A launch vehicle avionics system and control method

Abstract

The present invention discloses a carrier rocket avionics system and control method, belonging to the field of spacecraft control technology, including an integrated control device and a signal acquisition device, wherein the integrated control device is installed at the first core stage and is used to control the controlled terminal on the booster stage; the signal acquisition device is installed at the first core stage and includes a head acquisition device and a tail acquisition device; the head acquisition device is used to acquire signals from sensors arranged at the interstage section of the booster stage; the tail acquisition device is used to acquire signals from sensors arranged at the tail section of the booster stage. The present invention can effectively reduce the complexity of the carrier rocket avionics system, while reducing the weight of the carrier rocket avionics system, effectively improving the production efficiency of the carrier rocket and improving the carrying capacity.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft control technology, and in particular to an avionics system of a launch vehicle and a control method thereof. Background Art

[0002] my country's current launch vehicles are mainly liquid rockets, and rockets with boosters are mainly liquid boosters. Compared with liquid rockets, solid launch vehicles have advantages such as high reliability, strong rapid launch capability, and relatively simple control. However, due to the limited thrust of solid engines, launch vehicles with only solid core stages are difficult to form a large carrying capacity. Therefore, the overall rocket plan that uses a solid core stage bundled with solid boosters can greatly improve the carrying capacity of solid launch vehicles.

[0003] For launch vehicles with boosters, the avionics system architecture is often more complex, requiring a series of equipment such as controllers, editors, and batteries to be designed on each booster, and the equipment on each booster controls the control object on the booster. At the same time, due to factors such as the large number of sub-stages, the large number of control objects, and the complex connections, the number and complexity of avionics system equipment on launch vehicles with boosters tend to increase significantly. In addition, since launch vehicles with boosters are often larger in scale and carrying capacity, the reliability requirements for avionics systems are often higher, which further increases the complexity of the system. The above situation is particularly prominent on launch vehicles with solid core stages bundled with solid boosters.

[0004] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0005] In order to solve the above-mentioned technical problems, the present application provides a launch vehicle avionics system and control method, especially for a launch vehicle with a solid core stage bundled with solid boosters, which can effectively reduce the complexity of the launch vehicle avionics system, while reducing the weight of the launch vehicle avionics system, effectively improving the production efficiency of the launch vehicle and improving the carrying capacity.

[0006] A launch vehicle avionics system, comprising:

[0007] An integrated control device, which is installed on the core stage and is used to control the controlled terminal on the booster stage;

[0008] A signal acquisition device, which is installed at the core stage, and includes a head acquisition device and a tail acquisition device; the head acquisition device is used to acquire signals from sensors arranged at the interstage section of the booster stage; the tail acquisition device is used to acquire signals from sensors arranged at the tail section of the booster stage;

[0009] The integrated control device and the controlled terminal, the head acquisition and editing device and the sensor arranged in the interstage section of the booster stage, and the tail acquisition and editing device and the sensor arranged in the tail section of the booster stage are all electrically connected through lines with separate connectors.

[0010] Preferably, the controlled terminals on the booster stage include the booster stage interstage controlled terminals and the booster stage tail stage controlled terminals; the booster stage interstage controlled terminals include the engine safety mechanism controlled terminals, the engine igniter controlled terminals, the main bundled separation pyrotechnic controlled terminals and the first thruster rocket controlled terminals; the booster stage tail stage controlled terminals include the engine servo mechanism controlled terminals, the bundled connecting rod separation pyrotechnic controlled terminals and the second thruster rocket controlled terminals.

[0011] Preferably, the integrated control device is arranged in the interstage section of the first core stage; the head collecting and editing device is arranged in the interstage section of the first core stage; and the tail collecting and editing device is arranged in the tail section of the first core stage.

[0012] Preferably, the integrated control device and the controlled terminal on the booster stage are communicatively connected via a 1553B bus protocol.

[0013] Preferably, when the integrated control device and the controlled terminal on the booster stage are communicatively connected via the 1553B bus protocol, a single controlled terminal on the booster stage is electrically connected to the bus via a single coupler or a single switch connected to a sub-line.

[0014] Preferably, the coupler or the switch is arranged in the booster stage where the controlled terminal connected thereto is located, and the coupler or the switch is arranged close to the separation connector of the tail section of the booster stage.

[0015] Preferably, the controlled terminal of the engine safety mechanism, the controlled terminal of the main binding separation pyrotechnic device and the controlled terminal of the binding link separation pyrotechnic device are all connected to the main line by parallel wires.

[0016] Preferably, the power supply lines and signal acquisition lines of the sensors in the interstage section of the booster stage and the sensors in the tail section of the booster stage are both twisted-pair shielded lines.

[0017] According to another aspect of the present application, a launch vehicle control method is also provided, which is controlled by using the launch vehicle avionics system, including: when using an integrated control device to control the controlled terminal on the booster stage, a time-sharing control strategy is adopted, including: time-sharing control of each engine insurance mechanism controlled terminal on each booster stage one by one; when separating the control terminal used to implement the booster stage, time-sharing control is performed in a manner where the two booster stages are the same separation group.

[0018] Preferably, when the control terminal for realizing the booster stage is separated and controlled, the two booster stages are set as the same separation group for time-sharing control, and the two booster stages symmetrically arranged on both sides of the core stage are set as the same separation group.

[0019] Compared with the prior art, this application has at least the following beneficial effects:

[0020] 1. The present invention is particularly suitable for a pure solid launch vehicle with a solid core stage bundled with a solid booster, which can effectively reduce the complexity of the launch vehicle's avionics system, reduce the number of avionics system devices on the rocket, reduce production costs, and improve the assembly efficiency of the launch vehicle.

[0021] 2. The present invention can effectively reduce the weight of the launch vehicle's avionics system and effectively improve the launch vehicle's carrying capacity. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings:

[0023] Figure 1 It is a system connection schematic diagram of the launch vehicle avionics system of the present invention;

[0024] Figure 2 The figure is a schematic diagram of the connection of the 1553B communication bus in the launch vehicle avionics system of the present invention.

[0025] The above drawings include the following reference numerals:

[0026] 10. Booster-level controlled terminal A; 20. Booster-level controlled terminal B; 30. Booster-level controlled terminal C; 40. Booster-level controlled terminal D; 50. Core-level controlled terminal; 100. Core-level; 200. Booster-level; 201. Booster-level I; 202. Booster-level II; 203. Booster-level III; 204. Booster-level IV; 300. Integrated control equipment; 400. Head acquisition and editing device; 500. Tail acquisition and editing device. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0028] For launch vehicles with solid boosters, the number of controlled objects on each booster stage is not large. Considering that the controlled objects or connection objects on the booster stage are all set at the head or tail, and the connection points between the booster stage and the core stage are also located at the interstage and tail sections of the core stage, the equipment installed on the core stage can be used to control the controlled objects on the booster stage, thereby greatly reducing the number of equipment and reducing the complexity of the system.

[0029] The control device adopts an integrated design and is implemented by an integrated control device installed in the interstage section of the core.

[0030] The signal acquisition equipment adopts a distributed design and is implemented by two devices, including a head acquisition device installed in the interstage section of the first core stage and a tail acquisition device installed in the tail section of the first core stage. When collecting sensor signals, relevant sensor signals are collected nearby. That is to say, according to the scheme of collecting relevant sensor signals nearby, the head acquisition device installed in the interstage section of the first core stage is used to collect sensor signals of multiple booster stage interstage sections close to it, and the tail acquisition device installed in the tail section of the first core stage is used to collect sensor signals of multiple booster stage tail sections close to it.

[0031] This solution is particularly suitable for launch vehicles with solid core stages bundled with solid boosters. It can reduce the number and complexity of equipment in the avionics system of launch vehicles with solid booster stages, reduce costs, and improve carrying capacity.

[0032] like Figure 1 and Figure 2 As shown, an avionics system of a launch vehicle includes: an integrated control device 300 and a signal acquisition device. The integrated control device 300 is installed on the core stage 100 and is used to control the controlled terminal on the booster stage; the signal acquisition device is installed on the core stage 100, including a head acquisition device 400 and a tail acquisition device 500. The head acquisition device 400 is used to acquire signals from sensors arranged in the interstage section of the booster stage, and the tail acquisition device 500 is used to acquire signals from sensors arranged in the tail section of the booster stage.

[0033] The integrated control device 300 and the controlled terminal, the head acquisition and editing device 400 and the sensor arranged in the interstage section of the booster stage, and the tail acquisition and editing device 500 and the sensor arranged in the tail section of the booster stage are all electrically connected through lines with separate connectors.

[0034] In this embodiment, the launch vehicle includes a core stage 100 and four booster stages 200 symmetrically arranged around the core stage 100 along the axis of the core stage 100. The core stage 100 includes a core stage solid engine, a core stage interstage and a core stage tail section, the core stage interstage is fixedly arranged at the upper end of the core stage solid engine, and the core stage tail section is fixedly arranged at the lower end of the core stage solid engine. The booster stage 200 includes a booster stage interstage, a booster stage solid engine and a booster stage tail section, the booster stage interstage is fixedly arranged at the upper end of the booster stage solid engine, and the booster stage tail section is fixedly arranged at the lower end of the booster stage solid engine. The four booster stages 200 are divided into booster stage I 201, booster stage II 202, booster stage III 203 and booster stage IV 204. The booster-level controlled terminals are divided into a booster-level controlled terminal A10, a booster-level controlled terminal B20, a booster-level controlled terminal C30 and a booster-level controlled terminal D40.

[0035] When collecting relevant sensor signals, the head collecting and editing device 400 installed in the interstage section of the core first stage is used to collect the sensor signals set in the interstage section of the booster stage in booster stage I 201, booster stage II 202, booster stage III 203 and booster stage IV 204, and the tail collecting and editing device 500 installed in the tail section of the core first stage is used to collect the sensor signals set in the tail section of the booster stage in booster stage I 201, booster stage II 202, booster stage III 203 and booster stage IV 204, so as to realize the local collection of relevant sensor signals, thereby avoiding the influence of electromagnetic interference on the sensor signals during long-distance cable transmission, and also reducing the attenuation of the signal during transmission.

[0036] The booster-level controlled terminal A10 is located in the booster-level Ⅰ201, the booster-level controlled terminal B20 is located in the booster-level Ⅱ202, the booster-level controlled terminal C30 is located in the booster-level Ⅲ203, and the booster-level controlled terminal D40 is located in the booster-level Ⅳ204.

[0037] The integrated control device 300 is arranged in the interstage section of the core 1, the head acquisition and editing device 400 is arranged in the interstage section of the core 1, and the tail acquisition and editing device 500 is arranged in the tail section of the core 1. The controlled terminals on the booster stage 200 include the booster stage interstage section controlled terminals and the booster stage tail section controlled terminals.

[0038] Specifically, the controlled terminals of the booster stage interstage section include the controlled terminals of the engine safety mechanism, the controlled terminals of the engine igniter, the controlled terminals of the main bundled separation pyrotechnics and the controlled terminals of the first thruster rocket; the controlled terminals of the booster stage tail section include the controlled terminals of the engine servo mechanism, the controlled terminals of the bundled connecting rod separation pyrotechnics and the controlled terminals of the second thruster rocket.

[0039] Preferably, the integrated control device 300 and the controlled terminal on the booster stage 200 are communicated with each other via a 1553B bus protocol.

[0040] When the integrated control device 300 and the controlled terminal on the booster stage communicate via the 1553B bus protocol, each working unit including the bus controller and each controlled terminal is coupled to the bus via a transformer, and to ensure the communication effect, under the condition of transformer coupling, the sub-line length does not exceed 6m.

[0041] In this embodiment, a single controlled terminal on the booster stage is electrically connected to the bus through a single coupler or a single switch connected to a sub-line to prevent the sub-line length from exceeding 6m. It should be noted that the coupler here refers to a general coupler, which is used for transformer coupling connection between the sub-line and the bus. The switch refers to a switchable coupler that can realize the switching of the main line and bus load through a switch. When the launch vehicle is multi-stage separated, after a certain stage of equipment is disconnected, the bus is switched to the bus load to reduce bus signal radiation and reflection.

[0042] Preferably, the coupler or the switch is arranged in the booster stage 200 where the controlled terminal connected thereto is located, and the coupler or the switch is arranged close to the separation connector at the tail section of the booster stage, so that the length of the sub-line connected to the controlled terminal can be further shortened.

[0043] Preferably, the engine insurance mechanism controlled terminal, the main bundled separation pyrotechnic controlled terminal and the bundled connecting rod separation pyrotechnic controlled terminal are all controlled terminals with large current demand during the control process, and the voltage drop of the sub-line connected thereto is large. The engine insurance mechanism controlled terminal, the main bundled separation pyrotechnic controlled terminal and the bundled connecting rod separation pyrotechnic controlled terminal are all connected to the main line in parallel with the wire, so as to reduce the impedance of the sub-line and effectively control the voltage drop.

[0044] Furthermore, when the number of the separated connector contacts is limited by the number of welded wires, a crimping terminal is provided on the sub-wire, and the crimping terminal is used to realize the conversion of a single wire into multiple wires.

[0045] Preferably, the power supply lines and signal acquisition lines of the sensors in the interstage section of the booster stage and the sensors in the tail section of the booster stage are both made of twisted-pair shielded cables. The use of twisted-pair shielded cables can prevent the sensor signals from being affected by electromagnetic interference during long-distance cable transmission, and also reduce signal attenuation during transmission.

[0046] As another embodiment of the present invention, the integrated control device 300 is also used to control the core-level controlled terminal 50 .

[0047] A launch vehicle control method is provided, which uses the launch vehicle avionics system for control, including: when using the integrated control device 300 to control the controlled terminal on the booster stage 200, a time-sharing control strategy is adopted, including: time-sharing control is performed on each engine insurance mechanism controlled terminal on each booster stage 200 one by one; when separation control is performed on the control terminal used to realize the booster stage 200, time-sharing control is performed in a manner that two booster stages are the same separation group.

[0048] Since there are control objects on all four boosters, the current is very large when they are controlled simultaneously, which is costly for the avionics system design. The time-sharing control strategy can greatly reduce the current demand, and thus the voltage drop can be better controlled.

[0049] Preferably, when the control terminal for realizing the separation control of the booster stage 200 is used, the two booster stages symmetrically arranged on both sides of the first core stage are set as the same separation group in the time-sharing control. This control method can ensure that the two booster stages symmetrically arranged on both sides of the first core stage act synchronously, thereby improving the stability of the launch vehicle.

[0050] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0051] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0052] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0053] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A launch vehicle avionics system, characterized in that: include: An integrated control device (300), the integrated control device (300) being installed on the core stage (100) and used to control a controlled terminal on the booster stage (200); A signal acquisition device, the signal acquisition device being installed on the core stage (100), comprising a head acquisition device (400) and a tail acquisition device (500); the head acquisition device (400) is used to acquire signals from a sensor disposed in the booster stage interstage section; the tail acquisition device (500) is used to acquire signals from a sensor disposed in the booster stage tail section; The integrated control device (300) and the controlled terminal, the head acquisition and editing device (400) and the sensor arranged in the booster stage interstage section, and the tail acquisition and editing device (500) and the sensor arranged in the booster stage tail section are all electrically connected via a line with a separate connector; The controlled terminals on the booster stage (200) include a booster stage interstage controlled terminal and a booster stage tail stage controlled terminal; the booster stage interstage controlled terminal includes an engine insurance mechanism controlled terminal, an engine igniter controlled terminal, a main bundle separation pyrotechnic controlled terminal and a first side thrust rocket controlled terminal; The booster stage tail section controlled terminal includes an engine servo mechanism controlled terminal, a binding connecting rod separation pyrotechnic controlled terminal, and a second side thrust rocket controlled terminal; The integrated control device (300) is arranged at the inter-stage section of the first core stage; the head collecting and editing device (400) is arranged at the inter-stage section of the first core stage; and the tail collecting and editing device (500) is arranged at the tail section of the first core stage.

2. The launch vehicle avionics system according to claim 1, characterized in that: The integrated control device (300) is communicatively connected to the controlled terminal on the booster stage (200) via a 1553B bus protocol.

3. The launch vehicle avionics system according to claim 2, characterized in that: When the integrated control device (300) is connected to a controlled terminal on the booster stage (200) for communication via the 1553B bus protocol, a single controlled terminal on the booster stage (200) is electrically connected to the bus via a single coupler or a single switch connected to a sub-line.

4. The launch vehicle avionics system according to claim 3, characterized in that: The coupler or the switch is arranged in the booster stage (200) where the controlled terminal connected thereto is located, and the coupler or the switch is arranged close to the separation connector of the rear section of the booster stage.

5. The launch vehicle avionics system according to claim 4, characterized in that: The controlled terminal of the engine insurance mechanism, the controlled terminal of the main bundling separation pyrotechnic device and the controlled terminal of the bundling connecting rod separation pyrotechnic device are all connected to the main line in a parallel wire manner.

6. The launch vehicle avionics system according to claim 1, characterized in that: The power supply lines and signal acquisition lines of the sensors in the interstage section of the booster stage and the sensors in the tail section of the booster stage are all twisted-pair shielded cables.

7. A launch vehicle control method, characterized in that: Controlling the launch vehicle avionics system according to any one of claims 1 to 5 includes: using an integrated control device (300) to control the controlled terminal on the booster stage (200), adopting a time-sharing control strategy, including: performing time-sharing control on the controlled terminal of each engine insurance mechanism on each booster stage (200) one by one; and performing time-sharing control on the control terminal used to realize the booster stage (200) by separating and controlling the two booster stages (200) as the same separation group.

8. The launch vehicle control method according to claim 7, characterized in that: When the control terminal for realizing the booster stage (200) is separated and controlled, the two booster stages (200) are set as the same separation group for time-sharing control, and the two booster stages (200) symmetrically arranged on both sides of the core stage (100) are set as the same separation group.

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