A satellite-borne solid-state power amplifier control and telemetry circuit

Abstract

The application provides a kind of satellite-borne solid-state power amplifier control and telemetry circuit, comprising: detection diode, four-way operational amplifier, stabilivolt, two-way operational amplifier and double negative voltage controlled attenuator;The detection diode is connected with microwave coupler;Four-way operational amplifier is connected with positive power voltage;The stabilivolt is connected with four-way operational amplifier output end;The two-way operational amplifier is connected with positive and negative power voltage;Double negative voltage controlled attenuator is connected with two-way operational amplifier two output ends;When input power increases, the direct current voltage that detection diode detects increases, the detection voltage that four-way operational amplifier input increases, the control positive pressure 1 that four-way operational amplifier output increases, the control negative pressure 1 that two-way operational amplifier output increases, so that the attenuation value of double negative voltage controlled attenuator increases, and input power decreases.After reaching dynamic balance, input power maintains the level before change, and output power does not change.

Description

Technical Field

[0001] This invention relates to the field of remote control and telemetry circuits, and more particularly to the field of automatic gain control and telemetry circuits for spaceborne solid-state power amplifiers. Background Technology

[0002] Solid-state power amplifiers (SPAs) have become an indispensable component in satellite communications, serving as a crucial link in both space-to-ground and inter-satellite communication. To adapt to power fluctuations caused by front-end input variations and achieve relatively stable output power to ensure communication quality, automatic gain control (AGC) circuits are increasingly widely used in SPAs. Meanwhile, the power telemetry voltage of the power amplifier, as a key telemetry indicator of its operational stability, is also a standard parameter in SPAs.

[0003] In related technologies, power amplifiers mostly use a single voltage-controlled attenuator to balance the power fluctuations of the input signal. However, when applied to higher frequency bands, a dual voltage-controlled attenuator is necessary to meet the requirements.

[0004] Therefore, it is necessary to design a peripheral circuit that can be used for dual-voltage voltage-controlled attenuators and also has the function of power telemetry output. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the present invention aims to provide a spaceborne solid-state power amplifier control and telemetry circuit, characterized in that it includes: a detector diode, a four-channel operational amplifier, a Zener diode, a dual-channel operational amplifier, and a dual negative voltage-controlled attenuator;

[0006] The detector diode is connected to the microwave coupler; the four-channel operational amplifier is connected to the positive power supply voltage; the Zener diode is connected to the output terminal of the four-channel operational amplifier; the dual-channel operational amplifier is connected to both the positive and negative power supplies; the dual negative voltage-controlled attenuator is connected to the two output terminals of the dual-channel operational amplifier.

[0007] When the input power increases, the DC voltage detected by the detector diode increases, the detection voltage input to the four-channel operational amplifier increases, the control positive voltage 1 output by the four-channel operational amplifier increases, and the absolute value of the control negative voltage 1 output by the dual-channel operational amplifier increases, which increases the attenuation value of the dual negative voltage controlled attenuator and reduces the input power.

[0008] In one possible implementation, the detector diode is used to couple the microwave signal from the microwave coupler into a DC voltage, which is then sent to the four operational amplifiers for processing.

[0009] In one possible implementation, the four operational amplifiers comprise four independent operational amplifier circuits, which can be interchangeable.

[0010] In one possible implementation, three of the four operational amplifiers are used to output control positive voltage 1 from the non-inverting amplifier circuit, control positive voltage 2 from the subtractor circuit, and telemetry voltage from the non-inverting amplifier circuit, respectively.

[0011] In one possible implementation, the dual operational amplifier comprises two independent operational amplifier circuits, which can be interchangeable.

[0012] In one possible implementation, both operational amplifier circuits in the dual operational amplifier are used as inverters to output control negative voltage 1 and control negative voltage 2, and the order of the two operational amplifier circuits can be adjusted.

[0013] In one possible implementation, a Zener diode is connected before the telemetry voltage output by the dual operational amplifier.

[0014] In one possible implementation, the control input signal of the dual negative pressure voltage-controlled attenuator consists of two negative pressures, the sum of which is a fixed value.

[0015] In one possible implementation, the automatic gain control of the spaceborne solid-state power amplifier covers a range of DC to 20 GHz.

[0016] Compared with the prior art, the present invention has at least the following beneficial effects:

[0017] 1. The spaceborne solid-state power amplifier control and telemetry circuit provided by this invention implements functions such as inverting amplification, subtraction, and inverter using two operational amplifiers. It has advantages such as simple circuitry, high integration, and high adjustability, and can be applied to solid-state power amplifiers in the S / C / X / Ku bands, covering application scenarios from DC to 20GHz. It can also be applied to voltage-controlled attenuators with dual voltage control.

[0018] 2. The present invention provides a control and telemetry circuit for a spaceborne solid-state power amplifier. This method has certain versatility and can be widely applied not only to spaceborne systems but also to electronic systems such as radar, launch vehicles, and electronic countermeasures. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0020] Figure 1 This is a logic diagram of the spaceborne solid-state power amplifier control and telemetry circuit described in this invention.

[0021] Figure 2 This is a schematic diagram of an example of the control and telemetry circuit for the spaceborne solid-state power amplifier described in this invention. Detailed Implementation

[0022] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0023] like Figure 1 As shown, the spaceborne solid-state power amplifier control and telemetry circuit provided by this invention includes: a detector diode, a four-channel operational amplifier, a Zener diode, a dual-channel operational amplifier, and a dual negative voltage-controlled attenuator. The detector diode is connected to a microwave coupler; the four-channel operational amplifier is connected to a positive power supply voltage; the Zener diode is connected to the output terminal of the four-channel operational amplifier; the dual-channel operational amplifier is connected to both the positive and negative power supply voltages; and the dual negative voltage-controlled attenuator is connected to the two output terminals of the dual-channel operational amplifier.

[0024] Those skilled in the art will understand that the spaceborne solid-state power amplifier control and telemetry circuit provided in this embodiment is a multifunctional control and telemetry circuit composed of operational amplifiers. A detector diode detects the microwave signal from the microwave coupler into a DC voltage, which is then supplied to two of the four operational amplifiers: one uses a non-inverting amplifier circuit to amplify the detected signal to a suitable value and a Zener diode to regulate the voltage, providing the power telemetry voltage for the entire satellite; the other uses a non-inverting amplifier circuit to amplify the detected signal to a suitable value, generating control positive voltage 1. Based on the device characteristics of the dual negative voltage-controlled attenuator, a calibration voltage is provided to the positive input terminal of the third channel of the four operational amplifiers. The obtained control positive voltage 1 is input to the negative input terminal of the third channel of the four operational amplifiers, and a subtractor circuit is used to obtain the difference between the calibration voltage and control positive voltage 1, which is used as control voltage 2.

[0025] The obtained positive control voltage 1 and positive control voltage 2 are input to the negative input terminals of the two channels of the dual operational amplifier, respectively. By applying the inverting amplifier circuit, the negative values ​​of positive control voltage 1 and positive control voltage 2 are obtained and used as negative control voltage 1 and negative control voltage 2, respectively.

[0026] Furthermore, control negative pressure 1 and control negative pressure 2 are respectively input to the two input terminals of the dual negative pressure voltage-controlled attenuator, serving as the control signals for this voltage-controlled attenuator. The dual negative pressure voltage-controlled attenuator is connected to the microwave amplification link of the solid-state power amplifier, and by adjusting control positive pressure 1 to a suitable value, a suitable attenuation value is provided to the solid-state power amplifier.

[0027] Those skilled in the art will understand that when the input power increases, the DC voltage detected by the detector diode increases, and the detection voltage input to the four operational amplifiers increases. At this time, the control positive voltage 1 output by the four operational amplifiers increases, and the absolute value of the control negative voltage 1 output by the two operational amplifiers increases, which increases the attenuation value of the dual negative voltage controlled attenuator, thus reducing the input power. After reaching dynamic equilibrium, the input power remains at the level before the change, and the output power remains unchanged.

[0028] When the input power decreases, the DC voltage detected by the detector diode decreases, and the detection voltage input to the four operational amplifiers decreases. At this time, the control positive voltage 1 output of the four operational amplifiers decreases, and the absolute value of the control negative voltage 1 output of the two operational amplifiers decreases, causing the attenuation value of the dual negative voltage controlled attenuator to decrease, thus increasing the input power. After reaching dynamic equilibrium, the input power remains at the level before the change, and the output power remains unchanged.

[0029] Furthermore, in one embodiment, such as Figure 2As shown, the spaceborne solid-state power amplifier control and telemetry circuit provided by this invention further includes: a first resistor to a twenty-fourth resistor, and a first capacitor to a third capacitor. The first resistor is connected to the output and input terminals of the first channel of the dual-channel operational amplifier. The second resistor is connected to the positive control voltage 2 and the negative input terminal of the first channel of the dual-channel operational amplifier, respectively. The third resistor is connected to ground and the positive input terminal of the first channel of the dual-channel operational amplifier, respectively. The fourth resistor is connected to the negative control voltage 2 and the output terminal of the first channel of the dual-channel operational amplifier, respectively. The fifth resistor is connected to ground and the positive input terminal of the second channel of the dual-channel operational amplifier, respectively. The sixth resistor is connected to the negative control voltage 1 and the output terminal of the second channel of the dual-channel operational amplifier, respectively. The seventh resistor is connected to the positive control voltage 1 and the negative input terminal of the second channel of the dual-channel operational amplifier, respectively. The eighth resistor is connected to the positive input terminal of the seventh and sixth resistors, respectively. The ninth resistor is connected to the negative input terminal and the output terminal of the fourth channel of the four-channel operational amplifier, respectively. The tenth and twelfth resistors are connected in series and connected to ground and the output terminal of the first channel of the four-channel operational amplifier, respectively. The eleventh resistor is connected to ground and the calibration voltage, respectively. The thirteenth resistor is connected to the control positive voltage 1 and the eleventh resistor. The fourteenth resistor is connected to the positive input terminal of the first channel of the four-channel operational amplifier and the detector voltage. The fifteenth resistor is connected to the positive input terminal of the fourth channel of the four-channel operational amplifier and the calibration voltage. The sixteenth resistor is connected in parallel with the Zener diode. The seventeenth resistor is connected to the positive input terminal of the second channel of the four-channel operational amplifier and ground. The eighteenth resistor is connected to the positive input terminal of the second channel of the four-channel operational amplifier and the detector voltage. The nineteenth resistor is connected to the negative input terminal of the second channel of the four-channel operational amplifier and ground. The twentieth resistor is connected to the negative input terminal of the second channel of the four-channel operational amplifier and ground. The twenty-first resistor is connected to the output terminal of the third channel of the four-channel operational amplifier and ground. The twenty-second, twenty-third, and twenty-fourth resistors are connected in series and connected to the output terminal of the third channel of the four-channel operational amplifier and the telemetry voltage. The first capacitor is connected to the positive power supply and ground of the dual-channel operational amplifier. The second capacitor is connected to the negative power supply and ground of the dual-channel operational amplifier. The third capacitor is connected to the positive power supply and ground of the four-channel operational amplifier.

[0030] Those skilled in the art will understand that the first, second, and fourth resistors constitute the inverting amplifier of the first channel of the dual-channel operational amplifier; the sixth, seventh, and eighth resistors constitute the inverting amplifier of the second channel of the dual-channel operational amplifier; the third and fifth resistors are used to protect the input terminals of the dual-channel operational amplifier to prevent excessive current from burning out the operational amplifier. The tenth, twelfth, and fourteenth resistors constitute the non-inverting amplifier of the first channel of the four-channel operational amplifier; the eighteenth, twentieth, and twenty-fourth resistors constitute the non-inverting amplifier of the second channel of the four-channel operational amplifier; the ninth, thirteenth, and fifteenth resistors constitute the subtractor of the fourth channel of the four-channel operational amplifier; the eleventh, seventeenth, nineteenth, and twenty-first resistors all serve as protection resistors for the operational amplifier. The twenty-second and twenty-third resistors limit the detector voltage and current to prevent excessive current from burning out the interface circuit. The sixteenth resistor is a voltage divider resistor, which divides the output detector voltage and protects it through a Zener diode. The first to third capacitors are all filter capacitors, serving a filtering function.

[0031] Furthermore, the four operational amplifier described in this patent uses the first, second, and fourth channels, while the third channel is left floating, and the order in which the three channels are used can be adjusted.

[0032] Furthermore, the dual operational amplifier described in this patent has a first output controlling negative voltage 2 and a second output controlling negative voltage 1, and the order of these two outputs can be adjusted.

[0033] Furthermore, the positive voltage of the power supply is +10V, and the negative voltage is -10V.

[0034] Furthermore, the spaceborne solid-state power amplifier control and telemetry circuit can be applied to solid-state power amplifiers in the S / C / X / Ku bands, covering application scenarios from DC to 20GHz.

[0035] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A control and telemetry circuit for a spaceborne solid-state power amplifier, characterized in that, include: Detector diodes, four-channel operational amplifiers, Zener diodes, dual-channel operational amplifiers, and dual negative voltage-controlled attenuators; The detector diode is connected to the microwave coupler; the four-channel operational amplifier is connected to the positive power supply voltage; the Zener diode is connected to the output terminal of the four-channel operational amplifier; the dual-channel operational amplifier is connected to both the positive and negative power supplies; the dual negative voltage-controlled attenuator is connected to the two output terminals of the dual-channel operational amplifier. When the input power increases, the DC voltage detected by the detector diode increases, the detection voltage input to the four-channel operational amplifier increases, the control positive voltage 1 output by the four-channel operational amplifier increases, and the absolute value of the control negative voltage 1 output by the dual-channel operational amplifier increases, which increases the attenuation value of the dual negative voltage-controlled attenuator and reduces the input power. The four-channel operational amplifier includes four independent operational amplifier circuits, which can be substituted for each other. Three of the four operational amplifiers are used to output control positive voltage 1 from the non-inverting amplifier circuit, control positive voltage 2 from the subtractor circuit, and telemetry voltage from the non-inverting amplifier circuit, respectively.

2. The spaceborne solid-state power amplifier control and telemetry circuit according to claim 1, characterized in that, The detector diode is used to couple the microwave signal from the microwave coupler into a DC voltage, which is then sent to the four operational amplifiers for processing.

3. The spaceborne solid-state power amplifier control and telemetry circuit according to claim 1, characterized in that, The dual-channel operational amplifier includes two independent operational amplifier circuits, which can be substituted for each other.

4. The spaceborne solid-state power amplifier control and telemetry circuit according to claim 3, characterized in that, Both operational amplifier circuits in the dual operational amplifier are used as inverters to output control negative voltage 1 and control negative voltage 2, and the order of the two operational amplifier circuits can be adjusted.

5. The spaceborne solid-state power amplifier control and telemetry circuit according to claim 4, characterized in that, A Zener diode is connected before the output telemetry voltage of the dual operational amplifier.

6. The spaceborne solid-state power amplifier control and telemetry circuit according to claim 1, characterized in that, The control input signal of the dual negative pressure voltage-controlled attenuator consists of two negative pressures, the sum of which is a fixed value.

7. The spaceborne solid-state power amplifier control and telemetry circuit according to claim 6, characterized in that, The automatic gain control of the spaceborne solid-state power amplifier covers a range of DC to 20 GHz.

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