Power control method for communication system of closed space vehicle

Abstract

The invention discloses a power control method for a communication module between a closed space vehicle and a command set. By means of the method, energy can be saved, and the endurance can be prolonged; meanwhile, a relay micro base station projection condition is given; and the continuity of a communication link is ensured when the aircraft executes a task in a closed space.

Description

Technical Field

[0001] The present invention relates to the field of UAV communication, and particularly to a method for controlling the power of a communication system for a closed - space aircraft. Background

[0002] In a closed space, such as a mine roadway, aircraft are mostly used for dangerous area detection, modeling, and emergency rescue. However, the natural environment in coal mine roadways is very complex, with a lot of dust, water spray, high temperature, and high humidity; the communication signal coverage is poor, and some roadways have no communication coverage at all. When the aircraft performs emergency rescue, the continuity of communication must be ensured at all times. Since the usual point - to - point communication distance is limited, especially at turning points, the communication effect is even worse. In the case of emergency rescue, how to ensure smooth and continuous communication between the aircraft and the rear command post is the key to ensuring the completion of the flight mission.

[0003] In addition, flight time is also one of the main parameters that everyone is concerned about in emergency rescue. If the communication module transmits data at a fixed power in any case, it will cause energy waste. The transmission power of traditional data transmission modules has several levels, and generally requires manual configuration. This situation is suitable for fixed communication; but for aircraft, this situation is not suitable. There are also cases where the transmission rate of services is reduced at the cost of reducing power. However, for aircraft undertaking emergency rescue and dangerous area detection, the transmission rate of services cannot be reduced in some scenarios. Therefore, for aircraft performing flight missions in closed spaces, it is necessary to adjust their transmission power. For this reason, the following invention is designed. Summary of the Invention

[0004] The present invention discloses a method for controlling the power of a communication system for a closed - space UAV; using this method can make the communication module energy - saving, and moreover, maintain the continuity of the communication link. This method includes the following two situations.

[0005] Embodiment 1: Power control process of the console for the flight platform

[0006] The console detects the signal SINR received from the flight platform every time interval T, and compares it with the preset threshold value SINT t ; if the SINR is not greater than or equal to SINT t , and the power of the communication module of the flight platform has not been adjusted to the maximum, then the console sends a command to the flight platform to increase the transmission power by Δ up . If the transmission power of the communication module of the aircraft has been adjusted to the maximum, then the console sends a command to the flight platform to eject a relay station. If the SINR > SINT t +Δ sinr , then the console sends a command to the flight platform to reduce the transmission power by Δ down .

[0007] Embodiment 2: Power Control Process of Flight Platform for Console Communication Module

[0008] The flight platform detects the signal SINR received from the console every time interval T and compares it with the preset threshold value SINT t ; If SINR is not greater than or equal to SINT t , and the power of the console communication module has not been adjusted to the maximum, the flight platform sends a command to increase the transmission power by Δ up to the console. If the transmission power of the console communication module has been adjusted to the maximum, the flight platform automatically ejects the relay station. If SINR > SINT t + Δ sinr , the console sends a command to decrease the transmission power by Δ down to the flight platform.

[0009] Embodiment 3: Signaling Process between Console and Flight Platform

[0010] (1) Signaling Frame Format Sent from Console to Flight Platform

[0011] Frame header Direction Control word Error correction coding

[0012] Frame Header: Frame Number

[0013] Direction: C to P;

[0014] Control Word: 001 represents an increase by Δ up ; 010 represents a decrease by Δ down ; 000 represents maintaining the original level; 100 represents an acknowledgment; 111 represents ejecting the micro relay station;

[0015] Error Correction Coding: Represents some error detection and correction flag bits;

[0016] (2) Signaling Frame Format Sent from Flight Platform to Console

[0017] Frame header Direction Control word Error correction coding

[0018] Frame Header: Frame Number

[0019] Direction: P to C;

[0020] Control Word: 001 represents an increase by Δ up ; 010 represents a decrease by Δ down ; 000 represents maintaining the original level; 100 represents an acknowledgment;

[0021] Error Correction Coding: Represents some error detection and correction flag bits; Brief Description of the Drawings

[0022] Figure 1 This is a control process of the power of the flight platform by the console of a closed - space aircraft (transmission power adjustment principle of the flight - platform communication module) provided in the first embodiment of the present invention. Specific implementation mode

[0023] To make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will be described in detail with reference to the drawings and specific embodiments.

[0024] As Figure 1 shown, it includes the following steps:

[0025] S101: The communication module of the console detects the signal - to - interference - plus - noise ratio SINR of the signal received from the flight every time interval T;

[0026] S102: Compare the SINR measured in S101 with the set threshold value SINT t for comparison.

[0027] S103: If the SINR is not greater than this threshold value, determine whether the power of the flight platform has been adjusted to the maximum;

[0028] S104: If the transmission power of the flight platform has not been adjusted to the maximum, the console sends a power - control command to the flight platform to increase its transmission power by Δ up .

[0029] S105: If the power of the flight platform has been adjusted to the maximum; then the console sends a command for the ejection relay station to the flight platform.

[0030] S106: Further determine whether SINR > SINT t +Δ SINR holds,

[0031] S107: If the determination in S106 holds, the console sends a command to the flight platform to decrease the transmission power by Δ down ;

[0032] S108: If the determination in S106 does not hold, the transmission power of the flight - platform communication module remains unchanged. Brief description of the drawings

[0034] Figure 2 This is a control process of the power of the console by the flight platform of a closed - space aircraft (transmission power adjustment principle of the console communication module) provided in the second embodiment of the present invention.

[0035] The specific implementation mode is to make the technical problems, technical solutions and advantages to be solved by the present invention clearer. The following will be described in detail with reference to the drawings and specific embodiments.

[0036] As shown Figure 2 below, it includes the following steps:

[0037] S201: The communication module of the flight platform detects the signal-to-interference-plus-noise ratio (SINR) of the signal received from the console every time interval T;

[0038] S202: Compare the SINR measured in 01 with the set threshold value SINT t for comparison;

[0039] S203: If the SINR is not greater than this threshold value, determine whether the power of the console has been adjusted to the maximum;

[0040] S204: If the transmission power of the console has not been adjusted to the maximum, the flight platform sends a power control command to the console to increase its transmission power by Δ up ;

[0041] S205: If the power of the console has been adjusted to the maximum; the flight platform automatically ejects the relay station;

[0042] S206: The flight platform further determines whether SINR > SINT t +Δ SINR holds;

[0043] S207: If the determination in 06 holds, the flight platform sends a command to the console to decrease the transmission power by Δ down ;

[0044] S208: If the determination in 06 does not hold, the transmission power of the console communication module remains unchanged. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 3 This is a signaling process (power control signaling between the command console and the flight platform) between the flight platform of a closed-space aircraft and the console provided in the third embodiment of the present invention.

[0047] DETAILED DESCRIPTION To make the technical problems, technical solutions, and advantages to be solved by the present invention clearer, the following will be described in detail with reference to the accompanying drawings and specific embodiments.

[0048] As Figure 2 shown below, it includes the following steps:

[0049] S301: When the condition for increasing the transmission power is satisfied, the console sends a command to increase the power to the flight;

[0050] S302: When the condition for decreasing the transmission power is satisfied, the console sends a command to decrease the power to the flight;

[0051] S303: When the condition of constant transmission power is satisfied, the console sends a command of constant power to the flight.

[0052] S304: When the ejection condition is satisfied, the console sends a command of an ejection relay station to the flight.

[0053] S305: When the condition of increasing the transmission power is satisfied, the flight platform sends a command of increasing power to the console.

[0054] S306: When the condition of decreasing the transmission power is satisfied, the flight platform sends a command of decreasing power to the console.

[0055] S307: When the condition of constant transmission power is satisfied, the flight platform sends a command of constant power to the console.

[0056] Parameter Design

[0057] 1) Detection Interval T Design

[0058] If T is too large, there may be a disconnection phenomenon between the aircraft and the command post; if T is too small, it will cause frequent judgment, wasting DSP computing resources and electric energy; therefore, the selection of T should consider the flight speed of the flight platform and the turning situation of the roadway. Generally, it is in the order of seconds, such as 1 second, 2 seconds, 3 seconds, etc.

[0059] 2) SINR t Design

[0060] SINR directly affects the BER or BLER of the signal. Generally, SINR is convenient to calculate, so SINR is mostly used for detection. On the premise that the modulation and demodulation method is known, the corresponding curve of SINR and BER or BLER can be obtained, and SINR can be calculated according to the received permission value of BLER. t .

[0061] 3) Δ up and Δ down Design

[0062] If Δ is too large, there may be an over-ejection phenomenon, resulting in too many ejected micro repeaters; conversely, if Δ is too small, there may be a missed ejection phenomenon, risking intermediate communication interruption.

[0063] 4) Δ SINR Design

[0064] SINR = (P s - P l ) / (I + N). When the transmission power is increased by Δ up , the corresponding received SINR will increase by Δ up / (I + N); when the transmission power is decreased by Δ downWhen this happens, the corresponding received SINR will decrease by Δ down / (I + N); that is, Δ SINR The set value of should not be less than Δ down / (I + N). Where P s is the transmit power, and P l is the path loss; I is the system interference, and N is the system noise.

Claims

1. A power method for a communication system of a closed - space aircraft, comprising the following steps: Example 1: The power control process of the console for the flight platform The console detects the signal SINR received from the flying platform every other time interval T and compares it with the preset threshold value SINT t ; if SINR is not greater than or equal to SINT t , and moreover, the power of the communication module of the flying platform has not been adjusted to the maximum, then the console sends a command to increase the transmission power by Δ up to the flying platform. If the transmission power of the communication module of the aircraft has been adjusted to the maximum, then the console sends a command to eject the relay station to the flying platform. If SINR > SINT t + Δ sinr , then the console sends a command to decrease the transmission power by Δ down to the flying platform. Example 2: The power control process of the flight platform for the communication module of the console The flight platform detects the signal SINR received from the console every other time interval T and compares it with the preset threshold value SINT t ; if SINR is not greater than or equal to SINT t , and moreover, the transmission power of the console communication module has not been adjusted to the maximum, then the flight platform sends a command to increase the transmission power by Δ up to the console. If the transmission power of the console communication module has been adjusted to the maximum, the flight platform automatically ejects the relay station. If SINR > SINT t +Δ sinr If so, the console sends a command to the flying platform to lower the transmission power by Δ down . Example 3: The signaling process between the console and the flight platform (1) The signaling frame format sent from the console to the flight platform Frame header: Frame number Direction: C to P; Control word: 001 represents an upward adjustment of Δ up ; 010 represents a downward adjustment of Δ down ; 000 represents maintaining the original level; 100 represents Ack response; 111 represents ejecting a micro relay station; Error - correction coding: Represents some error - detection and error - correction flag bits; (2) The signaling frame format sent from the flight platform to the console Frame header: Frame number Direction: P to C; Control word: 001 represents an upward adjustment of Δ up ; 010 represents a downward adjustment of Δ down ; 000 represents maintaining the original level; 100 represents Ack response; Error - correction coding: Represents some error - detection and error - correction flag bits; 2. The method according to claim 1 in Embodiment 1, characterized in that Every time interval T, the console calculates the SINR of the signal received from the flying platform and compares this calculated value with the preset threshold SINT t ; if the SINR is not greater than or equal to SINT t , and the power of the communication module of the flying platform has not been adjusted to the maximum, the console sends a command to increase the transmission power by Δ up to the flying platform. If the transmission power of the communication module of the flying vehicle has been adjusted to the maximum, the console sends a command to eject the micro relay station to the flying platform. If SINR > SINT t + Δ sinr , the console sends a command to decrease the transmission power by Δ down to the flying platform. Even if the parameters taken are different, as long as the control logic is similar to the above, it falls within the scope covered by this claim book.

3. The method according to the second embodiment of claim 1, characterized in that, The flight platform detects the signal SINR received from the console every time interval T and compares it with the preset threshold value SINT t ; if SINR is not greater than or equal to SINT t , and moreover, if the power of the console communication module has not been adjusted to the maximum, the flight platform sends a command to increase the transmission power by Δ up to the console. If the transmission power of the console communication module has been adjusted to the maximum, the flight platform automatically ejects the micro relay station. If SINR > SINT t + Δ sinr , the console sends a command to decrease the transmission power by Δ down to the flight platform. Even if the parameters taken are different, as long as the control logic is similar to the above, it falls within the scope covered by this claim 4. The method according to claim 1 in Embodiment 3, characterized in that, The signaling format sent from the console to the flight platform and the response frame format and related content are specified, including the expression of direction and the definition of control words; Any frame format that is the same, even if the content is not completely the same, falls within the scope of this claim.

5. The method according to claim 1 in Embodiment 3, characterized in that, The command signaling format and response signaling format sent from the flight platform to the console and their related content are specified, including the expression of direction and the definition of control words; Any frame format that is the same, even if the content is not completely the same, falls within the scope of this claim.

6. The method according to claim 1 in Embodiment 3, characterized in that, In the command sent from the console to the flight platform, the content of projecting a micro relay station is included. Even if the signaling coding is not exactly the same, as long as the content covering the ejecting relay station or relay station falls within the scope of this claim.

Images