RU135620U1 - EMERGENCY DETECTION DETECTION DEVICE FOR ROCKET AND SPACE ENGINEERING PRODUCTS - Google Patents

Abstract

A device for detecting the emergency state of rocket and space technology products, containing an information storage unit and a radio transmitter with an antenna, characterized in that it has a microprocessor located in a space protected from radiation from outer space radiation and connected by an information storage unit and sensors that record the fact of the collision of the product with space debris particles and the effects of external radiation, and the unit for preliminary processing of the signal from the sensors, while all the hardware devices Twa amortized located on the platform placed in the lower housing part, the upper part of the apparatus body installed battery and antenna radio transmission apparatus is made of a microstrip and has four units arranged on a side surface of the intermediate housing part.

Description

The proposed device relates to the field of rocket and space technology (RKT) and is intended to detect the cause of the emergency state of the RKT product during its operation, and primarily at the stage of launching and putting the product into orbit.

Analysis of statistical data for the last 10 years on launches of RCT products showed that at the stage of launching and putting products into orbit, at least 8% of accidents occur annually. However, it is not always possible to find out the cause of the accident, in particular, due to the failure of the standard on-board telemetry system and when the RCT product was outside the radio visibility zone from the product launch area, which is especially typical for domestic RCT products. As a result, the conclusion suggests itself that it is necessary to monitor the output of the product throughout this stage, for which it is necessary to have a sufficient number of mobile tracking stations, placing them appropriately outside the radio visibility zone from the territory of the country that launched the product, or to have relay satellites for this purpose. However, these tools become useless if the standard on-board telemetry system of the launched product fails. In these conditions, it seems appropriate to equip the launched product with an autonomous system (device) for detecting the emergency state of the product.

Similar devices are known. For example, according to the patent RU2281240 of 08/10/2006, IPC В66С (the first analogue), it is envisaged to obtain data on parameters characterizing the load and spatial position of the load-lifting machine controlled by the driver, with the possibility of writing parameters to the device memory and reading if necessary.

However, this device is not intended to register, for example, the fact of collision with elements of space debris and the fact of exposure to radiation from outer space and the impact of mechanical loads.

The device according to the patent FR 2819084 (A1), G07C 7/00, 07/05/2002 (2nd analogue) is also known, according to which the system for recording vehicle parameters (land, sea, air) includes a means for storing vehicle parameters before and during its accident, the control unit and the radio transmitter, transmitting information including through the satellite-relay at the request signal. However, this device is also not designed to record the fact of collision with elements of space debris and the fact of exposure to an external radiation source that can damage the telemetry system, which, given the scope of the proposed utility model, does not have sufficient reliability. The control unit has the limited task of giving, upon request, a signal for the issuance of the requested information, and, in addition, the design of the antenna is not defined in this analogue. This analogue of the device is quite large, in particular, due to the availability of means of ejection of the storage device, it does not have protection against vibration and shock loads, however, it is the closest to the claimed device and is selected as a prototype.

The purpose of the proposed technical solution is to ensure the registration and transmission to the Earth of the facts of collision of the RKT product with elements of space debris, as well as the impact of radiation from it on outer space, ensuring the independence of the operation of the emergency state detection device from the state of standard onboard telemetry and power supply systems, in conditions of radiation outer space and mechanical loads.

This goal is achieved by the fact that a microprocessor is installed in the device for detecting the emergency state of a rocket and space technology device, which is connected with sensors that record the fact of the collision of the product with particles of space debris and the effects of outer space radiation, forming an information frame for transmitting it via radio channel to Earth, a preliminary processing unit signal from sensors, as well as a stand-alone battery. All device hardware is located on a shock-absorbing platform located in a casing protected from radiation from outer space.

The technical result of the device for detecting the emergency state of an RCT product is its autonomy, independence from standard on-board telemetry and power supply systems when recording facts of a collision of a product with space debris and exposure to radiation from outer space.

Structurally, the proposed device includes:

- an autonomous power source, for example, in the form of a battery of lithium-ion batteries;

- microprocessor device;

- information storage device;

- secondary power supply;

- a unit for preliminary processing of signals from sensors recording the fact of the collision of the product with space debris elements;

- a device for collecting messages from sensors;

- radio transmitting device;

- antenna-feeder device made in the form of four small antenna units placed on the outer surface of the housing;

- a housing consisting of three parts and containing a shock-absorbing platform and connectors (sockets) for connecting sensors;

- piezo and fiber optic sensors.

In a microprocessor device, the main element is a microprocessor, which is a software-controlled device that polls sensors that monitor the technical condition of the product’s systems and sensors that record the effect of outer space on the RCT product, which processes the received information and transfers it to the information storage device, which is then read by the microprocessor and is formed by him in the form of an information frame for transmission to Earth using a radio transmitting device, directs the microprocessor. The presence of a microprocessor ensures the independence of the operation of the device from the state of the standard on-board telemetry system, due to failure of which it is often not possible to find out the cause of the emergency condition of the product.

To fix the fact of collision with particles of space debris, it is most appropriate to use acoustic emission sensors (piezoelectric sensors) (see patent No. 2402468 of 10.27.2010), the signal from which is proposed to be converted in a pre-processing unit introduced into the device for detecting the emergency state of the product Rkt. To register the fact of irradiation of the product with an external radiation source, a fiber-optic sensor can be used (see patent No. 2432553 of 10.27.2011).

The device’s equipment is proposed to be placed in a protective case (see the decision to grant a patent for a utility model, ref. No. 2012107018/07 (010688) dated 03/21/12), which allows protecting the device’s equipment from radiation from outer space and from mechanical loads, as well as mount microstrip antenna blocks with minimum overall dimensions of the housing.

Each of the four blocks of a microstrip antenna with a U-shaped slit excited by a coaxial probe is a thin conductive plate on a dielectric substrate (expanded polystyrene), bounded on the opposite side by the screen plane. The thickness of the substrate is taken to be approximately 0.07 of the length of the radio wave. (See V.F. Elk “Microstrip and Dielectric Resonator Antennas for CAD-Models of Mathematical Modeling.” Antennas NTTZh, 2002 No. 11 (66) p. 34-77). On each of the four sides of the housing there is a corresponding opening for mounting the antenna unit.

In addition to an autonomous power source, the device also has a secondary power source.

The secondary power source has a circuit for analyzing the state of the onboard power supply system and, in the event of the failure of the latter, it switches to an independent power source.

A self-contained power supply, for example, in the form of a battery of lithium-ion batteries of the 32650 series, MagicSihine 5000 is proposed to be placed in the upper part of the housing. Moreover, for a more compact placement of the battery, it is advisable to use batteries with a rectangular cross-section. Batteries with their mass provide protection of downstream equipment from radiation of outer space, which allows to reduce the mass of the upper part of the body, and therefore the mass of the entire device.

In the lower part of the housing there is a shock-absorbing platform for the device hardware, as well as connectors (sockets) for connecting conductors from sensors.

The figure 1 shows a General view of the device, where it is indicated: 1 - the lower part of the housing, 2 - the middle part of the housing, 3 - the upper part of the housing, 4 - an autonomous power source in the form of a battery flooded with epoxy compound, 5 - microstrip slot antenna unit, 6 - coaxial probe, 7 - radio transmitting device, 8 - board with a secondary power source, 9 - board with a microprocessor device, information storage and message collection devices, 10 - board with a unit for preliminary processing of signals from sensors recording the fact of stress products with space debris particles, 11 - the shock-absorber, 12 - amortized platform 13 - connector (female).

The equipment is installed on a shock-absorbing platform 12 without the middle 2 and upper 3 parts of the body. At the final stage of installation, after installing the middle part of the housing 2 on the lower part of the housing 1, access is made to the coaxial probe 6 of the antenna and the cables from the battery 4 are connected, after which the upper part of the housing 3 with the battery 4 is installed.

In FIG. 2 shows a variant of the structural diagram of the proposed device, where it is indicated: 4 - autonomous power supply (AIP), 5 - microstrip slot antenna unit (antenna-feeder device-AFU), 7 - radio transmitting device (RPDU), 8 - secondary power source (VIL ) with a circuit for analyzing the state of the on-board power supply system (BOT), 9 - microprocessor device (MPU), 10 - pre-processing unit (BPO), 14 - information storage device (ultrasound), 15 - address / data bus (included in the MPU) , 16 - input / output port (included in the MPU), 17 - mouth Message Collection Devices (CSS).

The proposed utility model ensures the independence of the device for detecting the emergency state of the RCT product from onboard standard telemetry and power supply systems, recording the facts of the collision of the product with particles of space debris and irradiation with an external radiation source, as well as the protection of the device hardware from radiation from outer space and from mechanical loads while providing the smallest possible overall mass parameters of the proposed device.

Claims (1)

A device for detecting the emergency state of rocket and space technology products, which contains an information storage unit and a radio transmitter with an antenna, characterized in that it has a microprocessor located in a space protected from radiation from outer space radiation and is connected by an information storage unit and sensors that record the fact of the collision of the product with space debris and the effects of external radiation, and the unit for preliminary processing of the signal from the sensors, while all the hardware devices Twa amortized located on the platform placed in the lower housing part, the upper part of the apparatus body installed battery and antenna radio transmission apparatus is made of a microstrip and has four units arranged on a side surface of the intermediate housing part.

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