Device for airflow control of hypersonic flying vehicle

FIELD: rocketry and space engineering.

SUBSTANCE: proposed device has nose section 1 and central and additional aerodynamic needles 3 made in form of thin cylindrical rods which are stowed in special passages made in nose section of flying vehicle. One passage is located along axis of symmetry and other passages are located at some distance from axis of symmetry smoothly over circumference whose center lies at axis of symmetry. Each passage is provided with mechanism for delivery of aerodynamic needles towards incoming flow; provision is made for extension of each needle through definite length for forming special configuration of set of needles which is necessary for their joint operation in airflow control.

EFFECT: possibility of obtaining constant coordinate of center of pressure of hypersonic flying vehicle; reduced force of drag; possibility of forming control forces and moments for manoeuvring in atmosphere.

4 dwg

 

The invention relates to rocket and space technology. The predominant use is the improvement of aerodynamic characteristics of maneuvering in the atmosphere hypersonic aircraft (GLA) based on control flow.

The known device for controlling the aerodynamic resistance of the aircraft (LA) [1], comprising a retractable aerodynamic surfaces (flaps, spoilers, aerodynamic skirts etc) or working by changing parameters of the gas in the zones of separation and containing elements of energomashinen that implement the suction or blowing gas in the boundary layer or zone of separation. The disadvantages of these devices are design complexity, most of the additional weight and instability of the aerodynamic characteristics, which reduce the accuracy and controllability of the aircraft.

Closest to the claimed device is a device to control the aerodynamic resistance [2], containing the forebody aerodynamic needle, made in the form of a thin cylindrical rod with a conical tip supplied with additional aerodynamic needles placed in the device for the storage and supply of aerodynamic needle, and the control system. The device needed to reduce drag is paratov with the specified device, which is provided by the formation of zones of separation, close to conical (liquid cones), the pressure which is significantly less than prior devices without needles.

A significant disadvantage of this device is that the set of additional aerodynamic needle in the device for storage and filing, and the device itself for storage and supply of aerodynamic needles greatly aggravate the design of the bow of the aircraft despite the fact that the stored additional aerodynamic needles do not participate in the operation of the device during the whole flight. Also raises doubts about the claimed constant static stability of hypersonic aircraft, as during replacement of burnt aerodynamic needle on additional nose of the aircraft a certain period of time will be left without a control device.

The aim of the invention is to improve the aerodynamic characteristics on the basis of reduction of head resistance and the creation of control forces and moments for manageability hypersonic aircraft.

This objective is achieved in that known device for controlling the flow containing the nose and Central and additional aerodynamic needle, done is installed in the form of a thin cylindrical rods, equipped with a control system and executed in the fore part of the LA channels intended for the storage and supply of aerodynamic needle, and the control system. Moreover, the channels for the storage and supply of aerodynamic needles made in the form of cylindrical channels. One of the channels is located on the axis of symmetry, and the rest at a distance from the symmetry axis and evenly spaced around the circumference centered on the axis of symmetry, and each channel is equipped with a feed mechanism aerodynamic needle towards the incident flow with the possibility of extension of each of the needles towards the incident flow for compiling the configuration of the set of aerodynamic needles required for sharing their work management wrap CHAP.

Comparative analysis of the proposed device with the prototype shows that the introduction of the device of the set of aerodynamic needles specified configuration, device storage and filing and management system allows you to reduce the drag of the bow of the aircraft and to improve the controllability of the aircraft.

Figure 1 shows a General view of the device for controlling the flow hypersonic aircraft.

Figure 2 shows a front view of the device for controlling the flow hypersonic aircraft.

Figure 3, 4 pok is explained geometric characteristics of the device control flow hypersonic aircraft.

The device consists of a forward part 1, along the longitudinal axis of which is cylindrical guides channels 2, which is the extension of the aerodynamic needle 3, with the mechanisms of their nomination 4. At the end of the bow 1 on frames attached control system 5.

The operation of the device is as follows. On a signal from the control system 5 in accordance with the program voltage is supplied from the onboard source of power CHAP on the feeders aerodynamic needle 4. The feeders needles shall nominate an aerodynamic needle to a predetermined length relative to the bow of the aircraft and as the burning of the tips of the needles carry out a further extension of the needles, thus maintaining its length constant.

Aerodynamic needle is supposed to make of fiberglass or carbon fiber [2], the drift rate of the material on which large supersonic speeds is a reasonable amount of time, necessary for the normal functioning of the device.

Estimation of technical efficiency of the device is carried out by simulating flight conditions in a supersonic wind tunnel ST-3 (V=650 m/s (M=4,15)). Experimental data were obtained for various lengths as the Central aerodynamic needle, and on the additional needles, determining the configuration of a set of needle device control flow.

The proposed structural diagram of a device for controlling the flow GLA can be used when developing and designing a space re-entry vehicles engaged in planning the descent in the atmosphere, in the development and design of aerospace aircraft, as well as in the development of new types of items of combat equipment missiles.

Literature

1. Krasnov NF and other Aerodynamics separated flow: Uch. aid for technical Colleges. /Nfree, Vinceremos, Vtechnology; edited Nfresh. - M.: Higher school, 1988. - 480-482 C.

2. Galkin N.A., Bashkatov I.P., Tugushev NN. Description of the invention to the patent of the Russian Federation: the Application 96118391/02, 12.09.1996.

Device to control the flow hypersonic aircraft, containing axisymmetric nose, center, and additional aerodynamic needle, made in the form of a thin cylindrical rods, characterized in that the bow is made of cylindrical channels placed in them aerodynamic needles, and one of the channels is located on the axis of symmetry, and the rest at a distance from the symmetry axis and evenly spaced around the circumference centered on the axis of symmetry, and each channel is equipped with a feed mechanism aerodynamic needle nest ECU incident flow with the possibility of extension of each of the needles to form the configuration of a set of aerodynamic needles, necessary for their joint work on the control flow hypersonic aircraft.



 

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