞兰鹏杰张靖梁海波李浩马力伟
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST