JPH06247399A - Automatic flight safety operating device of spacecraft - Google Patents

Abstract

PURPOSE:To automatically effect safe operation of spacecraft (rocket, etc.) inside an onboard computer provided in the spacecraft. CONSTITUTION:An onboard computer 2 provided in spacecraft 1 calculates the position, velocity and attitude of the spacecraft 1 using a navigation calculating function 4, and a flight condition judging function 5 is used to originate judgment data on whether or not the spacecraft 1 should be destroyed according to the reference data of a flight safety related data base and to the current flight condition, and a destruction judging function 7 is used to make a final decision on whether or not the spacecraft should be destroyed. When the spacecraft is to be destroyed, a destruction signal is outputted so that a destruction device 9 destroys the spacecraft 1. The condition of the spacecraft 1 is outputted from a telemetry data transmission unit 10 and transmitted directly or via a relay satellite 11 to a terrestrial radar 12.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an automatic flight safety operation device applied to the function of a computer mounted on space equipment.

[0002]

2. Description of the Related Art Flight safety operation of space equipment has been conventionally performed as shown in FIG. That is, the flight status data sent from the space device 01 such as a rocket is received by the ground radar station 02, and based on the laser data acquired by the ground radar station 02, the large-scale computer 03 on the ground determines the flight status and monitors it. Various monitor diagrams are shown by the device 04. When it is necessary to destroy the space device 01, a person pushes the command destruction button 05 from the ground by operating a button. Then, the destruction signal is sent to the space device 01, the destruction device mounted on the space device 01 operates, and the space device 0
I was destroying 1.

[0003]

A real-time monitor is essential for determining the flight status of space equipment. Therefore, during the period when the flight status needs to be monitored, the flight data of the space equipment can always be acquired from the ground radar (visible range). It is necessary to set the flight plan (position, velocity, attitude) so that the aircraft will fly to (1).

In order to satisfy the above requirements, it is necessary to sacrifice the payload loading capacity of space equipment, and a great deal of time is required when preparing a flight plan.

During operation, it is necessary to have personnel for operations such as ground radar and ground-based computer, including backup personnel. Considering the period of data preparation, practice, etc., high cost is required, and space equipment launch price. Has contributed to the rise. In addition, the above radar and computer
Maintenance is required during the period without a launch, which also contributes to the price increase.

In view of the above-mentioned prior art, it is an object of the present invention to provide an automatic flight safety operation device for space equipment, which is capable of automatically performing flight safety operation in the space equipment.

[0007]

According to the present invention for solving the above-mentioned problems, the flight situation data of the navigation calculation result (position, velocity, attitude, etc.) and the aircraft flight data (engine combustion pressure, etc.) and the flight safety-related data base. Flight status judgment function to judge the flight status by inputting (nominal flight plan, destruction limit line data, etc.) and destruction judgment execution function to send a destruction signal to destroy space equipment based on the judgment in the flight status judgment function Is equipped in a space-equipped computer, and the space equipment is further equipped with a telemetry / data transmission device for transferring the determined flight status and destruction signal to the ground station.

[0008]

[Operation] From the data of position, velocity, attitude, etc. obtained from the navigation calculation results, the predicted drop points of the space equipment, orbital elements, etc. are calculated by the flight status judgment function. These data will be compared with nominal flight plans, etc., based on flight safety-related data, and also compared with aircraft condition data to prepare data that can be used to judge whether the aircraft should be destroyed. Based on this data, a signal is sent to the destruction device mounted on the aircraft only when the conditions for destruction are satisfied. Since these working conditions need to be communicated to people on the ground, they are added to conventional airframe telemetry signals and data is transferred to the ground. Since these operations can be performed even at locations where space equipment cannot be directly confirmed from the ground, in that case, data transfer can be performed by inter-satellite communication via a data relay satellite in a geostationary orbit.

[0009]

Embodiments of the present invention will be described below in detail with reference to the drawings. FIG. 1 shows an embodiment of the present invention. In this embodiment, the space computer 1 such as a rocket is mounted on the on-board computer 2, IMU.
An (Intertial Measuring Unit) 3, a destruction device 9, and a telemetry / data transmission device 10 are provided. The IMU 3 is composed of an accelerometer and a gyro for determining the velocity and position of a vehicle with respect to a certain reference coordinate in inertial navigation or guidance, and may also include a certain type of computer. Aircraft flight data 8 and external data 14 are input to the onboard computer 2. GP as external data
S (Golbal Positioning System) etc.

The on-board computer 2 is equipped with a navigation calculation function 4, a flight status judgment function 5, a flight safety related data base 6, a destruction judgment execution function 7 and a guidance control function 15.

As components outside the space equipment, there are a data relay satellite 11, a ground radar 12, and a ground monitor device 13 in geostationary orbit.

The flight status judgment function 5, flight safety related data base 6, and destruction judgment execution function 7 in the on-board computer 2 are functions added by the present invention, and other components are conventional functions or slightly modified. Function can be achieved.

Position, velocity, and attitude information, which are the navigation calculation results based on the velocity and angular velocity increments, which are the outputs of the IMU 3 mounted on the spacecraft 1, are one of the basic inputs to this additional function. Is not sufficient, the external data 1 such as GPS is used in the present invention for the purpose of improving accuracy.
In principle, the high-precision navigation calculation function 4 by 4 is used.

From the position, velocity, and attitude information, the flight status judgment function 5 obtains data (predicted drop point, current position of the aircraft, orbital perigee altitude, etc.) necessary for flight safety operation.
This data and airframe flight data (engine combustion pressure etc.) 8 that can be acquired by conventional functions and flight safety related data
It is compared with reference data (nominal data, normal range dispersion data, conditions for destroying the aircraft, etc.) that have been entered in advance in the base 6, and data for determining whether or not to destroy the aircraft is created.

Next, the destruction judgment execution function 7 makes a final judgment on the destruction based on the present judgment data and the same data obtained several times in the past. The destruction device 9 receiving the destruction signal explodes and destroys the space device 1.

The above series of operations is carried out each time navigation calculation is carried out, and the result is always transmitted to the ground by the telemetry data transmitter 10 together with other airframe telemetry data so that a person on the ground can constantly monitor it. To Since this transmission is also performed in a flight range where the spacecraft 1 cannot be seen (visible) from the ground radar 12, the transmission is performed via the data relay satellite 11 in the geostationary orbit at that time. With the data sent to the ground, the status of the space equipment can be constantly monitored by the ground monitoring device 13.

[0017]

According to the present invention, the following effects can be obtained.

(1) By automatically performing the flight safety operation of the space equipment in the on-board computer, it becomes unnecessary to be visible from the ground radar station even in the flight section where the flight situation needs to be monitored, and the flight plan can be flexible. As a result, flight planning time is shortened. Also, the payload loading capacity will increase as the above constraint conditions are eliminated.

(2) Since the personnel, the large-scale computer (including maintenance), and the work required for the flight safety operation conventionally performed on the ground are not required, the launch cost of space equipment is greatly reduced.

(3) The same effect as (1) can be expected by performing data transfer via a data relay satellite on a geostationary orbit.

[Brief description of drawings]

FIG. 1 is a configuration diagram showing an embodiment of the present invention.

FIG. 2 is a configuration diagram showing a conventional technique.

[Explanation of symbols]

 1 Space Equipment 2 On-board Computer 3 IMU 4 Navigation Calculation Function 5 Flight Status Judgment Function 6 Flight Safety Related Data Base 7 Destruction Judgment Execution Function 8 Aircraft Flight Data 9 Destruction Device 10 Telemetry Data Transmission Device 11 Data Relay Satellite 12 Ground Data 13 Ground monitor

Claims (1)

[Claims] 1. A navigation calculation function for obtaining the position, velocity, and attitude of space equipment, and a comparison of the data and airframe flight data obtained by the navigation calculation function with reference data input to a flight safety-related data base. It has a flight situation judgment function that creates judgment data whether to destroy space equipment, and a destruction judgment execution function that decides whether to destroy based on the judgment data and outputs a destruction signal when destroying, On-board computer mounted on space equipment, equipped on space equipment, destruction device that destroys space equipment when receiving the destruction signal, equipped on space equipment, the judgment data and the destruction signal An automatic flight safety operation device for space equipment, which is equipped with a telemetry / data transmission device for sending to the ground.