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.
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) , 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 , 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 , 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.
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.
FIELD: spacecraft life-support systems.
SUBSTANCE: proposed system includes recoverable reservoir for drinking water whose rigid housing is provided with hermetic movable partition in form of bellows. Reservoir is connected with drinking water and gas sources and with user by means of pipe lines. Piston mounted in housing forms cavity for drinking water together with one of end plates of body and hermetic intermediate cavity with opposite end plate and said partition which is used for placing the changeable cartridges with absorbent for leakage through piston seal. Cavity between hermetic partition and said opposite end plate (interior of bellows) is communicated with gas source which is used for breathing of users. This system is used under weightlessness conditions without pressuring gas.
EFFECT: enhanced protection of reservoir walls and water against contamination with microorganisms.
2 c;, 1 dwg
FIELD: space engineering; devices and methods of maneuvering of spacecraft with the aid of solar sail.
SUBSTANCE: proposed method includes forming light-sensitive surface of solar sail and orientation of this surface in solar radiant flux. This surface is formed as cloud of finely-dispersed particles charged by solar photoelectrolizing. Stable shape close to sloping surface is imparted to cloud by means of electrostatic system of spacecraft. This system has at least one central and one concentric charge carriers of opposite signs. Control of shape and sizes of cloud may be performed by screening central charge or moving it relative to circular charge.
EFFECT: facilitated procedure; low expenses for deployment and control of spacecraft.
9 cl, 5 dwg
FIELD: rocketry and space engineering; development of new satellites and updating of present artificial satellites, 20 to 100 kg in mass.
SUBSTANCE: some parts of onboard equipment in proposed satellite are secured on radiation surface on inner side of solar battery framework. Other parts are located in pressure container; number of parts is dictated by condition of retaining thermal mode of equipment in pressure container. Solar sensors are mounted on end face of pressure container coupled with micro-satellite separation system. Sensors for operation with ground stations and sensors of scientific equipment are located on other end face of pressure container. They are mounted on rectangular plate fitted with bracket in form of parallelepiped whose side faces carry scientific sensor equipment. Mounted on opposite surface of plate are sensors for operation with ground stations and extensible gravitational boom. Mounted on end cargo of boom are optical sensors. Four L-shaped antennae are located in parallel relative to faces of plate.
EFFECT: reduction of satellite mass (by 10-12%) and its length (by 14-15%); enhanced reliability.
FIELD: mechanical engineering; production of constructions made out of composite materials of high-precision hardware products of space and land application.
SUBSTANCE: the invention is pertaining to the field of mechanical engineering, in particular, to production of constructions made out of composite materials for the high-precision hardware products of space and land designation, for example, conical nose cones of rocket carriers, transient bays, ring ramps. The lamellar sheathing is made out of layers of the fibrous material impregnated with a polymeric binding. Its each layer represents an unrolling or a part of a cone unrolling made in the form of a sector of a ring or a sector of a circle with a central angle β. In the capacity of the unidirectional fibrous material use a fibrous material impregnated with a polymeric binding. The central angle β of a sector of a ring or a sector of a circle makes 12-360 degrees. Each of layers of the lamellar sheathing consists of the placed butted to each other sectors with the equal central angle γ making 1-30 degrees. In each sector of one layer the fibers of the unidirectional fibrous material are located at the similar for this layer angle φ to the central axis of the sector equal to 0- ±90 degrees. The butts of the sectors of each subsequent layer are shifted in respect to the butts of the sectors of the previous layer at an angle δ composing a part of the central angle γ of the sector for. The technical result of the invention realization consists in creation of the sheathing with the stable physical-mechanical properties.
EFFECT: the invention ensures creation of the sheathing with the stable physical-mechanical properties.
FIELD: space engineering.
SUBSTANCE: rotation apparatus comprises casing (10), shaft (30) set in bearings (11) inside the casing, and motor (13) for rotating the shaft. Shaft (30) is provided with radial cantilevers (281) whose ends have a number of boxes (282) with experimental objects. The apparatus is provided with devices for damping vibration of the casing. Each of the devices has spring mechanism (255) that flexibly secures the casing to member (280) of the unmovable bearing and electromagnetic mechanism for setting. The latter comprises conductor (254) secured to member (280) and exciting coil (253) that embraces it and is mounted on the surface of casing (10). The coil is connected with the spring mechanism so that casing (10) is held by electromagnetic force that effects on conductor (254) when the coil is excited. The apparatus may be provided with a pickup that measures the space between casing (10) and member (280) of the bearing and control unit that receives the signals from the pickup. When the space exceeds a given value, the unit controls the current in exciting coil (253) to reduce casing vibration.
EFFECT: enhanced stability and improved vibration insulation of the apparatus.
7 cl, 8 dwg
FIELD: rocketry and space engineering; hermetic detachable joints for flying vehicle compartments.
SUBSTANCE: proposed joint consists of compartments forming threaded pair for butt connection of them. External thread is made on cylindrical body 4 of one of compartments and projection is strengthened with frame 5 provided with threaded seat 7 where captive retainer 7 of threaded pair is placed. Threads of pair have longitudinal slots 10 whose depth exceeds depth of thread and their length is no less than length of thread. Slots give free passage for respective projections of external and internal threads; projections are screwed together and their longitudinal planes of symmetry are aligned.
EFFECT: reduced mass; improved service characteristics.
4 cl, 4 dwg
FIELD: locks for developed position of swivel structural members of satellite, solar battery panels or antennae.
SUBSTANCE: proposed device includes articulation with leaf spring secured on its part; spring has hole in its free end; secured as cantilever on other part is rod whose free end may be engageable with hole of leaf spring. Parts are provided with two stops for their engagement in fixed position; one stop is rigid for limitation of relative rotation of parts during opposite motion; other stop is spring-loaded for avoidance of backlash in joints of articulation unit due to elastic forces. As a result, damage of leaf spring is excluded at autonomous opening of swivel structural members at high rotational speeds.
EFFECT: avoidance of backlash in joints of articulation unit.
FIELD: delivery of gaseous oxygen to spacecraft.
SUBSTANCE: proposed system includes high-pressure bottle and delivery main provided with starting valve, gas reducer, filters-current dischargers and adjusting valve. Filters-current dischargers mounted after starting valve and gas reducer are made in form of screen manufactured from corrosion-resistant metal at low specific resistance. Adjusting valve ensures required rate of oxygen flow through atomizing nozzle fitted at end of delivery main and communicated with consumer.
EFFECT: avoidance of formation of static electricity in oxygen layers; avoidance of fire danger.
FIELD: rocketry and space engineering; designing artificial satellites.
SUBSTANCE: proposed spacecraft has modules where service equipment is arranged and modules where target equipment and command and measuring devices are located. Optical devices of target equipment of infra-red range with cooled elements are mounted in central module. Radio equipment of on-board repeater is arranged in side modules whose position is changeable relative to position of central module. Optical and command and measuring devices are mounted on one frame at reduced coefficient of linear thermal expansion; they are combined with central module through three articulated supports. Cooled elements of optical devices are connected with radiators located beyond zone of thermal effect; service equipment module is provided with solar batteries having low dynamic effect on accuracy of spacecraft stabilization. Besides that, this module is provided with plasma engine whose working medium excludes contamination of said optical devices.
EFFECT: enhanced accuracy of spacecraft stabilization; electromagnetic compatibility of systems.
FIELD: spacecraft equipment; control of rotation parameters of rotator with experimental objects and measurement of mass of these objects.
SUBSTANCE: proposed device has body with grooves (10a, 10b) and rotating shaft (30) whose both ends are fitted in bearings (11, 12) of grooves (10a, 10b). Lower end of shaft (30) is connected with engine (13). Four arms (24-27) are mounted horizontally and are secured on shaft (30) at one end; experimental boxes (20-23) are fitted on other ends. Objects of constant or increasing weight, such as plants or animals and human being are placed in boxes (20-23) where artificial micro-gravitation is formed by rotation for conducting experiments or work in space. Vibration of shaft (30) and boxes (20-23) is absorbed by bearings (11,12). Provision may be also made for special-purpose vibration generator. Side plates (1a-1d), acceleration sensors (2a-2d) and sensors (3a-3d) showing the distance between objects and plates are mounted in boxes (20-23). Mass of object is determined by means of computer unit on basis of signals received from sensors (2,3) at collision of object with side plate. These and similar signals from additional sensors are used for control of said vibration generator and motion of counter-weights (not shown) for elimination of unbalance of rotator and suppression of vibrations.
EFFECT: enhanced efficiency; simplified procedure.
42 cl, 64 dwg
FIELD: space orbital stations.
SUBSTANCE: proposed system contacts autonomous subsystems located on cargo spacecraft and on space orbital station and including containers for liquid products with pipelines and valves. Container for liquid products of autonomous subsystem arranged on cargo spacecraft is made in form of bag of soft elastic cloth placed in rigid envelope and connected by flexible pipeline through hydraulic connector with change-over valve or through hydraulic connector with change-over valve and pump to similar container of other autonomous subsystem located on space orbital station. Space formed between bag and rigid envelope of autonomous subsystem located on cargo spacecraft communicates through valve with atmosphere of cargo spacecraft. Similar of container of autonomous subsystem located on space orbital station communicates through valve with atmosphere of space orbital station. Space orbital station is furnished with liquid wastes collecting system containing reservoir to be filled with liquid wastes in which space of bag is connected to semiconnector by means of flexible pipeline. Space formed between bag and rigid envelope communicates with atmosphere of space orbital station though valve or through valve and compressor. Invention makes it possible to create liquid products replenishment system providing utilization of liquid wastes from reservoir of autonomous subsystem at space orbital station by increasing efficiency of use of water container of autonomous subsystem of cargo spacecraft.
EFFECT: provision f utilization of liquid wastes.
3 cl, 2 dwg
FIELD: reduction of vortices behind aircraft.
SUBSTANCE: aircraft has starboard and port wings for forming lifting force; wings are provided with landing flaps for forming considerable lifting force. Vortex generator for forming controllable disturbance vortex is made in form of additional flap whose base is located in area of 10-% semispan to the right and to the left from external end of landing flap and beginning at 60% of depth of lifting wing profile. During flight, additional flap is kept in extended position; it may be retracted in wing when not in use. Controllable vortex is formed with this device.
EFFECT: reduction of vortices behind aircraft at landing approach.
15 cl, 9 dwg
SUBSTANCE: device comprises vortex pipe with a scroll for supplying and accelerating air and cold and hot end sections. The cold end section of the vortex pipe is provided with a ring plate. The diameter of the inner opening in the plate should be chosen to allow it to be fit on the vortex pipe with interference for increasing the area of the face of the cold section. The vortex pipe can be mounted in the guiding member which defines the inclination of the vector of the propulsion to the horizon. The hot section of the vortex pipe should be provided with a valve.
EFFECT: improved design.
3 cl, 2 dwg