Aircraft stabilisation not otherwise provided for (B64C17)

B64C17                 Aircraft stabilisation not otherwise provided for(54)
Tethered balloon with the autogyro screw stabiliser // 2628545
FIELD: aviation.SUBSTANCE: tethered balloon has a body of the soft design, rigging, rope tether unit and tail assembly. The lateral stabilisers of the tail assembly are formed by the autogyro screw, the axis of rotation of which is fixed at the top of the vertical stabiliser at the constant angle to the construction horizon.EFFECT: design simplification and take-off weight reduction.2 cl, 1 dwg
Tethered balloon with an autogyro screw in the cable lashing node // 2622314
FIELD: aviation.SUBSTANCE: tethered balloon has a body with a soft design, rigging, cable leashing node and tail unit. The cable leashing node has a suspended autogyro screw rotation axis of which is fixedly mounted relative to the body of the balloon at an angle which provides getting a disk area incidence angle relative to the oncoming air flow.EFFECT: increased balloon bed height on a dynamic ceiling.2 cl, 1 dwg

ethod of air pressure receivers management // 2615813
FIELD: aviation.SUBSTANCE: to control air pressure receivers (APR) troubleshoot APR by measuring the total and static pressures of the primary and backup APR define modules of the difference of total and static pressures, respectively, for the primary and backup APR, compare them with a predetermined threshold and outputs a signal to the pilot alerts failure when thresholds are exceeded.EFFECT: safety by reducing the detection time point of APR failure.1 dwg

Aircraft wing // 2580386
FIELD: aviation.SUBSTANCE: aircraft wing comprises carcass, skin, top and bottom airfoils and elements to deflect air flows attached to fuselage. Wing tip is equipped with hollow rotating on central axis disk with rim fixed on holder, convex top and flat bottom aerodynamic surfaces. Disc holder is arranged across relative to fuselage axial line and is fixed in frame to turn. Central axis is equipped with motor, made in form of a crosspiece with cups at ends, located on top and/or bottom of disc. Disc holder is equipped with brake catching its rotation.EFFECT: increased stability of aircraft in flight.3 cl, 6 dwg

Aircraft wing // 2576845
FIELD: aviation.SUBSTANCE: aircraft wing comprises attached to fuselage carcass, skin, top and bottom aerodynamic surfaces, airflow deflectors. Wing tip is equipped with hollow disk rotating on the central axis and equipped with rim, convex top and flat bottom aerodynamic surfaces. Disc holder is fixed to the carcass along the fuselage axial line. Between the end part of the wing and disc there is semi-annular slot arranged. Said holder is composed from top and bottom ribs with the flange for drive revolution.EFFECT: higher lifting capacity and in-flight stability of aircraft.3 cl, 3 dwg

Body for disc-flyer // 2576217
FIELD: aeronautics.SUBSTANCE: this invention relates to aeronautic simulation apparatus. Housing of disc-flyer containing rigid lighter than air gas-filled envelope having a shape of round biconvex lens to the shell around its circumference on holders attached at least one rigid ring disposed in the cavity stimulus thrust in one direction, wherein the ring cavity is filled with air. Driving force in the thrust ring mounted in the same chamber, equidistant from one another. Inner ring of its radius is made linear perforation.EFFECT: invention increases the stability of the housing when moving disc-flyer in air.3 cl, 4 dwg

Wide-body aircraft wing (versions) // 2568627
FIELD: aircraft engineering.SUBSTANCE: claimed wing comprises the carcass, skin, top and bottom airfoils, airflow deflectors and turbojet/jet engine. In compliance with the first version, carcass has the round through hole provided with hollow disc running on disc exposed to incident airflow and having the rim, convexed top airfoil and flat bottom airfoil. Annular slot is arranged between said disc and the carcass. Disc holder is fixed to the carcass along the fuselage axial line. Said holder is composed of top and bottom ribs with the flange for drive revolution. In compliance with the second version, the round through opening for yaw rudder shaft fitted from the side of bottom airfoil. Said yaw rudder is arranged from the side of the bottom/top airfoils.EFFECT: higher lift and in-flight stability.2 cl, 5 dwg

Airborne vehicle // 2548444
FIELD: aircraft engineering.SUBSTANCE: miniature remote-control aircraft comprises airfoil (17), two screw propellers (12, 13) and weight (20), its position being varied to vary the centre of gravity of miniature aircraft (10). Airfoil (17) is located above the plane defined by rotational axes of screw propellers (12, 13) to develop the lift. Airfoil (17) is composed of a top airfoil (17) arranged above bottom airfoil (18). This miniature aircraft represents a flying wing design. Aircraft in-flight position with respect to lengthwise axis (25) and/or aircraft (10) vertical axis (11) can be adjusted by the difference in propulsion, preferably between rpm of screw propellers (12, 13). If used as a reconnaissance plane it can be equipped with monitoring means.EFFECT: compact and durable structure with perfected flight characteristics.11 cl, 3 dwg

Airborne vehicle // 2544036
FIELD: aircraft engineering.SUBSTANCE: aircraft comprises fuselage, control cabin, delta wing, tail plane, engines arranged above said wing and undercarriage. Head parts of the wing and fuselage are connected by hollow prop equipped with rudder arranged between said wing and fuselage. Wig head section hangs over control cabin. Outer wing is arranged above fuselage to retain rear landing gear. Cavities accommodating flywheels running in opposite directions are made in the wing on both sides from central line.EFFECT: higher lift, mobility and stability.2 cl, 3 dwg

Onboard fuel gage-and-fuel flow rate meter system with compensation for temperature and fuel dielectric constant // 2533950
FIELD: instrumentation.SUBSTANCE: invention relates to aircraft instrumentation and can be used for ground aircraft fuelling control, measurement of aircraft in-flight fuel store, control over transverse aircraft fuel balance and generation of signal of fuel reserved residue. Proposed system comprises fuel parameter pickups arranged inside aircraft fuel tanks. These include level, temperature and dielectric constant pickups and fuel bottom level indicators. Besides, this system includes computer with LH and RH control module, control channels and memory cell related with fuel tank geometry, LH and RH modules of fuel meter and balancing device. Control board incorporates fuel density setter, fuelling control device and indicator. Fuel dielectric constant pickups are arranged level with fuel bottom level indicator. Onboard system computer has inputs to receive extra data from fuel flow rate pickups and aircraft bank and pitch transducers. Fuel data generated by fuel parameter transducers is fed to onboard computer control modules via fuel meter modules. Said data is set by control board. Onboard computer computes fuel flow rate magnitudes in every tank in aircraft on the whole as well as fuel amount different magnitudes in tanks located in symmetry of aircraft both sides.EFFECT: higher accuracy and reliability under standard and emergent operating conditions.1 dwg

Onboard system for fuel control and measurement with compensation for fuel temperature // 2532978
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. System onboard computer is provided with input to receive extra data from aircraft undercarriage indicator.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel temperature // 2532975
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. System onboard computer incorporates inputs to receive extra data from aircraft roll and pitch transducers.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel temperature // 2532974
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft roll and pitch transducers.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel dielectric constant // 2532970
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. Besides it includes control board with fuel density master, fuelling device and indicator. Note here that dielectric constant transducers are arranged level with fuel upper level indicators. System onboard computer incorporates inputs to receive extra data from aircraft roll and pitch transducers.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel dielectric constant // 2532969
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. Besides it includes control board with fuel density master, fuelling device and indicator. Note here that dielectric constant transducers are arranged level with fuel upper level indicators. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft undercarriage position indicator.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard fuel control system with compensation for fuel dielectric constant // 2532968
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. Note here that dielectric constant transducers are arranged level with fuel upper level indicators. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft roll and pitch transducers.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard fuel metering system with compensation for dielectric constant // 2532967
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. Besides it includes control board with fuel density master, fuelling device and indicator. Note here that dielectric constant transducers are arranged level with fuel upper level indicators. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft roll and pitch transducers.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control with compensation for fuel temperature // 2532966
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. System onboard computer incorporates inputs to receive extra data from aircraft roll and pitch transducers.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard fuel metering system with compensation for dielectric constant // 2532965
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. Note here that dielectric constant transducers are arranged level with fuel upper level indicators. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft undercarriage position indicator.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel dielectric constant // 2532964
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. Besides it includes control board with fuel density master, fuelling device and indicator. Note here that dielectric constant transducers are arranged level with fuel upper level indicators. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft roll and pitch transducers.EFFECT: higher efficiency and reliability at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel dielectric constant // 2532963
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. Besides it includes control board with fuel density master, fuelling device and indicator. Note here that dielectric constant transducers are arranged level with fuel upper level indicators. System onboard computer is provided with input to receive extra data from aircraft undercarriage indicator.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard fuel metering system with compensation for fuel temperature // 2532962
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft undercarriage position indicator.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel temperature // 2532946
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. System onboard computer is provided with input to receive extra data from aircraft undercarriage indicator.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel temperature // 2532943
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft roll and pitch transducers.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

Onboard system for fuel control and measurement with compensation for fuel temperature // 2532940
FIELD: aircraft engineering.SUBSTANCE: this system comprises fuel parameter transducers fitted in aircraft fuel tanks: Fuel level and dielectric constant, fuel upper and lower level indicators, onboard computer with left and right control modules, control channels and memory cells on fuel tank geometry, left and right fuel age modules, comparator and balance adjuster. System onboard computer incorporates inputs to receive extra data from fuel flow rate transducers and aircraft undercarriage position indicator.EFFECT: higher accuracy, validity and efficiency of measurement fuel mass store, fuel reserve supply and control over aircraft balance at standard and emergent conditions of system operation.1 dwg

ethod of using gyroscopic moment for aircraft (vehicle) control and aircraft control device // 2495789
FIELD: transport.SUBSTANCE: invention relates to stabilisation and orientation devices and can be used in engineering of gyros. Aircraft (vehicle) control device comprises case, central axle with bards, gyros with systems of attachment to bars. Said attachment system comprises frame, frame attachment, inclination and rotation system and gyro holder. Said case and central axle are secured via the system of extra moment.EFFECT: decreased weight, no need in gyro resetting.2 cl, 5 dwg

System and method of fuel transfer // 2482998
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering, particularly, to system intended for control over fuel transfer between aircraft fuel tanks. Proposed system comprises some fuel tanks 10, 12, fuel transducer 14 intended for measuring fuel amount if first fuel tank 10 data processor 16 to receive measurements results from said transducer. Said processor can define fuel amount variation rate for first fuel tank on the basis of received fuel amount measurement results in response to instruction on transfer fuel from first fuel tank into one or several other fuel tanks 12. In case fuel amount variation rate is lower than preset threshold while obtained fuel amount measurement result exceeds the expected value output signal is generated to indicate the fuel transfer fault.EFFECT: higher reliability of fuel transfer system and flight safety.14 cl, 3 dwg

ethod of adjusting aircraft center of gravity // 2482023
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering, particularly, to system intended for control over fuel transfer between aircraft fuel tanks. Proposed system includes fuel transfer between aircraft fuel tanks in compliance with preset order dependent upon decrease in aircraft full airborne weight caused by in-flight fuel consumption. Said preset order ensures keeping the aircraft center of gravity in preset range.EFFECT: higher reliability of fuel transfer system and flight safety.12 cl, 2 dwg

Test equipment for testing aircraft additional center tank system // 2452668
FIELD: physics.SUBSTANCE: invention relates to test equipment for testing aircraft additional centre tank (ACT) system. The test equipment comprises at least one of the following test modules: a first test module and a second test module. The first test module can be connected to the ACT system in place of part of control apparatus which performs an auxiliary fuel management computer (AFMC) function. The first test module has apparatus for generating one or more test signals imitating one or more ACT valve control instructions. The second test module can be connected to the ACT system in place of the control apparatus which performs an auxiliary level sensing control unit (ALSCU) function, while the other part of the control apparatus which performs the AFMC function remains in place in the ACT system. The second test module has apparatus for generating one or more test signals imitating one or more fuel level readings in the ACT.EFFECT: high efficiency of testing characteristics of an aircraft ACT system.15 cl, 3 dwg

ethod of equalising fuel capacity in aircraft wing tanks in operation on surface // 2438928
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering, particularly, to method of equalising fuel capacity in aircraft wing tanks. Proposed method consists in that equalising is performed by pumping fuel from aircraft central tank into wing tank with smaller fuel capacity. Note here that with no fuel in central fuel tank, fuel is pumped over from LH wing tank into RH wing tank using fuel priming and centralised drain line of aircraft fuel system, cross feed valve, RH wing tank priming valve and pump to feed fuel to LH engine. Pump to feed fuel to LH engine in LH wing tank is actuated along with centralised fuel drain valve by communicating line of feeding fuel to LH engine with fuel priming and centralised drain line. Then, with closed LH valve, valve to prime RH wing tank is moved to OPEN position to pump fuel over from LH to HT wing tank unless misbalance signal disappears. With no fuel in central fuel tank, fuel is pumped over from RH wing tank into LH wing tank in a similar way.EFFECT: ruling out unbalance between left and right wing fuel tanks.4 cl, 1 dwg

ethod of fuel reserve balancing in airplane wing tanks during ground operations (versions) // 2435706
FIELD: transportation.SUBSTANCE: invention refers to aviation, particularly to method of fuel reserve balancing in airplane wing tanks. Method involves balancing by fuel transfer first from central tank and then from the wing tank where fuel amount is larger to the wing tank where fuel amount is less. For that purpose, pump of fuel feed from right wing tank with less fuel to right motor is activated, with fuel feed valves of motors and cross-feed valve in closed position. Fuel is forwarded to active fuel mainline of fuel transfer jet pump from central tank to consumption tank of right wing tank, then fuel is transferred to the right wing tank in amount required to restore balance. Afterwards, if fuel volume in central tank is insufficient to restore balance and fuel is available in wing tanks, fuel is transferred from the left wing tank in ample amount to the right wing tank with smaller fuel reserve. For that purpose, left motor fueling pump is activated in the left wing tank with larger fuel reserve, centralised fuel drain valve is opened, thus connecting left motor fuel feed line with fueling and centralised drain line, with wing tank fueling valves closed. Then right wing tank fueling valve is opened, and fuel is transferred from left to right wing tank until imbalance signal disappears. Fuel transfer from right wing tank with larger fuel reserve to left wing tank with smaller fuel reserve is implemented in the same way.EFFECT: prevention of transverse imbalance between left and right wing tanks.4 cl, 1 dwg

ethod of equalising fuel capacity in aircraft wing tanks in operation on surface // 2435705
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering, particularly, to method of equalising fuel capacity in aircraft wing tanks. Proposed method consists in that equalising is performed by pumping fuel from aircraft central tank into wing tank with smaller fuel capacity. Note here that valves for feeding fuel to engines and cross valve stay in "shut-off" position to feed fuel from central tank via fuel transfer jet pump into wing tank sump compartment to feed therein an amount of fuel required for balancing fuel amount in both wing tanks.EFFECT: ruling out unbalance between left and right wing fuel tanks.2 cl, 1 dwg

ethod for balancing fuel reserve in aircraft wing tanks during ground operation (versions) // 2403179
FIELD: transport.SUBSTANCE: invention relates to the field of aviation, more specifically to a method for balancing fuel reserve in aircraft wing tanks during ground operation. The method consists in the following: balancing is executed via fuel pumping from the wing tank which contains more fuel to the central tank of an aircraft. In this process, to compensate a difference in fuel reserve between wing tanks the aircraft pump for fuel supply from left wing tank is switched on, centralised dump valve and central tank filling valve is opened, and fuel is fed under pressure to the central tank through central tank filling valve. Minor fuel part is returned from the central tank to the left wing tank by fuel jet pump.EFFECT: prevention of transverse imbalance between left and right wing tanks.4 cl, 1 dwg

Dirigible // 2385818
FIELD: transport.SUBSTANCE: invention refers to air navigation equipment. Dirigible includes a frame with the covering forming a cavity, ballonets with lighter-than-air gas, which are attached to the frame, stabiliser, propeller, crew compartment, passenger compartment and mooring device. In lower part of cavity there horizontally located are at least two rotors rotating in opposite directions. Rotors can be installed across the axis and lie in one and the same plane. Also rotors can be installed along the axis or one above the other.EFFECT: increase of flight stability.4 cl, 5 dwg

The method of determining the position of the center of mass of the helicopter // 2241637
The invention relates to the field of aviation technology and concerns a method for determining the position of the center of mass of the helicopter with bearing propellers mounted on the fuselage at different heights

The method of forming a gravitational device and gravitational device // 2223895
The invention relates to space technology, namely stabilizing devices designed to ensure the unambiguous orientation of the spacecraft

The control unit angular movement of the aircraft with fixed thrust // 2184053
The invention relates to techniques for aircraft control with fixed thrust under perturbations

The way the aircraft balance and management system development of fuel on the airplane // 2140377
The invention relates to fuel supply to the power plant in the part, which is associated with the pumping of fuel to ensure the balancing of the aircraft
The way to perform vertical take-off speed aircraft // 2121941
The invention relates to aviation and relates to a technology of performing vertical take-off speed aircraft

The generation of the control signals missile with a cruciform arrangement of wings // 2089452
The invention relates to the field of aviation, in particular to the stabilization systems of aircraft, and can be used in the autopilot guided missiles

Way down the accelerator of a space rocket in the landing zone and device for its implementation // 2043954
The invention relates to rocket and space technology and can be used to bring the exhaust accelerator first-stage space rocket "proton-M" in a limited area of impact to reduce the effect of ILV on the ecological state of the area of operation

The method of determining the position of the point of application of external forces helicopter // 2033941
The invention relates to an aircraft, and relates to a method of determining the position of the point of application of external forces helicopter
 
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