A launch vehicle pressure sensor launch-ground multiplexing system

Abstract

The application provides a launch vehicle pressure sensor rocket-ground multiplexing system, characterized in that the system comprises a ground direct measurement power supply, a ground control power supply, an on-rocket battery, an on-rocket power distribution device, an on-rocket pressure sensor, a ground direct measurement device and an on-rocket pressure control device; the ground direct measurement power supply, the ground control power supply and the on-rocket battery are connected with the on-rocket power distribution device; the on-rocket power distribution device is connected with the on-rocket pressure sensor; the on-rocket pressure sensor is connected with the ground direct measurement device and the on-rocket pressure control device through two RS485 channels; the ground direct measurement power supply is used for power supply during filling; the ground control power supply is used for power supply during pre-pressurization before launching; the on-rocket battery is used for power supply during flight pressurization; and the on-rocket pressure sensor is used for measuring the pressure in the tank. The application can reduce the matching of the launch vehicle pressure sensor, reduce the model cost, reduce the risk of sealing failure and improve the system reliability.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of launch vehicle electrical system, in particular to a launch vehicle pressure sensor rocket-ground multiplexing system. BACKGROUND

[0002] The launch vehicle is the basis of space activities. During the launch vehicle filling process, the pre-pressurization process before launch and the flight pressurization process, the pressure signal in the tank is needed. Generally, the pressure in the tank is introduced to the outside of the tank through the pressure introduction pipe, and then connected to the pressure sensor to obtain the pressure signal. Due to different work periods and control requirements, a set of pressure sensors is used in the launch vehicle filling process and the pre-pressurization process before launch, and another set of pressure sensors is used in the flight pressurization process. There are the following shortcomings:

[0003] 1) Increased model supporting cost

[0004] Because the flight pressurization control and the ground pressurization control are respectively matched with pressure sensors, and the actual requirements of the pressure sensors are completely consistent, the pressure sensors are repeatedly matched, increasing the model supporting cost.

[0005] 2) Difficulty in designing redundancy strategy

[0006] Because the pressurization control is crucial to the launch vehicle, redundancy design must be considered. Generally, three pressure sensors are matched for each tank for flight pressurization control, and two-out-of-three redundancy voting is performed. In order to reduce the supporting cost, two pressure sensors are generally matched for ground pressurization control, which brings difficulty in designing redundancy strategy. When a single pressure sensor fails, it is difficult to determine which pressure sensor fails under partial failure mode, which is prone to misjudgment.

[0007] 3) Increased risk of seal failure

[0008] Because all pressure sensors are connected to the tank through the pressure introduction pipe, once the sealing surface of any pressure sensor fails, it will cause the tank gas to leak, resulting in disastrous consequences. The more the number of pressure sensors is matched, the greater the risk is.

[0009] In the article "Design and Implementation of Closed Pressurization Control System for New Generation Launch Vehicle" in Spaceflight Control (2015.33(6)), the design of pressurization control in flight is introduced, which does not involve ground pressurization control.

[0010] In view of the above, it is necessary to develop a launch vehicle pressure sensor rocket-ground multiplexing system suitable for flight pressurization control and ground pressurization control: through power supply switching and two-way RS485 bus output of pressure signal, a set of pressure sensors is used for ground and flight pressurization control at the same time. SUMMARY

[0011] The application aims to provide a launch vehicle pressure sensor rocket-ground multiplexing system to reduce the cost of launch vehicle single machine matching and improve system reliability.

[0012] To achieve the above-mentioned purpose, the application provides a launch vehicle pressure sensor rocket-ground multiplexing system, characterized in that it comprises a ground direct measurement power supply, a ground control power supply, an on-rocket battery, an on-rocket power distribution device, an on-rocket pressure sensor, a ground direct measurement device, and an on-rocket pressure control device.

[0013] The ground direct measurement power supply, the ground control power supply, and the on-rocket battery are connected with the on-rocket power distribution device respectively, the on-rocket power distribution device is connected with the on-rocket pressure sensor, and the on-rocket pressure sensor is connected with the ground direct measurement device and the on-rocket pressure control device through two RS485 respectively.

[0014] The ground direct measurement power supply is used to supply power to the on-rocket pressure sensor through the on-rocket power distribution device during the filling process of the launch vehicle.

[0015] The ground control power supply is used to supply power to the on-rocket pressure sensor through the on-rocket power distribution device during the pre-pressurization process of the launch vehicle before shooting.

[0016] The on-rocket battery is used to supply power to the on-rocket pressure sensor through the on-rocket power distribution device during the flight pressurization process of the launch vehicle.

[0017] The on-rocket power distribution device is used to complete the power supply switching from the ground direct measurement power supply to the ground control power supply and the power supply switching from the ground control power supply to the on-rocket battery.

[0018] The on-rocket pressure sensor is used to measure the pressure in the tank and output through two RS485 bus interfaces to the ground direct measurement device and the on-rocket pressure control device respectively.

[0019] The ground direct measurement device is used to receive the pressure signal sent by the on-rocket pressure sensor through the RS485 bus during the filling process and the pre-pressurization process of the launch vehicle before shooting and transmit it to the external ground equipment for tank pressurization control.

[0020] The on-rocket pressure control device is used to receive the pressure signal sent by the on-rocket pressure sensor through the RS485 bus during the flight pressurization process of the launch vehicle and perform tank pressurization control.

[0021] Further, the on-rocket power distribution device physically isolates the ground direct measurement power supply line from the ground control power supply line.

[0022] Further, the ground direct measurement power supply is physically isolated from the ground control power supply by the relay contact after the power supply switching.

[0023] Further, the on-board pressure sensor, the on-board power distribution device, the ground direct measurement power supply and the ground direct measurement device jointly complete the pressure signal acquisition during the filling process of the launch vehicle.

[0024] The on-board pressure sensor, the on-board power distribution device, the ground control power supply and the ground direct measurement device jointly complete the pressure signal acquisition during the pre-pressurization process of the launch vehicle before launch.

[0025] The on-board pressure sensor, the on-board power distribution device, the on-board battery and the on-board pressurization control device jointly complete the pressure signal acquisition during the flight pressurization process of the launch vehicle.

[0026] Further, the ground direct measurement power supply outputs 28V and uses an independent power supply, which is only used to supply power to the on-board pressure sensor.

[0027] Further, the ground control power supply outputs 28V and supplies power to other control units in addition to the on-board pressure sensor.

[0028] Further, the on-board battery outputs 28V, and its power supply objects are consistent with the ground control power supply, and only the power supply period is different.

[0029] Further, the ground direct measurement device receives the pressure signal, checks the check bit in the message to ensure transmission correctness, removes outliers from the pressure signal and performs filtering processing, and then transmits to the external ground equipment for tank pressurization control.

[0030] Further, the on-board pressurization control device receives the pressure signal, checks the check bit in the message to ensure transmission correctness, removes outliers from the pressure signal and performs filtering processing, and then compares with the pressurization pressure band after three-out-of-two voting, and outputs according to the preset rules for tank pressurization control.

[0031] Further, the power supply switching circuit of the on-board power distribution device includes two first relays K1 and second relays K2, the ground direct measurement power supply is connected to the normally closed terminal 3 of the first relay K1 contact, the ground control power supply is connected to the common terminal 1 of the first relay K1 contact, the on-board battery is connected to the common terminal 1 of the second relay K2 contact, and the on-board pressure sensor is connected to the normally open terminal 2 of the first relay K1 contact and the normally open terminal 2 of the second relay K2 contact.

[0032] Compared with the prior art, the present application has the following advantages and positive effects:

[0033] 1) The present application realizes the power supply switching of the pressure sensor on the arrow at different stages through the arrow power distribution device, and the pressure sensor adopts double RS485 bus output, so that one set of pressure sensor can be used for ground pre-pressurization and flight pressurization control at the same time, thereby reducing the supporting cost of the pressure sensor;

[0034] 2) The ground pre-pressurization control and the arrow flight pressurization control share the pressure sensor, and also adopt the two-out-of-three redundancy voting measure, thereby improving the reliability of the ground pre-pressurization control; and since the number of pressure pipe interfaces is reduced, the sealing failure risk is reduced.

[0035] In summary, the pressure sensor arrow-ground multiplexing system of the present application can reduce the supporting of the pressure sensor of the carrier rocket, reduce the model cost, reduce the sealing failure risk, and improve the system reliability. BRIEF DESCRIPTION OF DRAWINGS

[0036] Figure 1 is a structural block diagram of the pressure sensor arrow-ground multiplexing system of the embodiment of the present application.

[0037] Figure 2 is a structural diagram of the switching circuit in the arrow power distribution device of the embodiment of the present application. DETAILED DESCRIPTION

[0038] The carrier rocket pressure sensor arrow-ground multiplexing system of the present application will be further described below in combination with the drawings and specific embodiments. It should be noted that the drawings are very simplified and non-precise ratios are used, which are only used for the purpose of conveniently and clearly assisting in the description of the embodiments of the present application.

[0039] The present application relates to a carrier rocket pressure sensor arrow-ground multiplexing system, which is composed of a ground direct measurement power supply, a ground control power supply, an arrow battery, an arrow power distribution device, an arrow pressure sensor, a ground direct measurement device, and an arrow pressurization control device. During the filling process of the carrier rocket, the ground direct measurement power supply supplies power to the arrow pressure sensor through the arrow power distribution device, and the arrow pressure sensor outputs to the ground direct measurement device through the RS485 bus; during the pre-pressurization process of the carrier rocket before launch, the ground control power supply supplies power to the arrow pressure sensor through the arrow power distribution device, and the arrow pressure sensor outputs to the ground direct measurement device through the RS485 bus; and during the flight pressurization process of the carrier rocket, the arrow battery supplies power to the arrow pressure sensor through the arrow power distribution device, and the arrow pressure sensor outputs to the arrow pressurization control device through the RS485 bus.

[0040] Figure 1 is a structural block diagram of the pressure sensor arrow-ground multiplexing system of the embodiment of the present application. As shown in Figure 1As shown, the rocket pressure sensor rocket-ground multiplexing system provided by the application comprises a ground direct measurement power supply 10, a ground control power supply 20, an on-rocket battery 30, an on-rocket power distribution device 40, an on-rocket pressure sensor 50, a ground direct measurement device 60, and an on-rocket pressure control device 70.

[0041] The ground direct measurement power supply 10 is used to supply power to the on-rocket pressure sensor 50 through the on-rocket power distribution device 40 during the filling process of the launch vehicle, and the output of the ground direct measurement power supply 10 is 28V, which is an independent power supply and is only used to supply power to the on-rocket pressure sensor 50.

[0042] The ground control power supply 20 is used to supply power to the on-rocket pressure sensor 50 through the on-rocket power distribution device 40 during the pre-pressurization process of the launch vehicle before launch, and the output of the ground control power supply 20 is 28V, which is used to supply power to other control units in addition to the on-rocket pressure sensor 50.

[0043] The on-rocket battery 30 is used to supply power to the on-rocket pressure sensor 50 through the on-rocket power distribution device 40 during the flight pressurization process of the launch vehicle, and the output of the on-rocket battery 30 is 28V, which has the same power supply object as the ground control power supply 20, and only the power supply period is different.

[0044] The on-rocket power distribution device 40 is used to complete the power supply switching of the ground direct measurement power supply 10 to the ground control power supply 20 and the power supply switching of the ground control power supply 20 to the on-rocket battery 30. The on-rocket power distribution device physically isolates the ground direct measurement power supply 10 line from the ground control power supply 20 line. After the filling of the launch vehicle is completed and the pre-launch process is entered, the on-rocket power distribution device 40 switches the power supply of the pressure sensor from the ground direct measurement power supply 10 to the ground control power supply 20, and the physical isolation of the ground direct measurement power supply line and the ground control power supply line is realized by opening the relay contact. 2 minutes before launch, the on-rocket power distribution device 40 switches the power supply of the pressure sensor from the ground control power supply 20 to the on-rocket battery 30.

[0045] The on-rocket pressure sensor 50 is used to measure the pressure in the tank, and outputs through two RS485 interfaces to the ground direct measurement device 60 and the on-rocket pressure control device 70, respectively. The on-rocket pressure sensor 50 is powered by a 28V primary power supply.

[0046] The ground direct measurement device 60 is used to receive the pressure signal sent by the on-rocket pressure sensor 50 through the RS485 bus during the filling process and the pre-pressurization process before launch, check the check bits in the message to ensure the correctness of the transmission, and after removing outliers and filtering the pressure signal, transmit it to the external ground equipment for tank pressurization control.

[0047] The on-board pressurization control device 70 is used for receiving the pressure signal transmitted by the on-board pressure sensor 50 through the RS485 bus during the flight pressurization process of the carrier rocket, checking the check bit in the message to ensure the correctness of transmission, removing outliers and filtering the pressure signal, comparing with the pressurization pressure band after two-out-of-three voting, and outputting the tank pressurization control according to the preset rules.

[0048] Figure 2 The on-board power distribution device of the embodiment of the application is an internal switching circuit structure schematic diagram. The power supply switching circuit of the on-board power distribution device 40 refers to Figure 2 , including a first relay K1 and a second relay K2. The ground direct measurement power supply 10 is connected with the normally closed terminal 3 of the first relay K1 contact, the ground control power supply 20 is connected with the common terminal 1 of the first relay K1 contact, the on-board battery 30 is connected with the common terminal 1 of the second relay K2 contact, and the on-board pressure sensor 50 is connected with the normally open terminal 2 of the first relay K1 contact and the normally open terminal 2 of the second relay K2 contact.

[0049] The working principle of the carrier rocket pressure sensor on-board and ground multiplexing system provided by the application is as follows:

[0050] During the filling process of the carrier rocket, the ground direct measurement power supply supplies power to the on-board pressure sensor through the on-board power distribution device, and the on-board pressure sensor outputs to the ground direct measurement device through the RS485 bus; during the pre-pressurization process of the carrier rocket before launch, the ground control power supply supplies power to the on-board pressure sensor through the on-board power distribution device, and the on-board pressure sensor outputs to the ground direct measurement device through the RS485 bus; during the flight pressurization process of the carrier rocket, the on-board battery supplies power to the on-board pressure sensor through the on-board power distribution device, and the on-board pressure sensor outputs to the on-board pressurization control device through the RS485 bus.

[0051] Therefore, the on-board pressure sensor, the on-board power distribution device, the ground direct measurement power supply and the ground direct measurement device jointly complete the acquisition of the pressure signal during the filling process of the carrier rocket; the on-board pressure sensor, the on-board power distribution device, the ground control power supply and the ground direct measurement device jointly complete the acquisition of the pressure signal during the pre-pressurization process of the carrier rocket before launch; and the on-board pressure sensor, the on-board power distribution device, the on-board battery and the on-board pressurization control device jointly complete the acquisition of the pressure signal during the flight pressurization process of the carrier rocket.

[0052] The carrier rocket pressure sensor on-board and ground multiplexing system has the characteristics of reducing the matching cost and improving the system reliability, and has strong adaptability.

[0053] It will be apparent to those skilled in the art that various modifications and variations can be made to the present application without departing from the spirit or scope of the application. Thus, it is intended that the present application cover modifications and variations of this application provided they come within the scope of the appended claims and their equivalents.

Claims

1. A launch vehicle pressure sensor launch-ground multiplexing system, comprising: The application relates to a pressure sensor system for a launch vehicle, and belongs to the technical field of launch vehicle control. The system comprises a ground direct measurement power supply, a ground control power supply, an on-vehicle battery, an on-vehicle power distribution device, an on-vehicle pressure sensor, a ground direct measurement device and an on-vehicle pressurization control device. The ground direct measurement power supply, the ground control power supply and the on-vehicle battery are connected with the on-vehicle power distribution device respectively, the on-vehicle power distribution device is connected with the on-vehicle pressure sensor, and the on-vehicle pressure sensor is connected with the ground direct measurement device and the on-vehicle pressurization control device through two RS485 respectively. The ground direct measurement power supply is used for supplying power to the on-vehicle pressure sensor through the on-vehicle power distribution device during a filling process of the launch vehicle. The ground control power supply is used for supplying power to the on-vehicle pressure sensor through the on-vehicle power distribution device during a pre-pressurization process of the launch vehicle before launching. The on-vehicle battery is used for supplying power to the on-vehicle pressure sensor through the on-vehicle power distribution device during a flight pressurization process of the launch vehicle. The on-vehicle power distribution device is used for completing power supply switching of the ground direct measurement power supply to the ground control power supply and power supply switching of the ground control power supply to the on-vehicle battery. The on-vehicle pressure sensor is used for measuring pressure in a storage tank and outputting through two RS485 bus interfaces respectively to the ground direct measurement device and the on-vehicle pressurization control device. The ground direct measurement device is used for receiving pressure signals sent by the on-vehicle pressure sensor through the RS485 bus during the filling process and the pre-pressurization process of the launch vehicle before launching, and transmitting the pressure signals to external ground equipment for storage tank pressurization control. The on-vehicle pressurization control device is used for receiving pressure signals sent by the on-vehicle pressure sensor through the RS485 bus during the flight pressurization process of the launch vehicle, and performing storage tank pressurization control.

2. A launch vehicle pressure sensor pad reuse system as in claim 1, wherein, The on-vehicle power distribution device physically isolates the ground direct measurement power supply line from the ground control power supply line.

3. A launch vehicle pressure sensor pad reuse system as in claim 2, wherein, After the ground direct measurement power supply switches power supply to the ground control power supply, the ground direct measurement power supply line is physically isolated from the ground control power supply line through relay contact disconnection.

4. A launch vehicle pressure sensor pad reuse system as in claim 1, wherein, The on-vehicle pressure sensor, the on-vehicle power distribution device, the ground direct measurement power supply and the ground direct measurement device jointly complete pressure signal acquisition during the filling process of the launch vehicle. The on-vehicle pressure sensor, the on-vehicle power distribution device, the ground control power supply and the ground direct measurement device jointly complete pressure signal acquisition during the pre-pressurization process of the launch vehicle before launching. The on-vehicle pressure sensor, the on-vehicle power distribution device, the on-vehicle battery and the on-vehicle pressurization control device jointly complete pressure signal acquisition during the flight pressurization process of the launch vehicle.

5. A launch vehicle pressure sensor pad reuse system as in claim 1, wherein, The ground direct measurement power supply outputs 28V and adopts an independent power supply, and is only used for supplying power to the on-vehicle pressure sensor.

6. A launch vehicle pressure sensor pad reuse system as in claim 5, wherein, The ground control power supply outputs 28V, and is used for supplying power to other control units in addition to the on-vehicle pressure sensor.

7. A launch vehicle pressure sensor pad reuse system as in claim 6, wherein, The on-vehicle battery outputs 28V, and has the same power supply object as the ground control power supply, and only differs in power supply period.

8. A launch vehicle pressure sensor pad reuse system as in claim 1, wherein, The ground direct measurement device receives pressure signals, checks a check bit in a message, is used for ensuring transmission correctness, removes wild values of the pressure signals and performs filtering processing, and then transmits the pressure signals to external ground equipment for storage tank pressurization control.

9. A launch vehicle pressure sensor pad reuse system as in claim 1, wherein, The arrow supercharging control device receives a pressure signal, checks the check bit in the message, ensures the transmission correctness, removes outliers and filters the pressure signal, compares with the supercharging pressure band after two-out-of-three voting, and outputs the storage tank supercharging control according to the preset rules.

10. A launch vehicle pressure sensor pad reuse system as in claim 1, wherein, The power supply switching circuit of the arrow power distribution device includes two first relays K1 and second relays K2, the ground direct measurement power supply is connected with the normally closed terminal 3 of the first relay K1 contact, the ground control power supply is connected with the common terminal 1 of the first relay K1 contact, the arrow battery is connected with the common terminal 1 of the second relay K2 contact, and the arrow pressure sensor is connected with the normally open terminal 2 of the first relay K1 contact and the normally open terminal 2 of the second relay K2 contact.

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