CN116238704A

CN116238704A - Simulator device for aircraft hanging point

Info

Publication number: CN116238704A
Application number: CN202310165291.9A
Authority: CN
Inventors: 薛春阳; 刘鑫
Original assignee: Beijing Polyvision Technology Development Co ltd
Current assignee: Beijing Polyvision Technology Development Co ltd
Priority date: 2023-02-15
Filing date: 2023-02-15
Publication date: 2023-06-09

Abstract

The invention relates to a simulator device for an aircraft hanging point, which comprises a plurality of simulators, wherein the simulators are sequentially connected to form a relay type structure, and node data interaction and synchronization are carried out among the simulators; the simulator comprises: the battery wireless module that just gentle just printed plate and just gentle just printed plate connect, just gentle just printed plate includes: the rigid printed board and the flexible board are welded together to form a whole, and the rigid printed board comprises: SOPC single chip. The design of the simulator with the minimum volume under the aircraft hanging point is realized by using an SOPC single chip, a relay type structure, an expandable battery wireless module and a rigid-flexible printed board.

Description

Simulator device for aircraft hanging point

Technical Field

The invention belongs to the technical field of comprehensive guarantee of an airplane, and particularly relates to a simulator device for an airplane hanging point.

Background

With the development of technology, aircraft auxiliary equipment is increasing. The checking of the aircraft hanging point before the aircraft mounts the weapon is extremely important, and the validity of the hanging point needs to be checked in advance so as to work effectively after the weapon is mounted at the hanging point. At present, aircraft hanging points are various in types, signal types are complex, and the traditional method is to simulate various signal loads by ATE equipment so as to measure the effectiveness of the hanging points. Automatic Test Equipment (ATE) is bulky, heavy, and inconvenient during use, so a simulator design with very small volumes is needed to quickly and accurately inspect an aircraft point of attachment interface. ATE equipment is an automated system that is intended for electrical, thermal and physical testing without direct human intervention. Especially for checking whether each hanging point function of the airplane is complete.

Disclosure of Invention

The invention aims to provide a simulator device for an aircraft hanging point, which solves the problems of large volume and inconvenient use and realizes the design of a very small-volume simulator under the aircraft hanging point.

In order to achieve the above purpose, the invention adopts the following technical scheme:

a simulator device of an aircraft hanging point comprises a plurality of simulators, wherein the simulators are sequentially connected to form a relay type structure, and node data interaction and synchronization are carried out among the simulators; the simulator comprises: a rigid-flexible printed board 4 and a battery wireless module 3 connected with the rigid-flexible printed board, the rigid-flexible printed board comprising: the rigid printed board and the flexible board are welded together to form a whole, and the rigid printed board comprises: SOPC single chip 1.

Preferably, the rigid-flexible printed board is mounted in a stacked manner into the simulator housing.

Preferably, the rigid printed board is electrically connected with the interconnection cable.

Preferably, the battery wireless module 3 is plugged into the simulator housing via a connector 6.

Preferably, the wireless battery module is mounted on one side of the simulator, and exchanges data with the simulator through a serial asynchronous bus.

Preferably, the battery wireless module includes: the battery module is used for providing power for the simulators, and the wireless module is used for carrying out data exchange for the simulators.

Preferably, the SOPC single chip is packaged with an ARM9 processor, an FPGA chip and necessary interfaces.

Preferably, the necessary interface includes a non-bus signal and a plurality of bus signals; the bus signals comprise GJB289A bus, HB6096 bus and CAN bus signals packaged in a chip; the non-bus interface includes analog signals, discrete magnitude signals, frequency magnitude, CCIR-D signals.

Compared with the prior art, the invention has the beneficial effects that:

the invention has simple connection, can exchange and synchronize data without adding redundant equipment, and greatly reduces the preparation time of test. The area of the printed boards is reduced, the space inside the simulator is utilized more efficiently, and the size of the connector between the interconnected printed boards is reduced.

Drawings

FIG. 1 is a functional block diagram of a SOPC single chip of the simulator apparatus of the present invention for aircraft waypoints;

FIG. 2 is a relay type block diagram of a simulator assembly of the aircraft hitch point of the present invention;

FIG. 3 is a schematic diagram of a battery wireless module and simulator of the simulator assembly of the present invention for aircraft hanging points;

FIG. 4 is a schematic view of a rigid-flexible printed circuit board of the simulator assembly of the aircraft hanging point of the present invention;

FIG. 5 is a front view of a simulator housing of the simulator assembly of the aircraft hitch point of the invention;

FIG. 6 is a side view of a simulator housing of the simulator assembly of the aircraft hitch point of the invention;

fig. 7 is a top view of a simulator housing of the simulator assembly of the aircraft hitch point of the invention.

Detailed Description

The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present invention are shown in the drawings.

Examples

As shown in FIG. 2, the invention provides a simulator device for an aircraft hanging point, which comprises a plurality of simulators, wherein the simulators are sequentially connected to form a relay type structure, and node data interaction and synchronization are carried out among the simulators; the simulator comprises: a rigid-flexible printed board 4 and a battery wireless module 3 connected with the rigid-flexible printed board, the rigid-flexible printed board comprising: five rigid printed boards 4 and four flexible boards 5, wherein the rigid printed boards are welded together through the flexible boards to form a whole, and the rigid printed board comprises: SOPC single chip 1. The relay type structure refers to that after one simulator receives the data of the last simulator, the data of the last simulator and the data of the simulator are combined into a data packet to be transmitted to the next simulator, and the like.

Preferably, the rigid-flexible printed board is mounted in a stacked manner into the simulator housing. The node comprises a rigid-flexible printed board and a simulator shell, and the rigid-flexible printed board is placed inside the node.

Preferably, the battery wireless module 3 is plugged into the simulator housing via a connector 6. The battery wireless module is an integral body and functionally divided into a wireless function and a battery function. The wireless battery module can be installed on one side of the simulator and exchanges data with the simulator through a serial asynchronous bus. The battery radio module is also connected with an antenna 7.

Preferably, as shown in fig. 1, the SOPC single chip is packaged with an ARM9 processor, an FPGA chip, and a necessary interface, where the necessary interface includes a non-bus signal and a plurality of bus signals; the bus signals comprise GJB289A bus, HB6096 bus and CAN bus signals packaged in a chip; the non-bus interface includes analog signals, discrete magnitude signals, frequency magnitude, CCIR-D signals. The SOPC single chip further comprises: power conversion, interface conversion, clock PLL, etc. for the completion function of power conversion, interface conversion.

The aircraft has a plurality of hanging points, and the number of the hanging points is more than a few and more than a dozen. However, bus-type networks require a bus cable to connect the nodes and termination resistors, which add to the complexity of the connection. The star network needs to have a central node for switching, so that the central node equipment is additionally added, and the variety of the equipment is increased. In order to accelerate the test and improve the efficiency, a plurality of simulators can be used for simultaneously testing the multi-hanging points, so that data exchange and synchronization among the simulators are needed. Furthermore, serial asynchronous buses are adopted between the simulators for data interaction and synchronization. As shown in fig. 2, the simulator does not adopt a traditional bus type network and a star type network, and adopts a relay type structure 2 to perform data interaction and synchronization of each node so as to realize simultaneous testing of a plurality of simulators. The right side socket of the first simulator and the left side socket of the second simulator are connected by using a cable, and then the right side socket of the second simulator and the left side socket of the third simulator are connected by using a cable, so that the simulation devices can be connected to form a simulator relay type structure. The structure connects all nodes together in an end-to-end mode, the connection method is simple, and data exchange and synchronization can be carried out without adding redundant equipment.

In order to further reduce the volume of the simulator, more efficiently utilize the space inside the simulator, reduce the volume of the connector between the interconnected printed boards, adopt the design of directly canceling the connector, but the signals that need to be electrically interconnected between each printed board, adopt the compliance board to connect each rigid printed board. As shown in fig. 4, five rigid printed boards are arranged in the simulator, the rigid printed boards bear the welding of components and the necessary installation of external interface connectors, the five rigid printed boards are connected into a whole through four flexible printed boards, and each rigid printed board is connected with an interconnection cable. The flexible printed board can be bent and twisted, and the integral printed board is placed in the simulator in a stacked mode, so that the three-dimensional space in the simulator is fully and efficiently utilized, and the three-dimensional size of the simulator is further reduced.

Considering the aircraft hanging point interface signals comprehensively, the interfaces of the general aircraft hanging point interface signals meeting the standard requirements of the GJB1188A are through-standard interfaces and non-through-standard interface signals. The interface signals are generally classified into bus interfaces, which are mainly composed of the GJB289A and HB6096 signals, and non-bus interfaces, which include analog signals, discrete signals, frequency signals, CCIR-D signals, and the like, according to signal characteristics. As shown in fig. 1, in order to save simulator space, a shenzhen micro SOPC single chip is used. The chip integrates and packages a plurality of bus signals and non-bus signals into one IC chip, and packages an ARM9 processor and an FPGA chip so as to expand signals. Meanwhile, necessary interface functions such as GJB289A bus, HB6096 bus, CAN bus signals and the like are also packaged into the chip, so that the design and the area of peripheral circuits are greatly reduced, and the area of a printed board is reduced.

As shown in fig. 3, the external front view of the battery wireless module is constituted by thick line portions. To further reduce the complexity of use and the number of interconnecting cables, battery wireless modules can be expanded as the environment of use permits. The battery wireless module is plugged through the connector of the simulator, and no additional cables and other accessories are needed to be added. As shown in fig. 5, the simulator and the battery wireless module are assembled first, and the battery wireless module can be quickly inserted into the left side of the simulator, so that the installation is convenient. And then the assembled simulator battery module is directly connected to the aircraft hanging point as a whole without a patch cable. As shown in fig. 6 and 7, in the simulator housing structure, each simulator can be directly connected to the aircraft hanging point for testing after being started, and connection between each simulator is not needed, so that the preparation time for testing is greatly reduced.

Minimizing the volume of the simulator has been achieved by the integrated use of the four component descriptions above. The method of microscopically combining SOPC single chips and rigid-flexible-rigid printed boards greatly utilizes the space inside the simulator by using an original relay type structure so as to exchange data without increasing equipment and minimum interconnection cables, and simultaneously expands battery wireless modules under the condition of considering environmental permission, thereby further reducing interconnection cables and test preparation time.

In the description of the present specification, reference to the term "in one embodiment," "in another embodiment," "exemplary," or "in a particular embodiment," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While the invention has been described in detail in the foregoing general description, embodiments and experiments, it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the invention and are intended to be within the scope of the invention as claimed.

Claims

1. The simulator device for the aircraft hanging point comprises a plurality of simulators, and is characterized in that the simulators are sequentially connected to form a relay type structure, and node data interaction and synchronization are carried out among the simulators; the simulator comprises: the battery wireless module that just gentle just printed plate and just gentle just printed plate connect, just gentle just printed plate includes: the rigid printed board and the flexible board are welded into a whole through the flexible board, and the rigid printed board comprises: SOPC single chip.

2. The aircraft hanging point simulator apparatus of claim 1, wherein the rigid-flexible printed board is mounted in a stacked manner within a simulator housing.

3. The aircraft hanging point simulator apparatus of claim 2, wherein the rigid printed board is electrically connected to an interconnect cable.

4. The aircraft hanging point simulator apparatus of claim 1, wherein the battery wireless module is plugged into the simulator housing via a connector.

5. The aircraft hanging point simulator apparatus of claim 4, wherein the wireless battery module exchanges data with the simulator via a serial asynchronous bus.

6. The aircraft hanging point simulator apparatus of claim 1, wherein the battery wireless module comprises: the battery module is used for providing power for the simulators, and the wireless module is used for carrying out data exchange for the simulators.

7. The aircraft hanging point simulator apparatus of claim 6, wherein the SOPC single chip is packaged with ARM9 processor, FPGA chip, necessary interface together.

8. The aircraft hanging point simulator apparatus of claim 7, wherein the requisite interface comprises a non-bus signal and a plurality of bus signals; the bus signals comprise GJB289A bus, HB6096 bus and CAN bus signals packaged in a chip; the non-bus interface includes analog signals, discrete magnitude signals, frequency magnitude, CCIR-D signals.