Airborne autonomous navigation equipment configuration architecture

Abstract

The invention provides an airborne autonomous navigation equipment configuration architecture, the task reliability is ensured by adopting a non-similar redundancy configuration, a light and small rotary modulation inertial navigation system is used as a main inertial navigation system to provide long-endurance high-precision navigation performance for an aircraft, and a light and small laser strapdown inertial navigation system is used as a standby inertial navigation system to ensure the basic reliability level.

Description

Technical Field

[0001] The present invention belongs to the field of aviation technology and relates to an airborne autonomous navigation equipment configuration architecture. Background Art

[0002] Usually, the autonomous navigation subsystem in the airborne avionics system is composed of two laser strapdown inertial / satellite combined navigation systems and one strapdown attitude and heading system. The two laser strapdown inertial / satellite combined navigation systems serve as one main and one backup to provide dual backup, and the strapdown attitude and heading system serves as an emergency backup system.

[0003] The shortcoming is that the accuracy of the two laser strapdown inertial / satellite combined navigation systems is not high. As the operation time increases, when the satellite fails, there may be a lack of reference correction information, which may lead to low accuracy of the aircraft's autonomous navigation and positioning, and common mode failures may exist. Summary of the Invention

[0004] The present invention provides an airborne autonomous navigation equipment configuration architecture, which solves the problems of low positioning accuracy and possible common mode failure in existing autonomous navigation subsystems.

[0005] The present invention provides an airborne autonomous navigation equipment configuration architecture, comprising: a main inertial navigation system of an autonomous navigation subsystem uses a light and small rotary modulation inertial navigation system, and a backup inertial navigation system uses a light and small laser strapdown inertial navigation system;

[0006] The emergency backup system adopts a strapdown attitude and heading system.

[0007] Optionally, the emergency backup system uses a fiber-optic strapdown attitude and heading system.

[0008] Optionally, the main inertial navigation system, the backup inertial navigation system and the emergency backup system are independent of each other.

[0009] Optionally, the main inertial navigation system and the backup inertial navigation system are each equipped with an anti-interference processing antenna.

[0010] Optionally, the strapdown attitude and heading system shares the same antenna with the main inertial navigation system or the backup inertial navigation system.

[0011] Optionally, the precision of the lightweight and compact rotary modulation inertial navigation system is higher than the precision of the lightweight and compact laser strapdown inertial navigation system.

[0012] Optionally, RS422 communication protocol is used between the main inertial navigation, backup inertial navigation, strapdown attitude and heading system and the antenna.

[0013] Optionally, the RINC429 communication protocol is used between the main inertial navigation, backup inertial navigation, strapdown attitude and heading system and avionics system.

[0014] The present invention provides an airborne autonomous navigation equipment configuration architecture. Compared with the prior art, the present invention has the following beneficial effects: a non-similar redundancy configuration is adopted to ensure mission reliability; a lightweight and compact rotary modulation inertial navigation system is used as a main inertial navigation system to provide the aircraft with long-duration and high-precision navigation performance; and a lightweight and compact laser strapdown inertial navigation system is used as a backup inertial navigation system to ensure a basic reliability level.

[0015] Compared with traditional laser inertial navigation systems, in terms of system weight, the total weight of the two laser inertial navigation systems is about 38kg, the weight of the lightweight rotary modulation inertial navigation system is about 14kg, and the weight of the lightweight laser strapdown inertial navigation system is about 8kg. The weight of the new architecture is reduced by about 16kg, accounting for 42%, which greatly reduces the total system weight and makes an important contribution to the weight reduction of the carrier aircraft. In terms of economy, the unit price of a single product is equivalent. In terms of aircraft navigation performance, the autonomous navigation accuracy of the new architecture is improved by an order of magnitude. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the configuration architecture of the autonomous navigation equipment of the airborne avionics system provided by the present invention. DETAILED DESCRIPTION

[0017] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative work are within the scope of protection of the present invention.

[0018] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed in order to provide a comprehensive understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement and method proposed below, but rather encompasses any improvements, replacements, and modifications to structures, methods, and devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, well-known structures and techniques are not shown to avoid unnecessary ambiguity in the present invention.

[0019] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0020] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0021] like Figure 1 As shown, the present invention is achieved through the following technical solutions: an inertial navigation system constitutes the core capability of autonomous navigation, a light and small rotation modulation inertial navigation system is used for the main inertial navigation of the autonomous navigation subsystem, a non-similar redundancy configuration is adopted to ensure mission reliability, a miniaturized rotation modulation inertial navigation system is configured to greatly improve the autonomous navigation performance, a light and small laser strapdown inertial navigation system is used for the backup inertial navigation, a miniaturized laser strapdown inertial navigation system is configured to ensure a basic reliability level, a satellite navigation receiver is used to realize inertial / Beidou-3 satellite combined navigation, a satellite navigation anti-interference antenna is configured to improve the survivability of satellite navigation, and finally, autonomous navigation is integrated in the flight management system to form a global optimal solution.

[0022] The two types of inertial navigation systems are matched with high and low performance, and have a comprehensive balance in performance and reliability.

[0023] The present invention provides an airborne autonomous navigation equipment configuration architecture, comprising: a main inertial navigation system of an autonomous navigation subsystem uses a light and small rotary modulation inertial navigation system, and a backup inertial navigation system uses a light and small laser strapdown inertial navigation system;

[0024] The emergency backup system adopts a strapdown attitude and heading system.

[0025] Optionally, the emergency backup system uses a fiber-optic strapdown attitude and heading system.

[0026] Optionally, the main inertial navigation system, the backup inertial navigation system and the emergency backup system are independent of each other.

[0027] Optionally, the main inertial navigation system and the backup inertial navigation system are each equipped with an anti-interference processing antenna.

[0028] Optionally, the strapdown attitude and heading system shares the same antenna with the main inertial navigation system or the backup inertial navigation system.

[0029] Optionally, the precision of the lightweight and compact rotary modulation inertial navigation system is higher than the precision of the lightweight and compact laser strapdown inertial navigation system.

[0030] Optionally, RS422 communication protocol is used between the main inertial navigation, backup inertial navigation, strapdown attitude and heading system and the antenna.

[0031] Optionally, the RINC429 communication protocol is used between the main inertial navigation, backup inertial navigation, strapdown attitude and heading system and avionics system.

[0032] Compared with the existing technology, the beneficial effects of the present invention are: adopting a non-similar redundancy configuration to ensure mission reliability, a lightweight and small rotary modulation inertial navigation system as the main inertial navigation system to provide the aircraft with long-endurance and high-precision navigation performance, and a lightweight and small laser strapdown inertial navigation system as a backup inertial navigation system to ensure a basic reliability level.

[0033] Compared with traditional laser inertial navigation systems, in terms of system weight, the total weight of the two laser inertial navigation systems is about 38kg, the weight of the lightweight rotary modulation inertial navigation system is about 14kg, and the weight of the lightweight laser strapdown inertial navigation system is about 8kg. The weight of the new architecture is reduced by about 16kg, accounting for 42%, which greatly reduces the total system weight and makes an important contribution to the weight reduction of the carrier aircraft. In terms of economy, the unit price of a single product is equivalent. In terms of aircraft navigation performance, the autonomous navigation accuracy of the new architecture is improved by an order of magnitude.

[0034] The above-described embodiments merely represent preferred embodiments of the present invention. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the present invention. It should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, and the scope of protection of the present invention is not limited thereto. Any person skilled in the art will readily conceive of various equivalent modifications or substitutions within the technical scope disclosed herein, and such modifications or substitutions should be encompassed within the scope of protection of the present invention.

Claims

1. An airborne autonomous navigation device configuration architecture, characterized in that: include: The main inertial navigation system of the autonomous navigation subsystem uses a lightweight rotary modulation inertial navigation system, and the backup inertial navigation system uses a lightweight laser strapdown inertial navigation system; The emergency backup system adopts a strapdown attitude and heading system.

2. The airborne autonomous navigation device configuration architecture according to claim 1, characterized in that: The emergency backup system uses a fiber-optic strapdown attitude and heading system.

3. The airborne autonomous navigation device configuration architecture according to claim 1, characterized in that: The main inertial navigation, backup inertial navigation and emergency backup systems are independent of each other.

4. The airborne autonomous navigation device configuration architecture according to claim 1, characterized in that: The main inertial navigation system and the backup inertial navigation system are each equipped with an anti-interference processing antenna.

5. The airborne autonomous navigation device configuration architecture according to claim 1, characterized in that: The strapdown attitude and heading system shares the same antenna with the main inertial navigation system or the backup inertial navigation system.

6. The airborne autonomous navigation device configuration architecture according to claim 1, characterized in that: The accuracy of the lightweight and small rotary modulation inertial navigation system is higher than that of the lightweight and small laser strapdown inertial navigation system.

7. The airborne autonomous navigation device configuration architecture according to claim 1, characterized in that: RS422 communication protocol is used between the main inertial navigation, backup inertial navigation, strapdown attitude and heading system and antenna.

8. The airborne autonomous navigation device configuration architecture according to claim 1, characterized in that: The RINC429 communication protocol is used between the main inertial navigation, backup inertial navigation, strapdown attitude and heading system and avionics system.

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