High-precision miniature integrated control assembly

Abstract

The invention provides a high-precision miniature integrated control assembly, which belongs to the technical field of aircraft control equipment and comprises a power board, a computer board, a power board and an IMU (Inertial Measurement Unit) board, the power supply board, the computer board and the power board are electrically connected with one another, and the computer board is electrically connected with the IMU board. Interboard and external interface interconnection is carried out by adopting the micro flexible belt, so that the area occupation of the PCB is reduced while the connection reliability is improved; by adopting a mode of grouping ignition circuits and sharing current-limiting resistors, the number of the current-limiting resistors of the direct-current ignition circuit is reduced, and the occupied volume is greatly reduced; by adopting a bare core mixing process, devices such as MOS (Metal Oxide Semiconductor) tubes, triodes and the like in the multi-path ignition circuit are subjected to bare core packaging, so that the occupied volume is further reduced; a frequency division multiplexing mode is adopted, a power supply cable and a communication cable are multiplexed, external electrical connection is simplified, and the product is more compact; and high-precision navigation is realized while the launching rapidity is met by adopting a large and small range and meter combined navigation mode.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft control equipment, and more specifically, relates to a high-precision micro-integrated control component. Background Art

[0002] In micro-aircraft, due to the limited load capacity and load space of the aircraft, its control components are usually required to be small in size and light in weight.

[0003] The control component integrates navigation, guidance stability, input and output, timing control, servo drive, and communication. The system is complex and multi-functional. Conventional control components are large in diameter and difficult to meet the requirements of micro-aircraft. On the other hand, for aircraft in specific application scenarios, fast response (seconds) is required. Conventional combined navigation that relies on GNSS is slow to search for satellites, and hot start also cannot meet the requirements of fast response. Conventional solutions that rely on transfer alignment and then switch to pure inertial navigation cannot simultaneously meet the requirements of high precision and large overload of live anti-transmission. Summary of the invention

[0004] In view of the technical problem that the size, weight and precision of existing conventional control components cannot meet the requirements of micro-aircraft, the purpose of the present invention is to provide a high-precision miniature integrated control component to solve at least one aspect of the shortcomings of existing conventional control components. The integrated control component is small in size, light in weight, and can achieve high-precision navigation.

[0005] To achieve the above object, the present invention provides a high-precision micro-integrated control component, comprising: a power supply board, a computer board, a power board and an IMU board; the power supply board, the computer board and the power board are electrically connected to each other, and the computer board and the IMU board are electrically connected;

[0006] The power board is used to supply power to the carrier aircraft; the computer board is provided with a processor, and the computer board is used to realize the communication interface, data processing, and navigation and guidance stability solution; the power board is provided with a servo drive circuit, which is used to realize the carrier aircraft firing timing control, input and output, and servo drive; the IMU board is used to measure and record the acceleration and angular velocity of the carrier aircraft in three-dimensional space;

[0007] The power board is provided with a plurality of groups of firing circuits, each group of firing circuits includes a plurality of firing circuits, each group of firing circuits shares a current limiting resistor, and each group of firing circuits does not work at the same time.

[0008] Furthermore, the semiconductor components in the multi-way ignition circuit are packaged using a bare core hybrid packaging process.

[0009] Furthermore, the semiconductor components include MOS tubes and triodes.

[0010] Furthermore, a frequency division multiplexing module and a secondary power supply module are provided on the power supply board. The frequency division multiplexing module multiplexes the power supply cables and communication cables in a frequency division multiplexing manner, and the secondary power supply module is used to realize secondary power conversion.

[0011] Furthermore, the power board, the computer board and the power board are electrically connected to each other via a micro-flex strip, and the computer board and the IMU board are electrically connected via a micro-flex strip.

[0012] Furthermore, the power board is electrically connected to the carrier through a micro-flex tape.

[0013] Furthermore, the power board is electrically connected to the steering gear through a micro-flex belt.

[0014] Furthermore, the IMU board is provided with two addition meters with different ranges. The large-range addition meter is used for sensitive short-term large overload of launch and calculation of initial launch speed; the small-range addition meter is used for pure inertial navigation after launch.

[0015] Furthermore, the two measuring instruments with different measuring ranges are respectively an accelerometer and a gyroscope.

[0016] Compared with the prior art, the present invention has the following technical effects:

[0017] A high-precision micro-integrated control component of the present invention can reduce the number of current-limiting resistors in DC ignition circuits by grouping multiple groups of ignition circuits on a power board, with each group of ignition circuits sharing a current-limiting resistor, thereby greatly reducing the volume occupied by the control component, making the control component smaller in size and lighter in weight, which is conducive to the high integration and miniaturization of the control component, making it better suitable for micro-aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0019] Figure 1 A schematic structural diagram of a high-precision micro-integrated control component provided by an embodiment of the present invention.

[0020] In the figure, each reference numeral is:

[0021] 1. Carrier, 2. Integrated control component, 3. Power board, 4. Computer board, 5. Power board, 6. IMU board, 7. Micro flex tape, 8. Frequency division multiplexing module, 9. Secondary power supply module, 10. Processor, 11. The first group of shared current limiting resistors, 12. The nth group of shared current limiting resistors, 13. The first ignition circuit, 14. The kth ignition circuit, 15. The mth ignition circuit, 16. The nth ignition circuit, 17. Bare core hybrid process module, 18. The first group of ignition circuits, 19. The nth group of ignition circuits, 20. Servo drive circuit, 21. Accelerometer, 22. Gyroscope. DETAILED DESCRIPTION

[0022] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0023] The terms used in the embodiments of the present invention are only for the purpose of describing specific embodiments, and are not intended to limit the present invention. The singular forms "a", "said" and "the" used in the embodiments of the present invention and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings.

[0024] The terms "first" and "second" are used only for descriptive purposes to distinguish objects such as substances from each other, and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. For example, without departing from the scope of the embodiments of the present invention, the first XX may also be referred to as the second XX, and similarly, the second XX may also be referred to as the first XX. Thus, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features.

[0025] The embodiment of the present invention provides a high-precision micro-integrated control component, the structure of which is as follows: Figure 1 As shown, the integrated control component 2 includes four PCB boards: a power board 3, a computer board 4, a power board 5 and an IMU board 6; the power board 3, the computer board 4 and the power board 5 are electrically connected to each other, and the computer board 4 and the IMU board 6 are electrically connected.

[0026] The power board 3 is used to supply power to the carrier 1, which is a micro-aircraft; the computer board 4 is provided with a processor 10, and the computer board 4 is used to realize the communication interface, data processing, and navigation and guidance stability solution; the power board 5 is provided with a servo drive circuit 20, and the power board 5 is used to realize the ignition timing control, input and output, and servo drive of the carrier 1; the IMU board 6 is used to measure and record the acceleration and angular velocity of the carrier 1 in three-dimensional space; the power board 5 is provided with multiple groups of ignition circuits, each group of ignition circuits includes multiple ignition circuits, each group of ignition circuits shares a current limiting resistor, and each group of ignition circuits does not work at the same time, that is, the multiple ignition circuits in the same group do not ignite at the same time.

[0027] like Figure 1 As shown, the power board 5 is provided with a first group of ignition circuits 18, ..., and an nth group of ignition circuits 19. The first group of ignition circuits 18 includes a first ignition circuit 13, ..., and a kth ignition circuit 14. The nth group of ignition circuits 19 includes an mth ignition circuit 15, ..., and an nth ignition circuit 16. The first group of ignition circuits 18 share a first group of common current limiting resistors 11, and the nth group of ignition circuits 19 share an nth group of common current limiting resistors 12.

[0028] For control components that use DC ignition and have multiple ignition requirements, conventional designs require each ignition circuit to be equipped with a current limiting resistor, and the power-type current limiting resistor is large in size and occupies a large space. In order to reduce the number of current limiting resistors in the DC ignition circuit, the embodiment of the present invention is based on the principle that the ignition circuits in each group do not act at the same time, by grouping the multiple ignition circuits, and each group shares the current limiting resistor, which can greatly reduce the number of current limiting resistors and reduce the size of the component. In this way, the volume occupied by the integrated control component 2 can be greatly reduced, making the integrated control component 2 smaller in size and lighter in weight, which is conducive to the high integration and miniaturization of the integrated control component 2, so that it can be better applied to micro-aircraft.

[0029] For a control component with multiple firing requirements, each firing circuit includes semiconductor components such as MOS tubes and triodes. These semiconductor components occupy a large space, and in order to further reduce the number of components, the semiconductor components in the multiple firing circuits of the embodiment of the present invention are packaged using a bare core hybrid packaging process. That is, the MOS tubes, triodes and other semiconductor components in the multiple firing circuits are bare-core packaged to form a bare core hybrid process module 17, which further reduces the volume occupied by these semiconductor components and is conducive to further miniaturization of the integrated control component 2.

[0030] Conventional control components use separate power supply and communication cables for external interfaces. There are 8 external interface cables, which occupy a large volume. In order to simplify the external electrical connection and make the product more compact, the power board 3 of the embodiment of the present invention is further provided with a frequency division multiplexing module 8 and a secondary power module 9, and the secondary power module 9 is used to realize the secondary power conversion. The frequency division multiplexing module 8 of the embodiment of the present invention adopts a frequency division multiplexing method to multiplex the power supply cable and the communication cable through the power carrier, which greatly simplifies the connection of the external electrical interface of the micro-aircraft. The external interface cables can be reduced to 4, making the integrated control component 2 more compact, which is conducive to further miniaturization of the integrated control component 2.

[0031] Conventional PCB boards are interconnected and connected to external interfaces by scattered wire welding, and the pads occupy a large area of ​​the PCB board, and the pad connection strength is low. In order to reduce the area of ​​the PCB board occupied by the scattered wire interconnection pads between PCB boards and to the outside, the power board 3, computer board 4 and power board 5 in the embodiment of the present invention are electrically connected to each other through a micro-flex tape 7, and the computer board 4 and IMU board 6 are electrically connected through a micro-flex tape 7. Furthermore, the power board 3 is electrically connected to the carrier 1 through the micro-flex tape 7. Furthermore, the power board 5 is electrically connected to the servo through the micro-flex tape 7. The micro-flex tape 7 is a flexible circuit board. The embodiment of the present invention adopts the micro-flex tape 7 for interconnection, which improves the connection reliability while reducing the area occupied by the PCB board, improves the space utilization rate, and is also conducive to further miniaturization of the integrated control component 2.

[0032] In view of the problem of high navigation accuracy requirements, in order to improve navigation accuracy, further, the IMU board 6 of the embodiment of the present invention is provided with two addition meters with different ranges, that is, the IMU board 6 of the embodiment of the present invention adopts a navigation method combining a large-range addition meter and a small-range addition meter, specifically, the zero position of the large-range addition meter is corrected by the small-range addition meter, and the large-range addition meter is used to sense short-term large overloads during transmission and calculate the initial velocity of the launch; the high-precision small-range addition meter is used for pure inertial navigation after the launch, and the initial value of the pure inertial navigation is obtained by the carrier 1 through transmission and alignment, thereby achieving high-precision navigation while meeting the rapidity of the launch. Specifically, the two addition meters with different ranges in the embodiment of the present invention are the accelerometer 21 and the gyroscope 22.

[0033] The integrated control assembly 2 of the embodiment of the present invention is composed of four PCB boards: a computer board 4, a power board 5, a power board 3 and an IMU board 6. A micro-flex tape 7 is used for interconnection between boards and external interfaces, thereby improving the connection reliability while reducing the area occupied by the PCB board. The method of grouping the ignition circuits and sharing the current limiting resistors is adopted to reduce the number of current limiting resistors in the DC ignition circuits, thereby greatly reducing the volume occupied. The bare core hybrid process is adopted to bare core package the MOS tubes, triodes and other devices in the multi-channel ignition circuits, thereby further reducing the volume occupied. The power supply cables and communication cables are reused in the form of frequency division multiplexing, simplifying the external electrical connections and making the product more compact. The method of combined navigation of large and small range plus meters is adopted, and the large range plus meter is used to sensitively transmit short-term large overloads, calculate the initial speed of the launch, and use the high-precision small plus meter for pure inertial navigation after the launch, thereby achieving high-precision navigation while meeting the rapidity of the launch.

[0034] The above embodiments only express several implementation methods of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the attached claims.

Claims

1. A high-precision micro-integrated control component, characterized in that: include: A power board, a computer board, a power board and an IMU board; the power board, the computer board and the power board are electrically connected to each other, and the computer board and the IMU board are electrically connected; The power board is used to supply power to the carrier aircraft; the computer board is provided with a processor, and the computer board is used to realize the communication interface, data processing, and navigation and guidance stability solution; the power board is provided with a servo drive circuit, which is used to realize the carrier aircraft firing timing control, input and output, and servo drive; the IMU board is used to measure and record the acceleration and angular velocity of the carrier aircraft in three-dimensional space; The power board is provided with a plurality of groups of firing circuits, each group of firing circuits includes a plurality of firing circuits, each group of firing circuits shares a current limiting resistor, and each group of firing circuits does not work at the same time.

2. A high-precision micro-integrated control component as claimed in claim 1, characterized in that: The semiconductor components in the multi-channel ignition circuit are packaged using a bare core hybrid packaging process.

3. A high-precision micro-integrated control component as claimed in claim 2, characterized in that: The semiconductor components include MOS tubes and triodes.

4. A high-precision micro-integrated control component as claimed in claim 1, characterized in that: The power board is provided with a frequency division multiplexing module and a secondary power supply module. The frequency division multiplexing module multiplexes the power supply cable and the communication cable in a frequency division multiplexing manner, and the secondary power supply module is used to realize secondary power conversion.

5. A high-precision micro-integrated control component as claimed in claim 1, characterized in that: The power board, the computer board and the power board are electrically connected to each other via micro-flex strips, and the computer board and the IMU board are electrically connected via micro-flex strips.

6. A high-precision micro-integrated control component as claimed in claim 5, characterized in that: The power board is electrically connected to the carrier through a micro-flex tape.

7. A high-precision micro-integrated control component as claimed in claim 6, characterized in that: The power board is electrically connected to the steering gear through a micro-flex belt.

8. A high-precision micro-integrated control component according to any one of claims 1 to 7, characterized in that: The IMU board is provided with two adding meters with different ranges. The large-range adding meter is used for sensitively transmitting short-term large overload and calculating the initial speed of the launch; the small-range adding meter is used for pure inertial navigation after the launch.

9. A high-precision micro-integrated control component as claimed in claim 8, characterized in that: The two types of meters with different measuring ranges are respectively an accelerometer and a gyroscope.

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