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The model’s programmed control was performed by the on-board autonomous control system, which was receiving information from inertial navigation system.

On sub-orbital trajectory the model angular orientation of the model was ensured by micro jet engines and after upper-air descending the model was controlled by plane-like control surfaces, which for the first time were used in our country at such great velocity and such great kinetic heating of material.

The flight range of the BOR-5 model from starting point to landing was approximately 2000 km. At 7…8-km altitude the on-board program control system forced the model by means of rudders into the tight spiral for decreasing of the flight velocity. And at approximately 3-km altitude the parachute was being developed to provide landing with 7¼8 m/s vertical speed (Figure 5).

Figure 5. The scheme of the BOR-5 model’s sub-orbital flight

The on-board telemetry system recorded all information internally and then transmitted it to the Earth for analyzing of aerodynamic characteristics. The information was received from several accelerometers, rate and acceleration sensors, free gyroscopes, pressure indicators, ailerons and rudder deviation sensors and sensor for measuring hinge moment on rudders. Besides, the information was transmitted from temperature thermocouples, calorimetric sensors and other temperature sensors.

The thermal indicator paint and the melting indicators were also used.

From 1984 five launchings have been fulfilled:

• 501 model – on 6^th July, 1984;

• 502 model - on 17^th April , 1985;

• 503 model - on 27^th December, 1986;

• 504 model - on 27^th August, 1987;

• 505 model – on 22^nd June, 1988.

The first two launching were performed in accordance with a program of flight-design tests of launcher rocket specially modified for the BOR-5 model. They included tests of model system functionality.

During the first launching the separation of the model from rocket launcher didn’t appear because of electrical failure and they fell down together while the second launching was absolutely successful.

Three launching according to the program of the BOR-5 model test appeared to be successful, were passed and they provided specialists with the full amount of data needed. The actual lift-to-drag ratio of the model appeared to be greater than calculated one.

The BOR-5 model was designed in NPO MOLNIYA under the direction of Deputy Chief Designer Dr. Samsonov E.A. The leading designers were Mr. Bogov U.P. and then Grachev I.G.. The construction design was made under the direction of Mr. Kavunovsky N.P. by Mr.: Chistov V.A., Khorev D.M., Glotov V.I., Mendzilo V.V., Frolkov V.M., Kiryanov I.V and other.

The models were produced on the Myasischev V.M. Experimental Machine-Building Plant under the direction of Mr.: I.M. Lipkin I.M. and Tvorogov N.G..

The BOR-4 and BOR-5 models were equipped with autopilots with a computer and on-board measure system. These systems were produced by the Flight Research Institute (Ministry of Aircraft Industry) under the leaderships of Dr. Vladychin G.P., Dr. Kondratov A.A., Dr. Fedorovich A.A., Mr. Khanov I.K. and Tishenko V.V.

The tests of both model versions (BOR-4 and BOR-5) were performed by the representatives of LII under the direction of Dr. Vladychin G.P. and Dr. Kondratov A.A. The specialists of the Military-Research Institute, NPO MOLNIYA and other organization under general supervision of the State Commission, headed by the first Deputy Director of GUKOS, General of aviation, Mr. Titov G.S. also took part in testing.

The Conclusion

The application of orbital and sub-orbital flying models for the confirmation by experimental data of the heat protection efficiency and reliability of aerodynamic calculation became a news in developing of the aerospace systems (ASSs) and was fulfilled for the first time in the world. Such models will find the application in further researches of aerospace systems (ASS).

The tests results of the BOR-4 flying model were used not only in the BURAN program, but also in development of the MAKS Multipurpose aerospace system with the AN-225 MRIA subsonic carrier aircraft. The orbital plane in this system as well as the SPIRAL plane and BOR-4 experimental plane have identical aerodynamic scheme ‘lifting body’ with deflected wing panels.

Wide experience of experimental researches in natural conditions of the BOR-5 model’s orbital and sub-orbital flight and SPIRAL analogue’s launching allowed to choose a well-founded aerodynamic configuration of orbital plane of the MAKS advanced system. In the nearest future this system will allow to decrease the cost of space missions and open new possibilities for fulfilling different tasks due to the advantages of air launch from the subsonic carrier-plane.

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